to 1-1-691
TRANSCRIPT
TO 1-1-691TECHNICAL MANUAL
CLEANING AND CORROSION PREVENTIONAND CONTROL,
AEROSPACE AND NON-AEROSPACE EQUIPMENT
F42620-00-D-0038FA8501-07-F-A080
This manual incorporates Interim Operational Supplement, TO 1-1-691 S-3, dated 29 October 2020.
DISTRIBUTION STATEMENT A - Approved for public release; distribution is unlimited. PA Case Number PA04-11-96. Other requests for thisdocument shall be referred to 406 SCMS/GUEE. Questions concerning technical content shall be referred to AFLCMC/EZPT-CPCO.
Published Under Authority of the Secretary of the Air Force
2 NOVEMBER 2009 CHANGE 18 - 22 FEBRUARY 2021
BASIC AND ALL UPDATES HAVE BEEN MERGED TO MAKE THIS A COMPLETE PUBLICATION.
Dates of issue for original and changed pages are:
Original. . . . . . . .0. . . .2 November 2009Change . . . . . . . . 1. . . . . . .12 April 2010Change . . . . . . . . 2 . . . . . . . 11 May 2011Change . . . . . . . . 3. . . . .15 January 2013Change . . . . . . . . 4. . . . . .14 March 2013Change . . . . . . . . 5 . . . . . . 5 August 2013Change . . . . . . . . 6 . . . . 17 February 2014Change . . . . . . . . 7 . . . . . . . 29 May 2014Change . . . . . . . . 8 . . . . . . . 11 July 2014Change . . . . . . . . 9 . . . . 4 December 2014
Change . . . . . . . 10. . . . .14 January 2015Change . . . . . . . 11 . . . . . . . . 2 July 2015Change . . . . . . . 12. . . . . .1 January 2016Change . . . . . . . 13 . . . . 20 February 2016Change . . . . . . . 14 . . . . . . . 13 July 2017Change . . . . . . . 15 . . . . . . . 30 June 2018Change . . . . . . . 16 . . .29 September 2018Change . . . . . . . 17. . . .8 November 2019Change . . . . . . . 18 . . . . 22 February 2021
TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 402, CONSISTING OF THE FOLLOWING:
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Title . . . . . . . . . . . . . . . . . . . . . 18A - B. . . . . . . . . . . . . . . . . . . . 18C Blank. . . . . . . . . . . . . . . . . . . .6i . . . . . . . . . . . . . . . . . . . . . . . . 17ii. . . . . . . . . . . . . . . . . . . . . . . .11iii - viii. . . . . . . . . . . . . . . . . . .16ix . . . . . . . . . . . . . . . . . . . . . . . 11x Blank . . . . . . . . . . . . . . . . . . . 11xi - xii . . . . . . . . . . . . . . . . . . . 17xiii - xiv . . . . . . . . . . . . . . . . . . 11xv. . . . . . . . . . . . . . . . . . . . . . .18xvi . . . . . . . . . . . . . . . . . . . . . . 17xvii Deleted . . . . . . . . . . . . . . . . 11xviii Deleted. . . . . . . . . . . . . . . .151-1 . . . . . . . . . . . . . . . . . . . . . . . 31-2 . . . . . . . . . . . . . . . . . . . . . . 142-1 - 2-7. . . . . . . . . . . . . . . . . . .02-8 . . . . . . . . . . . . . . . . . . . . . . . 22-9 - 2-11. . . . . . . . . . . . . . . . . .02-12 . . . . . . . . . . . . . . . . . . . . . 172-12.1 Added . . . . . . . . . . . . . . . 172-12.2 Blank. . . . . . . . . . . . . . . .172-13 - 2-20 . . . . . . . . . . . . . . . . . 03-1 . . . . . . . . . . . . . . . . . . . . . . . 33-2 . . . . . . . . . . . . . . . . . . . . . . 143-2.1 - 3-2.2 Deleted. . . . . . . . . .143-3 - 3-6. . . . . . . . . . . . . . . . . .143-7 - 3-8. . . . . . . . . . . . . . . . . .153-9 - 3-11. . . . . . . . . . . . . . . . . .53-12 . . . . . . . . . . . . . . . . . . . . . 183-13 . . . . . . . . . . . . . . . . . . . . . . 53-14 . . . . . . . . . . . . . . . . . . . . . . 03-15 . . . . . . . . . . . . . . . . . . . . . . 13-16 . . . . . . . . . . . . . . . . . . . . . . 03-17 - 3-19 . . . . . . . . . . . . . . . . . 53-20 . . . . . . . . . . . . . . . . . . . . . . 23-21 - 3-24 . . . . . . . . . . . . . . . . . 5
3-25 - 3-28 . . . . . . . . . . . . . . . . . 03-29 . . . . . . . . . . . . . . . . . . . . . 103-30 - 3-36 . . . . . . . . . . . . . . . . . 03-37 . . . . . . . . . . . . . . . . . . . . . . 53-38 . . . . . . . . . . . . . . . . . . . . . . 63-39 . . . . . . . . . . . . . . . . . . . . . 153-40 . . . . . . . . . . . . . . . . . . . . . . 53-41 . . . . . . . . . . . . . . . . . . . . . . 03-42 - 3-43 . . . . . . . . . . . . . . . . . 53-44 - 3-45 . . . . . . . . . . . . . . . . . 03-46 - 3-48 . . . . . . . . . . . . . . . . 133-48.1 - 3-48.2 Added. . . . . . . . . .23-49 . . . . . . . . . . . . . . . . . . . . . . 63-50 . . . . . . . . . . . . . . . . . . . . . . 03-51 . . . . . . . . . . . . . . . . . . . . . . 53-52 - 3-53 . . . . . . . . . . . . . . . . . 03-54 - 3-55 . . . . . . . . . . . . . . . . . 53-56 - 3-57 . . . . . . . . . . . . . . . . . 03-58 - 3-59 . . . . . . . . . . . . . . . . 103-60 - 3-63 . . . . . . . . . . . . . . . . . 53-64 . . . . . . . . . . . . . . . . . . . . . . 04-1 . . . . . . . . . . . . . . . . . . . . . . . 34-2 . . . . . . . . . . . . . . . . . . . . . . . 04-3 - 4-4. . . . . . . . . . . . . . . . . . .74-4.1 Added . . . . . . . . . . . . . . . . .74-4.2 Blank . . . . . . . . . . . . . . . . . 74-5 - 4-14. . . . . . . . . . . . . . . . . .04-15 . . . . . . . . . . . . . . . . . . . . . 104-16 - 4-18 . . . . . . . . . . . . . . . . . 05-1 - 5-11. . . . . . . . . . . . . . . . . .05-12 . . . . . . . . . . . . . . . . . . . . . . 55-13 - 5-15 . . . . . . . . . . . . . . . . . 05-16 . . . . . . . . . . . . . . . . . . . . . 135-17 - 5-26 . . . . . . . . . . . . . . . . . 05-27 . . . . . . . . . . . . . . . . . . . . . . 55-28 . . . . . . . . . . . . . . . . . . . . . . 35-29 . . . . . . . . . . . . . . . . . . . . . . 0
5-30 . . . . . . . . . . . . . . . . . . . . . . 35-31 - 5-39 . . . . . . . . . . . . . . . . . 05-40 - 5-41 . . . . . . . . . . . . . . . . 155-42 - 5-46 . . . . . . . . . . . . . . . . 165-46.1 Added . . . . . . . . . . . . . . . . 55-46.2 Blank . . . . . . . . . . . . . . . . 55-47 - 5-50 . . . . . . . . . . . . . . . . . 35-51 . . . . . . . . . . . . . . . . . . . . . 165-52 Added . . . . . . . . . . . . . . . . . 35-53 Added . . . . . . . . . . . . . . . . 165-54 Blank. . . . . . . . . . . . . . . . .166-1 . . . . . . . . . . . . . . . . . . . . . . . 06-2 . . . . . . . . . . . . . . . . . . . . . . . 56-3 . . . . . . . . . . . . . . . . . . . . . . 156-4 - 6-5. . . . . . . . . . . . . . . . . . .26-6 - 6-31. . . . . . . . . . . . . . . . . .06-32 . . . . . . . . . . . . . . . . . . . . . . 26-33 - 6-36 . . . . . . . . . . . . . . . . . 07-1 - 7-2. . . . . . . . . . . . . . . . . . .07-3 . . . . . . . . . . . . . . . . . . . . . . . 57-4 - 7-6. . . . . . . . . . . . . . . . . . .07-7 . . . . . . . . . . . . . . . . . . . . . . 107-8 - 7-10. . . . . . . . . . . . . . . . . .57-11 - 7-13 . . . . . . . . . . . . . . . . . 07-14 . . . . . . . . . . . . . . . . . . . . . . 57-15 - 7-19 . . . . . . . . . . . . . . . . . 07-20 Blank. . . . . . . . . . . . . . . . . .08-1 - 8-2. . . . . . . . . . . . . . . . . . .98-2.1 . . . . . . . . . . . . . . . . . . . . . 158-2.2 Blank . . . . . . . . . . . . . . . . . 98-3 - 8-5. . . . . . . . . . . . . . . . . . .08-6 . . . . . . . . . . . . . . . . . . . . . . . 38-7 . . . . . . . . . . . . . . . . . . . . . . . 58-8 . . . . . . . . . . . . . . . . . . . . . . . 08-9 . . . . . . . . . . . . . . . . . . . . . . 158-10 . . . . . . . . . . . . . . . . . . . . . . 18-11 . . . . . . . . . . . . . . . . . . . . . 12
TO 1-1-691
LIST OF EFFECTIVE PAGESINSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES.
NOTE The portion of the text affected by the changes is indicated by a vertical line in the outer margins ofthe page. Changes to illustrations are indicated by shaded or screened areas, or by miniaturepointing hands.
* Zero in this column indicates an original page.
A Change 18 USAF
8-12 - 8-13 . . . . . . . . . . . . . . . . . 38-14 . . . . . . . . . . . . . . . . . . . . . . 58-14.1 Added . . . . . . . . . . . . . . . . 38-14.2 Blank . . . . . . . . . . . . . . . . 38-15 . . . . . . . . . . . . . . . . . . . . . . 18-16 . . . . . . . . . . . . . . . . . . . . . . 58-16.1 Added . . . . . . . . . . . . . . . . 18-16.2 Blank . . . . . . . . . . . . . . . . 18-17 . . . . . . . . . . . . . . . . . . . . . . 08-18 Blank. . . . . . . . . . . . . . . . . .09-1 - 9-3. . . . . . . . . . . . . . . . . .149-4 Blank . . . . . . . . . . . . . . . . . . 010-1 Added . . . . . . . . . . . . . . . . . 410-2 . . . . . . . . . . . . . . . . . . . . . . 510-3 Added . . . . . . . . . . . . . . . . . 410-4 Blank. . . . . . . . . . . . . . . . . .4A-1. . . . . . . . . . . . . . . . . . . . . .15A-2 - A-9. . . . . . . . . . . . . . . . . .0A-10. . . . . . . . . . . . . . . . . . . . . .5A-11 - A-12 . . . . . . . . . . . . . . . . 0A-13 - A-14 . . . . . . . . . . . . . . . 18A-14.1 Added. . . . . . . . . . . . . . .18A-14.2 Blank . . . . . . . . . . . . . . . 18A-15 . . . . . . . . . . . . . . . . . . . . . 14A-16 - A-19 . . . . . . . . . . . . . . . . 0A-20 - A-21 . . . . . . . . . . . . . . . 10A-22 - A-54 . . . . . . . . . . . . . . . . 0A-55 - A-57 . . . . . . . . . . . . . . . . 5A-58 Blank . . . . . . . . . . . . . . . . . 0B-1 . . . . . . . . . . . . . . . . . . . . . . 15B-2 - B-18 . . . . . . . . . . . . . . . . . 0B-19 . . . . . . . . . . . . . . . . . . . . . . 2B-20 . . . . . . . . . . . . . . . . . . . . . 18B-20.1. . . . . . . . . . . . . . . . . . . .18B-20.2 Blank . . . . . . . . . . . . . . . . 2B-21 - B-27 . . . . . . . . . . . . . . . . 0B-28 - B-30 . . . . . . . . . . . . . . . . 8B-30.1 - B-30.3 Added . . . . . . . . . 8B-30.4 Blank . . . . . . . . . . . . . . . . 8B-31 - B-41 . . . . . . . . . . . . . . . . 0B-42 . . . . . . . . . . . . . . . . . . . . . . 2B-43 . . . . . . . . . . . . . . . . . . . . . 15B-44 - B-45 . . . . . . . . . . . . . . . . 0B-46 Blank . . . . . . . . . . . . . . . . . 0Glossary 1 - Glossary 4 . . . . . . . . 0Index 1 . . . . . . . . . . . . . . . . . . . 18Index 2 - Index 4. . . . . . . . . . . .17Index 4.1 Added . . . . . . . . . . . . . . 9Index 4.2 Blank . . . . . . . . . . . . . . 9Index 5 - Index 7. . . . . . . . . . . .17Index 8 . . . . . . . . . . . . . . . . . . . 18Index 8.1 - Index 8.2 Deleted . . . . 5Index 9 . . . . . . . . . . . . . . . . . . . 17
Index 10 Blank. . . . . . . . . . . . . .17Index 11 - Index 14 Deleted . . . . . 5
TO 1-1-691
LIST OF EFFECTIVE PAGES - continued
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* Zero in this column indicates an original page.
Change 18 B/(C blank)
TABLE OF CONTENTS
Chapter Page
LIST OF ILLUSTRATIONS . . . . . . . . . . . . . vii
LIST OF TABLES . . . . . . . . . . . . . . . . . . . . viii
INTRODUCTION . . . . . . . . . . . . . . . . . . . . xi
SAFETY SUMMARY . . . . . . . . . . . . . . . . . 0
1 INTRODUCTION . . . . . . . . . . . . . . . . . . . 1-1
1.1 CORROSION CONTROLPROGRAM. . . . . . . . . . . . . . . 1-1
1.1.1 Training . . . . . . . . . . . . . . . . . . . 1-11.1.2 Maintenance . . . . . . . . . . . . . . . . 1-11.1.3 Facilities . . . . . . . . . . . . . . . . . . . 1-11.2 SAFETY. . . . . . . . . . . . . . . . . . . 1-11.2.1 Responsibility of Supervisors . . . . . 1-11.2.2 Materials Handling . . . . . . . . . . . . 1-11.3 MATERIALS . . . . . . . . . . . . . . . 1-2
2 CORROSION THEORY . . . . . . . . . . . . . . . 2-1
2.1 INTRODUCTION TO CORRO-SION THEORY . . . . . . . . . . . . 2-1
2.2 DEFINITION OFCORROSION . . . . . . . . . . . . . 2-1
2.3 CHEMICAL DEFINITIONS . . . . . 2-12.3.1 Atom . . . . . . . . . . . . . . . . . . . . . 2-12.3.2 Electron . . . . . . . . . . . . . . . . . . . 2-12.3.3 Ions . . . . . . . . . . . . . . . . . . . . . . 2-12.3.4 Electrolyte. . . . . . . . . . . . . . . . . . 2-12.4 THEORY OF CORROSION . . . . . 2-12.4.1 Anode . . . . . . . . . . . . . . . . . . . . 2-12.4.2 Cathode . . . . . . . . . . . . . . . . . . . 2-12.4.3 Electrolyte. . . . . . . . . . . . . . . . . . 2-12.4.4 Electrical Contact . . . . . . . . . . . . . 2-12.5 DEVELOPMENT OF
CORROSION . . . . . . . . . . . . . 2-22.5.1 Corrosion Under Painted
Surfaces . . . . . . . . . . . . . . . . . 2-22.6 FACTORS INFLUENCE
CORROSION . . . . . . . . . . . . . 2-22.6.1 Type of Metal . . . . . . . . . . . . . . . 2-22.6.2 Dissimilar Metal Coupling (Galvanic
Corrosion). . . . . . . . . . . . . . . . 2-22.6.3 Anode and Cathode Surface
Area. . . . . . . . . . . . . . . . . . . . 2-32.6.4 Temperature . . . . . . . . . . . . . . . . 2-42.6.5 Heat Treatment and Grain
Direction. . . . . . . . . . . . . . . . . 2-42.6.6 Electrolytes . . . . . . . . . . . . . . . . . 2-42.6.7 Oxygen. . . . . . . . . . . . . . . . . . . . 2-52.6.8 Electrolyte Concentration. . . . . . . . 2-5
Chapter Page
2.6.9 Biological Organisms . . . . . . . . . . 2-52.6.10 Mechanical Stress. . . . . . . . . . . . . 2-52.6.11 Time . . . . . . . . . . . . . . . . . . . . . 2-52.7 TYPES OF CORROSION . . . . . . . 2-52.7.1 Uniform Surface Corrosion . . . . . . 2-52.7.2 Galvanic Corrosion. . . . . . . . . . . . 2-52.7.3 Pitting Corrosion . . . . . . . . . . . . . 2-62.7.4 Intergranular Corrosion . . . . . . . . . 2-62.7.5 Exfoliation Corrosion . . . . . . . . . . 2-62.7.6 Crevice/Concentration Cell
Corrosion . . . . . . . . . . . . . . . . 2-62.7.7 Corrosion Fatigue. . . . . . . . . . . . . 2-82.7.8 Filiform Corrosion . . . . . . . . . . . . 2-82.7.9 Fretting Corrosion . . . . . . . . . . . . 2-102.7.10 High Temperature Oxidation (Hot
Corrosion). . . . . . . . . . . . . . . . 2-112.8 METALS AFFECTED BY
CORROSION . . . . . . . . . . . . . 2-112.8.1 Magnesium . . . . . . . . . . . . . . . . . 2-112.8.2 Steel. . . . . . . . . . . . . . . . . . . . . . 2-122.8.3 Aluminum. . . . . . . . . . . . . . . . . . 2-122.8.4 Anodized Aluminum. . . . . . . . . . . 2-122.8.5 Titanium . . . . . . . . . . . . . . . . . . . 2-122.8.6 Copper and Copper Alloys. . . . . . . 2-132.8.7 Cadmium . . . . . . . . . . . . . . . . . . 2-162.8.8 CRES/Stainless Steel . . . . . . . . . . 2-162.8.9 Nickel and Chromium. . . . . . . . . . 2-162.8.10 Silver, Platinum, and Gold. . . . . . . 2-162.8.11 Graphite/Carbon Fiber
Composites . . . . . . . . . . . . . . . 2-162.9 CORROSIVE
ENVIRONMENTS. . . . . . . . . . 2-162.9.1 Moisture . . . . . . . . . . . . . . . . . . . 2-162.9.2 Temperature . . . . . . . . . . . . . . . . 2-172.9.3 Salt Atmospheres . . . . . . . . . . . . . 2-172.9.4 Ozone . . . . . . . . . . . . . . . . . . . . 2-172.9.5 Other Industrial Pollutants . . . . . . . 2-172.9.6 Sand, Dust, and Volcanic Ash. . . . . 2-182.9.7 Solar Radiation . . . . . . . . . . . . . . 2-182.9.8 Climate. . . . . . . . . . . . . . . . . . . . 2-182.9.9 Factors of Influence in Tropical
Environments . . . . . . . . . . . . . 2-182.9.10 Manufacturing . . . . . . . . . . . . . . . 2-192.9.11 Storage . . . . . . . . . . . . . . . . . . . . 2-192.9.12 Shipment . . . . . . . . . . . . . . . . . . 2-192.9.13 Industrial and Ship Emitted Air
Pollutants . . . . . . . . . . . . . . . . 2-192.9.14 Animal Damage . . . . . . . . . . . . . . 2-192.9.15 Microorganisms . . . . . . . . . . . . . . 2-192.10 DEGRADATION OF
NON-METALS . . . . . . . . . . . . 2-202.11 PREVENTIVE
MAINTENANCE. . . . . . . . . . . 2-20
TO 1-1-691
Change 17 i
Chapter Page
3 PREVENTIVE MAINTENANCE . . . . . . . . . 3-1
SECTION I INTRODUCTION. . . . . . . . . . . 3-1
3.1 PREVENTIVE MAINTENANCEPROGRAM. . . . . . . . . . . . . . . 3-1
3.1.1 Preventive Maintenance. . . . . . . . . 3-1
SECTION II CLEANING . . . . . . . . . . . . . . 3-6
3.2 INTRODUCTION . . . . . . . . . . . . 3-63.2.1 Reasons for Cleaning . . . . . . . . . . 3-63.2.2 When to Accomplish Work . . . . . . 3-73.2.3 Aircraft Clear Water Rinse (CWR)
Requirements. . . . . . . . . . . . . . 3-73.2.4 Immediate Cleaning . . . . . . . . . . . 3-83.2.5 Deployed Aircraft Wash
Requirements. . . . . . . . . . . . . . 3-83.3 CLEANING COMPOUNDS . . . . . 3-93.3.1 Alkaline Cleaners . . . . . . . . . . . . . 3-93.3.2 Solvent Emulsion and Aqueous
Cleaners for Turbine Engine GasPath and General AreaCleaning . . . . . . . . . . . . . . . . . 3-10
3.3.3 Aqueous Parts Washer CleaningSolutions. . . . . . . . . . . . . . . . . 3-10
3.3.4 Solvents . . . . . . . . . . . . . . . . . . . 3-113.3.5 Miscellaneous Cleaning Agents . . . 3-113.3.6 Steam Cleaning . . . . . . . . . . . . . . 3-123.3.7 Dilution . . . . . . . . . . . . . . . . . . . 3-123.4 CLEANING EQUIPMENT . . . . . . 3-293.4.1 High Pressure/Hot Water Wash
Equipment. . . . . . . . . . . . . . . . 3-293.4.2 Portable, 15 Gallon, Foam Generat-
ing, Cleaning Unit . . . . . . . . . . 3-293.4.3 Portable, 45 Gallon, Foam Generat-
ing Cleaning Unit. . . . . . . . . . . 3-323.4.4 Turbine Engine Compressor Clean-
ing Equipment . . . . . . . . . . . . . 3-333.4.5 Miscellaneous Large Cleaning
Equipment. . . . . . . . . . . . . . . . 3-333.4.6 Spray Cleaning Guns for
Solvents . . . . . . . . . . . . . . . . . 3-333.4.7 Pneumatic Vacuum Cleaner . . . . . . 3-333.4.8 Universal Wash Unit . . . . . . . . . . . 3-333.4.9 Aqueous Parts Washers . . . . . . . . . 3-343.4.10 Miscellaneous Equipment . . . . . . . 3-353.5 CLEANING PROCEDURES . . . . . 3-363.5.1 Warnings and Cautions . . . . . . . . . 3-363.5.2 Cleaning Methods . . . . . . . . . . . . 3-393.5.3 Clear Water Rinsing of Aircraft . . . 3-463.5.4 Post Cleaning Procedures . . . . . . . 3-463.5.5 Treatment and Disposal of Wash
Rack Waste . . . . . . . . . . . . . . . 3-473.5.6 Fungus Growth Removal . . . . . . . . 3-47
Chapter Page
3.5.7 Soil Barriers . . . . . . . . . . . . . . . . 3-48.23.5.8 Bird Strike Cleaning . . . . . . . . . . . 3-493.5.9 Bodily Fluids Contamination
Cleanup . . . . . . . . . . . . . . . . . 3-51
SECTION III LUBRICATION . . . . . . . . . . . 3-53
3.6 INTRODUCTION . . . . . . . . . . . . 3-533.6.1 Conventional Lubricants . . . . . . . . 3-533.6.2 Solid Film Lubricants . . . . . . . . . . 3-543.6.3 Application of Conventional
Lubricants . . . . . . . . . . . . . . . . 3-54
SECTION IV PRESERVATION . . . . . . . . . . 3-56
3.7 INTRODUCTION . . . . . . . . . . . . 3-563.7.1 Operational Preservation . . . . . . . . 3-563.7.2 Non-Operational Preservation. . . . . 3-563.7.3 Types of CPC’s . . . . . . . . . . . . . . 3-563.7.4 Time Limitations of CPC’s . . . . . . 3-573.7.5 Description of CPC’s . . . . . . . . . . 3-573.7.6 Preservation of Specific Areas . . . . 3-643.7.7 Preservation Application
Methods . . . . . . . . . . . . . . . . . 3-643.8 APPLICATION OF POLISH AND
WAX . . . . . . . . . . . . . . . . . . . 3-64
4 INSPECTION AND CORROSION PRONEAREAS. . . . . . . . . . . . . . . . . . . . . . . . . 4-1
SECTION I INSPECTION . . . . . . . . . . . . . 4-1
4.1 Purpose . . . . . . . . . . . . . . . . . . . 4-14.1.1 Responsibility . . . . . . . . . . . . . . . 4-14.1.2 Frequency of Inspections . . . . . . . . 4-14.1.3 General Inspections . . . . . . . . . . . 4-14.1.4 Detailed Inspections . . . . . . . . . . . 4-14.2 INSPECTION METHODS. . . . . . . 4-14.2.1 Visual inspection . . . . . . . . . . . . . 4-14.2.2 Depth Gauge . . . . . . . . . . . . . . . . 4-24.2.3 Visual Inspection with a
Borescope/Videoscope. . . . . . . . 4-34.2.4 Optical Depth Micrometers . . . . . . 4-34.2.5 Fluorescent Penetrant
Inspection . . . . . . . . . . . . . . . . 4-54.2.6 Eddy Current Inspection . . . . . . . . 4-64.2.7 Ultrasonic Inspection . . . . . . . . . . 4-64.2.8 Radiographic Inspection . . . . . . . . 4-64.3 EVALUATION OF CORROSION
DAMAGE. . . . . . . . . . . . . . . . 4-64.4 DEGREES OF CORROSION . . . . 4-64.4.1 Light Corrosion . . . . . . . . . . . . . . 4-94.4.2 Moderate Corrosion . . . . . . . . . . . 4-94.4.3 Severe Corrosion . . . . . . . . . . . . . 4-9
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SECTION II CORROSION PRONE AREAS . 4-9
4.5 COMMON AREAS . . . . . . . . . . . 4-94.5.1 Fasteners. . . . . . . . . . . . . . . . . . . 4-94.5.2 Faying Surfaces and Crevices. . . . . 4-94.5.3 Spot Welded Assemblies . . . . . . . . 4-94.5.4 Engine Exhaust and Gun Gas Im-
pingement Areas . . . . . . . . . . . 4-104.5.5 Wheel Wells and Landing Gear . . . 4-104.5.6 Flap and Slat Recesses . . . . . . . . . 4-114.5.7 Engine Frontal Areas and Air Inlet
Ducts . . . . . . . . . . . . . . . . . . . 4-114.5.8 Wing/Fin-Fold Joints and Wing and
Control Surface LeadingEdges . . . . . . . . . . . . . . . . . . . 4-14
4.5.9 Hinges . . . . . . . . . . . . . . . . . . . . 4-144.5.10 Control Cables. . . . . . . . . . . . . . . 4-144.5.11 Relief Tube Outlets. . . . . . . . . . . . 4-144.5.12 Water Entrapment Areas . . . . . . . . 4-144.5.13 Bilge Areas . . . . . . . . . . . . . . . . . 4-144.5.14 Battery Compartments and Battery
Vent Openings . . . . . . . . . . . . . 4-144.5.15 Magnesium Parts . . . . . . . . . . . . . 4-154.5.16 Electrical Connectors and Other
Components . . . . . . . . . . . . . . 4-15
4 CORROSION REMOVAL AND SURFACETREATMENT . . . . . . . . . . . . . . . . . . . . 4-0
SECTION I CORROSION REMOVAL . . . . . 5-1
5.1 PURPOSE. . . . . . . . . . . . . . . . . . 5-15.2 RESPONSIBILITY. . . . . . . . . . . . 5-15.3 CORRECTIVE ACTIONS. . . . . . . 5-15.4 PAINT REMOVAL. . . . . . . . . . . . 5-15.5 CORROSION REMOVAL. . . . . . . 5-15.5.1 Mechanical Methods . . . . . . . . . . . 5-25.5.2 Non-Powered Tools and
Materials. . . . . . . . . . . . . . . . . 5-25.5.3 Power Tools and Materials. . . . . . . 5-45.5.4 Abrasive Blasting . . . . . . . . . . . . . 5-75.6 SURFACE FINISH. . . . . . . . . . . . 5-115.7 PITTING ON CRITICAL
STRUCTURE . . . . . . . . . . . . . 5-115.8 CORROSION REMOVAL
PROCEDURES-MECHANICAL 5-115.8.1 Warnings and Cautions . . . . . . . . . 5-115.8.2 Non-Powered Mechanical Corrosion
Removal . . . . . . . . . . . . . . . . . 5-145.8.3 Powered Mechanical Corrosion
Removal . . . . . . . . . . . . . . . . . 5-155.8.4 Abrasive Blasting Corrosion
Removal . . . . . . . . . . . . . . . . . 5-155.9 CORROSION
REMOVAL-CHEMICAL. . . . . . 5-17
Chapter Page
5.9.1 Aluminum Alloys . . . . . . . . . . . . . 5-175.9.2 Magnesium Alloys . . . . . . . . . . . . 5-205.9.3 Ferrous Metal (Steel) Alloys Other
Than Stainless Steels(CRES). . . . . . . . . . . . . . . . . . 5-21
5.9.4 Stainless Steel (CRES) and NickelBased Alloys . . . . . . . . . . . . . . 5-26
5.9.5 Copper and Copper BasedAlloys . . . . . . . . . . . . . . . . . . 5-30
5.9.6 Titanium and Titanium BasedAlloys . . . . . . . . . . . . . . . . . . 5-32
5.9.7 Plated and Phosphated Surfaces . . . 5-33
SECTION II SURFACE TREATMENT . . . . . 5-36
5.10 PURPOSE. . . . . . . . . . . . . . . . . . 5-365.10.1 Chemical Prepaint Treatments . . . . 5-365.10.2 Surface Preparation. . . . . . . . . . . . 5-385.10.3 Precautions . . . . . . . . . . . . . . . . . 5-385.10.4 Application of Surface
Treatments . . . . . . . . . . . . . . . 5-395.10.5 Notes on Conversion Coating/Sur-
face Treatment . . . . . . . . . . . . . 5-405.10.6 Post Treatment. . . . . . . . . . . . . . . 5-405.10.7 Temporary Preservation. . . . . . . . . 5-41
SECTION III SHOT PEENING . . . . . . . . . . 5-42
5.11 REQUIREMENTS FOR SHOTPEENING. . . . . . . . . . . . . . . . 5-42
5.12 SHOT PEENING OF METALSURFACES. . . . . . . . . . . . . . . 5-42
5.12.1 Types of Peening . . . . . . . . . . . . . 5-425.12.2 Shot Peening Application. . . . . . . . 5-43
SECTION IV ROTO-PEENING. . . . . . . . . . 5-43
5.13 ROTO-PEENING (ROTARY FLAPPEENING) . . . . . . . . . . . . . . . 5-43
5.13.1 Roto-Peening Procedures . . . . . . . . 5-445.13.2 Determining Peening/Intensity . . . . 5-455.13.3 Peening Process Preparation. . . . . . 5-465.13.4 Post Peening Surface Finish . . . . . . 5-46
6 SEALANTS . . . . . . . . . . . . . . . . . . . . . . . 6-1
6.1 PURPOSE. . . . . . . . . . . . . . . . . . 6-16.2 APPLICATIONS . . . . . . . . . . . . . 6-16.3 SEALING COMPOUNDS. . . . . . . 6-16.3.1 Sealant Packaging . . . . . . . . . . . . 6-16.3.2 Polysulfide, Polyurethane, and Poly-
thioether SealingCompounds . . . . . . . . . . . . . . . 6-1
6.3.3 Silicone Sealing Compounds . . . . . 6-2
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6.3.4 Adhesion Promoters . . . . . . . . . . . 6-26.3.5 SAE AMS 3255 Oil and Water Re-
sistant, Expanded Polytetrafluoro-ethylene Sealing Tape (EPTFE)Skyflex . . . . . . . . . . . . . . . . . . 6-2
6.3.6 Av-Dec® Polyurethane SealantTapes and Two ComponentSealants . . . . . . . . . . . . . . . . . 6-2
6.4 EQUIPMENT . . . . . . . . . . . . . . . 6-26.4.1 Sealant Gun. . . . . . . . . . . . . . . . . 6-26.4.2 Application Nozzles . . . . . . . . . . . 6-36.4.3 Injection Gun . . . . . . . . . . . . . . . 6-36.4.4 Sealant Kits (Semkits®) . . . . . . . . 6-36.4.5 Sealant Removal and Application
Tools . . . . . . . . . . . . . . . . . . . 6-36.5 SEALANT MIXING. . . . . . . . . . . 6-36.5.1 Application Life. . . . . . . . . . . . . . 6-36.5.2 Storage Instructions . . . . . . . . . . . 6-46.5.3 Mixing MIL-PRF-81733, Type III
Sprayable Sealant Coating . . . . . 6-56.6 SEALANT APPLICATION
PROCEDURES . . . . . . . . . . . . 6-226.6.1 Cleaning . . . . . . . . . . . . . . . . . . . 6-226.6.2 Masking . . . . . . . . . . . . . . . . . . . 6-226.6.3 Adhesion Promoters . . . . . . . . . . . 6-256.6.4 Brush Spatula or Caulking Gun
Application . . . . . . . . . . . . . . . 6-256.6.5 Spray Gun Application . . . . . . . . . 6-266.6.6 Peel and Stick Application; SAE
AMS 3255 EPTFE Skyflex® andAv-Dec® HT3935-7 and HT3000Sealing Tapes . . . . . . . . . . . . . 6-26
6.7 SEALING OF SPECIFICAREAS . . . . . . . . . . . . . . . . . 6-27
6.7.1 Faying Surface Sealing . . . . . . . . . 6-276.7.2 Fillet Sealing . . . . . . . . . . . . . . . . 6-286.7.3 Injection Sealing . . . . . . . . . . . . . 6-286.7.4 Fastener Sealing. . . . . . . . . . . . . . 6-296.7.5 Integral Fuel Cells/Tanks and Re-
movable Fuel Tanks . . . . . . . . . 6-296.7.6 Form-In-Place (FIP) Gasket Sealant
Repair . . . . . . . . . . . . . . . . . . 6-296.7.7 SAE AMS 3255 EPTFE (Skyflex®)
and Av-Dec® HT3000 andHT3935-7 Sealing Tape GasketRepair . . . . . . . . . . . . . . . . . . 6-30
6.7.8 External Aircraft Structure . . . . . . . 6-316.7.9 Depressions . . . . . . . . . . . . . . . . . 6-316.7.10 Damaged Sealant . . . . . . . . . . . . . 6-316.7.11 Extensive Repair . . . . . . . . . . . . . 6-326.7.12 High Temperature Areas . . . . . . . . 6-326.7.13 Low Temperature Curing. . . . . . . . 6-326.8 STORAGE/SHELF LIFE CON-
TROL OF SEALANTS . . . . . . . 6-32
Chapter Page
7 TREATMENT OF SPECIFIC AREAS . . . . . . 7-1
7.1 INTRODUCTION . . . . . . . . . . . . 7-17.2 BATTERY COMPARTMENTS,
BOXES, AND ADJACENTAREAS . . . . . . . . . . . . . . . . . 7-1
7.2.1 Preparation of Solutions for Clean-ing and Neutralizing BatteryElectrolytes . . . . . . . . . . . . . . . 7-1
7.2.2 Cleaning and NeutralizingProcedures . . . . . . . . . . . . . . . 7-2
7.2.3 Paint Systems . . . . . . . . . . . . . . . 7-27.3 RELIEF TUBE AREAS . . . . . . . . 7-27.4 CORROSION TREATMENT FOR
STEEL CABLES . . . . . . . . . . . 7-37.5 PIANO TYPE HINGES . . . . . . . . 7-37.6 INTEGRAL AND EXTERNAL
FUEL TANKS AND DROPTANKS . . . . . . . . . . . . . . . . . 7-3
7.6.1 Corrosion Removal and Rework ofPitted Areas of Integral FuelTanks . . . . . . . . . . . . . . . . . . . 7-3
7.6.2 Removal of Corrosion and Reworkof Aluminum External FuelTanks/Drop Tanks. . . . . . . . . . . 7-4
7.7 FAYING SURFACES AND AT-TACHMENT POINTS . . . . . . . 7-5
7.7.1 Faying Surfaces, Joints, andSeams . . . . . . . . . . . . . . . . . . 7-5
7.7.2 Attaching Parts and Hardware . . . . 7-57.7.3 Severely Corroded (Rusted)
Hardware . . . . . . . . . . . . . . . . 7-67.8 NATURAL AND SYNTHETIC
RUBBER PARTS. . . . . . . . . . . 7-77.9 POTABLE WATER TANKS . . . . . 7-77.10 SURFACES AND COMPONENTS
EXPOSED TO EXHAUSTGASES, GUN GASES, ANDROCKET BLAST . . . . . . . . . . 7-7
7.11 ELECTRICAL AND ELECTRONICEQUIPMENT . . . . . . . . . . . . . 7-7
7.11.1 Grounding and BondingConnections. . . . . . . . . . . . . . . 7-7
7.11.2 Conduit and Junction Boxes. . . . . . 7-77.11.3 Wires and Cables . . . . . . . . . . . . . 7-77.11.4 Deleted. . . . . . . . . . . . . . . . . . . . 7-77.11.5 Moisture and Fungus Proofing of
Electrical and ElectronicEquipment. . . . . . . . . . . . . . . . 7-7
7.11.6 Antennas. . . . . . . . . . . . . . . . . . . 7-77.12 STRUCTURAL TUBING MEM-
BERS AND ASSEMBLIES . . . . 7-8
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7.12.1 Structural Aluminum AlloyTubing . . . . . . . . . . . . . . . . . . 7-8
7.12.2 Structural Magnesium AlloyTubing . . . . . . . . . . . . . . . . . . 7-8
7.12.3 Structural Copper Alloys, StainlessSteel (CRES) Alloys, and HeatResistant Alloy Tubing . . . . . . . 7-8
7.12.4 Structural Carbon Steel Tubing. . . . 7-87.13 NON-STRUCTURAL TUBING
MEMBERS ANDASSEMBLIES. . . . . . . . . . . . . 7-8
7.13.1 Aluminum Alloy Tubing . . . . . . . . 7-87.13.2 Stainless Steel (CRES) Tubing . . . . 7-97.13.3 Cadmium Plated Steel Tubing . . . . 7-107.13.4 Special Instructions for Tubing Fit-
tings and Sleeves . . . . . . . . . . . 7-107.13.5 Removable Installations. . . . . . . . . 7-107.14 CORROSION REMOVAL FROM
THIN METAL (0.0625 INCHTHICKNESS AND LESS). . . . . 7-11
7.15 AIR INTAKE DUCTS FOR JETAIRCRAFT. . . . . . . . . . . . . . . 7-11
7.16 CLOSELY COILED SPRINGS . . . 7-117.17 CORROSION PREVENTION ON
ASSEMBLIES AND PARTS RE-MOVED FROM AIRCRAFTDURING MAINTENANCE, 30DAY SHORT TERM STORAGE,AND OVER 30 DAY LONGTERM STORAGEREQUIREMENTS . . . . . . . . . . 7-11
7.17.1 Short Term Storage. . . . . . . . . . . . 7-117.17.2 Long Term Storage. . . . . . . . . . . . 7-127.18 DEPLETED URANIUM
COUNTERWEIGHTS. . . . . . . . 7-127.18.1 Corrosion and Finish Damage Treat-
ment Procedures. . . . . . . . . . . . 7-137.19 MONEL RIVETS. . . . . . . . . . . . . 7-147.20 BERYLLIUM-COPPER ALLOYS,
BERYLLIUM-ALUMINUM AL-LOYS, AND BERYLLIUMOXIDE. . . . . . . . . . . . . . . . . . 7-14
7.20.1 Corrosion Removal andTreatment . . . . . . . . . . . . . . . . 7-14
7.20.2 Depot Maintenance. . . . . . . . . . . . 7-147.21 EMI SEALS AND GASKETS . . . . 7-157.21.1 Treatment of EMI Seals and
Gaskets. . . . . . . . . . . . . . . . . . 7-15
8 EMERGENCY PROCEDURES . . . . . . . . . . 8-1
8.1 PURPOSE. . . . . . . . . . . . . . . . . . 8-18.2 RESPONSIBILITY. . . . . . . . . . . . 8-18.3 EMERGENCY
PREPARATIONS . . . . . . . . . . . 8-1
Chapter Page
8.3.1 Priority Removal List of Equipmentand/or Components. . . . . . . . . . 8-1
8.3.2 Emergency Reclamation Team . . . . 8-28.3.3 Emergency Reclamation
Equipment. . . . . . . . . . . . . . . . 8-28.3.4 Production Planning . . . . . . . . . . . 8-28.4 GENERAL PROCEDURES . . . . . . 8-2.18.4.1 Removal of Contaminated Installed
Equipment. . . . . . . . . . . . . . . . 8-88.4.2 Disassembly/Removal of
Components . . . . . . . . . . . . . . 8-88.4.3 Clean . . . . . . . . . . . . . . . . . . . . . 8-88.4.4 Tagging . . . . . . . . . . . . . . . . . . . 8-88.5 GENERAL CLEANING
PROCEDURES . . . . . . . . . . . . 8-88.5.1 Primary Method . . . . . . . . . . . . . . 8-98.5.2 Alternate Methods . . . . . . . . . . . . 8-98.5.3 Removing Fire Extinguishing Pow-
der (O-D-1407 Potassium Bicar-bonate [Purple K{PKP}], SodiumBicarbonate, Ammonium Phos-phate Monobasic) and/or OtherDry Chemical Agents . . . . . . . . 8-10
8.5.4 Removing MIL-F-24385 AqueousFilm Forming Foam (AFFF) FireExtinguishing Agent and OtherSynthetic Based Foaming AgentsIncluding High-Expansion (Hi-Ex) Foams . . . . . . . . . . . . . . . 8-10
8.5.5 Removal of Carbon Dioxide (CO2),HFC-125, Halon and 3MNOVEC 1230 Fire ExtinguishingAgents . . . . . . . . . . . . . . . . . . 8-11
8.5.6 Removal of Protein Type Foam andSoda-Acid Fire ExtinguishingAgents . . . . . . . . . . . . . . . . . . 8-11
8.5.7 Treatment After Landing on aFoamed Runway . . . . . . . . . . . 8-11
8.5.8 Treatment After Exposure to Volca-nic Ash. . . . . . . . . . . . . . . . . . 8-11
8.6 SPECIFIC INTERNALAREAS . . . . . . . . . . . . . . . . . 8-12
8.6.1 Aircraft Cockpit Area . . . . . . . . . . 8-128.6.2 Aircraft Ejection Seats . . . . . . . . . 8-128.6.3 Avionic, Electronic, and Electrical
Equipment. . . . . . . . . . . . . . . . 8-138.6.4 Photographic Equipment . . . . . . . . 8-138.6.5 Graphite or Carbon Fiber/Epoxy,
Boron Fiber/Epoxy, and TungstenFiber/Epoxy CompositeMaterials. . . . . . . . . . . . . . . . . 8-13
8.7 SPECIFIC EXTERNAL AREAS OFAIRCRAFT. . . . . . . . . . . . . . . 8-14
8.7.1 Airframes . . . . . . . . . . . . . . . . . . 8-148.7.2 Antennas. . . . . . . . . . . . . . . . . . . 8-14
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8.7.3 Reciprocating Engines. . . . . . . . . . 8-148.7.4 Turbine Engines . . . . . . . . . . . . . . 8-158.7.5 Treatment for Engines Which Have
Ingested Fire Extinguishing Pow-der (Potassium Bicarbonate[Purple K{PKP}], Sodium Bicar-bonate, Ammonium PhosphateMonobasic) and/or SyntheticFoaming Agents (AFFF, Hi-Ex,AR) . . . . . . . . . . . . . . . . . . . . 8-15
8.7.6 Helicopter Transmission, RotorHead, and Rotor Hub . . . . . . . . 8-16
8.7.7 Helicopter Main and Tail RotorBlades . . . . . . . . . . . . . . . . . . 8-16
8.7.8 Armament . . . . . . . . . . . . . . . . . . 8-168.7.9 Aircraft Fuel Systems . . . . . . . . . . 8-17
9 SOUTHWEST ASIA ENVIRONMENTS . . . . 9-1
9.1 INTRODUCTION . . . . . . . . . . . . 9-19.1.1 Climatic Conditions . . . . . . . . . . . 9-19.1.2 Aircraft Wash . . . . . . . . . . . . . . . 9-19.1.3 Aircraft Clear Water Rinse
(CWR) . . . . . . . . . . . . . . . . . . 9-19.1.4 Effects of Desert Environment . . . . 9-19.2 PRE-DEPLOYMENT
RECOMMENDATIONS . . . . . . 9-19.3 RECOMMENDED ACTIONS
WHILE DEPLOYED . . . . . . . . 9-29.3.1 High Efficiency Particulate Air
(HEPA) Filtration . . . . . . . . . . . 9-29.3.2 Areas to be Checked and
Cleaned . . . . . . . . . . . . . . . . . 9-29.4 POST DEPLOYMENT . . . . . . . . . 9-39.5 CORROSION PREVENTIVE
COMPOUNDS (CPC’s) . . . . . . 9-39.5.1 Recommended CPC’s . . . . . . . . . . 9-3
10 REMOTELY PILOTED AIRCRAFT CORRO-SION PREVENTION . . . . . . . . . . . . . . . 10-1
10.1 REMOTELY PILOTED AIRCRAFT(RPA). . . . . . . . . . . . . . . . . . . 10-1
10.1.1 Definition . . . . . . . . . . . . . . . . . . 10-1
Chapter Page
10.2 CORROSION CONTROLPROGRAM. . . . . . . . . . . . . . . 10-1
10.3 CARBON FIBER COMPOSITESAND CORROSION . . . . . . . . . 10-1
10.3.1 Corrosion Concerns . . . . . . . . . . . 10-110.3.2 Moisture Absorption . . . . . . . . . . . 10-210.4 CORROSIVE
ENVIRONMENTS. . . . . . . . . . 10-210.5 APPROVED CLEANING
COMPOUNDS . . . . . . . . . . . . 10-210.5.1 MIL-PRF-87937, Type IV and MIL-
PRF-85570, Type II . . . . . . . . . 10-210.5.2 MIL-PRF-87937, Type III and MIL-
PRF-85570, Type V . . . . . . . . . 10-210.5.3 A-A-59921 (Formerly MIL-C-
43616), Class 1A EmulsionCleaner. . . . . . . . . . . . . . . . . . 10-2
10.6 AIRCRAFT CLEANING. . . . . . . . 10-210.6.1 Frequency of Cleaning . . . . . . . . . 10-310.6.2 Wipe Down or Spot Cleaning. . . . . 10-3
APPENDIX A CONSUMABLEMATERIALS. . . . . . . . . . . . . . . . . . . . . . A-1
A.1 INTRODUCTION . . . . . . . . . . . . A-1A.1.1 Shelf Life . . . . . . . . . . . . . . . . . . A-1A.1.2 Consumable Materials
Containers. . . . . . . . . . . . . . . . A-1A.1.3 Local Purchase . . . . . . . . . . . . . . A-1A.1.4 Local Environmental Laws and
Regulations . . . . . . . . . . . . . . . A-1A.1.5 Unit of Issue Codes . . . . . . . . . . . A-1
APPENDIX B EQUIPMENT FOR CLEAN-ING AND CORROSION PREVENTIONAND CONTROL . . . . . . . . . . . . . . . . . . . B-1
B.1 INTRODUCTION . . . . . . . . . . . . B-1B.1.1 Unit of Issue Codes . . . . . . . . . . . B-1
GLOSSARY . . . . . . . . . . . . . . . . . . . . . Glossary 1
INDEX . . . . . . . . . . . . . . . . . . . . . . . . . Index 1
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LIST OF ILLUSTRATIONS
Number PageTitle
2-1 Simplified Corrosion Cell . . . . . . . . . . . 2-22-2 Elimination of Corrosion by Application
of an Organic Film to a MetalSurface . . . . . . . . . . . . . . . . . . . . . . 2-3
2-3 Effect of Sea Water on GalvanicCorrosion . . . . . . . . . . . . . . . . . . . . 2-3
2-4 Galvanic Corrosion in a FlashlightBattery . . . . . . . . . . . . . . . . . . . . . . 2-4
2-5 Effect of Area Relationship in DissimilarMetal Contacts . . . . . . . . . . . . . . . . . 2-4
2-6 Galvanic Corrosion of Magnesium Adja-cent to a Steel Fastener . . . . . . . . . . . 2-5
2-7 Pitting of an Aluminum WingAssembly . . . . . . . . . . . . . . . . . . . . 2-6
2-8 Cross-Section of Corrosion Pits . . . . . . . 2-62-9 Cross-Section of 7075-T6 Aluminum
Alloy . . . . . . . . . . . . . . . . . . . . . . . 2-72-10 Grain Structure of a Corroding Aluminum
Surface . . . . . . . . . . . . . . . . . . . . . . 2-72-11 Intergranular Corrosion of 7075-T6 Alumi-
num Adjacent to Steel Fastener. . . . . . 2-72-12 Example of Exfoliation . . . . . . . . . . . . . 2-72-13 Another Example of Exfoliation . . . . . . . 2-72-14 Concentration Cell Corrosion . . . . . . . . . 2-92-15 Stress Corrosion Cracking . . . . . . . . . . . 2-92-16 Galvanic Series of Metals and Alloys in
Sea Water . . . . . . . . . . . . . . . . . . . . 2-102-17 Filiform Corrosion Found Under Paint
Coating on a Magnesium Panel. . . . . . 2-112-18 Schematic of the Development of Filiform
Corrosion on an Aluminum Alloy . . . . 2-112-19 Magnesium Corrosion Products. . . . . . . . 2-122-20 Steel Corrosion Products (Rust) . . . . . . . 2-132-21 Aluminum Surface Corrosion
Products . . . . . . . . . . . . . . . . . . . . . 2-142-22 Cadmium Plated Surface Conditions . . . . 2-152-23 Failed Chromium Plating . . . . . . . . . . . . 2-173-1 Foam Generating Cleaning Unit (15
Gallons) . . . . . . . . . . . . . . . . . . . . . 3-303-2 Foam Generating Cleaning Unit (45
Gallons) . . . . . . . . . . . . . . . . . . . . . 3-313-3 Universal Wash Unit . . . . . . . . . . . . . . . 3-323-4 Top Loading Type . . . . . . . . . . . . . . . . 3-363-5 Front Loading Type . . . . . . . . . . . . . . . 3-363-6 Use of Aircraft Washing Applicator . . . . . 3-403-7 Aircraft Cleaning Procedure . . . . . . . . . . 3-413-8 Automatic Water Spray Nozzle . . . . . . . . 3-444-1 Depth Dimension of Corrosion Pits . . . . . 4-44-2 Fiber Optic Borescope. . . . . . . . . . . . . . 4-44-3 Optical Depth Micrometer (Analog Me-
chanical Read Out Type) . . . . . . . . . . 4-74-4 Optical Depth Micrometer (Digital Read
Out Type) . . . . . . . . . . . . . . . . . . . . 4-8
Number PageTitle
4-5 Typical Use of a Straight Edge to Deter-mine if Suspect Areas Have Been Pre-viously Reworked . . . . . . . . . . . . . . . 4-9
4-6 Corrosion Around Fasteners . . . . . . . . . . 4-104-7 Galvanic Corrosion of Aluminum Adjacent
to Steel Fasteners . . . . . . . . . . . . . . . 4-104-8 Spot Weld Corrosion . . . . . . . . . . . . . . . 4-114-9 Spot Welded Skin Corrosion
Mechanism . . . . . . . . . . . . . . . . . . . 4-114-10 Gun Blast Area Corrosion Points. . . . . . . 4-124-11 Exhaust Trail Area Corrosion Points . . . . 4-124-12 F-15 Nose Landing Gear Wheel Well . . . 4-124-13 Flaps Lowered to Expose Recess
Areas . . . . . . . . . . . . . . . . . . . . . . . 4-124-14 Reciprocating Engine Frontal Area Corro-
sion Points. . . . . . . . . . . . . . . . . . . . 4-134-15 Jet Engine Frontal Area Corrosion
Points . . . . . . . . . . . . . . . . . . . . . . . 4-134-16 Corrosion Prone Point of Air Inlet. . . . . . 4-134-17 Corrosion in Air Intake Duct . . . . . . . . . 4-144-18 Wing Fold Joint . . . . . . . . . . . . . . . . . . 4-154-19 Hinge Corrosion Points . . . . . . . . . . . . . 4-164-20 Piano Hinge Lugs . . . . . . . . . . . . . . . . . 4-164-21 Control Cables . . . . . . . . . . . . . . . . . . . 4-164-22 Personnel Relief Tube Vent . . . . . . . . . . 4-164-23 Common Water Entrapment Areas. . . . . . 4-174-24 Bilge Areas . . . . . . . . . . . . . . . . . . . . . 4-174-25 Battery Compartment . . . . . . . . . . . . . . 4-185-1 3M Co. Scotch-BriteTM Flap Brush and
Mandrel . . . . . . . . . . . . . . . . . . . . . 5-45-2 Abrasive Flap Wheels with Spindle
Mount. . . . . . . . . . . . . . . . . . . . . . . 5-45-3 3M Co. Radial Bristle Disc . . . . . . . . . . 5-55-4 3M Co. Roloc Discs . . . . . . . . . . . . . . . 5-65-5 3M Co. Inline Bristle Disc . . . . . . . . . . . 5-75-6 Abrasive Blasting Equipment . . . . . . . . . 5-105-7 Shaping Reworked Areas . . . . . . . . . . . . 5-135-8 Acceptable Clean-Up of Pitting Corrosion
on Critical Structure . . . . . . . . . . . . . 5-135-9 Limited Clearance. . . . . . . . . . . . . . . . . 5-145-10 A Water-Break Free Surface Compared
with One with Breaks . . . . . . . . . . . . 5-405-11 Magnetic Almen Strip Holder . . . . . . . . . 5-46.15-12 “A” Test Strip Magnetic to SAE J442 Stri-
pholder Arc Height ConversionGraph . . . . . . . . . . . . . . . . . . . . . . . 5-47
5-13 “A” Test Strip Arc Height Magnetic toSAE J442 Stripholder ConversionChart, 0.001 Inch . . . . . . . . . . . . . . . 5-48
TO 1-1-691
Change 16 vii
Number PageTitle
5-14 “N” Arc Height Magnetic to SAE J442Stripholder Conversion Graph. . . . . . . 5-49
5-15 “N” Arc Height Magnetic to SAE J442Stripholder Conversion Chart, 0.001Inch . . . . . . . . . . . . . . . . . . . . . . . . 5-50
5-16 Arc Height Plotting Chart . . . . . . . . . . . 5-515-17 Example of Coverage . . . . . . . . . . . . . . 5-525-18 Flap Deflection Ranges . . . . . . . . . . . . . 5-536-1 Pneumatic Sealant Gun . . . . . . . . . . . . . 6-66-2 Sealant Application Nozzles . . . . . . . . . . 6-76-3 Countersink Application Nozzles. . . . . . . 6-86-4 Rivet Application Nozzles . . . . . . . . . . . 6-96-5 Sealant and Adhesive Smoothing
Tools . . . . . . . . . . . . . . . . . . . . . . . 6-106-6 Sealant Injection Guns. . . . . . . . . . . . . . 6-116-7 Injection Style Semkit®. . . . . . . . . . . . . 6-126-8 Non-Metallic Spatula . . . . . . . . . . . . . . 6-266-9 Faying Surface Sealing . . . . . . . . . . . . . 6-286-10 Typical Fillet Seal. . . . . . . . . . . . . . . . . 6-296-11 Typical Injection Seal . . . . . . . . . . . . . . 6-306-12 Typical Methods of Sealing Fasteners . . . 6-31
Number PageTitle
6-13 Typical Lap Skin Sealing . . . . . . . . . . . . 6-336-14 Sealing Procedures for Typical Aircraft
Fitting. . . . . . . . . . . . . . . . . . . . . . . 6-346-15 Typical Spar Cap Sealing. . . . . . . . . . . . 6-356-16 Sealing of Access Doors . . . . . . . . . . . . 6-367-1 Beryllium-Copper Spiral Contact with En-
vironmental Fluorosilicone Seal . . . . . 7-167-2 Dorsal Longeron EMI Seal . . . . . . . . . . 7-177-3 Stainless Steel (CRES) EMI Screen. . . . . 7-177-4 Bonding Cable from Airframe to Graphite/
Epoxy Avionics Bay Door . . . . . . . . . 7-187-5 EMI Bonding Washers in an Avionics
Bay . . . . . . . . . . . . . . . . . . . . . . . . 7-199-1 Soil Makeup in the SWA Area . . . . . . . . 9-29-2 Global Dust Producing Regions . . . . . . . 9-29-3 Open Circuit Board. . . . . . . . . . . . . . . . 9-3B-1 Back Mounted Full Facepiece
Respirator . . . . . . . . . . . . . . . . . . . . B-43B-2 Front Mounted Full Facepiece
Respirator . . . . . . . . . . . . . . . . . . . . B-44B-3 Hooded Air Respirator System . . . . . . . . B-45
LIST OF TABLES
Number PageTitle
2-1 Corrosion of Metals - Type of Attack andAppearance of Corrosion Products . . . 2-15
3-1 Aircraft Wash Intervals . . . . . . . . . . . . . 3-23-2 Cleaning of Specific Areas and
Components. . . . . . . . . . . . . . . . . . . 3-123-3 Deicing/Anti-Icing Fluid Residue Inspec-
tion and Cleaning Procedures . . . . . . . 3-283-4 Recommended Dilution of Low Tempera-
ture Cleaner . . . . . . . . . . . . . . . . . . . 3-453-4.1 Fungus Growth Removal from Organic
Materials . . . . . . . . . . . . . . . . . . . . . 3-473-5 Common Military Greases and Their
Uses . . . . . . . . . . . . . . . . . . . . . . . . 3-553-6 Time Limitations for CPC’s . . . . . . . . . . 3-573-7 Corrosion Preventive Compounds . . . . . . 3-573-8 Preservation of Specific Areas and
Components. . . . . . . . . . . . . . . . . . . 3-604-1 NDI Inspection Tools for Various Types of
Corrosion . . . . . . . . . . . . . . . . . . . . 4-25-1 Grades of Abrasive Mats . . . . . . . . . . . . 5-35-2 Grades of Steel Wool . . . . . . . . . . . . . . 5-35-3 Recommended Powered Abrasives for
Corrosion Removal . . . . . . . . . . . . . . 5-85-4 Recommended Non-Powered Abrasives for
Corrosion Removal . . . . . . . . . . . . . . 5-105-5 Typical Chemical Corrosion Removal Pro-
cedures for Aluminum Alloy Parts andAssemblies . . . . . . . . . . . . . . . . . . . 5-18
Number PageTitle
5-6 Typical Chemical Corrosion Removal Pro-cedures for Magnesium Alloys . . . . . . 5-22
5-7 Typical Chemical Corrosion Removal Pro-cedures for Ferrous Metals Other ThanStainless Steel (CRES) . . . . . . . . . . . 5-26
5-8 Typical Chemical Corrosion Removal Pro-cedures for Stainless Steel (CRES) andNickel Based Alloys . . . . . . . . . . . . . 5-28
5-9 Control of Corrosion Removal/PicklingAction of Nitric-Acid-HydrofluoricSolutions . . . . . . . . . . . . . . . . . . . . . 5-30
5-10 Typical Chemical Corrosion Removal Pro-cedures for Copper and CopperAlloys. . . . . . . . . . . . . . . . . . . . . . . 5-32
5-11 Typical Chemical Corrosion Removal ofTitanium and Titanium BaseAlloys. . . . . . . . . . . . . . . . . . . . . . . 5-34
5-12 Typical Chemical Corrosion Removal Pro-cedures for Plated and PhosphatedSurfaces . . . . . . . . . . . . . . . . . . . . . 5-36
5-13 Prepaint Treatments for MetalSurfaces . . . . . . . . . . . . . . . . . . . . . 5-41
5-14 Tool Speed Operation Requirements . . . . 5-445-15 Standard Peening Intensity (Isp) for Com-
plete Coverage Arc-Height (All Num-bers in Inches) . . . . . . . . . . . . . . . . . 5-45
6-1 Sealing Compounds . . . . . . . . . . . . . . . 6-13
TO 1-1-691
LIST OF ILLUSTRATIONS - CONTINUED
viii Change 16
Number PageTitle
6-2 Time Requirements for Sealants WhenUsed at 75° F (24° C) and 50%RH. . . . . . . . . . . . . . . . . . . . . . . . . 6-22
8-1 Priority Guide for Emergency Treatmentof Aircraft, Missiles, andEquipment . . . . . . . . . . . . . . . . . . . . 8-3
8-2 Suggested List of Emergency ReclamationItems . . . . . . . . . . . . . . . . . . . . . . . 8-3
Number PageTitle
10-1 Air Force RPA Tiers . . . . . . . . . . . . . . . 10-1A-1 Unit of Issue Codes . . . . . . . . . . . . . . . A-1A-2 Consumable Materials . . . . . . . . . . . . . . A-2B-1 Unit of Issue Codes . . . . . . . . . . . . . . . B-1B-2 Equipment for Cleaning and Corrosion
Prevention and Control . . . . . . . . . . . B-2
TO 1-1-691
LIST OF TABLES - CONTINUED
Change 11 ix/(x blank)
INTRODUCTION
1 PURPOSE.
The purpose of this manual is to provide information onmaterials and procedures for the prevention and repair ofcorrosion damage to aircraft and missile weapon systems andrelated equipment. Supervisory and maintenance personnelshall use this manual as a guide for all corrosion control andmaintenance efforts. Contractors who maintain and repaircorrosion of aircraft, missiles, and related equipment shallalso use this manual. Use this manual in conjunction withand in support of the appropriate systems specific aircraft,missile, or equipment technical orders (TO’s). In the case ofa conflict between this manual and a systems specific air-craft, missile, or equipment manual, the system specificmanual shall take precedence over this manual. Paragraph 6lists related technical publications used by personnel in-volved in cleaning and corrosion control.
2 SCOPE.
The material in this manual provides basic cleaning, corro-sion prevention and control, and corrective maintenance in-formation to be used at organizational, intermediate, and de-pot levels. This manual is divided into eight chapters, twoappendices, a glossary, and an alphabetical index. Chapter 1explains the appropriate usage of this manual. Chapter 2 ex-plains what corrosion is, why it occurs, the various forms itcan take, and how to recognize it. Chapter 3 outlines ac-cepted procedures, methods, and materials to be used inmaintenance cleaning in Section I, lubrication in Section II,and preservation in Section III of aircraft, missiles, and re-lated equipment. Chapter 4 describes inspection techniquesfor detecting corrosion in Section I and discusses corrosionprone areas in Section II. Chapter 5 outlines the approvedmethods for the removal of corrosion damage in Section Iand the application of surface treatments in Section II. Chap-ter 6 covers recommended materials and procedures for theapplication of sealing compounds to aircraft, missile, andrelated equipment structures. Chapter 7 describes the recom-mended procedures for treating and protecting against corro-sion in specific areas. Chapter 8 outlines emergency proce-dures to be followed after exposure of aircraft to salt water,fire extinguishing chemicals, etc., Appendix A lists the rec-ommended materials for cleaning, corrosion prevention, sur-face treatment, and preservation of aircraft, missiles, and re-lated equipment. Appendix B lists equipment used forcleaning, corrosion removal, conversion coating, and sealingof aircraft, as well as associated safety equipment includingpersonal protective equipment (PPE) for these operations.
3 LIST OF ABBREVIATIONS AND ACRONYMS.
All abbreviations used in this manual are in accordance withASME Y14.38.
AFCPCO Air Force Corrosion Prevention and Con-trol Office
AFFF Aqueous Film Forming FoamAFPHIS Animal and Plant Health Inspection Ser-
vicesAISI American Iron and Steel InstituteAOR Area of ResponsibilityBOD Biological Oxygen DemandCaCO3 Calcium CarbonateCaSO4.2H2O Anhydrous Calcium SulfateCBR Chemical, Biological, RadiologicalCBRNE Chemical, Biological, Radiological,
Nuclear, and High-Yield ExplosiveCC Cubic CentimetersCFM Cubic Feet Per MinuteCPC Corrosion Preventive CompoundsCRES Corrosion Resistant SteelsCrO3 Chromic AcidCWR Clear Water Rinse°C Degrees Celsius°F Degrees FahrenheitDFT Dry Film ThicknessDI DeionizedDTIC Defense Technical Information CenterEA EachEPA Environmental Protection AgencyEPTFE Expanded Polytetrafluoroethyleneft Foot/FeetFIP Form-In-PlaceHAP Hazardous Air PollutantsHCFC HydrochlorofluorocarbonHEPA High Efficiency Particulate AirID Inside Diameterin InchIVD Ion Vapor DepositedKSI Kilograms per Square InchLG Landing GearLOX Liquid OxygenMEK Methyl Ethyl Ketonemg/L Milligrams per Litermm Hg Millimeters of MercuryMOS Maximum Operating SpeedNDI Non-Destructive InspectionNRA Nuclear Regulatory AgencyNSN National Stock NumberOD Outside DiameterODC Ozone Depleting Compounds
TO 1-1-691
Change 17 xi
ODS Ozone Depleting SubstancesPDM Program Depot MaintenancepH Potential of HydrogenPMB Plastic Media BlastPMF Pre-Mixed and FrozenPN Part NumberPPE Personal Protective Equipmentppm Parts Per MillionPSI Pounds Per Square InchQPD Qualified Products DatabaseQPL Qualified Products ListRH Relative HumidityRPM Rotations Per MinuteRTU Ready-To-UseSDS Safety Data SheetsSE Support EquipmentSLED Shelf Life Extension DocumentSPD System Program DirectorSPM System Program ManagerSWA Southwest AsiaTDS Total Dissolved SolidsTNP Touch-N-PrepTM
TO Technical OrderTPH Total Petroleum HydrocarbonTSS Total Suspended SolidsVOC Volatile Organic Compound
4 RELATED PUBLICATIONS.
NOTE
When searching Technical Order (TO) numbers inthe Enhanced Technical Information ManagementSystem (ETIMS) catalog, please use the wildcard(*) after typing in the TO number. Many TOs arenot available in paper format, (i.e., digital (WA-1)or Compact Disk (CD-1)). This ensures TOs in allmedia formats will populate the search.
The following publications contain information in support ofthis technical manual.
List of Related Publications
Number TitleAFI 20-114 Air and Space Equipment
Structural ManagementAFI 32-1067 Water SystemsAFI 32-7001 Environmental Management
List of Related Publications - Continued
Number TitleAFI 40-201 Managing Radioactive Mate-
rials in the U.S. Air ForceAFI 23-101 AF Material ManagementAFMAN 10-2503 Operations in a Chemical,
Biological, Radiological,Nuclear, and High-Yield Ex-plosive (CBRNE) Environ-ment
AFMAN 24-204-IP Preparing Hazardous Materi-als for Military Air Ship-ments
AFMAN 91-223 Aviation Safety Investiga-tions and Reports
AF-PAM 91-212 Bird/Wildlife Aircraft StrikeHazard (BASH) Manage-ment Techniques
AFI 91-203 Air Force Consolidated Oc-cupational Safety Instruction
ASME Y14.38 Abbreviations and Acronymsfor Use on Drawings andRelated Documents
DOD 4140.27-M Shelf Life ManagementManual
DOD 6050.5LR Hazardous Material Controland Management (HMC&M)
MIL-HDBK-729 Corrosion and CorrosionPrevention-Metals
TO 00-5-1 AF Technical Order SystemTO 00-20-1 Aerospace Equipment Main-
tenance Inspection, Docu-mentation, Policy and Proce-dures
TO 00-20-2 Maintenance Data Documen-tation
TO 00-25-107 Maintenance AssistanceTO 00-25-172 Ground Servicing of Aircraft
and Static Grounding/Bond-ing
TO 00-25-234 General Shop Practice Re-quirements for the Repair,Maintenance, and Test ofElectronic Equipment
TO 00-25-235 Safety Procedures andEquipment for ConfinedSpace Entry (Including Mis-sile Propellant Tanks)
TO 1-1-691
xii Change 17
List of Related Publications - Continued
Number TitleTO 00-35D-54 USAF Material Deficiency
Reporting and InvestigatingSystem
TO 00-85A-03-1 Preservation, Packaging andPacking - External AircraftFuel Tanks, Fuel Cells
TO 00-110A-1 Guidelines for Identificationand Handling of Aircraft andMaterial Contaminated withRadioactive Debris (Fallout)
TO 1-1-3 Inspection and Repair ofAircraft Integral Tanks andFuel Cells
TO 1-1-8 Application and Removal ofOrganic Coatings, Aerospaceand Non-Aerospace Equip-ment
TO 1-1-17 Storage of Aircraft and Mis-siles Systems
TO 1-1-24 Maintenance Repair andElectrical Requirements forFiberglass Airborne Ra-domes
TO 1-1-689-1 Cleaning and CorrosionControl, Volume I, CorrosionProgram and CorrosionTheory
TO 1-1-689-3 Cleaning and CorrosionControl, Volume III, Avion-ics and Electronics
TO 1-1-689-5 Cleaning and CorrosionControl, Volume V, Consum-able Materials and Equip-ment for Avionics
TO 1-1-690 General Advanced Compos-ite Repair Processes
TO 1-1A-1 Engineering H/B Series forAircraft Repair - GeneralManual for Structural Repair
TO 1-1A-8 Engineering Manual Seriesfor Aircraft and MissilesRepair Structural Hardware
TO 1-1A-9 Engineering Series for Air-craft Repair Aerospace MetalGeneral Data and UsageFactors
TO 1-1A-12 Fabrication, Maintenanceand Repair of TransparentPlastic
TO 1-1A-14 Installation Practices for Air-craft Electric and ElectronicWiring
List of Related Publications - Continued
Number TitleTO 1-1A-15 General Maintenance In-
structions for Support Equip-ment (SE)
TO 2-1-111 Standard Maintenance Prac-tices, Navy, USAF andArmy, P&W Aircraft En-gines
TO 2J-1-13 Cleaning of Gas TurbineAircraft Engines and Parts
TO 2J-1-18 Preparation for Shipmentand Storage of Gas TurbineEngines
TO 2J-1-32 Standard Maintenance Prac-tice Instructions - GE Air-craft Engines, Model TF-34-GE-100, A, -400, A, B,TF58-GE-3, -5, -8B, -10,-16, -100 (USCG), -400B,-402, T64-GE-6B, -7, A,100, -413, -415, -416,-416A, F404-GE-400,YF404-GE-400, F110-GE-400, YT700-GE-401, T700-GE-401, 4
TO 4B-1-32 Maintenance and O/H In-structions - All Type AircraftBrakes
TO 4S-1-182 General O/H & MaintenanceInstr. All FSC 1620 LandingGear & Components
TO 4W-1-61 Operation, Service, andMaintenance Instructions-AllAircraft Wheels
TO 10-1-179 Corrosion Control Manualfor Photographic Equipment
TO 13A1-1-1 Repair, Cleaning, Inspectionand Testing Aircraft SafetyBelts, Shoulder Harness, andMiscellaneous PersonnelRestraint Equipment
TO 31-1-221 Field Instructions for Paint-ing and Preserving Electron-ics Command Equipment
TO 33B-1-1 Nondestructive InspectionMethods
TO 34-1-3 Inspection and Maintenanceof Machinery and ShopEquipment
TO 35-1-3 Corrosion Prevention, Paint-ing, and Marking of USAFSupport Equipment (SE)
TO 1-1-691
Change 11 xiii
List of Related Publications - Continued
Number TitleTO 35-1-4 Processing and Inspection of
Support Equipment for Stor-age and Shipment
TO 36-1-191 Technical and ManagerialReference for Motor VehicleMaintenance
TO 42A1-1-1 Evaluation and Service Test-ing of Materials - Cleaning,Painting, Sealing, ProtectiveTreating, Anti-Corrosion,Inspection Materials, andRelated Items
TO 42A3-1-2 General Use of Cements,Sealants, and Coatings
List of Related Publications - Continued
Number TitleTO 42B-1-6 Corrosion Preventive Lubri-
cants and Anti-Seize Com-pounds
TO 42C-1-2 Anti-Icing, Deicing, and De-frosting of Parked Aircraft
TO 42C-1-12 Quality Control of Chemi-cals
TO 42C2-1-7 Electro Deposition of Metalsand Metal Surface Treat-ments to Meet Air ForceMaintenance Requirements
TO 1-1-691
xiv Change 11
1 RECORD OF APPLICABLE TIME COMPLIANCETECHNICAL ORDERS (TCTOS).
List of Time Compliance Technical Orders
TCTONumber
TCTOTitle
TCTODate
None
2 HARDNESS CRITICAL ITEMS (HCI).
The HCI symbol ( ) establishes special require-ments limiting changes and substitutions and thatthe specific parts listed must be used to ensurehardness is not degraded.
If included, items with nuclear survivability requirements aremarked with the HCI symbol ( ). All changes to, or pro-posed substitutions of, HCIs must be approved by the ac-quiring activity.
3 ELECTROSTATIC DISCHARGE SENSITIVE(ESDS) ITEMS.
All ESDS parts shall be handled in accordancewith the ESDS device handling procedures in TO00-25-234.
If included, items containing ESDS parts are marked withthe ESDS symbol ( ).
4 RESPONSIBILITY FOR CHANGES TO THISMANUAL.
This manual is maintained for technical content by the AirForce Corrosion Prevention and Control Office (AFCPCO),AFLCMC/EZPT-CPCO, 325 Richard Ray Blvd., RobinsAFB, GA 31098-1639, Tel: (478) 926-3284 (DSN 468-3284),Fax: (478) 926-6619 (DSN 468-6619), email:[email protected]; and for TO administration by WRALC/LESGI, 460 Richard Ray Blvd., Robins AFB, GA 31098-1640, Tel: (478) 926-7046 x122 (DSN 468-7046 x122),email: [email protected].
5 IMPROVEMENT REPORTS.
Recommended changes to this manual shall be submitted inaccordance with TO 00-5-1.
6 GENERAL SAFETY INSTRUCTIONS.
This manual describes physical and chemical processeswhich may cause injury or death to personnel, or damage toequipment if not properly followed. This safety summaryincludes general safety precautions and instructions that mustbe understood and applied during operation and maintenanceto ensure personnel safety and protection of equipment. Priorto performing any task, the WARNINGs, CAUTIONs andNOTEs included in that task shall be reviewed and under-stood.
7 WARNINGS, CAUTIONS, AND NOTES.
WARNINGs and CAUTIONs are used in this manual tohighlight operating or maintenance procedures, practices,conditions or statements which are considered essential toprotection of personnel (WARNING) or equipment (CAU-TION). NOTEs are used in this manual to highlight operat-ing or maintenance procedures, practices, conditions or state-ments which are not essential to protection of personnel orequipment. The headings used and their definitions are asfollows:
Highlights an essential operating or maintenanceprocedure, practice, condition, statement, etc.,which if not strictly observed, could result in in-jury to, or death of, personnel or long term healthhazards.
TO 1-1-691
Change 18 xvAll data on page xviii deleted
Highlights an essential operating or maintenanceprocedure, practice, condition, statement, etc.,which if not strictly observed, could result in dam-age to, or destruction of, equipment or loss of mis-sion effectiveness.
NOTE
Highlights an essential operating or maintenanceprocedure, condition or statement.
8 SAFETY PRECAUTIONS.
The following safety precautions shall be observed whileperforming procedures in this manual.
• Some cleaning materials specified herein are flam-mable and/or toxic. Keep away from open flame orother ignition sources. Do not use synthetic wipingcloths with flammable solvents. Open all circuitbreakers associated with battery power prior to ap-plication of any flammable solvent. Provide ad-equate ventilation and avoid skin/eye contact. WearPersonal Protective Equipment (PPE). Consult theSafety Data Sheets (SDS) for specific informationon hazards, effects, and protective equipment re-quirements.
• Some cleaning processes described herein use ma-terials and generate effluent that may be hazardousto personnel and the environment. Contact the localBioenvironmental Engineer and safety office forguidance on PPE and other health and safety pre-cautions, and waste disposal.
• Some cleaning operations described herein utilizepower tool operations and abrasive blasting opera-tions which often generate toxic/hazardous airborneparticles. Always wear proper PPE.
• Ensure that all electrical power is disconnected andall systems in aircraft, missiles, or equipment aredeactivated before starting cleaning operations onavionics, electronics, or electrical equipment to pre-vent electrical shock.
• Remove jewelry and remove/cover loose fittingclothing before operating power equipment to pre-vent entanglement and injury.
• Cleaning with compressed air can create airborneparticles that may enter eyes or penetrate skin. Pres-sure shall not exceed 30 PSIG. Wear goggles. Donot direct compressed air against skin.
• Depleted uranium is extremely toxic and shall beworked only under a license from the Nuclear Regu-latory Agency (NRA). Machining or other work,such as surface sanding, may be done only by thelicensee. No drilling, sanding, abrasive blasting, orother mechanical work is permitted on depleteduranium by any field level (organizational or inter-mediate) maintenance activity. If the protective fin-ish (plating) which covers the depleted uranium ischipped, peeled, or otherwise removed so the darkgray or black uranium oxide is visible, the part mustbe returned to the licensee for rework or disposal.Packaging and shipping procedures shall conformto AFI 40-201 and any other related current regula-tions for handling radioactive materials.
TO 1-1-691
xvi Change 17 All data on page xviii deleted
CHAPTER 1INTRODUCTION
1.1 CORROSION CONTROL PROGRAM.
All activities responsible for maintenance of aircraft, mis-siles, and related equipment shall establish corrosion preven-tion and control programs as required by AFI 20-114. Thetype of program depends upon the environment to which theaircraft, missile, or equipment may be exposed. Aircraft,missiles, and equipment may be exposed to industrial gases,salts, rain, mud, and mists containing sea salts if located nearsalt water. A comprehensive corrosion prevention and con-trol program shall provide a Structural Maintenance WorkCenter with personnel trained in the prevention, early detec-tion, reporting, and repair of corrosion damage. In addition,such a program requires a dedicated effort by all mainte-nance personnel to prevent corrosion from occurring and/orto detect it in its initial stages so it can be treated early thusminimizing costly repairs and improving the operationalreadiness of aircraft, missiles, and equipment.
1.1.1 Training. All personnel performing maintenance onaircraft, missiles, and related equipment shall be trained inbasic corrosion prevention and control skills and must befully aware of the reasons for the corrosion prevention andcontrol program. Without such training and understanding,more severe damage and additional problems will result.
1.1.2 Maintenance. An effective corrosion prevention andcontrol program shall include thorough cleaning, inspection,preservation, and lubrication, at specified intervals, in accor-dance with Chapter 3 and Chapter 4. Check for corrosiondamage and integrity of protective finishes during all sched-uled and unscheduled maintenance. Early detection and re-pair of corrosion will limit further damage. When corrosionis discovered, treat corrosion as prescribed in Chapter 5 andChapter 7 as soon as possible using only approved materials,equipment, and techniques. Only affected areas shall be re-paired. Seal in accordance with Chapter 6 and paint, as re-quired, in accordance with TO 1-1-8 and the systems spe-cific TO. All maintenance personnel shall report corrosionpromptly in accordance with established Air Force directives.
1.1.3 Facilities. In accordance with Paragraph 7.10.5 ofAFH 32-1084 titled “FACILITY REQUIREMENTS”, baseswith a large number of aircraft (40 or more large or mediumassigned aircraft) or located in a severe environment are au-thorized, with proper justification, a Corrosion Control Han-gar and aircraft wash hangar.
1.2 SAFETY.
Safety is everyone’s business and concern.
1.2.1 Responsibility of Supervisors. Work center super-visors shall receive the following training in accordance withestablished Air Force directives:
• The recognition and elimination of hazards.
• Occupational safety and health.
• The safety of the individual.
• Accident investigation and reporting.
• The inspection and maintenance of personal protec-tive equipment (PPE).
a. Supervisors shall ensure that all corrosion control per-sonnel are informed of current safety procedures.
• Characteristics of materials to which they willbe exposed.
• Required protective clothing and personal pro-tective equipment (PPE) to ensure safety ofpersonnel.
b. In addition, supervisors shall ensure that an adequatesupply of safety equipment is in a ready-for-issue con-dition, and that personnel under their control are given,and use, appropriate protective equipment to preventaccidents, injuries, and occupational illness. Mainte-nance personnel shall use the appropriate equipmentwhile exposed to hazardous conditions, and shall re-port any protective equipment that is broken, damaged,defective, or inadequate to the supervisor. No one shalluse protective equipment that is not in a satisfactoryand serviceable condition. Personnel shall comply withoccupational safety and health requirements, includingmedical examinations, respirator training and fit test-ing, and protection for eyes, ears, head, skin, and feet.
1.2.2 Materials Handling. Many of the materials and pro-cedures outlined in this manual are potentially hazardous topersonnel and potentially damaging to aircraft, missiles, andequipment, especially when improperly used. When usingany chemicals, such as paint removers, detergents, conver-sion coatings, and solvents, follow the correct proceduresand use appropriate protective gear to prevent personnel in-jury and structural damage. Read the appropriate warningsand cautions in this manual prior to use of any hazardousmaterials. Misuse of certain materials can damage parts orcause corrosion which may lead to catastrophic failure. Re-
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fer to DOD 6050.5LR, Hazardous Materials InformationSystem, and the appropriate Air Force directives for the han-dling, storage, and disposal of hazardous materials. Refer tolocal directives and policies pertaining to hazardous wastemanagement. When in doubt, contact the base safety office,and/or Bioenvironmental Engineer for assistance.
1.3 MATERIALS.
Consumable materials listed in Appendix A and accessorieslisted in Appendix B shall be used for corrosion preventionand control. The materials and equipment listed have beenapproved only after extensive testing to prove their ability toperform properly and effectively without damage to any ofthe metallic or nonmetallic materials used in aircraft, mis-
siles, and related equipment. Only those materials listed inthis manual shall be used for cleaning and corrosion preven-tion and control of aircraft, missile, and equipment compo-nents. Materials listed in other manuals shall be used onlywhen required procedures are not covered by this manual.Materials or processes considered to be an improvement overexisting ones shall be forwarded to the Aircraft System Pro-gram Director (SPD) or the Missile or Equipment SystemProgram Manager (SPM) and the Air Force Corrosion Pre-vention and Control Office (AFCPCO), AFLCMC/EZPT-CPCO, for further evaluation. When approved materials arenot available, substitutions shall only be made after approvalby the appropriate SPD/SPM in conjunction with the AF-CPCO. When several methods or materials are listed, thepreferred one is listed first, with alternates following.
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CHAPTER 2CORROSION THEORY
2.1 INTRODUCTION TO CORROSION THEORY.
This chapter is an introduction to corrosion theory, the causesof corrosion, and the factors which influence its develop-ment. The various forms of corrosion and the effect of cor-rosive environments on aircraft and metals are described.The purpose of this discussion is to provide maintenancepersonnel with the background knowledge necessary to un-derstand the causes of corrosion and to minimize corrosiondamage.
2.2 DEFINITION OF CORROSION.
Corrosion is the electrochemical deterioration of a metal be-cause of its chemical reaction with the surrounding environ-ment. This reaction occurs due to the tendency of metals toreturn to their naturally occurring states, usually oxide orsulfide ores. For example, iron in the presence of moistureand air will return to its natural state, iron oxide or rust.Aluminum and magnesium form corrosion products that arewhite oxides or hydroxides. When a water solution contain-ing soluble salts is present, corrosion of many alloys canoccur easily at ambient (room) temperatures. This type ofcorrosion can be effectively treated by maintenance person-nel as discussed in this manual. Corrosion can also occur inthe absence of water, but only at high temperatures such asthose found in gas turbine engines. However, the most com-mon type of corrosion (and the one that can be most effec-tively treated by maintenance personnel) is electrochemicalcorrosion.
2.3 CHEMICAL DEFINITIONS.
2.3.1 Atom. The smallest unit of an element. There areover 100 elements, including metals such as aluminum,magnesium, gold, platinum, iron, nickel, titanium, cadmium,chromium, copper, silver, lead, uranium, beryllium, zinc andcarbon and non-metals such as hydrogen, oxygen, nitrogen,sulfur, chlorine, helium and boron.
2.3.2 Electron. A negatively charged particle muchsmaller than an atom. An electric current occurs when elec-trons are forced to move through metal conductors. Elec-trons flow through water solutions only in the presence ofions.
2.3.3 Ions. Atoms or groups of atoms bound togetherwhich are either positively or negatively charged. An electriccurrent occurs when ions are forced to move through watersolutions. Ions cannot move through metal conductors.
2.3.4 Electrolyte. A liquid (usually water) solution con-taining ions. Salt water is an electrolyte: an aqueous (mean-ing, water) solution of sodium ions and chloride ions. Elec-trochemistry is the branch of chemistry concerned withchemical reactions at surfaces in contact with electrolytes.
2.4 THEORY OF CORROSION.
All structural metals will corrode to some extent in a naturalenvironment. When a metal corrodes, the metal atoms loseelectrons and become positively charged metal ions in theelectrolyte. In solution, the positively charged metal ions cancombine with negatively charged ions to form corrosionproducts, such as metallic chlorides, oxides, hydroxides, sul-fides, etc. Four conditions must exist before this type of cor-rosion can occur.
2.4.1 Anode. A metal which has a tendency to corrodemust be present (the corroding metal is known as the anode).
2.4.2 Cathode. A dissimilar conductive material (the cath-ode) which has less tendency to corrode than the anode mustbe present (such as a different metal, a protected part of thesame metal, or conductive plastics).
2.4.3 Electrolyte. A conductive liquid (electrolyte) mustconnect the anode and cathode (so that ions can carry elec-tric current between them).
2.4.4 Electrical Contact. Electrical contact between theanode and cathode (usually in the form of metal-to-metalcontact) must exist (so that electrons can move from theanode, where they are released, to the cathode).
2.4.4.1 Elimination of Anode, Cathode, Electrolyte, orElectrical Contact. The elimination of any one of the fourconditions, illustrated in Figure 2-1, will stop corrosion. Forexample, a paint film on a metal surface will prevent theconducting liquid (electrolyte) from connecting the anodeand cathode, thereby, stopping the electric current. (Refer toFigure 2-2). Another example: two connected dissimilarmetal parts placed in distilled water corrode very slowly dueto a lack of ions in solution to conduct the electric current; insea water the corrosion reaction is accelerated by a factor of1,000 or more. (Refer to Figure 2-3).
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2.5 DEVELOPMENT OF CORROSION.
All corrosive attack begins on the surface of metals. If al-lowed to progress, corrosion can penetrate in the metal. Ifcorrosion begins on an inside surface of a component (forexample, the inner wall of metal tube), it may go undetecteduntil perforation occurs. When corrosion products form, theyoften deposit on the corroding surface as a powdery deposit.This film of corrosion products may reduce the rate of cor-rosion, if the film acts as a barrier to electrolytes. Some met-als (such as stainless steel and titanium), under the right con-ditions, produce corrosion products that are so tightly boundto the corroding metal that they form an invisible oxide film(called a passive film), which prevents further corrosion.However, when the film of corrosion products is loose andporous (such as those of carbon steel, aluminum and magne-sium), an electrolyte can easily penetrate and continue thecorrosion process, producing more extensive damage thansurface appearance shows.
2.5.1 Corrosion Under Painted Surfaces. Paint coatingscan mask the initial stages of corrosion. Since corrosionproducts occupy more volume than the original metal, paintsurfaces should be inspected often for irregularities such asblisters, flakes, chips, lumps, and worm like tracks.
2.6 FACTORS INFLUENCE CORROSION.
Some factors which influence metal corrosion and the rate ofcorrosion are:
• Type of metal.
• Presence of a dissimilar, less corrodible metal (gal-vanic corrosion).
• Anode and cathode surface areas (in galvanic cor-rosion).
• Temperature.
• Heat treatment and grain direction.
• Presence of electrolytes (hard water, salt water, bat-tery fluids, etc.).
• Availability of oxygen.
• Presence of different concentrations of the sameelectrolytes.
• Presence of biological organisms.
• Mechanical stress on the corroding metal.
• Time of exposure to a corrosive environment.
2.6.1 Type of Metal. Most pure metals are not suitable foraircraft construction and are used only in combination withother metals, and sometimes non-metals, to form alloys.Most alloys are made up entirely of small crystalline re-gions, called grains. Corrosion can occur on surfaces of thoseregions, which are less resistant, and also at boundaries be-tween regions, resulting in the formation of pits and inter-granular corrosion. The metals most commonly used in air-craft construction are aluminum, steel, titanium, andmagnesium. Cadmium, zinc, nickel, chromium, and silverare sometimes used as protective platings. Metals have awide range of corrosion resistance. The most active metals(those which tend to lose electrons easily), such as magne-sium and aluminum, corrode easily and are listed at the topor anodic end of Figure 2-16. The most noble metals (thosewhich do not lose electrons easily), such as gold and silver,do not corrode easily and are listed at the bottom or cathodicend of Figure 2-16.
2.6.2 Dissimilar Metal Coupling (Galvanic Corrosion).When two dissimilar metals make electrical contact in thepresence of an electrolyte, the rate at which corrosion occursdepends on the difference in their activities, that is, theirpositions in Figure 2-16. The greater the difference in activ-ity, the faster corrosion occurs. For example, magnesiumwould corrode very quickly when coupled with gold in ahumid atmosphere. But aluminum would corrode veryslowly, if at all, in contact with cadmium. A flashlight bat-tery (or dry cell) is an example of galvanic corrosion put topractical use. In Figure 2-4, the zinc battery casing steadilycorrodes supplying a steady flow of electrons, but only whenthe switch is closed. When the switch is open, there is nocorrosion because electrons are not able to leave the zincanode.
Figure 2-1. Simplified Corrosion Cell
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2.6.3 Anode and Cathode Surface Area. The rate ofgalvanic corrosion also depends on the size of the parts incontact. If the surface area of the corroding metal (the an-ode) is smaller than the surface area of the less active metal(the cathode), corrosion will be rapid and severe. But, when
the corroding metal is larger than the less active metal, cor-rosion will be slow and superficial. For example, an alumi-num fastener in contact with a relatively inert Monel struc-
Figure 2-2. Elimination of Corrosion by Application of an Organic Film to a Metal Surface
Figure 2-3. Effect of Sea Water on Galvanic Corrosion
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ture may corrode severely, while a Monel bracket secured toa large aluminum member would result in a relatively super-ficial attack on the aluminum sheet. (Refer to Figure 2-5).
2.6.4 Temperature. Higher temperature environmentstend to produce more rapid corrosion due to acceleratedchemical reactions and, in humid environments, higher con-centration of water vapor in the air. In addition, nightly dropsin temperature can cause greater amounts of condensation,leading to increased corrosion rates.
2.6.5 Heat Treatment and Grain Direction. When heat-treated, heavy sections of metals do not cool uniformly and,as a result, tend to vary in chemical composition from onepart of the metal to another. This can cause galvanic corro-sion if one area is more active than another. Alloys, whichare fabricated by rolling, extruding, forging, or pressing, haveproperties which depend highly on direction (grain length vs.cross grain). For example, exposed end grains corrode muchmore easily than flattened elongated surfaces in sheet stock.This explains why exfoliation occurs at the edge of aircraftskin sections or next to countersunk fasteners.
2.6.6 Electrolytes. Electrically conducting solutions areeasily formed on metallic surfaces when condensation, saltspray, rain, or rinse water accumulate. Dirt, salt, acidic stackgases, and engine exhaust gases can dissolve on wet sur-faces, increasing the electrical conductivity of the electro-lyte, thereby increasing the rate of corrosion.
Figure 2-4. Galvanic Corrosion in a Flashlight Battery
Figure 2-5. Effect of Area Relationship in DissimilarMetal Contacts
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2.6.7 Oxygen. When some of the electrolyte on a metalsurface is partially confined (such as between faying sur-faces or in a deep crevice) metal in this confined area cor-rodes more rapidly than other metal surfaces of the samepart outside this area. This type of corrosion is called anoxygen concentration cell or differential aeration cell. Corro-sion occurs more rapidly than would be expected becausethe reduced oxygen content of the confined electrolyte causesthe adjacent metal to become anodic to other metal surfaceareas on the same part immersed in electrolyte exposed tothe air.
2.6.8 Electrolyte Concentration. In the same way thatmetals can corrode when exposed to different concentrationsof oxygen in an electrolyte, corrosion will also occur if theconcentration of the electrolyte on the surface varies fromone location to another. This corrosive situation is known asa concentration cell.
2.6.9 Biological Organisms. Slimes, molds, fungi, andother living organisms (some microscopic) can grow ondamp surfaces. Once they are well established, the area tendsto remain damp, increasing the possibility of corrosion. Theirpresence can cause the areas they occupy to have differentoxygen and electrolyte concentrations. In addition, corrosivewastes are secreted, which cause corrosion.
2.6.10 Mechanical Stress. Almost all alloys used in air-craft construction are sensitive to a form of corrosion knownas stress corrosion cracking. Manufacturing processes suchas machining, forming, welding, or heat treatment can leavestresses in aircraft parts. This residual stress and/or stressapplied to a part causes corrosion to proceed more rapidly instructurally important regions of the part until failure occurs.
2.6.11 Time. As time goes on, metals naturally tend tocorrode. In some cases, the corrosion process occurs at thesame rate, no matter how long the metal has been exposed to
the environment. In other cases, corrosion can decrease withtime, due to the barrier formed by corrosion products, orincrease with time if a barrier to corrosion is being brokendown.
2.7 TYPES OF CORROSION.
Corrosion is catalogued and typed in many ways. Occasion-ally, different names are used for the same type of corrosion.The common types of corrosion are described below.
2.7.1 Uniform Surface Corrosion. Uniform surface cor-rosion or etching results from a direct chemical attack on ametal surface and involves only the metal surface. On a pol-ished surface, this type of corrosion is first seen as a generaldulling or etching of the surface and, if the attack is allowedto continue, the surface becomes rough and possibly frostedin appearance. This type of corrosion appears uniform be-cause the anodes and cathodes are very small and constantlyshift from one area of the surface to another. An example isthe etching of metals by acids. The discoloration or generaldulling of metal created by exposure to elevated tempera-tures is not considered to be uniform surface corrosion.
2.7.2 Galvanic Corrosion. Galvanic corrosion occurswhen different metals are in contact with each other and anelectrolyte, such as salt water. It is usually recognizable bythe presence of a buildup of corrosion at the joint betweenthe metals. For example, aluminum skin panels and stainlesssteel doublers, riveted together in an aircraft wing, form agalvanic couple if moisture and contamination are present.Figure 2-6 shows galvanic corrosion of magnesium adjacentto steel fasteners. When metals which are known to be inelectrical contact are well separated from each other in Fig-ure 2-16, galvanic corrosion is probably occurring.
Figure 2-6. Galvanic Corrosion of Magnesium Adjacent to a Steel Fastener
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2.7.3 Pitting Corrosion. The most common corrosion onaluminum and magnesium alloys is called pitting. (Refer toFigure 2-7). It is first noticeable as a white or gray powderydeposit, similar to dust, which blotches the surface. Whenthe deposit is cleaned away, tiny pits or holes can be seen inthe surface. (Refer to Figure 2-8). Pitting corrosion can alsooccur in other types of alloys. The combination of smallactive anodes to large passive cathodes causes severe pitting.
2.7.4 Intergranular Corrosion. Intergranular corrosion isan attack on the grain boundaries of the metal. A highlymagnified cross section of any commercial alloy (refer toFigure 2-9 and Figure 2-10), shows the granular structure ofthe metal. It consists of quantities of individual grains, each
having a clearly defined boundary, which chemically differsfrom the metal within the grain. Frequently, the grain bound-aries are anodic (tend to corrode more easily) to the metalwithin the grain. When in contact with an electrolyte, rapidcorrosion occurs at the grain boundaries. Figure 2-11 showsintergranular corrosion of 7075-T6 aluminum alloy adjacentto steel fasteners. In this example, the grain boundaries areanodic to both the metal grain and the steel fastener.
2.7.5 Exfoliation Corrosion. Exfoliation (refer to Figure2-12 and Figure 2-13), is an advanced form of intergranularcorrosion where the surface grains of a metal are lifted up bythe force of expanding corrosion products occurring at thegrain boundaries. The lifting up or swelling is visible evi-dence of exfoliation corrosion. Exfoliation occurs on ex-truded, rolled, wrought and forged high strength aluminumand magnesium parts.
2.7.6 Crevice/Concentration Cell Corrosion. Crevicecorrosion occurs when the electrolyte has a different concen-tration from one area to another. Electrolyte inside the crev-ice contains less oxygen and more metal ions than electro-lyte just outside the crevice. As a result, the metal surfaces,even though they may be part of the same metal, have dif-ferent activities and corrosion occurs inside the crevice. Thiskind of corrosion also occurs when a surface is covered by aforeign material. There are three general types of crevice/concentration cell corrosion, (1) metal ion concentration cells(2) oxygen concentration cells, and (3) active-passive cells.(Refer to Figure 2-14).
Figure 2-7. Pitting of an Aluminum Wing Assembly
Figure 2-8. Cross-Section of Corrosion Pits
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2.7.6.1 Metal Ion Concentration Cells. Stagnant electro-lytes under faying surfaces will normally have a high con-centration of metal ions, while a low concentration of metalions will exist adjacent to the crevice created by the fayingsurface. The area of the metal in contact with the higherconcentration of metal ions will be cathodic and not showsigns of corrosion, but the area in contact with the lowermetal ion concentration will be anodic and suffer corrosion.Figure 2-14, View A, illustrates metal ion concentration cellcorrosion.
2.7.6.2 Oxygen Concentration Cells. Electrolyte in con-tact with metal surfaces will normally contain dissolved oxy-gen. An oxygen cell can develop at any point where theoxygen in the air is not allowed to diffuse into the solution,thereby creating a difference in oxygen concentration be-tween two points. Typical locations of oxygen concentrationcells are under either metallic or non-metallic deposits (dirt)on the metal surface and under faying surfaces such as riv-eted lap joints. Oxygen cells can also develop under gaskets,wood, rubber, plastic tape, and other materials in contact
Figure 2-9. Cross-Section of 7075-T6 Aluminum Alloy
Figure 2-10. Grain Structure of a CorrodingAluminum Surface
Figure 2-11. Intergranular Corrosion of 7075-T6Aluminum Adjacent to Steel Fastener
Figure 2-12. Example of Exfoliation
Figure 2-13. Another Example of Exfoliation
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with the metal surface. Corrosion will occur in the area oflow oxygen concentration (anode) as illustrated in Figure2-14, View B. Alloys, such as stainless steel, which owetheir corrosion resistance to surface passivity, are particu-larly susceptible to this type of crevice/concentration cellcorrosion.
2.7.6.3 Active/Passive Cells. Metals which depend on atightly adhering passive film, such as the oxide film on cor-rosion resistant steel, are prone to rapid corrosive attack byactive/passive cells. The corrosive action usually starts witha deposit of dirt or salt, which creates an oxygen concentra-tion cell. The passive film is then broken in the area of thesalt deposit and the more active metal beneath the passivefilm will be prone to corrosive attack. This small anodic areawill corrode rapidly due to the much larger area of the sur-rounding cathode (passive film). The result is rapid pitting ofthe surface, as illustrated in Figure 2-14, View C.
2.7.6.4 Stress Corrosion Cracking. Stress corrosioncracking (refer to Figure 2-15), is the intergranular or trans-granular cracking of a metal caused by the combined effectsof constant tensile stress (internal or applied) and corrosion.Internal or residual stresses are produced by cold working,forming, and heat treatment operations during manufactureof a part and remain concealed in the part unless stress reliefoperations are used. Other hidden stresses are induced inparts when press or shrink fits are used and when slightlymismatched parts are clamped together with rivets and bolts.All these stresses add to those caused by applying normalloads to parts in operation. Metals have threshold stressesbelow which stress corrosion cracking will not occur. Thisthreshold stress varies from metal to metal, is different fordifferent tempers of the same metal, and is different for eachof the three grain directions in which stress can be applied.
2.7.6.5 Associated Hazards. Stress corrosion cracking isan extremely dangerous type of failure because it can occurat stress levels far below the rated strength of a metal, start-ing from what is thought to be a very minor corrosion pit.Parts can completely sever in a split second or they can crackslowly, and the rate of cracking is very unpredictable in op-erating service. As an example, 7075-T6 aluminum alloy canfail by stress corrosion cracking when a stress which is only10% of its rated strength is present across the thickness of itsmetal grains or the short transverse grain direction.
2.7.6.6 Causes. Specific environments have been identi-fied which cause stress corrosion cracking of certain alloys.Salt solutions, seawater, and moist salt laden air may causestress corrosion cracking of heat treatable aluminum alloys,high strength steels, stainless steels, and some titanium al-loys. Magnesium alloys may stress corrode in moist air.Stress corrosion can be prevented by placing an insulating
barrier between the metal and the corrosive environment suchas protective coatings and water displacing corrosion pre-ventive compounds. Stress relief operations during fabrica-tion of parts will help because it lowers the residual stresslevel in the parts. Shot peening a metal increases resistanceto stress corrosion cracking by creating compressive stresseson the surface which must be overcome by an applied tensilestress before the surface sees any tension load.
2.7.7 Corrosion Fatigue. Corrosion fatigue is the crack-ing of metals caused by the combined effects of cyclic stressand corrosion and is very similar to stress corrosion crack-ing. No metal is immune to a reduction of its resistance tocyclic stressing if it is in a corrosive environment. Damagefrom corrosion fatigue is greater than the sum of the damagefrom both cyclic stresses and corrosion. Corrosion fatiguefailure occurs in two stages. During the first stage, the com-bined action of corrosion and cyclic stress damages the metalby pitting and crack formation in the pitted area. The secondstage is the continuation of crack propagation by a straightfatigue mode, in which the rate of cracking is controlled bythe stress concentration in the main cross section and thephysical properties of the metal. Fracture of a metal part dueto corrosion fatigue occurs at a stress far below the fatiguelimit even though the amount of corrosion may be very small.For this reason, protection of all parts subject to alternatingstress is particularly important, even in environments that areonly mildly corrosive. Preventive measures are the same asthose given above for stress corrosion cracking.
2.7.8 Filiform Corrosion. Filiform corrosion (refer to Fig-ure 2-17), is a special form of oxygen concentration cellcorrosion or crevice corrosion which occurs on metal sur-faces having an organic coating system. It is recognized byits characteristic wormlike trace of corrosion products be-neath the paint film. Filiform occurs when the relative hu-midity of the air is between 78 and 90%, and when the sur-face is slightly acidic. It starts at breaks in the coating system,such as scratches and cracks around fasteners and seams,and proceeds underneath the coating, due to the diffusion ofwater vapor and oxygen from the air through the coating.(Refer to Figure 2-18). Filiform corrosion can attack steel,magnesium, and aluminum surfaces, and may lead to moreserious corrosion in some locations. Filiform corrosion canbe prevented by storing equipment and aircraft in an envi-ronment with a relative humidity below 70%, by using coat-ing systems having a low rate of diffusion for oxygen andwater vapors, by maintaining coatings in good condition, andby washing equipment and aircraft to remove acidic con-taminants from the surface (such as those created by pollut-ants in the air). Maintain coatings in good condition (prompttouch-up around fasteners) and apply corrosion preventivecompounds (CPC’s) when paint is damaged.
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Figure 2-14. Concentration Cell Corrosion
Figure 2-15. Stress Corrosion Cracking
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2.7.9 Fretting Corrosion. This is a special form of con-centration cell corrosion which occurs in combination withsurface wear. The corrosion products increase the wear ofthe surface and the wear exposes more bare metal surface tobe corroded. The overall effect is greater than the single ef-fects of corrosion and wear added together. It has the generalappearance of galling, in which chunks of metal are tornfrom the surface with corrosion at the torn areas or raggedpits. This type of corrosion occurs on faying surfaces of closetolerance and on parts under high pressure in a corrosive
environment when there is slight relative movement of theparts such as that caused by vibration. Fretting corrosion isnormally encountered in heavily loaded static joints whichare subject to vibration and are not and/or cannot be sealedto prevent moisture entry, such as landing gear componentattachment areas having lug holes with slight press fits orslip fit bushings with very close tolerance bolts passingthrough the bushings. Another area is wing root access pan-els or wing-to-body fairings, which are generally not tightlysecured and cannot be sealed in faying surfaces.
Figure 2-16. Galvanic Series of Metals and Alloys in Sea Water
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2.7.10 High Temperature Oxidation (Hot Corrosion).Corrosion in the absence of water can occur at high tempera-tures, such as those found in turbine engine compressors andhot sections. When hot enough, metals can react directly withthe surrounding gases producing oxide scale (by-products ofoxidation). Contaminants, such as chlorides and sulfates (by-products of sulfidation), can accelerate the hot corrosion re-action by reducing the melting point of the metallic oxideand promoting its vaporization. High temperature ceramiccoatings can reduce this type of corrosion but are usuallyapplied only by the manufacturer due to highly specializedequipment required for application.
2.8 METALS AFFECTED BY CORROSION.
Characteristics of corrosion on metals are summarized inTable 2-1. The following is a discussion of corrosion char-acteristics of metals commonly used on aircraft, missiles,and related equipment.
2.8.1 Magnesium. Magnesium alloys are the lighteststructural metals used for aircraft and missile airframes.These alloys are highly susceptible to corrosion, which ap-pears as white, powdery mounds or spots when the metal
Figure 2-17. Filiform Corrosion Found Under Paint Coating on a Magnesium Panel
Figure 2-18. Schematic of the Development of Filiform Corrosion on an Aluminum Alloy
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surface is exposed to the environment without a protectivefinish. (Refer to Figure 2-19). The normal oxide-carbonatefilm formed on magnesium alloys does not provide sufficientcorrosion protection even in the mildest environment. Thecorrosion rate of a magnesium alloy increases when the al-loy is immersed in water, periodically subjected to moisture,coupled to a dissimilar metal, or exposed to water in whichconductive contaminants are dissolved. Corrosion of magne-sium alloys can be greatly diminished by the use of theproper protective finish. Some magnesium parts in currentaircraft and missiles have been originally protected by anod-izing processes, such as the ASTM D 1732, Class II, TypeIII (MIL-M-45202, Type I, Class A) HAE and the ASTM D1732, Class II, Type II (MIL-M-45202, Type I, Class C)DOW 17 coatings. The HAE process can be identified by thebrown to mottled gray appearance of the unpainted surface.DOW 17 coatings have a green to grayish-green color. Coat-ings of this type are thicker than those applied by immersionor brushing. Anodized finishes cannot be restored in the field.Care should be taken to minimize removal of these coatings.
2.8.2 Steel. Ferrous (iron) alloys are used to manufacturemany aircraft and missile components, and massive struc-tural assemblies in aircraft and missile ground support equip-ment, such as missile gantries, silo crib structures, framesand bodies of trailers and vans, and lesser structural partssuch as brackets, racks, and panels. If unprotected, ferrousalloy surfaces (with the exception of Corrosion ResistantSteels (CRES) or stainless steels) easily corrode or rust inthe presence of moisture. Ferrous alloy surfaces of structuresor assemblies are normally painted or plated and painted toprevent corrosion. Corrosion of steel is easily recognized be-cause the corrosion product is red rust. (Refer to Figure2-20). When ferrous alloys corrode, a dark corrosion productusually forms first, and when moisture is present, it convertsto red rust. Further attack is promoted by the rust absorbingmoisture from the air. Effective sacrificial coatings that pre-vent corrosion on ferrous alloys are cadmium plating or lowhydrogen embrittling zinc nickel (LHE Zn-Ni) plating perdrawing 201027456 (for all steels including high strengthsteels) or 201427084 (for low strength steel fasteners). LHE
Zn-Ni is an environmentally friendly alternative to cadmiumthat provides equivalent corrosion protection for ferrous al-loys including high strength steels. When switching fromcadmium to LHE Zn-Ni, the LHE Zn-Ni should be specifiedwith the same Type and Class (thickness) as the originalcadmium coating. Paint is often applied over cadmium orLHE Zn-Ni plated surfaces to provide additional protection.Testing has shown good performance when painting LHEZn-Ni coatings with epoxy primers per MIL-PRF-85582Type I, Class C2 or N or MIL-PRF-23377 Type I, Class C2or N.
2.8.3 Aluminum. Aluminum and its alloys are the mostwidely used materials for aircraft and missile construction.Aluminum is highly anodic as evidenced by its position inthe galvanic series. (Refer to Figure 2-16). However, the for-mation of a tightly adhering oxide film offers increased re-sistance under mild corrosive conditions. The corrosion prod-ucts of aluminum (refer to Figure 2-21), are white to graypowdery materials (aluminum oxide or hydroxide), whichcan be removed by mechanical polishing or brushing withabrasive. It is anodic to most other metals and, when in con-tact with them, galvanic corrosion of the aluminum will oc-cur. Aluminum alloys are subject to pitting, intergranularcorrosion, intergranular stress corrosion cracking, and corro-sion fatigue cracking. In some cases, the corrosion productsof the metal in contact with aluminum are corrosive to alu-minum. Therefore, it is necessary to clean and protect alumi-num and its alloys to prevent corrosion. Since pure alumi-num is more corrosion resistant as well as being more anodicthan most alloys, aluminum alloy sheet stock is often cov-ered with a thin layer of nearly pure aluminum called alclad.While fully intact, the alclad layer is very resistant to corro-sion because a very adherent oxide film rapidly forms on itssurface to protect it. Alclad is easily removed by harsh treat-ment with abrasives and tooling, exposing the more corro-sion susceptible aluminum alloy base metal surface. If thebreak in the alclad layer is small, the alclad will sacrificiallycorrode and protect the exposed base metal alloy because itis more anodic than the alloy. In such areas, chemical con-version coatings, paints, and corrosion preventive compoundsare especially important. In a marine environment, all alumi-num surfaces require protection.
2.8.4 Anodized Aluminum. Some aluminum parts areprotected with an electrochemically applied oxide coating(i.e., anodize). An aluminum oxide film on aluminum is anaturally occurring protective film, and anodizing merely in-creases the thickness and density of the oxide film. Whenthis coating is damaged in service, it can be only partiallyrestored by chemical conversion coating treatment of thedamaged area. (Refer to Chapter 5, Section II). Avoid dam-age (e.g., nicks and scratches) to the anodized surface duringprocessing of anodized aluminum alloy parts.
2.8.5 Titanium. Titanium and titanium alloys have manyuses in aircraft and missiles at temperatures up to 1,000° F(540° C). Above 1000° F, titanium readily absorbs gases fromthe surrounding air becoming very brittle. Titanium and its
Figure 2-19. Magnesium Corrosion Products
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alloys are highly corrosion resistant because an extremelyadherent oxide film forms on their surfaces almost immedi-ately upon contact with air and thus provides a protectivebarrier. This is identical to the way aluminum forms a pro-tective oxide film on its surface. Even at temperatures ap-proaching 1,000° F, titanium retains its strength and corro-sion resistance. When titanium is heated, different oxideshaving different colors form on the surface. A blue oxide
coating will form at 700° to 800° F (370° to 425° C), apurple oxide will form at 800° to 950° F (425° to 510° C),and a gray or black oxide will form at 1,000° F (540° C) orhigher. These are protective discolorations and should not beremoved. Titanium is the less active member (cathodic) ofmost dissimilar metal couples, and could possibly greatlyaccelerate corrosion of a dissimilar metal coupled to it.However, electrical insulation between titanium and other
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metals is provided by the rapidly formed, very adherent,non-conductive oxide film, which prevents galvanic corro-sion of the other metal. Frequent inspection of such areas isrequired to ensure that the oxide film has not failed and al-lowed corrosion to begin. Under certain conditions, chlo-rides and some chlorinated solvents may induce stress corro-sion cracking of certain titanium alloys.
2.8.6 Copper and Copper Alloys. Copper and copper al-loys are quite corrosion resistant and corrosion is usuallylimited to staining and tarnish. Generally, such changes insurface conditions are not dangerous and should ordinarilyhave no effect on the part. Copper corrosion is evidenced bythe accumulation of blue or blue-green corrosion productson the corroded part. Protective paint coatings are seldom
required because of the inherent resistance of the metal.However, paint finishes may be applied for decorative pur-poses or if the normal tarnish or green patina on the copperis objectionable. The green patina is merely a thin coatingconsisting mainly of basic copper sulfate and perhaps hy-drated copper carbonate. The patina in the thin, firmly adher-ing state actually offers increased corrosion protection to thebase metal, but the patina in a rough or frosted state shouldbe removed. When coupled with most metals used in aircraftconstruction, copper is the less active metal and greatly ac-celerates corrosion of the other metals. This is especiallytrue in copper/aluminum couples. Examples are usuallyfound in electrical components and in areas where copperbonding strips or wires are fastened to an aluminum chassisor structural components.
Figure 2-20. Steel Corrosion Products (Rust)
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Figure 2-21. Aluminum Surface Corrosion Products
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Table 2-1. Corrosion of Metals - Type of Attack and Appearance of Corrosion Products
Alloys Type of Attack to Which Alloy is Susceptible Appearance of Corrosion ProductMagnesium Alloy Highly susceptible to pitting. White, powdery, snow-like mounds, and
white spots on the surface.Low Alloy Steel (4000-
8000 Series)Surface oxidation and pitting; surface and inter-
granular corrosion.Reddish-brown oxide (rust).
Aluminum Alloy Surface pitting, intergranular, exfoliation, stresscorrosion and corrosion fatigue cracking, andfretting.
White to gray powder.
Titanium Alloy Highly corrosion resistant; extended or repeatedcontact with chlorinated solvents may result indegradation of the metal’s structural proper-ties.
No visible corrosion products at low tempera-ture. Various colored surface oxides de-velop above 700° F (360° C). Color depen-dant on temperature.
Cadmium (used as aprotective plating forsteel)
Uniform surface corrosion; used as sacrificialplating to protect steel.
From white powdery deposit to brown orblack mottling of the surface.
Stainless Steels (300-400 Series)
Crevice/concentration cell corrosion; some pit-ting in marine environments; corrosion crack-ing; intergranular corrosion (300 Series); sur-face corrosion (400 Series).
Rough surface; sometimes a red, brown, orblack stain.
Nickel-base Alloy (Inc-onel, Monel)
Generally has excellent corrosion resistancequalities; susceptible to pitting in sea water.
Green powdery deposit.
Copper-base Alloy,Brass, Bronze
Surface and intergranular corrosion. Blue or blue-green powdery deposit (patina).
Chromium (plate) Pitting (promotes rusting of steel where pits oc-cur in plate).
No visible corrosion products; blistering ofplating due to rusting of the base metal andlifting of plating.
Figure 2-22. Cadmium Plated Surface Conditions
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2.8.7 Cadmium. Metal parts are plated either to increasethe corrosion resistance of the parts or to develop certainphysical properties on the surface of the parts, such as abra-sion (wear) resistance and high temperature oxidation resis-tance. Parts may also be plated to create a compatible dis-similar metal contact, to provide a satisfactory surface forsoldering, or to provide a sacrificial metal layer. Cadmium isused as a coating to protect metal parts and to provide acompatible surface when a part is in contact with other ma-terials. Attack on cadmium is evidenced by brown to blackmottling of the surface or as white powdery corrosion prod-ucts. When cadmium shows mottling and isolated voids orcracks in the coating, the plating is still performing its pro-tective function. The cadmium plate on iron or steel contin-ues to protect until such time as actual iron rust appears.(Refer to Figure 2-22). Even then, any mechanical removalof corrosion products should be limited to metal surfacesfrom which the cadmium has been depleted.
2.8.8 CRES/Stainless Steel. Basically, stainless steels,or corrosion resistant steels (CRES), as they are more prop-erly described, are alloys of iron with chromium and nickel.Many other elements, such as sulfur, molybdenum, vana-dium, cobalt, columbium, titanium, and aluminum are addedin various amounts and combinations to develop specialcharacteristics. Stainless/CRES steels are much more resis-tant to common rusting, chemical action, and high tempera-ture oxidation than ordinary steels, due to the formation ofan invisible oxide film or passive layer on the surface ofthese alloys. Corrosion and heat resistance are the major fac-tors in selecting stainless/CRES steels for a specific applica-tion. However, it should be well understood that stainless/CRES steels are not the cure-all for all corrosion problems,due to service conditions which can destroy the oxide filmon their surfaces. Stainless/CRES steels are highly suscep-tible to crevice/concentration cell corrosion and stress corro-sion cracking in moist, salt laden environments and can causegalvanic corrosion of almost any other metal with whichthey are in contact if proper techniques of sealing and pro-tective coating are ignored. Stainless/CRES steels may bemagnetic or non-magnetic. The magnetic steels are identifiedby numbers in the American Iron and Steel Institute (AISI)400-Series, such as 410, 430, etc. These steels are not ascorrosion resistant as the non-magnetic steels which areidentified by numbers in the AISI 300-Series, such as 304,316, etc. The AISI 300-Series steels have nickel contentsranging from 6% to 22%, while the 400-Series steels havenickel contents of only 2%.
2.8.9 Nickel and Chromium. Nickel and chromium areused as protective platings. Chromium plating is also used toprovide a smooth, wear-resistant surface and to reclaim wornparts. Where corrosion resistance in a marine environment isrequired, a nickel undercoat is used. The degree of protec-tion is dependent upon plating thickness. Both of these met-als form continuous oxide coatings that can be polished to a
high luster and still protect not only themselves but also anyunderlying metal. Chromium platings contain micro-cracks,and corrosion/rust originates on the base metal below theseseparations and peels the plating from the surface. Figure2-22 shows the results of a failed chromium plate.
2.8.10 Silver, Platinum, and Gold. These metals do notcorrode in the ordinary sense, although silver tarnishes in thepresence of sulfur. The tarnish is a brown-to-black film. Goldtarnish is not really corrosion but is a very thin layer of soilsor contaminants that shows up as a darkening of the reflect-ing surfaces. All these metals are highly cathodic to almostall other metals and can cause severe galvanic corrosion ofalmost any metal with which they are in contact in the pres-ence of moisture if joint areas are not sealed or otherwiseinsulated.
2.8.11 Graphite/Carbon Fiber Composites. Graphite orcarbon fiber composites are materials which consist of rein-forcing fibers in a matrix, made of organic resin, usuallyepoxy. They are an important class of aviation materials be-cause of their high strength-to-weight ratios and high stiff-ness. Since carbon is the least active metal in the galvanicseries, it will accelerate the corrosion of any aircraft metal towhich it is coupled. Insulation between graphite or carbonepoxy composites and other metals is necessary to preventdissimilar metal attack on the attached part.
2.9 CORROSIVE ENVIRONMENTS.
Corrosion of aircraft, missiles, and equipment is caused byboth natural and man-made environments. Natural condi-tions, which affect the corrosion process, are moisture, tem-perature, salt atmospheres, ozone, sand, dust, solar radiation,insects and birds, and microorganisms. Man-made condi-tions, which also affect the corrosion process, are industrialpollution, manufacturing operations, storage conditions, andshipment. By understanding these conditions, maintenancepersonnel will be better able to prevent aircraft damage.
2.9.1 Moisture. Moisture is present in air as a gas (watervapor) or as finely divided droplets of liquid (mist or fog)and often contains contaminants such as chlorides, sulfates,and nitrates, which increase its corrosive effects. Moistureenters all areas of an aircraft or missile that air can enter. Allenclosed areas, which are not sealed, allow air to enter andleave as the difference in pressure between inside and out-side changes. These pressure differences occur when the air-craft changes altitude, when atmospheric pressure changes,and when the temperature of air inside an enclosed areachanges. Moisture will condense out of air when the air be-comes too cool to hold all of the moisture in it. The dewfound on aircraft and missile exteriors and many times ontheir interior surfaces after a cool night is the result of con-densation.
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2.9.1.1 Condensed Moisture. Condensed moisture willusually evaporate as surrounding air warms, but will leaveits contaminants (residues), including salts, behind. This canresult in the buildup of soils and salt contamination. Con-densed moisture and its contaminants can also be trapped inclose fitting wettable joints, such as faying surfaces. Somegasket and packing materials will absorb several times theirweight in water and, when heated, can transmit this retainedmoisture into the sealed area. Moisture can accumulate insuch areas through successive cycles of warming and cool-ing leaving pools of moisture and a relative humidity ap-proaching 100%. This is known as the desert still effect. Inaddition, moisture can be drawn into poor bond lines bycapillary action (wicking). Conditions of temperature andhumidity can vary widely in separate sections of aircraft de-pending on the success of environmental sealing condensa-tion and location near heat-generating equipment.
2.9.1.2 Effect of Moisture. Electrolyte formation resultsfrom condensation and/or collection of moisture. All non-metals absorb some moisture, which may cause changes indimensional stability, dielectric strengths, ignition voltages,and volume insulation resistances. In general, organic matrixcomposites are adversely affected by moisture and may suf-fer a loss of strength and stiffness from exposure. Hermeticsealing (liquid and vapor proof at normal temperatures andpressures) is recommended for moisture-critical items suchas capacitors and quartz crystals. Refer to TO 1-1-689 seriesfor additional information related to electronics equipment.
2.9.2 Temperature. Temperatures at the high end of therange for which equipment is designed may result in eitherimprovement or degradation of equipment, depending on
conditions. Some electronic equipment may not functionproperly at high temperatures. Generally, corrosion and otherharmful processes (such as the degradation of non-metallicmaterials) increase as temperatures rise, but in some in-stances, moderate increases in temperature may serve to re-duce corrosion by preventing condensation. Growth of moldsand bacteria is also inhibited by temperatures above 104° F(40° C). Temperatures at the low end of the design rangegenerally reduce the rate of corrosion.
2.9.3 Salt Atmospheres. When dissolved in water, saltparticles form strong electrolytes. The ocean, which carriesfrom 3.5 to 3.9% salt, is the world’s primary source of salt.Normal sea winds carry from 10 to 100 pounds of sea saltper cubic mile of air. Since dissolved salts are strong elec-trolytes, it is easy to understand why shipboard and coastalenvironments are highly corrosive.
2.9.4 Ozone. Ozone is a particularly active form of oxy-gen, which is formed naturally during thunderstorms, by arc-ing in electrical devices, and by photochemical reactions insmog. When ozone is absorbed by electrolyte solutions incontact with metals, it increases the rate of corrosion. It alsooxidizes many non-metallic materials, being particularlyharmful to natural and certain types of synthetic rubber.Rubber seals stored near welding equipment have experi-enced complete degradation.
2.9.5 Other Industrial Pollutants. Carbon (from internalcombustion engine exhaust), nitrates (from agricultural fer-tilizers), ozone (from electrical motors and welding opera-tions), sulfur dioxide (from engine exhaust and industrial and
Figure 2-23. Failed Chromium Plating
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ship smoke stacks), and sulfates (from automobile exhaust)are important airborne pollutants. The combination of thesepollutants contributes to the deterioration of non-metallicmaterials and severe corrosion of metals.
2.9.6 Sand, Dust, and Volcanic Ash. Sand, dust, andvolcanic ash are present in many areas. In industrial areas,they often contain a number of tar products, ashes, and soot.Dust is also found in the tropic zones during times of little orno rainfall. Sand and dust are extreme problems in the des-erts, since dry, powdery sand and dust are carried by wind.During sandstorms, they can penetrate sealed equipment aswell as many internal areas of airframes, and small sandparticles are often blown as high as 10,000 feet by the siroc-cos hot, dust laden winds). Sand, dust, and volcanic ash arehygroscopic and, when present on internal or external sur-faces of aircraft or electronic parts, can absorb and holdmoisture. The presence of sand, dust, and volcanic ash mayalso effect the operation of electrical contacts, prevent properaction of rotating motor-drive devices, and cause malfunc-tions of indicating instruments. Dust from volcanic areascontains chlorides and sulfates, which are extremely corro-sive in the presence of moisture. Although small amounts ofsand or dust may be unnoticed by operating personnel, theymay be sufficient to promote corrosion and wear.
2.9.7 Solar Radiation. The two ranges of solar radiationmost damaging to materials are ultraviolet, the range thatcauses sunburn, and infrared, the range that makes sunlightfeel warm. On earth, maximum solar radiation occurs in thetropics and equatorial regions, but considerable damage oc-curs in the temperate zones as a result of solar heating, pho-tochemical effects, and combinations of these two phenom-ena. Non-metals, especially organic and synthetic materials,are strongly affected by sunlight. Both natural and syntheticrubber deteriorates rapidly in sunlight. After extended expo-sure, plastics darken, paints lose their protective characteris-tics, polymers undergo marked decreases in strength andtoughness, and colors fade. This can lead to removal of es-sential color-coding on tubing and electronic components.Most electronic equipment is housed in enclosed structuresand is protected from solar radiation. Extra care must betaken in the selection and surface treatment of parts, such ascables and harnesses that are to be exposed to exterior envi-ronments.
2.9.8 Climate. Warm, moist air, normally found in tropi-cal climates, tends to accelerate corrosion while cold, dry air,normally found in arctic climates, tends to reduce corrosionrates. Corrosion does not occur in very dry conditions. Forthis reason, desiccants are used in shipping containers toproduce very dry local environments. The operational cli-mate extremes have always been considered in aircraft de-sign. However, certain areas within an aircraft, such as thecockpit and air-conditioned equipment bays, may be sub-jected to climatic conditions very different from external ar-eas of the aircraft. Relatively warm, dry air that has beencooled by air conditioners, thus increasing its relative hu-midity, and ducted into interior areas of the aircraft withoutdrying or passing it through an expansion valve can release
sufficient moisture to accelerate corrosion. It is imperative toconsider not only the exterior operational environment butalso the environments in which the equipment will be fabri-cated, transported, reworked, repaired, and mounted insidethe aircraft or missile.
2.9.8.1 Desert. Hot, wind-swept deserts create a severemaintenance problem because powdery dust can penetrateeven supposedly sealed components. High daytime tempera-tures, high humidities (in areas such as the Persian Gulf),ultraviolet radiation, and fine dust are the four most serious,destructive elements of the desert climate. Non-metallic ma-terials suffer the most damage from the hot desert climateswhere air temperature during the day may reach 124° F (51°C). Temperatures inside closed containers may be 100° F(38° C) higher than external air temperatures.
2.9.8.2 Temperate Zones. The temperate or intermediateclimate zone encompasses most of the North American andEuropean continents. These areas at various times of the yearmay approximate the extremes of polar, desert, or tropicaltemperatures and humidity. The temperate zone temperaturesrange from -25° to +59° F (-32° to +15° C) in the winter andfrom +59° to +125° F (+15° to +52° C) in the summer. Therelative humidity (RH) also fluctuates between 5 and 100.The most critical areas are coastal locations during the warmperiods of the year in which the RH approaches 100% atnight and the air has high concentrations of salt. Moisturefrom this salt-laden air can condense on equipment duringearly evening and morning hours, thereby causing seriouscorrosion. Because of its relatively mild temperatures, thetemperate zone is also the most heavily populated. Conse-quently, the smoke, smog, ozone, and corrosive fumes asso-ciated with heavy industry are also found there.
2.9.8.3 Tropics. The greatest challenge to the aircraft andmissile industries is to the design equipment that is protectedfrom corrosion and deterioration in the heat and humidity oftropical climates. Even though they encompass only a smallportion of the earth’s land area, the tropics demand thegreatest amount of consideration from the standpoint of cor-rosion treatment and control. Relative humidities of up to100% at ambient (room) air temperatures of 85° F (29° C)and above create a formidable threat of corrosion. When highhumidity and temperature conditions are combined with salt-laden air, the corrosive environment becomes extremely se-vere. The critical combination of high temperatures, conden-sation, high relative humidity, and contaminants such as saltand sand, may cause catastrophic failure of equipment. De-terioration of the materials used in electronic equipment mayalso be accelerated.
2.9.9 Factors of Influence in Tropical Environments.Tropical environments are noted for long periods of heavyrainfall during which 100 inches or more of rain may fall.Extended periods of high heat and humidity contribute torapid corrosion of metals, cracking and flaking of rubber andplastic materials, and deterioration of seals. Equipment,whether stored or in use, requires special protective contain-
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ers/measures and frequent preventive maintenance. microor-ganisms multiply excessively in tropical environments andattack many non-metallic materials. Many items becomecovered with fungi in a matter of hours. Electronic equip-ment requires special efforts for effective operation in thetropics. Intensive preventive maintenance and the best pos-sible protective techniques are necessary for aircraft, mis-siles, and their components in tropical environments.
2.9.10 Manufacturing. During the manufacture, assembly,or repair of aircraft, missiles, and their subsystems, manyfactors that might lead to corrosion may be introduced. Theuse of unsuitable materials and improper materials process-ing can cause corrosion. The shearing or hole-punching op-erations on some metal alloys, especially high strength alu-minum, may introduce stresses that eventually lead to stresscorrosion cracking. Assembly of parts in areas contaminatedby fumes or vapors from adjacent operations may result inentrapment of the fumes or vapors in the equipment whichmay cause future corrosion. Spaces that are air conditionedwithout humidity control may be sources of condensed mois-ture.
2.9.11 Storage. Even traces of corrosive vapors in pack-ages containing aircraft or missile parts may result in seriouscorrosion. Moreover, the natural breathing of packages mayintroduce moisture into the parts and equipment. Some pack-ing materials have been known to decompose and emit cor-rosive vapors during periods of prolonged storage. Refer toTO 1-1-17 and the system specific (-17) manual for addi-tional storage information.
2.9.12 Shipment. During shipment, materials such asplastics and lubricants are often exposed to environmentsthat were not considered during the design stage. Materialsshipped by air are subjected to changes in atmospheric pres-sure and can lose volatile components by out-gassing. Thevibration and mechanical shocks associated with shipmentby truck can damage protective coatings or platings. Ship-ment by ocean vessel may expose the equipment to corro-sive marine environments, vibrations and shock from enginesor sea conditions, and residual corrosive vapors from previ-ous shipments. Although packaging equipment in accordancewith MIL-STD-2073-1 will protect the equipment from cor-rosive environments, packaging may be damaged duringhandling and thus become ineffective.
2.9.13 Industrial and Ship Emitted Air Pollutants.Smog, smoke, soot, and other airborne contaminants are ex-tremely corrosive to exposed aircraft, missiles, and equip-ment. Many of the fumes and vapors emitted by ships andfrom factories can greatly accelerate metal corrosion. Indus-trial atmospheres may exist over large areas, since wind maycarry these corrodents many miles from their source. Gener-ally, air pollutants, when combined with water, create elec-trolytic solutions and accelerate corrosion.
2.9.14 Animal Damage. Damage to aircraft, missiles, andtheir subsystems may be caused by insects, birds, and vari-ous small animals, especially in tropical environments.
Equipment in storage is most susceptible to this type of at-tack, since animals may enter through vent holes or tears inpackaging and sometimes build nests. Moisture absorbed bynests plus excretions from animals may cause corrosion anddeterioration that goes unnoticed until equipment is put intouse and fails. Another type of damage may occur when or-ganic materials, such as upholstery, are shredded for nests orconsumed as food.
2.9.15 Microorganisms. Microbial attack includes the ac-tion of bacteria, fungi, or molds. Microorganisms are nearlyeverywhere and outnumber all other types of living organ-isms. Organisms that cause the greatest corrosion problemsare bacteria and fungi. Damage resulting from microbialgrowth can result from (1) the tendency of the growth tohold moisture which then causes corrosion, (2) digestion ofthe substrate as food for the microorganism, or (3) corrosionof the surface beneath the growth by secreted corrosive flu-ids
2.9.15.1 Bacteria. Bacteria may be either aerobic or an-aerobic. Aerobic bacteria require oxygen to live. They canaccelerate corrosion by oxidizing sulfur to produce sulfuricacid or ammonia to produce nitric acid. Bacteria living on oradjacent to metals may promote corrosion either by deplet-ing the oxygen supply or by releasing metabolic products.Anaerobic bacteria, on the other hand, can survive only whenfree oxygen is not present. The metabolism of these bacteriarequires them to obtain food sources by oxidizing inorganiccompounds such as iron, sulfur, hydrogen, and carbon mon-oxide. The resultant chemical reactions cause corrosion.
2.9.15.2 Microbial Growth Requirements. Fungi makeup one class of microorganisms that feed on organic matter.Low humidity levels inhibit the growth of most species offungi and bacteria. Ideal growth conditions for most fungiand bacteria are temperatures of +68° to +104° F (+20° to+40° C) and relative humidities of 85 to 100%. It was for-merly believed that microbial attack could be prevented byapplying moisture-proof coatings to nutrient materials or bydrying the interiors of compartments with desiccants. How-ever, some moisture-proof coatings are attacked by microor-ganisms, especially if the surface to which they are appliedis contaminated. Some microorganisms can survive in sporeform for long periods while dry and can become active whenmoisture is available. When desiccants become saturated,they form what is known as a “desiccant pump” whichpumps their absorbed moisture into the affected area byevaporation and allows microorganisms to begin to grow.Dirt, dust, and other airborne contaminants are the least rec-ognized contributors to microbial attack. Unnoticed, smallamounts of airborne debris may be sufficient to promote fun-gal growth by absorbing moisture.
2.9.15.3 Microbial Nutrients. Since fungi, bacteria, andother microorganisms are classified as living, it was previ-ously thought that only materials derived from living organ-isms could provide them with food. Thus wool, cotton,feathers, leather, etc., were known to be microbial nutrients.To a large extent, this rule of thumb is still valid but the
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increasing complexity of synthetic materials makes it diffi-cult, if not impossible, to determine from the name alonewhether a material will support growth of microorganisms.Many otherwise resistant synthetic materials are renderedsusceptible to microbial attack by the addition of chemicalswhich change the properties of the material. In addition, dif-ferent species of microorganisms have different growth re-quirements. The service life, size, shape, surface smooth-ness, cleanliness, environment, and species of microorganisminvolved all determine the degree of microbial attack on theaffected item.
2.10 DEGRADATION OF NON-METALS.
Non-metallic materials (plastics, elastomers, paints, and ad-hesives) are not subject to electrochemical corrosion, sinceions are not easily formed from non-metallic materials andtheir electrical conductivity is extremely low. The degrada-tion of non-metals depends on the chemical makeup of thematerial and the nature of the environment. In general, non-metallic materials on aircraft, missiles, and related equip-ment are selected for their obvious performance properties(flexibility, transparency, strength, electrical resistance, etc.,)as well as their resistance to heat, impact, abrasion, ultravio-let radiation, moisture, ozone and other detrimental gases,and operational fluids such as hydraulic fluid, lube oil, clean-
ers, deicing fluids, etc. However, the use of unauthorizedmaintenance chemicals and procedures can accelerate degra-dation and ultimately lead to material failure resulting inleakage, corrosion, electrical shorts, crazing, and/or mechani-cal failure.
2.11 PREVENTIVE MAINTENANCE.
The two most important factors in preventing corrosion, andthe only ones which can be controlled by field personnel, arethe removal of the electrolyte and the application of protec-tive coatings. Since the extent of corrosion depends on thelength of time electrolytes are in contact with metals, corro-sion can be minimized by frequent washing. If noncorrosivecleaners are used, the more frequently a surface is cleaned ina corrosive environment the less the possibility of corrosiveattack. In addition, by maintaining chemical treatments, paintfinishes, lubricants, and corrosion preventive compounds(CPC’s) in good condition, corrosion can be minimized. Thedegradation of non-metallic materials can be minimized byavoiding the use of unauthorized maintenance chemicals andprocedures. In addition, when repair or replacement of non-metallic materials is required, use only approved materials.Dedication to proper preventive maintenance practices maxi-mizes equipment reliability.
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CHAPTER 3PREVENTIVE MAINTENANCE
SECTION I INTRODUCTION
3.1 PREVENTIVE MAINTENANCE PROGRAM.
As directed by AFI 20-114, the prevention and control ofcorrosion on aircraft missiles and related equipment is acommand responsibility. Each command must place specialemphasis on the importance of the corrosion control pro-gram and lend its full support to ensure that corrosion pre-vention and control receives sufficient priority to be accom-plished along with other required maintenance.
3.1.1 Preventive Maintenance. Aluminum and magne-sium alloys found in aviation equipment will corrode if saltdeposits, other corrosive soils, or electrolytes are allowed toremain on their surfaces. To prevent corrosion, a constantcycle of cleaning, inspection, operational preservation, andlubrication must be followed. Prompt detection and removalof corrosion will limit the extent of damage to aircraft com-ponents. An effective preventive maintenance program re-quires all of the procedures specified in this chapter, but alsoincludes corrosion removal, paint removal, surface treatment,sealing, and painting. A disciplined preventive maintenanceprogram includes the following:
a. Regularly scheduled aircraft washing as specified inTable 3-1.
b. Regularly scheduled cleaning or wipe down of all ex-posed unpainted surfaces, such as landing gear strutsand actuating rods of hydraulic cylinders with a com-patible fluid or lubricant as specified by system spe-cific technical orders.
c. Keeping low-point drains open.
d. Inspection, removal, and reapplication of corrosionpreventive compounds (CPC’s) on a scheduled basis.
e. Earliest detection and repair of damaged protectivecoatings.
f. Use clean/fresh potable water for all aircraft, missile,and equipment washing and rinsing operations.
g. If using closed-loop water recycling systems for wash-ing aircraft, water shall meet the following require-ments and be tested every 30 days to detect anybuild-up of corrosive salts and/or other contaminants.Any abnormal readings should be reported to theAFCPCO for waiver consideration.
(1) Chloride content shall be 400 mg/L maximum(somewhat higher than EPA potable drinking wa-ter standard of 250 mg/L).
(2) pH shall be between 6.5 and 8.5.
(3) Total dissolved solids (TDS) content shall be 500mg/L maximum.
(4) Total suspended solids (TSS) content shall be 5mg/L maximum.
(5) The Langlier Saturation Index shall be slightlyabove 0.
(6) The biological oxygen demand (BOD) concentra-tion shall be 5 mg/L maximum.
(7) Adequate disinfection of the water shall be pro-vided to control the growth of microorganisms inthe water.
(8) The water hardness shall be between 75 and 150mg/L as CaCO3.
(9) The total petroleum hydrocarbon (TPH) contentshall be 10 mg/L maximum.
h. Use padded panel racks to store panels/parts for air-craft and equipment during maintenance; use protec-tive measures to prevent abrasions/scratches resultingfrom placement of parts, tools, tool boxes, etc., onwings, fuselage or other aircraft surfaces.
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Change 3 3-1
Table 3-1. Aircraft Wash Intervals
Air Base Name and Location Wash Interval by Severity* Asterisks before Air base Name and Location designatesenvironments considered as SWA and fall under Chapter 9.
Severe (30Days)
Moderate (90Days)
Mild (180Day)
*Afghanistan (All Locations) X*Aj Taif, SA X*Al Dhafra UAE X*Al Jouf, SA X*Al Udeid AB QATAR X*Ali Al Salem Kuwait XAllen C. Thompson Fld.; Jackson, MS XAltus AFB, OK XAnderson AFB, GU XAnchorage IAP, AK XAndrews AFB, MD (Washington DC) X*As Sulayyil, SA XAtlantic City, NJ XAviano AB, IT X*Bahrain X*Balad, Iraq XBangor IAP, ME XBarksdale AFB; Shreveport, LA XBarnes M. Apt.; Westfield, MA XBattle Creek, MI XBeale AFB; Marysville, CA XBirmingham Apt.; AL XBoise Air Term., ID (ANG) XBradley IAP; Windsor Locks, CT XBrindisi/Casale AB, IT XBuckley ANGB; Denver, CO XBurlligton IAP, VT XByrd Fld.; Richmond,VA X*Camp Lemonnier, Djibouti XCannon AFB; Clovis, NM XCapital Mun. Apt.; Springfield, IL XChannel Island; Port Hueneme NAS, CA XCharleston AFB, SC XCharleston Apt.; WV XCheyenne Apt.; WY XColumbus AFB, MS XCreech AFB, NV XCuracao Netherlands Antilles X*Cyprus International Airport XDanelly Fld.; Montgomery, AL XDavis-Monthan AFB; Tucson, AZ XDes Moines IAP, IA X*Dhahran, SA XDiego Garcia XDobbins ARB; Marietta, GA XDouglas IAP; Charlotte, NC XDover AFB, DE X
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3-2 Change 14 All data on pages 3-2.1 through 3-2.2 deleted
Table 3-1. Aircraft Wash Intervals - Continued
Air Base Name and Location Wash Interval by Severity* Asterisks before Air base Name and Location designatesenvironments considered as SWA and fall under Chapter 9.
Severe (30Days)
Moderate (90Days)
Mild (180Day)
Duluth IAP, MN XDyess AFB; Abilene, TX XEareckson (Shemya) AFB, Aleutian Is., AK XEast. WV Reg. Apt.; Martinsburg, WV XEdwards AFB; Rosamond, CA XEglin AFB; Valparaiso, FL XEglin AFB (Aux Fld.; #3), FL XEielson AFB, AK XEllington Fld.; Houston, TX XEllsworth AFB; Rapid City, SD XElmendorf AFB; Anchorage, AK XFairchild AFB; Spokane, WA XFairford, UK XFalcon AFB, CO XForbes Fld.; KS XFort Kutaka Army Base, AZ XFort Rucker, Enterprise, AL XFort Smith Mun. Apt.; AR XFort Wayne Apt.; IN XFrancis E. Warren AFB; Cheyenne, WY XFresno Air Term., CA XGeilenkhirchen, GE XGen. Mitchell IAP; Milwaukee, WI XGrand Forks AFB; Emarado, ND XGreat Falls IAP, MT XGreater Peoria Apt.; IL XGriffiss AFB; Rome, NY XGrissom ARB; Peru, IN XHancock IAP; Syracuse, NY XHanscomb AFB; Bedford, MA XHarrisburg IAP, PA XHector IAP; Fargo, ND XHickam AFB; Honolulu, HI XHill AFB; Ogden, UT XHolloman AFB; Alamogordo, NM XHomestead ARB, FL XHoward AB; Panama XHulman Reg. Apt.; IN XHurlburt Fld.; Fort Walton Beach, FL X*Incirlick AB, Turkey XIstres AB, France XJacksonville IAP, FL X*Jeddah, SA XJoe Foss Fld.; Sioux Falls, SD XKadena AB, Japan XKeesler AFB; Biloxi, MS XKey Fld.; Meridian, MS X
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Change 14 3-3
Table 3-1. Aircraft Wash Intervals - Continued
Air Base Name and Location Wash Interval by Severity* Asterisks before Air base Name and Location designatesenvironments considered as SWA and fall under Chapter 9.
Severe (30Days)
Moderate (90Days)
Mild (180Day)
*Khamis Mushay, SA X*Khandahar Afghanistan X*Kiruk Iraq X*King Khalid, SA XKingsley Fld.; Klamoth Falls IAP, OR XKirtland AFB, NM; Albuquerque, NM XKulis ANGB, Anchorage, AK XKunsan AB; S. Korea XLackland AFB, TX XLajes Fld.; Azores, Portugal XLambert Fld.; St. Louis IAP, MO XLangley AFB; Hampton, VA X*Larnaka International Apt.; Cyprus XLaughlin AFB; Del Rio, TX XLincoln Mun. Apt.; NE XLittle Rock AFB, AR XLuke AFB; Glendale, AZ XMacDill AFB; Tampa, FL XMalmstrom AFB; Great Falls, MT XManas Kyrgystan XMansfield Lahm Apt.; OH XMantas Ecuador XMarch ARB; Riverside, CA XMartin St. Apt.; Baltimore, MD XMaxwell AFB; Montgomery, AL XMcChord AFB; Tacoma, WA XMcConnell AFB, Wichita, KS XMcEntire ANGB; Columbia, SC XMcGhee Tyson Apt.; Alcoa, TN XMcGuire AFB; Wrightstown, NJ XMcMurdo Station Antarctica XMemphis IAP, TN XMinot AFB, ND XMinn.-St. Paul IAP, MN XMisawa AB, Japan XMoffett Fld.; CA XMoody AFB; Valdosta, GA XMoron AB, Spain XMountain Home AFB; Boise, ID XNAS Fort Worth, TX XNAS Keflavik, Iceland XNAS New Orleans, LA XNAS Pensacola, FL XNAS Sigonella; Sicily, Italy XNashville Met. Apt.; TN XNellis AFB; Las Vegas, NV XNewburgh Apt.; NY X
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3-4 Change 14
Table 3-1. Aircraft Wash Intervals - Continued
Air Base Name and Location Wash Interval by Severity* Asterisks before Air base Name and Location designatesenvironments considered as SWA and fall under Chapter 9.
Severe (30Days)
Moderate (90Days)
Mild (180Day)
New Castle Co. Apt.; Wilmington, DE XNiagra Falls IAP, NY XOffutt AFB; Omaha, NE XO’Hare IAP; Chicago, IL XOsan AB; S. Korea XOtis ANGB; Falmouth, MA XPatrick AFB; Cocoa Beach, FL XPease ANGB; Portsmouth, NH XPeterson AFB; Colorado Springs, CO XPittsburgh IAP, PA XPope AFB; Fayetteville, NC XPortland IAP, OR X*Prince Sultan AB, Al Kharj, SA XPuerto Rico IAP/Muniz ANGB; San Juan, PR XQuonset St. Apt.; Providence, RI X*RAF Akrotiri, Cyprus XRAF Lakenheath, UK XRAF Mildenhall, UK XRAF Waddington, UK XRamstein AB, GE X XRandolph AFB; San Antonio, TX XReno/Tahoe IAP, NV XRhein-Main, GE XRickenbacker IAP; Columbus, OH X*Riyadh, SA XRobins AFB; Warner Robins, GA XRosecrans Mem. Apt.; St. Joseph, MO XSalt Lake City IAP, UT XSchenectady Co. Apt.; NY XScott AFB; Belleville, IL XSelfridge ANGB; Mount Clemens, MI XSeymour Johnson AFB; Goldsboro, NC XShaw AFB; Sumter, SC XSheppard AFB; Wichita Falls, TX XSioux Gateway Apt.; Sioux City, IA XSouda Bay, Crete XSky Harbor Apt.; Phoenix, AZ XSpangdalhem AB, GE XSpringfield-Bleckley Mun. Apt.; OH XStandiford Fld./Lvle. IAP; Louisville, KY XSuffolk Co. Apt.; NY X*Tabuk, SA XTaegu, S. Korea X*Talil Iraq XTinker AFB; Oklahoma City, OK X*Thumrait Oman XToledo Exp. Apt.; Swanton, OH X
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Change 14 3-5
Table 3-1. Aircraft Wash Intervals - Continued
Air Base Name and Location Wash Interval by Severity* Asterisks before Air base Name and Location designatesenvironments considered as SWA and fall under Chapter 9.
Severe (30Days)
Moderate (90Days)
Mild (180Day)
Travis AFB; Fairfield, CA XTravis Fld.; Savannah, GA XTruax Fld./Dane City Reg. Apt.; Madison, WI XTucson IAP, AZ XTulsa IAP, OK XTyndall AFB; Panama City, FL XUSAF Academy, CO XVance AFB; Enid, OK XVandenburg AFB; Lompoc, CA XWestover AFB; Chicopee, MA XWhiteman AFB; Knobnoster, MO XWillow Grove ARS; Philadelphia, PA XWill Rogers IAP; Oklahoma City, OK XWright-Patterson AFB; Dayton, OH XYokota AB, Japan XYoungstown-Warren Reg. Apt.; ARS, OH X
SECTION II CLEANING
3.2 INTRODUCTION.
• Authorized cleaning agents and equipment arelisted in this chapter, Appendix A, and Appen-dix B. Order materials and equipment by NSNfrom the lists in these appendices through regu-lar supply channels, or local purchase fromvenders listed on the most current QPL/QPD ofa specification or by vender part number listedin these appendices for an authorized non-specification material.
• Specification QPL/QPD’s are the responsibilityof the authority for the specification. For infor-mation access, many cleaning and corrosionprevention and control process related specifi-cations having a QPL/QPD are available, withtheir most current revision, from the AF Portal.Search “AFCPCO”, or the Defense TechnicalInformation Center (DTIC) Scientific and Tech-nical Information Network web site: http://sti-net.dtic.mil.
• Do not use unauthorized cleaners. Althoughother commercial cleaners may appear to per-form as well as, or better than, approved prod-ucts, these materials may be corrosive to metalalloys used in aircraft, missiles, and relatedequipment. They can also accelerate degrada-
tion of non-metallic materials causing materialfailures which may result in fluid leakage, cor-rosion of surrounding metals, electrical shorts,crazing, and/or mechanical failure.
NOTE
Ozone depleting substances (ODS) are solventssuch as, but not limited to, 1,1,1 trichloroethane(MIL-T-81533) and trichlorotrifluoroethane (MIL-C-81302). These solvents, as well as productscontaining them, are still used in some aircraftmaintenance processes, including oxygen systemscleaning and some avionics cleaning. Alternatematerials continue to be identified. Wherever pos-sible, specifications are being changed to elimi-nate their use automatically. Some products thathave been reformulated are now flammable. Payclose attention to all CAUTION/WARNING labelson solvents and solvent-based products.
3.2.1 Reasons for Cleaning. Aircraft cleaning is the firststep in preventing aircraft corrosion. Cleaning requires aknowledge of the materials and methods needed to removecorrosive contaminants and fluids which tend to retain con-taminants. Clean aircraft, missiles, and related equipmentregularly in order to:
a. Prevent corrosion by removing salt deposits, other cor-rosive soils, and electrolytes.
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3-6 Change 14
b. Maintain visibility through canopies and windows.
c. Allow a thorough inspection for corrosion damage;aircraft washing before Isochronal (ISO)/Phase inspec-tions is strongly recommended to facilitate corrosioninspections.
d. Maintain turbine engine efficiency.
e. Reduce fire hazards by the removal of accumulationsof leaking fluids.
f. Improve overall appearance.
g. Ensure aerodynamic efficiency of the aircraft.
h. Maintain paint scheme characteristics.
3.2.2 When to Accomplish Work. Accomplish cleaningand related treatments at the frequency prescribed in thisSection, or more frequently if inspection indicates the need.Inspect areas of missiles not protected from the elements(e.g. rain, dust, snow, etc.,) daily. The Aircraft System Pro-gram Director (SPD) in conjunction with the Using Com-mand and the Air Force Corrosion Prevention and ControlOffice (AFCPCO) shall establish aircraft wash cycle require-ments. The unit Commander shall establish a definite sched-ule for inspection, cleaning, and corrosion treatment of theunit’s assigned aircraft, missiles, and equipment, and may athis/her discretion direct a wash cycle that is more frequent(not less frequent) than the established aircraft wash cycle toensure optimum corrosion protection and to promote theprofessional appearance of assigned aircraft, missiles, andequipment.
3.2.2.1 Cleaning Frequency. Base locations not listed inTable 3-1 will use the requirements of the nearest base loca-tion unless within 1.25 miles of salt water. All locationswithin 1.25 miles of salt water are considered severe andrequire 30 day wash. Contact AFCPCO for further guidanceif needed. The frequency of inspection, cleaning, and relatedcorrosion treatment depends on the type of systems assigneddeployments to corrosive environments well as the existinglocal environmental and other conditions. Table 3-1 specifiesthe required aircraft/weapon system wash interval by base orlocation as dictated by existing, recorded environmental andpollution data at each base and/or location unless a differentinterval is specified in a system specific technical order. Un-der certain local conditions, depending on aircraft type andusage, the established wash cycle may be insufficient. Sometypes of aircraft, missiles, and related equipment may re-quire more frequent cleaning of affected areas.
NOTE
When unique operational requirements, contingen-cies, droughts, or facility limitations severely im-pact a unit’s ability to wash as prescribed in Table
3-1. The requirement may be temporarily waivedtwo wash cycles not to exceed one year and ap-proved by the Aircraft System Program Director(SPD). The MAJCOM Corrosion Program Man-ager and AFCPCO shall be notified of all approvedwaivers to monitor for trends.
a. Excessive exhaust or gun blast soil and exhaust gasesaccumulate within impingement areas.
b. Paint is peeling, flaking, or softening.
c. Fluid leakage (coolant, hydraulic fluid, oil, etc.,) oc-curs.
d. Exposure to salt spray, salt water, or other corrosivematerials occurs.
e. Treated with deicing/anti-icing fluids. Deicing residueshould be removed at the first wash following the win-ter season. Refer to Table 3-3 for inspection and clean-ing instructions.
f. Deployments to corrosive environments with no or in-adequate wash capability.
3.2.3 Aircraft Clear Water Rinse (CWR) Require-ments.
Clear water rinsing shall not be accomplished out-side when the temperature is at 40° F (4° C) orbelow. Spraying flight control areas outside withwater when the temperature is below freezing canresult in ice that could impair flight controls.
Aircraft exposed to a salt water environment require clearwater rinse (CWR). Specific rinse requirements are as man-dated by aircraft station location, aircraft runway approach,and mission requirements.
3.2.3.1 Aircraft Stationed Within 1.25 Miles of SaltWater. All aircraft stationed within 1.25 miles (2 km) of saltwater require a CWR at least once every 15 days unlesswashed first.
3.2.3.1.1 Deployed Aircraft to Stations Within 1.25Miles (2KM) of Salt Water. All aircraft deployed to stationswithin 1.25 miles (2 km) of salt water for 10 days or moremust follow the CWR requirements of the deployment loca-tion. Deployment locations where mission requirementsand/or facilities limitations prevent accomplishment of CWR,the aircraft forms will be documented to require a CWR beperformed within 3 days of return to home station. Aircraftdeployed for 30 days or more to a location where a CWR
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Change 15 3-7
cannot be accomplished shall require a complete aircraftwashed within 5 days of returning to home station.
NOTE
When extremely unique requirements or facilitylimitations severely impact a unit’s ability to CWRdaily, this requirement may be temporarily waivedby the MAJCOM Corrosion Program Manager inconjunction with the Aircraft System Program Di-rector (SPD) who has the final approval authority.The MAJCOM Corrosion Program Manager mustforward a copy of the waiver to the Air Force Cor-rosion Prevention and Control Office (AFCPCO).
3.2.3.2 Low Level (Below 3,000 Feet) Salt Water Run-way Approach. Aircraft making two or more take-offs andor/landings, including touch-and-go landings, when the run-way approach is under 3,000 feet and over salt water requirea CWR after the aircraft completes the last flight of the day.
3.2.3.2.1 Single Take-Off and/or Landing. Any aircraft(primarily transient aircraft) performing only a single take-off and/or landing requiring low-level flight (below 3,000feet) over salt water in a single day are excluded from CWRunless there are ten or more occurrences within a 30 dayperiod. After the tenth occurrence, an entry shall be made inthe aircraft forms to require a CWR within 5 days after re-turning to home station.
3.2.3.3 Search, Rescue, and Recovery Missions andLow-Level Flight Operations Under 3,000 Feet. Search,rescue, and recovery missions or any other low-level flightoperations that require aircraft to operate over salt water ataltitudes under 3,000 feet require a CWR after the aircraftcompletes the last flight of the day.
NOTE
• Optimum use of taxi-through rinse facilities isrecommended for removal of salt contamina-tion.
• CWR does not satisfy aircraft washing require-ments as a CWR only removes readily water-soluble matter from aircraft exterior surfaces.
3.2.4 Immediate Cleaning. These affected areas and soilsmust be cleaned immediately.
a. Spilled electrolyte and corrosive deposits found aroundbattery terminals and battery area shall be cleaned,
neutralized, and treated. Close attention and regularcleaning is required for battery areas of aircraft, mis-siles, and equipment.
b. Areas of aircraft, missiles, and equipment exposed tocorrosive fire extinguishing materials shall be cleanedwithin 4 hours after application if at all possible. If anaircraft, missile, or piece of equipment is impoundedby an Accident Investigation Board, the board shallconsider the corrosive effect of fire fighting materialsand direct their removal as soon as possible consistentwith the accident investigation. Prompt removal ofthese materials saves considerable labor hours and ma-terials when salvaging and restoring equipment to aserviceable status. (Refer to Chapter 8 for instructions).
c. Salt deposits, relief tube waste, or other contaminants.
d. Aircraft, missiles, or equipment exposed to significantamounts of salt water. If shipped or transported viaship over salt water, they shall be cleaned and givenany necessary treatment after receipt, particularly if thepreservation and/or packaging are damaged.
e. Fungus growth.
f. Chemical, Biological, and/or Radiological Contami-nated Assets. Any asset that has been contaminated orpotentially contaminated must be identified, markedand decontaminated in accordance with AFMAN 10-2503, Operations in a Chemical, Biological, Radiologi-cal, Nuclear, and High-Yield Explosive (CBRNE) En-vironment and TO 00-110A-1.
g. Spills of corrosive chemicals. An entry in the aircraftAFTO 781A Form shall be made for all corrosivechemical spills and the chemicals shall be neutralizedin accordance with procedures in AFMAN 24-204-IP.
3.2.5 Deployed Aircraft Wash Requirements. All air-craft deployed to a location for more than 20 days shall fol-low the wash intervals from Table 3-1 of the deployed baselocation. Aircraft deploying from a location with a shorterwash interval than the deployed location must be washedimmediately prior to deploying, then will fall into the washintervals of the deployed location. If an aircraft cannot bewashed prior to deploying, the aircraft would remain on it’shome station wash cycle until after the first wash. After thefirst wash at the deployed location, the aircraft would followthe wash interval of the deployed location.
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3-8 Change 15
3.3 CLEANING COMPOUNDS.
Cleaning compounds work by dissolving soluble soils, emul-sifying oily soils, and suspending solid soils. There are sev-eral types of cleaning compounds, each of which cleans asurface using one or more of these mechanisms.
3.3.1 Alkaline Cleaners.
When high strength steels (typically 180 KSI andabove), some high strength aluminum, and somestainless steels are exposed to acid paint removers,plating solutions, other acidic materials (cleaners,etc.,) and even some alkaline materials, a cathodicreaction on the metal surface produces hydrogen.The hydrogen diffuses into the bulk metal, accu-mulating at grain boundaries and weakens thestructure. If the part is under load or contains re-sidual manufacturing stresses, sudden catastrophicfailure known as hydrogen embrittlement occurswhen the part can no longer sustain the internaland/or applied stresses. Hydrogen embrittlementhas been known to occur in parts stressed to only15% of the nominal tensile strength of the metal.
Many alkaline cleaners are not authorized for cleaning of AirForce aircraft, missiles, and related equipment because theyare incompatible with the polyimide insulation on the elec-trical wiring used on many aircraft, missiles, and relatedequipment. Cleaning compounds conforming to MIL-PRF-87937 and MIL-PRF-85570 and that are listed on the QPL/QPD for each specification have been tested and provencompatible with polyimide insulation. Types I and IV ofMIL-PRF-87937 and Types I and II of MIL-PRF-85570 allcontain detergents and foaming agents and work the sameway as any detergent solution. Type I cleaners of both speci-fications contain solvents and are more effective for removalof heavy oils and greases such as wire rope lubricant, butthey cannot be used in poorly ventilated areas due to theirsolvent content. Type IV of MIL-PRF-87937 and Type II ofMIL-PRF-85570 are all good general cleaners for removalof dirt, grime, light oils, and hydraulic fluid, and they areusable in confined areas such as cockpits, cabins, bilges, andequipment bays as they contain no solvents.
3.3.1.1 MIL-PRF-87937, Type I and MIL-PRF-85570,Type I. MIL-PRF-87937, Type I (terpene solvent based) andMIL-PRF-85570, Type I (aromatic solvent based) cleanersare water dilutable and biodegradable materials and are verygood general cleaners for washing aircraft, missiles, compo-nents, and support equipment. However, since they containsolvents, environmental and waste disposal factors need tobe considered prior to use. Since MIL-PRF-87937, Type Imaterials contain terpenes which are potentially corrosive ifentrapped and not completely removed, their use may berestricted on some weapon systems in specific applications.Always consult weapon system specific -23 TO’s for precau-
tions and/or restrictions on use of this class of materials.These cleaners may be used as alternates for MIL-PRF-87937, Type IV and MIL-PRF-85570, Type II materials.MIL-PRF-87937, Type I cleaners are approved for use onsupport equipment (SE) per TO 35-1-3 and aircraft wheelsper TO 4W-1-61.
3.3.1.2 MIL-PRF-87937, Type IV and MIL-PRF-85570,Type II. MIL-PRF-87937, Type IV and MIL-PRF-85570,Type II cleaners are water dilutable and biodegradable mate-rials and are the primary cleaners for washing the exterior ofaircraft, missiles, engines, and support equipment (SE). Theyare excellent materials for removing light to medium soils(greases, oils, grime, etc.,) from almost all surfaces. Sincethey contain no solvents, their use is not limited, except thatapproval by the aircraft SPD is required prior to use ontransparent plastic aircraft canopies, windows, and wind-shields/windscreens. Depending on the type of soils involved,these cleaners may be used in various dilutions as substitutesfor solvents in hand wipe cleaning of greasy and oily areas.Apply them from a pump spray bottle followed by dryingwith a clean, lint free cloth. When applied from a pumpspray bottle at the most dilute mixture recommended, theseare excellent cleaners for lightly soiled surfaces in aircraftcabins and cockpits such as non-transparent plastic parts andinstrument glass covers.
3.3.1.3 MIL-PRF-87937, Type III and MIL-PRF-85570,Type V. MIL-PRF-87937, Type III and MIL-PRF-85570,Type V are gel type cleaners intended for full strength appli-cation with no dilution in areas requiring special cleaning,such as aircraft wheel wells, control surface wells, and wingbutts. They contain small amounts of solvents, detergents,and thickening agents, which make them cling very well tovertical and overhead surfaces. These cleaners are very ef-fective in emulsifying and/or cleaning heavy deposits of hy-draulic fluids, oils, greases, and carbon. In areas where com-plete rinsing with water can be tolerated, they may be usedas direct replacements for solvent cleaners such as MIL-PRF-680, MIL-PRF-32295, Type II, and A-A-59601. To be mosteffective, these materials are applied full strength with nopre-rinsing of the surface, allowed to dwell 5 to 15 minutes,agitated with a non-metallic bristle brush, and then rinsedthoroughly with tap water. These cleaners are not intendedfor and shall not be used on transparent plastic aircraft cano-pies, windows, and windshields/windscreens.
3.3.1.4 MIL-PRF-87937, Type IV. MIL-PRF-87937,Type IV is also an excellent heavy duty, water dilutable,solventless cleaner intended for removal of light to heavydeposits of greases, oils, hydraulic fluids, and carbon fromaircraft, missile, and other equipment surfaces. It is not in-tended for and shall not be used on transparent plastic air-craft canopies and windows.
3.3.1.5 MIL-PRF-85570, Type IV. MIL-PRF-85570,Type IV is a cleaner that contains solvents, detergents, andsuspended rubber particles and is intended for removal ofexhaust gas and gun gas residues, smudges, boot marks, andother embedded soils from aircraft, missiles, and other equip-
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Change 5 3-9
ment with flat (low gloss)/camouflage coating systems. Whenrubbed across a soiled surface, the rubber particles in thecleaner mechanically entrap the soils like tiny erasers with-out polishing the surface of the coating system and increas-ing its gloss.
NOTE
Solvents used in MIL-PRF-85570, Type IV clean-ers may be hazardous air pollutants (HAP’s). Con-sult with Bioenvironmental Engineering before us-ing this cleaner. MIL-PRF-87937, Types III andIV or MIL-PRF-85570, Type V may be used asalternates.
3.3.1.6 MIL-PRF-85570, Type III. MIL-PRF-85570, TypeIII is a cleaner that contains detergents and fine abrasiveparticles and is intended for removal of exhaust gas and gunblast residues from aircraft with a high gloss coating system.When rubbed across a soiled surface, the abrasive particlesmechanically remove the soils which are then suspended inthe detergent while producing only a very minimal dulling ofthe high gloss coating system.
3.3.2 Solvent Emulsion and Aqueous Cleaners for Tur-bine Engine Gas Path and General Area Cleaning. MIL-PRF-85704, Types I, II, and III materials are solvent emul-sion (Types I and II) and aqueous (Type III) cleaners intendedfor cleaning the internal areas or gas path of aircraft turbineengines. A-A-59921 (formerly MIL-C-43616), Class 1A ma-terials are solvent emulsion cleaners intended for generalcleaning of heavily soiled exterior areas of aircraft, missiles,and other equipment. Use only those materials listed on theQPL/QPD’s for MIL-PRF-85704 and A-A-59921 (formerlyMIL-C-43616).
3.3.2.1 MIL-PRF-85704, Type I. MIL-PRF-85704, TypeI (solvent emulsion with aromatic hydrocarbons) and Type II(aqueous with some non-aromatic hydrocarbons) are materi-als intended for cleaning the interior of an aircraft engine byspraying the cleaner into the intake while the starter is mo-toring the engine. There is a Type II, RTU (ready-to-use)material that requires no dilution before use, but the bulkform of Type II and Type I must be diluted with water hav-ing a maximum conductivity of 10 micro-mho/centimeterand a pH in the 5.0 to 8.0 range before use. Type III (bulk,same water dilution requirements) and Type III RTU (ready-to-use with no dilution) are aqueous materials with no hy-drocarbon solvents intended for cleaning the interior of anaircraft engine by spraying the cleaner into the intake whilethe engine is on line or running per specific engine mainte-nance instructions. These cleaners work very well for re-moval of accumulated salts, dirt, and oily soils from thecompressor section and other areas of the gas path of aircraftengines, and their use is followed by spraying fresh tap wa-ter through the engine to rinse away the contaminants.
3.3.2.2 A-A-59921, (Formerly MIL-C-43616), Class1A. A-A-59921 (formerly MIL-C-43616), Class 1A aerosolmaterial is a solvent emulsion cleaner and is very effective
for removal of oily and greasy soils from general exteriorpainted (polyurethane only) and unpainted areas of aircraft,missiles, and other equipment.
NOTE
• MIL-PRF-85704 materials are specially formu-lated to minimize corrosion of aircraft turbineengines. Other types of cleaners shall not beused to clean engine interior areas without spe-cific approval by the engine SPM and/or as re-quired by the system specific engine mainte-nance TO. The system specific enginemaintenance TO shall be consulted for interiorcleaning procedures and the requirement/autho-rization to use MIL-PRF-85704 cleaners.
• A-A-59921 (formerly MIL-C-43616) solventemulsion cleaners shall not be used on non-polyurethane paint systems and markings astheir high solvent content can cause them tofade and/or streak. These cleaners also leave avery thin oil and/or solvent film on the surface,so they are not suitable for use as a final cleanerprior to painting, sealing, or adhesive bonding.
• Large scale use of bulk solvent emulsion clean-ers may cause problems for waste water treat-ment facilities. Local air pollution regulationsmay restrict the amount and application meth-ods of solvent emulsion cleaners. If so, useMIL-PRF-85704, Type II, RTU in lieu of theType I and the appropriate type of MIL-PRF-87937 or MIL-PRF-85570 in lieu of A-A-59921(formerly MIL-C-43616), Class 1A.
3.3.3 Aqueous Parts Washer Cleaning Solutions. Ma-terials conforming to and listed on the QPL/QPD for MIL-PRF-29602, Type I (liquid concentrate) and Type II (pow-der) Cleaning Compounds for Parts Washers and SprayCabinets, either diluted with water (Type I) or dissolved inwater (Type II) in accordance with manufacturer’s instruc-tions are the cleaning agents to be used in high pressurecabinet style parts washers for removing oils and greasesfrom disassembled components. They are not to be used forbearings unless authorized by system specific technical data.Due to their maximum allowable pH of 13.5, MIL-PRF-29602 cleaning solutions can attack/corrode aluminum al-loys. Aircraft SPD and/or equipment SPM engineering au-thority approval is required before cleaning aluminum alloyparts. In addition, many heated MIL-PRF-29602 solutionscan attack the IVD (Ion Vapor Deposited) aluminum coatingused on many high strength steel components and generatehydrogen, which can enter into the steel and cause a cata-strophic failure by hydrogen embrittlement. This is of par-ticular concern for IVD aluminum coated high strength steelaircraft landing gear (LG) components. These LG compo-nents shall be cleaned in aqueous parts washers using onlythose materials listed on the most current revision of theapplicable landing gear technical orders.
TO 1-1-691
3-10 Change 5
3.3.4 Solvents. Cleaning solvents dissolve oily and greasysoils so that they can be easily wiped away or absorbed on acloth. However, solvents differ significantly in their cleaningability, toxicity, evaporation rate, effect on paint, and flam-mability. A-A-59601, and/or MIL-PRF-680, are the mostcommon cleaning solvents used on aircraft due to their lowtoxicity, minimal effect on paint, and relative safety. MIL-PRF-32295, Type II cleaning solvents provides the cleaningperformance of MIL-PRF-680 and also with low toxicity,minimal effect on paint, and relative safety. Other solventssuch as alcohols, ketones, chlorinated solvents, and naphtha,are specialized materials restricted for use as recommendedin Table 3-2.
NOTE
• Solvent cleaning operations are becoming moreand more limited due to environmental regula-tions. Determine local requirements regardinglimitations on type and volume used and dis-posal from your work center supervisor, safetyofficer, and/or Bioenvironmental Engineer.
• MIL-PRF-32295 was developed as a low-VOCand HAP-free replacement for P-D-680, A-A-59601, and MIL-PRF-680.
• A-A-59601 Dry Cleaning and Degreasing Sol-vent P-D-680 and MIL-PRF-680 DegreasingSolvent, replace P-D-680 Dry Cleaning andDegreasing Solvent. MIL-PRF-680 has beenreformulated to reduce Hazardous Air Pollut-ants by reducing the aromatic content of thesolvent, while A-A-59601 is identical to P-D-680.
3.3.4.1 MIL-PRF-680 Degreasing Solvent and A-A-59601 Dry Cleaning and Degreasing Solvent, P-D-680.These solvents are used as cleaners and degreasers for paintedand unpainted metal parts and to remove corrosion preven-tive compounds. The solvents are available in several types.Although the degreasing effectiveness is approximately thesame, the flash points differ as follows: Type I, both specifi-cations, 100° F (38° C) minimum; Type II, both specifica-tions, 140° F (60° C) minimum; Type III, both specifica-tions, 200° F (93° C) minimum, Type IV (D-limoneneadditive), and MIL-PRF-680 only, 140° F (60° C) minimum.Though the flash points differ, all types will burn intenselyonce ignited. Type I, both specifications, is not authorized asa general cleaner due to its flammability, but may be used inparts washers designed for such solvents. Type II, bothspecifications, is the most common cleaning solvent used onaircraft, missiles, and equipment because of its higher flashpoint. If necessary, ASTM D 235, Type II, Class C, MineralSpirits may be used as a substitute for MIL-PRF-680 orA-A-59601, Type II. Type III, both specifications, is intendedfor use in confined spaces and in locations with environmen-tal constraints where a solvent with a very low vapor pres-sure (evaporation rate) and a very high flash point is re-quired. MIL-PRF-680, Type IV (D-limonene additive), maybe used where a higher flash point and strong solvency is
desired if approved by the aircraft SPD or the missile orequipment SPM. The dwell time for all types should be heldto a minimum (less than 15 minutes), to avoid damage topaint.
3.3.4.1.1 MIL-PRF-32295, Type II. These solvents areused as cleaners and degreasers for painted and unpaintedmetal parts and to remove corrosion preventive compounds.NAVSOLVE® is currently the only solvent meeting theMIL-PRF-32295 specification. NAVSOLVE® is a combus-tible solvent with a flash point of 142 °F (61.1 °C). NAV-SOLVE® has a solvent vapor pressure of 2.8 mm Hg (Con-forms to Type I limit of <7mm Hg @ 20 °C, and Type IIlimit of < 45 mm Hg @ 20 °C).
3.3.4.2 TT-I-735 Isopropyl Alcohol. Isopropyl alcohol isa flammable solvent used primarily as a disinfectant forcleaning fungus and mold. It is a poor degreaser.
3.3.4.3 ASTM D 740 Methyl Ethyl Ketone (MEK). Thisis a highly flammable solvent used primarily for cleaningprior to painting and bonding. It may also be used for clean-ing if surfaces become contaminated with leaking oils and/orhydraulic fluids after surface treatment. Most locations can-not use MEK due to environmental restrictions on use ofsolvents with vapor pressures greater than 44 millimeters ofmercury (mm Hg). MIL-PRF-87937, Type IV or MIL-PRF-85570, Type II (either-diluted one part cleaner to nine partswater), may be used as an alternate followed by rinsing thor-oughly with fresh water and air drying or surfaces may becleaned by solvent wiping with SAE AMS 3166, solvents,cleaning, Cleaning Prior to Application of Sealing Com-pounds.
3.3.4.4 Aliphatic Naphtha. Aliphatic naphtha is a highlyflammable solvent used primarily for cleaning oily or greasydeposits from acrylic canopy materials. Other solvents causecrazing of acrylics. It can also be used to remove masking orpreservation tape residue.
3.3.4.5 MIL-T-81772, Type I (Polyurethane) and TypeII (Epoxy) Thinner. Both of these thinners are highly flam-mable solvents that can be used for prepaint solvent cleaningwhen necessary at locations requiring a solvent vapor pres-sure less than 45 mm Hg.
3.3.5 Miscellaneous Cleaning Agents. Some othercleaning materials used on aircraft, missiles, and equipmentare listed here. P-P-560 plastic polish containing a mildabrasive is used to polish out scratches in acrylic canopy andwindow materials. Some alkaline chemicals used to neutral-ize specific acidic soils are: A-A-59370 ammonium hydrox-ide for urine and ASTM D 928 sodium bicarbonate for elec-trolyte spills from sulfuric acid batteries. Some acidicchemicals used to neutralize specific alkaline soils are: ANSI/AWWA B504 monobasic sodium phosphate and A-A-59282boric acid for electrolyte spills from nickel-cadmium batter-ies. MIL-F-24385 AFFF fire extinguishing agent containingwetting and foaming agents can be used to wash out residuesfrom fire extinguishing solutions made with salt water. A-A-
TO 1-1-691
Change 5 3-11
59199 optical glass lens cleaner is used for cleaning opticallenses on aircraft, missiles, and equipment. Solutions ofO-D-1435 and A-A-1439 disinfectants are used to sanitizeand deodorize relief tube areas; latrine areas including toiletbowls, urinals, and latrine buckets, garbage receptacles,sinks, galley areas, and other interior areas of aircraft andequipment requiring disinfection.
3.3.5.1 General Disinfectants. Calla® 1452 is a concen-trated disinfectant and AeroDis® 7127 is a ready-to-use dis-infectant that can be used as general cleaners for aircraft andequipment interior surfaces requiring disinfection. All mate-rials listed in this paragraph are to be mixed and/or appliedper manufacturer’s instructions unless otherwise specified bythe cognizant engineering authority and/or System ProgramOffices (SPO).
3.3.6 Steam Cleaning. Steam cleaning shall not be usedon aircraft and missiles at all levels (Organizational/Unit,Intermediate, or Depot) of maintenance. In addition, steam
cleaning shall not be used on the following items on equip-ment and components removed from aircraft and missiles:honeycomb bonded structure, sealant, fiberglass composites,acrylic windows and canopies, or electrical wiring. Steamcleaning erodes paint, crazes plastics, disbonds adhesives,damages electrical insulation, and drives lubrication out ofbearings.
3.3.7 Dilution. More concentrated solutions than those rec-ommended do not clean any better and are wasteful; MOREIS NOT ALWAYS BETTER. In fact, if too much cleaner isused, the solution merely becomes slippery film, preventingthe washing pad from loosening the soil and making rinsingmore difficult. Do not exceed the cleaner dilution ratios rec-ommended in Table 3-2.
Table 3-2. Cleaning of Specific Areas and Components
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
NOTE
• Cleaning procedures are listed in this table. Ordering information for approved materials can be found in Ap-pendix A. Ordering information for approved equipment can be found in Appendix B.
• Use of hot water (120° to 140° F/49° to 60° C) for rinsing during aircraft washing operations is strongly rec-ommended as it provides much more efficient rinsing and is known to reduce man-hours for aircraft washingoperations by approximately 20%.
• A-A-59601 dry cleaning and degreasing solvent, P-D-680, MIL-PRF-32295 and MIL-PRF-680 degreasing sol-vent are combustible. Keep away from open flames. Use in a well ventilated area. Wear rubber gloves andchemical or splash proof goggles. Avoid skin contact. Consult the local safety office regarding respiratoryprotection.
• Wear rubber gloves, chemical or splash proof goggles, and water resistant boots during cleaning operationsusing MIL-PRF-87937 and MIL-PRF-85570 cleaning compounds. If cleaner is splashed in eyes, rinse thor-oughly with fresh water for 15 minutes and report to medical facility. Remove clothing saturated with cleaningsolution immediately and flush exposed skin areas with fresh water.
EXTERIOR SUR-FACES, PAINTED
Light Soils (dirt,dust, mud, salt,loose soot)
MIL-PRF-87937,Type IV or MIL-PRF-85570, Type IIor
1 part cleaner in 9parts water
Apply cleaner solution withfoam generator, spray, sponge,soft brush, or cloth. Scrub andthen rinse with fresh waterand dry. MIL-PRF-87937,Type I materials contain ter-penes. Aircraft SPD and/ormissile or equipment SPMrestrictions may apply. Con-sult system specific mainte-nance manuals.
MIL-PRF-87937 orMIL-PRF-85570,Type I
1 part cleaner in16 parts water
TO 1-1-691
3-12 Change 18
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
Moderate Soils(hydraulic flu-ids, lube soils,light preserva-tives) HeavySoils (carbon-ized oil, agedpreservatives,grease, gunblast, and ex-haust deposits)
MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII or
1 part cleaner in 4parts water
Apply cleaner solution withfoam generator spray,sponge, soft brush, or cloth.Rub gently with a circularmotion for up to 1 minute.Rinse with fresh water anddry. Use of MIL-PRF-87937, Type I is subject torestrictions noted above.
MIL-PRF-87937 orMIL-PRF-85570,Type I
1 part cleaner in 9parts water
MIL-PRF-87937,Type III or MIL-PRF-85570, TypeV or
Undiluted Spray or brush on cleaner.After 5 to 15 minutes,brush and rinse thoroughly.
A-A-59601 or MIL-PRF-680
Degreasing SolventUndiluted
Pre-clean by wiping or brush-ing with A-A-59601, MIL-PRF-32295, Type II orMIL-PRF-680, Type II orIII solvent, then applycleaner solution with foamgenerator, spray, sponge, orcloth. Allow the cleaner todwell for up to 1 minutewithout scrubbing, thenscrub for up to a minute.Rinse thoroughly, then dry.Do not allow cleaning solu-tion to dry on surfaces orstreaking will occur. Use ofMIL-PRF-87937, Type I issubject to restrictions notedabove in Exterior PaintedSurfaces.
CCC-C-440, Type IIor III, Class 1 orA-A-2522, GradeA or SAE AMS3819, Class 1,Grade A and
Cotton Cheesecloth(Unbleached)White CottonCloth WhiteCleaning Cloth
MIL-PRF-87937 orMIL-PRF-85570,Type I or
1 part cleaner in 4parts water
MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII
1 part cleaner in 4parts water
Stubborn Soil onGloss PaintedAircraft (scuffmarks, ex-haust, etc.)
MIL-PRF-87937,Type IV
1 part cleaner in 4parts water
Apply cleaner with a dampcloth. Rub with a circularmotion. Rinse thoroughly,then dry. Do not allow thecleaner to dry on surfacesor rinsing may be difficult.
MIL-PRF-85570,Type III, IV, or V
Undiluted
Stubborn Soil onLow Gloss/Flatand/or Camou-flage PaintScheme Air-craft (scuffmarks, ex-haust, etc.)
MIL-PRF-85570,Type IV
Undiluted Apply cleaner with a non-abrasive cleaning pad. Al-low 1 to 3 minutes dwelltime. Rub with a circularmotion. Rinse thoroughly,then dry. Do not allow thecleaner to dry on surfacesor rinsing may be difficult.
TO 1-1-691
Change 5 3-13
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
Wear rubber gloves, chemical or splash proof goggles, and water resistant boots during cleaning operations usingMIL-PRF-87937 or MIL-PRF-85570 cleaning compounds. If cleaner is splashed in eyes, rinse thoroughly withfresh water for 15 minutes and report to medical facility. Remove clothing saturated with cleaning solution imme-diately and flush exposed skin with fresh water.
Do not allow MIL-PRF-87937 or MIL-PRF-85570, Type I cleaning solutions to contact canopy, window, or wind-shield/windscreen transparent plastic panels as they may cause crazing.
EXTERIOR SUR-FACES, UN-PAINTED
Gunblast resi-dues, carbon-ized exhaustresidues
MIL-PRF-87937 orMIL-PRF-85570,Type I or
1 part cleaner in 4parts water
Wet surface with fresh water.Apply cleaning solution andscrub briskly with A-A-58054, Type I, Grade A orB abrasive mat. Rinse withfresh water and dry. Use ofMIL-PRF-87937, Type I issubject to restrictions notedabove in Exterior PaintedSurfaces.
MIL-PRF-87937,Type III or MIL-PRF-85570, TypeIV or V
Undiluted
• Wear rubber gloves, chemical or splash proof goggles, and water resistant boots during cleaning operationsusing MIL-PRF-87937 or MIL-PRF-85570 cleaning compounds. If cleaner is splashed in eyes, rinse thor-oughly with fresh water for 15 minutes and report to medical facility. Remove clothing saturated with cleaningsolution immediately and flush exposed skin with fresh water.
• When using Ammonium Hydroxide (Ammonia), do not breathe vapors and avoid skin contact. Wash immedi-ately, if spilled on skin.
• When using Ammonium Hydroxide (Ammonia), do not allow any solutions to contact aircraft wiring. Flushimmediately with fresh water if spillage occurs.
• Avoid use of compressed air to clean electronic equipment. Do not use abrasives in radome compartments.
INTERIOR AREASLavatories
Urine residue A-A-59370 Ammonium Hy-droxide (Ammo-nia) 1 part in 20parts water
Sponge with a solution ofammonium hydroxide (am-monia). Flush with freshwater or wet surface withsodium bicarbonate solu-tion, allow to dry, and rinsewith fresh water. Dry with aclean cloth.
ASTM D 928 Sodium Bicarbon-ate, 6 OZ to 1GL of fresh wa-ter
TO 1-1-691
3-14
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
USDA Reg 100-12-1 Germicidal Tablets Use germicidal tables as toiletand urinal deodorants.
All types of soilson lavatorysurfaces
O-D-1435, A-A-1439, or AMS1476
Mix per manufac-turer’s instruc-tions
Pour solution into toilets, uri-nals, and latrine buckets.Scrub with a brush andrinse with fresh water.Sponge all other surfaceswith the solution, spongearea with fresh water, andwipe dry.
Floor and Deck Dirt, debris MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII (Preferred) or
1 part cleaner in 9parts water
Remove loose dirt withvacuum cleaner. Wipe withcleaning compound andrinse with fresh water. Useof MIL-PRF-87937, Type Iis subject to restrictionsnoted above in ExteriorPainted Surfaces.
MIL-PRF-87937, orMIL-PRF-85570,Type I (Alternate)
1 part cleaner in16 parts water
Radome and Equip-ment Compart-ment (Interior)
Dust, dirt, oil,and debris
MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII and
1 part cleaner in16 parts water
Remove loose dirt with avacuum cleaner. Wipe fiber-glass and other surfaceswith a cloth wet with clean-ing solution and rinse withcloth wet with fresh water.Dry with a clean cloth.
CCC-C-440, Type Ior II, Class 1 orA-A-59323, TypeII or SAE AMS3819, Class 1,Grade A or B
Cotton Cheesecloth(Unbleached)Cleaning Cloth,Low lint WhiteCleaning Cloth
Cockpit Interior Dust, dirt, mud,and light de-bris
MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII and
1 part cleaner in 9parts water
Loosen any accumulations ofmud on control pedals,floors, or other cockpitequipment with brush andremove with vacuumcleaner. Wipe with clothwet with cleaning solutionand follow with a cloth wetwith fresh water. Dry with aclean cloth.
A-A-50129 Cloth, Flannel
Environmental Con-trol Ducting
Light debris,dust, andgrime
MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII
1 part cleaner in 9parts water
Refer to applicable mainte-nance manuals.
NOTE
Refer to aircraft system specific manual to determine acrylic plastic parts.
ACRYLIC PLAS-TIC PARTS (EX-CEPT CANO-PIES ANDWINDOWS)
Light soil andsmudges
MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII and
1 part cleaner in16 parts water
Wipe with cloth wet withcleaning solution and followwith a cloth wet with freshwater. Dry with a cleancloth.A-A-50129 Cloth, Flannel
TO 1-1-691
Change 1 3-15
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
INTERIOR PLAS-TIC ANDGLASS PANELS
A-A-50129 Cloth, Flannel Vacuum and then dust withsoft, clean, damp cloth.Keep cloth free of grit byrinsing frequently in waterand wringing out.
ELASTOMERICSEALS
Dust, dirt, oil,and grime
MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII
1 part cleaner in 9parts water
Wipe with cloth wet withcleaning solution and rinsewith a cloth wet with freshwater. Dry with a cleancloth.CCC-C-440, Type I
or II, Class 1 orCotton Cheesecloth
(Unbleached)Cleaning Cloth
(Low lint) WhiteA-A-59323, Type II
or SAE AMS3819, Class 1,Grade A or B
Cleaning Cloth
Wear rubber gloves, chemical or splash proof goggles, and water resistant boots during cleaning operations usingMIL-PRF-87937 and MIL-PRF-85570 cleaning compounds. If cleaner is splashed in eyes, rinse thoroughly withfresh water for 15 minutes and report to medical facility. Remove clothing saturated with cleaning solution imme-diately and flush exposed skin with fresh water.
FABRIC PARTS,SOUND-PROOF-ING AND UP-HOLSTERY
Light soil and oilspots
MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII
1 part cleaner in 4parts water
Remove loose dirt withvacuum cleaner. Apply soapsolution with sponge andscrub briskly. Rinse withclean, dampened rag orsponge using clean, freshwater. Allow area to dry.Raise nap by brushing.
Do not use synthetic wiping cloths with flammable solvents, such as TT-N-95 aliphatic naphtha.
Refer to aircraft system specific manual to determine cleaning procedures for aircraft canopies. In addition, referto TO 1-1A-12. Remove rings, watches, or other hard objects from hands and wrists before washing transparentplastics. Personnel must also take precautions to prevent buttons, badges, or other hard objects from scratchingsurfaces. Do not use hard, dirty, or gritty cloths in cleaning and polishing transparent plastics. Wiping with suchcloths can mar and scratch plastic surfaces. Do not use any chemical compounds unless specifically authorized forcleaning plastics. Do not rub dry plastic panels with dry cloth, which might scratch surface or create electrostaticcharge that attracts dust.
TO 1-1-691
3-16
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
CANOPY EXTE-RIOR, PLASTICAND GLASSWINDOW ANDWINDSHIELD/WINDSCREENPANELS
Dust, dirt, grime,salt, and spray
P-P-560 Plastic PolishCompound
Rub gently with bare hands orclean cloth while flushingwith fresh water to removeloose dirt. Apply polishingcompound with a soft, cleancloth and rub using a circu-lar motion until clean. Pol-ish with another soft, cleancloth.
A-A-50129 Cloth, Flannel
Oil, grease TT-N-95 and Aliphatic Naphtha Apply naphtha with soft,clean cloth. Blot gently,solvent will evaporate andnot leave a film.
P-P-560 and Plastic PolishCompound
Apply polishing compound.Rub, using a circular mo-tion until clean and polishwith another soft, cleancloth.
A-A-50129 Cloth, Flannel
• Open all circuit breakers associated with battery power (refer to applicable system specific maintenance manu-als), prior to application of MIL-PRF-680 degreasing solvent, MIL-PRF-32295, Type II or A-A-59601 drycleaning and degreasing solvent, P-D-680.
• All of these solvents are combustible. Keep away from open flames. Use in a well ventilated area. Wear rubbergloves and chemical or splash proof goggles. Avoid skin contact. Consult the local safety office regarding re-spiratory protection.
Do not use excessive cleaning solvent on control cables. Solvent will remove internal lubricant.
CONTROLCABLES
Dust, dirt oil,and grease
A-A-59601 or MIL-PRF-680
Degreasing Solvent Wipe with clean cloth damp-ened with solvent. ApplyMIL-PRF-81309, Type IIwater displacing CPC tocables and re-coat cableswith MIL-PRF-16173,Grade 4 CPC.
MIL-PRF-81309,Type II and
Water Displacing,CPC
MIL-PRF-16173,Grade 4
CPC
Wipe away from seal areas to preclude collection of soil at seal junction areas. Make sure piston surface is cleanand completely lubricated but not dripping. If piston is dry, telescoping action of strut will force gritty particlesinto cylinder causing leaks and eventual failure. Do not use aerosol type cleaning fluids on hydraulic systems.
TO 1-1-691
Change 5 3-17
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
LANDING GEAREXPOSED PIS-TON SURFACES
Sand, dirt, saltdeposits, andother foreignparticles
MIL-PRF-83282 Hydraulic Fluid Clean exposed surfaces withclean cloth dampened withhydraulic fluid. Take carenot to scratch the surface.Wipe away from seals, nottoward them.
CCC-C-440, Type Ior II, Class 1 orA-A-59323, TypeII or SAE AMS3819, Class 1,Grade A or B
Cotton Cheesecloth(Unbleached)Cleaning Cloth(Low lint)Cleaning Cloth
• Open all circuit breakers associated with battery power (refer to applicable system specific maintenance manu-als), prior to application of MIL-PRF-680 degreasing solvent, MIL-PRF-32295, Type II or A-A-59601 drycleaning and degreasing solvent, P-D-680.
• All of these solvents are combustible. Keep away from open flames. Use in a well ventilated area. Wear rubbergloves and chemical or splash proof goggles. Avoid skin contact. Consult the local safety office regarding re-spiratory protection.
Do not use MIL-PRF-16173, Grade 4 or MIL-DTL-85054 on micro-switches or exposed piston rod surfaces.
DOORS, LINK-AGES, CYLIN-DERS
Dust, dirt, oil,and grease
A-A-59601 or MIL-PRF-680
Degreasing Solvent Brush surfaces, as necessary,with solvent. Cover rodends and springs with MIL-PRF-16173, Grade 4 CPC.Where lubrication is notrequired, MIL-DTL-85054CPC may be applied.
MIL-PRF-16173,Grade 4 or
CPC
MIL-DTL-85054 CPC
WHEELS ANDBRAKES
Oil, grease, dirt,sand, and otherforeign matter
For cleaning wheels andbrakes, reference TO 4W-1-61 and TO 4B-1-32.
Applicable LandingGear TechnicalOrder specifiedmaterials
Dilute and/or mixper manufactur-er’s instructions
Use only those cleaners listedin the most current revisionof the applicable landinggear technical order. Placeoff aircraft parts in theaqueous parts washer andrun through the completewash, rinse, and dry cycle.
TO 1-1-691
3-18 Change 5
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
• Open all circuit breakers associated with battery power (refer to applicable system specific maintenance manu-als), prior to application of MIL-PRF-680 degreasing solvent, MIL-PRF-32295, Type II or A-A-59601 drycleaning and degreasing solvent, P-D-680.
• All of these solvents are combustible. Use in a well ventilated area. Keep it away from open flames. Avoidcontact with skin.
• Wear rubber gloves, chemical or splash proof goggles, and water resistant boots during cleaning operationsusing MIL-PRF-87937 or MIL-PRF-85570 cleaning compounds. If cleaner is splashed in eyes, rinse thor-oughly with fresh water for 15 minutes and report to medical facility. Remove clothing saturated with cleaningsolution immediately and flush exposed skin with fresh water.
Protect tires from contact with degreasing solvents or cleaning solutions.
LANDING GEAR(OTHER THANEXPOSED PIS-TON AREA)AND WHEELWELLS
Dirt, grease, hy-draulic fluid,etc.
MIL-PRF-87937,Type III or MIL-PRF-85570, TypeV or
Undiluted Apply thixotropic gel, TypeIII or Type V cleaner withspray or brush and allow a5 to 15 minute dwell.Brush, if necessary, andrinse thoroughly with freshwater. Repeat rinsing withbrushing to remove cleanerresidues.
A-A-59601 or MIL-PRF-680
Undiluted Degreas-ing Solvent
Alternate procedure: Brush onsolvent to loosen stubbornsoil.
MIL-PRF-85570,Type I
1 part cleaner in 4parts water
Apply MIL-PRF-85570, TypeI, or MIL-PRF-87937, TypeI cleaning solution, brush,and rinse. Omit solvent pre-soak, if desired. Use ofMIL-PRF-87937, Type Imay be restricted as notedabove in Exterior PaintedSurfaces.
Before cleaning electrical and avionic equipment, make sure electrical power is disconnected. Injury and deathmay otherwise result.
TO 1-1-691
Change 5 3-19
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
Avoid use of compressed air in electronic compartments because air can force dust, dirt, and other foreign materi-als into components or equipment and cause damage.
ELECTRICALCONNECTORSAND AVIONICCOMPONENTS
Dust, dirt, lint,and other looseforeign matter,grease, oilsmudges, lighttarnish, corro-sion, or fungi
Refer to TO 1-1-689-1, TO1-1-689-3, and TO 1-1-689-5.
OXYGEN LINES(EXTERIORSURFACES)
Oil, grease Refer to system specific maintenance manuals.
Wear rubber gloves, chemical or splash proof goggles, and water resistant boots during cleaning operations usingMIL-PRF-87937 or MIL-PRF-85570 cleaning compounds. If cleaner is splashed in eyes, rinse thoroughly withfresh water for 15 minutes and report to medical facility. Remove clothing saturated with cleaning solution imme-diately and flush exposed skin with fresh water.
RELIEF TUBES(EXTERIOR)
Human waste(urine)
MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII
1 part cleaner in 9parts water
Wash thoroughly with solu-tion using a soft, bristlebrush, then rinse thoroughlywith fresh water and wipedry.
TO 1-1-691
3-20 Change 2
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
Wear rubber gloves, chemical or splash proof goggles, and water resistant boots during cleaning operations usingMIL-PRF-87937 or MIL-PRF-85570 cleaning compounds. If cleaner is splashed in eyes, rinse thoroughly withfresh water for 15 minutes and report to medical facility. Remove clothing saturated with cleaning solution imme-diately and flush exposed skin with fresh water.
Do not use strong alkaline cleaners or highly abrasive compounds when cleaning rotor tip cap areas. Refer to sys-tems specific technical orders for specific cleaning instructions.
HELICOPTERAND PROPEL-LER BLADES
Grime, oil,grease, exhauststains
MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII
1 part cleaner in 9parts water
Apply cleaning solution witha cleaning pad or brush andagitate. Rinse with freshwater and wipe dry.
A-A-3100 Cleaning PadHELICOPTER
CARGO ANDRESCUE HOISTCABLE, ANDEND FITTINGS
Salt and salt wa-ter
MIL-PRF-16173,Grade 3 or MIL-PRF-81309, TypeII or MIL-L-87177,Type I, Grade B
Water DisplacingCorrosion Pre-ventive Com-pound
Flush thoroughly with freshwater. Blow dry with clean,compressed air or thor-oughly dry with a cottoncloth. Spray with MIL-PRF-16173, Grade 3, MIL-PRF-81309, Type II, or MIL-L-87177, Type I, Grade Bcompound as it is beingrewound. Remove excesswith clean dry cloth.
A-A-50129 Cloth, Flannel
Wear rubber gloves, chemical or splash proof goggles, and water resistant boots during cleaning operations usingMIL-PRF-87937, or MIL-PRF-85570 cleaning compounds. If cleaner is splashed in eyes, rinse thoroughly withfresh water for 15 minutes and report to medical facility. Remove clothing saturated with cleaning solution imme-diately and flush exposed skin with fresh water.
HELICOPTERCARGO ANDRESCUE HOISTDRUM
Salt and salt wa-ter
MIL-PRF-87937 orMIL-PRF-85570,Type I
1 part cleaner in 9parts water
Rinse with fresh water. Applycleaning solution and scrubwith a clean cloth orsponge. Rinse with cleanwater. Blow dry with clean,compressed air or dry witha clean, dry cloth. Use ofMIL-PRF-87937, Type Imay be restricted as notedabove in Exterior PaintedSurfaces.
TO 1-1-691
Change 5 3-21
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
Wear rubber gloves, chemical or splash proof goggles, and water resistant boots during cleaning operations usingMIL-PRF-87937 or MIL-PRF-85570 cleaning compounds. If cleaner is splashed in eyes, rinse thoroughly withfresh water for 15 minutes and report to medical facility. Remove clothing saturated with cleaning solution imme-diately and flush exposed skin with fresh water.
HELICOPTERRESCUE SLING
Salt and salt wa-ter
MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII
1 part cleaner in 9parts water
Rinse with fresh water. Applycleaning solution withsponge or clean cloth. Rinsethoroughly with fresh water.Blow dry with clean, com-pressed air or suspend andallow to dry. If suspendedto dry, ensure water willdrain away from the buckle.
• Open all circuit breakers associated with battery power (refer to applicable system specific maintenance manu-als), prior to application of MIL-PRF-680 degreasing solvent, MIL-PRF-32295, Type II or A-A-59601 drycleaning and degreasing solvent, P-D-680.
• All of these solvents are combustible. Keep away from open flames. Use in a well ventilated area. Wear rubbergloves and chemical or splash proof goggles. Avoid skin contact. Consult the local safety office regarding re-spiratory protection.
ENGINES, RECIP-ROCATING
Oxidized oil,dust, carbon,salt deposits
A-A-59601 or MIL-PRF-680 and
Degreasing Solvent Apply solvent with cleaningcloth or brush. Repeat ap-plication and dry. Collectsolvent runoff and disposein accordance with localregulations.
CCC-C-440, Type Ior II, Class 1 or
Cotton Cheesecloth(Unbleached)
A-A-59323, Type IIor SAE AMS3819, Class 1,Grade A or B
Cleaning ClothLow Lint Clean-ing Cloth
Wear rubber gloves, chemical or splash proof goggles, protective wet weather clothing where necessary, and waterresistant boots during cleaning operations using cleaning compound MIL-PRF-85704, Types II or II RTU. Ifcleaner is splashed in eyes, rinse thoroughly with fresh water for 15 minutes and report to medical facility. Re-move clothing saturated with cleaning solution immediately and flush exposed areas with fresh water.
TO 1-1-691
3-22 Change 5
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
• Use only MIL-PRF-85704 cleaning compound for cleaning turbine engine gas paths. Prepare aircraft in accor-dance with applicable system specific maintenance manuals and/or maintenance work cards. In case of conflict,the manuals and/or work cards take precedence over the following instructions.
• MIL-PRF-85704, Type I gas path cleaners typically contain 30 to 60% solvent. When diluted (1 part cleaner to4 parts water), some products are above the 10% solvent limit and most contain enough naphthalene to causewash rack runoff to exceed the discharge permit limits. The current substitute is MIL-PRF-85704, Type II, awater-base product that contains less than 10% solvent in the concentrate. This material shall be used at thesame dilution ratio while using the same starter cranked engine wash procedures, which are currently approvedin aircraft engine manuals. MIL-PRF-85704, Type II RTU is ready-to-use (does not require dilution, but re-quired 5 times the storage space since it is already diluted with water).
GAS TURBINEENGINE INTE-RIOR (GASPATH)
Oxidized oil,dust, carbon,salt deposits
MIL-PRF-85704,Type II or
1 part cleaner in 4parts water
Use in accordance with appli-cable engine maintenancemanual instructions. Dis-pose of waste cleaner inaccordance with local regu-lations.
MIL-PRF-85704,Type II RTU
Do not dilute, thisis a ready mixform
Wear rubber gloves, chemical or splash proof goggles, and water resistant boots during cleaning operations usingMIL-PRF-87937, MIL-PRF-85570, or MIL-PRF-85704, Types I or II cleaning compounds. If cleaner is splashedin eyes, rinse thoroughly with fresh water for 15 minutes and report to medical facility. Remove clothing saturatedwith cleaning solution immediately and flush exposed skin with fresh water.
Prepare aircraft in accordance with applicable system specific maintenance manuals and/or maintenance workcards. In case of conflict, the manuals and/or work cards take precedence over the following instructions.
TO 1-1-691
Change 5 3-23
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
GAS TURBINEENGINE EXTE-RIOR, ENGINEBAY AND EN-GINE BAYDOORS
Oxidized oil,dust, carbon,salt deposits
MIL-PRF-85704,Type I or II or
1 part cleaner in 4parts water
Apply mixed cleaning solu-tions (MIL-C-43616, Class1, MIL-PRF-85704, Type Ior II, MIL-PRF-87937,Type IV, or MIL-PRF-85570, Type II) or the pre-mixed cleaners (MIL-C-43616, Class 1A or MIL-PRF-85704, Type II RTU)with a brush. Scrub, thenrinse with fresh water.When using the MIL-PRF-87937, Type III or MIL-PRF-85570, Type V, applythe undiluted concentratewith a brush, allow cleanerto remain on surface for 5minutes, then brush andrinse thoroughly. Dispose ofwaste cleaners in accor-dance with local directives.
A-A-59921 (formerlyMIL-C-43616),Class 1A or
Aerosol Can
MIL-PRF-85704,Type II RTU or
Do not dilute, thisis a ready mixform
MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII or
1 part cleaner in 4parts water
MIL-PRF-87937,Type III or MIL-PRF-85704, TypeV
Undiluted concen-trate
Never use a wire brush to clean a battery or a battery area. Wear rubber gloves, a rubber apron, and protectivegoggles when handling batteries.
• Nickel-cadmium batteries must not be exposed to acid or acid vapors. Battery electrolytes are extremely corro-sive. Spilled electrolyte shall be removed immediately. Refer to applicable system specific aircraft, missile, orequipment manuals for battery type.
• Fumes from overheated electrolyte will spread to adjacent areas causing rapid corrosion on unprotectedsurfaces.
NOTE
Refer to Chapter 7 for additional instructions.
TO 1-1-691
3-24 Change 5
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
Battery Compart-ments
Nickel-cadmiumbattery electro-lyte deposits(potassiumhydroxide so-lution)
A-A-59282 or Boric Acid Remove spilled electrolyteimmediately by flushingwith fresh water. Spray thecontaminated area with Bro-mothymol Blue solution.(Refer to Chapter 7). Neu-tralize the area by spongingor spraying generously withboric acid or sodium phos-phate solution. Brush with afiber bristle brush and flushwith fresh water. Reapplythe Bromothymol Blue so-lution to determine if all theelectrolyte has been neutral-ized. Retreat area, as re-quired, and rinse. Dry withclean wiping cloths. Keepthe cell vents open but donot allow any solutions toenter the cells. Preservecompartment with MIL-PRF-81309, Type II, Class1 or 2 or MIL-L-87177,Type I or II, Grade B CPC.Do not paint or preservebatteries.
ANSI/AWWA B504 Monobasic sodiumphosphate
Mix either material6 OZ in 1 GLwater
MIL-PRF-81309,Type II, Class 1 or2 or MIL-L-87177,Type I or II, GradeB
Water DisplacingCPC
TO 1-1-691
3-25
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
Lead-acid batteryelectrolyte de-posits (sulfuricacid solution)
ASTM D 928 Sodium bicarbon-ate, 6 OZ in 1GL water
Remove spilled electrolyteimmediately by flushingwith fresh water. Spray thecontaminated area with Lit-mus solution. (Refer toChapter 7). Neutralize thearea by sponging or spray-ing with sodium bicarbonatesolution. Apply generouslyuntil bubbling stops and theLitmus solution turns blue.Let it stay on the surfacefor 5 minutes but do notallow to dry. Brush with afiber bristle brush, thenflush with fresh water. Re-apply the Litmus solution todetermine if all the electro-lyte has been neutralized.Retreat the area, as re-quired, and rinse. Dry withclean wiping cloths. Keepthe cell vents open but donot allow any solutions toenter the cells. Preservecompartment with MIL-PRF-81309, Type II, Class1 or 2 or MIL-L-87177,Type I or II, Grade B CPC.Do not paint or preservebatteries.
MIL-PRF-81309,Type II, Class 1 or2 or MIL-L-87177,Type I or II, GradeB
Water DisplacingCPC
• Wear rubber gloves, chemical or splash proof goggles, and water resistant boots during cleaning operationsusing MIL-PRF-87937 or MIL-PRF-85570 cleaning compounds. If cleaner is splashed in eyes, rinse thor-oughly with fresh water for 15 minutes and report to medical facility. Remove clothing saturated with cleaningsolution immediately and flush exposed skin with fresh water.
• A-A-59601, Type III dry cleaning and degreasing solvent, P-D-680 and MIL-PRF-680, Type III degreasingsolvent are non-combustible, but can still burn if exposed to flames. Use in a confined area is allowed, but thisarea should still be well ventilated. Keep away from open flames. Avoid contact with skin.
TO 1-1-691
3-26
Table 3-2. Cleaning of Specific Areas and Components - Continued
Area or Component Type of Soil Cleaning Agent orCompound
Mixing Directionsand Nomenclature
Cleaning Procedures
BILGE AREAS Hydraulic fluid,water, dirt,metallic debris
MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII or
1 part cleaner in 9parts water
Vacuum clean liquids and de-bris. Wipe area with asponge dampened in clean-ing solution. Rinse bysponging with fresh water.Wipe dry with a cleancloth.
MIL-PRF-87937 orMIL-PRF-85570,Type I or
1 part cleaner in16 parts water
Use of MIL-PRF-87937, TypeI may be restricted as notedabove in Exterior PaintedSurfaces.
A-A-59601 or MIL-PRF-680, Type III
Degreasing Solvent Wipe with cloth dampenedwith solvent. Wipe dry witha clean cloth.
Algae contami-nation
MIL-PRF-87937,Type IV or MIL-PRF-85570, TypeII or
1 part cleaner in 4parts water
Mix cleaner and water in apump spray bottle. Spraymixture on contaminatedarea and allow it to dwell atleast 2 minutes. Wipe offwith a sponge and dry witha clean cloth. Use of MIL-PRF-87937, Type I may berestricted as noted above inExterior Painted Surfaces.
MIL-PRF-87937 orMIL-PRF-85570,Type I or
1 part cleaner in 9parts water
MIL-PRF-87937,Type III or MIL-PRF-85570, TypeV
Undiluted concen-trate
OPTICAL GLASS Dust, grease, andoil
A-A-59199 and Optical cleaner Spray cleaner onto flannel andcarefully wipe the lens orother optical surface. Wipedry with clean flannel cloth.
A-A-50129 Cloth, Flannel
EJECTION SEATS
• Application of corrosion preventive compounds (CPC’s) or paints to certain areas of ejection seats could pre-vent or restrict seat operation. Specific ejection seat instructions must be followed carefully.
• See system specific ejection seat maintenance manuals and SPM instructions for corrosion prevention and con-trol and lubrication of ejection seats.
REMOVABLEMETAL FUELTANKS
Fuel residues,grease, andexhaust depos-its
MIL-PRF-85570 Use MIL-PRF-85570 deter-gent in accordance withprocedures in systems spe-cific fuel tank manuals.
TO 1-1-691
3-27
Table 3-3. Deicing/Anti-Icing Fluid Residue Inspection and Cleaning Procedures
Area Components VisuallyInspect for
Characteristics Cleaning Procedures Lubrication
Wing RearSpar Area,Includingthe Actua-tion Com-ponents
Spoilers, aile-rons, flaper-ons (if appli-cable),control sur-face hingesand balancebays
The presenceof dry orrehydrateddeicing/anti-icing fluidresidue
Dry residue is hardto see, has a thinfilm and is par-tially covered withdirt or grease
Spray areas with finemist of warm waterto rehydrate any resi-due present. Rehy-drate process may beslow, especially ifresidue has accumu-lated over a longperiod of time. If norehydrated residue isvisible, repeat theabove procedurethree more timesincluding the 15minute wait periodto allow rehydrationto occur.
After wash, per-form lubrica-tion/CPC re-quirements perapplicable TO.
Wing Lead-ing Edge
Devices includ-ing actuatingcomponents
Rehydrated residuewill be a gel-likesubstance, morevisible thickness
HorizontalStabilizerRear Spar
Actuating com-ponents forelevators,elevator tabs(if appli-cable), con-trol surfacehinges andbalance bays
Do not spray flightcontrol areas withwater when thetemperature is be-low freezing un-less the aircraft isin a heated hangar/shelter. Doing socan result in icethat impairs theflight controls.
Vertical Sta-bilizer
Actuating com-ponents forthe rudder,control sur-face hinges
Remove identified resi-due using warm wa-ter with rags and softbristle brushes. Alow pressure air (10to 15 PSI) is usefulto rinse away theresidue. Deicing fluid(SAE AMS 1425,Type I) or a mixtureof water and Type Ideicing fluid workswell to remove resi-due.
TO 1-1-691
3-28
3.4 CLEANING EQUIPMENT.
• Do not use high pressure spray nozzles to ap-ply cleaning compounds. Cleaning compoundsshall only be applied using a low pressure soapnozzle. High pressure can cause cleaning com-pounds to become entrapped in enclosed areacausing corrosion.
• High pressure wash equipment shall never beused on aircraft landing gear and components,wheels, and brakes as they can force lubricantsout of bearings and attach points and cause cor-rosion and wear problems.
NOTE
• Use only cleaning materials and equipment au-thorized and described in this manual. Experi-mentation with unauthorized cleaners maydamage aircraft, missiles, and equipment thusreducing reliability and increasing maintenancecosts.
• Cleaning equipment specific to one type of air-craft, missile, or piece of equipment is not cov-ered by this manual. Approved equipment forgeneral cleaning is discussed in this manual andordering information is presented in AppendixB of this manual. General operating instructionsare in Paragraph 3.4.1 through Paragraph 3.4.9.See specific equipment operating manuals fordetailed equipment operating instructions.
3.4.1 High Pressure/Hot Water Wash Equipment. Ifapproved by the aircraft SPD and/or the equipment SPM,high pressure/hot water wash equipment can be used forgeneral purpose cleaning of aircraft, support equipment, andvehicles. These machines can deliver four gallons per minuteof water and/or cleaning solution at a temperature of 210° Fand a pressure of 3000 PSI at the attach points on the ma-chine for each output hose. These machines shall be oper-ated per these instructions and the directions in the specificequipment operating manual.
a. Fill the cleaner reservoir with only approved cleaningcompounds.
b. Set the water cleaning compound mixture ratio to fiftyparts water to one part cleaner.
c. Use only 40° flat fan spray nozzles.
d. Ensure that the nozzle stand-off distance to the surfaceis always at least 12 inches and never less.
NOTE
• Pressure and temperature at the nozzles will beless than at the hose attach points on the ma-chine due to losses in the hoses.
• This equipment may remove any loose sealantand/or paint.
3.4.2 Portable, 15 Gallon, Foam Generating, CleaningUnit. This cleaning unit is compact, portable, light, and idealfor cleaning hard to reach areas. It consists of a 54 inchapplicator wand, 50 feet of hose, and a 15 gallon tankmounted on a frame with rubber tire wheels. (Refer to Fig-ure 3-1). The control system allows the operator to adjust thefoam wetness to fit any job. The cleaning unit provides afoam capable of clinging to vertical surfaces to soften anddislodge soils. These machines shall be operated per theseinstructions and the directions in the specific equipment op-erating manual.
Do not service the portable 15 gallon foam gener-ating cleaning unit without releasing the tank pres-sure.
When the cleaning task is completed, drain andflush the tank with fresh water to prevent formingan extremely concentrated solution by pouring ad-ditional cleaner into the solution remaining in thetank which could damage the equipment beingcleaned.
a. Release the tank pressure prior to servicing and re-move the tank fill cap. Fill the tank with an authorized,pre-diluted cleaning solution while leaving an adequateair space at the top of the tank. Replace the tank fillcap.
b. Connect the air supply hose to the air inlet valve onthe air regulator.
NOTE
Refer to Table 3-2 for the proper cleaner to watermix ratio.
c. Open the cleaning compound metering valve and theair inlet valve to the full, open position and set the airregulator to a pressure within the range of 30 to 70PSI.
d. Open the foam discharge valve while directing thenozzle at the surface to be cleaned.
TO 1-1-691
Change 10 3-29
Figure 3-1. Foam Generating Cleaning Unit (15 Gallons)
TO 1-1-691
3-30
Figure 3-2. Foam Generating Cleaning Unit (45 Gallons)
TO 1-1-691
3-31
e. If the foam is too wet, close the cleaning compoundmetering valve slightly. If the foam is too dry, open thecleaning compound metering valve slightly and/orlower the air pressure slightly by adjusting the airregulator. Dry foams have a longer dwell time and pro-long the cleaning operation but wet foams clean better.
f. Apply the foam to the surface and allow it to dwell fora minimum of 1 minute, but not long enough to dry onthe surface, and then scrub with a cleaning kit, brush,or cloth and rinse. Refer to Table 3-2 for additionalinstructions.
3.4.3 Portable, 45 Gallon, Foam Generating CleaningUnit. This cleaning unit is a simplified, portable pressureoperated, foam-dispensing system. (Refer to Table 3-2). Ituses available air supply for its power source without usingpumps. Air is metered directly into the pressurized solutionchamber which forces cleaning solution into the hose to cre-ate foam. These machines shall be operated per these in-structions and the directions in the specific equipment oper-ating manual.
Figure 3-3. Universal Wash Unit
TO 1-1-691
3-32
Do not service the portable 45 gallon foam gener-ating cleaning unit without releasing the tank pres-sure.
When the cleaning task is completed, drain thetank and flush with fresh water to prevent formingan extremely concentrated solution by pouring ad-ditional cleaner into the solution remaining in thetank which could damage the equipment beingcleaned.
a. Release the tank pressure prior to servicing. Close thecleaning compound metering valve and the air valveand open the air dump valve to bleed off retained airpressure.
b. Open the tank by removing the cover retaining boltsand lifting off the cover. Fill the tank with an autho-rized, pre-diluted cleaning solution while leaving anadequate air space at the top of the tank. Replace thecover and bolt it firmly in place.
NOTE
Refer to Table 3-2 for the proper cleaner to watermix ratio.
c. Make sure the cleaning compound metering valve andthe air valve are closed. Attach an air line to the airinlet/dump valve on the side of the unit and fill thevoid in the tank with air until the pressure is within therange of 30 to 70 PSI as indicated at the air regulator.
d. Open the air valve and then open the cleaning com-pound metering valve slowly while pointing the nozzleat the surface to be cleaned. Adjust the cleaner com-pound metering valve until the desired foam consis-tency is reached.
e. If the foam is too wet, close the cleaning compoundmetering valve slightly and/or open the air valveslightly. If the foam is too dry, open the cleaning com-pound metering valve slightly and/or close the air valveslightly.
f. Apply the foam to the surface and allow it to dwell fora minimum of 1 minute, but not long enough to dry onthe surface, and then scrub with a cleaning kit, brush,or cloth and rinse. Refer to Table 3-2 for additionalinstructions.
3.4.4 Turbine Engine Compressor Cleaning Equip-ment. Equipment used for cleaning aircraft turbine enginesis contained in specific system specific engine TO’s.
3.4.5 Miscellaneous Large Cleaning Equipment. Otherequipment such as truck, trailer, or wash rack/hangermounted spray or foam equipment may be available at manylocations.
3.4.6 Spray Cleaning Guns for Solvents. These solventspray guns have an extended nozzle/tube and require ap-proximately 14 CFM of air at 50 PSI to siphon solvent orcleaner from container and deliver it to a surface in a non-atomized spray.
3.4.7 Pneumatic Vacuum Cleaner. This unit is a small,portable, wet/dry, air-operated vacuum cleaner for removingdebris and water from aircraft. (Refer to Appendix B).
3.4.8 Universal Wash Unit. Universal wash units are usedfor general purpose cleaning. (Refer to Figure 3-3). Theyapply cleaning solutions to aircraft and/or equipment sur-faces in a non-foam state at the approximate rate of 2.5 gal/min at a pressure of 30 PSI. These machines shall be oper-ated per these instructions and the directions in the specificequipment operating manual.
Use the universal wash unit in the horizontal po-sition only.
a. Connect the strainer unit to the intake hose and insertit into the container of water or cleaning compoundsolution.
b. Connect the wand and the spray nozzle assembly tothe output/discharge hose or connect the dischargequick disconnect to the aircraft wash manifold quickdisconnect.
c. Press the start switch on the unit or the remote startswitch and observe the pressure gauge on the unit. Itshould indicate an increase of pressure immediately.When the pressure reaches approximately 10 PSI, re-lease the start switch and the unit will continue to run.
d. Point the nozzle at the aircraft or equipment surface tobe cleaned and spray the surface with the cleaning so-lution.
e. Press the stop switch on the unit or the remote stopswitch to stop the unit.
TO 1-1-691
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f. Allow the cleaning compound solution to dwell forseveral minutes, but not long enough to dry on thesurface, and then scrub with a cleaning kit, brush, orcloth and rinse. Refer to Table 3-2 for additional in-structions.
3.4.9 Aqueous Parts Washers. These units are automaticindustrial power washers comprised of an enclosed cabinetequipped with a system of spray impingement nozzles, acycle timer, a cleaning solution reservoir with a heater unit,a fluid pump, and an effluent reservoir with a skimmer unitfor removal of oil, grease, and residues. (Refer to Figure 3-4and Figure 3-5). These automatic washers can effectivelyclean aircraft, missile, and equipment components by usingaqueous cleaning solutions applied at varying combinationsof high temperatures and pressures for the removal of soils,oils/greases, corrosion preventive compounds, and other con-taminants when authorized by the aircraft SPD and/or themissile or equipment SPM. These machines shall be oper-ated per these instructions and the directions in the specificequipment operating manual.
3.4.9.1 Effectiveness of Cleaning in Aqueous PartsWashers.
Materials used in and effluent generated by thiscleaning process may be hazardous to personneland the environment. Contact the local Bioenvi-ronmental Engineer and safety office for guidanceon personal protective equipment (PPE) and otherhealth and safety precautions and waste disposal.Parts may be very hot and retain hot water and/orcleaning solution in part cavities at the end of thecleaning cycle. Handle parts with water proof andheat resistant protective gloves and drain entrappedfluids back into the parts washer.
• Aqueous parts washers shall not be used toclean bearings unless authorized by system spe-cific technical data.
• Due to the maximum allowable pH of 13.5 forthe MIL-PRF-29602 cleaning compounds usedin these parts washers, they can attack alumi-num alloy and IVD aluminum coated parts.Aircraft SPD and/or missile or equipment SPMapproval is required prior to cleaning thesetypes of parts in aqueous parts washers.
• Due to the possibility for hydrogen embrittle-ment and other damage, only those cleaners
which have been tested, approved, and listed inthe most current revision of the applicable land-ing gear technical order shall be used in aque-ous parts washers for cleaning LG componentsincluding wheels and brakes.
• Depending on the type of equipment used, wa-ter/cleaning solution spray pressures in aque-ous parts washers can range from 40 to 100PSI. Suitable fixtures and/or baskets must beused to secure components during the cleaningcycle to prevent damage caused by impinge-ment of the high pressure spray.
The effectiveness of cleaning in aqueous parts washers isinfluenced by several factors that should be considered whenusing this cleaning method.
3.4.9.1.1 Spray Nozzles. There are two basic nozzle de-signs, fan and cone spray. The distance of the parts in thecabinet from the spray nozzles determines how effective theforce of the spray from the nozzles will be and the area ofcoverage. Placing parts too close to the spray nozzles re-duces the surface coverage of the nozzles and too far fromthe spray nozzles reduces the force of the spray. Understand-ing this and racking parts properly in aqueous parts washerswill improve the cleaning effectiveness of the machine.
3.4.9.1.2 Bath Quality. Maintaining the condition of thecleaning bath affects its ability to remove soils. There aretwo types of detergents used in aqueous cleaning, emulsify-ing and non-emulsifying. Emulsifying cleaners break downthe oils and greases and hold them in suspension in the bath.With these cleaning materials, their cleaning ability becomesdegraded by excessive amounts of oil and greases being heldin the bath. It is important to monitor and change the bathsolution routinely to maintain effective cleaning. The non-emulsifying cleaners break down the oils and greases but donot hold the materials in the bath solution, they rise to thetop of the bath. It is important to have an effective skimmeron machines using non-emulsifying cleaners to remove theoil and greases. The proper concentration of cleaner in thebath also affects the bath performance. The heated cleaningsolutions cause evaporation and proper make up of both wa-ter and cleaner should be added. This should be monitoredregularly and adjustments made per the manufacturer’s in-structions.
3.4.9.1.3 Skimmers and Filtration. Several types of bothskimmers and filtration systems are available for use withaqueous parts washers. These have a major impact on main-taining bath quality. It is recommended that both the filtersand skimmers be used and that they be maintained properlyper manufacturer’s instructions to ensure bath quality andthe cleaning effectiveness of the machine.
TO 1-1-691
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3.4.9.2 Determination of Capacity of the AqueousParts Washer. Determine the capacity of the aqueous partswasher cleaning compound reservoir and fill it with MIL-PRF-29602 or the applicable landing gear technical orderapproved cleaning compound solution mixed/diluted per themanufacturer’s directions.
NOTE
Agitation prior to reaching the required operatingtemperature may cause the cleaning solution tofoam excessively. Do not use the washer until thecleaning solution has stabilized at the proper tem-perature.
a. Allow the cleaning solution to stabilize at the tempera-ture recommended by the manufacturer within therange of 140° to 180° F.
• When cleaning components which can entrapfluids, load the components in the basket so thatas many cavities as possible that can entrap flu-ids are face down to prevent corrosion causedby fluid retention.
• Due to evaporation of the heated cleaning baths,the bath level must be monitored. This is nec-essary to ensure levels do not go down and ex-pose the heating elements of the machine asthis will cause them to burn out.
b. Place components to be cleaned in the aqueous partswasher and either secure them to the turntable or se-cure the basket in which they are placed on the turn-table.
Do not leave parts unattended in the washer cabi-net as the very hot and humid environment insidethe unit can cause the parts to corrode rapidly. Re-move the cleaned components from the washer assoon as possible after the cycle is complete.
c. Set the wash cycle timer for 3 to 30 minutes depend-ing on the type of soil to be removed, the quantity ofsoils on the parts, and the number of parts involvedand based on the manufacturer’s recommendations inthe equipment operating manual. Light degreasing mayrequire only 3 minutes while heavy soils and baked on
grease may require a full 30 minute cycle. Always runthe aqueous parts washer for the entire programmedtime cycle and then allow the cleaned components tocool for a short time before removing and handlingthem.
d. If the cleaned components are to be subjected to animmediate in line process such as fluorescent penetrantinspection, surface treatment and/or painting, or fol-low-on precision cleaning, rinse the part with fresh tapwater and dry them thoroughly.
e. Apply a film of MIL-PRF-81309, Type II, MIL-L-87177, Type I, Grade B, or MIL-PRF-16173, Grade 3,followed by a film of MIL-PRF-16173, Grade 4 onbare steel parts that have been cleaned and rinsed andwill be left unprotected from the environment withoutfurther processing for a period of time.
3.4.10 Miscellaneous Equipment. Accessories and con-sumable materials for manual cleaning operations are listedin Appendix A and Appendix B, and include the followingimportant items.
a. The 3M Co., PN 251 aircraft washing kit (refer to Fig-ure 3-6), is a conformable plastic device/head with asurface for attaching non-abrasive cleaning pads andsponges. It attaches to a mop handle for cleaning air-craft surface areas.
b. A-A-3100, non-metallic cleaning and scouring pads arecrimped polyester fiber pads for use with detergentsand solvents for cleaning aircraft, missile, and equip-ment surfaces. These pads can also be attached to a3M Co., PN 251 aircraft washing kit.
c. MIL-B-23958, non-metallic bristle brushes are used toagitate MIL-PRF-87937 and MIL-PRF-85570 deter-gent cleaners on aircraft, missile, and equipment sur-faces during cleaning operations.
d. CCC-C-440, Type I or II, Class 1 or 2 cheesecloth,CCC-C-46, Type I, Class 7 non-woven wiping cloths,A-A-59323, Type I or II low lint cleaning cloths, andSAE AMS 3819, Class 1 or 2, Grade A or B cleaningcloths are used for cleaning critical areas where anexceptionally clean cloth is required, such as solventcleaning prior to painting, adhesive bonding, or seal-ing.
e. A-A-2806, or equal, plastic pump-spray bottles areused for applying diluted MIL-PRF-87937, Type I or
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IV and MIL-PRF-85570, Type I or II, or concentratedMIL-PRF-87937, Type III and MIL-PRF-85570, TypeV cleaning solutions to small, localized areas beingcleaned.
3.5 CLEANING PROCEDURES.
Where high outdoor temperatures are encountered (80° F/27° C and above) and an indoor wash rack is not available,cleaning operations should be scheduled for early morning,late afternoon, or night. Wet aircraft exteriors with fresh wa-ter before applying cleaners to cool surfaces and help pre-vent fast evaporation and drying of cleaners during hotweather. For cold weather procedures, refer to Paragraph3.5.2.6.
NOTE
Only water meeting the requirements in Paragraph3.1.1, step g shall be used in cleaning operations(washing and rinsing) on aircraft, missiles, andequipment.
3.5.1 Warnings and Cautions. The following warningsand cautions shall be observed during aircraft cleaning op-erations:
3.5.1.1 Electrical.
• Aircraft and/or other equipment shall not bewashed, cleaned, or inspected on an outdoorwashrack when an electrical storm is in the im-mediate area.
• Open all circuit breakers associated with bat-tery power (refer to applicable aircraft manu-als), prior to application of flammable solventcleaners.
• In order to guard against the danger of staticelectricity, aircraft shall be electricallygrounded during all cleaning operations andwhen moored and parked.
• Before cleaning electrical and avionic equip-ment, make sure electrical power is discon-nected. Injury or death may otherwise result.
Figure 3-4. Top Loading Type
Figure 3-5. Front Loading Type
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3.5.1.2 Personal Protection.
• Wear rubber gloves, chemical or splash proofgoggles, and water resistant boots during clean-ing operations using MIL-PRF-87937, MIL-PRF-85570, or MIL-PRF-85704 cleaning com-pounds. If cleaner is splashed in eyes, rinsethoroughly with fresh water for 15 minutes andreport to medical facility. Remove clothingsaturated with cleaning solution immediatelyand flush exposed skin areas with fresh water.
• Cleaning solutions are slippery. Use mainte-nance stands where practical. A safety harnessand safety lines shall be used when standing onupper surfaces of aircraft during cleaningoperations.
Consult the local safety office and Bioenvironmental Engi-neer for personal protective equipment (PPE) requirements.
3.5.1.3 Use of Solvents.
• Do not use synthetic wiping cloths with flam-mable solvents such as TT-N-95 aliphatic naph-tha.
• Solvents shall not be applied with atomizingspray equipment. This is not only hazardous,but violates environmental regulations in mostareas.
• Keep all solvents away from open flames andany live electrical circuit or sources of electri-cal arcing. Ensure that residual solvent is re-moved from aircraft, engine bays, and equip-ment.
• Use solvents only in well ventilated areas. Wearchemical resistant rubber gloves and chemicalor splash proof goggles when using solvents.Avoid skin contact. Consult the local safety of-fice and Bioenvironmental Engineer regardingrespiratory protection.
• Do not mix cleaning compounds with any sol-vent, MIL-PRF-32295, such as A-A-59601 andMIL-PRF-680. The added solvents create a firehazard, a serious disposal problem, and candamage non-metallic materials.
3.5.1.4 Use of Cleaners.
• Steam shall not be used for cleaning aircraft,missiles, or their components. Steam can dam-age and/or deteriorate sealants, paint coatings,and elastomers.
• Do not apply MIL-PRF-87937 (except Type IV)or MIL-PRF-85570 (except Type II), A-A-59921 (formerly MIL-C-43616), or MIL-PRF-85704, Type I cleaning solutions or any unau-thorized solvents to electrical wiring or plasticaircraft canopies as they may cause damage toinsulation or crazing of transparent surfaces.
• Do not use cleaning compounds at higher con-centrations than those recommended. Do notallow cleaning solutions to dry on aircraft sur-faces. Such practices cause streaking and candamage aircraft finishes and components.
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3.5.1.5 Water Intrusion.
• To prevent entrapment of water, solvents, andother cleaning solutions inside of aircraft, mis-sile, and equipment parts and structural areas,all drain holes, flapper valves, etc., shall beopened before washing to ensure that properdrainage occurs.
• Do not wash or rinse aircraft, missiles, or equip-ment with a solid stream of water. Use a softspray pattern to avoid damaging fragile sectionsor causing water intrusion.
• Do not direct water streams at pitot tubes, staticports, vents, etc. These areas shall be adequatelyprotected by masking prior to starting a clean-ing operation.
• Relubricate all fittings and other lube points inareas where cleaning compounds have been ap-plied, such as wheel wells, flap wells, flightcontrol wells, etc. Ensure that these areas areadequately drained and check the system spe-cific aircraft manual to determine lubricationrequirements.
3.5.1.6 Oxygen Systems.
Observe warnings and cautions in system specificoxygen system manuals.
3.5.1.7 Special Precautions.
Use extreme care when cleaning around radomes,access doors to integral fuel tank cells, light fix-tures, electrical components, antennas, etc. Theseareas may be damaged by cleaning solutions andequipment.
3.5.1.8 Preparation for Cleaning.
Open all circuit breakers associated with batterypower (refer to applicable system specific aircraftmanuals), prior to application of any flammablesolvent.
Cover acrylic or polycarbonate canopies and win-dows on aircraft during washing operations to pre-vent accidental scratching or crazing by cleaningcompounds and equipment. Cover canopies and/orwindows with A-A-50129 flannel cloth. Cover theflannel cloth on the canopies and/or the windowswith MIL-PRF-131, Class 1 barrier material (plas-tic side toward aircraft) and tape it to the canopyand/or window frames, or the painted surface nearthem using AMS-T-21595, Type III masking tapeor AMS-T-22085, Type II preservation tape orequivalent. Do not apply the tape directly to thetransparent surfaces.
3.5.1.9 Pre-Wash Lubrication Point Protection. To pro-tect against cleaning solution entrapment, inspect all lubrica-tion points having exposed lubrication fittings. Prior to mask-ing any components or parts, remove all foreign matter fromjoints, fittings, and bearing surfaces, using a CCC-C-46,non-woven cleaning cloth or an SAE AMS 3819, Class 1,Grade B cleaning cloth. Wipe up all spilled or excess oil andgrease. Mask all fittings which will be exposed to wash so-lutions with MIL-PRF-131, Class 1, barrier material andAMS-T-21595, Type III masking tape or equivalent, asneeded. See the applicable system specific maintenancemanuals and card, and Paragraph 3.6 for location of lubrica-tion points.
NOTE
Consult the system specific aircraft (-23) corro-sion manual for cleaning operation masking re-quirements for specific aircraft in addition to thosein this manual.
3.5.1.10 Water/Cleaning Compound Intrusion. Take thefollowing steps to prevent water/cleaning compound intru-sion during cleaning operations:
a. Close all doors, removable panels, and emergencyopenings, and seal and/or mask their edges, if required,to prevent leakage into interior areas. Mask all areaswhere cleaning solutions and water can become en-trapped and cause corrosion and other damage to air-craft and missile components and structure, such aspod doors, areas around thrust rings, radomes, opticalglass, nirdomes, etc. Use prefabricated covers and/orMIL-PRF-131, Class 1 barrier material and AMS-T-21595, Type III masking tape or AMS-T-22085, TypeII preservation tape or equivalent for masking.
b. Check drain holes. Make sure that all drain holes areclean by inserting a probe, such as a pipe cleaner, into
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them except for pressurized flapper valves. Refer tosystem specific aircraft maintenance manuals or (-23)corrosion manuals for location of drain holes.
Make sure that pitot static tubes and static vents/openings/ports are not fouled by tape adhesivetransfer. Cover them as directed in step c below.
c. Cover all static vents, openings, and ports with circularcut pieces of MIL-PRF-131, Class 1 barrier material(plastic side toward the aircraft surface) and hold inplace with AMS-T-21595, Type III masking tape orAMS-T-22085, Type II preservation tape or equivalent.Refer to system specific aircraft and missile mainte-nance manuals and (-23) corrosion manuals for loca-tions of static vents, openings, and ports to be masked.Place covers on pitot static tubes. If covers are notavailable, a piece of MIL-PRF-131, Class 1 barriermaterial may be cut and taped in place on the pitotstatic tube with AMS-T-21595, Type III masking tapeor AMS-T-22085, Type II preservation tape or equiva-lent. Covers and masking must be removed prior torelease of aircraft for flight. Particular care shall betaken to ensure that static vents, openings, and portsand pitot static tubes are not fouled by tape adhesivetransfer. In the event of significant adhesive transfer,clean with TT-N-95 aliphatic naphtha.
Do not use a direct spray of water or cleaningcompound on carbon brakes, wheels, or wheelhubs. If wheel bearings are suspected of contami-nation, corrosion, or loss of lubricant, removewheel bearings and relubricate in accordance withapplicable system specific maintenance instruc-tions and TO 4W-1-61. If carbon brakes are sus-pected of contamination, decontaminate per appli-cable system specific maintenance instructions andTO 4B-1-32.
d. Cover wheels with covers designed and manufacturedfor the specific aircraft or locally fabricated covers toprevent water/cleaning compound contamination ofwheel bearings and carbon brakes. Carbon brakes havetemporarily reduced performance when subjected towater, deicers, degreasers, and oil. Protect brakes fromdirect impingement of fluids as much as practical dur-ing maintenance and aircraft cleaning operations. Weakor spongy brakes (and in some cases, smoke), mayresult until the contaminants are burned off (normallyone flight/take off and landing).
3.5.2 Cleaning Methods.
• Wear rubber gloves, chemical or splash proofgoggles, and water resistant boots during clean-ing operations using MIL-PRF-87937, MIL-PRF-85570, or MIL-PRF-85704 cleaning com-pounds. If cleaner is splashed in eyes, rinsethoroughly with fresh water for 15 minutes andreport to medical facility. Remove clothingsaturated with cleaning solution immediatelyand flush exposed skin areas with fresh water.
• Open all circuit breakers associated with bat-tery power (refer to applicable system specificaircraft manuals), prior to application of flam-mable solvents.
• There are potential health risks associated withcleaning compounds if proper handling, mix-ing, and usage instructions are not followed.Consult the specific cleaning compound SafetyData Sheets (SDS) and the local safety officeand Bioenvironmental Engineer for specificinformation.
The methods for cleaning aircraft, missiles, and equipmentmay vary depending upon the type of aircraft, missile, orequipment involved. Use the following methods for cleaningaircraft, missile, and equipment exterior surfaces. Refer toTable 3-2 for instructions on specific areas and componentsand Table 3-3 for deicing/anit-icing fluid residue inspectionand removal.
3.5.2.1 Alkaline Detergent and/or Solvent EmulsionCleaning, Painted and Unpainted Surfaces; Fresh Wa-ter Readily Available.
Do not use A-A-58054 abrasive mats for cleaningoperations on painted or unpainted surfaces.
Accomplish cleaning operations in planned steps startingwith the lowest and most inboard surfaces to be cleaned andwork upward and outward. Dilute and/or mix cleaning com-pounds as recommended in Table 3-2.
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a. Flush aircraft, missile, or equipment surfaces with freshwater when necessary to reduce skin temperature.Streaking will occur if cleaning solutions run down onand/or dry on hot painted or unpainted surfaces.
• A-A-59921 (formerly MIL-C-43616) solventemulsion cleaner and A-A-59601 and/or MIL-PRF-680 solvents shall not be used on non-polyurethane paint systems and markings as thesolvent materials will cause them to fade.
• Consult the base Bioenvironmental Engineerbefore using these solvent materials as they cancreate waste disposal problems.
b. Apply properly mixed/diluted MIL-PRF-87937, Type Ior IV, or MIL-PRF-85570, Type I or II cleaning com-pound solution from a bucket, spraying equipment (in-cluding the high pressure type if approved by the air-craft SPD and/or the missile or equipment SPM), orfoaming equipment. Scrub surfaces with a 3M Co., PN251 aircraft washing kit (Appendix B, Item No. 1) fit-ted with a cleaning pad (Appendix A, Item No. 37,refer to Figure 3-6), one of the 3M Co., improved washpads fitted to its appropriate holder and handle (Ap-pendix A, Item No. 38), or with a cleaning brush. Al-low the solution to dwell on the surface for 5 to 10minutes. Start at the lower and inboard edges of thesurfaces being cleaned working upward and outward.(Refer to Figure 3-7).
NOTE
MIL-PRF-87937, Type I materials contain ter-penes. Aircraft SPD and/or missile or equipmentSPM restrictions may apply. Consult system spe-cific maintenance manuals.
c. Rinse away the loosened soil and cleaner with fresh,heated, tap water at a temperature of 120° F/49° Cminimum to 140° F/60° C maximum. Use a rubberpadded shutoff spray nozzle (refer to Figure 3-8), torinse the cleaner and loosened soil from aircraft, mis-sile, or equipment surface. Adjust the nozzle to pro-vide a light to coarse fan spray directed at an anglebetween 15° and 30° from the surface. Start at theoutboard and upper edges of the area being rinsed
working inward and downward. Continue rinsing untilall evidence of cleaner and soils have been removedfrom aircraft, missile, or equipment. Small areas maybe rinsed with water applied with cloths or spongeswhich are rinsed out frequently, and then dried with aclean cloth or sponge, or allowed to air dry.
NOTE
If hot water is unavailable, regular tap water maybe used for rinsing but it takes a great deal longer,requires much more water, and is not as efficientin removal of residue from the surface. Hot waterrinsing is known to reduce man-hours required forrinsing by approximately 20%.
d. For aircraft or equipment painted with a low gloss/flatand/or camouflage paint scheme, ground-in soils (bootmarks, smudges, etc.,) can be cleaned with MIL-PRF-85570, Type IV spot cleaner. Apply with a cleaningpad or sponge and after several minutes dwell time,scrub these areas with the pad or sponge and rinsethoroughly. When the rubber particles in this cleanerare rubbed with the pad, removable soils are erasedfrom the low areas or depressions in the surface of thepaint
Figure 3-6. Use of Aircraft Washing Applicator
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Figure 3-7. Aircraft Cleaning Procedure
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e. Clean wheel, flap, aileron, elevator, rudder wells, andother heavily soiled areas which can tolerate waterrinsing with MIL-PRF-87937, Type III or MIL-PRF-85570, Type V gel cleaner. These cleaning compoundsmay be sprayed on using a hand operated pump spray.Allow to dwell for 5 to 15 minutes and then rinsethoroughly with a rubber padded shutoff fan spraynozzle adjusted to provide a light to coarse fan spray.(Refer to Figure 3-8).
f. Clean painted and unpainted surfaces on aircraft, mis-siles, and/or equipment that are protected/treated withCPC’s with A-A-59921 (formerly MIL-C-43616),Class 1A solvent emulsion cleaner applied by spray orA-A-59601, Type II or III, MIL-PRF-32295, Type II,or MIL-PRF-680, degreasing solvents applied with abrush, cloth, sponge, or non-atomizing spray. Rinse thearea thoroughly with fresh tap water (preferably hotwater), and then wash by alkaline detergent cleaningper step b and step c above.
NOTE
MIL-PRF-87937, Type III or MIL-PRF-85570,Type V gel cleaning compounds may be used asalternates to clean CPC coated areas per proce-dure in step e above.
g. If surfaces are not clean at this point, repeat the clean-ing process.
3.5.2.2 Waterless Wipe Down. Waterless wipe downprocedures for spot cleaning will be used only when water isnot available for rinsing or when cold weather prevents theuse of water. The waterless wipe down method for removalof soils and corrosive salt residues is as follows:
a. Using a plastic spray bottle, apply MIL-PRF-87937,Type I or IV or MIL-PRF-85570, Type I or II, (mixedone part cleaner to nine parts water) to the exteriorsurfaces of the aircraft (several square feet at a time).
NOTE
MIL-PRF-87937, Type I materials contain ter-penes. Aircraft SPD and/or missile or equipmentSPM restrictions may apply. Consult system spe-cific maintenance manuals.
b. After 30 seconds, scrub, then wipe cleaner and soilfrom the surface with a clean CCC-C-46, Type I, Class7 or SAE AMS 3819, Class 1, Grade B cloth.
c. Rinse the cleaned surface with fresh water when it be-comes available and/or weather permits.
3.5.2.3 Alkaline Detergent Cleaning with Only LimitedFresh Water Available. Use the following procedure onlywhen sufficient rinse water is not available.
a. Mix either of the following in a bucket depending onthe type of soil to be removed.
(1) One part MIL-PRF-87937, Type I or IV or MIL-PRF-85570, Type I or II cleaning compound andsixteen parts water for removal of light to moder-ate soils.
(2) One part MIL-PRF-87937, Type I or IV or MIL-PRF-85570, Type I or II cleaning compound andfour parts water for removal of heavy soils.
NOTE
MIL-PRF-87937, Type I materials contain ter-penes. Aircraft SPD and/or missile or equipmentSPM restrictions may apply. Consult system spe-cific maintenance manuals.
b. Apply the cleaner with a cleaning pad, sponge, cloth,or cleaning brush one small area at a time (10 to 20SQFT).
c. Scrub the area with the applicator from step b, andthen wipe clean with a CCC-C-46, Type I, Class 7 orSAE AMS 3819, Class 1, Grade B cloth.
d. For very stubborn soils, clean with A-A-59601, MIL-PRF-32295,Type I or II, or MIL-PRF-680, degreasingsolvent, and then scrub with one of the above solutionsin step (1).
3.5.2.4 Solvent Cleaning. The use of MIL-PRF-87937,Type III or MIL-PRF-85570, Type V cleaning compoundsfor cleaning very stubborn or exceptionally oily areas onexhaust tracks, landing gears, wheel wells, control surfacewells, and engine nacelles will normally be sufficient. Whenthese materials do not completely clean these areas, A-A-59601, MIL-PRF-32295, Type II, or MIL-PRF-680, can beused in small quantities. The quantity used shall be limitedto the minimum necessary to accomplish the required clean-ing. Remember that solvents will burn intensely once ig-nited, so limit the amount of solvent available at the aircraft,missile, or piece of equipment to a maximum of three gal-lons under the use and/or control of each authorized personinvolved in the solvent cleaning operation. Each authorizedperson shall be thoroughly familiar with applicable safetyprecautions and disposal requirements/information. The sol-vent dwell time on painted surfaces shall be held to a mini-mum of 10 to a maximum of 15 minutes to prevent softeningof the paint. Any dirty solvent draining off the surface duringthe cleaning operation shall be controlled to prevent unau-thorized entry into the sewer. All solvent spillage shall becleaned up per local regulations/directions. In no instanceshall solvents be allowed to drain into or enter a public seweror otherwise be allowed to contaminate streams or lakes.These guidelines shall be followed when using A-A-59601,MIL-PRF-32295, Type II or MIL-PRF-680, solvents.
a. Use only in areas approved by the local safety office.
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b. Ensure that the area within 50 feet of the solventcleaning operation is clean and remains clear of allpotential ignition sources.
c. Use only explosion-proof electrical devices and powerequipment. Power units used in servicing shall beplaced upwind and beyond the 50 feet clearance. En-sure that the aircraft, missile, or equipment is properlygrounded.
d. No smoking shall be allowed in the solvent cleaningarea.
e. Mixing of solvents with other chemicals, cleaningcompounds, water, etc., is strictly prohibited except asspecified by this manual.
f. Suitable fire extinguishing equipment shall be avail-able to the solvent cleaning area.
g. Wear ANSI Z87.1, Type II goggles, protective wetweather clothing, solvent resistant gloves, boots, andhead covering. Use a respirator fitted with organic va-por cartridges when working in an enclosed area. En-sure that good ventilation is maintained. Consult thelocal safety office and Bioenvironmental Engineer forPPE requirements.
h. Apply A-A-59601, MIL-PRF-32295, Type II, or MIL-PRF-680, solvents using a pad, cloth, or brush. Cleanup solvent spills as they occur.
i. Ensure that no solvent is trapped or has entered theequipment interior. Remove by wiping with clean cot-ton wiping cloths or by blowing dry, using clean, lowpressure air (10-15 PSI).
j. Collect waste solvents and solvent wetted wiping ragsand dispose of them per local regulations/directions.
k. After cleaning with A-A-59601, MIL-PRF-32295, TypeII, or MIL-PRF-680 solvents, reclean the area usingprocedures in Paragraph 3.5.2.1 to remove residue leftby the solvents.
3.5.2.5 Interior Cleaning (Vacuum). Remove dirt, dust,small loose objects, paper, etc., from an area with an indus-trial or domestic type vacuum cleaner. A soft bristle brush onthe end of the inlet tube/hose of the vacuum cleaner will aidin removal of soils.
a. Inspect aircraft floor boards and bilge area underneaththe floor boards during depot level maintenance and as
may otherwise be required during field level mainte-nance for conditions that would necessitate cleaning orcorrosion removal and treatment. Particular attentionshall be given to urinal and latrine areas.
Accidental spills shall be investigated immediatelyafter occurrence to determine if the spilled mate-rials are corrosive. Spills determined to be corro-sive shall be neutralized as soon as possible perdirections in AFMAN 24-204-IP followed bycleaning per procedures in Table 3-2. Failure tocomply can result in extensive corrosion damageand possible unsafe conditions for operation of theaircraft, missile, or equipment.
b. When it is determined that harmful contamination, (i.e.,dirt, spillage, foreign material, etc.,) is present in anaircraft bilge area, remove the floor boards as neces-sary to allow proper cleaning of the bilge area.
c. Clean the aircraft bilge area by vacuuming up all looseforeign material, dirt, etc., The vacuum removal of dirtor soil may be aided by agitating with the brush. Becareful not to sweep or wipe the dirt, etc., into oily orwet areas.
Ensure there is adequate ventilation when usingA-A-59601, MIL-PRF-32295, Type II, or MIL-PRF-680, solvents and be sure the bilge and/orother areas are properly ventilated (blown out) be-fore floor boards are reinstalled or closed. Warn-ing signs shall be conspicuously placed at all air-craft entrances to indicate that combustiblematerials are being used. The guidelines cited inParagraph 3.5.2.4 for solvent cleaning proceduresapply.
d. Clean oily areas and/or spots by wiping them with aclean cloth dampened with A-A-59601, MIL-PRF-32295, Type II, or MIL-PRF-680, solvent followed im-mediately by drying with a clean dry cloth. Do notoversaturate the cloth used for applying the solventbecause this may result in the solvent puddling or en-tering recessed areas and creating a fire hazard. Pre-cautions shall be taken when using these solventsaround electrical equipment to prevent entry.
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Before starting the following cleaning operation,be sure that the spray or other method of applica-tion will not result in moisture damaging anycomponents, especially electrical components. Be-fore using a spray method, ensure all drain holesare open, that the fluid materials will drain, andthat the cleaning solution will not be forced intoinaccessible areas. Do not apply the solution toany moisture absorbing material such as insula-tion, sponge rubber (open cell), felt, etc.
e. If further cleaning is required, use a solution of onepart MIL-PRF-87937, Type IV or MIL-PRF-85570,Type II mixed with nine parts fresh water applied byspray, mop, sponge, or brush. Use this solution only ifit can be adequately rinsed and/or removed from thesurface.
f. After applying the cleaning solution, allow dwell timeof approximately 10 minutes, agitate the solution onthe surface with a non-metallic bristle brush, and flushor rinse with clean water. Check drain holes to ensurethat they are open and that the cleaning solution andwater are draining properly. Remove any remainingwater using clean cloths. The surface shall then bethoroughly dried by blowing warm air over the surfaceor wiping with clean, dry cloths.
g. In those areas where the above procedures cannot beused due to lack of drainage, possible damage to com-ponents, etc., hand cleaning procedures will have to beused. Apply a solution of one part MIL-PRF-87937,Type IV or MIL-PRF-85570, Type II mixed with nineparts water to the surface with a rag or sponge wettedwith the solution and then agitate it with the applicator.Immediately following agitation of the solution, rinsethe area by wiping it with a rag wetted with clean
Figure 3-8. Automatic Water Spray Nozzle
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water and then wipe it dry with a clean, dry rag. Thisprocedure may have to be repeated several times onextremely soiled areas.
h. If corrosion is encountered and/or paint is removed,treat the corrosion per this manual and the applicablesystem specific maintenance manual, and touch-up thepaint system per TO 1-1-8 and the applicable systemspecific maintenance manual before the floor boardsare replaced or area is closed.
3.5.2.6 Low Temperature Cleaning. Do not perform rou-tine scheduled cleaning when the temperature is 40° F (4° C)and below. Instead, aircraft, missiles, or equipment shall becleaned in an indoor, heated wash rack. However, if the tem-perature is between 40° F (4° C) and 32° F (0° C) and sucha facility is not available, exterior areas/surfaces on aircraft,missiles, or equipment contaminated with corrosive materi-als, such as runway deicing agents and salt water shall havethese areas/surfaces cleaned outdoors using the waterlesswipe down method in Paragraph 3.5.2.2. Normal cleaningsolutions cannot be used in freezing weather of 32° F (0° C)and below, so under these conditions, the following proce-dures shall be used for cleaning:
Table 3-4. Recommended Dilution of Low Tem-perature Cleaner
Ambient (Room)Temperature
Dilution Ratio (PartsMixture: Parts Water)
+30° F and above 1:4+10° F to +30° F 1:2+10° F and below 1:1
SAE AMS 1424, Type I aircraft deicing/anti-icingfluid is mildly toxic. Contact with skin and eyesshall be avoided. Do not inhale deicing fluid mist.Spray equipment operators and personnel usingbrush applicators should stay on the windward side
of the aircraft and/or equipment to be cleaned dur-ing cleaning solution application. Chemical, splashproof goggles and wet weather gear, includingboots and gloves, shall be worn by all mainte-nance personnel involved in low temperaturecleaning operations.
TT-I-735 isopropyl alcohol or any other alcoholshall not be used for deicing acrylic plastic cano-pies. Use Type SAE AMS 1424, Type I aircraftdeicing/anti-icing fluid for these applications.
a. If necessary, deice the aircraft, missile, or equipmentper procedures in TO 42C-1-2 and/or the applicablesystem specific maintenance manual.
b. Solvent clean heavily soiled areas of aircraft by wipingor brushing with A-A-59601, Type II or III or MIL-PRF-680, Type II or III degreasing solvent using pro-cedures in Paragraph 3.5.2.2.
c. To make a low temperature cleaner, mix ½ pint ofconcentrated/undiluted MIL-PRF-87937, Type IV orMIL-PRF-85570, Type II cleaning compound into onegallon of the ready-to-use (RTU) SAE AMS 1424,Type I aircraft deicing/anti-icing fluid or into one gal-lon of a solution of the concentrated form of the SAEAMS 1424, Type I aircraft deicing/anti-icing fluid di-luted 1 to 1 with water. If necessary, warm either ofthese cleaning compound materials until they can beeasily poured into the deicing/anti-icing fluid. Mixthoroughly.
d. Dilute this mixture, as required, by the ambient (room)temperature involved per Table 3-4 and mix thoroughly.
e. Scrub the aircraft, missile, or equipment using a brush,cloth, or aircraft washing kit.
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f. Rinse by deicing as in step a. Heated deicing/anti-icingfluid mixtures will speed up the rinsing process.
3.5.3 Clear Water Rinsing of Aircraft.
• Do not rinse aircraft with a solid stream of wa-ter. Use a soft, spray pattern to avoid damagingfragile sections or causing water intrusion. Wa-ter must not be directed at pitot tubes, staticports, vents, etc. Critical areas shall be ad-equately protected with ground plugs, covers,etc.
• Clear water rinsing shall not be accomplishedoutside when the temperature is at 40° F (4° C)or below. Spraying flight control areas outsidewith water when the temperature is belowfreezing can result in ice that could impair flightcontrols.
• Application of water in wheel wells, flap wells,flight control wells, etc., may necessitate therelubrication of some components/areas. Ensurethat these areas are adequately drained andcheck the system specific aircraft maintenancemanuals to determine lubrication requirements.
NOTE
• Clear water rinsing does not satisfy aircraftwashing requirements.
• Only water meeting the requirements in Para-graph 3.1.1, step g shall be used for clear waterrinse operations.
3.5.3.1 Requirements. As directed by the requirementsin Paragraph 3.2.3, aircraft shall be clear water rinsed toremove salt contamination from aircraft surfaces caused byoperations near salt water. Most salt deposits are readily dis-solved and/or dislodged and flushed away by rinsing. Rins-ing can be done in a taxi-through facility or by direct manualspraying.
3.5.3.2 Taxi-Through Rinsing. Deluge rinse facilities(bird baths) are automatic installations located in a taxiwayarea for use by aircraft after flight through salt air. Theseinstallations provide multiple jet sprays of fresh water tocover the entire aircraft exterior surface to rinse off salt andwater soluble contaminants. Such facilities should be used asfrequently as possible per the requirements in Paragraph3.2.3.
3.5.3.3 Manual Application. Fresh water can be appliedfrom a hand held hose or piece of spraying equipment. Theforce or pressure used to apply the water is not as critical as
the amount of water. Satisfactory results are achieved withan amount of water that will create a full flowing action overthe surface. This requires a minimum of eight gallons perminute (GPM) of water at a nozzle pressure of 25 PSI mini-mum to 175 PSI maximum.
3.5.3.4 Rinsing Procedures. Clear water rinsing shall beaccomplished as follows:
a. Direct water at an angle of 15° to 30° from the surface.Ensure that sufficient water flow is achieved on all sur-faces.
b. Begin rinsing on lower surfaces and work upwardstarting with the lower wing surfaces, then the lowerfuselage, and the lower horizontal stabilizer surfaces.Then rinse from the top down, starting with the upperand lower surfaces of the horizontal stabilizer on T-tailaircraft, the vertical stabilizer surfaces, then the upperfuselage, upper wing surfaces, and upper horizontalstabilizer surfaces. (Refer to Figure 3-7).
3.5.4 Post Cleaning Procedures.
Do not use synthetic wiping cloths with flammablesolvents as these solvents can dissolve them.
3.5.4.1 Post Cleaning Task Sequence. Strict compli-ance with the following post cleaning procedures is essentialand they shall be done in the following order.
a. Remove covers and masking from all static vents, pitotstatic tubes, air ducts, heater ducts, etc.
b. Remove tape from all other openings sealed with mask-ing tape.
c. Remove all tape adhesive residues with TT-N-95 ali-phatic naphtha or TT-I-735 isopropyl alcohol.
d. Ensure all drain holes are open by inserting a probe,such as a pipe cleaner.
e. Ensure that all areas that accumulate water have beendrained and/or otherwise dried. Whenever this is a re-curring problem, specialized procedures shall be de-veloped and implemented to remove entrapped waterand other fluids to prevent their accumulation.
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3-46 Change 13
An effective corrosion prevention and control pro-gram requires that prescribed preservation and lu-brication procedures be accomplished as soon aspossible after a cleaning operation to prevent/mini-mize the occurrence of corrosion.
f. Upon completion of all cleaning operations, lubricateall exposed static joints and inject lubricant into alllube fittings in the areas cleaned in accordance withParagraph 3.6 and applicable system specific mainte-nance manuals to displace any entrapped water orcleaning materials that could cause corrosion and fail-ure of lubricated parts if they remained.
g. Apply preservatives/corrosion preventive compounds(CPC’s) to components in the area cleaned in accor-dance with Paragraph 3.7 and applicable system spe-cific maintenance manuals, as necessary. Cleaningcompounds tend to remove preservatives, making pre-viously protected surfaces vulnerable to corrosion.
3.5.5 Treatment and Disposal of Wash Rack Waste.
NOTE
Cleaning solutions which remove greases, oils, andsurface contamination from aircraft, missiles,equipment, and components may exceed dischargeconcentration limits for oil and grease (especiallywhere oil/water separators are not installed or notoperating properly), naphthalene (from cleanerscontaining aromatic hydrocarbons), chromium,cadmium, nickel, or other heavy metals (fromcleaning operations involving engines or platedparts). If your wash rack is a source of hazardous
waste, consult the base safety office and/or Bioen-vironmental Engineer to determine corrective ac-tion. Take precautionary measures to prevent washrack waste from contaminating lakes, streams, orother natural environments. Some chemicals usedfor cleaning require treatment or other specialcontrols prior to disposal.
The disposal of materials shall be accomplished in accor-dance with applicable directives and in a manner that willnot result in the violation of local, state, or federal pollutiondirectives.
a. To reduce the problems associated with disposal andthe actual cleaning process, all work shall be accom-plished on an approved wash rack. The only exceptionto this requirement shall be for those facilities whichare temporarily established to support combat opera-tions or special missions.
b. Aircraft wash rack cleaning waste shall receive theequivalent of secondary sewage treatment. When MIL-PRF-85704, Type I solvent emulsion cleaning solutionsare used, waste shall be released so that the total efflu-ent entering the waste treatment plant does not containmore than the amount limited by local environmentalregulations or 100 parts per million (PPM) of cleaningcompound.
3.5.6 Fungus Growth Removal. Fungus growth (mildewand mold) occurs on the surface of organic materials (plas-tics, paper, organic coatings/paints, etc.,) and inorganic ma-terials (metals, concrete, etc.,) particularly in warm, damp/humid climates. Fungus growths must be removed to preventcorrosion of metals and deterioration of other materialscaused by fungus by-products. Refer to Table 3-4.1 for spe-cific cleaning instructions.
Table 3-4.1. Fungus Growth Removal from Organic Materials
Organic Material Type of Soil Cleaning Agent orCompound
Mixing Directions andNomenclature
Cleaning Procedures
A 50-50 by volume mixture of isopropyl alcohol and water is flammable with a flash point of 60 °F. Use only withadequate ventilation and comply with guidelines for solvent cleaning in this chapter. Open all circuit breakersassociated with battery power (refer to applicable system specific maintenance manuals), prior to application ofTT-I-735 isopropyl alcohol. Do not use synthetic wiping cloths with flammable solvents such as TT-I-735 isopropylalcohol. Failure to strictly observe could result in injury to, or death of personnel or long term health hazards.
TO 1-1-691
Change 13 3-47
Table 3-4.1. Fungus Growth Removal from Organic Materials - Continued
Organic Material Type of Soil Cleaning Agent orCompound
Mixing Directions andNomenclature
Cleaning Procedures
Do not use isopropyl alcohol on transparent acrylic or polycarbonate plastics used for aircraft canopies andwindows or methacrylate plastic (Plexiglass) components as it can cause them to craze. If not strictly observe couldresult in damage to or destruction of, equipment or loss of mission effectiveness.
Plastics,PlasticElectricalInsulation
Fungi, Mold,Mildew
TT-I-735, Grade A orB (IsopropylAlcohol)
50-50 by volume solutionof TT-I-735, Grade AOr S, and fresh tapwater with two (2) fluidounces of P-D-410,Type II detergent pergallon of solution.
Scrub the contaminated areawith a lint free cloth orsponge wet with 50-50TT-1-735 solution. Wipe offthe residue with a lint freecloth wet with fresh tapwater and wipe dry with aclean, dry cloth.CCC-C-440, Type I or
II, Class 1 orA-A-59323, Type IIor SAE AMS 3819,Class 1, Grade A orB.
Cotton CheeseclothCleaning Cloth LowLint Cleaning Cloth
Navclean Mildew Mix per manufacturer’sdirections.
Apply and clean contaminatedarea using lint free cloth,soft bristle brush or spongewet with Navclean. Allowformula to remain on thesurface for 5-15 minutes.Thoroughly rinse treatedsurfaces with fresh tap waterto ensure no residueremains. Reapply Navcleanas necessary followed bythorough rinsing. Inspecttreated surfaces for detergentresidue. If any indication ofresidue remains, rinse treatedsurfaces again with freshwater and re-inspect. Repeatprocess as necessary toremove residue.
Remover Kit NSN6850-01-581-2150(Single Kit) or NSN6850-01-581-2172(Five Single Kits)
TT-N-95 Aliphatic Naphtha is flammable and toxic to the skin, eyes, and respiratory tract. Keep away from allsources of ignition. Avoid skin and eye contact. Good general ventilation is adequate. Failure to strictly observecould result in injury to, or death of personnel or long term health hazards.
TT-N-97 Aromatic Naphtha shall not be used to clean transparent plastics as it can attack and damage them. If notstrictly observed could result in damage to or destruction of equipment or loss of mission effectiveness.
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3-48 Change 13
Table 3-4.1. Fungus Growth Removal from Organic Materials - Continued
Organic Material Type of Soil Cleaning Agent orCompound
Mixing Directions andNomenclature
Cleaning Procedures
Acrylic,PolycarbonateandMethacrylate(Plexiglass)TransparentPlasticComponents
Fungi, Mold,Mildew
TT-N-95 (AliphaticNaphtha
Aliphatic Naphtha Scrub contaminated area withlint free cloth or sponge wetwith TT-N-95 and then wipewith a clean, dry cloth. Ifpolishing is required, rubarea with SS-P-821, Grade For finer pumice abrasive.Consult TO 1-1A-12 fordetails on polishingtransparent plastics.
CCC-C-440, Type I orII, Class 1 orA-A-S9323, Type IIor SAE AMS 3819,Class 1, Grade A orB.
Cotton CheeseclothCleaning Cloth LowLint Cleaning Cloth
SS-P-821 or FinerPumice GroundAbrasive
Pumice Ground Abrasive
Metal Surfacesother thanelectricalconnectors
Fungi, Mold,Mildew
IT-I-735, Grade A or B(Isopropyl Alcohol)
Isopropyl Alcohol Wipe the contaminated surfaceother than electricalconnectors with TT-I-735,Grade A or B followed bycleaning per the standardmethods in Table 3-2 for thetype of area involved.
CCC-C-440, Type I orII, Class 1 orA-A-S9323, Type IIor SAE AMS 3819,Class 1, Grade A orB.
Cotton CheeseclothCleaning Cloth LowLint Cleaning Cloth
Navclean MildewRemover Kit NSN6850-01-581-2150(Single Kit) or NSN6850-01-581-2172(Five Single Kits)
Mix per manufacturer’sdirections.
Apply and clean contaminatedarea using lint free cloth,soft bristle brush or spongewet with Navclean. Allowformula to remain on thesurface for 5-15 minutes.Thoroughly rinse treatedsurfaces with fresh tap waterto ensure no residueremains. Reapply Navcleanas necessary followed bythorough rinsing. Inspecttreated surfaces for detergentresidue. If any indication ofresidue remains, rinse treatedsurfaces again with freshwater and reinspect. Repeatprocess as necessary toremove residue.
Exterior Surfacesof ElectricalConnectors andMalePins/Contacts
Fungi, Mold,Mildew
TT-I-735, Grade A orB (IsopropylAlcohol)
Isopropyl Alcohol Wipe contaminated exteriorsurface with a lint free clothor brushing withnon-metallic bristle brushwet with TT-I-735, Grade Aor B followed by rinsingwith a stream of the alcoholfrom a plastic wash bottleand then drying with clean,dry, oil free compressed air(15 PSI max).
CCC-C·440, Type I orII, Class 1 orA-A-S9323, Type IIor SAE AMS 3819,Class 1, Grade A orB.
Cotton CheeseclothCleaning Cloth LowLint Cleaning Cloth
Non-metallic BristleBrush (tooth brush)
TO 1-1-691
Change 2 3-48.1
Table 3-4.1. Fungus Growth Removal from Organic Materials - Continued
Organic Material Type of Soil Cleaning Agent orCompound
Mixing Directions andNomenclature
Cleaning Procedures
NOTE
Consult TO 1-1-689 series for additional information on cleaning of electrical connectors.
FemalePins/Contacts
Fungi, Mold,Mildew
TT-I-735, Grade A orB (IsopropylAlcohol)
Isopropyl Alcohol Scrub pins/contacts with pipecleaner or toothpicksaturated with TT-I-735,Grade A or B followed byrinsing with a stream ofalcohol with a plastic washbottle and drying with clean,dry, oil free compressed air(15 PSI max).
Pipe Cleaner orToothpick
Fuel Systems Fungi, Mold,Mildew
Contact the appropriate aircraftSPD and/or missile orequipment SPM.
3.5.7 Soil Barriers.
Do not apply soil barrier materials to any areaother than engine exhaust and gun gas residue ar-eas on aircraft having a camouflage or a flat paintscheme. These materials increase the speculargloss and IR reflectance of paint systems therebycompromising the effectiveness of the camouflageand flat paint schemes.
Soil barriers are transparent materials that are very effective
in preventing damage to both painted and unpainted engineexhaust track areas and areas exposed to gun gas residue onaircraft and/or other equipment. Soil barrier materials shallbe applied to these areas on aircraft immediately after curingof a new or overcoat paint system prior to engine run andexisting paint systems after each aircraft wash as a part ofthe aircraft wash. Soil, soot, and/or gun gas residue gradu-ally accumulate on or in the soil barrier film instead of thepaint system protected by the film. When the protected areadoesn’t meet acceptable aircraft or equipment appearancestandards or an aircraft undergoes a routine wash, removethe soil barrier film per Paragraph 3.5.7.3 and reapply perParagraph 3.5.7.2 using materials specified in Paragraph3.5.7.1.
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3-48.2 Change 2
3.5.7.1 Materials. McGean-Rocho, Inc., PN Cee-Bee A-6is the soil barrier material approved for use on Air Forceaircraft and equipment.
NOTE
• Rain or water do not deteriorate soil barriermaterials but solvents, alkaline cleaners, andsolvent emulsion cleaners tend to degradeand/or remove them.
• If the temperature of the surfaces to be treatedwith soil barriers reaches or exceeds 100° F(38° C), cool the surfaces with a light spray offresh water before applying soil barrier materi-als.
• No prior cleaning and/or rinsing of an area isrequired if soil barriers are being applied on anew or overcoat paint system.
3.5.7.2 Application. If an old soil barrier film is presenton the surface, remove it per Paragraph 3.5.7.3.
a. Thoroughly clean surface with MIL-PRF-87937, TypeIV or MIL-PRF-85570, Type II cleaning compound perTable 3-2 and Paragraph 3.5.2.1.
b. Rinse surface thoroughly with fresh water to removeall grease, oil, dirt, and cleaning compound residue andallow the water to drain off.
c. When most of the rinse water has drained off, apply auniform film of either soil barrier material listed inParagraph 3.5.7.1 with a non-atomizing type sprayer(garden sprayer), brush, or roller, and allow the film todry for 1 hour before releasing the aircraft or equip-ment.
d. Flush the sprayer and/or rinse the brush or roller withfresh water immediately after completing the applica-tion operation. If soil barrier materials dry on/in appli-cation equipment, remove it with A-A-59601, MIL-PRF-32295, Type II, or MIL-PRF-680, degreasingsolvent or soak the equipment in a solution of one part
MIL-PRF-87937, Type IV or MIL-PRF-85570, Type IIcleaning compound and four parts water for a mini-mum of 4 hours.
3.5.7.3 Removal.
a. Apply McGean-Roncho, Inc., PN Cee-Bee A-276LV(NSN 6850-01-529-2002) soil barrier remover or A-A-59601, or MIL-PRF-680, degreasing solvent to thesurface from which the soil barrier film is to be re-moved with a non-atomizing sprayer, mop, brush, orcloth.
NOTE
• Soil barrier removers may be used as receivedor diluted 1 to 1 with water, but undiluted worksbest.
• Soil barrier removers are to be used only forremoval of soil barrier films. They shall not beused for any other type of aircraft or equipmentcleaning
b. Allow the soil barrier remover or solvent to dwell onthe surface until it penetrates the soil barrier film (usu-ally about 20 to 60 minutes).
c. Scrub the area thoroughly with a brush or 3M Co., PN251 aircraft washing kit fitted with a non-abrasivecleaning pad or sponge, and then flush the area withfresh water.
d. Reapply soil barrier material per Paragraph 3.5.7.2.
3.5.8 Bird Strike Cleaning. Aircraft occasionally collidewith birds in the air during take-off or landing resulting inresidue that must be cleaned from the exterior and/or interiorof the aircraft after landing. In areas where avian influenza A(H5N1) outbreaks are ongoing among bird populations (SeeEmbargo of Birds from Specified Countries: http://www.cd-c.gov/flu/avian/outbreaks/embargo.htm), special precautionsand cleaning procedures must be followed. Collisions with
TO 1-1-691
Change 6 3-49
infected birds pose a risk of contaminating the exterior and/orinterior surface of the aircraft with infectious blood, feces,feathers, or other materials.
3.5.8.1 Bird Strike Cleanup.
• Any potential risk of human exposure to infec-tious material from bird strikes may be reducedby observing the following cleaning recommen-dations.
• Use non-sterile vinyl or nitrile gloves that coverpart of the arm.
• If the cleaning method may create splashing,safety goggles or glasses and an N-95 Dispos-able Respirator (Appendix B, Table B-2, ItemNo. 70), or equivalent, surgical mask may beworn to protect mucous membranes.
• Under the advisement of the Base Safety Officeand Bioenvironmental, flexibility in modifyingpersonal protective equipment requirementsmay be necessary as determined on the basis ofthe task and circumstances of the cleaning ac-tivity.
• Wear disposable coveralls to protect clothingand skin while cleaning.
• Avoid touching the mouth or face area withsoiled hands or gloves. Wash hands thoroughlywith soap and water after cleaning or beforeeating or smoking. Clean hands with an alco-hol-based hand gel (at least 60% alcohol) whennot visibly soiled or when soap and water arenot available.
The following procedures describe a normal bird strikecleanup.
a. Place bird carcasses and/or parts in a double plasticbag and contact the installation safety office in accor-dance with AFMAN 91-223 Aviation Safety Investiga-tions and Reports.
b. If the bird strike occurred in a suspected H5N1 area,use one of the four approved treatment methods andinclude necessary documentation when shipping re-mains to the Smithsonian Institution, Division of BirdsNHB, E610, MRC 116, 10th and Constitution Ave.,NW, Washington, DC 20560. The USDA approvedmethods include:
(1) Immerse in 70% alcohol and allow to dry.
(2) Heat to 130º F for at least 30 minutes.
(3) Immerse in phenol and allow to dry.
(4) Immerse in 10% formalin and allow to dry.
(5) Required documentation includes:
(a) Certificate of Origin.
(b) Certificate of Treatment.
(c) Copy of Smithsonian U.S. Dept. of Agricul-ture Animal and Plant Health Inspection Ser-vice (APHIS) permit. All documents can beaccessed at http://afsafety.af.mil/SEF/Bash/SEFW_new.shtml or contact the Bird/Wild-life Aircraft Strike Hazard (BASH) Team at(505) 846-1440/5673/5679. Reference AF-PAM 91-212 for more information on theBASH Team.
• Do not wash contaminated surfaces with highpressurized water or cleaner, which could aero-solize H5N1 viral particles that could be in-haled.
• Consult the installation’s Civil Engineering En-vironmental Flight and Bioenvironmental Engi-neering Flight for proper containment, decon-tamination and/or disposal of contaminatedwastewater.
c. Clean the exterior and interior surfaces of the aircraft,removing blood, feces, feathers, or other material thor-oughly using hand-cleaning method only as outlined inParagraph 3.5.2.5, step g of this TO. Apply a solutionof MIL-PRF-87937 or MIL-PRF-85570 mixed perParagraph 3.3 of this TO. Apply the cleaning solutionto the surface with an aircraft wash pad and agitate.
d. Rinse the area using low pressure water. In areas wherewater could damage components or create drainageproblems, rinse area with rag wetted with clean water.
e. Wipe the area with a clean, dry rag.
f. Repeat the above procedure, as necessary, for ex-tremely soiled/contaminated areas.
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3-50
Consult the Base Bioenvironmental Office forproper disposal and handling of contaminatedcleaning tools and materials.
NOTE
Consult the weapons system specific, (-23, orequivalent), manual for cleaning requirements inaddition to those in this manual.
g. Place all scrapers, brushes, rags and other cleaningtools in a designated receptacle for proper cleaningand/or disposal.
3.5.8.2 Internal/Enclosed (Water Sensitive) AreaCleanup. Use the following procedures in internal/enclosedareas where use of copious amounts of water could damagecomponents, create drainage problems, etc.
a. Follow Paragraph 3.5.8.1, step a through step g, exceptat step c, use one of the prepackaged ready-to-use(RTU) cleaners MIL-PRF-87937 (NSN 6850-01-461-0065) or A-A-59921, Class 1A (NSN 6850-00-005-5305).
Ethyl alcohol is flammable and moderately toxicto skin, eyes, and respiratory tract. Eye and skinprotection is required. Good general ventilation isrequired.
Consult system specific manuals to identify sys-tem de-energizing requirements prior to usingflammable materials in aircraft interior areas.
b. Wipe the area with clean cloth saturated in 70% ethylalcohol (O-E-760, NSN 6550-01-315-5333). The alco-hol must remain on the surface approximately 10 min-utes to ensure the H5N1 virus is killed. More than oneapplication may be required to achieve this dwell-time.
Consult the Base Bioenvironmental Office forproper disposal and handling of contaminatedcleaning tools and materials.
c. Place all scrapers, brushes, rags and other cleaningtools in a designated receptacle for proper cleaningand/or disposal.
3.5.9 Bodily Fluids Contamination Cleanup. Aircraftoccasionally are dispatched to transport enemy prisoners,wounded/medically ill personnel, or human remains. The in-terior of the aircraft can become contaminated with differenttypes of human bodily fluids during these operations. It isrecommended that prior to transporting, which could resultin bodily fluid contamination, some type of barrier materialbe applied to the cargo areas such as plastic, canvas, or bar-rier paper. This will help contain the contaminants and re-duce the cleanup efforts required upon arriving at the finaldestination. The aircraft should be considered contaminatedif bodily fluids come in contact with aircraft surfaces, equip-ment, or personnel. This paragraph will address the cleanupof bodily fluids in regards to corrosion damage potential toaircraft and equipment such as cargo, pallet, etc. For infor-mation regarding personnel protection, contact your localbioenvironmental office.
3.5.9.1 Bodily Fluid Containment During Flight.
• Use non-sterile vinyl or nitrile gloves that coverpart of the arm.
• Wear safety goggles or glasses and an N-95Disposable Respirator (Appendix B, Table B-2,Item No. 70), or equivalent, surgical mask toprotect the mucous membranes and inhalationof blood borne pathogens that may exist.
• Under the advisement of the Base Safety Officeand Bioenvironmental, flexibility in modifyingpersonal protective equipment requirementsmay be necessary as determined on the basis ofthe task and circumstances of the cleaning ac-tivity.
• Avoid touching the mouth or face area withsoiled hands or gloves. Wash hands thoroughlywith soap and water after cleaning or beforeeating or smoking. Clean hands with an alcoholbased hand gel (at least 60% alcohol), whennot visibly soiled or when soap and water arenot available.
The following procedures are general guidelines for the con-tainment of bodily fluids during flight.
a. If possible, cordon off the contaminated area to keepunauthorized personnel away from the area and track-ing the fluids throughout the aircraft.
b. Apply paper towels or other absorbent material to thefluid to absorb the fluids and minimize the spill area.
3.5.9.2 Bodily Fluid Cleanup. To reduce any potentialdamage to the aircraft/equipment during the cleanup, person-nel shall adhere to the following cleaning procedures.
TO 1-1-691
Change 5 3-51
• Use non-sterile vinyl or nitrile gloves that coverpart of the arm.
• Wear safety goggles or glasses and an N-95Disposable Respirator (Appendix B, Table B-2,Item No. 70), or equivalent, surgical mask toprotect the mucous membranes and inhalationof blood borne pathogens that may exist.
• Under the advisement of the Base Safety Officeand Bioenvironmental, flexibility in modifyingpersonal protective equipment requirementsmay be necessary as determined on the basis ofthe task and circumstances of the cleaning ac-tivity.
• Wear disposable coveralls (Appendix B, TableB-2, Item No. 94) to protect clothing and skinwhile cleaning.
• Avoid touching the mouth or face area withsoiled hands or gloves. Wash hands thoroughlywith soap and water after cleaning or beforeeating or smoking. Clean hands with an alcoholbased hand gel (at least 60% alcohol), whennot visibly soiled or when soap and water arenot available.
• Consult the Installation BioenvironmentalFlight for proper disposal of contaminatedwaste materials.
• In the event of contract fleet service or aircraftwash contract personnel performing this opera-tion, ensure all personnel are thoroughly briefedon cleanup and disinfectant procedures.
Chlorine bleach and other disinfectants are harm-ful to the aircraft structure. Personnel must strictlyadhere to the following procedures to limit poten-tially harmful effects.
NOTE
The use of non-approved Industrial/Janitorial typecleaners can be corrosive to equipment and shallnot be used.
a. Clean the cargo floor or other contaminated areas ofthe aircraft by absorbing all liquid spills with papertowels, or equivalent, absorbent material.
b. Clean the contaminated spill area thoroughly using asolution of MIL-PRF-87937 or MIL-PRF-85570 in ac-cordance with Table 3-2.
3.5.9.3 Disinfection of Contaminated Areas.
• Use non-sterile vinyl or nitrile gloves that coverpart of the arm.
• Wear safety goggles or glasses and an N-95Disposable Respirator (Appendix B, Table B-2,Item No. 70), or equivalent, surgical mask toprotect the mucous membranes and inhalationof blood borne pathogens that may exist.
• Under the advisement of the Base Safety Officeand Bioenvironmental, flexibility in modifyingpersonal protective equipment requirementsmay be necessary as determined on the basis ofthe task and circumstances of the cleaning ac-tivity.
• Protective footwear covers (Appendix B, TableB-2, Item No. 103) should be worn if walkingin the contaminated area is unavoidable.
• Avoid touching the mouth or face area withsoiled hands or gloves. Wash hands thoroughlywith soap and water after cleaning or beforeeating or smoking. Clean hands with an alcoholbased hand gel (at least 60% alcohol), whennot visibly soiled or when soap and water arenot available.
• Consult the Installation BioenvironmentalFlight for proper disposal of contaminatedwaste materials.
• Aircraft power must be turned off prior to startof disinfection process. Isopropyl alcohol ishighly flammable.
• Open aircraft doors/hatches to ventilate the air-craft interior for a minimum of 10 minutes dur-ing and prior to reapplying power to the air-craft.
• Use a non-synthetic wiping cloth with TT-I-735isopropyl alcohol.
• Do not use isopropyl alcohol on transparentacrylic or polycarbonate plastics used for air-craft canopies and windows or methacrylate(plexiglas).
Following cleanup of contaminated area, the areas must bedisinfected. Undiluted isopropyl rubbing alcohol or a dilutedsolution of isopropyl alcohol, TT-I-735, mixed in a 70%concentration should be used.
TO 1-1-691
3-52
NOTE
Iso-Tech Kits(tm) (NSN 6515-01-524-9755) areavailable through medical supply channels. Thesekits contain all the items needed to complete thedisinfection process.
a. Use a paper towel, rag, or equivalent, dampened withundiluted isopropyl rubbing alcohol (NSN 6505-00-655-8366) to wipe the affected area. If using isopropylalcohol, TT-I-735, use a diluted 70% solution mixture.To obtain a 70% solution of isopropyl alcohol, TT-I-735, fill a one pint container to 70% by volume of100% isopropyl alcohol, TT-I-735, and 30% by vol-ume distilled water (if distilled water is unavailable,tap water can be used). Do not pour the disinfectantsolution onto the aircraft surface.
b. Reapply, as necessary, to allow the solution to dwellon the surface for 10 minutes.
c. Rinse the area with clean paper towels, or equivalent,material dampened with clean water.
d. Dry the area with clean paper towels, or equivalent,material.
Use caution when removing PPE after disinfectantoperations as to avoid personal contamination.
e. Remove PPE.
f. Place contaminated materials, such as paper towels andPPE in biohazard bag, or equivalent. Securely closewith twist tie.
g. Dispose of contaminated materials as directed by thelocal bioenvironmental office.
SECTION III LUBRICATION
3.6 INTRODUCTION.
Lubrication performs a dual purpose, to prevent wear be-tween moving parts and also to fill air spaces, displace wa-ter, and provide a barrier against corrosive elements. Thelubrication requirements contained in system specific main-tenance manuals and/or cards are usually adequate to pre-vent corrosion of most lubricated surfaces under normal op-erating conditions. Aircraft lubrication shall be accomplishedonly by personnel qualified in lubrication procedures. In theevent that the specified lubricant is not available, requestsubstitutions from the aircraft SPD and/or the missile orequipment SPM.
NOTE
Comply with relubrication time frame require-ments outlined in the system specific maintenancemanual.
3.6.1 Conventional Lubricants. Table 3-5 contains thetitle, specification, intended use, and temperature range ofthe most frequently used conventional lubricating materials.
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3-53
3.6.2 Solid Film Lubricants.
• Not all lubricating materials are compatiblewith each other and/or metals used in Air Forceaircraft, missiles, or equipment. Some areknown to promote galvanic corrosion or causepaint or acrylic plastics to deteriorate. Usingthe correct lubricating material is critical. Donot use greases or oils with solid film lubri-cants. Use only lubricants specified by appro-priate system specific manuals and/or cards.
• Do not lubricate Teflon bearings or bushings.Clean teflon bearings and bushings with A-A-59601, MIL-PRF-32295, Type II, or MIL-PRF-680, degreasing solvent.
• Lubricants containing graphite, either alone orin mixture with any other lubricants, shall notbe used since graphite is cathodic to most met-als and will cause galvanic corrosion in thepresence of electrolytes.
• Do not use solid film lubricants in areas subjectto rotational speeds above 100 RPM underheavy loads or on roller bearing elements be-cause they will not provide adequate lubrica-tion in these situations.
• Do not use solid film lubricants in conjunctionwith oils or greases as they are not compatible.
Solid film lubricants are used where conventional lubricantsare difficult to apply or retain, or where other lubricants maybe contaminated with dust, wear products, or moisture andto reduce fretting corrosion on close tolerance fittings thatsee primarily static loads with only very small relative move-ment caused by vibration. Typical applications of solid filmlubricants are sliding motion components such as flap tracks,hinges, turnbuckles and cargo latches.
3.6.2.1 Surface Preparation for Solid Film Lubricants.As with paints, surface preparation prior to application isextremely important to the service wear life of solid filmlubricants. In reality, solid film lubricants are nothing morethan paints with solid (powder) type lubricants used as thepigment. They are usually applied over surfaces pre-coatedwith other films, such as anodize (aluminum and magnesiumbase material), phosphate (steel base material), and some-times over organic coatings such as epoxy primers.
3.6.2.2 SAE AS5272 (MIL-PRF-46010). SAE AS5272(MIL-PRF-46010), lubricant, solid film, heat cured, corro-sion inhibiting is a heat cured, corrosion inhibiting, solidfilm lubricant that provides extended wear life. It can beused on aluminum, copper, steel, stainless steel, and titanium
in areas of infrequent operation and in areas requiring longterm protection under static conditions to prevent galling,corrosion, and metal seizure. Because SAE AS5272 (MIL-PRF-46010), Type I must be cured at 400° F (205° C) for 1hour and Type II must be cured at 300° F (149° C) for 2hours, they are not suitable for all applications as metallur-gical damage may occur at these temperatures.
3.6.2.3 MIL-PRF-46147 and/or MIL-L-23398. MIL-PRF-46147 and/or MIL-L-23398, lubricant, solid film, aircured, corrosion inhibiting are air cured, corrosion inhibit-ing, solid film lubricants that can be used on aluminum, steeland titanium in areas of infrequent operation and areas re-quiring long term protection under static conditions to pre-vent galling, corrosion, and metal seizure. They providemoderate wear life and corrosion protection in these areaswhen it is not feasible to use a solid film lubricant that re-quires curing at elevated temperatures, and can be used torepair damaged SAE AS5272 (MIL-PRF-46010) heat cured,solid film lubricants. MIL-L-23398, Type I (bulk) and TypeII (aerosol) both require a 6 hour cure at a temperature of77° ±3° F (25° ±2° C). MIL-PRF-46147, Form 1 (bulk) andForm 2 (aerosol); Type I (standard solvents) require a 18hour cure and Type II (low VOC content), both forms, re-quire a 24 hour cure at these same temperatures. Curing ofboth MIL-L-23398 and MIL-PRF-46147 solid film lubricantsmay be accelerated by allowing air drying at room tempera-ture for 30 minutes to flash off solvents and then heating to125° ±5° F (52° ±3° C) for 1 to 1 ½ hours.
3.6.3 Application of Conventional Lubricants.
When lubricating hinges and pinned joints, applya generous quantity of either MIL-PRF-63460(preferably), MIL-PRF-81309, Type II, or MIL-PRF-32033 water displacing, Corrosion preventivecompound (CPC) before applying the specified lu-bricant. Actuate hinges several times to make surethat the CPC’s and lubricants penetrate all crev-ices thoroughly, and then wipe off excess from ex-terior surfaces.
Apply lubricants as sparingly as possible to prevent accumu-lation of dust, dirt, and other foreign matter, but always ap-ply enough to provide adequate lubrication. Wipe away anyexcess lubricant. Using the proper method of application asspecified in the appropriate system specific maintenancemanual is important. Apply lubricants by one of the follow-ing methods:
• Grease guns, lever or pressure type.
• Oil, squirt, and aerosol spray cans.
• Hand or brush.
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3-54 Change 5
3.6.3.1 Grease Gun Application. When applying greasetype lubricants in pressure type grease fittings (Zerk fittings)with a grease gun, clean grease fitting with A-A-59601,MIL-PRF-32295, Type II, or MIL-PRF-680, degreasing sol-vent and clean cloth before applying lubricant. Make surethe lubricant has emerged around the bushing. If no greaseappears, check the fitting and grease gun for proper opera-tion. Be certain the grease gun is properly attached to the
fitting prior to applying pressure. When applying grease to aflush type (high pressure) fitting, make sure that the greasegun is fitted with a flush type adapter and held perpendicularto the surface of the fitting before applying pressure. If thefitting does not accept lubrication, replace the fitting and lu-bricate. Wipe excess grease from the fitting and the surround-ing surfaces with a clean, dry cloth.
Table 3-5. Common Military Greases and Their Uses
Specification and Nomenclature Intended Use Recommend Temperature RangeAMS-G-4343 Grease, Pneu-
matic System (NATO CodeG-392)
Lubrication between rubber and metal parts ofpneumatic systems; pressurized cabin bulk-head grommets and other mechanisms requir-ing rubber to metal lubrication.
-65° to 200° F (-54° to 93° C)
AMS-G-6032 Grease, Plug,Valve, Gasoline and Oil Re-sistant (NATO Code G-363)
Tapered plug valves; gasket lubricant or seal;general plug valve and fitting use where gaso-line, oil, alcohol, or water resistance is re-quired.
-32° to 200° F (0° to 93° C)
MIL-G-21164 Grease, Molyb-denum Disulfide, for Lowand High Temperatures(NATO Code G-353)
Heavily loaded steel sliding surfaces, accessorysplines, or anti-friction bearings carrying highloads and operating through wide temperatureranges where molybdenum disulfide will pre-vent or delay seizure in the event of inad-equate lubrication. This grease is not intendedfor use in wheel bearings.
-100° to 250° F (-73° to 121° C)
MIL-PRF-23827 Grease, Air-craft and Instrument, Gearand Actuator Screw (NATOCode G-354)
Lubrication of ball, roller, and needle bearings,gears, and sliding and rolling surfaces ofequipment such as instruments, cameras, elec-tronic gear and aircraft control systems thatare subject to extreme marine and low tem-perature conditions; rolling and sliding sur-faces of equipment with low motivating power(low torque equipment); general use on air-craft gears, actuator screws, and other equip-ment with high load carrying capacity. Its ex-tremely low volatility makes it useful onaircraft optical equipment since it will not pro-duce oil fogging.
-100° to 250° F (-73° to 121° C)
MIL-G-25013 Grease, Aircraft,Ball and Roller Bearing(NATO Code G-372)
Lubrication of ball and roller anti-friction bear-ings that operate at extreme high or low tem-peratures, especially in applications wheresoap-type petroleum or synthetic oil greasesand oils cannot be used. Can be used on air-craft actuators, gearboxes, and similar equip-ment.
-100° to 450° F (-73° to 232° C)
MIL-G-25537 Grease, Aircraft,Helicopter, Oscillating Bear-ing (NATO Code G-366)
Lubrication of aircraft bearings having oscillat-ing motion of small amplitude.
-65° to 160° F (-54° to 71° C)
MIL-PRF-27617 Grease, Air-craft and Instrument, Fueland Oxidizer Resistant
Lubrication of taper plug valves, gaskets, andbearings in aircraft and ground support equip-ment fuel systems; lubrication of valves,threads, and bearings of liquid oxygen (LOX)systems of aircraft, aerospace vehicles, andsupport equipment. Do not use on aluminumor magnesium dynamic bearings due to pos-sible ignition hazard.
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Table 3-5. Common Military Greases and Their Uses - Continued
Specification and Nomenclature Intended Use Recommend Temperature RangeType I (NATO Code G-397) -65° to +300° F (-54° to +149°
C)Type II (NATO Code G-398) -40° to +400° F (-40° to +204°
C)Type III (NATO Code G-399) -30° to +400° F (-34° to +204°
C)Type IV (NATO Code G-1350) -100° to +400° F (-73° to +204°
C)Type V -100° to +450° F (-73° to +232°
C)MIL-PRF-81322 Grease, Air-
craft, General Purpose, WideTemperature Range (NATOCode G-395)
NLGI, Grade 1: arresting gear sheave spacersand other equipment that operates under highcontact loads and high sliding speeds.
-65° to +350° F (-54° to +177°C)
NLGI, Grade 2: aircraft wheel bearings and in-ternal brake wheel assemblies, anti-frictionbearings, gearboxes, and plain bearings. Bothwill withstand high speed operations and op-erations on equipment subject to extreme ma-rine environments.
SECTION IV PRESERVATION
3.7 INTRODUCTION.
Corrosion preventive compounds (CPC’s), or preservatives,are used to protect metal aircraft, missile, and equipmentparts and components by preventing corrosive materials fromcontacting and corroding bare metal surfaces. Many of thesecompounds are also able to displace water, including seawater, and other contaminants from these surfaces, and someprovide lubrication, as well as corrosion protection. Gener-ally, CPC’s are mixtures of special additives in petroleumderivative bases (special oils or greases). CPC’s range inappearance and consistency from the thick, black types, suchas MIL-PRF-16173, Grade 1, to light oils, such as MIL-PRF-32033. The thicker CPC’s provide the best corrosionprotection, are longer lasting, and are more difficult to re-move. The thinner materials provide some lubrication and donot crack, chip, or peel but they must be removed and re-placed regularly to provide continuing protection.
3.7.1 Operational Preservation. The day to day applica-tion of CPC’s to prevent corrosion on operational aircraft isknown as operational preservation. Areas which are corro-sion prone or where paint has been damaged should be rou-tinely protected by CPC’s until more permanent treatment,such as paint touch-up or sealant, can be applied.
3.7.2 Non-Operational Preservation. Preservation of air-craft or components during periods of prolonged inactivity,storage, or shipment is known as non-operational preserva-tion.
3.7.3 Types of CPC’s. CPC’s can be separated into twomajor categories, water displacing and non-water displacingcompounds.
3.7.3.1 Water Displacing Compounds. Water displacingCPC’s can be used to remove water, including sea water, orother electrolytes from metal surfaces. MIL-PRF-81309,MIL-PRF-63460, MIL-PRF-16173, Grade 3, and MIL-PRF-32033 are water displacing CPC’s that are able to penetrateinto cracks, crevices, voids at faying surface edges, aroundfastener heads, and into hinges. They usually provide verythin coatings, one mil (0.001 inch) or less in thickness, thatare clear or translucent and remain soft and oily after appli-cation, so they cannot provide long term protection outdoorsor in areas which are frequently handled. Another type,MIL-DTL-85054, differs from the other water displacingcompounds as it doesn’t penetrate into joints very well, butforms a relatively hard, dry film on exterior surfaces, andtherefore, it can be used for protection outdoors and in areasof frequent handling.
3.7.3.2 Non-Water Displacing Compounds. Non-waterdisplacing CPC’s may be used on dried surfaces or on sur-faces which have been first treated with a water displacingCPC. MIL-PRF-16173, Grades 1, 2, and 4 are non-waterdisplacing CPC’s. They are heavier bodied, waxy typegreases which provide long term corrosion protection byforming a barrier film on metal surfaces. These CPC’s pro-vide thicker coatings and are light brown to very dark brown
TO 1-1-691
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in color, with a waxy greasy appearance. They provide goodcorrosion protection in areas where large amounts of watercollect on or run off of structures.
3.7.4 Time Limitations of CPC’s. Because of their tem-porary nature, CPC’s must be regularly removed and re-placed to provide continuing corrosion protection. Table 3-6provides the recommended time intervals for indoor and out-door CPC use.
3.7.5 Description of CPC’s. A list of CPC’s and theirintended uses is summarized in Table 3-7.
Table 3-6. Time Limitations for CPC’s
CPC Outdoor1 Indoor2 Indoor Covered3
Soft, Thin FilmsMIL-PRF-81309, Type II 14 Days 30 Days 180 DaysMIL-PRF-81309, Type III 5 Days 14 Days 90 DaysMIL-L-87177, Grade B 5 Days 14 Days 90 DaysMIL-PRF-16173, Grade 3 14 Days 30 Days 180 Days
Lubrication and ProtectionMIL-PRF-32033 5 Days 30 Days 180 DaysMIL-PRF-63460 5 Days 30 Days 180 Days
Hard, Thick FilmsMIL-DTL-85054 90 Days 210 Days 365 DaysMIL-PRF-16173, Grade 4 90 Days 210 Days 365 DaysMIL-PRF-16173, Grade 2 90 Days 210 Days 365 DaysMIL-PRF-16173, Grade 1 210 Days 365 Days 365 Days
1 Outdoor: Without cover; exposed to elements in a mild climate; absence of Outdoor: Without cover; exposed to ele-ments in a mild climate; absence of Outdoor: Without cover; exposed to elements in a mild climate; absence of rainand other washing forces; free from air and water borne pollutants.
2 Indoor: Hangars, shop areas, storage or parts accumulation areas, warehouses.3 Indoor covered: Items are wrapped or sealed in a water-resistant material and stored indoors in a hangar, warehouse, or
shop area. Soft, thin film CPC’s were designed for indoor use and ease of removal.
Table 3-7. Corrosion Preventive Compounds
Specification and Nomenclature Intended Use Type of CoatingWATER-DISPLACING CPC’s
MIL-PRF-32033 Lubricating Oil, Gen-eral Purpose, Preservative, (WaterDisplacing, Low Temperature); Mili-tary Symbol PL-S; NATO CodeO-190
Lubrication and corrosion protection ofhinges, other moving parts, small arms andautomatic weapons, and wherever a lowtemperature, water displacing lubricant isrequired; requires frequent reapplications.
Soft, oily coating and lubricant.
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Table 3-7. Corrosion Preventive Compounds - Continued
Specification and Nomenclature Intended Use Type of CoatingMIL-PRF-63460 Lubricant, Cleaner,
and Preservative for Weapons andWeapons Systems; Military SymbolCLP; NATO Code S-758
Lubrication and short term preservation ofhinges, and small and large caliber weap-ons in all climatic conditions within a tem-perature range of -65° to +150° F (-54° to+66° C); facilitates the effective removalof firing residues, gums, and other con-taminants from weapons components whileproviding adequate lubrication and shortterm preservation. Of all water displacingCPC’s, this material is the best lubricant.Excellent water displacing characteristicsand penetration into tight joints.
Thin corrosion preventive lubricantfilm.
MIL-PRF-16173 Corrosion PreventiveCompound, Solvent Cutback, ColdApplication, Grade 3
Displacement of water; short term corrosionprotection of metal surfaces during ship-ment, storage, and in-service use; can beused on moving parts where minor lubrica-tion is required, such as on hinges, bombracks, and sliding parts.
Soft, oily, thin film (1.0 mil), lightamber color.
MIL-PRF-81309 Corrosion PreventiveCompounds, Water Displacing, Ultra-thin Film, Type II
Displacement of water; short term corrosionprotection of metal surfaces during ship-ment, storage, and in-service use; corrosionprotection of moving parts where very mi-nor lubrication is required, such as hingeareas, bomb racks, and sliding parts. Can-not be used on interior of electrical orelectronic equipment and connectors.
Soft, oily, very thin film (0.5 mil)translucent, light amber color.
Type III Displacement of water; corrosion protectionof electrical, avionics, and other electronicequipment, electrical connector plugs andcontact pins.
Soft, oily, ultra thin film (0.2 mil),translucent, light amber color.
MIL-L-87177 Lubricants, CorrosionPreventive, Water Displacing, Syn-thetic, Grade B
Displacement of water, corrosion protection,and some lubrication on in-service lightlyloaded moving parts.
Soft, oily, thin film (0.5 mil), trans-lucent, light amber color.
MIL-DTL-85054 Corrosion PreventiveCompound, Water Displacing, Clear
Corrosion protection and water displacementfor non-moving parts, such as skin seams,installed fastener heads where paint hascracked, access panel edges, and areaswith damaged paint. Cannot be used oninterior areas of electrical or electronicsequipment and connectors or in joint areasof moving parts as it dries to a hard film.
Dry, thin film (1.0 mil), transparent,colorless to slight blue tint.
NON-WATER DISPLACING CPC’sMIL-PRF-16173 Corrosion Preventive
Compound, Solvent Cutback, ColdApplication, Grade 1
Protection of metal surfaces against corrosionwhen exposed with or without coveringindoors or outdoors. Cannot be used iftemperatures will fall below 0° F (-18° C)as the film will crack and can peel fromthe surface leaving it unprotected.
Hard, tack-free, thick film (4.0mils), dark brown or black color.
Grade 2 Protection of metal surfaces against corrosionduring rework or storage; film remainstacky.
Soft, non-drying, thick (2.0 mils),light brown color.
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3-58 Change 10
Table 3-7. Corrosion Preventive Compounds - Continued
Specification and Nomenclature Intended Use Type of CoatingGrade 4 Protection of metal surfaces against corrosion
during indoor storage when a transparentcoating is required; coating of aircraft andequipment interior, metal wire controlcables.
Soft, tack-free, thick (2.0 mils),light brown color.
3.7.5.1 MIL-PRF-81309, Corrosion Preventive Com-pound, Water Displacing, Ultra Thin Film and MIL-L-87177, Lubricants, Corrosion Preventive, Water Dis-placing, Synthetic.
MIL-DTL-85054, MIL-PRF-63460, and MIL-PRF-81309 have been revised to eliminate ODC’s.Some reformulated products now contain flam-mable solvents and/or propellants. Pay close atten-tion to all CAUTION/WARNING labels on theproduct containers.
MIL-PRF-81309 and MIL-L-87177 materials are generalpurpose corrosion preventive compounds for use when a thin,water displacing CPC is needed. MIL-PRF-81309 and MIL-L-87177 are for indoor protection and short term protectionwhere surfaces can be re-coated when required. These mate-rials are excellent water displacing compounds which pro-vide an ultra thin, soft film (0.5 mil or less). The MIL-PRF-81309 specification covers two types of materials and theMIL-L-87177 specification covers one grade of material thatare useful for Air Force purposes to provide temporary pro-tection from corrosion while still being easily removable witha solvent. They should not be used around LOX fittings. Allof these CPC’s may be applied by either dipping, brushing,or spraying with a pump or aerosol sprayer.
3.7.5.1.1 MIL-PRF-81309, Type II and MIL-L-87177,Grade B. These CPC’s form a soft, thin film for general useon moving or sliding parts where some lubrication is needed,such as on hinges or bomb rack components. These materi-als can be easily washed away by rain or wash procedures,so frequent reapplication may be required. They are useful inthe protection of areas which cannot be properly drained orcontain recesses that are particularly difficult to reach due totheir excellent water displacing abilities.
3.7.5.1.2 MIL-PRF-81309, Type III and MIL-L-87177,Grade B. These CPC’s form an ultra thin, soft film thatprovides excellent water displacement and corrosion protec-tion.
3.7.5.2 MIL-DTL-85054, Corrosion Preventive Com-pound, Clear. MIL-DTL-85054 is a water displacing CPCwhich forms a clear, hard/dry, semi-flexible film. It is in-tended for use as a protective coating on bare metal areaswhere the paint system has been damaged or failed untiltouch-up and/or repainting is practical. Because of its paint-like characteristics, it provides no lubrication and blockselectrical conductivity.
3.7.5.2.1 Application of MIL-DTL-85054.
Ensure that all areas where MIL-DTL-85054 isapplied are fully dried before sealing an area. Al-though MIL-DTL-85054 is a corrosion preventivecompound, its solvent vapors may cause corrosionif not allowed to dissipate.
MIL-DTL-85054 can be applied by either dipping, brushing,or spraying with a paint spray gun or an aerosol can, but it isprimarily applied by spraying from aerosol cans. Invert theaerosol can after each use and spray to clear the spray tip(nozzle) of entrapped material. If an aerosol can does notspray, invert and depress the spray tip several times to clearthe delivery tube and spray tip (nozzle). If the can still doesnot spray, remove and clean the plastic spray tip (nozzle),and then reinstall the spray tip (nozzle), and spray again toclear the delivery tube. Dip application provides only a verythin coating and therefore much less corrosion protection.
3.7.5.2.2 Removal of MIL-DTL-85054. Remove MIL-DTL-85054 if it is damaged due to abrasion, there are cracksin the coating, or if there is evidence of corrosion under thecoating. Since excessive MIL-DTL-85054 buildup is diffi-cult to remove, especially after prolonged exposure to directsunlight, remove previously applied coatings before reappli-cation. If the solvents recommended in Table 3-8 do not re-
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Change 10 3-59
move old films of MIL-DTL-85054, spraying on fresh MIL-DTL-85054 to soften the film and wiping or rubbing whilewet is often effective.
3.7.5.3 MIL-PRF-16173, Corrosion Preventive Com-pound, Solvent Cutback, Cold Application. MIL-PRF-16173 covers five different grades of CPC’s which can beapplied by brushing or dipping. Grades 1, 2, and 4 do notdisplace water and must be applied to dried surfaces or tosurfaces which have been treated with MIL-PRF-81309,Type II or III, MIL-L-87177, Grade B, or MIL-PRF-16173,Grade 3.
3.7.5.3.1 Grade 1. A thick, hard, black CPC which canbe removed with difficulty using mineral spirits or degreas-ing solvents. It offers the most corrosion protection of all theCPC’s indoors and outdoors, and may be used at tempera-tures down to 0° F (-18° C). If used at temperatures below0° F (-18° C), the CPC film can crack and fall off leaving thesurface unprotected.
Table 3-8. Preservation of Specific Areas and Components
Area or Component CPC Application Instructions Removal Instructions
NOTE
Prior to the application of preservatives (CPC’s), ensure removal of old preservative CPC coatings.
EXTERIOR SURFACES NOTREQUIRING LUBRICA-TION
Unpainted areas and areas withdamaged paint which do notrequire lubrication (fastenerheads; faying surface, accesspanel, door, and frame edges;attachment points; non-mov-ing attachment hardware;wheel well areas; ram airducts; and flap/slat cavities)
MIL-DTL-85054 Wipe off dirt and excessmoisture. Apply thincoating of MIL-DTL-85054. Allow to dry ½hour. Apply a secondcoat.
Use a non-synthetic wipingcloth wet with A-A-59601, MIL-PRF-32295,Type II, or MIL-PRF-680, degreasing solvent.For stubborn MIL-DTL-85054, refer to Para-graph 3.7.5.2.2.
MIL-PRF-81309, Type II,MIL-L-87177, Grade B,and MIL-PRF-16173,Grade 4
Wipe off dirt and excessmoisture. Apply a coat-ing of MIL-PRF-81309,Type II or MIL-L-87177,Grade B followed by acoating of MIL-PRF-16173, Grade 4.
EXTERIOR SURFACES NOTREQUIRING HIGH PER-FORMANCE LUBRICANTOR HYDRAULIC FLUID
Sliding or moving parts requir-ing only minor lubrication(bomb rack components,hinges, door locks)
MIL-PRF-63460 Apply a continuous wetcoat of MIL-PRF-63460.
Use a non-synthetic wipingcloth wet with A-A-59601, MIL-PRF-32295,Type II, or MIL-PRF-680, degreasing solvent.
MIL-PRF-81309, Type II,MIL-L-87177, Grade B,and MIL-PRF-32033
Apply a coating of MIL-PRF-81309, Type II orMIL-L-87177, Grade Bfollowed by a coating ofMIL-PRF-32033. Ifhandled, reapply as nec-essary.
THREADED SURFACES
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3-60 Change 5
Table 3-8. Preservation of Specific Areas and Components - Continued
Area or Component CPC Application Instructions Removal InstructionsScrews, various fasteners MIL-PRF-63460, MIL-PRF-
81309, Type II, MIL-L-87177, Grade B, or MIL-PRF-16173, Grade 4
Dip screws or fasteners inCPC and install. Whendisassembly is frequent,use MIL-PRF-63460,preferably, or use MIL-PRF-81309, Type II orMIL-L-87177, Grade Bas alternates. When dis-assembly is infrequent,use MIL-PRF-16173,Grade 4 for long termprotection.
Immerse screws or fasten-ers in A-A-59601, MIL-PRF-32295, Type II, orMIL-PRF-680, degreas-ing solvent and blot orblow dry.
HYDRAULIC PISTON SUR-FACES
System hydraulic fluid Wipe exposed surface witha cloth dampened withthe hydraulic fluid usedin the system. Alwayswipe away from seals.Take care not to scratchsurfaces.
Do not remove. Reapply asnecessary.
ELECTRICAL CONNECTORSHELLS (EXTERIOR SUR-FACES)
NOTE
For additional information, refer to TO 1-1-689-3.
Connector shells located in con-trol surface wells, wheelwells, bilge areas, and otherinterior areas of aircraft andmissiles, and all areas ofother equipment
MIL-DTL-85054 Wipe off dirt and excessmoisture. Apply thincoating of MIL-DTL-85054. Do not allowCPC to contact internalsurfaces. Allow to dry ½hour and then apply asecond coat.
Use a non-synthetic wipingcloth wet with A-A-59601, MIL-PRF-32295,Type II, or MIL-PRF-680, degreasing solvent.
For stubborn MIL-DTL-85054, refer to Para-graph 3.7.5.2.2.
MIL-C-81309, Type II or III,MIL-L-87177, Grade B,and MIL-PRF-16173,Grade 4
Wipe off dirt and excessmoisture. Apply coatingof MIL-PRF-81309, TypeII or III or MIL-L-87177,Grade B followed by acoating of MIL-PRF-16173, Grade 4.
ELECTRICAL CONNECTORSHELLS (INTERIOR SUR-FACES)
NOTE
For additional information, refer to TO 1-1-689-3.
Do not use any other type of CPC than those listedhere on the interior of electrical connector shells asall other types will interfere with electricalconductivity.
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Change 5 3-61
Table 3-8. Preservation of Specific Areas and Components - Continued
Area or Component CPC Application Instructions Removal InstructionsConnector shells located in all
the same areas noted for exte-rior surfaces of connectors
MIL-PRF-81309, Type III orMIL-L-87177, Grade B
Wipe off dirt and excessmoisture. Apply a thin,uniform coating of CPC.
Use a non-synthetic wipingcloth wet with TT-I-735isopropyl alcohol.
ELECTRICAL CONNECTORPINS (ALL)
Do not use any othertype of CPC than thoselisted here on electricalconnector pins andsockets as they willinterfere with electricalconductivity.
Connector pins and sockets MIL-PRF-81309, Type III orMIL-L-87177, Grade B
Apply a continuous thin,wet coat of CPC. Ifhandled or exposed towater, reapply.
Use an acid brush withnon-synthetic bristles toapply TT-I-735 isopropylalcohol to pins and sock-ets. Lightly dab all pinsand sockets, and thenblot dry.
ELECTRICAL AND ELEC-TRONIC EQUIPMENT
Refer to TO 1-1-689-3.
CONTROL CABLES (ALL)(INTERIOR AND EXTE-RIOR)
MIL-PRF-81309, Type II orMIL-L-87177, Grade B
Apply a continuous film ofMIL-PRF-81309, TypeII, MIL-L-87177, GradeB, or MIL-PRF-16173,Grade 3 water displacingCPC by aerosol can orby wiping with cloth wetwith the CPC.
Use a non-synthetic wipingcloth wet with A-A-59601, MIL-PRF-32295,Type II, or MIL-PRF-680, degreasing solvent.
MIL-PRF-16173, Grade 3and MIL-PRF-16173,Grade 4
Follow with a coating ofMIL-PRF-16173, Grade4 applied with a non-synthetic cloth or a non-metallic bristle brush.
HELICOPTER CARGO HOISTDRUM
MIL-PRF-81309, Type II orMIL-L-87177, Grade B,MIL-PRF-16173, Grade 3
Apply a continuous film ofMIL-PRF-81309, TypeII, MIL-L-87177, GradeB, or MIL-PRF-16173,Grade 3 water displacingCPC to the drum sur-faces by aerosol can orby wiping with a non-synthetic cloth wet withthe CPC. Wipe with aclean cloth to removeexcess.
Use a non-synthetic wipingcloth wet with A-A-59601, MIL-PRF-32295,Type II, or MIL-PRF-680, degreasing solvent.
MIL-DTL-85054 Spray a continuous film ofMIL-DTL-85054 on thedrum surfaces by aerosolcan. Allow to dry ½ hourand then apply a secondcoat.
For stubborn MIL-DTL-85054, refer to Para-graph 3.7.5.2.2.
ARMAMENTS Refer to the system specific equipment maintenance and/or instruction manual.
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3-62 Change 5
Table 3-8. Preservation of Specific Areas and Components - Continued
Area or Component CPC Application Instructions Removal InstructionsEJECTION SEATS Refer to the system specific ejection seat maintenance manuals and SPM instructions.
3.7.5.3.2 Grade 2. A thick, soft, grease-like, brown CPCthat remains tacky and can be removed with mineral spiritsor degreasing solvents. It protects under relatively severeconditions and given adequate maintenance touch-up as nec-essary, can be used for most maximum protection require-ments. It may be used at temperatures down to -40° F (-40°C). It is not a good choice for parts that are handled fre-quently since it remains tacky.
3.7.5.3.3 Grade 3. A thin, soft, oily film, water displac-ing CPC. This CPC doesn’t penetrate into tight joints as wellas MIL-PRF-81309, Type II or MIL-L-87177, Grade B, soone of them should be used as a substitute for this type ofapplication.
NOTE
Remove the MIL-PRF-16173, Grade 3 film withA-A-59601, MIL-PRF-32295, Type II, or MIL-PRF-680, degreasing solvent prior to inspectingan area when the coating is dark and prevents vi-sual inspection of the underlying surface for cracksand hydraulic leaks.
3.7.5.3.4 Grade 4. A thick, soft, waxy type CPC that driesto a tack-free, semi-transparent film through which identifi-cation can be read. It provides good protection under rela-tively severe conditions when touched-up as necessary. It isexcellent for use on in-service equipment over MIL-PRF-81309, Type II, MIL-L-87177, Grade B, or MIL-PRF-16173,Grade 3 water displacing CPC since it dries to a tack-freefilm. It can be used at temperatures down to -40° F (-40° C).
3.7.5.4 MIL-PRF-63460, Lubricant, Cleaner, and Pre-servative for Weapons and Weapon Systems.
• If MIL-PRF-63460 is used in an area whichwill later be sealed or totally enclosed with no
ventilation, allow at least 4 hours for the sol-vent to evaporate prior to sealing or closing offthe area. Although MIL-PRF-63460 is a corro-sion preventive compound, its solvent vaporsmay cause corrosion if not allowed to dissipate.
• Do not use MIL-PRF-63460 on rubber or otherelastomeric parts. MIL-PRF-63460 containssolvents which attack rubber O-rings and otherelastomeric parts. Do not use as a direct substi-tute for MIL-PRF-32033.
MIL-PRF-63460 is a thin, water displacing, protective, pen-etrating lubricant used for cleaning, lubrication, and preser-vation of aircraft, missile, and equipment hinges and fittingjoints that experience only minor and infrequent relative mo-tion, and on parts and areas of small or large caliber weap-ons. This material has good lubricating properties between-65° and +150° F (-54° and +65° C), and it is the best lubri-cant of all water displacing CPC’s. It may be applied bybrushing, dipping, or spraying by aerosol can or a pumpsprayer.
3.7.5.5 MIL-PRF-32033, Lubricating Oil, General Pur-pose, Preservative, Water Displacing.
MIL-PRF-32033 material suffers a loss of viscos-ity or starts to gel at very low temperatures, there-fore, it shall not be used when temperatures candrop below -40° F (-40° C).
MIL-PRF-32033 is a general purpose, water displacing, lu-bricating oil with preservative properties intended for thelubrication and preservation of aircraft, missile, and equip-ment components. It may be applied by brushing, dipping, orspraying by aerosol can or a pump sprayer.
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3.7.6 Preservation of Specific Areas.
• Do not use corrosion preventive compounds onthe interior of fuel tanks or fuel cells, engines,or engine fuel systems as fouling of fuel sys-tems may occur.
• Do not use corrosion preventive compounds onengine parts or accessories which exceed 800°F (427° C). Corrosive reactions may occur withCPC’s at high temperatures.
• CPC’s are not compatible with LOX and shouldnot be used on oxygen equipment, lines, fit-tings, or storage bottles. Fire may result.
NOTE
Use only corrosion preventive compounds (CPC’s)authorized by and described in this manual and/ora system specific equipment manual.
Table 3-8 provides procedures for the preservation of spe-cific areas and components where the use of a CPC on ex-posed metal surfaces is generally recommended for reducingcorrosion. This list does not constitute authority to use CPC’son specific equipment. The use of some or all types of CPC’sin certain areas or on equipment may be detrimental. There-fore, consult the appropriate system specific aircraft, missile,or equipment corrosion and/or maintenance manuals beforeapplying a CPC in a new area to determine which, if any,compounds should be used in that area.
3.7.7 Preservation Application Methods.
• CPC’s and solvents can produce toxic vapors.Use only in well ventilated areas. Avoid con-tact with skin. Consult the local safety officeand Bioenvironmental Engineer for PersonalProtective Equipment (PPE) requirements.
• Do not use synthetic wiping rags or cloths withthese materials as they will dissolve the syn-thetic cloth/rag.
• Keep CPC’s and solvents away from openflames, heat, or sparks as they are flammable.
CPC’s can be applied by brushing, dipping, or spraying. Thearea of application, viscosity of the material, and conditionsunder which they need to be applied are factors that influ-ence the decision of which application method should beused. Low viscosity materials are best applied by spraying,whereas high viscosity materials are more suited for brush-ing or dipping. Dipping can be used for all types of materialsbut the thickness of the coating obtained with low viscositymaterials may be too thin to provide adequate corrosion pro-tection. Prior to application of preservatives, remove old pre-servative coatings and then apply a fresh coating using oneof the following methods:
3.7.7.1 Brushing. Brushing may be accomplished usingan ordinary paint brush. This method is most appropriate forapplying thick materials on small areas or in areas where itis necessary to prevent material from getting on surroundingareas or nearby equipment.
3.7.7.2 Dipping. Dipping may be accomplished using anysuitable container for the CPC. It is most suitable for smaller,disassembled parts. It cannot be used for assemblies whichcontain any part or area adversely affected by the CPC.
3.7.7.3 Spraying.
For spray application, do not thin or dilute bulkpreservative CPC unless absolutely necessary. Donot use synthetic wiping cloths. Mask off adjacentareas to prevent overspray.
Spraying may be accomplished using paint spraying equip-ment, various types of pump sprayers, or aerosol cans. Thismethod is very effective for application to large areas whereconfined areas are not involved. The viscosity of the materialwill determine which type of spraying apparatus to use.
3.8 APPLICATION OF POLISH AND WAX.
Polishing and waxing of aircraft exterior surfaces is prohib-ited.
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CHAPTER 4INSPECTION AND CORROSION PRONE AREAS
SECTION I INSPECTION
4.1 PURPOSE.
Frequent corrosion inspections are essential for an effectiveoverall corrosion control program. Early detection, identifi-cation, and treatment minimizes the costs resulting from cor-rosion damage. Without regular systematic inspections, cor-rosion will seriously damage aircraft, missiles, andequipment. This chapter describes the basic visual and Non-Destructive (NDI) inspection procedures for detecting corro-sion as well as some of the signs of corrosion damage.
4.1.1 Responsibility. Corrosion detection is everyone’sresponsibility. Since corrosion can occur almost anywhereon aircraft, missiles, and equipment, all maintenance person-nel must be able to identify and report corrosion problems.Personnel performing any scheduled inspections shall bequalified in corrosion detection and shall have attended ap-propriate corrosion prevention and control courses estab-lished by AETC and the MAJCOM, and required by AFI20-114.
4.1.2 Frequency of Inspections. The frequency and ex-tent of inspections are established by the aircraft SystemProgram Director (SPD) and/or the missile or equipmentSystem Program Manager (SPM). However, during sched-uled or unscheduled maintenance actions on aircraft, mis-siles, or equipment and their components, the area involvedas well as those within 36 inches (18 inches on each side) ofthe repair or treatment area shall be visually inspected forcorrosion. Additional inspections of areas particularly proneto corrode, such as magnesium gear boxes, wheel and con-trol surface wells, bilge areas, etc. may be necessary. Corro-sion prone areas are discussed in Paragraph 4.5.
4.1.3 General Inspections. A general inspection of air-craft, missiles, and equipment is performed as follows:
a. Clean area thoroughly per instructions in Paragraph3.5.
Prior to removing any access covers or panelscoated with TT-P-2760 flexible polyurethaneprimer either with or without a MIL-PRF-85285polyurethane topcoat, score the coating system at
the edges of the cover/panel with a sharp plastictool to prevent fraying or peeling of the paint fin-ish system when the panel is removed for the firsttime after the finish system is applied.
b. If corrosion is suspected, examine the area with a 10Xmagnifying glass and flashlight. Pay particular atten-tion to edges of skin panels, rivet heads, and othercorrosion prone areas. If blisters, bubbles, or othercoating irregularities are present, attempt to dislodgethe paint by scraping with a sharp plastic tool. If paintdoes not dislodge easily, the irregularity is probably asag or run which is confined to the paint film itself andno further action is necessary. When corrosion is sus-pected but no irregularities are present, clean and drythe area per Paragraph 3.5 and apply a strip of 3M Co.,PN 250 (preferred) or A-A-883, Type II, flat-backmasking tape over the area leaving a two inch lengthfree at one end. Hand rub the tape for several strokesin order to assure good adhesion. Grip the free end ofthe tape and remove the tape with an abrupt liftingmotion. Where paint is removed, inspect and deter-mine the extent/degree of corrosion as described byParagraph 4.4.
c. Remove corrosion, clean, and treat the surface per pro-cedures in Chapter 5 and touch-up the paint per TO1-1-8.
4.1.4 Detailed Inspections. A detailed inspection of air-craft, missiles, and equipment shall be performed if the cor-rosion damage found during a general inspection is suspectedto be extensive or severe and/or as specified in appropriatesystem specific aircraft, missile, or equipment maintenancemanuals. Aircraft, missiles, and equipment shall be carefullyinspected for corrosion using the NDI tools and procedureslisted in Table 4-1. Refer to Paragraph 4.5 for information oncommon corrosion prone areas.
4.2 INSPECTION METHODS.
4.2.1 Visual inspection. Visual inspection is the mostwidely used method for the detection and evaluation of cor-rosion. It is very effective for detecting most types of corro-sion if done carefully with a knowledge of where and forwhat to look. Read Chapter 2 (Corrosion Theory) before per-forming corrosion inspection paying particular attention to
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Table 2-1 (Appearance of Corrosion Products). The follow-ing tools can be used to find and evaluate the extent of cor-rosion damage:
• Flashlight.
• 10X Magnifying Glass.
• Plastic Scraper.
• Depth Gauge, pin micrometer type.
• Borescope.
• Optical Micrometer.
4.2.1.1 Evidence of Corrosion. Aluminum corrosionproducts are either white, gray, or black and may appear as apaste when wet or as either a hard, adherent film or easilycrumbled deposits when dry. Magnesium corrosion productsare white and powdery and form in large amounts with sig-nificant losses to the base metal. Steel corrosion products(rust) are red, brown, or black deposits either in the form ofa powder or when severe, as flakes that peel off easily. Cop-per corrosion products (patina) are blue or blue-green depos-its that adhere tightly to the surface. Titanium and stainlesssteels do not produce significant amounts of visible corro-sion products on their surfaces but they can exhibit crackingdue to stress corrosion cracking. When corrosion occurs be-neath a paint system, the surface of the paint appears blis-tered, bubbled, or distorted.
4.2.2 Depth Gauge. Depth gauges are tools used to mea-sure the depth of corrosion pits and areas reworked for pit-ting, exfoliation, and other types of corrosion to determinethe extent of corrosion damage and the amount of metalremoved during rework. If the pit and/or rework area depthare within allowable tolerances specified in a system specific
aircraft, missile, or equipment manual as directed by Para-graph 5.6, the pits can be acceptably reworked, and areasreworked for corrosion damage of any type are acceptable.Reapplication of a protective coating system to reworkedareas per TO 1-1-8 and the applicable system specific air-craft, missile, or equipment manual is required. If the depthof pits or a reworked area are not within allowable toler-ances, the part must be replaced or repaired, if allowed, or arequest for engineering assistance must be submitted to theaircraft SPD and/or the missile or equipment SPM.
NOTE
On thin sheet material, waviness in the materialmay result in false depth readings. Several read-ings may be necessary or it may be necessary toimprovise another method for determining thedepth of the corrosion damage. The depth gauge isnot suitable for determining the depth of a stresscorrosion or corrosion fatigue crack due to therelatively large size of the indicator pin.
4.2.2.1 Use of Depth Gauges. Take several depth read-ings in the affected area and select the deepest reading as thecorrosion damage depth. Where there are several damagedareas in the same skin panel or component part, plot or sketcha diagram of the depth and location of each damaged areafor comparison with damage limits specified in the appli-cable system specific aircraft, missile, or equipment manualsor for forwarding to the aircraft SPD and/or the missile orequipment SPM engineer when requesting engineering assis-tance. Place the depth gauge base flat against the undamagedsurface on each side of the corrosion damage area. Whentaking measurements on concave or convex surfaces, placethe base perpendicular to the surface. (Refer to Figure 4-1).Also, on the interior or exterior of an aircraft fuselage or amissile body, it is best to align the length of the depth gaugebase with the fuselage or body length.
Table 4-1. NDI Inspection Tools for Various Types of Corrosion
EquipmentType of Corrosion Detected orEvaluated (See Type Below)
Borescope 1, 2, 3, 4, 5, 10, 11, 12Depth Gauge 4, 5Optical Micrometer 1, 2, 4, 5, 6, 7, 8, 10, 11Fluorescent Penetrant 3, 4, 8, 9Eddy Current 1, 3, 4, 6, 8, 9Ultrasonic 3, 4, 6, 8, 9,Radiography 6, 8, 9,Type 1 Uniform surface corrosion
2 Galvanic or dissimilar metal corrosion3 Intergranular attack (general)4 Intergranular attack (exfoliation)5 Pitting6 Crevice/concentration cell corrosion
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Table 4-1. NDI Inspection Tools for Various Types of Corrosion - Continued
EquipmentType of Corrosion Detected orEvaluated (See Type Below)
7 Fretting corrosion8 Stress corrosion cracking9 Corrosion fatigue10 Filiform corrosion11 Microbiologically induced corrosion12 High temperature oxidation
4.2.3 Visual Inspection with a Borescope/Videoscope.The borescope has a small, high intensity light that can beused to aid in the inspection of interior surfaces which arenot accessible by any other method. Insert the head assemblyinto any cavity having a large enough opening. With thecavity illuminated, visually inspect it’s interior for defects,such as damage to the paint system and corrosion. (Refer toFigure 4-2).
NOTE
Wearing eyeglasses makes it difficult to place theeye at the ideal distance from the eyepiece and theview is distorted by external glare and reflection.Rubber eye shields on optical instruments (e.g.borescope, optical micrometer) are designed toshut out external light, but are not as effectivewhen glasses are worn. For these reasons, it isdesirable that the inspector be able to adjust theinstrument without wearing glasses to compensatefor variations in visual acuity.
4.2.3.1 The videoscope is essentially an advanced versionof a borescope. It utilizes a miniaturized camera and lightsource to transmit a very clear image to a hand-held videomonitor. The clarity of the image makes minor corrosion andpaint damage much easier to identify than is possible when aconventional borescope is used. Also, since the image ap-pears on a video monitor instead of inside a small borescopeinstrument tube, the problems commonly associated withwearing eyeglasses when using a borescope are avoided.Some videoscopes have additional corrosion mitigation ca-pabilities, such as the ability to extract entrapped water, re-move minor corrosion through dry ice abrasion, and applycorrosion prevention compounds (CPCs). These additionalcapabilities expand the usefulness of these types of video-scopes far beyond corrosion inspection and identification.Refer to the applicable weapons system technical order andequipment operating manual for information on the properapplication and use of videoscopes.
4.2.4 Optical Depth Micrometers.
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4.2.4.1 Analog Mechanical Read-Out Type. This in-spection tool is an alternate for the digital read-out opticaldepth micrometer and is used to measure the depth ofscratches, cracks, pits, and reworked areas and/or the height
of spurs and other protrusions. (Refer to Figure 4-3). Theoptical depth micrometer is first focused on the highest sur-face in the area of interest and a reading is taken. A secondreading is taken when the lowest surface is in focus. The
Figure 4-1. Depth Dimension of Corrosion Pits
Figure 4-2. Fiber Optic Borescope
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difference between the readings is the distance between thetwo surfaces. Optical micrometers are available with 100 and200 power magnification, reticle eyepieces, and accessorylighting. Use the procedures outlined below to determine thedepth of corrosion pits and/or areas reworked due to corro-sion damage on any surface with the optical depth microm-eter.
a. Select the appropriate base surface (e.g., flat, curved,round, or inside/outside angle surfaces) in the areawhere the measurement is to be made that will providea stable location for the micrometer feet.
b. Position the micrometer solidly over the base surfaceA of Figure 4-3 (undamaged surface close to surface Bof Figure 4-3) to make an initial measurement. Whilethe micrometer is set over the surface, a pin point oflight will cover the area being measured.
c. Look through the eyepiece of the micrometer and ro-tate the micrometer thimble clockwise or counterclock-wise starting with the hundred thousandth scale, thenthe ten thousandth scale, and finally the thousandthscale until surface A of Figure 4-3 comes into sharpfocus using extreme care when focusing to reduce in-accuracy in the measured values.
d. Obtain and record the reading for surface A of Figure4-3 located on the vernier scale. Since the vernier scaleis not one that can be simply read, an experiencedtechnician with the proper training is required to readthe scale accurately.
e. Position the micrometer over surface B of Figure 4-3(corrosion pit or area reworked due to corrosion dam-age) to measure the pit or rework depression depth.When measuring the depth of corrosion pits or re-worked areas, ensure that the surface being measuredhas a large enough area to focus on for an accuratereading.
f. Repeat procedures in step c and step d on surface B ofFigure 4-3. Take several readings from the corrosiongrind-out area and/or the corrosion pit and use thedeepest reading for the depth calculation.
g. Subtract the surface A of Figure 4-3 reading from thesurface B of Figure 4-3 reading to obtain the depth ofa corrosion grind-out or a corrosion pit or: Pit/DamageDepth = B Reading - A Reading.
4.2.4.2 Digital Read-Out Type. This digital read-out op-tical depth micrometer is the preferred inspection tool formeasuring the depth of scratches, cracks, pits, and reworkedareas and/or the height of spurs and other protrusions. (Referto Figure 4-4). The optical depth micrometer is first focusedon the highest surface in the area of interest (usually an un-damaged surface next to a scratch, pit, or grind out area),and the digital display is set to zero (0). The micrometer isthen focused on the lowest surface of the area being inspected
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(the bottom of the scratch, pit, or grind out area). The read-ing shown in the digital display when the lowest surface isbrought into focus is the actual depth of the area or the dif-ference between the undamaged surface and the bottom ofthe damaged area. This type of optical micrometer comeswith extra lenses capable of 40, 80, 100, and 200 powermagnification. The depth of narrow features such as stresscorrosion and corrosion fatigue cracks can be observed andmeasured with the higher power lenses while using the reticleeyepiece to measure the width of such features. The digitalmicrometer kit also includes interchangeable bases, acces-sory lighting, and a sample scratch plate for demonstrationand practice. Use the procedures outlined below to deter-mine the depth of corrosion pits and/or areas reworked dueto corrosion damage on any surface with the optical depthmicrometer.
a. Select the appropriate base to use on the type of sur-face (e.g. flat, curved, round, or inside/outside angle)on which the measurement will be made.
b. Turn on the digital display and check to see if it readsin inches and not millimeters. Change it to inches withthe in/mm button, if necessary.
NOTE
The “origin” button is not needed or used in thisapplication.
c. Shine a flashlight down through the eyepiece to spotthe target and position the micrometer. Look throughthe eyepiece and focus up and down to assure thatboth the high and low surfaces are within the field ofview. Rotating the focus thimble counterclockwisemoves the lens up and clockwise moves the lens down.The 10X objective lens will focus when it is approxi-mately ¼ in above the surface.
d. Focus on surface A and carefully press the “zero” but-ton on the display without moving the micrometer.
e. Focus on surface B and read the depth on the digitaldisplay while observing the following points:
(1) Do not move the micrometer base when refocus-ing between surface A at the 0.000 inch digitalread-out and surface B.
(2) To get accurate readings, take extreme care in fo-cusing. Be sure to focus well past the surface B(clockwise rotation) you picked in case evenlower areas might be found.
(3) If both surfaces A and B are not within the fieldof view, use the 4X lens to get a wider field ofview.
f. Take several readings from the corrosion damaged/grind out area and select the deepest reading as theactual depth.
4.2.5 Fluorescent Penetrant Inspection.
The apparent simplicity of the penetrant inspec-tion is deceptive. Very slight variations in the in-spection process can invalidate the inspection byfailing to indicate serious flaws. It is essential thatpersonnel performing penetrant inspection betrained and experienced in the penetrant process.
NOTE
The following inspection methods shall be accom-plished only by qualified and certified NDI techni-cians. Refer to TO 33B-1-1 and the specific sys-tem specific NDI manual for more detailedinspection procedures.
Fluorescent penetrant inspections require components to becleaned and then treated with a fluorescent penetrating liquidwhich is capable of entering surface cracks and/or flaws.After removing the penetrant from the surface, a developer(powder or liquid suspension of powder) is applied to absorbpenetrant trapped in the cracks or flaws. Under ultravioletlight, the absorbed penetrant is visible directly above thecracks or flaws from which it was drawn out. The penetrantinspection method is used to detect stress corrosion cracking,corrosion fatigue and plain fatigue cracks, intergranular cor-rosion, and residual corrosion following corrosion removalby grinding or sanding. Intergranular corrosion attack at me-tallic grain boundaries and the network of very fine cracks itforms are visible in the early stages only under a 10X orgreater magnification, and developer is not used when evalu-ating a penetrant indication with a magnifying glass. In ad-dition, if penetrant inspection is used to monitor a surfacefor adequacy of corrosion removal by grinding or sanding,caution must be exercised because mechanical removal meth-ods can cause smearing which may obscure indications ofremaining corrosion. When monitoring corrosion grind outareas with penetrant, a developer is not used following re-moval of excess surface penetrant because the area must alsobe examined with a 10X magnifying glass after a minimum5 minute dwell time. When corrosion is no longer detectedin a corrosion grind-out area, the inspection process shall berepeated using non-aqueous developer to determine if anycracks are present.
4.2.5.1 Limitations of Penetrant Inspection.
4.2.5.1.1 Flaw Location. Penetrant inspection is appli-cable to all solid, non-porous materials provided the flaw
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being inspected for is open to the surface of the part. Todetect subsurface flaws, another inspection method must beused.
4.2.5.1.2 Restricted Flaw Openings. The penetrant in-spection process depends upon the ability of the penetrant toenter and exit the flaw opening. Any factor that interfereswith the entry or exit reduces its effectiveness. Organic coat-ings, such as paint, oil, grease, or resin, are examples of thisinterference. Any coating that covers or bridges the flawopening prevents penetrant entry, and even if it does notcover the opening, material at the edge of the opening affectsthe mechanism of penetrant entry and exit, and greatly re-duces the reliability of the inspection. Coatings at the edgeof the flaw may also retain penetrant causing backgroundfluorescence. An inspection method other than penetrant mustbe used if the organic coating cannot be stripped or removedfrom the surface in the area to be inspected.
4.2.5.1.3 Smeared Metal. Mechanical operations, such asshot peening, machine honing, abrasive blasting, buffing,wire brushing, grinding, or sanding can smear or peen thesurface of metals. This mechanical working closes or re-duces the surface opening of any existing discontinuities orflaws. Mechanical working (smearing or peening) also oc-curs during service when parts contact or rub against eachother. Penetrant inspection will not reliably indicate discon-tinuities or flaws when it is performed after a mechanicaloperation or service that smears or peens the surface. Chemi-cal etching per procedures in TO 33B-1-1 and/or the systemspecific aircraft, missile, or equipment NDI manual is rec-ommended prior to penetrant operations to improve test sen-sitivity when smeared metal is present.
4.2.5.1.4 Porous Surfaces. Penetrant inspection is im-practical on porous materials with interconnected subsurfaceporosity. The penetrant rapidly enters the pores and migratesthrough the network. This results in an overall fluorescenceor color that masks any potential discontinuity or flaw indi-cations. In addition, removal of the penetrant after the in-spection may be impossible.
4.2.6 Eddy Current Inspection. The eddy current inspec-tion method may be used to detect or evaluate accessible andinaccessible surfaces for corrosion. This method can detectand evaluate pitting, intergranular, exfoliation, stress corro-sion cracking, and corrosion fatigue cracking. Detection ofcorrosion with eddy current techniques is used on aircraft,missile, and equipment skins where corrosion may occur oninaccessible interior surfaces. Corrosion usually occurs in ar-eas where moisture is entrapped in faying surface areas. Ifrelatively uniform thinning is expected, corrosion detectionmay be simply a matter of thickness measurement. In mostinstances, corrosion is confined to smaller localized areas ofrelatively small diameter. As skin thicknesses increase, sen-sitivity to small areas and shallow depths of corrosion isreduced. Corrosion on either member of faying surfaces maybe detected. Refer to TO 33B-1-1 and/or the system specific
NDI manuals for more detailed inspection procedures. Eddycurrent can also be used for corrosion removal inspectionsbut is less sensitive than penetrant.
4.2.7 Ultrasonic Inspection. The ultrasonic inspectionmethod may be used to detect exfoliation, intergranular, pit-ting, corrosion, and stress corrosion and corrosion fatiguecracking. Ultrasonic thickness gauging is included in thismethod. Ultrasonic inspection for far-side pitting and inter-nal exfoliation corrosion may be accomplished using shear(“S”) wave and longitudinal (“L”) wave techniques. The useof a delay line transducer is recommended for “L” waveinspection to improve resolution of both near and far surfacecorrosion. Technique development is required for each spe-cific application. Refer to TO 33B-1-1 and/or system specificNDI manuals for more detailed inspection procedures.
4.2.8 Radiographic Inspection. Although the radio-graphic inspection method is available for detection andevaluation of corrosion, it is generally used only when noother method can accomplish the inspection. The labor hourrequirements are high for on-aircraft/missile/equipment radi-ography as well as requiring restricted access for other main-tenance personnel during the inspection. Radiographic in-spection is used in combination with ultrasonics to determinethe condition of aluminum honeycomb. Refer to TO 33B-1-1and/or system specific NDI manuals for more detailed in-spection procedures.
4.3 EVALUATION OF CORROSION DAMAGE.
Visually determine if the corrosion is present in an areawhich has previously been reworked. If the corrosion dam-age is in a previously reworked area, measure the damage toinclude the material which has previously been removed. Astraight edge and a 10X magnifying glass may be used toassist in determining if an area has previously been reworked.Place the straight edge across the area being examined atvarious angles and check for irregularities, low spots, or de-pressions. (Refer to Figure 4-5). If any irregularities, lowspots, or depressions are found and a visual determinationcannot verify previous rework, closely examine the suspectedarea and the surrounding area using the 10X magnifyingglass. After determining that the area has been previouslyreworked, evaluate the depth of the previous rework (grind-out) to determine if further metal removal will exceed grind-out limits specified in the applicable aircraft, missile, orequipment system specific manuals or as specified in Para-graph 5.6. Depth measurements can also be made using thedepth gauges as described in Paragraph 4.2.2 and Paragraph4.2.4.
4.4 DEGREES OF CORROSION.
Corrosion must be evaluated after the initial inspection andcleaning to determine the nature and extent of repair or re-work needed. It is difficult to draw a distinct and specificdividing line among the degrees of corrosion, so reliableevaluation requires sound maintenance judgment. Use thefollowing categories in reporting degrees of corrosion.
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Figure 4-3. Optical Depth Micrometer (Analog Mechanical Read Out Type)
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Figure 4-4. Optical Depth Micrometer (Digital Read Out Type)
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4.4.1 Light Corrosion. This degree of corrosion is indi-cated by the protective coating being scraped, gouged, orchipped to bare metal, or showing the tracks of filiform cor-rosion in the film and the bare metal showing is character-ized by discoloration of surface corrosion and/or pitting to adepth of approximately one mil (0.001 inch) maximum. Thistype of damage can normally be removed by light handsanding.
4.4.2 Moderate Corrosion. This degree of corrosion lookssomewhat like light corrosion except some blisters or evi-dence of scaling and flaking of the coating or paint system is
present and the pitting depths may be as deep as 10 mils(0.010 inch). This type of damage is normally removed byextensive hand sanding or light mechanical sanding.
4.4.3 Severe Corrosion. The general appearance of thisdegree of corrosion is similar to moderate corrosion in theappearance of the coating system but with severe intergranu-lar corrosion cracks and blistering exfoliation with scaling orflaking of the metal surface. The pitting depths are deeperthan 10 mils (0.010 inch). This damage must be removed byextensive mechanical sanding or grinding and may require apatch type repair or component replacement.
SECTION II CORROSION PRONE AREAS
4.5 COMMON AREAS.
There are certain corrosion prone areas common to all air-craft, missiles, and equipment. (Refer to Figure 4-6 throughFigure 4-25). Corrosion prone areas should be cleaned, in-spected, and treated more frequently than less corrosionprone areas. The following paragraphs describe the areas andcontain illustrations to aid in inspections. However, the list isnot complete and should be expanded by referring to thesystem specific maintenance manuals and cards for each spe-cific aircraft, missile, or piece of equipment which showother possible trouble spots.
4.5.1 Fasteners. There are hundreds to thousands of fas-teners on aircraft, missile and equipment exterior surfaces,and areas around these fasteners are trouble spots. (Refer toFigure 4-6 and Figure 4-7). These areas are subject to highoperational loads and/or moisture intrusion which makes theskin material highly susceptible to corrosion at fastener lo-cations. High strains cause paint to crack around the fasten-
ers which provides a path for corrosive materials to enter thejoint between fastener heads and skin panels. Any paint thatis not highly flexible will crack to some degree around fas-teners.
4.5.2 Faying Surfaces and Crevices. Similar to corro-sion around fasteners, corrosion in faying surfaces, seams,and joints is caused by the intrusion of salt water and/orother corrosive fluids or agents. Entry of fluids by capillaryaction causes corrosive liquids to flow into the tightest ofjoints. The effect of corrosion resulting from fluid intrusioninto joint areas is usually detectable as bulging of the skinsurface.
4.5.3 Spot Welded Assemblies. Spot welded assembliesare particularly corrosion prone due to entrapment of corro-sive agents between the parts of the assemblies. (Refer toFigure 4-8 and Figure 4-9). Corrosive attack causes skinbuckling or spot weld bulging (refer to Figure 4-9), andeventual spot weld fracture. Skin and spot weld bulging may
Figure 4-5. Typical Use of a Straight Edge to Determine if Suspect Areas Have Been Previously Reworked
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be detected in their early stages by sighting or feeling alongspot welded seams. This condition is prevented by keepingpotential moisture entry points such as gaps, seams, and holescreated by broken spot welds filled with a sealant or a suit-able preservative or CPC.
4.5.4 Engine Exhaust and Gun Gas Impingement Ar-eas. Exhaust and gun gas impingement areas include areason an aircraft, missile, or piece of equipment exposed toengine, rocket, missile, and equipment exhaust, gun blast orany other surface exposed to them on installed equipment.These gases cover the organic finish on the surface with de-posits (i.e. corrosive ash and residual solids) that damage thefinish. Surfaces located in the path of rocket and gun blasts,including gun compartment systems and spent ammunitioncollection chutes, are particularly susceptible to deteriorationand corrosion. (Refer to Figure 4-10). In addition to the cor-
rosive effect of the gases and exhaust deposits, the protectivefinish is often blistered by the heat, blasted away by the highvelocity gases, or abraded by spent shell casings or solidparticles from engine, gun, and rocket exhausts/gases. (Referto Figure 4-11). These areas require more attention duringinspections.
4.5.5 Wheel Wells and Landing Gear. Wheel well areasprobably receive more abuse than any other area on an air-craft. They are exposed to water spray, mud, salt and otherrunway deicing agents, gravel, and other flying debris fromrunways during taxiing, takeoff, and landing. They are alsoexposed to salt air and spray when aircraft are parked atlocations near salt water. Because of the many complicatedshapes, assemblies, and fittings in the area, complete cover-age with protective coatings is difficult to maintain. (Refer toFigure 4-12).
Figure 4-6. Corrosion Around Fasteners
Figure 4-7. Galvanic Corrosion of Aluminum Adjacent to Steel Fasteners
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4.5.6 Flap and Slat Recesses. Flap and slat recesses/wells (refer to Figure 4-13), and equipment installed in themare normally hidden from view since flaps and slats are usu-ally maintained in the retracted/closed position when an air-craft is on the ground and they may experience corrosionthat goes unnoticed unless special inspections are performed.
4.5.7 Engine Frontal Areas and Air Inlet Ducts. Sincethese areas are constantly abraded by dirt, dust, and gravel,and eroded by rain, special attention shall be given to thefollowing:
a. Engine frontal areas (refer to Figure 4-14 and Figure4-15), for general surface corrosion, pitting, intergranu-lar corrosion, and erosion.
b. Leading edges of air inlet ducts, including hardwareinside ducts (refer to Figure 4-16 and Figure 4-17), fordamaged/deteriorated protective coating/paint system,galvanic corrosion at fastener locations, general sur-face corrosion, exfoliation corrosion, and erosion.
Figure 4-8. Spot Weld Corrosion
Figure 4-9. Spot Welded Skin Corrosion Mechanism
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Figure 4-10. Gun Blast Area Corrosion Points
Figure 4-11. Exhaust Trail Area Corrosion Points
Figure 4-12. F-15 Nose Landing Gear Wheel Well
Figure 4-13. Flaps Lowered to Expose Recess Areas
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Figure 4-14. Reciprocating Engine Frontal AreaCorrosion Points
Figure 4-15. Jet Engine Frontal Area Corrosion Points
Figure 4-16. Corrosion Prone Point of Air Inlet
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c. Due to heat dissipation requirements, oil cooler coresand reciprocating engine cylinder fins are not usuallypainted. Engine accessory mounting bases may havesmall, unpainted areas on the machined mounting sur-faces. With moist, salt-laden air flowing over thesesurfaces, they are vulnerable to general surface corro-sion/rusting and pitting.
4.5.8 Wing/Fin-Fold Joints and Wing and Control Sur-face Leading Edges.
a. Wing and fin-fold areas are vulnerable to corrosive at-tack when the wings or fins are folded so they requirespecial attention. (Refer to Figure 4-18).
b. Both wing and control surface leading edges on air-craft are constantly exposed to salt laden air and winderosion which make them vulnerable to corrosion sothey both require special attention.
4.5.9 Hinges. Hinges (refer to Figure 4-19 and Figure4-20), are highly susceptible to corrosion because of dissimi-lar metal contact that results from wear and damage to pro-tective metallic coatings. They are natural traps for dirt, salt,and moisture. Piano type hinges which are used extensivelyon aircraft hatches and control surfaces are especially vul-nerable to attack.
4.5.10 Control Cables. Control cables present a corro-sion problem whether they are made of carbon steel or stain-less steel. As shown in Figure 4-21, the presence of barespots in the plastic cladding on clad cables or missing orgaps in the protective CPC coating are the main contributingfactors to the corrosion of cables. Dirt, grime, and rust thatcollect between cable strands lead to more severe corrosionand wear that eventually cause cable failure.
4.5.11 Relief Tube Outlets. Urine products are very cor-rosive. (Refer to Figure 4-22). Relief tube areas should becleaned frequently and the paint finish kept in good condi-
tion. The relief tubes are usually made of plastic and do notpresent a corrosion problem, but the surrounding metallicaircraft fuselage structure can be severely corroded by urineproducts.
4.5.12 Water Entrapment Areas. Figure 4-23 showscommon water entrapment areas. Design specifications re-quire that aircraft have drains installed in all areas wherewater may collect, but in many cases these drains are inef-fective either because of improper location or because theyare plugged by sealants, fasteners, dirt, grease, and/or otherdebris. The plugging of a single drain hole or the altering ofthe attitude of the aircraft can cause serious structural defectif salt water or other corrosives remain for any appreciableamount of time in one of these entrapment areas. Daily in-spection and cleaning, if necessary, of low point drains is astandard requirement. These areas may accumulate waterfollowing washing or rinsing of aircraft. Where this is a re-curring problem, field units shall request the aircraft SPD todevelop procedures to prevent water accumulation. Drainholes shall not be drilled by field units unless specificallyauthorized by the aircraft SPD.
4.5.13 Bilge Areas. Aircraft bilge areas are natural col-lection points (i.e., low points/areas in an aircraft fuselage)for water, salt water, dirt, loose fasteners, drill shavings, andother debris. (Refer to Figure 4-24). Keeping bilge areas freeof debris and fluids, maintaining the protective finish systemin good condition, and application of CPC’s, as required, inaircraft system specific maintenance manuals are the bestprotection against corrosion in bilge areas.
4.5.14 Battery Compartments and Battery Vent Open-ings. In spite of protective paint systems, corrosion preven-tive compounds, and venting provisions, battery compart-ments are high corrosion problem areas. (Refer to Figure4-25). Fumes from overheated battery electrolyte will spreadto adjacent internal cavities causing rapid corrosion of un-protected surfaces. If the battery installation has an external
Figure 4-17. Corrosion in Air Intake Duct
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vent opening on the aircraft, missile, or equipment skin, in-clude this area in battery compartment inspection and main-tenance procedures. Frequent cleaning and neutralization ofdeposits will minimize corrosion. Leakage of electrolytes ofeither sulfuric acid from lead-acid batteries or potassium hy-droxide from nickel-cadmium batteries will cause corrosion.Consult the applicable system specific maintenance manualsof the particular aircraft, missile, or piece of equipment todetermine which type of battery is used. Refer to Chapter 3,Chapter 8, and system specific maintenance manuals for in-structions on neutralizing battery electrolytes.
4.5.15 Magnesium Parts. Magnesium parts are extremelycorrosion prone. Special attention must be given to propercorrosion preventive surface pretreatment of their surfaces,insulation from contact with other metal surfaces, and main-tenance of protective paint coatings.
4.5.16 Electrical Connectors and Other Components.Some electrical connectors are potted with a sealant com-pound to prevent the entrance of water into the backsideareas of connectors where wires are attached to pins. RubberO-rings are also used to seal moisture out of the front side orpin mating areas of connectors when two connector halvesare mated together. If moisture gets into electrical plugs, itwill cause corrosion and electrical failure. Electrical plugsmust be disconnected periodically for inspection and corro-sion treatment. The use of improper and unauthorized seal-ants, potting compounds, and corrosion preventive com-pounds can cause severe corrosion damage and/or electricalfailure of electrical connectors or components.
Figure 4-18. Wing Fold Joint
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Figure 4-19. Hinge Corrosion Points
Figure 4-20. Piano Hinge Lugs
Figure 4-21. Control Cables
Figure 4-22. Personnel Relief Tube Vent
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Figure 4-23. Common Water Entrapment Areas
Figure 4-24. Bilge Areas
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Figure 4-25. Battery Compartment
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CHAPTER 5CORROSION REMOVAL AND SURFACE TREATMENT
SECTION I CORROSION REMOVAL
5.1 PURPOSE.
This chapter covers procedures for corrosion removal andsurface treatment. When corrosion is detected, a specific andimmediate corrective action is required. Each type of corro-sion has its own specifics and requires special treatment.Complete treatment involves a thorough inspection of allcorroded areas, evaluation of the corrosion damage (refer toChapter 4), paint removal per TO 1-1-8, corrosion removalper this chapter, application of chemical surface treatmentsper this chapter, sealing (refer to Chapter 6), and application/touch-up of protective paint finishes per TO 1-1-8.
5.2 RESPONSIBILITY.
Propellers and helicopter blades have critical bal-ance requirements. Refer to the appropriate sys-tem specific propeller or blade manual for evalua-tion and repair limits for corrosion, erosion, andabrasion damage.
Personnel assigned to perform corrosion removal correctivemaintenance tasks shall be specially trained in the use ofchemical paint removers, abrasive materials, powered andhand tools, depth and area measurement of metal removed,and determination of damage limits from the applicable sys-tem specific maintenance manuals. Inadequate training willlead to further damage of equipment and poses a safety haz-ard to the individual.
5.3 CORRECTIVE ACTIONS.
Corrective maintenance depends on the type of surface in-volved (metallic or composite), the area of the damaged sur-face (small corrosion spot or large heavily corroded area),and the degree of corrosion, as determined in Chapter 4.Composite materials, such as fiberglass or graphite-rein-forced structures, shall not be exposed to chemical paint re-mover, but shall only be scuff sanded to the primer coat.Since composite materials do not corrode, corrosion removaltechniques are not applicable and shall not be used. Corro-sion shall always be removed by the mildest effective tech-
nique. For mechanical procedures specific to the variousmetal alloys, refer to Table 5-3 and Table 5-4.
5.4 PAINT REMOVAL.
Refer to TO 1-1-8 for proper paint removal procedures.Choose the most effective method that produces the leastamount of hazardous waste and danger to personnel for thejob to be accomplished.
5.5 CORROSION REMOVAL.
Corrosion can be removed by either mechanical or chemicalmethods. Certain factors must be considered prior to startingany corrosion removal operation. The most important factoris that corrosion products must be removed completely with-out causing additional damage to the structure during theprocess. This can be accomplished by first removing all cor-rosion visible through a 10X magnifying glass, then remov-ing an additional two mils (0.0020 inch) to ensure that alldeposits have been eliminated. Failure to remove all corro-sion allows the corrosion to continue even after affected sur-faces are refinished. Additional factors to consider are asfollows:
a. Before attempting to remove corrosion products, stripthe paint and clean contaminants from the surface.Surface contaminants and paint interfere with corro-sion removal procedures and make the operation moredifficult.
b. Protect adjacent components and parts from corrosionresidue and possible damage that could be caused bythe removal operation. Corrosion residue can cause ad-ditional corrosion and damage the surface finish of thesurrounding area. An accidental slip of a corrosion re-moval tool can quickly result in additional damage.
c. Prior to corrosion removal, determine the allowablelimits from the system specific aircraft, missile, and/orequipment manuals and/or technical orders. When re-moving corrosion from critical aircraft, missile, orequipment structure, take the following steps:
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(1) If allowable metal removal or damage limits willnot be exceeded, remove corrosion completely.Metal loss due to corrosion damage is cumula-tive. Metal loss from prior corrosion removal op-erations and corrosion removal from areas on theopposite side of a part must be considered whenassessing the degree of corrosion damage.
(2) If allowable damage limits will be exceeded, re-pair the damaged area or replace parts per proce-dures in system specific aircraft, missile, or equip-ment repair manuals/technical orders. Coordinateany repair or part replacement not covered inthese manuals/technical orders with the aircraftSPD or the missile or equipment SPM.
5.5.1 Mechanical Methods. There are various mechani-cal methods for removing corrosion from metal surfaces. Themethod used and the types of tools and equipment selectedfor the removal operation depend on the type of metal in-volved, the location and accessibility of the corroded area,the degree of damage, and the type of corrosion involved. Itis important that the removal method, tools, and equipmentselected be compatible with the metal surface. Compatibilityinvolves two considerations: the mechanical effect of theequipment and tools on the surface and the compatibility ofmetallic particles worn off the removal equipment and toolswhich might become embedded in the metal surface.
5.5.1.1 Mechanical Compatibility.
Corrosion removal accessories/tools, such as flapbrushes or rotary files, shall be used on one typeof metal only. For example, a flap brush used toremove corrosion from aluminum alloys shall notbe used to remove corrosion from magnesium al-loys or steel also.
Mechanical compatibility refers to the selection of the righttools and equipment to prevent additional damage caused bythe removal process. Often, it is necessary to select a seriesof removal techniques involving the use of different gradesor classes of equipment and material to effectively removethe corrosion products. The initial use of a rapid and coarseremoval method followed by a slower and finer removalmethod produces a smooth metal surface finish (e.g. using avacuum blaster first followed by using a fine abrasive clothor paper to finish the job).
5.5.1.2 Material Compatibility. Material compatibility re-fers to using a medium for brushing, abrading, blasting, etc.,that will not cause additional corrosion. Material compat-ibilities are assured by using like metals during corrosionremoval operations (e.g. regular carbon steel wool shall neverbe used to remove corrosion from aluminum alloys as it willembed in the aluminum alloy surface and cause galvaniccorrosion).
5.5.2 Non-Powered Tools and Materials.
5.5.2.1 Abrasive Mats. Abrasive mats are made from anylon mesh material impregnated with various grades of alu-minum oxide. Abrasive mats are available in 9 x 11 inchsheets under A-A-58054, Type I, Class 1, Grade A - VeryFine (280-400 grit), Grade B - Fine (180 grit), and Grade C- Medium (100-150 grit). These mats are used by hand toremove small areas of corrosion and/or paint where the useof powered tools would be impractical or prevented by theshape or accessibility of the area. Table 5-1 is a guide forrelating abrasive mat materials to coated abrasive paperand/or cloth grit particle sizes.
5.5.2.2 Abrasive Cloth. Abrasive cloths with bonded alu-minum oxide grit per A-A-1048 and silicon carbide grit perA-A-1200 are used for dry sanding of light to moderate cor-rosion products. They are available in 9 x 11 inch sheets and2 or 3 inch wide x 150 foot long rolls in 240 grit (Fine) and320 grit (Very Fine) grades.
5.5.2.3 Abrasive Paper. Heavy paper with silicon car-bide grit bonded to it per A-A-1047 is used for either wet ordry sanding to remove light to moderate corrosion. It isavailable in 9 x 11 inch sheets in 240 grit (Fine) and 320 grit(Very Fine) grades. Silicon carbide is usually more effectivethan aluminum oxide on harder metals such as low carbonand corrosion resistant steel alloys. Other abrasive paper andcloth with bonded emery or flint are available but they sufferfrom poor efficiency and short working life.
5.5.2.4 Metallic Wools. Metallic wools are abrasive ma-terials used for removing corrosion that is not tightly bondedto a metal surface. The four major types of metallic woolsare aluminum, copper, stainless (CRES) steel, and carbonsteel. Metallic wools are available in five grades, rangingfrom very fine to extra coarse. Table 5-2 is a guide to helpselect the correct grade of metallic wool.
5.5.2.4.1 Use of Metallic Wool on Corroded Metals.The type of corroded metal must be known before usingmetallic wool. Carbon steel wool is used on low carbon steelalloys, aluminum wool is used on aluminum and magnesiumalloys, copper wool is used on copper, bronze, and brassalloys, and stainless steel wool is used on stainless (CRES)steel alloys. The use of metallic wools which are not gal-vanically compatible with the metal surface being treated isnot authorized. These metallic wool materials are very goodfor removing corrosion from tubing or extruded parts. Re-move all metallic wool residue from the metal surface beingtreated and the surrounding area with a vacuum cleaner. Me-tallic wool particles can create galvanic cells if left on themetal surface.
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Table 5-1. Grades of Abrasive Mats
Grade Coated Abrasive (CA) EquivalentMedium (C) 100 - 150
Fine (B) 180 - 240Very Fine (A) 240 - 320
Super Fine (AA) 500 & finerUltra Fine (AAA) 10 microns & finer
Table 5-2. Grades of Steel Wool
Type Grade UseVery Fine Final smoothing
II Fine Most commonly usedIII Medium General purposeIV Coarse Rough workV Extra coarse Restoration work
5.5.2.5 Wire Brushes. Wire brushes are available withcarbon steel, stainless (CRES) steel, aluminum, and brassbristles and are used to remove heavy corrosion deposits andflaking paint that are not tightly bonded to the metal surface.Densely set, short, stiff bristles are most effective for rapidcorrosion removal. The metallic bristles must be compatiblewith the metal surface being treated to prevent galvanic cor-rosion with stainless (CRES) steel being considered neutraland usable on all metals. Do not use brushes with a bristlewire gauge or diameter above 0.010 inch, as severe gougingof the surface leading to stress risers and fatigue crackingmay occur. Remove the corrosion with a linear motion, donot cross-hatch as this will unnecessarily damage the sur-rounding surface area. After wire brushing, the surface areasmust be polished with fine abrasive paper to remove and/orsmooth out gouges and scratches.
5.5.2.6 Pumice Powder. Pumice powder is a very fineand soft abrasive used to remove stains or to remove surfacecorrosion on thin metal surfaces where minimum metal re-moval is allowed. It is mixed with water and then rubbedover the area with a soft cloth to polish the surface. After thecorrosion is removed, the powder is wiped off the surfacewith a clean cloth wet with fresh water.
5.5.2.7 Scrapers. Scrapers are used primarily for the ini-tial removal of heavy corrosion deposits such as flaking rustand exfoliation blisters, and are particularly effective in cor-ners and crevices that cannot be reached with other equip-ment. Scrapers may be locally manufactured from phenolicplastic, fiberglass, aluminum alloys, plain carbon steel orcarbide-tipped carbon steel, or stainless (CRES) steel. Plasticand fiberglass scrapers may be used on any type of metalsurface but are of limited value due to their softness relativeto a metal surface, stainless (CRES) steel and carbide-tippedcarbon steel scrapers may be used on any type of metal sur-face, aluminum alloy scrapers may be used only on alumi-num or magnesium alloy surfaces, and plain carbon steelscrapers may be used only on carbon steel surfaces. Scrapersmade from copper or brass alloys shall never be used on anystructural metal surface as galvanic corrosion will result.Failure to use the correct metal scraper can also lead to gal-vanic corrosion after the part is returned to service. Surfaceareas must receive further finishing after corrosion removalwith scrapers due to the gouging action of scrapers and thedifficulty in determining complete corrosion removal aftertheir use.
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5.5.3 Power Tools and Materials.
• Power tool operations can often generate toxicairborne particles containing heavy metals, suchas chromium (in the form of chromates), tita-nium, nickel, and beryllium, depending on thesurface being treated. Eye protection, ventila-tion, and an adequate respirator for dust controlare required.
• Do not use hands to probe for air leaks in powertools and their hoses as injury may result.
• Before using any powered equipment, removeany clothing such as ties and shirts with longloose sleeves as well as all rings and other jew
elry which might become entangled in theequipment. Always wear proper personal safetyequipment (PPE), such as goggles, face-shields,respirators, etc. Ensure that all electrical equip-ment is grounded.
• Corrosion removal with power tools is a veryaggressive method which shall only be usedwhen and where the extent of corrosion makesnon-powered corrosion removal impractical.The indiscriminate use of power tools for cor-rosion removal can result in damage to protec-tive surface finishes.
Power tools are used to remove heavy corrosion from local-ized areas on metal surfaces or mild to severe corrosion overlarge surface areas. Their use results in saving time andmoney, but care must be exercised when using power tools.Application of excessive pressure can easily damage metal
Figure 5-1. 3M Co. Scotch-BriteTM Flap Brush and Mandrel
Figure 5-2. Abrasive Flap Wheels with Spindle Mount
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surfaces and cause internal metallurgical changes in the metaldue to excessive heat buildup.
5.5.3.1 Pneumatic Drill Motors. Pneumatic drill motorsare the preferred power tools for removing heavy corrosionor reworking large surface areas. The drill motor is normallyused with wire brush wheels, rotary files, flap brushes, sand-ing pads, abrasive wheels, or buffing wheels. These drills areavailable in many shapes and sizes to satisfy almost anyrequirement. Check all pneumatic equipment air hoses forbreaks or bulges in the coverings.
a. Maximum chuck capacity of portable powered drills isusually ¼ inch. Insert the tool shank into the drill andtighten chuck securely with the chuck key prior to use.When it is difficult or impossible to reach the workarea with a straight drill, use a flexible shaft or angleadapter. The flexible shaft permits working around ob-structions with a minimum of effort.
b. To prevent the rotary file, abrasive wheel, flap brush,or sanding disc from digging into the metal, keep thetool off the metal when initially starting the drill mo-tor. When the abrading stroke is finished, lift the toolfrom the metal before releasing the power to the mo-tor.
c. Holding the drill motor with both hands, apply moder-ate pressure while holding the rotary file, sanding disc,flap brush, or abrasive wheel against the work surface.
When using the pneumatic tool as a sander, be sure tocheck the size and type of the abrasive disc. Ensurethat the type of disc is compatible with the metal. Keepthe sanding disc tilted to approximately a 10 degreeangle so that only one side of the disc is in contactwith the metal surface. If the entire disc surface is incontact with the surface, a “bucking” effect will occur.Excessive pressure will cause a “chattering” effect.Move the tool over the surface with slightly overlap-ping strokes. Do not grind, sand, or file in one area forany extended length of time without stopping and al-lowing the metal to cool. Excessive heating of themetal will alter its metallurgical structure.
5.5.3.2 Pneumatic Sanders. The proper technique forusing pneumatic sanders with oscillating heads shall includethe following:
a. To prevent the sander from digging into the metal, startthe sander before it touches the metal. When the sand-ing stroke is finished, lift the sander from the metalbefore pressing the stop switch. Do not lay the unitdown with the motor running.
b. For best results, apply moderate pressure while hold-ing the sander against the work. Move the sander overthe surface with parallel and slightly overlappingstrokes. Move it as slowly as possible without causingoverheating of the metal. Generally, the coverage rateshould be about two square feet per minute.
Figure 5-3. 3M Co. Radial Bristle Disc
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5.5.3.3 3M Co. Scotch-BriteTM Finishing Flap Brushes.
Do not use flap brushes (refer to Figure 5-1), downto within 2 inches of core. Continued use beyondthis limit may cause gouging due to loss of flex-ibility of fiber. When using flap brushes, applyminimal pressure to remove a minimum amountof metal. Excessive pressure on flap brushes willcause paint at the edge of the area being workedto melt, gum up, and streak onto the work area.Do not use on non-metallic surfaces.
Flap brushes are made of non-woven, nylon webbing im-pregnated with aluminum oxide grit. The brushes are veryeffective for removing mild surface corrosion and preppingsurfaces. It can also be used for mechanical removal andfeathering of paint systems. The brushes are comprised of aseries of flaps bonded to a cardboard core and attached to amandrel. Each flap impacts the surface as the brush spins.When used correctly, the brushes will lead to minimal metalremoval. The flap brush and mandrel (refer to Figure 5-1),shall be assembled so that the arrow, painted on the brush, isfacing the operator and points in the direction of rotation(clockwise). To achieve maximum effectiveness, use at thespecified RPM and do not exceed the maximum RPM ratingspecified on the brush to prevent disintegration during useand either damage to equipment or injury to personnel.
5.5.3.4 Abrasive Flap Wheels. Abrasive flap wheelscome in various types. One type is made of paper flaps im-pregnated with aluminum oxide abrasive and mounted on aspindle. (Refer to Figure 5-2). Another type is made from aresin reinforced nylon mesh impregnated with aluminum ox-ide abrasive in a convoluted flap form per A-A-59292, Class1 or a unitized, rigid, laminated form per A-A-59292, Class2, both of which are mounted on arbors. Depending on gritsize, these wheels can be used to remove medium to severecorrosion from thick materials, but caution must be used tominimize the amount of metal removal. For the most effec-tive use of this equipment, use at the specified RPM andnever exceed the maximum RPM rating specified on thewheel to prevent disintegration of the wheel during use andeither damage to equipment or injury to personnel.
5.5.3.5 Abrasive Cloth and Paper. Aluminum oxide andsilicon carbide cloth and paper can be used with sanders anddrill motors by cutting suitable pieces from stock or usingprecut discs mounted on pad type holders.
5.5.3.6 Powered Wire Brushes. Powered wire brushesare available with various types of wire (straight, twisted, orcrimped), various lengths of wire (short, medium, or long),and various wire densities (light, medium, or heavy). Differ-ent actions can be obtained by varying wire type, trim length,and density.
Figure 5-4. 3M Co. Roloc Discs
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5.5.3.7 Rotary Files.
Unless authorized and directed by the cognizantaircraft SPD or missile or equipment SPM, rotarywire brushes are not authorized for corrosion re-moval on any metals except low strength carbonsteels. They can severely damage softer metal al-loys such as aluminum and magnesium by leavingdeep gouges in them and cause fatigue problemsin high strength steel and aluminum alloys due tothe stress risers created by the deep scratches/gouges they leave on the surface.
Since they provide one of the fastest ways to remove corro-sion and underlying metal, rotary files should only be handledby an experienced structural repair technician. This tool is atungsten carbide cylinder or cone into which cutting edgeshave been machined. When installed in the chuck of a pneu-matic drill, rapid metal removal can be achieved.
5.5.3.8 3M Co. RolocTM Disc and Radial Disc Abra-sives.
Improper use of rotary files can rapidly damagealuminum structures by creating thin spots thatexceed established damage limits. Their use is au-thorized only for removal of severe intergranular
or exfoliation corrosion by qualified structural re-pair technicians. Do not use rotary files to removecorrosion from installed fasteners.
These tools are available in various grits and diameters tocover all corrosion removal requirements from initial grindout to final finishing/smoothing of the grind-out area. TheRolocTM discs consist of a spindle that screws into a discpad that receives a screw on type paper coated abrasive disc,a Scotch-BriteTM nylon mesh abrasive disc, or a plasticBristle DiscTM abrasive. These disc assemblies are mountedto either a straight or right angle type pneumatic drill toremove corrosion from all types of readily accessible metalsurfaces. The radial type plastic Bristle DiscTM is similar toa flap wheel and is mounted to an arbor either by itself or inmultiples with the assembly being installed in a straight typepneumatic drill to remove corrosion from all types of metalsurfaces, particularly in bores and recessed areas. To achievemaximum effectiveness with these discs, use at the specifiedRPM and never exceed the maximum RPM rating specifiedon the disc to prevent disintegration of the disc during useand either damage to equipment or injury to personnel.
5.5.4 Abrasive Blasting.
Abrasive blasting operations create airborne par-ticles which may be hazardous to the skin andeyes. A hood, gloves with gauntlets, and adequateventilation are required.
Figure 5-5. 3M Co. Inline Bristle Disc
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In abrasive blasting, abrasive media is propelled toward thework piece either with air pressure (conventional or vacuumblasting) or with water (wet blasting).
5.5.4.1 Conventional Equipment. Two types of equip-ment are used to propel dry abrasives, direct pressure feedand suction/venturi feed. In direct pressure equipment: theabrasive holding tank is a pressure vessel from which abra-sive media is forced, through a metering device, into thepressurized blast line to the blast nozzle. In suction/venturifeed equipment, the abrasive holding tank is unpressurizedand provides media, through a metering device, into a pass-ing air stream which then propels it through the blast hose tothe blast nozzle. Small blast cabinets known as glove boxes(refer to Figure 5-6, A), are built to accommodate small partsand have a recycle system which removes dust and lightparticle contaminants such as paint chips or corrosion prod-ucts. Blasting rooms, designed for large components, use arecycling and ventilating system. The operator works withinthe room, using a blast gun.
NOTE
Suction/venturi feed equipment requires highernozzle pressure than direct pressure equipment toobtain the required abrasive action. Pressures givenin Table 5-3 are for direct pressure equipment. Asa general rule, increase the nozzle pressure by 50%when using suction/venturi feed equipment.
5.5.4.1.1 Blast Media. A wide variety of materials invarious sizes (measured by mesh or grit size) are availablefor blasting applications. Only aluminum oxide per A-A-59316, Type I, Grades A or B and glass beads per AMS2431/6, Designation Nos. 15, 12, 9, and 6 (sizes 10-13) abra-sives are approved for use on aircraft, missiles, and theircomponents. Other media may be used on steel componentsof support equipment as designated in TO 35-1-3 and/or theequipment system specific maintenance manual.
5.5.4.1.2 Air Hoses. The nozzle pressure of a blast streamis affected by the length and inside diameter (ID) of the airhoses. It is best to use the shortest hose possible to preventexcessive pressure drop due to friction. If it is necessary tocouple lengths of hose, use quick disconnect external cou-plers.
5.5.4.1.3 Blast Nozzles. In general, larger nozzle sizesare preferable to smaller ones because more area can becleaned per hour with the same amount of labor. High effi-ciency, wear resistant nozzles (e.g. tungsten carbide) shouldbe used since they have a longer service life and direct theblasting particles more efficiently. Inspect nozzles periodi-cally for wear and discard them when the orifice is worn to adiameter which is 50% greater than the diameter when new.A worn nozzle, just as a larger nozzle, will require a largervolume of air flow from the compressor to sustain the neededpressure at the nozzle.
Table 5-3. Recommended Powered Abrasives for Corrosion Removal
Abrasive Blasting Parameters
AlloyFlap Brush, Abra-
sive Wheels1Abrasive Cloth/
Paper2 Media3 Pressure (PSI) Other ToolsAluminum
Alloys(Clad)
Aluminum oxideor silicon car-bide
Aluminum oxideor silicon car-bide
Glass beads (Sizes10-13) or (AGB-15, 12, 9, or 6)
30-404 None
AluminumAlloys(Non-clad)
Aluminum oxideor silicon car-bide
Aluminum oxideor silicon car-bide
Glass beads (Sizes10-13) or (AGB-15, 12, 9, or 6)
40-454 Rotary files(fine fluted)
MagnesiumAlloys
Aluminum oxideor silicon car-bide
Aluminum oxideor silicon car-bide
Glass beads (Sizes10-13) or (AGB-15, 12, 9, or 6)
10-354 Rotary files(fine fluted)
Ferrous Met-als (otherthan Stain-less Steel)
Aluminum oxideor silicon car-bide
Aluminum oxideor silicon car-bide
Aluminum oxide(Type I, Grade A orB); Glass beads(Sizes 10-13) or(AGB-15, 12, 9, or6)
40-504 40-504 Rotary files,Wirewheels(steel orstainlesssteel)
Stainless Steeland Nickelalloys
Aluminum oxideor silicon car-bide
Aluminum oxideor silicon car-bide
5 Glass beads (Sizes10-13) or (AGB-15, 12, 9, or 6)
40-504 Wire wheels(stainlesssteel) Ro-tary files(fine fluted)
Copper Alloys DO NOT USE POWERED ABRASIVE METHODS DUE TO TOXICITY OF RESIDUE/PAR-TICLES GIVEN OFF - IN PARTICULAR FROM BERYLLIUM-COPPER ALLOYS.
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Table 5-3. Recommended Powered Abrasives for Corrosion Removal - Continued
Abrasive Blasting Parameters
AlloyFlap Brush, Abra-
sive Wheels1Abrasive Cloth/
Paper2 Media3 Pressure (PSI) Other Tools
Powered abrasive operations on titanium alloys can generate severe sparking. Keep area clear of all ignitable sub-stances when performing powered abrasive operations on titanium alloys.
Titanium Al-loys
Aluminum oxideor silicon car-bide
Aluminum oxideor silicon car-bide
Glass beads (Sizes10-13) or (AGB-15, 12, 9, or 6);Aluminum oxide(Type I, Grade A orB)
40-504 40-504 None
Plated andPhosphatedSurfaces
DO NOT USE POWERED ABRASIVE METHODS DUE TO TOXICITY OF RESIDUE/PAR-TICLES GIVEN OFF FROM MANY TYPES OF PLATING AND PROBABLE SEVEREDAMAGE TO VERY THIN PLATING FILMS.
1 This includes RolocTM type discs and in-line radial type Bristle DiscsTM.2 This includes RolocTM type discs.3 Media specifications: Glass beads - AMS 2431/6 aluminum oxide - A-A-59316.4 Indicated pressure is for direct pressure equipment. For suction/venturi equipment, use 50% higher pressure.5 Use only on heavily corroded parts prior to acid pickling and/or passivation.
5.5.4.1.4 Air Supply. Frictional losses in the hoses reducethe pressure at the nozzle and nozzle wear increases the vol-ume of air needed to maintain the desired nozzle pressure.To allow for nozzle wear, it is generally good practice to usea compressor with the capability of delivering at least 1 ½times the cubic feet per minute (CFM) of air required for anew nozzle to permit adjustments as the nozzle wears. Mois-ture and oil in the air stream gradually accumulates in theabrasive during blasting operations and will eventually causethe abrasive to clog the blaster. A water and oil separatormust be used in the compressed air supply line to preventthis problem.
5.5.4.2 Portable Vacuum Abrasive Blast Equipment.Also known as vacu-blasters or dry honing machines, thesedevices are portable machines designed to recover the abra-sive as it rebounds from the work piece. Vacu-blasters havean abrasive hopper, a reclaimer, a dust collector, a vacuumpump, and a blast gun which contains both a blast nozzleand a vacuum duct surrounding the nozzle for recovery ofthe media. (Refer to Figure 5-6, B). This equipment is usefulonly on flat or slightly curved surfaces so that the rebound-ing media can be collected by the vacuum duct surroundingthe blast nozzle. Refer to TO 35-1-3, the equipment opera-
tors manual, and systems specific maintenance manuals forthe aircraft, missile, or equipment being repaired for furtherinformation on the authorization and use of these machines.
5.5.4.3 Wet Abrasive Blasting Equipment. Wet abrasiveblasters use high pressure water as the medium for the deliv-ery of abrasives. This method is not as harmful to the basemetal as dry abrasive blasting due to the cushioning effect ofthe water medium. Unfortunately, this effect inhibits thespeed with which corrosion products are removed and thewater can be driven into joint areas and cause corrosion it-self. For these reasons, this method should not be used onaircraft or missiles. Wet abrasive blasters are useful for re-moving rust from steel surfaces of support equipment. Theabrasive material is normally not recoverable in wet blastingoperations, and only sand per A-A-59316, Types II or VI,Grades B or C, aluminum oxide per A-A-59316, Type I,Grades A or B, or glass beads per AMS 2431/6, DesignationNo. AGB-6 (Size 13) shall be used. A corrosion inhibitormust be added to the water or a temporary protective filmsuch as a Corrosion Preventive Compound (CPC) must beapplied to the blasted surface immediately after blasting toprevent rusting of the steel surface until the part can bepainted.
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Table 5-4. Recommended Non-Powered Abrasives for Corrosion Removal
AlloyNon-Woven
AbrasiveAbrasive Cloth/
Paper Metallic Wool Brushes OthersAluminum
AlloysAbrasive Mat Aluminum oxide,
Silicon carbideAluminum wool Stainless steel,
AluminumPumice paste, Carbide-
tipped scrapersMagnesium
AlloysAbrasive Mat Aluminum oxide,
Silicon carbideNone Stainless steel,
AluminumPumice paste, Carbide-
tipped scrapers
Figure 5-6. Abrasive Blasting Equipment
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Table 5-4. Recommended Non-Powered Abrasives for Corrosion Removal - Continued
AlloyNon-Woven
AbrasiveAbrasive Cloth/
Paper Metallic Wool Brushes OthersFerrous Met-
als (otherthan Stain-less Steel)
Abrasive Mat Aluminum oxide,Silicon carbide
Steel wool Carbon steel,Stainless steel
Carbide-tipped scrapers
StainlessSteel andNickel Al-loys
None Aluminum oxide,Silicon carbide
Stainless steelwool
Stainless steel,Aluminum
None
Copper Al-loys
None Aluminum oxide(400 grit), Sili-con carbide (400grit)
Copper wool Brass None
Titanium Al-loys
Abrasive Mat Aluminum oxide,Silicon carbide
Stainless steelwool
Stainless steel,Aluminum
Pumice paste, Carbide-tipped scrapers
Cadmium orZinc Platedsurfaces
Abrasive Mat Aluminum oxide,Silicon carbide
None None None
Chromium,Nickel, Tin,or CopperPlated Sur-faces
Abrasive Mat Aluminum oxide,Silicon carbide
None Stainless steel,Aluminum
None
PhosphatedSurfaces
USE METHOD RECOMMENDED FOR BASE METAL
5.6 SURFACE FINISH.
All depressions resulting from corrosion removal shall beblended smoothly and evenly with the surrounding originalsurfaces. In critical and highly stressed areas, all pits remain-ing after removal of corrosion products, by any method, shallbe blended out to prevent stress risers which may becomestarting points for stress corrosion cracking and/or metal fa-tigue. On non-critical structures, it is not necessary to blendout pits remaining after removal of corrosion products sincethis can result in unnecessary metal removal. Always checkthe system specific aircraft, missile, or equipment mainte-nance/repair manuals for maximum allowable depth of de-pressions due to pitting or corrosion removal. The generalguidelines for shaping and blending corrosion grind outs areshown in Figure 5-7 through Figure 5-9. For additional in-formation on blend out procedures, refer to the system spe-cific aircraft, missile, or equipment maintenance manualsand/or contact the aircraft SPD or the missile or equipmentSPM.
5.7 PITTING ON CRITICAL STRUCTURE.
On critical structures having a large number of closely spacedpits, intervening material may be removed to minimize sur-face irregularity or waviness. The resulting depression shall
have no sharp corners and shall be saucer-shaped, whereverclearance permits, with its major axis running spanwise onwings and horizontal stabilizers, longitudinally on fuselages,and vertically on vertical stabilizers. (Refer to Figure 5-7).In areas where a true saucer shaped depression cannot beformed due to inadequate clearance, blend out a depressionas nearly as possible to that shape so that there are no abruptor sharp edges.
5.8 CORROSION REMOVAL PROCEDURES-ME-CHANICAL.
5.8.1 Warnings and Cautions. The following warningsand cautions shall be observed during corrosion removal op-erations.
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5.8.1.1 Personal Protection.
• Many materials such as copper alloys (espe-cially beryllium-copper, refer to Paragraph7.20), cadmium plate, chromate conversioncoatings, paints containing chromates, lead,barium, and strontium, and chemicals used forcorrosion removal are toxic. Use approved res-pirators, eye protection, and skin protection.Take proper safety precautions to avoid inhala-tion or ingestion of chemical fumes or liquidsand dust from corrosion products during corro-sion removal. Wash hands thoroughly beforeeating or smoking.
• All powered mechanical corrosion removal pro-cedures create airborne particles. Respiratorsand eye protection and adequate ventilation arerequired.
• It is essential that all blasting media and otherresidue be completely removed after abrasiveblasting operations. The blasting media can bevery slippery and can cause dangerous falls.
• Operators shall be adequately protected withcomplete face and head covering equipment,and provided with pure breathing air per re-quirements of AFI 91-203 and AFOSH Stan-dards 48-137 for all abrasive blasting opera-tions.
• Wear leather gloves when using metallic woolsto prevent hand injuries.
• Do not use abrasive flap brushes, wheels, discs,or wire brushes above their authorized RPMrating. These tools can fly apart causing seriousinjury.
• Abrasive blasting operations create extensiveairborne particles which may be hazardous tothe eyes, lungs, skin, etc. A hood, gloves withgauntlets, and respirator are required.
• Exercise caution when using sharp or pointedtools to prevent injury.
• Depleted uranium is extremely toxic and shallbe worked only under a license from theNuclear Regulatory Agency (NRA). Machiningor other work, such as surface sanding, may bedone only by the licensee. No drilling, sanding,abrasive blasting, or other mechanical work ispermitted on depleted uranium by any fieldlevel (organizational or intermediate) mainte-nance activity. If the protective finish (plating)which covers the depleted uranium is chipped,peeled, or otherwise removed so the dark grayor black uranium oxide is visible, the part mustbe returned to the licensee for rework or dis-posal. Packaging and shipping procedures shallconform to AFI 40-201 and any other relatedcurrent regulations for handling radioactivematerials.
TO 1-1-691
5-12 Change 5
Figure 5-7. Shaping Reworked Areas
Figure 5-8. Acceptable Clean-Up of Pitting Corrosion on Critical Structure
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5.8.1.2 Mechanical Damage.
• Use extreme care to ensure that blast mediadoes not contaminate hydraulic, fuel, oil, cool-ant, or oxygen systems. Blockages in flightcritical components caused by abrasive mediaparticles can result in loss of life and aircraft.
• Finely divided dried particles of many materi-als (metallic, organic, and inorganic) can formexplosive mixtures with air resulting in dustexplosion hazards. Use extreme care when dryabrasive blasting magnesium and titanium al-loys and provide adequate ventilation to pre-vent formation of explosive dust mixtures dur-ing all abrasive blasting operations.
• Abrasive blasting operations of these surfacesshall not be subjected to severe abrasive action.Do not use rotary files to remove corrosionfrom installed fasteners.
• Use only non-powered abrasive paper, cloth, ormat, powered flap brushes or wheels, or abra-sive blasting to remove corrosion from highsteels. Other power tools can cause local over-heating and/or formation of notches which cangenerate fatigue or stress corrosion crackingfailures. Refer to TO 4S-1-182 for additionalprocedures/restrictions to be used on aircraftlanding gear components.
• Dry abrasive blasting of titanium alloys andhigh strength steel crates sparking. Ensure thatthe abrasive blasting area is free of all flam-mable vapors and liquids.
• Do not use flap brushes down to within twoinches from the center of the hub. Continueduse beyond this limit may cause gouging due toloss of flexibility of the fiber. Follow directionof rotation as indicated by arrow imprinted onside surface of the core.
• Excessive pressure on flap brushes will causepolyurethane paint to melt, gum up, and streakaround the area being worked
• Protect areas adjacent to corrosion removal op-erations from chips, dust, and other debriswhich could produce dissimilar metal corrosionon previously uncorroded surfaces.
• Use only those materials recommended in Table5-3 and Table 5-4 to prevent dissimilar metalparticles from becoming embedded in surfacesand generating rapid galvanic corrosion.
• Be careful when removing corrosion from softplated surfaces (zinc, cadmium, etc.). Soft plat-ing is easily damaged or removed by mechani-cal methods.
5.8.2 Non-Powered Mechanical Corrosion Removal.This method is accomplished by abrading the corroded sur-face with hand held tools or abrasives to remove the corro-sion. It is normally used to remove surface corrosion andother forms of mild to moderate corrosion by scraping orwearing away the corrosion products along with a minoramount of base metal. The basic steps in this procedure areas follows:
Figure 5-9. Limited Clearance
TO 1-1-691
5-14
a. Determine whether all the corrosion can be removedwithout exceeding the allowable damage limits beforestarting the removal operation. If damage limits willbe exceeded, repair or replace the part per directions inthe applicable system specific aircraft, missile, orequipment maintenance manual or request dispositionfrom the aircraft SPD or the missile or equipment SPMif repair or replacement is not covered in the manuals.
b. Protect adjacent components and/or areas from scale,chips, corrosion products, and chemical agents. Masklap joints, hinges, faying surfaces, access doors, airscoops, and other openings which would allow chips,dust, or other debris to enter interior areas. Use barriermaterial/paper and masking tape.
(1) Clean the affected area to remove grease, oil, andsoils. (Refer to Chapter 3).
(2) Using materials in Table 5-4, remove all corro-sion using the mildest effective method. Deter-mine whether corrosion has been completely re-moved by inspecting with a 10X magnifier. (Referto Appendix B). If necessary, a more sensitiveevaluation can be made by using fluorescent pen-etrant in conjunction with the magnifier.
(3) When complete removal has been attained, blendor fair out the edges of the damaged areas usingfine abrasive paper or cloth. After all corrosionhas been removed, recheck to ensure that allow-able damage limits have not been exceeded
(4) Treat the surface in accordance with Section II ofthis chapter and apply protective coatings in ac-cordance with TO 1-1-8 and the applicable sys-tem specific maintenance manual.
5.8.3 Powered Mechanical Corrosion Removal. Pow-ered corrosion removal is generally done using pneumaticdrills with flap brush, rotary file, sanding pad, or abrasivewheel attachments. This method is normally used to removeheavy corrosion by wearing away the corrosion products.Part of the base metal is abraded away with the corrosionproducts using this procedure. The basic steps in corrosionremoval are as follows:
a. Determine whether all the corrosion can be removedwithout exceeding the allowable damage limits before
starting the removal operation. If damage limits willbe exceeded, repair or replace the part per directions inthe applicable system specific aircraft, missile, orequipment maintenance manual or request dispositionfrom the aircraft SPD or the missile or equipment SPMif repair or replacement is not covered in the manuals.
b. Protect adjacent components and/or areas from scale,chips, corrosion products, and chemical agents. Masklap joints, hinges, faying surfaces, access doors, airscoops, and other openings which would allow chips,dust, or other debris to enter interior areas. Use barriermaterial/paper and masking tape.
(1) Clean the affected area to remove grease, oil, andsoils. (Refer to Chapter 3).
(2) Using materials in Table 5-3, remove all corro-sion using the mildest effective method. Deter-mine whether corrosion has been completely re-moved by inspecting with a 10X magnifier. (Referto Appendix B). If necessary, a more sensitiveevaluation can be made by using fluorescent pen-etrant in conjunction with the magnifier.
(3) When complete removal has been attained, blendor fair out the edges of the damaged areas usingfine abrasive paper or cloth.
(4) After all corrosion has been removed, recheck toensure allowable damage limits have not been ex-ceeded.
(5) Treat the surface in accordance with Section II ofthis chapter and apply protective coatings in ac-cordance with TO 1-1-8 and the applicable sys-tem specific maintenance manual.
5.8.4 Abrasive Blasting Corrosion Removal. Before be-ginning abrasive blasting operations, ensure that all safetyprecautions listed in the warnings and cautions in Paragraph3.5.1.2 and Paragraph 5.8.1.2 are fully observed. Failure tocomply with these precautions may result in harm to person-nel and equipment.
5.8.4.1 Abrasive Blasting Procedures. The blasting op-eration should be accomplished in the following steps.
TO 1-1-691
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PMB used for blasting ferrous metals shall not beused to blast non-ferrous metals (i.e. aluminum,magnesium, etc.). Abrasives used for cleaning fer-rous metals will retain many ferrous metal par-ticles which will contaminate any non-ferrousmetal and promote corrosion. It is recommendedthat separate PMB booths or cabinets be obtainedand labeled as “For Ferrous Only” and “Non-Fer-rous Only”.
NOTE
A log should be maintained for each PMB unit totrack media usage hours. Blast media used on air-craft and aircraft components shall be tested forcontamination or purged every 80 hours of equip-ment operation or after each aircraft or large pieceof aerospace equipment is blasted (whichever islonger). Blast media used on non-aerospace equip-ment such as SE shall be tested or purged every800 hours of equipment operation. Follow TO1-1-8, Paragraph 2.11.12 for contamination testingprocedures.
a. Inspect corroded areas and surfaces and decide whichones can be abrasively blasted and what techniqueswill be used. Clean any oil, grease, or other soils fromsurfaces with MIL-PRF-87937, Type IV, MIL-PRF-85570, Type II, or an approved cleaning solvent suchas A-A-59601, MIL-PRF-32295, Type II and/or MIL-PRF-680, per instructions in Chapter 3 of this manual.
(1) Blasting shall not be used in areas or under con-ditions that would allow any escaped abrasiveparticles to contaminate any system, engine, orother component.
(2) Examine all corroded areas for corrosion blisters.If intergranular and/or exfoliation corrosion ispresent, use other recommended mechanical re-moval methods. Abrasive blasting will not removethese types of corrosion effectively.
(3) Blasting shall not be performed on surfaces wherethere is a danger of warping or distorting the basematerial. Sheet metal, 0.0625 inch (16 gauge, U.S.Standard) or thinner, shall not be blasted. Consultthe applicable system specific aircraft, missile, orequipment manuals to determine metal type,thickness, and allowable metal removal limits forthe particular part.
b. Determine what areas need protection from the mediablast stream and entrapment of the media and mask orseal these areas. Composite surfaces and those requir-ing a very smooth surface finish (63 RMS or better),must be effectively protected from the media blast
stream. Use form fitting metal or wood shields, as re-quired, and an impact resistant tape such as 3M Co.,PN 510 or YR-500.
c. Statically ground the abrasive blast equipment and theaircraft, missile, or equipment to be blasted.
d. Blast corroded areas using the pressures and materialsgiven in Table 5-3. Do not attempt to use pressureshigher than those specified since higher air pressurestend to cause significant damage to components byrapidly removing too much surrounding metal alongwith the corrosion products. When cleaning non-fer-rous metal alloys (i.e. aluminum, magnesium, etc.,)never use media which has been used for cleaning fer-rous metals. Abrasives used for cleaning ferrous met-als will retain many ferrous metal particles which willcontaminate any non-ferrous metal being blasted. Re-fer to the applicable abrasive blasting equipment op-erator’s manual for specific operating instructions.
(1) Direct the blast stream at the surface from whichcorrosion is being removed to sweep across thesurface at an angle of 30° to 40° from the blastnozzle to the surface. Several short passes overthe corroded area with the blast nozzle are muchmore effective and less damaging to the surround-ing metal than dwelling on an area for an ex-tended period of time. Passes should start a fewinches before and end a few inches beyond thecorroded area being worked.
(2) Maintain the nozzle distance from the surface be-ing cleaned wherever the best cleaning is obtainedwithin the range of 2 inches minimum to 6 inchesmaximum.
(3) Continue blasting with short passes over the cor-roded area until a near-white metal surface is ob-tained. A near-white metal surface is a surfacefrom which all mill scale, rust, oxides, any othertypes of corrosion products, paint, and/or anyother foreign matter have been removed.
(4) On critical high strength aluminum and steel parts,it is necessary to fair out and smooth edges ofpits to reduce stress concentrations that generatemetal fatigue and/or stress corrosion crackingproblems. The most effective manner is to rotatethe blast nozzle around the outer edge of the pitkeeping the nozzle at a constant rate using sev-eral short passes over the corroded area.
e. Upon completion of blasting, inspect for the presenceof corrosion in the blasted area. It may be necessary touse fluorescent penetrant inspection in conjunction witha 10X magnifier. Pay particular attention to areas whereit is suspected that pitting has progressed into inter-granular attack because abrasive blasting has a ten-
TO 1-1-691
5-16 Change 13
dency to close up streaks of intergranular corrosionrather than remove them if the operator uses an im-proper impingement angle. If corrosion has not beenremoved in a total blasting time of 60 seconds on anyone specific area, other mechanical methods of removalshould be utilized.
NOTE
• Refer to the individual system specific aircraft,missile, or equipment maintenance manuals forlimits on metal removal. Do not exceed theselimits without engineering approval from theaircraft SPD or the missile or equipment SPM.
• Abrasive blasting will not remove intergranularand/or exfoliation corrosion from aluminum al-loys.
• Abrasive blasting shall be used on stainlesssteel (CRES) and nickel alloy parts only to re-move severe/heavy corrosion and prior to acidpickling and/or passivation.
f. Completely clean all residue from the surface and ex-posed areas using either a pneumatic or an electricwet/dry vacuum cleaner. The vacuum cleaner nozzleshall be plastic or covered with masking tape to pro-tect surfaces from mechanical damage. Clean the sur-face using materials and procedures in Chapter 3. Treatand protect all blasted areas as soon as possible afterblasting in accordance with the procedures in SectionII of this chapter.
5.9 CORROSION REMOVAL-CHEMICAL.
The following paragraphs discuss chemical removal proce-dures for use on aircraft, missile, and other equipment parts/components and assemblies. Each type of metal alloy re-quires specific chemicals for removal of the different typesof corrosion that are encountered on the metal alloy. Theauthorized chemical corrosion removal materials and proce-dures for their usage for each of the various metal alloysused on Air Force aircraft, missiles, and equipment is dis-cussed separately for each metal alloy.
5.9.1 Aluminum Alloys. These paragraphs outline chemi-cal corrosion removal procedures for aluminum alloy partsand assemblies of aircraft, missiles, and other equipment.Table 5-5 provides procedures for removal of specific typesof corrosion.
5.9.1.1 Preparation. Before starting chemical removal ofcorrosion products, perform the following procedures:
a. Clean all dirt, grease, oil, and other contamination fromsurfaces to be worked in accordance with Chapter 3.
b. Inspect the equipment to determine which area(s) areand should be treated with a chemical corrosion re-moval compound. If an aircraft is being prepared forcomplete painting or repainting, all cleaned bare alu-minum surfaces shall be treated.
• Protect all magnesium surfaces from contactwith SAE AMS-1640 (MIL-C-38334) corrosionremoval compound and treat later, as prescribedin this manual. Steel and cadmium plated partsshould also be protected from this compound,but protection of all steel and cadmium platedsteel fastener heads in large structures is im-practical and need not be done.
• Do not allow these chemical corrosion remov-ers to contact high strength steel. Hydrogenembrittlement may occur and cause a cata-strophic failure.
c. Mask all lap joints, hinges, faying surfaces, accessdoors, air scoops, and other openings that would allowthe corrosion removal compound to enter interior areasor crevices, or contact unprotected magnesium, steel,and cadmium plated parts. Mask with MIL-PRF-131,Class 1 water and vapor proof barrier material (plasticside toward the surface) and SAE AMS-T-23397, TypeII (MIL-T-23397, Type II) masking tape. 3M Co., PN425 tape is the most effective tape for extensive opera-tions, such as chemical corrosion removal and surfacepreparation on large structures such as aircraft exteri-ors during depot repaint operations.
5.9.1.2 Chemical Corrosion Removal Materials forAluminum Alloys. SAE AMS-1640 (MIL-C-38334, Type I)Corrosion Removal Compound for Aircraft Surfaces is theauthorized general chemical remover for removing corrosionproducts from aluminum alloys, in particular on larger areas.Limited area corrosion removal can also be accomplished byusing MIL-DTL-81706, Class 1A chemical conversion coat-
TO 1-1-691
5-17
ing solution or Semco® PN Pasa-Jell 102 gel-type alumi-num corrosion remover in conjunction with A-A-58054, TypeI, Grade B or C abrasive mats.
5.9.1.2.1 SAE AMS-1640 (MIL-C-38334, Type I) Cor-rosion Removing Compound for Aircraft Surfaces.
SAE AMS-1640 (MIL-C-38334, Type I) andSemco® PN Pasa-Jell 102 are moderately toxicand MIL-DTL-81706, Class 1A is highly toxic toskin, eyes, and respiratory tract. Chemical orsplash proof goggles and/or face shields, andchemical resistant rubber gloves, and aprons arerequired. Good general ventilation is normallyadequate.
This material is a liquid concentrate material which shall bemixed with an equal volume of tap water before use; furtherdilution renders it ineffective. This material has a shelf lifeof one year from the date of manufacture, discard any of thematerial which has reached or exceeded its shelf life. SAEAMS-1640 (MIL-C-38334, Type I) is used as a generalchemical corrosion remover to remove surface and pittingcorrosion products from aluminum alloy surfaces. It is notLiquid Oxygen (LOX) compatible.
5.9.1.2.1.1 Application and Use. The procedure for ap-plication and use of SAE AMS-1640 (MIL-C-38334, Type I)materials is as follows:
a. After mixing properly, apply the solution by eitherflowing, mopping, sponging, brushing, wiping, orspraying with a non-atomizing sprayer onto the surfacebeing worked. For large areas, begin the application at
the lowest point and work upward while using a circu-lar motion to apply the solution to ensure proper cov-erage and to disturb the oxide film on the surface.
b. Allow the solution to dwell on the surface for 11 to 12minutes while vigorously agitating it on the surface atleast every 2 minutes with a non-metallic, acid resis-tant, bristle brush or an A-A-58054, Type I, Grade Bor C abrasive mat. Then rinse the surface thoroughlywith fresh water heated to a temperature of +120° to+140° F (+49° to +60° C). The solution is much moreeffective if it is also heated to a temperature of +120°to +140° F (+49° to +60° C) and applied while warm.For severe pitting, removal may be aided by lightlyagitating the pits by hand with a stainless steel (CRES)wire bristle brush with wire bristles having a maxi-mum diameter between 0.005 and 0.006 inch (5-6mils). Areas with moderate to heavy surface or pittingcorrosion may require additional applications.
c. After each solution application and rinse, examine thearea being worked, aided with a 10X magnifier forpitting, to determine if all corrosion products have beenremoved. If not, repeat this process a maximum ofthree more times. If corrosion products remain afterthe fourth application of this chemical remover, use anappropriate mechanical method described in this chap-ter to remove the remaining corrosion products.
NOTE
MIL-DTL-81706/MIL-DTL-5541, Class 1Achemical chromate conversion coating shall be ap-plied immediately after the final rinse when corro-sion removal is the last process of a rework opera-tion, or when the item or area will be painted.
Table 5-5. Typical Chemical Corrosion Removal Procedures for Aluminum Alloy Parts and Assemblies
Type of CorrosionStep 1
Corrosion Removal
Step 2Surface Treatment(When Applicable)
Step 3Final Protective Paint Finish
(When Applicable)Light or heavy pit-
ting or etching ofaluminum alloys(clad)
Remove corrosion withSAE AMS-1640 (MIL-C-38334, Type I) perParagraph 5.9.1.2.1.
MIL-DTL-81706/MIL-DTL-5541, Class 1A per Sec-tion II of this chapter.
See TO 1-1-8 and aircraft, mis-sile, or equipment systemspecific maintenance manu-als for paint system.
Light or heavy pit-ting or etching ofaluminum alloys(non-clad)
Remove corrosion withSAE AMS-1640 (MIL-C-38334, Type I) perParagraph 5.9.1.2.1 fol-lowed by appropriatemechanical methods inthis chapter, if neces-sary.
As above As above
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Table 5-5. Typical Chemical Corrosion Removal Procedures for Aluminum Alloy Parts and Assemblies- Continued
Type of CorrosionStep 1
Corrosion Removal
Step 2Surface Treatment(When Applicable)
Step 3Final Protective Paint Finish
(When Applicable)Intergranular or exfo-
liation corrosion ofaluminum alloys
Not applicable. Removecorrosion by appropriatemechanical methods inthis chapter.
As above As above
Light or heavy pit-ting or etching onsmall aluminumalloy parts whichcan be removedfor treatment
Remove corrosion and/oroxide film by immersionin a SAE AMS-1640(MIL-C-38334, Type I)prepared per Paragraph5.9.1.2.1.
Immersion in MIL-DTL-81706, Class 1A solutionper Section II of thischapter.
As above
Stress corrosioncracking of alumi-num
Not applicable. Replace/repair, as required, inthe structural handbook
See step 1 See step 1
5.9.1.2.2 Semco® PN Pasa-Jell 102. This material is agel type chemical corrosion remover for use on aluminumalloys in limited areas, in particular where LOX compatibil-ity is required, to remove pitting and surface corrosion oretching/oxidation. Pasa-Jell 102 is a relatively strong acidmixture that can be detrimental to equipment or componentsif improperly used. Therefore, it shall be used only in smallareas and primarily where LOX compatibility is an essentialrequirement. Personnel must be properly trained and quali-fied to use this material for corrosion removal.
5.9.1.2.2.1 Application and Use.
Do not use aluminum or any type of steel wool toapply or agitate Semco® PN Pasa-Jell 102 or firewill result.
Excessive use of abrasive materials and Semco®PN Pasa-Jell 102 can cause removal of protectivecladding (Alclad) and/or excessive metal removal.
The procedure for application and use of Semco® PN Pasa-Jell 102 material is as follows:
a. Apply Pasa-Jell 102 with an acid brush. Agitate areasof deep pitting with an acid brush that has the bristlesshortened by cutting off half their length or an A-A-58054, Type I, Grade A or B abrasive mat until corro-sion products are removed. A thin, evenly dispersedfilm gives the best results. Keep the dwell time to theminimum necessary to effectively remove the corro-
sion products (5 to 12 minutes). Usually, dwell timecan be controlled by closely observing the reaction ofthe Pasa-Jell 102 mixture with the aluminum surfaceto which it is applied to determine when all corrosionproducts have been lifted from the surface.
b. After all the corrosion products have been freed fromthe surface or the maximum 12 minutes dwell time isreached, whichever is first, wipe off the Pasa-Jell 102and other residue with a clean, moist cloth followed byrinsing with a stream of fresh tap water applied with awash bottle or continue to wipe with a clean, moistcloth, frequently rinsed in fresh tap water.
c. Inspect the area being worked to determine if all cor-rosion has been removed giving particular attention topitted areas. Use a 10X magnifier to aid in examina-tion of questionable areas. Remaining corrosion willappear as a powdery crust, slightly different in colorthan the uncorroded base metal. One application ofPasa-Jell 102 is usually sufficient in most cases. How-ever, in severe cases, the preceding steps may have tobe repeated.
5.9.1.2.3 MIL-DTL-81706, Class 1A Chemical Chro-mate Conversion Coating Solutions. Limited area corro-sion removal from aluminum alloy surfaces while simultane-ously applying a chemical chromate conversion coating canbe accomplished by using a MIL-DTL-81706, Class 1A so-lution in conjunction with an A-A-58054, Type I, Grade Cabrasive mat. This material helps to clean an area by oxidiz-ing all organic soils on the aluminum alloy surface, whilethe abrasive mat acts to remove the corrosion products, andthen the solution forms a chemical chromate conversioncoating film on the aluminum alloy surface. If organic soilsare present, they will turn green upon application of the so-lution. The green residue and the solution contaminated with
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the residue should be wiped from the surface and discarded.Mix the MIL-DTL-81706, Class 1A solution in accordancewith the manufacturer’s instructions and Section II of thischapter. It is recommended that the technician practice onsome condemned components or parts prior to using thismaterial on serviceable aircraft, missile, or equipment alumi-num alloy parts.
5.9.1.2.3.1 Application of MIL-DTL-81706, Class 1ASolutions for Corrosion Removal.
MIL-DTL-81706, Class 1A chemical chromateconversion coating solutions are moderately toxicto the skin, eyes, and respiratory tract. Chemicalor splash proof goggles and chemical resistantrubber gloves are required. Good general ventila-tion is normally adequate.
MIL-DTL-81706, Class 1A solutions shall not beused on high strength steels (180 KSI or higher),due to the potential of hydrogen embrittlement.Also, they shall not be used on magnesium, tita-nium, or cadmium or zinc plated parts/surfaces asthey will damage and/or corrode these metals.
The procedures for application of these materials for corro-sion removal are the same as those cited in Section II of thischapter for the standard chemical chromate conversion coat-ing solutions, except as follows:
a. The small area requiring corrosion removal and sur-face treatment can be cleaned with the chemical chro-mate conversion coating solution instead of cleaning,rinsing, and drying per Chapter 3 before application ofthe solution.
b. Thoroughly wet or flood the area being worked withthe solution and keep it wet with solution until allphases of the process are completed and the final filmis formed to prevent streaking and/or powdering on thesurface.
c. Lightly abrade the surface while wet with the solutionusing a A-A-58054, Type I, Grade C abrasive mat.
d. If the solution turns green, continue to abrade the en-tire area until it is completely cleaned and then wipeall dirty solution from the surface with a sponge, whichshould leave a bright, shiny surface. If dark spots orlines are seen in the area which indicates the presenceof residual spots of moderate to severe corrosion, re-apply the solution and vigorously agitate the wettedarea with an abrasive mat as before. If the corrosion is
not completely removed after this second applicationof solution, remove the remaining corrosion using anappropriate mechanical method in this chapter. Aftercorrosion removal is complete and the dirty solution isremoved, reapply MIL-DTL-81706, Class 1A to forma MIL-DTL-5541, Class 1A film on the surface andallow the film to form in accordance with proceduresin Section II of this chapter for application of chemicalchromate conversion coatings to aluminum alloy sur-faces.
5.9.1.3 Application of Organic Coatings. Reapply theorganic coating system specified in the appropriate systemspecific maintenance manual and/or engineering drawing forthe aircraft, missile, or piece of equipment and TO 35-1-3for support equipment (SE) using TO 1-1-8 for applicationprocedures. Apply a MIL-DTL-5541, Class 1A chemicalchromate conversion coating using materials conforming toMIL-DTL-81706, Class 1A, if not already done, per SectionII of this chapter and paint within 48 hours after applicationof the conversion coating. Reapply the conversion coating inaccordance with Section II of this chapter if more than 48hours have elapsed since application of a conversion coating.
5.9.2 Magnesium Alloys. These paragraphs outlinechemical corrosion removal procedures for the removal ofcorrosion from magnesium alloy parts and assemblies of air-craft, missiles, or other equipment. Table 5-6 provides pro-cedures for the removal of specific types of corrosion. Re-movable parts can be treated more effectively by applyingone of the electrodeposition conversion coatings, such asType IV or VII, of SAE AMS-M-3171 (MIL-M-3171) aftercorrosion removal instead of the brush on Type VI coatingspecified for coating repair after corrosion removal fromsmall areas discussed here.
5.9.2.1 Preparation. Before starting chemical removal ofcorrosion products, remove paint from the area per TO 1-1-8and clean all grease, oil, and other contamination from sur-faces to be worked in accordance with Chapter 3 if immer-sion, spray, or vapor blast cleaning is not practical. If prac-tical, use one of the procedures for cleaning magnesiumalloys by immersion, spray, or vapor blast included in SAEAMS-M-3171 (MIL-M-3171).
5.9.2.2 Chemical Corrosion Removal Materials forMagnesium Alloys. Chromic acid pickle solution which is amixture of A-A-55827 chromic acid in water may be used toremove surface oxidation and light corrosion from magne-sium alloy surfaces. It is not adequate for removal of deeppitting, heavy corrosion, sand or other blast media residue,or the effects of blasting which will require use of one of themechanical methods described in this chapter. If properlyused, this chemical method removes much less metal caus-ing much less reduction of sectional thickness than mechani-cal methods, but it shall not be used on parts containingcopper or steel inserts unless they are completely maskedoff. Do not allow excessive amounts of anions such as chlo-rides, sulfates, or fluorides to build up in the solution, they
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tend to coat or etch the metal surface rather than removingcorrosion products. Do not reuse old solutions, prepare freshsolutions for each separate removal operation.
5.9.2.2.1 Application and Use.
• Do not allow rags, brushes, abrasive mats, orany other item soaked with A-A-55827 chro-mic acid or the chromic acid pickle solutionprepared with it to come in contact with anyorganic solvent (MEK, acetone, paint thinner,A-A-59601/MIL-PRF-680 dry cleaning solvent,etc.,) or fire will result.
• A-A-55827 chromic acid and the chromic acidpickle solution prepared with it are highly toxicto the skin, eyes, and respiratory tract. Chemi-cal splash proof goggles and/or face shield,chemical resistant rubber gloves and apron arerequired. Good general ventilation is usuallyadequate. In case of eye or skin contact, flushwith water immediately and report to the basemedical facility.
The procedure for application and use of chrome pickle so-lution, a mixture of A-A-55827 chromic acid in water, is asfollows:
a. Mix 24 ounces of A-A-55827 chromium trioxide inenough water to make one gallon for each gallon ofsolution being prepared in a container fabricated fromlead lined steel (any alloy), stainless steel (any CRESalloy), or 1100 aluminum alloy. For depot level opera-tions only, a removable part that is being treated canbe completely immersed in the solution with an im-mersion time ranging from 1 to 15 minutes at an oper-ating temperature ranging from 190° to 202° F (88° to94° C). For hand application with the solution at roomtemperature, the dwell time for the solution on the sur-face is 15 minutes minimum to 30 minutes maximum.Step b through step d are for hand application. Step ethrough step g apply to both the immersion and handapplication methods.
b. Mask off the surrounding areas, in particular to includeall nearby operating mechanisms, joints, crevices, cop-per and/or steel inserts, and plated steel to keep thesolution from attacking them.
c. Apply the chromic acid pickle solution carefully to thecorroded area with an A-A-289 acid brush.
d. Allow the solution to remain on the surface for ap-proximately 15 minutes for a solution at room tem-perature. Agitate the area with an A-A-289 acid brushhaving half the bristle length cut off or an A-A-58054,Type I, Grade B or C abrasive mat.
e. Thoroughly rinse the solution from the surface withplenty of fresh tap water.
f. Repeat the preceding sequence, as necessary, until allcorrosion products have been removed and the metal isa bright metallic color.
g. Apply a SAE AMS-M-3171 (MIL-M-3171), Type VIchromic acid brush-on pretreatment coating to the areafrom which corrosion was removed in accordance withprocedures in Section II of this chapter for applicationof a brush-on chromic acid pretreatment coating tomagnesium alloy surfaces. If desired, parts that weretreated by complete immersion may receive one of theother coatings listed in SAE AMS-M-3171 (MIL-M-3171) for depot level operations.
5.9.2.3 Application of Organic Coatings. Reapply theorganic coating system specified in the appropriate systemspecific maintenance manual and/or engineering drawing forthe aircraft, missile, or piece of equipment and TO 35-1-3for support equipment (SE) using TO 1-1-8 for applicationprocedures. Apply the paint within 48 hours after applicationof the pretreatment coating. Reapply the pretreatment coat-ing in accordance with Section II of this chapter if more than48 hours have elapsed since application of the pretreatmentcoating.
5.9.3 Ferrous Metal (Steel) Alloys Other Than Stain-less Steels (CRES). These paragraphs outline chemicalcorrosion removal procedures for treating ferrous metal alloyparts and assemblies of aircraft, missiles, and other equip-ment. Use of chemical corrosion removers on steels is rec-ommended only for areas where there is no danger of entrap-ping the chemicals in crevices and/or recesses. Table 5-7provides procedures for the removal of specific types of cor-rosion.
5.9.3.1 Preparation. Before starting chemical removal ofcorrosion products, remove paint from the area per TO 1-1-8and clean all heavy deposits of grease, oil, and other con-taminants from the surfaces to be worked in accordance withChapter 3.
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Table 5-6. Typical Chemical Corrosion Removal Procedures for Magnesium Alloys
Type of Corrosion Step 1Corrosion Removal
Step 2Surface Treatment
Step 3Protective Finish
Light pitting or sur-face oxidation/etching
Remove corrosion withchromic acid pickle solu-tion per Paragraph5.9.2.2.
SAE AMS-M-3171 (MIL-M-3171),Type VI per Section II of thischapter
Approved paint systemper Paragraph 5.9.2.3
Heavy pitting oretching
Not applicable. Removecorrosion by an appropri-ate mechanical method inthis chapter.
As above As above
Intergranular orexfoliation
Not applicable. Removecorrosion by an appropri-ate mechanical method inthis chapter.
As above As above
Light or heavy cor-rosion on smallparts which canbe removed fortreatment
Remove corrosion in accor-dance with SAE AMS-M-3171 (MIL-M-3171).
As above As above
Stress corrosioncracking
Not applicable. Replace orrepair, as required, in thesystem specific structuralhandbook.
Not applicable Not applicable
5.9.3.2 Chemical Corrosion Removing Materials forFerrous Metal Alloys Other Than Stainless Steels(CRES). Chemical corrosion/rust removers for steels are oftwo types; the MIL-C-10578 acid type and the A-A-59260(MIL-C-14460) alkaline type.
5.9.3.2.1 MIL-C-10578 Corrosion Removing and MetalConditioning Compound (Phosphoric Acid Base). MIL-C-10578 covers six separate types of phosphoric acid basedcorrosion/rust removing compounds used to remove corro-sion/rust from ferrous metal surfaces. The following typesare available:
5.9.3.2.1.1 Type I (Wash-Off) and II (Wipe-Off). Type Iand II materials are suitable as rust removers for ferrousalloy metal parts. They may also be used as metal condition-ers for ferrous and nonferrous (zinc galvanized, cadmium,brass, and relatively pure aluminum or alclad) metals priorto the primer and paint application and/or as a corrosionpreventive to provide minor corrosion protection to thesemetals in an unpainted condition. Remove very heavy rustincrustations using an appropriate mechanical method listedin this chapter and heavy grease, oil, and other contamina-tion per Chapter 3 as directed by Paragraph 5.9.3.1 beforeapplication of these materials. Type I is a little more efficientin removing rust and grease than Type II. Type I materialsare applied by either spray, dip, flow-on, brush, rag, orsponge and are always rinsed off with water, preferably hot.Type II materials are applied by either brush, rag, or sponge
and do not have to be rinsed off with water, but are wiped offwith clean, damp rags followed by wiping with clean, dryrags prior to painting. Type II materials leave a light, gray-white coating/film on the surface that acts as a pretreatmentfor painting.
5.9.3.2.1.2 Type III (Inhibited). Type III materials are in-tended for corrosion/rust removal from chromium plated fer-rous alloy surfaces and those bare ferrous alloy surfaces re-quiring very close dimensional tolerances. Remove veryheavy rust incrustations by an appropriate mechanical methodin this chapter and heavy grease, oil, and contamination perChapter 3 as directed by Paragraph 5.9.3.1 or by vapordegreasing before application of these materials. Type IIImaterials are applied by either spray, dip, flow-on, brush orby full immersion in a tank containing the material. Parts areleft in the solution tank or the solution is left on the surfaceof the part until the rust is dissolved or loosened sufficientlyto permit easy removal, and then the residue is rinsed off thesurface with fresh, tap water, preferably hot, and the part isdried. It is then ready for application of the required corro-sion preventive treatment or paint system application.
5.9.3.2.1.3 Type IV (Non-Foaming). Type IV materialsare very similar to Type I, except that non-foaming deter-gents are included in the mixture. It is intended for use inpressurized spray systems at temperatures up to 150° F (66°C) maximum, after which it is rinsed off with fresh, tap wa-ter.
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5.9.3.2.1.4 Type V (Immersion Tank). Type V materialsare also very similar to Type I, except no grease removingsolvents are used in these materials, so they are only suitablefor use on surfaces from which all grease, oil, and contami-nation have been completely removed by cleaning per Chap-ter 3 as directed by Paragraph 5.9.3.1. It is intended for usein immersion tanks either at ambient (room) temperatures orat temperatures up to 140° F (60° C) maximum.
5.9.3.2.1.5 Type VI (Brush, Spray, or Dip). Type VI ma-terials are surface pretreatments and/or rust converters forapplication on either newly sand blasted or corroded/rustysteel surfaces by spray, brush, or dipping. All old grease, oil,and dirt must be removed as well as all loose and scaly rustbefore applying these materials. After application, they areallowed to dwell on the surface for a minimum of 6 hours toform a pretreatment coating on uncorroded ferrous alloys orto convert the rust on a corroded ferrous surface to a protec-tive, pretreatment film. After a dwell time of 6 hours, theexcess materials are rinsed off, the surface is allowed to airdry, and then the surface can be primed and painted or treatedwith a CPC.
5.9.3.2.2 Application and Use of MIL-C-10578 Corro-sion Removing Compounds.
• Phosphoric acid corrosion removal compoundsare toxic to the skin, eyes, and respiratory tract.Chemical splash proof goggles and rubbergloves and aprons are required. Use only in awell ventilated area. In case of eye or skin con-tact, flush immediately with water and report tothe Base Medical Facility.
• When mixing, always add the phosphoric acidcorrosion remover to the water. Do not add thewater to the acid, since this causes excessiveheat to be generated.
• High strength steel parts, those heat-treatedabove Rockwell C40 (180,000 PSI) tensilestrength, are subject to hydrogen embrittlementwhen exposed to acids, therefore, use of acidrust/corrosion removers on these parts is pro-hibited.
• Do not use acidic rust/corrosion removers ifthere is a danger of entrapping the materials increvices or recesses, as they can cause corro-sion in these areas.
5.9.3.2.2.1 Application and Use of Type I (Wash-Off).The directions for application and use of these materials areas follows:
a. Add one part of the concentrated material as receivedto three parts of water by volume. Use either a stain-less steel, aluminum, vinyl, polyethylene, or rubbermixing container.
b. Remove heavy grease, oil, and contamination perChapter 3 and heavy rust using an appropriate me-chanical method in this chapter before applying thechemical removal compound.
c. Protect adjacent components by masking to preventdamage by scale, chips, corrosion products, or chemi-cals.
d. Apply the solution to the surfaces to be treated by ei-ther non-atomized spray, dip, flow-on, or brush. Allowthe material to remain only long enough to wet thesurface and cause etching. On rusted surfaces, allowthe solution to dwell on the surface long enough toloosen the rust (2 to 10 minutes, depending on thedegree of rusting) while agitating the surface with anA-A-58054, Type I, Grade C abrasive mat or a handheld stainless steel (CRES) brush.
e. Rinse the surface with fresh tap water, preferably hot(120° -140° F/49° -60° C). Allow the surface to drythoroughly prior to application of a rust/CPC or a re-quired paint system.
5.9.3.2.2.2 Application and Use of Type II (Wipe-Off).The directions for application and use of these materials areas follows:
a. Add one part of the concentrated material as receivedto three parts of water by volume. Use the same typeof mixing containers specified in Paragraph 5.9.2.2.1,step a.
b. Remove heavy grease, oil, and contamination perChapter 3 and heavy rust using an appropriate me-chanical method in this chapter before applying thechemical removal compound.
c. Protect adjacent components by masking to preventdamage by scale, chips, corrosion products, or chemi-cals.
d. Apply the solution to the surfaces to be treated by ei-ther brush, rag, or sponge. Allow the compound todwell on the surface for about 30 seconds.
e. Wipe off residue first with damp rags followed withdry rags leaving no more than a light gray-white coat-ing film on the surface. Allow the surface to dry thor-oughly prior to applying the required paint system.
5.9.3.2.2.3 Application and Use of Type III (Inhibited).The directions for application and use of these materials areas follows:
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a. Follow these procedures for non-atomized spray, flow-on, and brush applied operations with Type III materi-als.
(1) Add one part of the concentrated material, as re-ceived, to one part of water by volume. Use thesame type of mixing containers specified in Para-graph 5.9.2.2.1, step a.
(2) Remove grease, oil, and contamination per Chap-ter 3 and heavy rust using an appropriate me-chanical method in this chapter prior to applyingthe chemical removal compound.
(3) Protect adjacent components by masking to pre-vent damage by scale, chips, corrosion products,or chemicals.
(4) Apply the solution to the surfaces to be treated bynon-atomized spray, flow-on, or brush. Allow theconditioner to dwell on the surfaces long enoughto loosen and/or dissolve the rust, and then rinseoff all residue with fresh, hot, tap water (120°-140° F/49° -60° C).
(5) Allow the surface to thoroughly dry, and then ei-ther apply a CPC or a required paint system, orplace the part directly into service, whichever isdirected by the system specific maintenance tech-nical data for the equipment involved.
Heated dip tanks shall be properly ventilated andventilation shall be evaluated by the Bioenviron-mental Engineer prior to initial use.
b. Follow these procedures for dip tank operations withType III materials.
(1) Stainless steel (CRES) tanks are preferred for usewith this method. Mix the material, as specified,for non-atomized spray, flow-on, and brush appli-cations, but mix it in the stainless steel (CRES)dip tank.
(2) Immerse the part in the solution only long enoughto loosen the rust. For heavy rust removal, thesolution can be heated to 140° F (60° C) maxi-mum.
(3) Agitate the part in the solution to increase therust removal rate. Rinse in a continuously over-flowing fresh, cold, tap water rinse tank, if avail-able, or spray with fresh, hot, tap water (120°
-140° F/49° -60° C). Thoroughly dry the partsand immediately apply the required paint systemor CPC or place the part directly into service,whichever is directed by the system specific main-tenance technical data for the equipment involved.
5.9.3.2.2.4 Application and Use of Type IV (Non-Foaming). The directions for application and use of thesematerials are as follows:
a. Add one part of the concentrated material as receivedto three parts of water by volume. Use the same typeof mixing containers as specified in Paragraph5.9.3.2.2.1, step a.
b. Remove all heavy grease, oil, and contamination perChapter 3 and heavy rust using an appropriate me-chanical method in this chapter prior to applying thechemical removal compound.
c. Apply the solution to the surface being treated by non-atomized, pressurized spray. To increase the rust re-moval rate, the solution may be heated up to a tem-perature of 150° F (66° C).
d. Rinse with fresh, tap water, preferably hot (120° -140°F/49° -60° C).
e. Allow the part to thoroughly dry prior to application ofa rust/CPC or a required paint system.
5.9.3.2.2.5 Application and Use of Type V (ImmersionTank). The directions for application and use of these mate-rials are as follows:
a. Add one part of the concentrated material as receivedto three parts of water by volume. Use the same typeof mixing containers as specified in Paragraph5.9.3.2.2.1, step a and pour the solution into a stainlesssteel (CRES) immersion tank or mix the solution di-rectly in the immersion tank.
b. This material contains no solvents to assist in cleaning,so all heavy grease, oil, and contamination must bethoroughly removed per Chapter 3 or immersion in analkali bath prior to immersing a part in the corrosionremoval solution. Remove heavy rust with an appro-priate mechanical method in this chapter also prior toimmersion of the part in the chemical removal com-pound.
c. Submerge the part being treated in the chemical re-moval compound just long enough to loosen the rust.For heavy rust removal, the solution can be heated to atemperature of 140° F (60° C).
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d. After immersion, rinse all metal surfaces thoroughlywith fresh, tap water, or immerse the part in an alkalisolution followed by rinsing with fresh, tap water.
e. Allow the part to thoroughly dry prior to applying aCPC or a required paint system.
5.9.3.2.2.6 Application and Use of Type VI (Brush,Spray, or Dip). The directions for application and use ofthese materials are as follows:
a. Add one part of the concentrated material as receivedto three parts of water by volume. Use the same typeof mixing containers specified in Paragraph 5.9.2.2.1,step a. This material is also available mixed in a pentype applicator for direct application to the surface.
b. Remove all heavy grease, oil, and contamination perChapter 3 and heavy rust using an appropriate me-chanical method in this chapter prior to applying thechemical removal compound.
c. Apply the solution to the surface being treated bybrush, any sprayer that will accommodate acid solu-tions, dipping the part in the solution, or with the penapplicator.
d. Allow the material to dwell on the surface and reactwith the metal and convert the rust to a protective filmfor 6-24 hours for brush and spray applications. Fordip applications, allow the part to remain in the solu-tion for 1-5 hours, and then remove it from the solu-tion, and allow the material to dwell on the part sur-faces for an additional 6-24 hours.
e. After the dwell time is completed, rinse all excess/unreacted material off all part surfaces with fresh, run-ning, tap water for at least 30 seconds.
f. Allow the part to thoroughly dry prior to applying aCPC or a required paint system.
5.9.3.2.3 A-A-59260 (MIL-C-14460, Type I) CorrosionRemoving Compound, Sodium Hydroxide Base; forElectrolytic or Immersion Application. This is a highly al-kaline chemical corrosion/rust removing compound suitablefor rust removal by immersion of the parts in the solution. Itdoesn’t cause dimensional change of critical or machinedsurfaces and it is safe to use on high strength steels as it will
not cause hydrogen embrittlement. It can be used on smallparts with or without paint, grease, or other surface coatings.
5.9.3.2.4 Application and Use of A-A-59260 (MIL-C-14460, Type I) Corrosion Removing Compounds. Thedirections for application and use of these materials are asfollows:
• A-A-59260 (MIL-C-14460, Type 1) corrosion/rust removing compound is a sodium hydrox-ide solution and therefore, highly alkaline. It istoxic to the skin, eyes, and respiratory tract.Chemical splash proof goggles and/or faceshields and chemical resistant rubber glovesand aprons are required. Heated dip tanks shallbe properly ventilated and ventilation shall beevaluated by the Bioenvironmental Engineerprior to their initial use.
• When preparing/mixing this highly alkaline so-lution, never pour water onto the sodium hy-droxide granules or flakes, this will generate anexcessive amount of heat. Always pour the so-dium hydroxide granules/flakes into the water.
a. Prepare/mix this alkaline corrosion/rust remover solu-tion per the manufacturer’s instructions printed on thecontainer to obtain a solution concentration of fivepounds of sodium hydroxide granules or flakes pergallon of water. Use either carbon steel or stainlesssteel (CRES) tanks to contain the solution.
b. Immerse the parts in the corrosion/rust remover solu-tion. Rust removal time varies with the extent of therust. At room temperature, rust removal is very slow,and a long soak time is required. This solution is mosteffective if the temperatures of the solution is broughtup to the point of a rolling boil which increases therate of the corrosion/rust removal significantly.
c. Rinse the parts thoroughly in fresh, tap water (prefer-ably hot -120° -140° F/49° -60° C).
d. Dry the parts thoroughly and immediately apply a CPCor a required paint system.
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Table 5-7. Typical Chemical Corrosion Removal Procedures for Ferrous Metals Other Than Stain-less Steel (CRES)
Type of Corrosion Corrosion RemovalLight or heavy rust on installed parts where
chemical rust removal is practical.Remove very heavy corrosion by wire brushing, sanding, or
other appropriate mechanical method in this chapter fol-lowed by phosphoric acid etch with MIL-C-10578, Type I,II, IV, or VI materials. (Refer to Paragraph 5.9.3.2.2.1, Para-graph 5.9.3.2.2.2, Paragraph 5.9.3.2.2.4, and Paragraph5.9.3.2.2.6). Do not use phosphoric acid etch on highstrength steel.
Light or heavy rust on small parts where vattreatment is practical.
Acid Method: Remove corrosion by immersing parts in MIL-C-10578, Type III, V, or VI phosphoric acid solution. (Referto Paragraph 5.9.3.2.2.3, Paragraph 5.9.3.2.2.5, and Para-graph 5.9.3.2.2.6). Do not use phosphoric acid on highstrength steel.
Alkaline Method: (Recommended for critical or mechanicalsurfaces). Remove corrosion by immersing parts in A-A-59260 (MIL-C-14460, Type I) alkaline solution. (Refer toParagraph 5.9.3.2.4).
5.9.3.3 Application of Organic Coatings. Reapply theorganic coating system specified in the appropriate systemspecific maintenance manual and/or engineering drawing forthe aircraft, missile, or piece of equipment and TO 35-1-3for support equipment (SE) using TO 1-1-8 for applicationprocedures. Apply the paint system, when required, within 4hours after completion of the corrosion removal procedure toprevent surface rusting from occurring. As a minimum, aprimer should be applied within this time frame.
5.9.4 Stainless Steel (CRES) and Nickel Based Alloys.These paragraphs outline chemical corrosion removal proce-dures for stainless steel (CRES) and nickel based alloy partsand assemblies. Table 5-8 provides procedures for removingspecific types of corrosion. Chemical corrosion removal isrecommended for severely corroded areas only when there isno danger of entrapping chemicals in recesses, cavities, or
joint areas or damaging surrounding metals and plating. Usethese chemical procedures on installed components whichare not readily removable. When internal corrosion is evi-dent, affected components shall be removed and processedthrough an overhaul facility in accordance with system spe-cific maintenance manuals for the specific aircraft, missile,or piece of equipment.
5.9.4.1 Preparation. If the corroded area is contaminatedwith grease, oil, dirt, or any other foreign material, clean thearea per Chapter 3.
a. Protect adjacent unaffected areas not being treated bymasking to prevent damaging them with the chemicalsused.
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• A-A-59601, MIL-PRF-32295, Type II andMIL-PRF-680, dry cleaning and degreasing sol-vents are toxic to the skin, eyes, and respiratorytract. Skin and eye protection are required.Avoid repeated or prolonged skin contact or in-halation. Good general ventilation is normallyadequate.
• When using metallic wools, wear leather glovesand exercise care to prevent injury to hands andfingers.
• Take care to prevent solvents from splashing orrunning because they can damage paints andelastomers (e.g., rubbers, plastics).
• Take care to protect surrounding unaffected ar-eas next to the area being treated by preventingleakage of chemicals into recesses or inacces-sible areas in the structure which can cause ad-ditional damage from corrosion attack.
b. Remove all loose corrosion by abrading the surfacewith either A-A-1043, Type IV, Class 1 stainless steelwool, 240 grit ANSI B74.18 (A-A-1047) silicon car-bide abrasive paper or ANSI B74.18 (A-A-1200) sili-con carbide abrasive cloth, 240 grit ANSI B74.18 (A-A-1048) aluminum oxide abrasive paper or cloth, orA-A-58054, Type I, Grade C abrasive mat. Remove allloose particles by wiping the surface with a clean clothdampened with A-A-59601, MIL-PRF-32295, Type IIor MIL-PRF-680, dry cleaning and degreasing solvent.
5.9.4.2 Chemical Corrosion Removing Materials forStainless Steel (CRES) and Nickel Based Alloys. Thereare three types of chemicals used for corrosion removal fromstainless steels (CRES) and nickel based alloys, Semco® PNPasa-Jell 101 mineral acid, gel type material, MIL-C-10578,Type III inhibited phosphoric acid based solution, and acidpickling solutions consisting of a mixture of A-A-59105 (O-N-350) nitric acid, MIL-A-24641 hydrofluoric acid, and wa-ter.
5.9.4.2.1 Semco® PN Pasa-Jell 101. This is a mineralacid, gel type material used for chemical corrosion removalfrom assembled aircraft, missile, and equipment structures inareas involving LOX storage and gaseous oxygen transfersystems and other areas where a gel type material is neces-sary and/or preferred.
5.9.4.2.1.1 Application and Use of Semco® PN Pasa-Jell 101.
• Do not use aluminum or steel wool to agitateSemco® PN Pasa-Jell 101, as a combustiblereaction will occur.
• Semco® PN Pasa-Jell 101 contains strong ac-ids and is toxic to the skin, eyes, and respira-tory tract. Chemical splash proof goggles and/orface shield and chemical resistant rubber glovesand aprons are required. Avoid inhaling fumesand use only in a well ventilated area.
The directions for the application and use of this material areas follows:
a. Prepare the area per the procedures outlined in Para-graph 5.9.4.1.
b. Apply the Semco® PN Pasa-Jell 101 material to thearea being worked with an acid brush and in accor-dance with the manufacturer’s instructions.
c. To remove light to medium corrosion, agitate the areawith an acid brush having half the bristle length cutoff, if necessary. To remove heavy corrosion where pit-ting is present, agitate the area with an A-A-58054,Type I, Grade C abrasive mat until all corrosion em-bedded in pits and on the surface is removed. Allowthe material to dwell on the surface only long enoughto loosen and/or dislodge all the corrosion products.
d. Remove the Semco® PN Pasa-Jell 101 material andcorrosion products from the surface with a clean, lintfree cloth frequently rinsed in fresh tap water.
e. For a final wipe, use a clean, lint free dry cloth. Afterdrying, either apply a CPC or a required paint system,or place the part directly into service, whatever is di-rected by the system specific maintenance technicaldata for the equipment involved. Usually, stainless steel(CRES) and nickel based alloy parts do not requirepainting.
5.9.4.2.2 MIL-C-10578, Type III Corrosion Removingand Metal Conditioning Compound (Phosphoric AcidBase)/Inhibited. This is a phosphoric acid based materialthat can be used to remove corrosion from assembled air-craft, missile, and equipment structures in areas that do notcontain oxygen systems and where a liquid material is ac-ceptable.
5.9.4.2.2.1 Application and Use of MIL-C-10578, TypeIII. The directions for the application and use of this materialare as follows:
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Change 5 5-27
a. Prepare the area per the procedures outlined in Para-graph 5.9.4.1.
b. Protect adjacent components by masking to preventdamage by scale, chips, corrosion products, or chemi-cals.
c. Add one part of the concentrated material, as received,to one part of water by volume. Use either a stainlesssteel, aluminum, vinyl, polyethylene, or rubber mixingcontainer.
d. Apply the solution to the surfaces to be treated by non-atomized spray, flow-on, or brush. Allow the condi-tioner to dwell on the surfaces long enough to loosenand/or dissolve the corrosion/rust, and then rinse off allresidue with fresh, hot tap water (120° -140° F/49°-60° C).
e. Allow the surface to thoroughly dry and then eitherapply a CPC or a required paint system, or place thepart directly into service, whatever is directed by thesystem specific maintenance technical data for theequipment involved. Usually, stainless steel (CRES)and nickel based alloy parts do not require painting.
5.9.4.2.3 Acid Pickling for Corrosion Removal. (FORDEPOT AND OTHER AUTHORIZED FACILITY USEONLY). Acid pickling solutions consisting of a mixture ofA-A-59105 (O-N-350) nitric acid, MIL-A-24641 hydroflu-oric acid, and water are used to remove corrosion/rust fromremoved stainless steel (CRES) and nickel based alloy partsthat can be immersed in the solution.
Table 5-8. Typical Chemical Corrosion Removal Procedures for Stainless Steel (CRES) and Nickel Based Al-loys
Type of CorrosionStep 1
Corrosion RemovalStep 2
Surface TreatmentStep 3
Protective FinishLight to heavy corro-
sion/rust to includepitting on installedparts where liquidchemical corrosion/rust removal isimpractical becauseof location involv-ing LOX storageor gaseous oxygentransfer equipment,complexity of thestructure, or rins-ing difficulties.
Remove very heavy corrosion/rust first with stainless steelwool or wire brush, rotary file,or other mechanical means inthis chapter followed by appli-cation of Semco® PN Pasa-Jell101. (Refer to Paragraph5.9.4.2.1.1).
None Normally not required (referto Paragraph 5.9.4.3), fordiscussion of paint systems.
As above, when liq-uid chemical corro-sion/rust removalis practical.
Remove very heavy corrosion/rust as above first, followed byapplication of MIL-C-10578,Type III solution. (Refer toParagraph 5.9.4.2.2.1).
None As Above
Light to heavy corro-sion to includepitting on partswhich can be re-moved for process-ing.
Remove very heavy corrosion/rust as above first followed byimmersion in the nitric-hydro-fluoric-acid pickling solution.(Refer to Paragraph5.9.4.2.3.1).
Passivate in accor-dance withAMS2700, Type II,VI, VII, or VIII asapplicable to thetype of stainlesssteel (CRES) alloybeing treated.
As Above
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5-28 Change 3
5.9.4.2.3.1 Pickling Solution Concentration.
Scale loosening, pickling, and passivating solu-tions are all strong acids which are toxic to theskin, eyes, and respiratory tract. Chemical splashproof goggles and/or face shield and chemical re-sistant rubber gloves and aprons are required. Incase of eye or skin contact, flush immediately withwater and report to the Base Medical Facility.Avoid inhaling fumes and provide adequate venti-lation. Solution tanks shall be properly ventilatedwith a lateral exhaust type ventilation system. Theventilation system and procedure shall be properlyevaluated by the Bioenvironmental Engineer priorto initial use.
• Heat-treatable stainless steel alloys, such asAISI types 403, 410, 420, and others, are sus-ceptible to cracking when placed in picklingsolutions. Use only mechanical methods to re-move corrosion from these alloys.
• When preparing pickling solutions, never pourwater into the acids as excessive heat will begenerated. Always pour the acids into the wa-ter.
• Rubber lined or Koroseal tanks shall be used tohold these solutions because they are so highlyacidic.
Pickling solutions are prepared by mixing various amountsof A-A-59105 (O-N-350) nitric acid and MIL-A-24641 hy-drofluoric acid in water with the correct content of the twoacids for a given corrosion removal job being determined bythe testing procedure outlined below. The nitric acid contentmay vary from 5 to 50% by volume, while the hydrofluoricacid content may vary from 0.5 to 5% by volume. A solutionof 12 to 15% nitric acid by volume and 1% hydrofluoric acidby volume in water is normally used to remove light scaleand/or corrosion/rust. Increase the percentage of hydroflu-oric acid within the range specified above to remove heavierscale and/or corrosion/rust. As the amount of nitric acid in-creases with respect to the amount of hydrofluoric acid in thesolution, the rate of corrosion/rust and/or scale removal de-creases, because nitric acid inhibits the action of hydroflu-oric acid.
5.9.4.2.3.2 Pickling Solution Temperature. The tem-perature of the pickling solution may be adjusted from am-bient (room) temperature up to a maximum of 140º F (60ºC). Higher temperatures shall be avoided to reduce evapora-
tion loss of hydrofluoric acid. Use temperatures below 120ºF (49º C) if intergranular attack is experienced in localizedareas, such as weld zones.
NOTE
AISI 300-Series stainless steel (CRES) alloy tub-ing may be used to manufacture steam coils toheat the solution. The heating coils should be in-stalled so that they are easily replaced, since theywill be corroded by the solution over time.
5.9.4.2.3.3 Testing for Optimum Pickling Conditions.Optimum pickling conditions (temperature, time, and acidconcentration), shall be determined by exposing test panelsto various combinations of these parameters and processingthem through the entire cleaning and corrosion removal/pickling cycle. Excessive etching and/or intergranular attackof the base metal indicates conditions are too aggressive andslow removal rates indicate conditions are not aggressiveenough.
a. Make four inch square test panels from the same ma-terial from which the parts that will be treated aremade. Process these test panels through the completecleaning and corrosion removal/pickling cycle.
b. If etching or intergranular attack is excessive (i.e.,would cause the component to be condemned), or ifcorrosion removal is not complete, adjust the acid con-centration, immersion time, and/or solution tempera-ture until the desired result is obtained. Table 5-9 showsthe effect that varying the parameters of acid concen-tration, immersion time, and/or solution temperaturehas on the corrosion removal/pickling action of the so-lution.
5.9.4.2.3.4 Application and Use of Acid Pickling Solu-tions for Corrosion Removal. The directions for the appli-cation and use of nitric-acid-hydrofluoric acid solutions forcorrosion removal are as follows:
a. Clean parts to be treated per procedures in Chapter 3.
b. If severe scale is present, remove it by one of the fol-lowing methods:
(1) Remove scale using an appropriate mechanicalmethod in this chapter.
(2) Remove scale using this chemical method.
(a) Immerse parts in a solution of 8 to 10% byweight A-A-55828 (O-S-809) sulfuric acidand water at a temperature of 150° to 160° F(66° to 71° C) for about 5 minutes. If re-quired, scrub the surface of the parts with a
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stainless steel (CRES) wire brush to removeany sludge formed in the area having severescale.
(b) Repeat the above process, if required, andthen quickly rinse the parts thoroughly infresh, hot tap water at a temperature of 120°to 130° F (49° to 54° C).
c. Prepare the pickling solution by mixing the properproportions of A-A-59105 (O-N-350) nitric acid andMIL-A-24641 hydrofluoric acid in fresh tap water. Asa starting point, a typical pickling solution consists of15% nitric acid by volume and 2 to 3% hydrofluoricacid by volume in water. Make adjustments as deter-mined by results of the testing in Paragraph 5.9.4.2.3.3.
d. Immerse parts in the typical pickling solution at a tem-perature of 60° to 140° F (16° to 60° C) for a period of5 to 15 minutes. Make adjustments to the solution tem-perature and immersion time as determined by the re-sults of the testing in Paragraph 5.9.4.2.3.3. If required,scrub the surface of the parts with a stainless steel(CRES) wire brush to loosen and remove all corrosionproducts.
NOTE
• Ensure that the parts are completely immersedin these solutions to prevent corrosive attack ofthe part at the liquid level line.
• New welds should be mechanically vibrated oragitated during the pickling operation.
e. Immediately after removing the parts from the picklingsolution, thoroughly rinse the parts with fresh, hot tapwater at a temperature of 120° to 130° F (49° to 54°C).
5.9.4.3 Passivation of Stainless Steel (CRES) AlloyParts. After corrosion removal is completed on removedstainless steel (CRES) parts, passivate the surfaces of theseparts as follows:
a. Prepare a passivating solution in accordance withAMS2700 either Type II, VI, VII, or VIII as applicableto the stainless steel (CRES) alloy of the part to bepassivated.
Table 5-9. Control of Corrosion Removal/Pickling Action of Nitric-Acid-Hydrofluoric Solutions
Action is More Aggressive Action is Less Aggressive1. When the nitric acid content is decreased and/or the
hydrofluoric acid content is increased.1. When the nitric acid content is increased and/or the hydroflu-
oric acid content is decreased.2. When the temperature is increased. 2. When the temperature is decreased.3. When immersion time is increased. 3. When immersion time is decreased.
b. Immerse the part in the passivating solution held withinthe temperature range and for the time interval speci-fied in AMS2700.
c. Remove the parts from the passivating solution andthoroughly rinse with fresh, hot tap water at a tempera-ture of 120° to 130° F (49° to 54° C). As required byAMS2700, immerse all ferritic and/or martensitic stain-less steel (CRES) alloy parts in a 4 to 6% by weightsolution of A-A-59123 (O-S-595) sodium dichromatein water at a temperature of 140° to 160° F (60° to 71°C) for 30 minutes.
d. Remove the parts from the sodium dichromate solu-tion. Rinse thoroughly with fresh tap water and dry.Place the parts directly in service or in the supply sys-tem unless painting is required by system specifictechnical data.
5.9.4.4 Application of Organic Coatings. Stainless steels(CRES) and nickel based alloys are normally not painted.However, where extreme corrosive conditions are encoun-tered, where organic finishes are required for decorative pur-poses, or where the stainless steel (CRES) or nickel based
alloy is in contact with a dissimilar anodic metal, paintingmay be required. Reapply the organic coating system speci-fied in the appropriate system specific maintenance manualand/or engineering drawing for the aircraft, missile, or pieceof equipment and TO 35-1-3 for support equipment (SE)using TO 1-1-8 for application procedures.
5.9.5 Copper and Copper Based Alloys. These para-graphs outline chemical corrosion removal procedures forcopper and copper based alloy parts and assemblies of air-craft, missiles, and equipment. Table 5-10 provides proce-dures for removing specific types of corrosion.
5.9.5.1 Preparation. If the corroded area is contaminatedwith grease, oil, dirt, or other foreign materials, clean thearea per Chapter 3. Protect adjacent components and areasnot being treated by masking to prevent damaging them withthe chemicals used.
5.9.5.2 Chemical Corrosion Removing Materials forCopper and Copper Based Alloys. There are two types ofchemical solutions used for corrosion removal from copperand copper based alloys provided there is no danger ofchemical entrapment in crevices and/or recesses: MIL-C-
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5-30 Change 3
10578, Type III Corrosion Removing and Metal Condition-ing Compound (Phosphoric Acid Base)/Inhibited solutionand A-A-55828 (O-S-809) Sulfuric Acid solution.
5.9.5.2.1 MIL-C-10578, Type III Corrosion Removingand Metal Conditioning Compound (Phosphoric AcidBase)/Inhibited. This is a phosphoric acid based materialused to remove corrosion from assembled copper and/orcopper alloy aircraft, missile, and equipment structures inareas that do not contain oxygen systems and where a liquidmaterial is acceptable.
5.9.5.2.1.1 Application and Use of MIL-C-10578, TypeIII Solutions. The directions for the application and use ofthis material are as follows:
a. Prepare the area per the procedures outlined in Para-graph 5.9.5.1.
b. Add one part of the concentrated material, as received,to one part of water by volume. Use either a stainlesssteel, aluminum, vinyl, polyethylene, or rubber mixingcontainer.
c. Apply the solution to the surfaces to be treated by non-atomized spray, flow-on, or brush. Allow the condi-tioner to dwell on the surfaces long enough to loosenand/or dissolve the corrosion and then rinse off allresidue with fresh, hot tap water (120° -140° F/49°-60° C).
d. Allow the surface to thoroughly dry, and then eitherapply a CPC or a required paint system, or place thepart directly into service, whatever is directed by thesystem specific maintenance technical data for theequipment involved.
5.9.5.2.2 A-A-55828 (O-S-809) Sulfuric Acid Solu-tions. Sulfuric acid solutions may be used to remove corro-sion from copper and/or copper alloy components which canbe disassembled and treated in immersion tanks. The tanksmust be either manufactured from or lined with either stain-less steel (CRES), lead, ceramic, glass, or acid resistant rub-ber and they must be provided with an adequate lateral ex-haust ventilation system. Part holding racks must bemanufactured from either stainless steel (CRES) or Monel.The proper conditions (i.e., time, temperature, and acid con-centration) for the process shall be determined by the sametest procedure outlined in Paragraph 5.9.4.2.3.3, using testpanels made from the same material being treated.
5.9.5.2.2.1 Application and Use of A-A-55828 (O-S-809) Sulfuric Acid Solutions.
Sulfuric acid solutions are toxic to the skin, eyes,and respiratory tract. Chemical, splash proofgoggles and/or face shields and chemical resistantrubber gloves and aprons are required. In case ofeye or skin contact, flush immediately with freshwater and report to the Base Medical Facility.
The directions for the application and use of this material areas follows:
a. Disassemble the components from which corrosionwill be removed to the piece part level, as necessary.
b. Prepare parts per the procedures outlined in Paragraph5.9.5.1.
When preparing sulfuric acid solutions, never pourwater into the acid, as excessive heat will be gen-erated. Always pour the acid into the water.
c. Prepare a 5 to 10% by volume solution of A-A-55828(O-S-809) sulfuric acid in water and maintain the so-lution temperature within a range of 60° to 120° F (16°to 49° C). As required by Paragraph 5.9.5.2.2, deter-mine the actual operating solution concentration andtemperature within the ranges listed above and estab-lish the required part immersion time by testing perParagraph 5.9.4.2.3.3.
Do not process components having assembled dis-similar metal parts or separate parts made fromdifferent metals in a sulfuric acid solution, as cor-rosion problems can result.
d. Immerse parts in the sulfuric acid solution preparedand maintained at the solution concentration and tem-perature per step c, for the immersion time establishedin step c.
e. Remove the parts from the acid solution and immedi-ately rinse them thoroughly with fresh tap water.
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NOTE
Thorough rinsing is important since any residualacid will cause staining of the metal surface.
f. If a red stain appears on the parts following the abovetreatment, remove the stain by immersion of the partsin a solution of 4 to 10% by volume A-A-55828 (O-S-809) sulfuric acid and 4 to 8 ounces per gallon of so-lution of A-A-59123 (O-S-595) sodium dichromate inwater maintained within a temperature range of 60° to120° F (16° to 49° C).
Compressed air used for drying purposes can causeairborne particles that may enter the eyes. Eyeprotection is required. Air pressure shall not ex-ceed 30 PSI.
g. Dry rapidly, preferably with hot air, to prevent waterstains on the surface, and then either apply a CPC or arequired paint system, or place the part directly intoservice, whatever is directed by the system specificmaintenance technical data for the equipment involved.
5.9.5.3 Application of Organic Coatings. Normally cop-per and copper based alloys are not painted. If required, re-apply the organic coating system specified in the system spe-
cific maintenance manual and/or engineering drawing for theaircraft, missile, or piece of equipment and TO 35-1-3 forsupport equipment (SE) using TO 1-1-8 for application pro-cedures.
5.9.6 Titanium and Titanium Based Alloys. These para-graphs outline chemical corrosion removal procedures fortitanium and titanium alloy parts and assemblies. Table 5-11provides procedures for removing specific types of corro-sion.
5.9.6.1 Preparation. If the corroded area is contaminatedwith grease, oil, dirt, or other foreign materials, clean thearea per Chapter 3.
a. Protect adjacent unaffected areas not being treated bymasking to prevent damage from scale, chips, corro-sion products, or chemicals.
b. If present, remove gray or black oxides by an appro-priate mechanical method in this chapter.
5.9.6.2 Chemical Corrosion Removal Materials for Ti-tanium and Titanium Based Alloys. There are two types ofchemical solutions used for corrosion removal from titaniumand titanium based alloys: an acid pickling solution of A-A-59105 (O-N-350), nitric acid and MIL-A-24641, hydroflu-oric acid in water, and an SAE AMS-1640 (MIL-C-38334)corrosion removing compound solution.
Table 5-10. Typical Chemical Corrosion Removal Procedures for Copper and Copper Alloys
Type of Corrosion Step 1Corrosion Removal
Step 2Surface Treatment
Step 3Protective Finish
Tarnish or coloredcorrosion products(patina) on in-stalled compo-nents wheneverchemical corro-sion removal ispractical.
Remove corrosion withMIL-C-10578, Type IIIcorrosion removing com-pound (phosphoric acidbase)/inhibited. (Refer toParagraph 5.9.5.2.1.1).
Not required Refer to Paragraph5.9.5.2.1.1 for specificinstructions.
Corrosion on partswhich can be dis-assembled forimmersion treat-ment.
Remove corrosion by im-mersion in A-A-55828(O-S-809) sulfuric acidsolution. (Refer to Para-graph 5.9.5.2.1.1, step athrough step d).
If required, remove stain byimmersion in A-A-55828(O-S-809) sulfuric acid solu-tion and A-A-59123 (O-S-595) sodium dichromate so-lution. (Refer to Paragraph5.9.5.2.2.1, step f throughstep h).
As above
TO 1-1-691
5-32
5.9.6.2.1 Acid Pickling Solutions.
• Nitric-acid-hydrofluoric acid pickling solutionsare toxic to the skin, eyes, and respiratory tract.Chemical, splash proof goggles and/or faceshields and chemical resistant rubber glovesand aprons are required. In case of eye or skincontact, flush immediately with water and re-port to the Base Medical Facility. Use only in awell ventilated area.
• When preparing sulfuric acid solutions, neverpour water into the acid, as excessive heat willbe generated. Always pour the acid into thewater.
Titanium is susceptible to hydrogen embrittlementin acid solutions. Therefore, acid pickling shall beused only when other corrosion methods are notadequate. Competent operators must be assignedto monitor the process.
An acid pickling solution for removing corrosion from re-moved titanium and titanium alloy parts consists of a mix-ture of 20% by volume, A-A-59105 (O-N-350), nitric acidand 3% by volume, MIL-A-24641, hydrofluoric acid in wa-ter. This solution will remove most oxide coatings from tita-nium, provided the scale was formed at temperatures below1000° F (538° C) by immersing them in the solution. Asnoted in Paragraph 5.9.6.1, step b, gray or black oxides whichform at temperatures above 1000° F (538° C) should be re-moved by an appropriate mechanical method in this chapter,such as abrasive blasting, prior to the acid pickling to pre-vent pitting of the titanium.
5.9.6.2.1.1 Application and Use of Acid Pickling Solu-tions. The directions for the application and use of thesematerials are as follows:
a. Remove the components to be treated and disassemblethem to the piece part level.
b. Prepare the parts per Paragraph 5.9.6.1.
c. Immerse the parts in the nitric-acid-hydrofluoric acidpickling solution specified in Paragraph 5.9.6.2.1 whilemaintaining the solution at room temperature. Allowthe parts to remain in the solution only long enough toloosen and remove the oxide film from the surface.Intermittent scrubbing of the part surfaces with an acidbrush or wiping them with a cloth during this opera-tion will facilitate oxide film removal and minimizeany pitting of the part surfaces.
NOTE
This process may be optimized by adjusting theacid concentration and immersion time as deter-mined by testing per Paragraph 5.9.4.2.3.3 prior tostarting the pickling operation
d. Remove the parts from the solution and immediatelyrinse them thoroughly in fresh, running tap water. Ei-ther air dry them at room temperature or dry them in acirculating air oven at a temperature of 180° to 240° F(82° to 116° C).
e. If required by system specific technical data, apply anorganic coating system per Paragraph 5.9.6.3.
5.9.6.2.2 SAE AMS-1640 (MIL-C-38334) CorrosionRemoval Compound for Aircraft Surfaces. This is thesame material used to remove corrosion from aluminum al-loy surfaces, and it may also be used to remove corrosionfrom titanium and titanium alloy assemblies and/or on equip-ment surfaces. (Refer to Paragraph 5.9.1.2.1).
5.9.6.2.2.1 Application and Use of SAE AMS-1640(MIL-C-38334). The procedure for application and use ofthis corrosion removal compound to remove corrosion prod-ucts/oxides from titanium and titanium alloy surfaces is thesame as it is for aluminum alloy surfaces. (Refer to Para-graph 5.9.1.2.1.1).
5.9.6.3 Application of Organic Coatings. Titanium andtitanium alloys do not normally require a paint system forcorrosion protection. Where organic finishes are required fordecorative purposes, for continuity with the finish system onsurrounding surfaces, or to provide a barrier to prevent con-tact with a dissimilar anodic material, prepare the titanium ortitanium alloy surface for painting by applying a thixotropicMIL-DTL-81706/MIL-DTL-5541, Class 1A chemical chro-mate conversion coating solution per Section II of this chap-ter. Apply the organic finish system specified in the appli-cable system specific aircraft, missile, or equipmentmaintenance manual and/or engineering drawing and TO 35-1-3 for support equipment using TO 1-1-8 for applicationprocedures.
5.9.7 Plated and Phosphated Surfaces. These para-graphs outline chemical corrosion removal procedures forremoving corrosion from plated and phosphated surfaces.Table 5-12 provides guidelines for touch-up of corroded ar-eas, but where an organic finish on the plated part is speci-fied and/or required for engineering or other reasons, thetable can be used as a guide for treating the entire surface ofthe plated or phosphated parts. Chemical corrosion removalusing acid type chemical corrosion/rust removers is recom-mended for use where there is no danger of the chemicalsbecoming entrapped in crevices or recesses. They are in-tended for brush application following removal of heavycorrosion by an appropriate mechanical means in this chap-
TO 1-1-691
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ter to remove the remaining red rust and other types of cor-rosion from the base metal and to condition the metal sur-face for better paint adhesion.
5.9.7.1 Preparation.
Many platings and their corrosion products, suchas copper, cadmium, and chromium are toxic. Takeproper safety precautions to avoid inhalation oringestion of residue created during corrosion re-moval operations. Wash hands thoroughly beforeeating, drinking, or smoking after removing corro-sion from plated surfaces.
If the corroded area is contaminated by grease, oil, dirt, orother foreign materials, clean the area per Chapter 3. Protectadjacent components and areas by masking to prevent dam-age from scale, chips, corrosion products, and the chemicalsused.
5.9.7.2 Treatment of Corroded Areas on Cadmium orZinc Plated Surfaces. Cadmium and zinc platings provideanodic protection to underlying steel/ferrous (sometimes cop-per) base metal. If the plating surface is broken during nor-mal usage, the cadmium or zinc plate being anodic to thebase metal will corrode preferentially and sacrificially pro-tect the base metal. The removal of corrosion from cadmiumor zinc plated surfaces shall be limited to the removal of theplating and the base metal corrosion products from the local-ized area of the underlying base metal.
5.9.7.2.1 Application and Use of Chemical CorrosionRemovers on Cadmium and Zinc Plated Surfaces. Thedirections for the application and use of chemical removerson these plated surfaces are as follows:
a. Prepare the area per Paragraph 5.9.7.1.
b. As stated in Paragraph 5.9.7, remove heavy cadmiumor zinc and base metal corrosion products from part
surfaces using an appropriate hand type mechanicalmethod in this chapter such as ANSI B74.18 (GGG-C-520, Type II, Class 1) 240 grit abrasive paper, ANSIB74.18 (A-A-1047) 240 grit abrasive cloth, or A-A-58054, Type I, Grade B abrasive mat. Avoid removingundamaged cadmium or zinc plating adjacent to thecorroded area and limit corrosion removal to the im-mediate area of the corrosion on the base metal andthe plating surrounding it.
c. Remove any remaining corrosion and condition thesurface of the plating and base metal with MIL-C-10578, Type I, wash-off, phosphoric acid base, corro-sion removing and conditioning compound. Refer toParagraph 5.9.3.2.2.1 for additional instructions for ap-plication and use of this material. Allow the acid tocontact the surface only long enough to remove thecorrosion and then rinse the area thoroughly with freshtap water.
d. Allow the area to dry and immediately apply an or-ganic coating system or CPC as directed by systemspecific technical data. (Refer to Paragraph 5.9.7.5).
NOTE
These procedures are intended only for field leveltreatment of localized corroded areas on cadmiumor zinc plated surfaces and reapplication of a pro-tective coating after corrosion removal. When theuse of organic finishes or the thickness of the or-ganic finish will impair the normal operation of apart, severely corroded parts must be removed andreplaced. Where facilities are available, parts withseverely corroded cadmium or zinc plating maybe stripped and replated in accordance with proce-dures in TO 42C2-1-7. When high strength steelsare being replated, use only those specialized pro-cedures authorized for high strength steels as manyplating solutions can cause hydrogen embrittle-ment of these materials.
Table 5-11. Typical Chemical Corrosion Removal of Titanium and Titanium Base Alloys
Type of Corrosion Corrosion Removal Protective FinishLight to heavy oxide on
parts where acid picklingis practical on removedparts.
(1) Remove gray or black oxide by an ap-propriate mechanical method in thischapter.
When required, refer to Paragraph5.9.6.3.
(2) Remove remaining oxide by immersionin nitric-acid-hydrofluoric acid solution.(Refer to Paragraph 5.9.6.2.1.1.
Light to heavy oxide onassembled parts and/or onequipment surfaces.
(1) As in (1) above. As above
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Table 5-11. Typical Chemical Corrosion Removal of Titanium and Titanium Base Alloys - Continued
Type of Corrosion Corrosion Removal Protective Finish(2) Remove remaining oxide by treating
with SAE AMS-1640 (MIL-C-38334)solution. (Refer to Paragraph 5.9.6.2.2.1and Paragraph 5.9.1.2.1.1).
5.9.7.3 Treatment of Corroded Areas on Plated Sur-faces Except Cadmium or Zinc Plating. When a breakoccurs in the surface of either chromium, nickel, tin, or cop-per platings, corrosion of the steel/ferrous base metal andundercutting of the plating will rapidly follow. The corrosionwill occur at a highly accelerated rate due to the galvanicaction of these platings which are highly cathodic to thesteel/ferrous base metals.
5.9.7.3.1 Application and Use of Chemical CorrosionRemovers on Plated Surfaces Except Cadmium or ZincPlating. Directions for the application and use of chemicalremovers on plated surfaces except cadmium and zinc plat-ings are as follows:
a. Prepare the area per Paragraph 5.9.7.1.
b. Remove heavy corrosion by an appropriate hand typemechanical method in this chapter, such as a wire brushor abrasive paper, cloth, or mat.
c. Remove any remaining corrosion and condition thesurface of the plating and base metal with MIL-C-10578, Type I, wash-off, phosphoric acid base, corro-sion removing and conditioning compound. Refer toParagraph 5.9.3.2.2.1 for additional instructions for ap-plication and use of this material. Allow the acid tocontact the surface only long enough to remove thecorrosion and then rinse the area thoroughly with freshtap water.
d. Allow the area to dry and immediately apply an or-ganic coating system or CPC or place the part directlyinto service, whichever is directed by system specifictechnical data. (Refer to Paragraph 5.9.7.5).
NOTE
These procedures are intended only for field leveltreatment of localized corroded areas on chro-mium, nickel, tin, and copper plated surfaces.
Where service temperatures preclude the use oforganic finishes and/or the film thickness of theorganic finish will impair normal operation of thepart, severely corroded parts must be removed andreplaced. Where facilities are available, severelycorroded parts with chromium, nickel, tin, or cop-per plating may be stripped and replated in accor-dance with procedures in TO 42C2-1-7. Whenhigh strength steels are being replated, use onlythose specialized procedures authorized for highstrength steels as many plating solutions can causehydrogen embrittlement of these materials.
5.9.7.4 Treatment of Corroded Areas on PhosphatedSurfaces. Cadmium and zinc plated surfaces as well asmany bare steel surfaces are treated with a phosphate coat-ing at the time of manufacture to improve paint adhesionand corrosion resistance of the surfaces or as a base for theapplication of grease, oil, or CPC’s. When phosphated sur-faces corrode, corrosion should be removed by the methodrecommended for the base material.
5.9.7.5 Application of Organic Coatings. Organic coat-ings may be applied to phosphated surfaces and some platedsurfaces to provide corrosion protection to the plating and/orto increase the corrosion protection the plating or phosphatecoating provides to the base metal. They should not be usedwhen the part operates at temperatures which preclude theiruse or when the finish will prevent the part from performingits intended function. Organic coatings shall not be used onbearing or wearing surfaces of gears, cams, slides, etc., andon surfaces requiring electrical conductivity. Apply the or-ganic finish system specified in the applicable system spe-cific aircraft, missile, or equipment maintenance manualand/or engineering drawing and TO 35-1-3 for support equip-ment using TO 1-1-8 for application procedures.
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Table 5-12. Typical Chemical Corrosion Removal Procedures for Plated and Phosphated Surfaces
Type of Corrosion Corrosion Removal Protective Finish1
Light corrosion of plating andbase metal under and atbreaks in cadmium or zincplatings.
Remove corrosion from platingand base metal with an abrasivepaper, cloth, or mat. Completecorrosion removal and conditionmetal with MIL-C-10578, TypeI, wash-off, phosphoric acidbase corrosion removing andconditioning compound. (Referto Paragraph 5.9.7.2.1 and Para-graph 5.9.3.2.2.1).
Refer to Paragraph 5.9.7.5 for discussionof organic coating systems.
Light corrosion of base metalunder and at breaks in tin,chromium, nickel, or copperplatings.
Remove corrosion from the basemetal using an appropriate handmechanical method in thischapter followed by metal con-ditioning with MIL-C-10578,Type I, wash-off, phosphoricacid base corrosion removingand conditioning compound.(Refer to Paragraph 5.9.7.3.1and Paragraph 5.9.3.2.2.1).
As above
Heavy corrosion of base metalunder and at breaks in cad-mium, zinc, chromium,nickel, or copper platings.
As above As above
Light to heavy corrosion ofbase metal under and atbreaks in phosphate coatings.
Remove corrosion by methodused for corrosion removal onthe base metal.
As above
1 Protective finish should be applied only when the service temperature of the part does not preclude use of an organiccoating and/or where the film thickness of the coating will not impair the operation of the part.
SECTION II SURFACE TREATMENT
5.10 PURPOSE.
Surface treatment of the metal with a prescribed chemical toform a protective film is an important step in the corrosionprevention process. Properly applied chemical treatmentsimpart considerable corrosion resistance to the metal andgreatly improve the adhesion of subsequently applied paints.Epoxy primers, for example, which do not adhere well tobare aluminum alloy surfaces, adhere very well to them whenthey are treated with chemical conversion coatings.
5.10.1 Chemical Prepaint Treatments. Also known aschemical conversion coatings, chromate conversion coatings,chemical films, or surface pretreatments, these treatments areaqueous acid solutions of active inorganic compounds whichcombine with aluminum or magnesium surfaces to form acorrosion resistant film. In addition, these films improve theadhesion of paint coatings.
5.10.1.1 MIL-DTL-81706 Chemical Conversion Mate-rials for Coating Aluminum and Aluminum Alloys. MIL-DTL-81706 covers six different forms (I, II, III, IV, V, andVI) of two different classes (1A and 3) of chromate prepainttreatment materials (with various fluoride activators) withfour separate application methods (A-spray, B-brush, C-im-mersion, and D-pen application) for treating bare and cladaluminum surfaces, including touch-up of damaged anodizedaluminum and titanium alloys. Application of these materialsand the performance of the coatings developed by them arecovered by MIL-DTL-5541. MIL-DTL-81706, Class 1Acoatings provide maximum protection against corrosion whenleft unpainted and superior adhesion when paint systems areapplied. Class 3 coatings are intended for use as a corrosionpreventative film for electrical and electronic applicationswhere low contact resistance is required. Class 1A is avail-able in the following forms:
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5.10.1.1.1 Form I (Concentrated Liquid).
• Form II (powder) and Form V (premeasuredthixotropic powder) contain chromic acid dustand the other forms contain liquid chromic acidall of which can cause burns of the skin, eyes,and mucous membranes, including irritationand ulcers of the nasal septum. Use chemicalresistant, rubber gloves and aprons, chemical,splash proof goggles and/or face shield, and adust filter mask when mixing the powder andhandling the solutions.
• Chromic acid is a strong oxidizer and may ig-nite on contact with organic materials and re-ducing agents.
NOTE
Mix the Form I concentrated liquid, the Form IIpowder, and the Form V premeasured thixotropicpowder in accordance with the manufacturer’sinstructions.
When the concentrated liquid is mixed with water, prefer-ably deionized (DI) water, per the manufacturer’s instruc-tions, it forms a solution equivalent to a Form III solutionand is ready for use in touch-up by brush, spray, and immer-sion (Methods A, B, and C) applications. The unused por-tions of the mixed solution may be stored in a container andused, as required. The shelf life of the concentrated liquidand the mixed solution is around six months if they are notcontaminated.
5.10.1.1.2 Form II (Powder). When the powder is mixedwith water, DI water, per the manufacturer’s instructions, asolution equivalent to a Form III solution is formed that canbe used for brush, spray, and immersion (Methods A, B, andC) applications. The powder has an indefinite shelf life untilmixed with water. The unused portions of the mixed solutionmay be stored in a closed container and used as required.Once mixed, the shelf life of the solution is around sixmonths if the solution is not contaminated.
5.10.1.1.3 Form III (Pre-Mixed Liquid). This material isready for use, as received, for brush, spray, and immersion(Methods A, B, and C) applications. The Form III pre-mixedliquid is the most convenient form of MIL-DTL-81706 foruse at field level since it requires no mixing but is moreexpensive than the Form II powder. The shelf life of thisliquid is about six months from the date of manufacture.
5.10.1.1.4 Form IV (Pre-Mixed, Thixotropic Liquid).This material is a thickened, pre-mixed liquid which isready-to-use, as received, for brush (Method B) application.It is ideal for use on small areas, particularly vertical sur-faces, since it will remain in place without running. It is alsointended for use as a surface pretreatment on titanium alloysprior to painting. The shelf life of this liquid is about sixmonths from the date of manufacture.
5.10.1.1.5 Form V (Premeasured, Thixotropic Pow-der). This material is a premeasured powder that will form athixotropic solution equivalent to Form IV when mixed withwater, preferably DI water, per the manufacturer’s instruc-tions. Its use and application are the same as Form IV. Thepowder has an indefinite shelf life until mixed with water.The unused portions of the mixed solution may be stored ina closed container and used as required. Once mixed, theshelf life of the solution is about six months if the solution isnot contaminated.
5.10.1.1.6 Form VI (Pre-Mixed Liquid in a Self-Con-tained Applicator Device). This material is a pre-mixed,ready-to-use liquid contained in its own applicator device/pen for application by (pen application) (Method D). It isintended to touch-up small damaged areas of MIL-DTL-5541chemical chromate conversion coatings and anodized coat-ings, and to apply a pretreatment coating on corrosion grindout areas on aluminum alloys. The shelf life of the solutionsin the applicators is about six months from the date of manu-facture.
5.10.1.2 SAE AMS-M-3171 (MIL-M-3171), Type VIMagnesium Alloy, Processes for Pretreatment and Pre-vention of Corrosion on; Chromic Acid Brush-On Treat-ment.
The newly formed conversion coating is soft andcan be easily removed. Do not disturb the coatedsurface until coating is completely dry. Maintainthe drying temperature below 140° F (60° C) toavoid compromising integrity of the film. Theminimum drying time is 2 hours.
Also known as the Henkel Process, this is a corrosion pre-ventive and prepaint surface treatment/conversion coating forapplication on all magnesium alloys after corrosion removalby either brush-on or immersion methods. Either obtain thepre-mixed SAE AMS-M-3171 (MIL-M-3171), Type VI solu-tion through supply channels or mix the solution per theseinstructions.
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• SAE AMS-M-3171 (MIL-M-3171), Type VI,contains chromic acid which can cause burnsof the skin, eyes, and mucous membranes, in-cluding irritation and ulcers of the nasal sep-tum. Use chemical resistant rubber gloves andaprons, chemical, splash proof goggles and/orface shield, and dust filter mask when mixingor handling these chemicals and/or solutions.
• Chromic acid is a strong oxidizer and may ig-nite on contact with organic materials such assolvents, thinners, and reducing agents.
• MIL-DTL-81706/MIL-DTL-5541 aluminumconversion coating is not authorized for treat-ing magnesium alloy surfaces as it can causecorrosion of these surfaces as well as poor paintadhesion to magnesium alloys.
a. Obtain a one gallon stainless steel, aluminum, vinyl,polyethylene or rubber container.
b. Add ½ gallon of water, preferably DI water, to thecontainer.
c. Add 1-1/3 ounces (37.8 grams) of A-A-55827 (O-C-303) Chromic Acid (CrO3) and 1 OZ (28.3 grams) ofO-D-210 Anhydrous Calcium Sulfate (CaSO4.2H2O)to the water. (Refer to Appendix A for ordering infor-mation of chemicals).
d. Top off with enough water to make one gallon of so-lution and mix thoroughly until calcium sulfate hascompletely dissolved into the solution.
5.10.2 Surface Preparation. After completing corrosionremoval, proceed as follows:
a. Feather the edges of the paint around areas that havebeen chemically or mechanically stripped for removaland treatment of corrosion prior to pretreatment/con-version coating and repainting to ensure a smooth,overlapping transition between the old and new paintsurfaces. Feathering shall be accomplished using 240or 320 grit ANSI B74.18 (A-A-1048) aluminum oxideabrasive cloth or paper, A-A-58054, Type I, Grade Bor C (fine or medium) aluminum oxide abrasive mat,or a fine or very fine aluminum oxide finishing flapbrush.
b. Clean the surface of the parts and/or areas being treatedper procedures in Chapter 3 to remove all grease, oil,and dirt, and then rinse with fresh water. For watersensitive areas, use an approved cleaning solvent perprocedures in Chapter 3.
c. Abrade the area from which corrosion was removedwith an A-A-58054, Type I, Grade A or B (Very Fineor Fine) aluminum oxide abrasive mat to remove theoxide layer/coating. This is the most effective meansfor cleaning the surface so that it will accept a prepainttreatment/chemical conversion coating.
NOTE
For aluminum alloy surfaces, the oxide layer maybe removed from the area being treated with SAEAMS-1640 (MIL-C-38334) corrosion removingcompound per procedures in TO 1-1-8 and/orParagraph 5.9.1.2.1 of this manual followed byrinsing with fresh water.
d. After abrading and/or deoxidizing the area, rinse thesurface thoroughly by flushing with fresh water, pay-ing particular attention to fasteners and other areaswhere residues may become entrapped. At this stage ofthe cleaning process, the surface should be water-breakfree. (Refer to Figure 5-10). A surface showing water-breaks (water beading or incomplete wetting) is in-dicative of contamination, which will later interferewith conversion coating, sealing, and painting.
e. If the surface is not free of water-breaks, repeat step b,step c, and step d.
NOTE
Areas of aircraft, missiles, or equipment that havebeen waxed, particularly with a silicone material,or that have been treated with a silicone grease oroil require special cleaning to obtain a surface freeof water breaks. When silicone wax, grease, or oilare suspected, solvent clean using an approvedcleaning solvent per procedures in Chapter 3, andthen perform step b, step c, and step d.
5.10.3 Precautions. Observe the following precautionswhen applying chemical prepaint treatments on aluminum,titanium, or magnesium.
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5.10.4 Application of Surface Treatments.
• Chemical prepaint treatments are toxic to theskin, eyes, and respiratory tract. Use chemicalresistant rubber gloves and aprons, and chemi-cal, splash proof goggles and/or face shieldduring mixing or application. If the material(which is an acid) accidentally contacts the skinor eyes, flush immediately with plenty of freshwater and report to the Base Medical Facility ifeyes are affected or the skin is burned.
• Mixing and application should be done in anadequately ventilated area. Avoid prolongedbreathing of vapors.
• Chemical conversion coating/prepaint treatmentmaterials are strong oxidizers and are a firehazard in contact with flammable, combustible,and readily oxidizable materials. They must bestored separately from flammable, combustible,and oxidizable materials and never mixed incontainers previously containing flammable,combustible, and oxidizable products. Ragscontaminated with chemical conversion coatingmaterials should be thoroughly rinsed and dis-posed of as soon as it is practicable.
• Do not use chemical prepaint treatments onhigh strength steel parts. Catastrophic failuremay occur due to hydrogen embrittlement.
• Do not use steel, lead, copper, or glass contain-ers for holding/storing chemical prepaint treat-ments. Use only plastic, rubber, or stainlesssteel. Brushes with tin plated steel handles orferrules may be used but contact with the treat-ment solution should be minimized.
NOTE
Acrylic tip of TNP pen can be modified or alteredto form any shape to allow touching up hard toreach areas.
Refer to Table 5-13 for recommended materials and proce-dures for specific alloys. Immediately after cleaning to a wa-ter break-free surface and rinsing thoroughly, apply chemicalconversion coating material by brush, sponge stick moist-ener, immersion, or non-atomizing spray. The type of appli-
cation method used depends on the type of conversion ma-terial being applied, the area to be covered, and whetherapplication is on a removed part or on an assembly or onequipment area. The sponge stick moisteners and the Touch-N-PrepTM (TNP) pens are particularly useful for small areas.The sponge stick moisteners may be used to apply all typesof conversion coatings for aluminum, magnesium, and tita-nium alloys and when used, they should be rinsed with freshwater and discarded at the end of each work shift. The TNPpens are used to apply MIL-DTL-81706, Class 1A, Form VI,Method D (Alodine 1132) conversion coatings on aluminumalloys.
5.10.4.1 Conversion Coating Using TNP Pens. The re-pair of damaged chemical conversion coatings on aluminumalloys can be accomplished by applying Alodine 1132 usingthe TNP pens conforming to MIL-DTL-81706, Class 1A,Form VI, Method D. The TNP pen applicators are ideal fortouching-up small surface areas such as nicked, scratched,and chipped areas in a protective coating system. The solu-tion applied with TNP pens doesn’t require rinsing or wipingoff following application, thus minimizing hazardous wastegeneration. Empty pens can be returned to manufacturer fordisposal. To use the TNP pen, remove the cap and charge thetip by pressing the tip against a flat surface for 10 to 15seconds. The conversion coating solution will saturate thetip. Do not oversaturate the tip. Refresh solution often dur-ing use in a similar fashion. Use of TNP pens is restricted to1 sq ft.
a. Prepare and clean the damaged area to be repaired inaccordance with Paragraph 5.10.2 prior to using theTNP pen.
b. Immediately following cleaning, use the TNP pen toapply a chemical conversion coating solution in over-lapping parallel strokes. Do not over apply the solutionwhich would allow puddles, drips, or runs to form.
c. Apply one coat of solution and allow coating to dryfor 5 to 10 minutes before next application.
d. Apply a second coat perpendicular to the first coat andallow it to dry. The treated surface does not requirerinsing or wiping off and it can be air dried at ambient(room) temperature or force air dried with hot air. Oncecompletely dried, the coating is ready for primingand/or painting.
e. After processing, if bare surface areas still exist, repeatstep b through step d. Also, if the treated surface doesnot turn to an iridescent yellow color shortly followingapplication, reclean the surface and reapply per step athrough step d.
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5.10.5 Notes on Conversion Coating/Surface Treat-ment. Prepaint treatments shall be applied immediately aftercorrosion removal procedures. Failure to obtain a good con-version coating may be attributed to the following:
a. Allowing too long a period of contact prior to rinsingcan result in a powdery coated surface. Chemical con-version coating/prepaint treatments for aluminum al-loys shall be rinsed immediately when the surface hasan iridescent yellow to gold appearance. This usuallyoccurs in 1 to 5 minutes. A brownish color indicatestoo long a dwell time and produces a powdery coating.This will not provide a good surface to which thepaint/coating system can adhere. If a powdery coatingis formed, remove it with an A-A-58054, Type I, GradeB abrasive mat and reapply the material. The normaldwell time for magnesium conversion coating/paintpretreatments is 1 to 3 minutes to form a brown-greenfilm, but longer contact times for magnesium pretreat-ments do not usually cause problems. Titanium alloysrequire a dwell time of 45 minutes using a thixotropicMIL-DTL-81706, Form IV or V solution. ConsultChapter 3 of TO 1-1-8 and the material manufacturer’sinstructions for additional instructions for mixing andapplication of conversion coating solutions.
b. Allowing pretreatment solutions to contact lead, steel,copper, glass, or other incompatible materials can re-duce the effectiveness of the solutions and may pre-vent adequate pretreatment.
c. Insufficiently cleaned metal surfaces will prevent theconversion coating from forming on the metal surface.Cleaning must provide a water break-free surface. Re-fer to Paragraph 5.10.2, step d.
d. Insufficient dwell time doesn’t allow the conversioncoating to form on the metal surface. As the solutionapproaches its shelf life, or at temperatures below 50°F (10° C), more time may be required to form goodfilms.
e. Test a solution or material that is beyond its shelf lifedate using a small sample of scrap of the aluminum ormagnesium alloy metal that is to be treated. If a irides-cent yellow to gold coating is produced within 5 min-utes on an aluminum alloy or a brown-green coating isformed within 3 minutes on a magnesium alloy at 77°F (25° C), the material may be used.
5.10.6 Post Treatment. Chemical conversion coated sur-faces should be allowed to dry in accordance with thechemical manufacturer’s recommended instructions beforethey are subsequently painted or adhesion failures may oc-cur. More time may be required at low temperatures or highhumidity. The coating is soft until completely dried. Do notwipe the area with a cloth or brush when coating is still wet,since this will remove the coating. To avoid contaminationof the treated surface and to provide a surface that is recep-tive to organic coatings, prime the treated area per proce-dures in TO 1-1-8 with the primer specified in the systemspecific maintenance manual for the aircraft, missile, orequipment involved within 48 hours after application of theconversion coating/prepaint treatment. If this is not possible,perform temporary preservation procedures (refer to Para-graph 5.10.7), as soon as possible. If the surface is allowedto become dirty, scratched, or more than 48 hours haveelapsed since its application, it must be cleaned with a wetA-A-58054, Type I, Grade A or B abrasive mat and retreatedbefore any organic coatings/paint systems or sealants are ap-plied.
Figure 5-10. A Water-Break Free Surface Compared with One with Breaks
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5.10.7 Temporary Preservation. Under adverse condi-tions or when the pressure of operations will not permit theapplication and curing of an organic coating/paint system,
apply an appropriate CPC in accordance with Chapter 3.
Table 5-13. Prepaint Treatments for Metal Surfaces
Alloy Surface Treatment ProcedureAluminum Al-loys
MIL-DTL-81706, Class 1A, Form I(Concentrated Liquid), Form II(Powder), Form III (Pre-mixed Liq-uid), Method A, B, or C
Prepare a proper solution with either Form I or II ma-terials per the manufacturer’s instructions and TO1-1-8 or use a Form III solution, as received. Spraythe solution with a non-atomizing sprayer (Method A)or brush the solution with a sponge stick applicator orbrush (Method B) on the part or area being treated orimmerse a removed part in solution (Method C). Keepthe part/area wet with or the part immersed in the so-lution for 1 to 5 minutes, until an iridescent yellow/gold color is obtained. Immediately rinse part thor-oughly. Allow to dry in accordance with chemicalmanufacturer’s recommended instruction prior topainting but not to exceed 48 hours. 1
MIL-DTL-81706, Class 1A, FormVI, Method D; TNP Pen
Brush the surface using the acrylic tip of the pen toapply a MIL-DTL-81706, Form VI conversion coatingper Method D. (Refer to Paragraph 5.9.4.1). Thetreated surface does not require rinsing.
Magnesium Al-loys
SAE AMS-M-3171 (MIL-M-3171),Type VI (Chromic Acid Brush-onTreatment)
Obtain a pre-mixed solution or mix a solution per in-structions in Paragraph 5.10.1.2. Apply the solution tothe area being treated with a sponge stick applicator orbrush and keep the area wet with solution for 1 to 3minutes until a brown-green, brassy, or brown-yellowcolor is obtained. Immediately rinse part thoroughly.Allow part to dry in accordance with chemical manu-facturer’s recommended instruction. 1
Ferrous Metal(other thanStainless Steel)
None Treatment prior to painting is limited to corrosion re-moval, cleaning, and application of MIL-PRF-26915organic zinc rich primer or MIL-C-8514 or DOD-P-15328 wash primer per instructions in TO 1-1-8. Someof the MIL-C-10578 treatments will leave a film ad-equate to paint over. (Refer to Paragraph 5.9.3.2.2).
Stainless Steeland Nickel Al-loys
None Under engineering guidance, surfaces may be pickled.(Refer to Paragraph 5.9.4.2.3).
Cooper Alloys None 2
Titanium Alloys MIL-DTL-81706, Class 1A, FormIV (Pre-mixed Thixotropic Liquid)or Form V (Pre-mixed Thixotropicpowder)
Obtain the Form IV pre-mixed thixotropic liquid ormix the Form V pre-mixed thixotropic powder withwater per the manufacturer’s instructions and apply thesolution to the surface being treated with a spongestick applicator or a brush. Allow the solution to dwellon the surface for 45 minutes and then rinse thor-oughly with fresh water. Allow to dry in accordancewith chemical manufacturer’s recommended instruc-tion prior to painting but not to exceed 48 hours. 1
Plated and Phos-phated Cadmium
None 2
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1 Drying time may be accelerated by blowing with filtered warm air (140° F/60° C maximum). If the air contains oil(from a compressor) or other impurities, the paint system which is applied over the conversion coating will not pass wettape adhesion tests and will probably peel leading to additional corrosion. Drying air temperatures higher than 140° F(60° C) will degrade the conversion coating and cause it to lose its effectiveness.2 Treatment is limited to corrosion removal and cleaning. These surfaces are not normally painted, but may require paint-ing for decorative purposes, or in instances where the surface will be in contact with a dissimilar anodic metal. (CPC’s)may be applied as recommended in Chapter 3.
SECTION III SHOT PEENING
5.11 REQUIREMENTS FOR SHOT PEENING.
Prior to completing any shot peening operations ensure youhave been trained, have consulted Program Office Engineer-ing, and purchased the following AMS and SAE Standards:
• AMS 2431 - General Shot Peening Requirements
• AMS 2430 - Shot Peening, Automatic
• SAE J442 - Test Strip, Holder, and Gage for ShotPeening
• SAE J2277 - Shot Peening Coverage Determination
5.12 SHOT PEENING OF METAL SURFACES.
Shot peening is a cold working process which produces acompressive stress on the metal surface to alter the mechani-cal properties of the metal. This process utilizes peening me-dia, (i.e. steel shot, glass beads, etc.) in order to slightlydistort the metal surface. This compressive stress on the sur-face increases the resistance of the metal to fatigue and stresscorrosion cracking because both begin on the surface of themetal when it is subjected to tensile stresses. The closure ofexposed end grains and grain boundaries increases the resis-tance of the metal to intergranular corrosion; in particular, itincreases the resistance of high strength aluminum alloys toexfoliation corrosion. Because it increases resistance to cor-rosion and fatigue, peening is specified for protection of nu-merous new, high strength steel and aluminum alloy parts aswell as being required as a final procedure during rework/grind-out of corrosion damaged areas at both field and depotlevels of maintenance on many aircraft, missile, and otherequipment components fabricated from these metals. Shotpeening will not restore the strength lost in a metal structurecaused by metal removal due to corrosion damage, but itincreases corrosion and fatigue resistance of the remainingmetal. Shot peening requires the use of larger sized abrasiveparticles than used in abrasive blasting operations, special-ized blasting procedures for accomplishment, and specialtechniques and equipment for measuring the intensity andsaturation or surface coverage of a peening operation.
5.12.1 Types of Peening.
Peening operations can cause injury to personnelas high speed airborne abrasive particles can strikeunprotected areas of the body, enter into the respi-ratory tract, and cause slippage due abrasive resi-due buildup on the floor. Personal protectivegoggles and/or a faceshield, dusk filter mask,gloves, and coveralls are required for personnelengaged in peening operations. The work areasshall be kept clean of abrasive residue buildup,and adequate ventilation shall be provided.
• Peening is a specialized process requiring spe-cialized training in peening techniques used.Personnel who have not been specificallytrained for peening operations and/or who arenot thoroughly familiar with the specificationswhich cover these operations AMS 2430,AMS2431 and its subordinate slash numbers (/1through /8), AMS2590, SAE J442, SAE J443and SAE J2277 shall not be allowed to performpeening operations. Damage to structure, injuryto personnel, ineffective peening, and a falsesense of security about the condition of peenedaircraft, missile, or piece of equipment struc-ture will result if untrained and inexperiencedpersonnel are allowed to perform peening op-erations.
• Damage to equipment can also result from abra-sive particles which enter working mechanisms.Masking and shielding materials shall be usedto prevent penetration of abrasive particles inareas adjacent to the area being peened and tocontain abrasive overspray to prevent damageto the structure.
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There are two basic types of peening used on Air Forceequipment: shot peening using metallic, glass or ceramicshots per AMS 2430, covered in Section III and roto-peeningper SAE AMS 2590, covered in Section IV.
• Metallic Shot using data from SAE AMS 2431
• Glass Shot using data from SAE AMS 2431
• Ceramic Shot using data from SAE AMS 2431
5.12.1.1 Metallic, Glass, or Ceramic Shot Peening.
Do not use peening media (i.e. steel shot, glassbeads, etc.,) previously used for peening one typeof metal to peen a different type of metal, as con-tamination of the metal surface and subsequentgalvanic corrosion will result. Do not use any steelwire or shot for peening aluminum alloy surfaces,as steel particles will become embedded and causegalvanic corrosion. Use only AMS 2431/6 glassbead shot or AMS 2431/7 ceramic bead shot perparameters outlined in AMS2430 for peening alu-minum alloys.
Metallic, glass, and ceramic shot peening, per AMS2430, isthe peening of a meal surface by directing an air drivenstream of abrasive particles onto the metal surface, using thesame type of equipment employed for abrasive blasting toremove corrosion. The materials used are, stainless steel
(CRES) cut wire shot per AMS2431/4, cast steel shot perAMS2431/1 and /2, conditioned carbon steel wire shot perAMS2431/3 and /8, ceramic bead shot per AMS2431/7, andglass bead shot per AMS2431/6. Consult AMS2430 for allparameters that concern peening, such as intensity, saturationpoints, angle of blasting, nozzle distance, dwell times, pres-sures, and cast shot, cut wire shot, and glass or ceramic beadshot sizes. Shot peening by blasting will not be discussedfurther in this manual as this is normally a depot level op-eration requiring a specific step by step work procedure foreach job and is not used very often in every day corrosionremoval work.
5.12.2 Shot Peening Application. Shot peening is typi-cally used to induce surface residual compressive stresses inmetal parts to increase fatigue strength and resistance tostress-corrosion cracking for parts such as axles, springs (he-lical, torsional and leaf), gears, shafting, aircraft landing gear,structural parts, and similar items, but usage is not limited tosuch applications. Ceramic and glass shot peening, eitherwet or dry, may be used when iron contamination of stain-less steel or non-ferrous parts is a consideration.
5.12.2.1 Related peening processes, such as tumble peen-ing, manual peening, peen forming and straightening, peen-ing for prevention of intergranular corrosion, and peening toproduce a surface texture, are beyond the scope of this speci-fication.
5.12.2.2 Shot peening in accordance with AMS 2432meets or exceeds the requirements of AMS 2430. Part certi-fication in accordance with AMS 2432 is acceptable in addi-tion to AMS 2430.
SECTION IV ROTO-PEENING
5.13 ROTO-PEENING (ROTARY FLAP PEENING).
Rotary flaps containing cast steel shot conformingto AMS2431/1 and /2 shall not be used to peenaluminum alloy surfaces since they can becomeembedded in the surface and cause galvanic cor-rosion.
Roto-peening or rotary flap peening per AMS 2590 is a pro-cess that uses fiber type flaps with tungsten carbide shot em-bedded and bonded to the ends. The flap is mounted in amandrel and rotated in an electric or pneumatic powered tool,properly speed controlled to peen a metal surface. Roto-peening equipment shall conform to AMS 2592. Consult thespecification covering roto-peening of metal parts, AMS2590. This method of peening is convenient for small sur-
face areas where corrosion rework has been accomplished inplace on an aircraft, missile, or piece of equipment since itdoes not produce the contamination and abrasive residue as-sociated with the airblast methods and doesn’t require re-moval/disassembly of a part for placement in a blast booth.Roto-peening is the primary peening process used on air-craft, missile, and equipment components after corrosion re-moval, so it is the only peening process discussed in detail inthis manual. These procedures are limited in scope for useonly for peening or repeening metal surfaces after corrosionremoval and no other purpose. Peening that may be accom-plished is limited as follows:
a. The area peened shall not be larger than 3 x 4 inches.
b. When more than one area on a component requirespeening, the cumulative size of these areas shall notexceed 3 x 4 inches.
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c. This procedure is not authorized for peening to accom-plish fatigue or stress relief on previously unpeenedareas where corrosion removal is not involved.
d. Any roto-peening operation which exceeds these pa-rameters shall be accomplished in accordance with allrequirements in AMS2590 and MIL-R-81841 in addi-tion to these procedures.
e. Roto-peening shall be used on a weapon system com-ponent only when required in a specific system, spe-cific technical order, or the component is identified ashaving been previously peened.
5.13.1 Roto-Peening Procedures.
Roto-peening operations create airborne particles.Eye protection in the form of safety goggles/glasses and/or face shield is required.
5.13.1.1 Equipment. The tools required for roto-peeningare a rotary tool, a flap wheel assembly, Almen test stripsand gage and a magnetic test strip holder.
NOTE
A Flapspeed Kit containing all required Roto-Peening Equipment can be purchased using NSN5280-20-010-9597.
5.13.1.1.1 Rotary Tools. The rotary tool shall be capableof operating within ±100 rpm the speed shown in Table 5-14,while operating a flap in contact with the work piece. Theequipment shall be capable of reproducing consistently therequired peening intensities. Either pneumatic or electricallypowered tools properly speed-controlled are acceptable.
5.13.1.1.2 Flap Assembly. The flap wheel assemblies in-cluding mandrels and flaps shall conform to AMS 2592. Thetool flaps are rotated rapidly and manually forced against thesubstrate being peened. A portion of the flat face of each flapembedded with shot strikes the metal surface causing peen-ing.
5.13.1.1.3 Almen Test Strips and Gage. Almen teststrips and gage shall conform to SAE J442. Test specimensshall be A, C, or N type as specified by the cognizant engi-neering organization.
5.13.1.1.4 Magnetic Test Strip Holder. The magnetictest strip holder conforming to Figure 5-11 shall be used. Itshall consist of a nonmagnetic material block with three per-manent magnets loosely recessed into the top side for thepurpose of positioning a test strip. The bottom surface of theholder shall be faced with non-skid material. A strip of metalconforming to the requirements of the test strip shall be per-manently bonded to the top surface to provide a level ap-proach surface to the test strip. This will prevent the shot onthe flaps from hitting the exposed end of the test strip whichmay dislodge them from the flap. The magnets shall hold thetest strip to the top of the block and against the bonded teststrip.
Table 5-14. Tool Speed Operation Requirements
Flap Assembly Description (Inches) Rotary Tool Operation Speed (RPM)Mandrel with 1 x 2 flaps 1500 to 5000Mandrel with 9/16 x 1 1/4 flaps 1500 to 8000Mandrel with 9/16 x 1 flaps 1500 to 8000
5.13.1.1.5 10x to 30x Magnifying Glass. Used for ob-servation of the surface to determine surface coverage.
5.13.1.2 Surface Preparation Procedure. Prepare therequired surface for peening as follows:
5.13.1.2.1 Dimensions and Part Conditions. Surfaceareas required for roto-peening shall meet the dimensionaland surface finish requirements before peening. Unless oth-erwise directed, all heat treatments required to develop speci-fied mechanical properties, and all machining, grinding, andrequired polishing operations shall be completed beforepeening. Prior to roto-peening, all fillets shall be properlyformed, all burrs shall be removed, and all sharp edges andcorners to be peened shall be machined or sanded to providethem with a sufficient radius to result in complete coveragewithout any distortion.
5.13.1.2.2 Cleaning and Coating/Paint Removal. Un-less otherwise specified, all surface areas requiring roto-peening shall be cleaned in accordance with Chapter 3 ofthis manual and coatings/paints shall be removed from theareas per procedures in TO 1-1-8.
5.13.1.2.3 Masking. Any areas of the part which havecritical surface finishes that must be free from peening shallbe suitably masked or otherwise handled to protect themfrom damage caused by the rotary flap action. Masking ofareas not requiring peening and whose surface finishes arenot critical is optional.
5.13.1.2.4 RPM and Peening Time Determination. Therequired peening intensity “Arc Height” for peening needs tobe converted to Roto-Peening Intensity. First use Table 5-15to find the “Material Thickness” and “Material Type” for the
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aircraft part that requires rotary peening. Once the shot peen-ing “Arc Height” is found using Table 5-15, the followingfigures are used to convert “Arc Height” for Roto-Peeningintensity and time requirements.
NOTE
For Almen Strip “A” use Figure 12 and Figure 13.For Almen Strip “N” use Figure 14 and Figure 15.For Almen Strip “C” Contact Cognizant Engineer.
Table 5-15. Standard Peening Intensity (Isp) for Complete Coverage Arc-Height (All Numbers in Inches)
Material Thickness(Inches)
Steel: Under Steel: Over Titanium and Aluminum and200,000 PSI 200,000 PSI Titanium Alloys Aluminum Alloy
0.090 or less 0.003-0.006A 0.003-0.006A 0.00-0.006A0.090- 0.375 0.006-0.012A 0.006-0.010A 0.006-0.010A 0.006-0.010A0.375 or more 0.012-0.016A 0.006-0.010A 0.060-0.010A 0.010-0.014A
NOTE
• Base on test strip holder as specified in AMS-S-2430.
• The suffix letter A indicates that the values have been determined by using an A type Almen test strip. An Atype Almen test strip is used for arc-heights up to 0.024A.
• For greater intensities, Almen test strip C should be used. Any conversions for C test strips shall be provided bythe cognizant engineering prior to use.
• Almen test strip N is used if the intensity is less than 0.004A
5.13.2 Determining Peening/Intensity. The peening in-tensity is determined from a saturation curve in accordancewith Paragraph 5.13.2.1.1. The saturation curve intensity islimited to each individual operator and equipment type used.Intensity verification is the peening of one test strip for theintensity time “T” from the saturation curve of initial proce-dure qualification. Intensity verification is acceptable if theconverted test strip arc height is within ± 0.0015 inch (±0.038mm) of the original arc height and within the required inten-sity range. The peening intensity required after corrosion re-moval is that which is specified in a system specific mainte-nance technical order for the specific weapon system or itmay be determined from Table 5-15.
T = TsA/As
T = Total peening time, in minutes.Ts = Saturation peening time, as de-
termined from Figure 5-14and/or Figure 5-15, in minutes.
A = Area of part to be peened insquare inches.
As = The 2.25 in2 area of the teststrip when a flap with a widthof 3/4 inch or less is used; ifthe flap width is greater than3/4 inch, multiply effectivewidth of the flap by 3 inches toobtain As.
Isp = Standard peening intensity mea-sured with an AMS-S-13165Almen test strip holder. Theintensity range required forsaturation peening for variousmetal alloys at various thick-nesses is specified in Table5-15.
A = 3 x 4 inch = 12 inch2
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As = 1 x 3 inch = 3 inch2. This is thecase since a Type II, Class 1flap is 1 in (wider than 3/4 in).
Isp = 0.010A (10 mils). This is themaximum allowed intensity foraluminum alloys with a thick-ness within the 0.090 inch to0.375 inch range as determinedwith a AMS-S-13165 (MIL-S-13165) Almen strip holder andspecified in Table 5-18.
Irp = 13.2 mils (0.013A). This is therequired roto-peening intensitymeasured with a MIL-W-81940Almen strip holder. It is deter-mined by entering Figure 5-12on the horizontal (X) axis withthe Isp of 10 mils, moving up tothe line in the graph, and read-ing across to the vertical (Y)axis to find an Irp of 13.2 mils.
T = (3.25) 12/3 = 13.00 min = 13min and 0 sec at a flap speed of2500 RPM.
5.13.2.1 Arc Height Conversion. Strip arc height mea-surements obtained using the magnetic strip holder shall beconverted to the values equivalent to those that are obtainedusing the SAE J442 strip holder using Figure 5-11 throughFigure 5-16. Only the converted arc heights will be used fordata points on saturation curves.
5.13.2.1.1 Intensity Determination Methods. Intensityshall be determined by either of the two methods below. TheSAE J443 10% rule method is preferred but the coveragemethod is permitted.
5.13.2.1.1.1 SAE J443 10% Rule Method. Intensity isdetermined from a saturation curve with the converted archeight at the first point whose time when doubled producesan arc height increase of 10% or less per SAE J443.
5.13.2.1.1.2 Almen Test Strip Coverage Method. Forthis method a saturation curve is developed by plotting con-verted arc heights and strip coverage versus time. Intensity isdetermined as the converted arc height of the saturation curvetest strip at the time when it reaches full coverage as deter-mined by the methods in SAE J2277. Peening of the extremeends of Almen strips is not necessary. However, uniformcoverage of at least the central 2 inches of length is essentialto ensure accurate arc height measurements across the Al-men gage 1.25 inch support ball distance.
5.13.3 Peening Process Preparation.
5.13.3.1 Rotary Tool Speed. To achieve the requiredpeening intensity on an A test strip, the speed necessary forthe flap equipment may be estimated by referring to Table5-14. This is a first estimate that must be adjusted by gen-eration of a saturation curve.
5.13.3.2 Flap Operation. The flap assembly shall bemoved over the surface being peened with longitudinalsweeps and transverse oscillation; i.e., circular motion toprovide uniform surface coverage. Flap standoff distanceshall be determined by the operator so as to be comfortable,sustainable, and effective.
NOTE
The flaps used for this procedure are expensiveand tear apart easily when over the edge of a partduring the peening operation. The use of a hardrubber material clamped in place at the edges ofthe part being peened will prevent the flaps fromdropping over the edge of the part during thepeening operation, thus increasing the useful lifeof each flap.
5.13.3.3 Coverage. Areas of parts specified shall bepeened to complete visual coverage as specified in SAEJ2277 except parts being reshaped or straightened. Deter-mine coverage by visually inspecting surfaces using 10x to30x magnification. Every portion of the critical surface shallshow visible evidence of plastic flow to demonstrate com-plete coverage and saturation which is indicated by the com-plete obliteration of the original surface finish and overlap-ping peening impressions. If visual coverage with 10x to 30xmagnification is not clear refer to SAE J2277 for alternatemethods.
5.13.3.4 Part Peening Time. The area to be peened shallbe peened in increments of time and visually inspected forcoverage until full coverage (98%) is achieved (Figure 5-17).Coverage time is a function of part material hardness. Softparts will receive larger peening dimples and will cover fasterthan harder parts. For coverage requirements greater than100% the time to reach 100% shall be determined first priorto further coverage peening. Higher coverages require timemultiples of the 100% coverage time for the peened area
5.13.4 Post Peening Surface Finish. Conversion coat orpassivate the peened area in accordance with Section II orother applicable paragraphs of this chapter. Apply protectivecoatings, as specified, in the system specific maintenancemanual for the aircraft, missile, or equipment involved usingapplication procedures in TO 1-1-8.
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Figure 5-11. Magnetic Almen Strip Holder
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Figure 5-12. “A” Test Strip Magnetic to SAE J442 Stripholder Arc Height Conversion Graph
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Figure 5-13. “A” Test Strip Arc Height Magnetic to SAE J442 Stripholder Conversion Chart, 0.001 Inch
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Figure 5-14. “N” Arc Height Magnetic to SAE J442 Stripholder Conversion Graph
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Figure 5-15. “N” Arc Height Magnetic to SAE J442 Stripholder Conversion Chart, 0.001 Inch
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Figure 5-16. Arc Height Plotting Chart
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Figure 5-17. Example of Coverage
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Figure 5-18. Flap Deflection Ranges
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CHAPTER 6SEALANTS
6.1 PURPOSE.
This chapter covers sealing compounds and procedures fortheir application to aircraft, missile, and equipment struc-tures. When properly applied, sealants prevent the intrusionof moisture from condensation, rain, and salt water as wellas dust, dirt, and aircraft fluids into joint areas where theycan cause extensive corrosion. Sealants are one of the mostimportant tools for corrosion prevention and control. To beeffective, it is critical that the correct sealant be chosen for aspecific area/situation and that it be applied correctly. Onlyqualified personnel thoroughly familiar with sealants andtheir application shall be permitted to handle and apply them.
6.2 APPLICATIONS.
Sealants are used for the following reasons:
a. Fuel sealing (fuel tanks and delivery components).
b. Pressure area sealing (aircraft cabin areas).
c. Weather and fluid sealing (aircraft, missile, and equip-ment exterior and interior skin and structural joints andsurfaces).
d. Firewall sealing (engine and ordnance areas).
e. Electrical sealing (bulkhead wiring, electrical connec-tors, and components).
f. Acid-resistant sealing (aircraft, missile, and equipmentbattery compartments, and aircraft relief tubes andwaste collection tanks).
g. Window sealing (aircraft and equipment windows).
h. High temperature sealing (engine areas, anti-icingducts, and some electronics).
i. Aerodynamic sealing/smoothing (aircraft and missileexterior skin surfaces).
6.3 SEALING COMPOUNDS.
Table 6-1 lists approved sealing compounds and their avail-able types, properties, and intended use. Refer to the appli-cable aircraft, missile, or equipment system specific mainte-nance manual and Paragraph 6.7 for specific informationconcerning selection of the proper sealing compound and its
application. Observe the warnings and cautions in Paragraph6.6 when using any sealing compound.
6.3.1 Sealant Packaging. Sealants are generally pack-aged and available as three different types of packaging orunits of issue (U/I).
6.3.1.1 Two-Part Kit (KT). The package consists of twoseparate containers, usually metal cans. One contains thecatalyst (Part A) and the other contains the base compound(Part B), each in premeasured amounts for mixing together.
6.3.1.2 Cartridge (CA). Cartridges come in two differenttypes. One for single component sealants and one for twocomponent sealants.
6.3.1.2.1 Single Component Sealants. Single compo-nent sealants are contained in a plastic cartridge or tube in aready-to-use condition requiring no mixing. If some of asingle component sealant remains after a job, it can be storedand used at a future time as long as the cartridge/tube istightly capped at the nozzle opening to prevent contact withair.
6.3.1.2.2 Two Component Sealants. Two componentsealants are packaged in Semkits® which are complete plas-tic cartridge assemblies that store both sealant components(each in separate chambers). Mixing of sealant materials isaccomplished within the assembly, which is then used forapplication. Semkits® are convenient because they eliminatethe need to measure and handle the materials for mixing andgenerate less waste as they contain small quantities for smallarea applications.
6.3.1.3 Pre-Mixed and Frozen (PMF). Two componentsealants can be pre-measured, mixed, and frozen at tempera-tures of -40° F (-40° C) and stored at temperatures of -20° F(-29° C) or lower with the unit of issue being in ounces. ThePMF material in plastic tubes is a convenient package con-figuration for low and intermittent usage applications, par-ticularly in depot level operations. Simply thaw the materialand use.
6.3.2 Polysulfide, Polyurethane, and PolythioetherSealing Compounds. All these materials are two compo-nent with the Part B base containing the prepolymer and thePart A catalyst containing the curing agent packaged in sepa-rate containers supplied together as a kit. When thoroughlymixed, the catalyst cures the prepolymer to a rubbery solid.Rates of cure depend on the type of prepolymer and catalyst,
TO 1-1-691
6-1
as well as the temperature and humidity. Full cure of thesematerials may require as long as 7 days. Refer to Table 6-1for a general description of these materials.
6.3.3 Silicone Sealing Compounds.
Room Temperature Vulcanizing (RTV) siliconesconforming to MIL-A-46106 produce acetic acid(vinegar smell) which is corrosive. Therefore, as arule of thumb, if the RTV silicone material smellslike vinegar, don’t use it.
These materials are generally one component materials whichcure by reacting with moisture in the air. If silicones areapplied too thick or in such a way that moisture is preventedfrom entering the material, they may not cure at all. In addi-tion, many unauthorized silicone sealing compounds produceacetic acid, indicated by a vinegar smell, while curing whichcan lead to severe corrosion problems. There are two sili-cone sealant specifications, MIL-A-46146 and MIL-A-46106.Only MIL-A-46146 materials are noncorrosive. MIL-A-46106 materials give off acetic acid while curing and shallnot be used on Air Force equipment.
6.3.4 Adhesion Promoters.
Solvent based adhesion promoters are hygroscopic(absorb moisture) and must be kept away frommoisture. Discard material if it becomes cloudy ora precipitate is formed.
Some sealing compounds may require the application of aspecial primer or adhesion promoter prior to sealant applica-tion in order to develop a good adhesive bond with the sur-face. Use only those primers or adhesion promoters recom-mended by the manufacturer for their product. Thesematerials are especially important for MIL-S-85420, SAE-AMS3277 (supersedes MIL-S-29574), and some siliconebased sealants. Refer to Appendix A for a listing and de-scription of adhesion promoters.
6.3.5 SAE AMS 3255 Oil and Water Resistant, Ex-panded Polytetrafluoroethylene Sealing Tape (EPTFE)Skyflex. The sealant tape consists of an extruded gasket(most of the time with several protruding ribs) with a pres-sure sensitive adhesive backing. No mixing is required andthere are no application life constraints or cure times in-
volved. The sealing tape does not require removal and re-placement unless damaged. The adhesive backing is onlyrequired to hold the sealing tape in place until an accesspanel, floor panel, or component is reinstalled. Tapes may bespecial ordered without adhesive backing for use in areaswhere fluid exposure (e.g. hydraulic fluid or fuel) is expectedand applied with a fluid resistant rubber cement. Refer toTable 6-1 for a general description of these tapes.
NOTE
Use of the EPTFE (Skyflex) sealing tape requiresauthorization from the aircraft SPD or the missileor equipment SPM engineering authority.
6.3.6 Av-Dec® Polyurethane Sealant Tapes and TwoComponent Sealants. Av-Dec® sealing tapes are precuredpolyurethane gasket tapes with the HT3935-7 series having atacky adhesive on both sides and the HT3000 series having atacky adhesive on one side and a permanent Teflon filmbacking on the other side. These tapes require no mixing,have unlimited application life, and require no cure time.The HT3995-7 series tapes are particularly useful for sealinghigh moisture areas such as aircraft floor panels. The HT3000series are useful for sealing frequently removed inspectionand access panels, since once applied they are totally reus-able unless damaged; damaged areas only may be removedand replaced. The HT3326-5 SelfLeveling Green liquid andTF2219 thick orange, TG8498-50, and TG20101-50 thixo-flex grey paste materials are two component curable sealantsthat are particularly useful in filling voids and cavities toprevent moisture and fluid accumulation and subsequent cor-rosion damage in areas where ease of removal for inspectionand/or operational requirements is necessary.
6.4 EQUIPMENT.
The following equipment is available.
NOTE
Avoid air bubbles as much as possible during thefilleting operation. Allow the sealant to cure to, atleast, the tack-free stage before moving the assem-bly.
6.4.1 Sealant Gun. The Semco® Model 250-A or itsequivalent (refer to Figure 6-1), fitted with one of the nozzlesfrom Figure 6-2 is used for the application of fillet seals.When using this gun, the nozzle tip must be pointed into theseam and maintained at a 45 degree angle to the line oftravel, forcing the bead of sealing to precede the gun tip to
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minimize entrapment of air. Use fairing/smoothing tools (i.e.,spatulas and spreaders) shown in Figure 6-5 to work sealantsand adhesives into seams.
6.4.2 Application Nozzles.
Care should be taken when using rivet nozzles toprevent sealant material from filling fastener holes.
In addition to the standard, fillet, and ribbon nozzles in Fig-ure 6-2, the countersink and rivet nozzles in Figure 6-3 andFigure 6-4, respectively, can also be used with sealant guns.Countersink nozzles can be used to apply sealants into thecountersink of fastener holes prior to fastener installation.Rivet nozzles are suitable for use to apply sealants intocountersink and through hole prior to fastening part(s) withrivets. The rivet nozzles have a spring-loaded tip. It serves asa check valve and allows for dispensing the precise amountof sealant material.
6.4.3 Injection Gun. Figure 6-6 illustrates two types ofinjection guns used for injecting sealant into confined holes,slots, structural voids, joggles, etc. Follow the proceduresoutlined in the applicable aircraft, missile, or equipment sys-tem specific maintenance manual and the injection gunmanufacturer’s operation instructions for the proper prepara-tion and use of these guns. For hard to reach areas, attach anextension nozzle to the injection tip.
6.4.4 Sealant Kits (Semkits®).
Before using sealant materials, refer to the sealantSafety Data Sheets (SDS) for information on han-dling precautions.
Certain types of sealants, such as SAE AMS-S-8802 (MIL-S-8802) and MIL-PRF-81733, are available as ready-to-usekits (Semkits®). These kits are compact, two-part mixingapplication units designed for convenient storage, easy mix-ing, and proper application of the sealant in small quantities.The base component of the sealant is packed in standard 2 ½OZ and 6 OZ cartridges which are placed in a filleting gunor injection gun for application after mixing with the accel-erator/catalyst. There are two styles: the Barrier Style, whichholds proportioned amounts of the two components sepa-rated by an aluminum barrier disc and the Injection Style,which stores the accelerator/catalyst material within the in-jection rod to separate it from the base compound prior touse. (Refer to Figure 6-7). When using Semkits®, note thatthe handle or the injection/dasher rod contains a pre-mea-sured amount of accelerator/catalyst and should be retaineduntil the ramrod has been operated to break the seal at thebottom of the injection/dasher rod releasing the accelerator/catalyst into the base component and mixing is completed.
All of the materials contained inside these two-componentSemkit® packages are mixed within the cartridges. Followthe manufacturer’s recommended storage instructions forthese Semkits®.
6.4.5 Sealant Removal and Application Tools.
• Sealant removal must be accomplished usingnon-metallic scrapers. The use of metallicscrapers (i.e. steel, aluminum, tin, brass, exactoknives, and pocket knives) to remove sealant isprohibited.
• Metallic scrapers scratch the aircraft surfacepotentially causing cracking and corrosion.
The most commonly used tools for removing or fairing outsealants are shown in Figure 6-5. Other tools may be manu-factured as needed to fit a specific situation. Only plasticshall be used to manufacture these sealant removal and ap-plication tools. The Pneumatic Vibro Gun Sealant Removalkit or Rapid Desealing System (RDS) listed in Table B-2may also be used.
6.5 SEALANT MIXING.
The proper weighing and mixing of components is essentialto assure proper curing and adhesion of sealants. Use anappropriate weight scale (refer to Appendix B), to accuratelymeasure the materials before blending. Accomplish all mix-ing in one designated central area in each organization. Poly-sulfide and polythioether sealants consist of two separatelypackaged components, a base compound (usually Part B)and an accelerator/catalyst (usually Part A) in ½ pint (6 OZ),pint (12 OZ), and quart (24 OZ) kits. The base-to-accelera-tor/catalyst ratio varies with different manufacturer’s of thesame type of sealant. It is important, therefore, to mix thematerial according to the manufacturer’s instructions recom-mendations. Add accelerator/catalyst into the base in the cor-rect ratio and mix until a uniform color is obtained. Difficul-ties with curing and/or adhesion of polysulfide andpolythioether sealants are frequently caused by incompletemixing. Two component sealants are chemically cured anddo not depend on solvent evaporation for curing. Slow handmixing is recommended for two-component can type kits. Ahigh speed mechanical mixer should not be used as internalheat will be generated thus reducing application life and in-troducing air into the mixture. Refer to Figure 6-7 for injec-tion style Semkit® mixing instructions.
6.5.1 Application Life. Application life and cure times aredependant on environmental considerations. The applicationlife of a sealant is the length of time that a mixed sealingcompound remains usable at 77° F (25° C) and 50% relativehumidity (RH). This time (in hours), known as a dash num-ber, is denoted as the last number in a sealant designation(e.g. MIL-PRF-81733, Type II-2 has an application life of 2
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hours). Table 6-2 indicates application times, tack-free times,and full cure times for each sealant type and dash number at77° F (25° C) and 50% RH. For each 18°F (10°C) increasein the temperature above 77° F (25° C), the application,tack-free, and cure times are shortened by approximatelyone-half, while for each 18°sF (10°sC) decrease in the tem-perature below 77° F (25° C), the application, tack-free, andcure times are lengthened by approximately one-half. Foreach 15% increase in RH above 50%, the application, tack-free, and cure times are shortened by approximately one-half, while for each 15% decrease in RH below 50%, theapplication, tack-free, and cure times are lengthened by ap-proximately one-half. Maintenance personnel should beaware of the effects of temperature and humidity on the ap-plication life of a sealant. Mix only the amount of materialthat can be applied during the rated work life of the sealant.
6.5.1.1 Enhancement of Sealant Curing. There are sev-eral corrective measures that can be used to prevent and/orlessen sealant curing problems caused by various environ-mental conditions.
a. At a relative humidity of 30% RH or lower (some-times even 40% RH causes a problem), it is very dif-ficult to properly cure sealants. When these conditionsare experienced, adding water vapor to the air to in-crease the humidity by either wetting down the floor ofthe facility, covering the area being sealed with a wetcloth without it touching the sealant surface and keep-ing the cloth wet during the cure cycle, or some otherconvenient method will eliminate the problem.
Do not apply heat to sealants until 30 minutesminimum have elapsed at ambient (room) tem-perature after application to allow the containedsolvents to flash off. Most solvents are flammableand could catch fire if the sealants are exposed tohigher temperatures before the solvents flash off.
NOTE
If sealants are heated to a temperature of 110° F(43° C) or greater as noted in step b below, noadjustment to the humidity is required.
b. Except for MIL-S-85420 and SAE-AMS3277 (MIL-S-29574) sealants that are designed to cure properly withgood adhesion at low temperatures, sealant curing isextremely slow when applied at ambient (room) airtemperatures of 50° F (10° C) and below and adherevery poorly to metal structure having a surface tem-perature of 60° F (16° C) and below due to poor sur-face wetting properties at the time of application. Theseproblems can be eliminated by preheating the metalsurfaces to which a sealant will be applied to a tem-perature of 60° F (16° C) or higher and/or heating thesealant to a temperature of 130° F ±10° F (54° C ±6°
C) after application with hot air, infrared lamps, orsome other approved method after allowing the sealantto stand for minimum of 30 minutes at ambient (room)temperature after it is applied to flash off its containedsolvents.
c. If sealants are applied to metal surfaces having a sur-face temperature of 100° F (37° C) or at ambient(room) air temperatures of 95° F (35° C) or greater,will very likely have bubbles in the cured sealant film,commonly called “solvent pop” due to too rapid evapo-ration of the solvents contained in the sealant. Cool themetal surface down to a temperature of 90° F (32° C)or lower by wetting it down with water and then wip-ing the surface dry or by some other approved methodand/or relocate the equipment to which sealant is to beapplied to an area having an ambient (room) tempera-ture of 90° F (32° C) or lower prior to applying thesealant and keep the equipment in this cooler conditionfor a minimum of 30 minutes to allow the containedsolvents to flash off before relocating the equipment ina hotter area or applying heat to the sealant.
d. Sometimes sealant must be applied in areas whereother maintenance is being accomplished which leadsto sealant smears in the area caused by walking onand/or dragging tools through sealant that is not com-pletely cured. To minimize this problem, apply a poly-ethylene film over the uncured sealant after allowing aminimum of 30 minutes at ambient (room) tempera-ture after it is applied to flash off its contained solventsand permit the film to remain in place until the sealanthas completely cured.
e. The Rapid Curing Device (RCD) (Refer to AppendixB) can be used with SPD/SPO approval for acceleratedcuring of sealants. The RCD consist of the main con-trol module, the thermorcactor (infra-red emitter), 30feet of hosin, temperature sensors and other associatedcomponents. Propane used with the RCD must be pur-chased and stored separately. The RCD is effective onlywhen the energy it generates hits the entire area beingcured. Use on blocked, unreachable, or multiple repairareas will not reduce curing time.
6.5.2 Storage Instructions. When large quantities of seal-ants are used, such as for depot level maintenance opera-tions, it may be advantageous to pre-mix and freeze sealantsto provide a ready supply of mixed sealants when they areneeded. Store two-part kits and Semkit® package sealantsaccording to instructions on the container. Store polysulfidesealants in a pre-mixed and frozen (PMF) form in a freezerat -40° F (-40° C) or below for retention of optimal applica-tion properties and shelf life. Polythioether sealants requireextremely low temperature refrigeration at -80° F (-62° C) orbelow for optimal retention of application properties andshelf life. Thawing of PMF sealants can be accomplished intwo ways. For ambient (room) temperature thaw, place thePMF cartridge in a vertical position. Let stand at +70° to+80° F (+21° to +27° C) approximately 30 minutes. Dry any
TO 1-1-691
6-4 Change 2
condensation from the exterior of the cartridge prior to use.For water bath thaw, place the PMF cartridge upright in a+120° F (49° C) water bath for approximately 4 to 6 min-utes. Upon removal from the bath, carefully dry the exteriorof the cartridge before using.
6.5.3 Mixing MIL-PRF-81733, Type III Sprayable Seal-ant Coating. The base component (Part B) of MIL-PRF-81733, Type III has a tendency to settle out during storage,so it requires thorough mixing with a standard paint shakerto obtain a uniform consistency before the addition of theaccelerator component (Part A). The accelerator component(Part A) requires hand shaking or stirring with a wood stirpaddle/stick in its container to obtain a uniform consistencybefore adding it to the base component (Part B). After bothcomponents, base and accelerator, have been stirred/mixed
separately, add the proper amount of the accelerator to thebase in its container and mix the combined materials, pref-erably with a paint shaker for 3 minutes in an upright posi-tion followed by 3 minutes in an inverted position for kits upto 1 gallon, and for 5 to 10 minutes with an air driven agi-tator in a pressure pot for kits greater than 1 gallon. Forproper application life and cure, the base and acceleratormust be combined in the proper ratio and mixed prior to theaddition of any thinner (solvents). After mixing, the sealantmay be thinned for spraying to a viscosity of 20 to 25 sec-onds in a No. 2 Zahn cup (refer to TO 1-1-8), with a 20 to30% by volume addition of a 50% by volume mixture ofMEK conforming to ASTM D 740 and Toluene conformingto A-A-59107, and stirring for 2 minutes with an air drivenagitator at 70 RPM.
TO 1-1-691
Change 2 6-5
Figure 6-1. Pneumatic Sealant Gun
TO 1-1-691
6-6
Figure 6-2. Sealant Application Nozzles
TO 1-1-691
6-7
Figure 6-3. Countersink Application Nozzles
TO 1-1-691
6-8
Figure 6-4. Rivet Application Nozzles
TO 1-1-691
6-9
Figure 6-5. Sealant and Adhesive Smoothing Tools
TO 1-1-691
6-10
Figure 6-6. Sealant Injection Guns
TO 1-1-691
6-11
Figure 6-7. Injection Style Semkit®
TO 1-1-691
6-12
Tabl
e6-
1.Se
alin
gC
ompo
unds
Spec
ifica
tion
Type
sA
vaila
ble
Prop
ertie
sIn
tend
edU
seM
IL-P
RF-
8173
3(s
uper
sede
sM
IL-S
-817
33),
Seal
ing
and
Coa
ting
Type
I(t
hin)
-fo
rbr
ush
ordi
pap
plic
atio
nTw
oco
mpo
nent
sSe
alin
gfa
ying
surf
aces
and
for
wet
inst
alla
tion
offa
sten
ers
onpe
rman
ent
stru
ctur
ere
-pa
irs.
Cla
ss1,
Gra
deA
ma-
teri
als
are
the
pref
erre
dse
al-
ants
for
thes
eap
plic
atio
nsas
they
prov
ide
the
best
corr
o-si
onpr
otec
tion.
Com
poun
d,C
orro
sion
Inhi
bitiv
eTy
peII
(thi
ck)
-fo
rse
alan
tgu
nor
spat
ula
appl
icat
ion
Roo
mte
mpe
ratu
recu
re
Cla
ss1
-Po
lysu
lfide
Type
III
(spr
ayab
le)
-fo
rsp
ray
gun
appl
icat
ion
Serv
ice
tem
p:-6
5°to
+25
0°F
(-54
°to
+12
1°C
)C
lass
2-
Poly
thio
ethe
rTy
peIV
(spr
eada
ble)
-fo
rfa
y-in
gsu
rfac
ese
alin
gre
quir
ing
exte
nded
asse
mbl
ytim
es
Peel
stre
ngth
:15
inlb
wid
th(m
in)
Gra
deA
-C
hrom
ate
Inhi
bito
rsC
orro
sion
inhi
bitin
gG
rade
B-
Non
-Chr
omat
eIn
hibi
-to
rsR
esis
tsfu
el,
oil,
and
hydr
aulic
fluid
.SA
EA
MS-
S-88
02(s
uper
sede
sM
IL-S
-880
2),
Seal
ing
Com
-po
und,
Tem
pera
ture
Res
ista
nt,
Inte
gral
Fuel
Tank
san
dFu
elC
ell
Cav
ities
,H
igh
Adh
esio
n(P
olys
ulfid
e)
Cla
ssA
(thi
n)-
for
brus
hap
-pl
icat
ion
Two
com
pone
nts
Use
dfo
rfil
let
and
brus
hse
al-
ing
inte
gral
fuel
tank
san
dfu
elce
llca
vitie
s.N
otto
beex
pose
dto
fuel
orov
er-
coat
edun
tilta
ck-f
ree.
Cla
ssB
(thi
ck)
-fo
rse
alan
tgu
nor
spat
ula
Roo
mte
mpe
ratu
recu
re
Cla
ssC
(spr
eada
ble)
-fo
rus
ew
here
exte
nded
asse
mbl
ytim
esar
ere
quir
ed
Serv
ice
tem
p:-6
5°to
+25
0°F
(-54
°to
+12
1°C
)
Peel
stre
ngth
:20
inlb
wid
th(m
in)
No
corr
osio
nin
hibi
tors
Res
ists
fuel
,oi
l,an
dhy
drau
licflu
id.
TO 1-1-691
6-13
Tabl
e6-
1.Se
alin
gC
ompo
unds
-C
onti
nued
Spec
ifica
tion
Type
sA
vaila
ble
Prop
ertie
sIn
tend
edU
seSA
EA
MS
3276
(sup
erse
des
MIL
-S-8
3430
),Se
alin
gC
om-
poun
d,In
tegr
alFu
elTa
nks
and
Gen
eral
Purp
ose
(Pol
ysul
fide)
Cla
ssA
(thi
n)-
for
brus
hap
-pl
icat
ion
Two
com
pone
nts
Cla
ssB
(thi
ck)
-fo
rse
alan
tgu
nor
spat
ula
appl
icat
ion
Roo
mte
mpe
ratu
recu
re
Cla
ssC
(thi
ck)
-fo
rus
ew
here
exte
nded
asse
mbl
ytim
esar
ere
quir
ed
Serv
ice
tem
p:-6
5°to
+25
0°F
(-54
°to
+12
1°C
)su
stai
ned,
inte
rmitt
ent
(abo
ut6
hour
sm
ax)
expo
sure
to36
0°F
(182
°C
)
For
high
erte
mpe
ratu
reap
pli-
catio
ns.
Use
dfo
rfu
elta
nkse
alin
g,ca
bin
pres
sure
seal
-in
g,ho
lean
dvo
idfil
ling,
and
aero
dyna
mic
smoo
thin
g;fo
rfa
ying
surf
ace
seal
ing,
wet
-ins
talla
tion
offa
sten
ers,
over
coat
ing
fast
ener
s,an
dse
alin
gjo
ints
and
seam
sin
fuel
wet
area
s;an
dfo
rno
n-st
ruct
ural
adhe
sive
bond
ing.
Tre
atbo
ndsu
rfac
esw
ithSA
EA
MS
3100
adhe
sion
prom
oter
toen
hanc
ese
alan
tad
hesi
on.
Cla
ssD
(thi
ck)
-fo
rho
lean
dvo
idfil
ling
Peel
stre
ngth
:20
inlb
wid
th(m
in)
Cla
ssE
(thi
ck)
-fo
rau
tom
atic
rive
ting
equi
pmen
tap
plic
a-tio
n
No
corr
osio
nin
hibi
tors
Res
ists
fuel
,oi
l,an
dhy
drau
licflu
id
PR-1
773
(sup
erse
des
PR-1
403G
),Se
alin
gC
ompo
und,
Non
-Chr
o-m
ate
Cor
rosi
onIn
hibi
tive
Poly
sulfi
deR
ubbe
rC
AG
EC
ode
#835
74
Cla
ssB
(thi
ck)
-fo
rse
alan
tgu
nor
spat
ula
appl
icat
ion
Two
com
pone
nts
Pref
erre
dse
alan
tfo
rge
nera
lpu
rpos
e,lo
wad
hesi
onse
al-
ing
ofac
cess
door
s,flo
orpa
nels
and
plat
es,
rem
ovab
lepa
nels
,an
dfo
rmed
inpl
ace
(FIP
)ga
sket
sin
non-
fuel
area
s.C
anbe
used
tore
pair
defe
cts
inFI
PG
aske
ts.
Roo
mte
mpe
ratu
recu
reSe
rvic
ete
mp:
-65°
to25
0°F
(-54
°to
+12
1°C
)Pe
elst
reng
th:
2in
lbw
idth
(max
)C
orro
sion
inhi
bito
rsR
esis
tsfu
el,
oil,
and
hydr
aulic
fluid
.SA
EA
MS
3267
/1,
/2,
/3,
and
/4(s
uper
sede
sM
IL-S
-878
4),
Seal
ing
Com
poun
d,L
owA
d-he
sion
,C
orro
sion
Inhi
bitin
g,fo
rR
emov
able
Pane
lsan
dFu
elTa
nkIn
spec
tion
Plat
es
Cla
ssA
(thi
n)-
for
brus
hap
-pl
icat
ion
Two
com
pone
nts
Poly
sulfi
deru
bber
seal
ing
com
poun
dfo
rfil
let
and
fay
surf
ace
seal
ing
ofre
mov
able
stru
ctur
essu
chas
acce
ssdo
ors,
floor
pane
lsan
dpl
ates
,re
mov
able
pane
ls,
and
fuel
tank
insp
ectio
npl
ates
.N
otfo
rhi
ghte
mpe
ra-
ture
area
sor
perm
anen
tst
ruct
ures
.
Cla
ssB
(thi
ck)
-fo
rse
alan
tgu
nor
spat
ula
appl
icat
ion
Roo
mte
mpe
ratu
recu
re
Serv
ice
tem
p:-6
5°to
250°
F(-
54°
to+
121°
C)
/1=
Cla
ssA
-½Pe
elst
reng
th:
4in
lbw
idth
(max
)/2
=C
lass
B-½
Cor
rosi
onIn
hibi
tors
/3=
Cla
ssA
-2R
esis
tsfu
el,
oil,
and
hydr
aulic
fluid
./4
=C
lass
B-2
TO 1-1-691
6-14
Tabl
e6-
1.Se
alin
gC
ompo
unds
-C
onti
nued
Spec
ifica
tion
Type
sA
vaila
ble
Prop
ertie
sIn
tend
edU
seSA
EA
MS
3374
/1,
/2,
/3,
and
/4(s
uper
sede
sM
IL-S
-382
49),
Seal
ing
Com
poun
d,A
ircr
aft
Fire
wal
l
Type
1(o
ne-p
art
high
tem
p.si
licon
e)-
cond
ensa
tion
cure
d
One
com
pone
nt,
Type
1;Tw
oco
mpo
nent
s,Ty
pes
2,3,
and
4Se
alin
gfir
ewal
lst
ruct
ures
ex-
pose
dto
very
high
tem
pera
-tu
res
agai
nst
the
pass
age
ofai
ran
dva
pors
.C
ures
onex
posu
reto
air.
/1=
Type
1Ty
pe2
(tw
o-pa
rthi
ghte
mp.
silic
one)
-ad
ditio
ncu
red
Roo
mte
mpe
ratu
recu
re
/2=
Type
2Ty
pe3
(tw
o-pa
rthi
ghte
mp.
silic
one)
-co
nden
satio
ncu
red
Serv
ice
tem
p:-6
5°to
+40
0°F
(-54
°to
+20
4°C
)w
ithst
ands
flash
tem
pera
ture
of20
00°
F(1
093°
C)
/3=
Type
3Ty
pe4
(tw
o-pa
rtpo
lysu
lfide
)Pe
elst
reng
th:
10in
lbw
idth
(min
)/4
=Ty
pe4
No
corr
osio
nin
hibi
tors
Res
ists
fuel
,oi
l,an
dhy
drau
licflu
idM
IL-S
-854
20,
Seal
ing
Com
-po
unds
,Q
uick
Rep
air,
Low
Tem
pera
ture
Cur
ing
Poly
sul-
fide,
for
Air
craf
tSt
ruct
ures
Cla
ssA
(thi
n)-
for
brus
hap
-pl
icat
ion
Two
com
pone
nts
Qui
ckre
pair
seal
ing
ofai
rcra
ftst
ruct
ures
atlo
wte
mpe
ra-
ture
s.U
seon
lyw
ithth
ere
c-om
men
ded
adhe
sion
pro-
mot
er/p
rim
erfo
rop
timum
resu
lts.
Whe
ncu
red
ata
tem
pera
ture
ofat
leas
t75
°F
(24°
C),
the
fly-a
way
time
is2
to3
hour
s.W
hen
cure
dat
ate
mpe
ratu
reas
low
as45
°F
(7°
C),
the
fly-a
way
time
is4
hour
sfo
rTy
peII
seal
-an
tsan
d8
hour
sfo
rTy
peI
seal
ants
.T
his
seal
ant
shou
ldbe
stor
edat
ate
mpe
ratu
reno
tto
exce
ed+
80°
For
poor
adhe
sion
will
resu
lt.
Type
I-
Dic
hrom
ate
cure
syst
emC
lass
B(t
hick
)-
for
seal
ant
gun
orsp
atul
aap
plic
atio
nL
owte
mpe
ratu
recu
re
Type
II-
Man
gane
secu
resy
stem
Serv
ice
tem
p:-6
5°to
200°
F(-
54°
to+
93°
C)
Peel
stre
ngth
:10
inlb
wid
th(m
in)
No
corr
osio
nin
hibi
tors
Res
ists
fuel
,oi
l,an
dhy
drau
licflu
id.
TO 1-1-691
6-15
Tabl
e6-
1.Se
alin
gC
ompo
unds
-C
onti
nued
Spec
ifica
tion
Type
sA
vaila
ble
Prop
ertie
sIn
tend
edU
seSA
E-A
MS3
277
(MIL
-S-2
9574
),Se
alin
gC
ompo
und,
Poly
thio
-et
her,
for
Air
craf
tSt
ruct
ures
,Fu
elan
dH
igh
Tem
pera
ture
Res
ista
nt,
Fast
Cur
ing
atA
m-
bien
t(R
oom
)Te
mpe
ratu
rean
dL
owTe
mpe
ratu
res
Cla
ssA
(thi
n)-
for
brus
hap
-pl
icat
ion
Two
com
pone
ntM
ultip
urpo
seai
rcra
ftst
ruct
ure
and
inte
gral
fuel
tank
seal
-an
tsw
ithra
pid
ambi
ent
(roo
m)
and
low
tem
pera
ture
curi
ngca
pabi
litie
s.U
seof
man
ufac
ture
rsre
com
men
ded
prim
eris
requ
ired
prio
rto
appl
ying
this
seal
ant
for
prop
erad
hesi
on.
Type
Ica
nbe
used
asan
alte
rnat
efo
rSA
EA
MS-
S-88
02(M
IL-S
-88
02)
infu
elta
nkap
plic
a-tio
nsan
dTy
peII
can
beus
edas
anal
tern
ate
for
MIL
-PR
F-81
733.
Type
I,N
oco
rros
ion
inhi
bito
rsin
term
itten
tus
eto
+40
0°F
(204
°C
)G
rade
A,
Gen
eral
use,
fuel
tank
san
dai
rcra
ftst
ruct
ures
Gra
deA
1,A
mbi
ent
orim
med
iate
heat
cure
afte
rap
plic
atio
nat
tem
psup
to35
0°F
(175
°C
)C
lass
esB
&C
only
Gra
deB
(enh
ance
dcr
aze
resi
stan
cefo
rai
rcra
ftac
rylic
tran
spar
enci
es)
Cla
ssB
(thi
ck)
-fo
rse
alan
tgu
nor
spat
ula
Low
(dow
nto
+20
°F/
-7°
C)
and
ambi
ent
(roo
m)
tem
pera
ture
curi
ng;
Type
I,G
rade
A1
only
-ca
nbe
heat
cure
dat
tem
pera
-tu
res
upto
+35
0°F
(+17
5°C
)
Type
II,
Cor
rosi
onin
hibi
tive
in-
term
itten
tus
eto
360°
F(1
82°
C)
Cla
ssC
(sem
i-th
ick)
-ex
tend
edas
sem
bly
times
for
fayi
ngsu
rfac
ese
alin
g
Serv
ice
tem
p:-8
0°to
+30
0°F
(-68
°to
+15
0°C
)w
ithin
ter-
mitt
ent
use
to+
400°
(+20
4°C
)fo
rTy
peI
and
+36
0°F
(+18
2°C
)fo
rTy
peII
Peel
stre
ngth
:20
inlb
wid
th(m
in)
Cor
rosi
onin
hibi
ting
-Ty
peII
only
Type
Iha
sno
corr
osio
nin
hibi
tors
Res
ists
fuel
,oi
l,an
dhy
drau
licflu
id.
TO 1-1-691
6-16
Tabl
e6-
1.Se
alin
gC
ompo
unds
-C
onti
nued
Spec
ifica
tion
Type
sA
vaila
ble
Prop
ertie
sIn
tend
edU
seM
IL-A
-461
46,A
dhes
ive
-Se
al-
ants
,Si
licon
e,R
oom
Tem
pera
-tu
reV
ulca
nizi
ng(R
TV
),N
on-
corr
osiv
e(f
orus
ew
ithSe
nsiti
veM
etal
san
dE
quip
-m
ent)
Gro
upI
-G
ener
alpu
rpos
eO
neco
mpo
nent
Con
veni
ent
one
com
pone
nt,
nonc
orro
sive
,R
TV
silic
one
seal
ant
for
use
with
sens
itive
met
als
and
equi
pmen
t.N
otto
beus
edw
here
resi
stan
ceto
fuel
s,oi
ls,
orhy
drau
licflu
ids
isre
quir
ed.
Che
ckm
anuf
actu
rer’
sin
stru
ctio
nsfo
rpr
imer
requ
irem
ents
onth
em
etal
subs
trat
ebe
ing
seal
ed,
and
appl
yth
esp
eci-
fied
prim
erbe
fore
appl
ying
the
seal
ant.
Gro
upII
-H
igh
stre
ngth
Roo
mte
mpe
ratu
recu
reG
roup
III
-H
igh
tem
pera
ture
,ea
chgr
oup
has
two
type
s.Se
rvic
ete
mp:
-70°
to+
400°
F(-
57°
to+
204°
C)
for
Gro
ups
I&
IIan
d-7
0°to
+60
0°F
(-57
°to
+31
6°C
)fo
rG
roup
III
Type
I-
Thi
xotr
opic
past
ein
lbs
Peel
stre
ngth
:G
roup
I,Ty
peI:
15in
lbs
wid
th(m
in),
Type
II:
4in
lbs
wid
th(m
in),
Gro
ups
II&
III:
(bot
hty
pes)
:40
inlb
sw
idth
(min
)Ty
peII
-Se
lf-l
evel
ing
liqui
dN
oco
rros
ion
inhi
bito
rsL
ong
shel
flif
eSh
ort
cure
time
SAE
AM
S32
55,
Seal
ing
Tape
,Po
lyte
trafl
uoro
ethy
lene
,E
x-pa
nded
(EPT
FE)
Oil
and
Wat
erR
esis
tant
;(S
kyfle
x(®
))
Cla
ss1:
Con
tinuo
usR
ibbe
d,in
clud
es:
Skyfl
ex®
PN’s
:Pr
efor
med
gask
etta
pew
ithno
adhe
sive
onei
ther
side
exce
ptas
note
din
“Int
ende
dU
se”
colu
mn
Seal
ing
offa
ying
surf
aces
,ac
cess
/rem
ovab
lepa
nels
,flo
orbo
ards
,an
dw
ind-
scre
ens.
Not
for
fuel
soak
edor
very
high
tem
pera
ture
appl
icat
ion.
Non
haza
rdou
sal
tern
ativ
eto
low
adhe
sion
,tw
oco
mpo
nent
seal
ants
.So
me
ofth
ese
seal
ing
tape
sha
vea
low
peel
stre
ngth
adhe
sive
onon
esi
deto
hold
the
tape
inpl
ace
onon
esu
r-fa
cew
hile
the
mat
ing
part
isbe
ing
inst
alle
d.
GU
A-1
071-
1-
for
fay
surf
aces
≤1in
wid
eN
om
ixin
g,m
aski
ng,
orcu
ring
requ
ired
GU
A-1
001-
1-
for
fay
surf
aces
≤1in
wid
eSe
rvic
ete
mp:
-65°
to+
450°
F(-
54°
to+
232°
C)
with
shor
tte
rmex
posu
reto
600°
F(3
15°
C)
GU
A-1
001-
2-
for
fay
surf
aces
≤1in
wid
ew
here
thic
ker
tape
isne
eded
tofil
lfa
ysu
r-fa
cega
p
Peel
stre
ngth
:2
lb/in
wid
th(m
ax)
for
side
with
adhe
sive
only
GU
A-1
017-
1-
for
fay
surf
aces
≤1in
wid
eN
oco
rros
ion
inhi
bito
rs
TO 1-1-691
6-17
Tabl
e6-
1.Se
alin
gC
ompo
unds
-C
onti
nued
Spec
ifica
tion
Type
sA
vaila
ble
Prop
ertie
sIn
tend
edU
seG
UA
-140
1-1
-fo
rfa
ysu
rfac
es≤1
inw
ide
indr
yar
eas
offlo
orbo
ards
and
whe
rea
thic
ker
tape
isne
eded
tofil
lfa
ysu
rfac
ega
ps
Res
ists
wat
er,
fuel
,oi
l,an
dhy
-dr
aulic
fluid
GSC
-21-
8076
7-00
-fo
rfa
ysu
rfac
es<
1in
inhi
ghm
ois-
ture
area
sof
floor
boar
dsan
dw
here
thic
ker
tape
isne
eded
tofil
lfa
ysu
rfac
ega
psC
lass
2:C
ontin
uous
Non
-R
ibbe
d,in
clud
es:
Skyfl
exPN
’sG
UA
-100
3-1
-fo
rco
mpe
nsa-
tion
tape
ana
rrow
un-r
ibbe
dta
peus
edto
fill
irre
gula
ritie
son
ase
alin
gsu
rfac
eor
repa
irm
inor
dam
age
toa
prev
i-ou
sly
appl
ied
tape
seal
GU
A-1
057-
1-
for
fay
surf
aces
<1
inw
ide,
used
assh
im/
barr
ier
tore
sist
min
orch
af-
ing
GU
A-1
058-
1-
for
fay
surf
aces
<1
inw
ide,
used
asa
shim
/ba
rrie
rto
resi
stm
inor
chaf
-in
gG
UA
-105
9-1
-fo
rfa
ysu
rfac
es>
1in
wid
e,us
edas
shim
/ba
rrie
rto
resi
stm
inor
chaf
-in
gG
UA
-130
1-1
-fo
rfa
ysu
rfac
e<
1in
wid
ew
ithth
ick
gaps
TO 1-1-691
6-18
Tabl
e6-
1.Se
alin
gC
ompo
unds
-C
onti
nued
Spec
ifica
tion
Type
sA
vaila
ble
Prop
ertie
sIn
tend
edU
seA
v-D
ec®
HiT
ak®
Poly
uret
hane
Tape
Seal
ant
(PN
HT
3935
-7-
XX
X)
Pref
orm
edga
sket
tape
with
adhe
-si
veon
both
side
san
dth
inpo
lyet
hyle
nere
leas
efil
mon
one
side
For
fay
surf
ace
seal
ing
ofar
-ea
sw
here
fluid
intr
usio
nis
apr
oble
msu
chas
airc
raft
floor
pane
lsan
dca
rgo
tiedo
wn
fittin
gs.
For
max
imum
seal
ing,
rem
ove
the
rele
ase
film
for
adhe
sion
tobo
thsu
rfac
es.
For
easi
erpa
nel
rem
oval
and
max
imum
reus
-ab
ility
,le
ave
the
rele
ase
film
inpl
ace
onth
esi
deco
ntac
t-in
gth
ere
mov
able
pane
l.D
amag
edse
ctio
nsof
the
tape
are
easi
lyre
pair
edas
itha
sve
rygo
odad
hesi
onto
itsel
f.
-100
for
fay
surf
aces
≤1in
wid
eN
om
ixin
g,m
aski
ng,
orcu
ring
requ
ired
-150
for
fay
surf
aces
≤1in
upto
1.5
inw
ide
Serv
ice
tem
p:(8
5°to
+27
5°F
(65°
to+
135°
C)
will
with
-st
and
shor
tno
n-co
ntin
uous
expo
sure
tohi
gher
tem
pera
-tu
res
-200
for
fay
surf
aces
>1.
5in
upto
2in
wid
ePe
elst
reng
th:
1-4
inlb
wid
th
-250
for
fay
surf
aces
>2
inup
to2.
5in
wid
eN
oco
rros
ion
inhi
bito
rs
Res
ists
wat
er,
deic
ing
fluid
s,fu
el,
oil,
and
hydr
aulic
fluid
(inc
lud-
ing
Skyd
rol
LD
-4)
TO 1-1-691
6-19
Tabl
e6-
1.Se
alin
gC
ompo
unds
-C
onti
nued
Spec
ifica
tion
Type
sA
vaila
ble
Prop
ertie
sIn
tend
edU
seA
v-D
ec®
HiT
ak®
Tuf
Seal
TM
Poly
uret
hane
Tape
Seal
ant
(PN
HT
3000
-XX
X)
Pref
orm
edga
sket
tape
with
adhe
-si
veon
one
side
and
ape
rma-
nent
Teflo
nfil
mba
ckin
gon
the
oppo
site
side
For
fay
surf
ace
seal
ing
ofno
n-pe
rman
ent
stru
ctur
esu
chas
acce
ssan
din
spec
tion
pane
ls/
cove
rson
airc
raft
,m
issi
les,
and
equi
pmen
tto
prev
ent
fluid
entr
yin
toth
efa
ying
surf
ace
area
san
dth
eca
vi-
ties
over
whi
chth
epa
nels
/co
vers
are
inst
alle
d.T
heTe
flon
back
ing
ishi
ghly
abra
sion
resi
stan
tan
dpe
r-m
itssl
ight
mov
emen
tof
the
cove
rsw
ithou
tda
mag
ing
the
stru
ctur
eto
whi
chit
isat
-ta
ched
.T
heta
peis
very
du-
rabl
e,so
itm
aybe
reus
edm
any
times
once
itis
in-
stal
led,
and
dam
aged
sec-
tions
are
easi
lyre
pair
edas
itha
sve
rygo
odad
hesi
onto
itsel
f.
-100
for
fay
surf
aces
≤1in
wid
eN
om
ixin
g,m
aski
ng,
orcu
ring
requ
ired
-150
for
fay
surf
aces
>1
inup
to1.
5in
wid
eSe
rvic
ete
mp:
(85°
to+
275°
F(6
5°to
+13
5°C
)-2
00fo
rfa
ysu
rfac
es>
1.5
inup
to2
inw
ide
Peel
stre
ngth
:2-
5in
lbw
idth
ad-
hesi
vesi
deon
ly,
the
othe
rsi
deha
sa
perm
anen
tTe
flon
film
back
ing
No
corr
osio
nin
hibi
tors
Res
ists
wat
er,
deic
ing
fluid
s,fu
el,
oil,
and
hydr
aulic
fluid
(inc
lud-
ing
Skyd
rol
LD
-4)
Av-
Dec
®Se
lfL
evel
ingT
MG
reen
(PN
HT
3326
-5-X
XX
)an
dT
hixo
flex
Ora
nge
Inje
ctab
le(P
NT
F221
9)Se
alan
ts
Self
Lev
elin
gG
reen
-fo
rfil
ling
void
san
d/or
cavi
ties
onho
ri-
zont
alsu
rfac
esw
here
ase
lf-
leve
ling
liqui
dm
aybe
used
;su
pplie
din
eith
er50
CC
(-05
0)or
200
(-20
0)ca
r-tr
idge
s
Two
com
pone
ntse
alan
ts;
both
are
supp
lied
indu
alsy
ring
esco
ntai
ning
the
requ
ired
amou
nts
ofre
sin
and
hard
ener
for
mix
ing
onsi
te
The
Self
Lev
elin
gTM
Gre
ense
alan
tis
inte
nded
tofil
lvo
ids/
cavi
ties
onho
rizo
ntal
surf
aces
such
asai
rcra
ftse
attr
ack
depr
essi
ons
topr
even
tflu
ids
from
accu
mul
atin
gin
them
and
caus
ing
corr
osio
nw
hile
still
bein
gea
sily
re-
mov
edfo
rre
quir
edin
spec
-tio
nsan
d/or
oper
atio
nal
use.
Als
ous
eful
tofil
lca
vitie
sar
ound
ante
nna
conn
ecto
rs.
Thi
xofle
xTM
Ora
nge
-fo
rfil
l-in
gvo
ids/
cavi
ties
onho
ri-
zont
al,
vert
ical
,or
over
head
surf
aces
whe
rea
past
em
ate-
rial
isre
quir
ed;
supp
lied
in50
CC
cart
ridg
es
Mix
ing
and
disp
ensi
ngis
acco
m-
plis
hed
with
acce
ssor
ies
ob-
tain
edfr
omth
eve
ndor
per
the
vend
or’s
inst
ruct
ions
Serv
ice
tem
p:-6
0°to
+26
0°F
(-51
°to
+12
7°C
)(e
ither
type
)
TO 1-1-691
6-20
Tabl
e6-
1.Se
alin
gC
ompo
unds
-C
onti
nued
Spec
ifica
tion
Type
sA
vaila
ble
Prop
ertie
sIn
tend
edU
sePe
elst
reng
th:
both
1-4
inlb
wid
thT
heT
hixo
flexT
MO
rang
ese
al-
ant
isin
tend
edfo
rfil
ling
the
sam
evo
ids/
cavi
ties
asab
ove
asw
ell
asth
ose
onve
rtic
alan
dov
erhe
adsu
rfac
esw
hile
still
bein
gea
sily
rem
oved
for
requ
ired
insp
ectio
nsan
d/or
oper
atio
nal
use.
No
corr
osio
nin
hibi
tors
Res
ists
wat
er,
deic
ing
fluid
s,fu
el,
oil,
and
hydr
aulic
fluid
(inc
lud-
ing
Skyd
rol
LD
-4)
TO 1-1-691
6-21
6.6 SEALANT APPLICATION PROCEDURES.
• Solvents are flammable. Never use near igni-tion sources, i.e. lighted cigarettes, electricalarcing, heat sources, etc.
• When cleaning an area prior to applying a seal-ant, apply a small amount of solvent to a cleancloth, wipe the surface, and follow by wipingwith a clean, dry cloth. Immediately after use,place used rags into an appropriate HAZMATcontainer, and then dispose of per local direc-tives. This minimizes exposure of personnel toand release of solvent vapors into the environ-ment.
• Sealants, with the exception of SAE AMS 3255(Skyflex®) EPTFE and Av-Dec® sealant tapes,are toxic to the skin, eyes, and respiratory tract.Wear rubber or polyethylene gloves and chemi-cal proof goggles and/or face shield when us-ing these materials and make sure ventilation isadequate in the area where they are used. Washhands thoroughly with soap and water beforeeating or smoking.
• MIL-PRF-81733 is not suitable for use on theinterior of integral fuel tanks and shall not beused for these applications. SAE AMS-S-8802(MIL-S-8802) and SAE-AMS3277 (MIL-S-29574) are the authorized sealants for the inte-rior of integral fuel tanks.
• No RTV sealant which produces acetic acid,such as those conforming to MIL-S-46106,shall be used on aircraft. No RTV sealant shallbe used in areas where exposure to fuels andoils will be encountered. If RTV sealants arerequired by the structural repair manual, ensurethat the sealant conforms to MIL-A-46146, Ad-hesives/Sealants, Silicone, RTV, Noncorrosive(for use on sensitive metals and equipment),and/or is listed in Appendix A as being a non-corrosive RTV silicone sealant.
• SAE AMS-S-8802 (MIL-S-8802) sealantshould not be exposed to fuel or overcoateduntil it is tack-free as it will not cure properly.SAE AMS-S-8802 is used to fillet and brushseal on the interior of integral fuel tanks only.
• Do not use SAE AMS 3267 (MIL-S-8784) seal-ant in high temperature areas or for permanentstructural installations. These sealants have nohigh temperature resistance and very low peelstrength. Some typical uses of SAE AMS 3267(MIL-S-8784) sealants include sealing aircraftfloor panels and plates and fuel tank inspectionplates.
6.6.1 Cleaning. If the surfaces have been contaminatedfollowing corrosion removal and surface treatment per in-structions in Chapter 5, clean the area with a clean CCC-C-440, Type I or II, Class 2 cheesecloth, an SAE AMS 3819,Class 2, Grade A cleaning cloth, or a CCC-C-46, Type I,Grade 7 non-woven cleaning cloth saturated with eitherA-A-59281, Type I or SAE AMS 3166 solvent. Begin at thetop of the area to be sealed and work downward. Dry thesurfaces immediately with a clean cloth. Do not allow sol-vent to evaporate from the surface because it will allow someor all of the oil, dirt, etc., to redeposit, making it impossibleto remove with a dry cloth. Use a stiff, bristle brush to cleanaround bolts, rivets, etc. Always use clean cloth as each newarea is cleaned.
NOTE
Always pour solvent on the cloth to avoid con-taminating the solvent supply. Reclaimed solventsor soiled cleaning cloths shall not be used. Aftersurface treatment, do not contaminate areas to besealed with soiled hands or tools.
6.6.2 Masking. To prevent sealant from contacting adja-cent areas during application and smoothing out operations,the surrounding area not being sealed can be masked offwith AMS-T-21595, Type I masking tape. (Refer Figure 6-8).In cases where the tape is likely to remain in place for morethan two days on items exposed to direct sunlight and wheretape residue on the surface cannot be tolerated, use AMS-T-22085, Type II (3M Co., PN 481 or 225) preservation andsealing tape. Masking tape is very useful during fillet sealingof exterior surface lap and butt seams.
Table 6-2. Time Requirements for Sealants When Used at 75° F (24° C) and 50% RH
Specification Type or Class1 Assembly Time(Hr)
Tack-FreeTime (Hr)
Approximate FlyAway Time (Hr)
Application Meth-od(s)
MIL-PRF-81733(supersedes MIL-S-81733)
I, CL 2-¼ - 4 - Brush
TO 1-1-691
6-22
Table 6-2. Time Requirements for Sealants When Used at 75° F (24° C) and 50% RH - Continued
Specification Type or Class1 Assembly Time(Hr)
Tack-FreeTime (Hr)
Approximate FlyAway Time (Hr)
Application Meth-od(s)
I-½ CL1-16CL2-8
- Brush
I-2 - CL1-24CL2-16
- Brush
II, CL 1-1/16 - 4 - Gun or spatulaII-¼ - CL1-8
CL2-1- Gun or spatula
II-½ - CL1-16CL2-2
- Gun or spatula
II-2 - CL1-24CL2-12
- Gun or spatula
II-4 - 32 - Gun or spatulaIII-1 - 8 - SprayIV-4 8 40 - Brush or spatulaIV-12 24 120 - Brush or spatulaIV-24 48 180 - Brush or spatulaIV-40 120 600 - Brush or spatulaIV-48 168 1008 - Brush or spatula
SAE AMS-S-8802(supersedes MIL-S-8802)
A-½ - 10 40 Brush
A-1 - 20 55 BrushA-2 - 40 72 BrushB-½ - 10 30 Gun or spatulaB-1 - 20 55 Gun or spatulaB-2 - 40 72 Gun or spatulaB-4 - 48 90 Gun or spatulaC-12 12 - - Brush or spatulaC-20 20 96 - Brush or spatulaC-80 80 120 - Brush or spatulaC-96 96 - - Brush or spatula
SAE AMS 3276(supersedes MIL-S-83430)
A-½ - 10 30 Brush
A-2 - 24 72 BrushA-4 - 36 90 BrushB-¼ - 6 16 Gun or spatulaB-½ - 10 30 Gun or spatulaB-1 - 12 36 Gun or spatulaB-2 - 24 72 Gun or spatulaB-4 - 36 90 Gun or spatulaB-6 - 48 120 Gun or spatulaB-12 - 120 240 Gun or spatulaC-½ - 10 30 Brush or spatulaC-2 - 24 72 Brush or spatulaC-8 20 96 120 Brush or spatulaD-¼ - 6 16 Gun or spatulaD-½ - 10 30 Gun or spatula
TO 1-1-691
6-23
Table 6-2. Time Requirements for Sealants When Used at 75° F (24° C) and 50% RH - Continued
Specification Type or Class1 Assembly Time(Hr)
Tack-FreeTime (Hr)
Approximate FlyAway Time (Hr)
Application Meth-od(s)
E 6 120 240 Used w/auto rivetequipment
PR-1773 (super-sedes PR-1403G)
B-½ - 4 6 Gun or spatula
PRC-DeSoto Int. B-2 - 8 16 Gun or spatulaSAE AMS 3267/1
(supersedes MIL-S-8784)
A-½ - 10 24 Brush
SAE AMS 3267/3(supersedes MIL-S-8784)
A-2 - 24 72 Brush
SAE AMS 3267/2(supersedes MIL-S-8784)
B-½ - 10 24 Gun or spatula
SAE AMS 3267/4(supersedes MIL-S-8784)
B-2 - 24 72 Gun or spatula
SAE AMS 3374/1(supersedes MIL-S-38249)
1- N/A - 6 14 days Gun or spatula
SAE AMS 3374/2(supersedes MIL-S-38249)
2-4 - 24 7 days or 1 day @120° F (49° C)
Gun or spatula
SAE AMS 3374/3(supersedes MIL-S-38249)
3-4 - 6 14 days Gun or spatula
SAE AMS 3374/4(supersedes MIL-S-38249)
4-½ - 2 7 days Gun or spatula
MIL-S-85420 Ty I, C1A-1/6 - 2 (ST), 4(LT)2
4 (ST), 8 (LT)2 Brush
Ty I, C1B-1/6 - 2 (ST), 6(LT)2
4 (ST), 8 (LT)2 Gun or spatula
Ty II, C1A-1/6 - 2 (ST), 4(LT)2
4 (ST), 6 (LT)2 Brush
Ty II, C1B-1/6 - 1 ¼ (ST), 4(LT)2
4 (ST), 6 (LT)2 Gun or spatula
SAE-AMS3277 A-¼ - 1 / 3 / 6 1.5 / 4 / 83 Brush(MIL-S-29574) A-½ - 1.5 / 3 / 63 3 / 8 / 163 Brush
A-2 - 9 14 BrushB-¼ - 1 /3 / 63 1.5 / 4 / 83 Gun or spatulaB-½ - 2 / 6 / 63 3 / 8 / 163 Gun or spatulaB-2 - 9 14 Gun or spatulaC-4 8 - 24 Brush or spatula
MIL-A-46146 Gp I, Ty I - 5 - Gun or spatulaGp I, Ty II - 5 - PourGp II, Ty I - 5 - Gun or spatulaGp II, Ty II - 5 - PourGp III, Ty I - 5 - Gun or spatulaGp III, Ty II - 5 - Pour
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Table 6-2. Time Requirements for Sealants When Used at 75° F (24° C) and 50% RH - Continued
Specification Type or Class1 Assembly Time(Hr)
Tack-FreeTime (Hr)
Approximate FlyAway Time (Hr)
Application Meth-od(s)
SAE AMS 3255EPTFE SealingTape (Skyflex®)
Class 1 - 0 0 Peel and stick
Av-DecTM
HT3935-7 &HT3000 Series
Class 2 - 0 0 Peel and stick
Polyurethane Seal-ing Tapes
- - 0 0 Peel and stick
Av-DecTM Inject-able Polyure-thane Sealants
SelfLevelingTM
Green,HT3326-5
<20 (minutes) 45 (minutes)max
- Gun with syringe
ThixoflexTM Or-ange, TF2219
<3 (minutes) 7 (minutes)max
- Gun with syringe
1 The number after the dash (-) indicates the room temperature working life of the sealant after it is mixed.2 (ST) = Standard Temperature of +75° F (+24° C); (LT) = Low Temperature of +45° F (+7° C).3 1st # @ +75° F (+24° C); 2nd # @ +40° F (+4° C); 3rd # @ +20° F (-7° C).
6.6.3 Adhesion Promoters. In some cases, it may benecessary to improve the adhesion of sealants by the use ofadhesion promoters. Adhesion promoters are solvents thatcontain additives which leave a residue on the surface aftersolvent evaporation to promote adhesion. To apply, clean thearea per Paragraph 6.6.1, brush or wipe the surface to besealed with the liquid solution, and allow the treated surfaceto dry by evaporation without touching the treated areas for30 minutes to an hour before applying sealant. AMS 3100adhesion promoter, PN PR-148 or PR-182 is essential to re-pairing integral fuel tanks where new polysulfide sealant willbe applied over aged, fuel soaked polysulfide sealant. If apolythioether sealant is to be applied over a polysulfide seal-ant, PN PR-186 is recommended for use at the sealant inter-face. If the surface becomes contaminated or sealant is notapplied within 2 hours after applying an adhesion promoter,reclean the area and reapply the adhesion promoter per theabove instructions. Refer to Appendix A for informationrelative to purchasing/ordering these adhesion promoters.
6.6.4 Brush Spatula or Caulking Gun Application. Priorto masking and sealing, prepare and clean the surface inaccordance with Paragraph 6.6.1.
Do not contaminate areas to be sealed with hands,tools, etc., after surface treatment and primer ap-plication.
a. To prevent sealant from contacting adjacent areas dur-ing application and smooth out, outline the areas beingsealed with masking tape, AMS-T-21595, Type I sothat each tape strip is 1/16 to 3⁄8 in from the edge ofbutt seams and the upper surface edge of a lap seam,and ¼ to 3⁄8 in from the lower surface edge of a lapseam. If tape residue on these surfaces is excessive,remove adhesive residues using TT-N-95 aliphaticnaphtha. Masking may be very beneficial during filletsealing of exterior surface lap seams and filling exte-rior surface butt seams.
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b. Apply sealant between the pieces of tape.
(1) Thick sealants may be applied with a non-metal-lic spatula or spreader to fillet seal lap seams orflush fill butt seams as shown in Figure 6-8. Avoidthe entrapment of air. Work sealant into recessesby sliding the edge of the spatula firmly back overrecesses. Smoothing will be easier if the non-me-tallic spatula is first dipped in water.
(2) Brushable sealants are applied with a brush andsmoothed until the desired thickness is reached.
(3) Thick sealants may be applied with a caulkinggun, and if done carefully, will not usually re-quire masking. This method is especially adapt-able to filling seams or the application of form-in-place gaskets. On exterior surfaces whereaerodynamic smoothness is required, masking isnecessary to allow smoothing the sealant after ap-plication without smearing it onto surroundingsurfaces.
c. Remove masking tape after the sealant has been ap-plied and before it begins to set. Cure time depends onthe application life of the sealant materials used, thetemperature, and the RH. When sealant no longer feelstacky, prime and topcoat as necessary and required bysystem specific technical data per application instruc-tions in TO 1-1-8.
d. Remove all uncured sealant residue by wiping the areawith an SAE AMS 3819, Class 2, Grade A, or equiva-lent, cleaning cloth wetted with a liquid product knownas Sky Wash® distributed by AeroSafe Products Inc.and wiping dry with a clean, dry cloth of the sametype.
NOTE
MEK conforming to ASTM D 740 may be used asan alternate solvent for cleaning up uncured seal-ant residues as long as it is not environmentallyprohibited and the aircraft SPD and/or the missileor equipment SPM approves its use and requires itin system specific technical data.
6.6.5 Spray Gun Application. Prior to masking and seal-ing, prepare surface in accordance with Paragraph 6.6.1.
If any dirt or oil residues accumulate after conver-sion coating, clean thoroughly with solvent to en-sure adequate adhesion of paint, primer, and seal-ant.
a. Mask off adjacent areas with either MIL-PRF-121,Type I or II or MIL-PRF-131, Class 1 barrier materialheld in place with AMS-T-21595, Type I masking tapeto minimize overspray on adjacent areas.
b. Apply MIL-PRF-81733, Type III sprayable sealant in asolid, continuous pattern per the manufacturer’s in-structions and TO 1-1-8.
NOTE
The dry film thickness (DFT) of spray sealantcoatings shall be in the range of 3 to 5 mils (0.003to 0.005 in).
6.6.6 Peel and Stick Application; SAE AMS 3255EPTFE Skyflex® and Av-Dec® HT3935-7 and HT3000Sealing Tapes. Prior to application, prepare surface in ac-cordance with Paragraph 6.6.1.
After surface treatment and any required primerapplication, do not contaminate areas to be sealedwith soiled hands or tools as contamination pre-vents proper sealing tape adhesion.
a. Examine faying surfaces to be sealed and build up anyuneven areas on the aircraft, missile, or equipmentframe flange. Use Skyflex®, PN GUA-1003-1 com-pensation tape or a small piece of the same type ofSkyflex® tape that will be used for SAE AMS 3255sealing tape applications and a small piece of the same
Figure 6-8. Non-Metallic Spatula
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type of Av-DecTM tape that will be used for HT3935-7and/or HT3000 sealing tape applications. This willcreate a level faying surface for panel sealing.
b. Select the proper PN sealant tape so that it will coverthe full width of the faying surface to be sealed. Tapemay be applied to either the aircraft, missile, or equip-ment frame flange or to the panel faying surface.
(1) Measure and cut the required length of sealanttape.
(2) For corners, cut the ends of the tape at a 30°angle so that the sealant tape from the convergingside will overlap by one-quarter to one-half inch.Do not fold the tape in corners as this will resultin triple layer thickness.
Use care not to pull or stretch the sealant tape as itis applied. The stretched SAE AMS 3255 EPTFEand Av-Dec® HT3000 tapes will retract even ifclamped between faying surfaces and the Av-Dec®HT3935-7 tapes will be reduced in thickness. Ineither case, inadequate sealing may result.
(3) Peel the non-stick backing paper off the sealanttape a little at a time as the tape is applied to theaircraft, missile, or equipment frame flange ormating panel surface.
NOTE
• Applying a small amount of extra pressure tothe upper surface of the sealant tape will causethe pressure sensitive adhesive to adhere betterto the faying surface on which it is being ap-plied and it will create indentations/discolor-ation at the fastener holes allowing for easierlocation/identification. If done with Av-Dec®3935-7 sealant tapes, it must be done beforethe non-stick backing paper is removed.
• If an SAE AMS 3255 sealant tape without apressure sensitive adhesive backing has beenordered for use in areas where fluid exposure isexpected, 3M Co., PN Scotchgrip® 847 or 1099plastic adhesive (refer to Appendix A), may beused to hold the sealing tape in place duringpanel installation.
(4) After applying the full length of the sealant tape,run fingers back and forth on the upper surface ofthe sealant tape to press the tape against the air-craft, missile, or equipment frame flange or theaccess panel surface to promote adherence of theadhesive.
NOTE
For Av-Dec® HT3935-7 sealant tapes, this mustbe done before the non-stick backing is removed.
(5) Puncture all fastener holes using an object with asharp point such as an awl or a scribe.
NOTE
As fasteners are installed, the sealant materialpushed into the fastener holes will help to sealagainst moisture intrusion.
(6) Install the access door/panel.
NOTE
No curing time is required. All fasteners should bewet installed with MIL-PRF-16173, Grade 4;MIL-PRF-63460 CPC material specified in thespecific aircraft, missile, or equipment system spe-cific maintenance manual.
6.7 SEALING OF SPECIFIC AREAS.
6.7.1 Faying Surface Sealing. Faying surfaces are sealedby applying sealants to the connecting surfaces of two ormore parts. (Refer to Figure 6-9). It is a very effective sealand should be used for all assembly or reassembly. Whenpossible, it should be used in conjunction with fillet sealing.There are two types of faying surface seals, removable andpermanent. Removable seals are used around access doors,removable panels, inspection plates, etc. A removable sealcan be formed using a low adhesion sealant that adheres toboth surfaces or by using a high adhesion sealant that ad-heres to one surface and a parting agent on the mating sur-face. Permanent seals are created using high adhesion seal-ants between permanently fastened structures. To create apermanent seal, coat either one or both mating surfaces witha high adhesion sealant before assembling the parts and thenassembling them while the sealant is still wet. Apply enoughsealant to force a bead to squeeze out along the joint afterassembly and also install all fasteners wet with the sealant.Assemble parts within the rated application life and/or as-sembly life of the sealant while taking into account the ef-fects of temperature and humidity on these times.
a. For permanent structure, all faying surfaces, seams,and lap joints outside of fuel wet and high temperatureareas shall be protected with MIL-PRF-81733, Type IIor IV, Class 1 or 2, Grade A sealant. Apply the sealingcompound to one or both surfaces and squeeze the parttogether to ensure the complete coating of the entiremating or faying surface. Excess material squeezed outshall be removed so that the fillet remains at the jointedges. The fillet width shall not be less than ¼ inch.For seams, the sealant shall fill the seam entirely up toflush with the surface. Joint, joggle, or cavity areas
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which could hold water shall be filled with MIL-PRF-81733, Type II, Class 1 or 2, Grade A, SAE AMS-S-8802, Class B, or SAE AMS 3276, Class B sealant.
b. If sealing is impossible because of mechanical or otherfactors, prime both surfaces with two coats of MIL-PRF-23377, Type I, Class C epoxy primer or TT-P-2760, Type I, Class C polyurethane primer per instruc-tions in TO 1-1-8.
c. Faying surfaces that are to be adhesive bonded shall betreated and processed as specified by the approvedbonding procedure in the applicable system specificmaintenance manual.
d. On faying surfaces, seams, or joints which require dis-assembly for maintenance, either SAE AMS 3267 orPN PR-1773 low adhesion sealant shall be used. (PNPR-1773 sealant contains non-chromate corrosion in-hibitors).
NOTE
SAE AMS 3255 (Skyflex®) sealing tapes or Av-Dec® HT3935-7 and HT3000 sealing tapes maybe used in lieu of the low adhesion curing typesealants in many removable joint areas requiring
periodic disassembly for maintenance when ap-proved by the aircraft SPD and/or the missile orequipment SPM.
e. On plastic components, the joints shall be suitablysealed and faired into the adjacent surfaces with MIL-PRF-81733, Type II or IV, Class 1 or 2, Grade A, SAEAMS-S-8802, Class B, or SAE AMS 3276 sealant, un-less otherwise specified in the applicable system spe-cific maintenance manuals, to stop the formation ofpockets which will entrap moisture, dirt, etc.
NOTE
MIL-PRF-81733, Type II or IV, Class 1 or 2,Grade A sealant shall be used for rivets that re-quire wet installation on plastic components.
6.7.2 Fillet Sealing. The fillet, or seam, as shown in Fig-ure 6-10, is the most common type found on an aircraft,missile, or piece of equipment. Fillet seals are used to coverstructural joints or seams along stiffeners, skin butts, walls,spars, and longerons, and to seal around fittings and fasten-ers. This type of sealing is the most easily repaired. It shouldbe used in conjunction with faying surface sealing and inplace of it if the assembly sequence restricts the use of fay-ing surface sealing.
6.7.3 Injection Sealing. This type of seal, as shown inFigure 6-11, is used primarily to fill voids created by struc-tural joggles, gaps, and openings. Use only those sealantsrecommended by the aircraft, missile, or equipment manu-
facturer. Force sealant into the areas using a sealant gun.This method is a means of producing a continuous seal where
Figure 6-9. Faying Surface Sealing
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it becomes impossible to lay down a continuous bead ofsealant while fillet sealing. Clean the voids of all dirt, chips,burrs, grease, and oil before injection sealing.
6.7.4 Fastener Sealing. Figure 6-12 illustrates techniquesused to seal different types of fasteners. Fasteners are sealedeither during assembly or after assembly. Install them wetwith sealant in accordance with requirements in the appli-cable system specific maintenance manual for fasteners inpermanent structures. To seal during assembly, apply thesealant to the hole or dip the fastener into sealant, and installfastener while sealant is wet. For removable parts, coat thelower side of the fastener head only. Do not coat the hole orthe fastener shank or threads, as this makes future removalalmost impossible without damage to the part. To seal afterassembly, cover the pressure side of the fastener with sealantafter installation. Corrosion damaged areas in the counter-sinks around removable and fixed fasteners may be filledwith the fastener in place. Cadmium coated fasteners thathave been blasted or abraded during corrosion removal shallbe primed in accordance with the applicable system specificmaintenance manual and TO 1-1-8 and then coated withMIL-PRF-81733, Type I, Class 1 or 2, Grade A sealant.
6.7.5 Integral Fuel Cells/Tanks and Removable FuelTanks. Refer to TO 1-1-3 and/or the aircraft’s system spe-cific maintenance manual for fuel area sealing procedures.
6.7.6 Form-In-Place (FIP) Gasket Sealant Repair. Af-ter removal of all loose sealant material, thoroughly cleanthe area to be resealed per Paragraph 6.6.1. Areas of the oldseal to which new sealant will be added must be cleaned andabraded using an abrasive mat or abrasive cloth (refer toAppendix A), to expose a clean, fresh surface.
a. Apply MIL-PRF-81733, Type II-½, Class I, Grade A,PR-1773, Class B-½, or SAE AMS 3276, Class B-½sealant, preferably with a sealant gun. The new sealantshould match the configuration of the removed sealantbut should be of sufficient depth to ensure contact withthe mating surface.
b. Apply a very thin film of MIL-PRF-32033 oil or VV-P-236 petrolatum to the mating surface of the accessdoor/panel and close and/or install the access door/panel. If installed with fasteners, lubricate them withthe same material used on the door/panel mating sur-face, install ½ of the required fasteners (every otherfastener), and torque to ½ to ¾ of the specified torquefor the assembly.
Figure 6-10. Typical Fillet Seal
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c. Do not open or remove the door/panel for a minimumof 24 hours.
NOTE
The main function of the pressure sensitive adhe-sive backing on the SAE AMS 3255 (Skyflex®)sealant tape is to hold the EPTFE sealant tape inplace during access door/panel assembly. The ad-hesive on one side of the Av-Dec® HT3000 seal-ant tape acts as a seal as well as holding the seal-ant tape in place. Peeling/delamination of theadhesive from the aircraft, missile, or equipmentframe flange or access door/panel requires replace-ment of the sealant tape if the tape is no longerlocated in the faying surface. Visually inspect seal-ant tape material for nicks, cuts, gouges and de-lamination/separation.
6.7.7 SAE AMS 3255 EPTFE (Skyflex®) and Av-Dec®HT3000 and HT3935-7 Sealing Tape Gasket Repair. Inorder to preserve seal integrity, it is necessary to inspect thesealant tape each time an access panel is removed.
NOTE
Av-Dec® HT3935-7 sealing tape requires com-plete replacement each time an access door/panelsealed with it is removed as it has an adhesive onboth sides. Scrape the old tape off with a plastictool and apply a new length of tape as done origi-nally.
a. Cut and remove damaged section of sealant tape.
b. Measure and cut a new piece of SAE AMS 3255 (Sky-flex®) or Av-Dec® HT3000 sealant tape approximatelyone inch longer than the removed section.
c. Peel the non-stick backing paper off and install a newsection of sealant tape so it overlaps the previouslyinstalled sealant tape by one-quarter to one-half of aninch on each side of the repair site.
NOTE
Ends of the repair splice must overlap the existingsealant tape to ensure seal integrity. Use care notto pull or stretch the sealant tape patch as it isapplied. The stretched SAE AMS 3255 EPTFE andAv-Dec® HT3000 sealant tape patches will retracteven if clamped between faying surfaces and in-adequate sealing may result.
d. Once the sealant tape patch is applied, run fingers backand forth on the upper surface of the sealant tape patchto promote adherence of the adhesive.
NOTE
Applying a small amount of extra pressure to theupper surface of the sealant tape patch will causethe pressure sensitive adhesive to adhere better tothe faying surface and overlapped areas of oldsealant tape and it will create indentations/discol-oration at the fastener holes allowing for easierlocation/identification.
Figure 6-11. Typical Injection Seal
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e. Puncture any affected fastener holes with a sharppointed object such as an awl or a scribe.
NOTE
As fasteners are installed, the sealant materialpushed into the fastener holes will help seal againstmoisture intrusion.
f. Install access panel.
NOTE
No curing time is required. All fasteners should bewet installed with MIL-PRF-16173, Grade 4 CPC,MIL-PRF-63460 CPC, or CPC material specifiedin the specific aircraft, missile, or equipment sys-tem specific maintenance manual.
6.7.8 External Aircraft Structure. If, during normal main-tenance, it becomes necessary to remove and replace compo-nents (wing planks, skin, spar caps, fasteners, fittings, etc.,)they shall be sealed when reinstalled, even if they were notsealed originally. The only exception to this requirement is atemporary repair accomplished for a one time flight to a de-pot or overhaul facility. Refer to Figure 6-13 through Figure6-16 for typical sealing methods.
6.7.9 Depressions. When the thickness of metal is re-duced by more than 15 mils (0.015 in) in the removal ofcorrosion damage, fill the depression with MIL-PRF-81733,Type II, Class 1 or 2, Grade A sealant after applying achemical conversion treatment per Section II of Chapter 5.
NOTE
The above procedure does not apply to the use ofSAE AMS 3255 EPTFE and Av-Dec® HT3935-7or HT3000 sealing tapes or to the use of SAEAMS-S-8802 (MIL-S-8802) sealant inside integralfuel tanks.
6.7.10 Damaged Sealant. Many areas on aircraft, mis-siles, and equipment are sealed either at the factory or bydepots during rework. Fresh sealant shall be applied when-ever the previously applied sealant is damaged. Remove thedamaged sealant with a plastic scraper and, if necessary, pre-pare the metal surface in accordance with Section II ofChapter 5. Slightly roughen a strip of the undamaged sealantapproximately one inch wide around the boundary of thestripped area with an A-A-58054, Type I, Grade C abrasivemat and then clean the area per Paragraph 6.6.1. Apply the
Figure 6-12. Typical Methods of Sealing Fasteners
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new sealant by brush, sealant gun, or spatula and then smoothout the surface with a spatula, as required. The new sealantshould overlap onto the roughened area of the old sealant.
NOTE
• To assist with removal of damaged sealant, aliquid product known as Sky Restore® distrib-uted by AeroSafe Products Inc., (refer to Ap-pendix A), may be applied to the damaged areawith a non-metallic bristle brush, an SAE AMS3819, Class 2, Grade A, or equivalent, cleaningcloth, or a pump spray bottle and allowed todwell for 15 to 50 minutes until the sealant issoftened. A plastic scrapper may then be usedto remove the damaged sealant. This materialhas a fairly obnoxious odor so it must be usedeither in a well ventilated area or personnelmust wear an appropriate respirator in all con-fined areas.
• After the damaged sealant is scrapped away,the area must be neutralized and cleaned with aliquid product known as Sky Wash® distrib-uted by AeroSafe Products Inc., (refer to Ap-pendix A), applied in the same manner as above,scrubbed with the same type of brush or clothas used above, and wiped dry.
• Other tools useful for sealant removal are the3M Co. SR Radial Bristle Discs and plastic SRCutters, the Kell-Strom Tool Co., OZ7000pneumatic sealant removal kit, The RDS001Rapid Desealing System (RDS), OZ7006manual sealant removal kit or a rubber palmsupport handle with a set of plastic scrapers.(Refer to Appendix B).
6.7.11 Extensive Repair. If corrosion damage is so ex-tensive that structural repair is necessary, all faying surfacesbetween patches (or doublers) and skins shall receive a sur-face treatment per Section II of Chapter 5 before the repairparts are installed. Coat the faying surfaces with MIL-PRF-81733, Type IV, Class 1 or 2, Grade A sealant prior to instal-lation of patch and install all fasteners wet with MIL-PRF-81733, Type I or IV, Class 1 or 2, Grade A sealant.
6.7.12 High Temperature Areas. In areas where the tem-perature is expected to rise above 250° F (121° C), a one-part silicone sealant, MIL-A-46146, Type I or III or SAEAMS 3374, Type 1, 2, 3, or 4 silicone sealant should be usedfor temperatures up to +400° F (+204° C). SAE AMS 3276(MIL-S-83430) sealant may be used in areas that experienceintermittent temperatures up to +360° F (+182° C). Applica-tion of these sealants is by spatula or sealant (caulking) gunper Paragraph 6.6.4.
6.7.13 Low Temperature Curing. When cold climates in-terfere with sealing operations by prolonging the sealant cur-ing reaction, use MIL-S-85420 or SAE-AMS3277 (MIL-S-29574). For better adhesion, an adhesion promoter can beused. Refer to Paragraph 6.3.3. SAE AMS 3255 EPTFE andAv-DecTM HT3935-7 or HT3000 sealant tape gasket materi-als may be used for low temperature sealing operations whenspecified in system specific technical data and/or is approvedby the aircraft SPD and/or the missile or equipment SPM.
6.8 STORAGE/SHELF LIFE CONTROL OF SEAL-ANTS.
All sealants have a specified shelf life. The date of manufac-ture and the shelf life are listed on each container. The shelflife is dependent on storing the sealant in its original, un-opened container in an area where the temperature does notexceed 80° F (27° C). Sealants shall not be stored in areaswhere the temperature exceeds 80° F (27° C). Prior to use,sealant containers shall be inspected to determine if the ma-terial has exceeded its shelf life. If a sealant has exceeded itsoriginal shelf life, then it shall not be used until the updatetesting has been performed. Sealants may be extended one-half of their original shelf life after passing the required tests.Updating may be repeated until sealant fails to pass testing.No sealant shall be used if it fails testing. Minimum updatetesting can be performed as follows:
a. Select one kit of sealant from each manufacturer’sbatch of material to be tested for updating.
b. Visually examine the content of each can in the kit. Ifthe base polymer is lumpy or partially cured or cannotbe mixed with the curing agent, dispose of the openedkit and all kits from that batch of sealant.
c. If the kit can be blended to form a homogeneous mix-ture, determine whether the working time is suitablefor the intended purpose by applying the mixture to aclean scrap of metal. If the working time is not accept-able, dispose of the opened kit and all others from thatbatch.
d. If the working time is acceptable, the applied sealantshall be tested for proper cure time by periodicallychecking its hardness. The batch of sealant representedby applied test sealant can be extended one-half itsoriginal shelf life if it achieves approximately the samehardness as sealant from kits of another batch whichare within their established shelf life.
e. This updating process may be repeated until the seal-ant fails to pass any of the above tests.
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Figure 6-13. Typical Lap Skin Sealing
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Figure 6-14. Sealing Procedures for Typical Aircraft Fitting
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Figure 6-15. Typical Spar Cap Sealing
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Figure 6-16. Sealing of Access Doors
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CHAPTER 7TREATMENT OF SPECIFIC AREAS
7.1 INTRODUCTION.
This chapter describes the procedures recommended fortreating and protecting against corrosion in several specificareas known to be corrosion prone areas and contains illus-trations to aid in inspections. This chapter is not all inclu-sive. Applicable system specific maintenance manuals forspecific aircraft, missiles, and/or equipment should be con-sulted also to determine all corrosion prone areas on a spe-cific system, and the required treatment and preventive mea-sures in these areas as well as any existing expanded oramplified instructions for areas covered by this chapter.
7.2 BATTERY COMPARTMENTS, BOXES, AND AD-JACENT AREAS.
Observe precautions listed in previous chapters (orreferences) for cleaning compounds, solvents, sur-face treatments, sealants, and paints as these ma-terials can injure personnel if used improperly.
The battery, battery cover, battery box, and adjacent areas(especially areas below the battery compartment where bat-tery electrolyte may have seeped) are subject to the corro-sive action of the battery electrolyte. Two different types ofbatteries are encountered on aerospace and non-aerospaceequipment: lead-acid, having a sulfuric acid electrolyte andnickel-cadmium, having a potassium hydroxide electrolyte.Methods for cleaning up and neutralizing spilled and/orleaked electrolytes are given in Table 3-2.
7.2.1 Preparation of Solutions for Cleaning and Neu-tralizing Battery Electrolytes.
• When handling electrolytes, chemical splashproof goggles and chemical resistant rubbergloves and aprons shall be worn. If any electro-lyte contacts the skin or eyes, flood the affectedarea immediately with water and report to theBase Medical Facility. An emergency showerand an eye wash station in the area where workinvolving electrolytes is being performed arerequired.
• Isopropyl alcohol, TT-I-735 is highly flam-mable. Use only in a well ventilated area andkeep away from all sources of ignition.
Both sulfuric acid and potassium hydroxide bat-tery electrolytes will cause severe corrosion ofmetallic structures. Avoid dripping electrolyte onor allowing contaminated gloves, rags, sponges,etc., to come in contact with aircraft, missile, orequipment structures. Place all items contaminatedwith electrolyte in a leak-proof plastic containerprior to removing them from the area of the air-craft, missile or piece of equipment. Remove anybattery box which contains spilled electrolyte fromthe aircraft, missile, or piece of equipment prior tocleaning it. Electrolyte spilled on aircraft, missileor equipment structure shall be cleaned up as soonas possible after it has been detected.
NOTE
The use of indicating solutions can sometimes beavoided and/or at least limited in scope by usingtest strips of litmus paper. When trying to initiallydetect electrolyte spills from acid batteries (suchas lead-acid), apply a strip of blue litmus paper tothe wet surface. A color change to red indicates anacid is present. When trying to detect spills fromalkaline batteries (such as nickel-cadmium), applyred litmus paper to the wet surface. A color changeto blue indicates an alkaline solution is present.
There are four different solutions needed for the detection,neutralization, and cleanup of spilled and/or leaked batteryelectrolytes. Indicating solutions (litmus solution for lead-acid batteries and bromothymol blue solution for nickel-cad-mium batteries) are required for cleaning areas subjected toelectrolyte spills to determine the location of contaminatedareas and to indicate if these areas have been completelyneutralized. A 10% by weight sodium bicarbonate (ordinarybaking soda) solution is required to neutralize sulfuric acidfrom lead-acid batteries and a 3% by weight boric acid ormonobasic sodium phosphate solution is required to neutral-ize potassium hydroxide from nickel-cadmium batteries.These solutions are prepared per the following procedures:
7.2.1.1 Litmus Indicating Solution. Pour one pint of amixture containing 70% by volume of TT-I-735 isopropylalcohol and 30% by volume distilled water into a plasticspray bottle with a hand squeeze pump. Add one tablespoonof litmus powder into the solution, and mix thoroughly untila deep blue color is observed.
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7.2.1.2 Bromothymol Blue Indicating Solution. Pour onepint of bromothymol blue solution into a plastic bottle with ahand squeeze pump. Using an eye dropper, add one drop at atime of phosphoric acid into the solution with subsequentmixing after each drop until the color of the solution changesfrom blue to gold or amber.
7.2.1.3 Sodium Bicarbonate Neutralizing Solution.Pour one pint of distilled water into a 500ml polyethylenewash bottle, add ¾ of an ounce of ASTM D 928 sodiumbicarbonate powder, and mix thoroughly.
7.2.1.4 Boric Acid and/or Monobasic Sodium Phos-phate Neutralizing Solutions. Pour one pint of distilledwater into a 500ml polyethylene wash bottle, add ¾ of anounce of either A-A-59282 boric acid powder or ANSI/AWWA B504 monobasic sodium phosphate powder, and mixthoroughly.
7.2.2 Cleaning and Neutralizing Procedures.
a. Determine the type of electrolyte involved by dippinga small strip of blue and a small strip of red litmuspapers into the liquid puddle. If the red litmus staysred and the blue litmus turns red, the liquid is acid. Ifthe blue litmus stays blue and the red litmus turns blue,the liquid is basic or alkaline.
b. Remove any standing liquid or puddles with a squeezebulb type syringe, absorbent cloth, or sponge. Placethe used items in a leak proof container for disposal toprevent the contamination of other areas.
c. Spray the entire suspected area with the proper indica-tor solution, using the minimum amount needed to wetthe entire surface. For spills/leaks from lead-acid bat-teries, use the litmus solution which will change incolor from deep blue to a bright red in areas contami-nated by sulfuric acid. For spills/leaks from nickel-cadmium batteries, use the bromothymol blue solutionwhich will change in color from amber or gold to adeep blue in areas contaminated by potassium hydrox-ide.
d. Apply the correct neutralizing solution to the areaswhere the indicating solution has been applied. Forspills/leaks from lead-acid batteries, use a sodium bi-carbonate solution. For spills/leaks from nickel-cad-mium batteries, use either a boric acid or monobasicsodium phosphate solution. Ensure that the area is wellsaturated including all seams and crevices where elec-trolyte could collect. Use care to prevent neutralizingsolutions from spreading to adjacent areas and on air-craft, ensure that bilge area drains are open. Allow flu-ids to flow overboard from these drains on aircraft.Allow the neutralizing solution to remain on the sur-face for at least 5 minutes or until all bubbling actionceases, whichever is longer.
NOTE
When neutralizing sulfuric acid, the litmus indi-cating solution will change back from its brightred color to a light blue as the neutral point isreached. When neutralizing potassium hydroxide,the bromothymol blue indicating solution willchange back from its deep blue color to a lightamber color as the neutral point is reached.
e. Rinse the area thoroughly with a liberal amount ofclean tap water and remove any standing liquid orpuddles, as specified in step b.
f. Reapply the indicator solution, as in step c. If the so-lution does not change color, rinse the area, as in stepe and dry the area with clean cloths or rags. If thesolution changes color, repeat step d and step e.
g. Remove any corrosion noted per procedures in SectionI of Chapter 5, apply conversion coating treatment perprocedures in Section II of Chapter 5, apply sealantspecified by the applicable system specific maintenancemanual and Chapter 6 using procedures in Chapter 6,and apply primer and paint coatings per the applicablesystem specific maintenance manual using proceduresin TO 1-1-8 if bare metal is exposed. If bare metal wasnot exposed, or when the paint system applied is curedto a tack-free state, apply a protective film of eitherMIL-PRF-81309, Type II or MIL-L-87177, Type I orII, Grade B CPC to the area.
7.2.3 Paint Systems. Special acid and/or alkali resistantcoatings are usually required for battery compartments,boxes, and areas. Refer to the applicable system specific air-craft, missile, or equipment maintenance manual for the spe-cific paint system requirements.
7.3 RELIEF TUBE AREAS.
O-D-1435 disinfectant solutions are highly alka-line and can burn the eyes and the skin. Wearchemical resistant splash proof goggles and/or faceshield and chemical resistant rubber gloves whenusing these solutions.
Interior and exterior relief tube areas shall be inspected andcleaned after each flight. Cleaning shall be accomplished byprocedures outlined in Chapter 3. After cleaning, the exposedareas shall be disinfected by wiping down with a cloth wet-ted with an O-D-1435 disinfectant solution prepared per themanufacturer’s instructions. The interior of the tubes shall bedisinfected by pouring the solution through them. Rinse thedisinfectant solution from the area with fresh tap water andwipe dry with a clean, dry cloth. After cleaning and disin
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fecting, remove any corrosion noted per procedures in Sec-tion I of Chapter 5. For areas having exposed bare metal,apply the type of conversion coating material required forthe specific metal alloy involved per procedures in Section IIof Chapter 5. Touch up the paint system in the area, as re-quired, with the primer and topcoat specified in the appli-cable system specific maintenance manual with applicationper procedures in TO 1-1-8.
7.4 CORROSION TREATMENT FOR STEELCABLES.
• Consult the applicable system specific mainte-nance manual for cable detensioning and ten-sioning requirements prior to performing anymaintenance.
• Do not use metallic wools to clean installedsteel control cables. The use of metallic woolwill cause dissimilar metal particles to becomeembedded in the cables and create further cor-rosion problems (galvanic corrosion). Use onlya clean cloth dampened with A-A-59601, MIL-PRF-32295, Type II, or MIL-PRF-680, degreas-ing solvent to clean steel control cables. Exces-sive solvent will remove internal cable lubricantand allow the cable strands to abrade and fur-ther corrode.
If the surface of a cable is corroded, relieve cable tensionand carefully force the cable open by reverse twisting. Visu-ally inspect the interior. Corrosion on the interior strandsconstitutes failure and the cable must be replaced. If no in-ternal corrosion is detected, remove loose external rust andcorrosion with a clean, dry, coarse-weave rag or fiber brush.Clean the control cables with a clean cloth dampened withA-A-59601, MIL-PRF-32295, Type II, or MIL-PRF-680,degreasing solvent. After thorough cleaning, apply a thin filmof either MIL-PRF-81309, Type II, MIL-L-87177, Type I orII, Grade B, or MIL-PRF-16173, Class II, Grade 3 waterdisplacing CPC to the cable surface by aerosol spray or acloth dampened with the CPC followed by a liberal applica-tion of MIL-PRF-16173, Class II, Grade 4 CPC with a non-metallic brush. Wipe off any excess CPC. If excessive CPCis allowed to build up, it will interfere with the operation ofcables at fairleads, pulleys, or grooved bell-crank areas.
7.5 PIANO TYPE HINGES.
Corrosion inhibiting solid film lubricants are often applied tohinge pins and nodes to provide lubrication and to reducecorrosion problems. Refer to Section II of Chapter 3 for pro-cedures on touch-up and replacement of these lubricantswhen hinges are disassembled. Each time an aircraft, missileor piece of equipment is washed, make sure that all hingesare cleaned in accordance with Chapter 3. After washing,apply a coating of a water displacing CPC. Use either MIL-
PRF-63460, MIL-PRF-81309, Type II, or MIL-L-87177,Type I or II, Grade B followed by MIL-PRF-32033 to thenode and hinge pin areas of all piano hinges including thosecoated with solid film lubricants.
7.6 INTEGRAL AND EXTERNAL FUEL TANKS ANDDROP TANKS.
For additional instructions on materials and procedures usedin aircraft fuel tank areas. Refer to TO 1-1-3.
7.6.1 Corrosion Removal and Rework of Pitted Areasof Integral Fuel Tanks. Complete removal of corrosionproducts is required to prevent recurrence of corrosion in theaffected areas.
Power abrasive removal operations create airborneparticles. Eye protection is required. Good generalventilation is normally adequate.
a. Remove corrosion by mechanical methods in Section Iof Chapter 5 using materials and procedures listed therefor aluminum alloys, except that abrasive blasting shallnot be used. In general, a power driven abrasive on aflexible shaft is the most effective means of corrosionremoval in this area. Corrosion removal shall be fol-lowed by hand sanding with 280 grit abrasive paper orcloth followed by 400 grit abrasive paper or cloth toproduce a smooth surface finish. The system specificaircraft -3 and -23 manuals shall be consulted to assurestructural limits are not exceeded.
To prevent injury to personnel, exercise cautionwhen using sharp or pointed tools.
b. After sanding operations are completed, clean abrasiveresidue off reworked areas with a clean cloth and in-spect for small shiny patches which appear muchbrighter than the base metal. These generally indicateexfoliation underneath the exposed shiny surface be-low a blister from which the top has been partiallyremoved. As the surface is being sanded during re-work, these blisters, being high points, receive most ofthe abrasive action, leaving the blister area muchbrighter than the surrounding base metal. To com-pletely remove this corrosion, the blisters must be bro-ken open to fully expose the exfoliation and powderycorrosion deposits underneath. It is usually much fasterand easier to pry the top off the blister with a sharpinstrument. This operation requires extreme caution toprevent unnecessary gouges or scratches in the basemetal. Pitted and exfoliated areas must be reworked toa depth sufficient to remove all the corrosion and the
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resulting depression must be blended into the surround-ing surface. All loosened material must be removedfrom the fuel tank by vacuuming prior to further treat-ment.
c. Abrade the bare metal reworked area to remove theoxide film which forms on it and the surface of theSAE AMS-C-27725 (MIL-C-27725) fuel tank coatingadjacent to the reworked areas to remove the glossfrom it with A-A-58054, Type I, Grade A abrasive mat.
A-A-59281 (MIL-C-38736) solvents are flam-mable and toxic to skin, eyes, and respiratory tract.Chemical resistant splash proof goggles and/orface shield and chemical resistant rubber glovesare required. Respirators are required when usingthis solvent in enclosed areas.
d. Clean the areas thoroughly to remove all residue, oil,and grease with a clean, lint free cloth conforming toeither A-A-2522, Grade A, Color 1, CCC-C-440, TypeI or II, or SAE AMS 3819, Class 2, Grade A wettedwith A-A-59281, Type I (MIL-C-38736, Type I) sol-vent. Do not allow solvent to dry by evaporation, wipethe area dry with a clean cloth to prevent redepositingthe soils on the surface.
e. Apply MIL-DTL-5541/MIL-DTL-81706, Class 1Aconversion coating to the reworked area per Section IIof Chapter 5.
PR-148 adhesion promoter is flammable and toxicto skin, eyes, and respiratory tract. Chemical orsplash proof goggles and rubber gloves are re-quired. Respirators are required when using thismaterial in enclosed areas.
f. Apply PR-148 (PRC-DeSoto Int. Corp.) adhesion pro-moter to the reworked area and the dulled area of thecoating around the reworked area and allow it to dryfor 30 minutes minimum to 2 hours maximum.
MIL-PRF-81733 sealants are moderately toxic toskin and body (if ingested). Wear chemical resis-tant gloves and avoid other skin contact. Washhands thoroughly before eating, drinking, or smok-ing after using these sealants.
g. Using an acid brush which has had the bristles clippedoff to half their original length, scrub MIL-PRF-81733,
Type I or II sealant onto the reworked area while mak-ing sure the sealant wets the entire area and overlapsslightly on to the dulled area of the coating around thereworked area. Add more sealant with the brush until aslight mound is formed and smooth the surface withthe brush.
h. Replace any fillet or brush coat sealant removed tofacilitate rework of a corroded area per instructions inTO 1-1-3.
Polyurethane coatings are flammable and toxic tothe skin, eyes, and respiratory tract. Chemical re-sistant splash proof goggles and/or face shield,chemical resistant rubber gloves, and an organicvapor face mask are required. Avoid all skin con-tact. Exhaust ventilation is required when usingthis material in enclosed spaces/areas. Keep allopen flames and any other sources of ignitionaway from the area in which this material is beingused.
i. When sealant applied in step g and step h above istack-free, overcoat the sealant with a MIL-C-83019clear flexible polyurethane coating. Overlap of thiscoating onto the dulled area of the SAE AMS-C-27725(MIL-C-27725) coating around the reworked area shallnot exceed ¼ inch.
7.6.2 Removal of Corrosion and Rework of AluminumExternal Fuel Tanks/Drop Tanks. Complete removal ofcorrosion products is required to prevent recurrence of cor-rosion in the affected areas.
7.6.2.1 Tank Exterior Surfaces.
Tanks which have contained fuel are hazardousuntil all vapors and residual fuel deposits havebeen removed. They are potential explosion andhealth hazards and should be treated as such. Re-fer to TO 1-1-3 for proper purging procedures.
Remove corrosion from these surfaces and rework the areaper the following procedure:
a. If painted, remove paint from area where corrosion issuspected per instructions in TO 1-1-8 such that a mar-gin of good metal around the suspected area is ex-posed.
b. Remove and treat corrosion using an appropriate me-chanical method in Section I of Chapter 5.
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c. Apply MIL-C-5441/MIL-DTL-81706, Class 1A con-version coating to bare metal areas per procedures inSection II of Chapter 5.
d. Touch up area from which paint was removed per in-structions in the applicable system specific -23 aircrafttechnical order using procedures in TO 1-1-8.
7.6.2.2 Tank Interior Surfaces. Remove corrosion fromthese surfaces and rework the area per the following proce-dure:
NOTE
The interior surface of aluminum alloy tanks shallnot be painted.
a. If a preservative mixture is present, remove it onlyfrom the immediate area requiring corrosion removaland treatment. Mix one part MIL-PRF-87937, Type IVcleaner with nine parts fresh tap water by volume. Ap-ply the cleaner solution to the area with a sponge, softbrush, or cloth. Scrub the area thoroughly, remove pre-servative, and rinse with fresh tap water. Use a clean,dry, lint free cloth to dry the area.
b. Remove and treat corrosion using an appropriate me-chanical method in Section I of Chapter 5, exceptabrasive blasting shall not be used.
c. Apply MIL-DTL-5541/MIL-DTL-81706, Class 1Aconversion coating to bare metal areas per proceduresin Section II of Chapter 5.
d. Per direction of TO 00-85A-03-1, preserve the interiorof assembled tanks by fogging with preservative orapplying it with a clean, lint free cloth soaked in apreservative solution. The preservative solution shallconsist of one part of MIL-C-6529, Type 1 CPC andthree parts of MIL-PRF-6081, Grade 1010 oil. If spray-ing the preservative to protect the entire tank interior,spray with a pressure spray that provides complete at-omization, and vent the tank at the farthest practicabledistance from the introduction point of the oil mixtureduring spraying operations. The amount of preserva-tive shall be a minimum of 0.12 CC per square foot ofinternal surface.
NOTE
• Tanks containing foam baffling shall not bepreserved.
• This preservative compound is compatible withgasoline and jet type fuels, so it need not beremoved before placing tank in service.
7.7 FAYING SURFACES AND ATTACHMENTPOINTS.
NOTE
Treat and process faying surfaces of parts, compo-nents, or structures which are assembled by adhe-sive bonding in accordance with the applicablesystem specific aircraft, missile, or equipmentmaintenance manual that covers adhesive bond-ing.
7.7.1 Faying Surfaces, Joints, and Seams. When re-pairs are made on equipment or accessories and/or compo-nents are installed or structures are reinstalled, the attachingor faying surfaces shall be protected by sealing all metal tometal and composite to metal contact surfaces. All perma-nent structures shall be installed with faying surfaces wetwith MIL-PRF-81733, Type I or IV, Class 1 or 2, Grade Asealant. All removable structures such as access doors, in-spection plates, floor panels and plates, and other removablepanels (components requiring frequent removal for mainte-nance requirements) shall either be installed with faying sur-faces wet with SAE AMS 3367, Class A or B or PR-1773,Class B sealant or with SAE AMS 3255 (Skyflex®) or Av-DecTM HT3935-7 or HT3000 sealant tape in the joints asspecified by the system specific maintenance manual. In ad-dition to faying surface sealing, fillet seal all critical interiorseams (those in corrosive areas such as aircraft bilges andlatrines) and all exterior seams (those exposed to the outsideenvironment) on permanent structure so that fillet is flushwith the surface for butt seams and fairs smoothly into theadjoining surface for lap seams using MIL-PRF-81733, TypeII, Class 1 or 2, Grade A sealant. Fillet seal all critical inte-rior and all exterior butt and lap seams on removable struc-tures that were faying surface sealed with SAE AMS 3367 orPR-1773 sealant in the same manner with SAE AMS 3267,Class B or PR-1773, Class B sealant. Refer to Chapter 6 foradditional details on sealant selection and application proce-dures. The coating system on all structures adjacent to thesealed seams and joints shall be touched up after sealantinstallation to match the surrounding structure in accordancewith the applicable system specific maintenance manual withapplication per TO 1-1-8 procedures.
7.7.2 Attaching Parts and Hardware. Attaching parts,such as nuts (standard, speed, and self-locking), bushings,spacers, washers, screws (standard and self-tapping), sleevesfor shake-proof fastener studs, clamps, bolts, etc., do notneed to be painted in detail except when dissimilar metal orwood contact is involved with the materials being joined orexposure to a corrosive interior environment or the exteriorenvironment will occur in service. However, all parts shallbe installed wet with sealant. For permanent installations,use MIL-PRF-81733, Type I or IV, Class 1 or 2, Grade Asealant and coat the entire mating surface of the parts. For
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removable installations, use SAE AMS 3367, Class A or PR-1773, Class B sealant and coat only the lower side of theheads of screws and bolts with sealant. For removable instal-lations, do not coat the threads and shanks of screws andbolts or the holes into which they are inserted because thiswill make future removal almost impossible without damag-ing the parts. As an alternate for removable installations, theshanks, threads, and lower side of the heads of standardscrews and bolts may be coated with MIL-PRF-63460, MIL-PRF-16173, Class II, Grade 3, or MIL-PRF-32033 CPC be-fore they are installed. Close tolerance bolts and parts shallbe coated with corrosion inhibiting, solid film lubricant. UseSAE AS5272 (MIL-PRF-46010, heat curing type) on non-aluminum parts when 400° F (205° C) ovens are available.Use MIL-L-23398 or MIL-PRF-46147 (air curing type) onaluminum parts and on all types of metallic parts when 400°F (205° C) ovens are unavailable. The solid film lubricantshall be applied and completely cured prior to assembly.(Refer to Section II of Chapter 3 for application and curingprocedures). Bolts shall be coated on shanks and threadsonly. A thin bead of sealant shall be applied under the bolthead to impart a wet seal. If possible, bolt head, nut, and boltend shall be fillet sealed after installation. MIL-PRF-81733,Type II, Class 1 or 2, Grade A shall be used for sealing.
NOTE
The following does not apply to parts which arelubricated in the joint areas immediately before orafter installation or to close tolerance bolts andparts which are removed frequently for mainte-nance requirements.
a. All rivets shall be installed wet with MIL-PRF-81733,Type I or IV, Class 1 or 2, Grade A sealant. In fuelcontact areas, the exposed rivet head and approxi-mately ¼ in of the adjacent structure shall be brush-over-coated with SAE AMS-S-8802 (MIL-S-8802),Class A sealant.
b. All machine screws, countersunk fasteners, bolts (headend), and nuts which are used in contact with magne-sium shall be installed with 5056 aluminum alloywashers. These parts, including the washers, shall beinstalled wet with MIL-PRF-81733, Type II, Class 1,Grade A sealant and shall be completely fillet sealedwith the same material after installation.
c. Adjustable parts, such as tie rod ends and turnbucklesshall be installed as follows:
(1) If possible, surfaces and threads shall be lubri-cated and protected before assembly with a filmof SAE AS5272 (MIL-PRF-46010, heat curingtype) or MIL-L-23398 or MIL-PRF-46147 (aircuring type) corrosion inhibiting, solid film lubri-cant which shall be completely cured prior to as-sembly. (Refer to Section II of Chapter 3 for ap-plication and curing procedures). Afterinstallation, apply a thin coating of DOD-L-25681
lubricant to all surfaces of these parts located inhigh temperature areas. Apply a thin coating ofMIL-PRF-63460, MIL-PRF-16173, Class II,Grade 3, MIL-PRF-32033, MIL-PRF-81309, TypeII, or MIL-L-87177, Type 1 or 2, Grade B waterdisplacing, CPC to all surfaces of these parts lo-cated in other lower temperature areas.
(2) If solid film lubricants cannot be applied, use athin coating of DOD-L-25681 lubricant on allsurfaces before and after assembly when locatedin high temperature areas. Apply a thin coating ofMIL-PRF-63460, MIL-PRF-16173, Class II,Grade 3, MIL-PRF-32033, MIL-PRF-81309, TypeII, or MIL-L-87177, Type 1 or 2, Grade B waterdisplacing, CPC after assembly when located inother lower temperature areas.
d. If possible, slip fit parts shall be assembled with mat-ing surfaces wet with MIL-PRF-81733, Type I or IV,Class 1 or 2, Grade A sealant. If not possible, coat theID of the holes in the receiving part, which is normallythe larger structure, with a corrosion inhibiting, solidfilm lubricant conforming to MIL-L-23398 or MIL-PRF-46147 (air curing types) and the OD of the mat-ing part with one conforming to MIL-PRF-46010 (heatcuring type) or one conforming to MIL-L-23398 orMIL-PRF-46147 (air curing types). The solid film lu-bricant shall be applied and completely cured prior toassembly. (Refer to Section II of Chapter 3 for appli-cation and curing procedures).
e. Press fit parts shall be installed with faying surfaces(the OD of the part and the ID of the hole) wet withMIL-PRF-81733, Type IV, Class 1 or 2, Grade A seal-ant and the edges of these parts shall be fillet sealedwith MIL-PRF-81733, Type II, Class 1 or 2, Grade Asealant after installation.
f. All cut edges and holes drilled or reworked for bolts,screws, rivets, studs, and bushings of aluminum alloyand magnesium alloy structures or parts shall receive achemical conversion coating treatment prior to the in-stallation of the fasteners or bushings and prior to in-stalling or refinishing the structure or parts. Apply aMIL-DTL-5541/MIL-DTL-81706, Class 1A chromateconversion coating to aluminum alloy parts and SAEAMS-M-3171 (MIL-M-3171), Type VI chromic acidbrush-on pretreatment to magnesium alloy parts perprocedures in Section II of Chapter 5.
7.7.3 Severely Corroded (Rusted) Hardware. Severelycorroded common hardware such as screws, bolts, and wash-ers should be replaced. Economic consideration shall begiven to replacement of other corroded screws, bolts, nuts,washers, etc., instead of cleaning and recoating or replating.However, major replacements should be accomplished dur-ing overhaul and/or scheduled depot maintenance. When aprotective coating, such as cadmium plating on bolts, screws,
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etc., is damaged, immediate action shall be taken to apply anappropriate protective finish to prevent corrosion (rusting).Refer to Section III of Chapter 3 for proper corrosion pre-ventative materials.
7.8 NATURAL AND SYNTHETIC RUBBER PARTS.
Natural and synthetic rubber shall not be painted or oiled. Asa general rule, grease should not be applied to rubber parts,but some parts, such as O-rings, require a grease coating(consult the appropriate system specific maintenancemanual). Many types of rubber are subject to fungus growth(e.g. mold, mildew) which can cause deterioration of therubber and corrosion of surrounding metal surfaces. If fun-gus is noted on rubber parts, clean the parts and remove thefungus per procedures in Section I of Chapter 3.
7.9 POTABLE WATER TANKS.
The interior surface of aluminum alloy potable water tanksshall not be painted or conversion coated. Remove corrosionby using the mechanical methods outlined in Section I ofChapter 5 and ensure all debris is removed.
7.10 SURFACES AND COMPONENTS EXPOSEDTO EXHAUST GASES, GUN GASES, AND ROCKETBLAST.
Residues from exhaust gases, gun gases, and rocket blast arevery corrosive and can cause deterioration of paint systems.Frequent cleaning of these areas to remove residue is re-quired and shall be accomplished in accordance with SectionI of Chapter 3.
7.11 ELECTRICAL AND ELECTRONIC EQUIP-MENT.
Avionic and electrical equipment are easily damaged by con-tamination with corrosion removal debris and by applicationof improper corrosion control materials. Many of the con-ventional corrosion treatment methods used on airframe,missile, and equipment structural components are also usedon areas adjacent to or supporting avionic equipment, elec-trical equipment, wire bundles, and other electrical parts.Personnel performing airframe corrosion control tasks on oraround this equipment shall be familiar with materials andprocedures used for corrosion prevention and control on
electrical and electronic equipment to ensure that no damageto electrical or avionic equipment will occur. For more spe-cific information, refer to TO 1-1-689 series, TO 00-25-234,TO 1-1A-14, and the specific system specific equipmentmaintenance manuals.
7.11.1 Grounding and Bonding Connections. After thegrounding or bonding connection has been made, overcoatthe entire connection, including all bare areas on the metalsurface, with MIL-PRF-81733, Type II, Class 1 or 2, GradeA sealant.
7.11.2 Conduit and Junction Boxes. Electrical conduit(exterior) and junction boxes (interior and exterior) shall beprimed with two coats of MIL-PRF-23377, Type I, Class Cepoxy primer or TT-P-2760, Type I, Class C polyurethaneprimer applied per procedures in TO 1-1-8. If corrosion isfound, remove it by mechanical methods outlined in SectionI of Chapter 5. Before applying the primer, apply a MIL-DTL-5541/MIL-DTL-81706, Class 1A chromate conversioncoating to aluminum alloy parts and SAE AMS-M-3171(MIL-M-3171), Type VI chromic acid brush-on pretreatmentto magnesium alloy parts per procedures in Section II ofChapter 5 to all reworked areas and any other bare metalareas.
7.11.3 Wires and Cables. Electrical wires and cableshaving plastic jacket insulation and/or braided wire exteriorshielding shall not be painted or coated except as requiredfor moisture and fungus proofing. Consult TO 1-1-689 se-ries, TO 1-1A-14, and TO 00-25-234 for additional informa-tion.
7.11.4 Deleted.
7.11.5 Moisture and Fungus Proofing of Electrical andElectronic Equipment. Consult TO 1-1-689, TO 1-1A-14,and TO 00-25-234 for information on fungus proofing thisequipment.
7.11.6 Antennas. Dissimilar metal (Galvanic) corrosionoften occurs at antenna attach points. Refer to TO 1-1-689series for repair information. Refer to the system specificmaintenance manuals for information on paint touch-up andfinishing. Apply paint and coatings per procedures in TO1-1-8.
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7.12 STRUCTURAL TUBING MEMBERS AND AS-SEMBLIES.
Only non-powered mechanical procedures and materialsspecified in Section I of Chapter 5 shall be used to removecorrosion on structural tubing. Reworked areas shall alwaysbe polished to a smooth surface, using 400 to 600 grit abra-sive mat, paper, or cloth as the final step in the corrosionremoval procedure. The following paragraphs outline gen-eral practices for the protection of structural tubing.
7.12.1 Structural Aluminum Alloy Tubing. Treat andpaint the exterior surfaces of all tubing and the interior sur-faces of open ended tubing closed off by riveted or boltedend surfaces with the finish system designated in the appli-cable system specific maintenance manual. Apply paint perprocedures in TO 1-1-8. All bolted or riveted caps or com-ponents shall be installed with faying surfaces and fastenerswet with MIL-PRF-81733, Type I or IV, Class 1 or 2, GradeA sealant. Interior surfaces of tubing closed by welded endplugs or components shall be coated with MIL-PRF-16173,Class II, Grade 2 or 4 CPC using the fill and drain method ofapplication through holes located near each end of the tubes.These holes shall subsequently be closed by installing blindrivets wet with MIL-PRF-81733, Type II, Class 1 or 2, GradeA sealant and overcoating the rivet head with the same ma-terial after installation.
7.12.2 Structural Magnesium Alloy Tubing. All surfacesof magnesium tubing shall be treated with a SAE AMS-M-3171 (MIL-M-3171), Type VI chromic acid brush-on pre-treatment coating per procedures in Section II of Chapter 5and painted with the finish system designated in the appli-cable system specific maintenance manual with applicationper procedures in TO 1-1-8. Install all parts onto the tubingwith all faying surfaces and fasteners wet with MIL-PRF-81733, Type I or IV, Class 1 or 2, Grade A sealant.
7.12.3 Structural Copper Alloys, Stainless Steel(CRES) Alloys, and Heat Resistant Alloy Tubing. Theinterior and exterior surfaces of these types of tubing do notrequire a finish system. However, to prevent galvanic corro-sion of other metals with which these types of tubing are incontact, install parts and attach tubing with faying surfacesand fasteners wet with MIL-PRF-81733, Type I or IV, Class1 or 2, Grade A sealant when located in areas not exposed tohigh temperatures or SAE AMS 3374, Type 1, 2, 3, or 4sealant for high temperature areas.
7.12.4 Structural Carbon Steel Tubing.
7.12.4.1 Exterior. All exterior surfaces of steel tubing as-semblies shall be finished with one coat of MIL-PRF-26915,Type I or II, Class A or B, zinc-rich primer, MIL-PRF-23377,Type I, Class C or MIL-PRF-85582, Type I, Class C2 epoxyprimer, or TT-P-2760, Type I, Class C polyurethane primer
followed by two coats of MIL-PRF-85285 polyurethane top-coat with the color as specified in the applicable system spe-cific maintenance manual. After corrosion (rust) is removedand before applying a primer, apply an appropriate MIL-C-10578 film per Section I of Chapter 5 or a MIL-C-8514 orDOD-P-15328 wash primer coating to bare metal areas perprocedures in TO 1-1-8. Apply primer and topcoat materialsper procedures in TO 1-1-8.
7.12.4.2 Interior. For tubing assemblies without weldedor crimped ends, coat all interior surfaces with MIL-PRF-23377, Type I, Class C epoxy primer or MIL-PRF-26915,Type I or II, Class A or B, zinc-rich primer using a fill-and-drain procedure. Where practical, in lieu of the fill-and-drainprocedure, two coats of primer may be spray applied to in-terior surfaces of all assemblies using a spray gun with anextension wand.
7.12.4.3 Sealing. After coating the interior, clean the ex-terior surfaces of all assemblies adjacent to holes in the tubewalls by solvent wiping to remove any oil, grease, or othercontamination. Seal all holes in tube walls by installing blindrivets in the holes wet with MIL-PRF-81733, Type II, Class1 or 2, Grade A sealant and overcoating the rivet heads withthe same material after installation. Assemble all tubing as-semblies manufactured by riveting or bolting members to-gether with fittings with faying surfaces and fasteners wetwith MIL-PRF-81733, Type I or IV, Class 1 or 2, Grade Asealant.
7.13 NON-STRUCTURAL TUBING MEMBERS ANDASSEMBLIES.
Use the same procedures and materials specified for corro-sion removal on structural tubing members and assembliesin Paragraph 7.12 to remove corrosion from non-structuraltubing.
7.13.1 Aluminum Alloy Tubing.
Do not use A-A-59601, MIL-PRF-32295, Type IIand/or MIL-PRF-680 degreasing solvents or othersolvents that are not oxygen compatible in areasinvolving oxygen storage, including transfer sys-tems, and on the surfaces of missiles using liquidpropellant. Failure to observe these precautionscan result in serious or fatal injury to personneland complete destruction of the equipment.
Protect aluminum tubing exposed directly to the outside en-vironment during either flight or ground operations by ap-plying the exterior finish system specified in the applicable
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system specific maintenance manual with application perprocedures in TO 1-1-8. Treat aluminum tubing according tothe following procedures:
a. Clean in accordance with Section I of Chapter 3.
b. Remove corrosion in accordance with Paragraph 7.12,using non-powered mechanical methods specified inSection I of Chapter 5.
c. Apply a MIL-DTL-81706, Class 1A chemical chromateconversion coating to all interior and exterior surfacesof tubing per procedures in Section II of Chapter 5,except coat only the exterior surfaces of oxygen lines.For new tubes, apply conversion coating to the entiretube after fabrication and prior to the installation. Ifcorrosion has been removed from tubing, apply con-version coating to all bare, reworked areas.
No paint or corrosion preventive compound shallbe applied to any tubular interior surface. Takenecessary precautions to prevent primer or paintfrom entering the interior areas of tubing. Wheredouble flares are used (e.g., on oxygen systems),cap the ends and apply the finish system after theflaring operation. Paint end fittings after installa-tion on the aircraft, missile, or equipment. Use ex-treme care to prevent contamination of interiorsurfaces of hydraulic, oxygen, and air speed indi-cator tubing during painting operations.
d. No paint or corrosion preventive compound shall beapplied to any interior surfaces of non-structural tub-ing. Apply the specified exterior finish system to allexterior surfaces or reworked areas of tubing exposedto the environment in the same sequence given abovefor structural aluminum tubing. Touch-up any coatingsystems damaged during tubing installation with thecoating system specified in the system specific mainte-nance manual with application per procedures in TO1-1-8.
7.13.2 Stainless Steel (CRES) Tubing.
• Do not use A-A-59601, MIL-PRF-32295, TypeII or MIL-PRF-680 degreasing solvents or other
solvents that are not oxygen compatible in ar-eas involving oxygen storage, including trans-fer systems, and on the surfaces of missiles us-ing liquid propellant. Failure to observe theseprecautions can result in serious or fatal injuryto personnel and complete destruction of theequipment.
• SAE AMS 3166 wipe solvent is flammable andtoxic to the skin, eyes, and respiratory tract.Eye and skin protection is required. Use onlyin a well ventilated area.
• Apply a small amount of SAE AMS 3166 sol-vent to a clean cloth and wipe the surface. Fol-low by wiping with a clean cloth or dry rag.This minimizes the amount of solvent used aswell as preventing redepositing contaminationon the surface.
• To control solvent odor, used rags should beimmediately placed in sealed plastic bags orcovered containers and disposed of in accor-dance with local directives.
Protect stainless (CRES) steel tubing exposed directly to theoutside environment, either during flight or ground opera-tions, by applying the exterior finish specified in the appli-cable system specific maintenance manual with applicationper procedures in TO 1-1-8. Austenitic (3XX series) stain-less (CRES) steels are highly susceptible to pitting, crevicecorrosion, and stress corrosion cracking when exposed tomoist, salt-laden air and when deposits of dirt and debris areallowed to collect on areas of the tubing covered by metalbrackets or parts. Treat stainless steel (CRES) tubing accord-ing to the following procedures:
a. Clean in accordance with Section I of Chapter 3.
b. Remove corrosion in accordance with Paragraph 7.12,using non-powered mechanical methods specified inSection I of Chapter 5.
c. Immediately before painting, wipe areas which will bepainted with a lint free cloth moistened with SAE AMS3166 wipe solvent and dry with a clean cloth. Do notallow drying by evaporation, since soils will redepositon the surface.
d. Apply the finish system specified for stainless steel(CRES) tubing in the system specific technical manu-als per TO 1-1-8 procedures.
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7.13.3 Cadmium Plated Steel Tubing.
• SAE AMS 3166 wipe solvent is flammable andtoxic to the skin, eyes, and respiratory tract.Eye and skin protection is required. Use onlyin a well ventilated area.
• Apply a small amount of SAE AMS 3166 sol-vent to a clean cloth and wipe the surface. Fol-low by wiping with a clean cloth or dry rag.This will minimize the amount of solvent usedas well as preventing redepositing contamina-tion on the surface.
• To control solvent odor, used rags should beimmediately placed in sealed plastic bags orcovered containers and disposed in accordancewith local directives.
Bare cadmium plating deteriorates rapidly when subjected toabrasion, most bases (alkalis) and acids, and marine, indus-trial, and very humid environments. It should always be pro-tected with a paint system to prevent corrosion. Treat cad-mium plated steel tubing in accordance with the followingprocedures.
a. Clean in accordance with Section I of Chapter 3.
b. Remove deteriorated plating and corrosion on basemetal (steel) in accordance with Paragraph 7.12, usingnon-powered mechanical methods specified in SectionI of Chapter 5.
c. Immediately before painting, wipe areas which will bepainted with a lint free cloth moistened with SAE AMS3166 wipe solvent and dry with a clean cloth. Do notallow drying by evaporation since soils will redepositon the surface.
d. Apply the specified finish system for steel tubing inthe system specific technical manuals per TO 1-1-8procedures.
7.13.4 Special Instructions for Tubing Fittings andSleeves. Corrosion often occurs on sleeves and their fittingsand/or on the tubing in contact with them due to the crevicespresent at their attachment points. Galvanic corrosion oftenoccurs because the type of sleeve or fitting chosen is notelectrochemically compatible with the tubing. When corro-sion is found on these areas or when tubing, fittings, or
sleeves are replaced, consult the applicable system specificmaintenance manual to determine the proper types of sleevesand fittings. Fillet seal all fittings located in areas which areinaccessible for inspection and refinishing during operationalservice at the joint area with MIL-PRF-81733, Type II, Class1 or 2, Grade A sealant at the time of installation and prior topainting. After sealant is tack-free, paint the tubing, fittings,and sealant as directed in tubing in the system specific tech-nical manuals per TO 1-1-8 procedures.
7.13.5 Removable Installations.
• Do not use MIL-PRF-16173 corrosion preven-tive compounds on any oxygen line fittings.These materials contain petroleum solvents thatare not Liquid Oxygen (LOX) compatible. Ex-plosion may occur if oxygen contacts these ma-terials and if the resulting mixture is subjectedto sudden pressure or impact. After installation,apply the exterior paint system specified in theapplicable system specific maintenance manualwith application per procedures in TO 1-1-8 toexposed tubing, sleeves, and back portions ofthe B nuts of these fittings and a LOX compat-ible grease/lubricant to the gap at the front endof the B nut and the adjacent tubing for a lengthof one inch.
• Provide adequate ventilation when using A-A-59601, MIL-PRF-32295, Type II and/or MIL-PRF-680 degreasing solvents. Avoid repeatedor prolonged skin contact of inhalation orvapors.
Do not apply the finish system on fittings and adjacent tub-ing for a distance of one inch from the back and front endsof the fittings on tubing areas requiring periodic removaland/or opening during service. Clean all old preservativecoatings and dirt from the fitting, sleeves, and tubing endswith a clean, lint free cloth wetted with either A-A-59601,MIL-PRF-32295, Type II, or MIL-PRF-680, degreasing sol-vent and wipe dry with a clean, dry, lint free cloth beforereinstalling tubing and tightening fittings. Except for oxygenline fittings, apply a MIL-PRF-81309, Type II, MIL-L-87177,Type I or II, Grade B, or MIL-PRF-16173, Class II, Grade 3water displacing, CPC by spray or brush to all fitting sur-faces after they are tightened, including the exposed areas ofthe sleeves and the unfinished areas of the tubing. Allow theCPC to dry for at least 1 hour and apply MIL-PRF-16173,
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Class II, Grade 4 or MIL-DTL-85054 CPC over the sameareas by spraying or brushing.
7.14 CORROSION REMOVAL FROM THIN METAL(0.0625 INCH THICKNESS AND LESS).
Do not allow metallic or corrosion particles tobuild up around the area being polished or on thepolishing tool (abrasive cloth or paper) during thepolishing operation. Damage to thin metal surfacesmay result.
Moderate to severe pitting and all intergranular and/or exfo-liation corrosion on thin metal requires removal by mechani-cal methods specified in Section I of Chapter 5 as appropri-ate for the type of metal involved. Use extreme care andconsult the applicable system specific maintenance manualfor structural damage limits when removing corrosion fromthin metal. When stains, surface corrosion, and mild pittingare found on thin structural skins (i.e., aircraft, missile, andequipment skins), chemical methods specified in Section I ofChapter 5, as appropriate for the type of metal involved, maybe used to remove the corrosion. In lieu of chemical corro-sion removal, the following convenient and effective me-chanical method for the removal of minor corrosion or stainson all metals may be used.
a. Mix ground SS-P-821, Grade F pumice powder abra-sive with clean tap water to form a paste. Using aclean, soft cloth (such as CCC-C-440 cheesecloth), ap-ply the paste to the area being treated and abrade thearea with a light rubbing motion.
b. When the pumice paste has dried to a white powder,wipe it off with a clean, dry, soft cloth. If corrosionproducts (observed as stubborn stains) still exist, use a600 grit wet or dry abrasive paper, cloth, or mat andwater to remove the remaining corrosion. Wipe cleanwith a clean, soft, dry cloth.
c. Refer to Section II of Chapter 5 for the required sur-face treatment on the type of metal involved andtouch-up the area with the finish system specified inthe applicable system specific maintenance manualwith application per procedures in TO 1-1-8.
7.15 AIR INTAKE DUCTS FOR JET AIRCRAFT.
Air intake ducts are fabricated from materials (usually 5000Series aluminum), which have high corrosion resistance.Certain components of these ducts may be cast aluminum ormagnesium. Frequent cleaning of the ducts is usually suffi-cient to preclude attack by corrosion. Aircraft performinglow level missions or take-offs and landings over salt water
or in highly saline atmospheres may require the ducts to bepainted to reduce corrosion attack. A requirement for a coat-ing as determined and/or recommended by the operating unitshall be coordinated with the MAJCOM Corrosion Manager,the aircraft SPD, and the Air Force Corrosion Prevention andControl Office (AFCPCO). The MIL-PRF-23377, Type I,Class C epoxy primer/MIL-PRF-85285 or APC polyurethanetopcoat paint system, color to match the surrounding area, isusually recommended for painting the ducts, but the finaldetermination of the coating to be used shall be made by theaircraft SPD in conjunction with the AFCPCO.
7.16 CLOSELY COILED SPRINGS.
Springs which are so tightly coiled that the areas betweenthe coils can not be plated or painted for corrosion protectionshall be coated with a MIL-PRF-81309, Type II, MIL-L-87177, Type I or II, Grade B, or MIL-PRF-16173, Class II,Grade 3 water displacing CPC applied by spraying or dip-ping and allowing it to dry for at least 1 hour. After drying, acoating of MIL-PRF-16173, Class II, Grade 4 CPC shall beapplied to the springs by spraying or dipping.
NOTE
These requirements do not apply to springs oper-ating in oil or hydraulic fluids.
7.17 CORROSION PREVENTION ON ASSEMBLIESAND PARTS REMOVED FROM AIRCRAFT DURINGMAINTENANCE, 30 DAY SHORT TERM STORAGE,AND OVER 30 DAY LONG TERM STORAGE RE-QUIREMENTS.
7.17.1 Short Term Storage. Short term storage is definedas any period up to 30 days for the purposes of this manual.When assemblies or parts are removed from the aircraft,missile, or equipment for repair, or to gain access to areas ofthe aircraft, missile, or equipment for maintenance, they shallbe treated to prevent corrosion prior to placement into shortterm storage. All items shall be stored indoors in a coveredarea to protect them from the elements. Refer to TO 1-1-17and the applicable system specific maintenance manual and(-17) storage manual for specific details on storage of a par-ticular part or assembly.
a. Assemblies or parts having bare metal surfaces, suchas internal and working surfaces on landing gear com-ponents, shall be properly lubricated or protected bycoating with the aircraft, missile, or equipment greases,hydraulic fluids, or oils normally applied in operationalservice.
b. High strength steel components which are stripped oftheir protective coatings shall have a film of MIL-PRF-81309, Type II, MIL-L-87177, Type I or II, Grade B,or MIL-PRF-16173, Class II, Grade 3 water displacing
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CPC applied to all bare surfaces whenever there is alapse of 2 hours or more in the rework cycle. The partshall then be loosely over-wrapped with MIL-PRF-121,Type II, Grade A, Class 1 barrier paper.
c. Completely painted parts need no other special protec-tive measures, except in marine or high humidity envi-ronments. In these cases, a MIL-PRF-81309, Type II,MIL-L-87177, Type I or II, Grade B, or MIL-PRF-16173, Class II, Grade 3 water displacing CPC shallbe applied to the part. The part shall then be looselyover-wrapped with MIL-PRF-121, Type II, Grade A,Class 1 barrier paper.
d. Prior to rework or reapplication of the required protec-tive coating, remove old CPC with solvent and reapplythe appropriate aircraft, missile, or equipment lubri-cant to areas requiring lubrication. The CPC compoundapplied to provide temporary protection shall not beused for lubrication in lieu of the appropriate lubricantspecified for use on a particular part or assembly.
7.17.2 Long Term Storage. If the storage of assembliesor parts will exceed 30 days, increased protective measuresare required, particularly on critical parts and high strengthsteel components. All items shall be stored indoors in a cov-ered area to protect them from the elements. Refer to TO1-1-17 and to the applicable system specific maintenanceand (-17) storage manuals for specific details on storage of aparticular part or assembly.
a. All bare metal surfaces and surfaces with damagedplating or paint, shall be coated with MIL-PRF-81309,Type II, MIL-L-87177, Type I or II, Grade B, or MIL-PRF-16173, Class II, Grade 3 water displacing CPCfollowed by application of a coating of MIL-PRF-16173, Class II, Grade 4 long term CPC. The part shallthen be over-wrapped with MIL-PRF-121, Type II,Grade A, Class 1 barrier paper.
b. Completely repainted parts need no other special pro-tective measures, except in marine or high humidityenvironments. In these cases, surfaces shall be coatedwith MIL-PRF-81309, Type II, MIL-L-87177, Type Ior II, Grade B, or MIL-PRF-16173, Class II, Grade 3water displacing CPC followed by application of acoating of MIL-PRF-16173, Class II, Grade 4 longterm CPC. The part shall then be over-wrapped withMIL-PRF-121, Type II, Grade A, Class 1 barrier paper.
c. Depending on the length of time in storage, reapplica-tion of CPC’s may be required. Refer to Section III ofChapter 3 for time limitation information on CPC’s.
d. Prior to returning the part or assembly to service, re-move CPC’s with solvent and reapply the appropriateaircraft, missile, or equipment lubricant to areas re-quiring lubrication. The CPC compound applied to
provide temporary protection shall not be used for lu-brication in lieu of the appropriate lubricant specifiedfor use on a particular part of assembly.
7.18 DEPLETED URANIUM COUNTERWEIGHTS.
Many aircraft control surfaces such as ailerons and elevatorsare equipped with counterweights fabricated from depleteduranium for mass balancing purposes. Depleted uranium isused because of its very high weight per unit of volume(density). To protect the depleted uranium from corrosion,many of the counterweights are plated with a copper strike,followed with a nickel strike, followed by a full thicknesscadmium plate and then overcoated with the organic finish(paint) system specified for the specific aircraft. These coun-terweights are usually impression stamped for identificationas follows; “Caution: Radioactive Material, Depleted Ura-nium, High Salvage Value, Manufactured by - - -, Fabrica-tion No. - - -, Finished Weight - - - lb. Unauthorized Altera-tions Prohibited.” All personnel shall observe the followingrequirements of the Nuclear Regulatory Commission relativeto depleted uranium.
To restrict radiation exposure to a maximum of10% of the Nuclear Regulatory Commission’s es-tablished limits for radioactive materials workersand to comply with the requirements in AFI 40-201, observe these precautions to control exposureto radiation emitted from these weights. Failure tocomply may result in overexposure to radiationand the need for medical attention.
a. All work on depleted uranium counterweights shallconform to the requirements of AFI 40-201.
b. Chemical or mechanical processing of depleted ura-nium counterweights, other than repair or restorationof plating, organic finish system, and/or other cover-ing, requires a Nuclear Regulatory Commission li-cense.
c. Do not machine, grind, file, sand, drill, weld, or other-wise mechanically work these counterweights at field/organizational maintenance units. Depleted uraniumand its oxide corrosion products in the form of dust,fumes, or particles are highly toxic if ingested.
d. If at all possible, remain at least two feet away fromthe depleted uranium counterweights since radiation isalmost nil at this distance and greater. If any part ofthe body comes within 1 foot of a depleted uraniumcounterweight, keep a record of the exposure time anddo not allow the total exposure time to exceed 40 hoursper calendar quarter. If it becomes necessary to touch a
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depleted uranium counterweight, keep a record of theexposure time and do not allow the total exposure timeto exceed 13 hours per calendar quarter.
e. If an aircraft with control surfaces having depleteduranium counterweights is being transferred to anotherunit or the aircraft or one of its control surfaces isbeing scrapped, notify the receiving unit and/or sal-vage personnel of their presence and bring these pre-cautions to their attention.
f. Remove the depleted uranium counterweights and/orthe control surfaces containing them from the aircraftafter any aircraft accident.
g. Dispose of depleted uranium counterweights per direc-tions in AFI 40-201.
NOTE
Refer to applicable system specific maintenancemanual to determine the location of depleted ura-nium parts and to determine any specific direc-tions for work either on the counterweights or inareas immediately adjacent to the counterweights.
7.18.1 Corrosion and Finish Damage Treatment Pro-cedures. Follow these procedures when treating finish sys-tem and/or corrosion damage on depleted uranium counter-weights.
a. Visually inspect the organic finish system (paint) forblisters and flaking. If found, peel away the paint flakesand inspect the plating for blisters and flaking. If found,peel away the plating flakes and inspect the surface ofthe depleted uranium for pitting and/or intergranularexfoliation corrosion. The corrosion products are verydark brown to gray to black color similar to rust onsteel and will flake off in the same fashion.
b. Collect all of peeling and/or flaking paint and/or plat-ing residue, check it for radioactivity, and dispose of itper instructions in AFI 40-201 if radioactivity is noted.
c. Field/organizational units are not authorized to removecorrosion found on the depleted uranium itself. Field/organizational units are limited to the following ac-tions on depleted uranium counterweights.
(1) Accomplish step a and step b above.
(2) Apply one thick coat of MIL-PRF-81733, Type Ior II, Class 1 or 2, Grade A sealant to the barearea with a brush per the manufacturer’s instruc-tions.
(3) After the sealant cures at least to a tack-free state,apply one coat of MIL-PRF-85285 polyurethane
in the color specified in the system specific tech-nical data by brush per procedures in TO 1-1-8over the sealant with a slight overlap onto thesurrounding paint surface.
(4) Make an entry in the appropriate aircraft forms toindicate a requirement for depot level repair ofthe affected counterweight at the next aircraft de-pot input for PDM or other depot level mainte-nance.
d. Depot facilities (ALC prime for the aircraft), can re-move corrosion from depleted uranium counterweightsand rework them, but only if properly licensed by theNuclear Regulatory Commission. If the prime ALC isnot licensed to perform the work, the affected counter-weights shall be removed from the control surfacesand packaged for shipment per instructions in AFI 40-201, and shipped to a properly licensed facility for ei-ther rework or disposal, as appropriate. If the primeALC performs rework of depleted uranium counter-weights after they are removed from the control sur-face, it shall be done in accordance with AFI 40-201and a definitive process order developed and approvedby the aircraft SPD in conjunction with the ALC cor-rosion prevention and control manager. This processorder shall include the following procedures as a mini-mum:
(1) Remove the affected counterweight from the con-trol surface per instructions in the applicable sys-tem specific maintenance manual.
(2) Remove the paint from the counterweight sur-faces per procedures in TO 1-1-8.
(3) Remove the plating from the counterweight sur-faces per procedures in TO 42C2-1-7.
(4) Remove any corrosion from the depleted uraniumsurfaces using an appropriate mechanical methodin Section I of Chapter 5 of this manual that isapproved and listed in the process order makingsure to observe all the precautions in the WARN-ING above and in AFI 40-201.
(5) Check all residue for radioactivity and dispose ofany residue found to be radioactive per instruc-tions in AFI 40-201.
(6) Replate the counterweight with the plating(s)specified in the applicable system specific techni-cal data per procedures in TO 42C2-1-7.
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(7) Apply a MIL-PRF-23377, Type I, Class C epoxyprimer and MIL-PRF-85285 polyurethane topcoatin the color specified in the applicable systemspecific maintenance manual per procedures inTO 1-1-8.
(8) Reinstall the counterweight on the control surfaceper instructions in the applicable system specificmaintenance manual with faying surfaces and fas-teners wet with MIL-PRF-81733 Type I or IV,Class 1 or 2, Grade A sealant.
7.19 MONEL RIVETS.
Corrosion of nickel-copper alloy (monel) is evidenced bygreen corrosion products (patina). Removal of this type ofcorrosion is not required as the corrosion products are veryadherent and provide a degree of protection to the monelbase metal. If desired, corrosion products may be removedas follows:
a. Scrub with a non-metallic bristle brush wet with solu-tion of 6 OZ of ASTM D 928 sodium bicarbonate pergallon of water.
b. Thoroughly rinse the affected area with fresh tap waterand wipe dry with a clean, lint free cloth or blow drywith oil free, low pressure air.
7.20 BERYLLIUM-COPPER ALLOYS, BERYLLIUM-ALUMINUM ALLOYS, AND BERYLLIUM OXIDE.
Dust, corrosion products (beryllium oxide), andother fine particles generated by beryllium and be-ryllium alloys are toxic when inhaled or allowedto contact skin. Severe poisoning can result if be-ryllium dust and/or fumes are inhaled and causedelayed lung injury and/or death. OSHA regula-tions require use of personal protective equipment(PPE) suitable for the task being performed. Con-sult the local Bioenvironmental Engineer for de-termination of the type of PPE required. Do notweld, drill, cut, file, sand, abrade, machine, or per-form any other mechanical action on beryllium al-loy parts that will create airborne dust particlesfrom the operation without using appropriate PPEand facility dust collection systems.
NOTE
Surface discoloration is normal and removal isneither advised nor is it necessary.
7.20.1 Corrosion Removal and Treatment. If it is notfeasible to remove the part from the aircraft, missile, or pieceof equipment for corrosion removal and treatment, the pro-
cedure may be performed on an installed part in place. Tominimize the generation of fine beryllium, beryllium oxide,beryllium-copper alloy, and/or beryllium-aluminum alloydust particles when removing corrosion from beryllium-cop-per alloy fittings such as contacts, bushings, etc., and beryl-lium-aluminum alloy parts, proceed as follows:
a. Wear disposable coveralls, gloves, hood, cartridge res-pirator, and other PPE, as required, by the local Bioen-vironmental Engineer.
b. Dampen an A-A-58054, Type I, Grade B abrasive matwith A-A-59601, MIL-PRF-32295, Type II, or MIL-PRF-680, degreasing solvent and abrade the corrosionproducts from the surface.
c. To prevent the spread of toxic dust, keep mat wetthroughout the corrosion removal process.
d. Clean the surface with disposable towels dampenedwith degreasing solvent after the completion of corro-sion removal and wipe dry with a clean, dry towel.
e. Apply a film of MIL-PRF-81309, Type II, or MIL-L-87177, Type I, Grade B water displacing, CPC to be-ryllium-copper bushings and MIL-PRF-81309, Type IIIor MIL-L-87177, Type I, Grade B to beryllium-coppercontacts by spraying. Apply a MIL-DTL-81706/MIL-DTL-5541, Class 1A conversion coating to the surfaceof beryllium-aluminum alloy parts per procedures inSection II of Chapter 5.
f. Wipe work area clean with disposable towels damp-ened with A-A-59601, MIL-PRF-32295, Type II, orMIL-PRF-680, degreasing solvent and wipe the areadry with a clean, dry towel.
g. Place disposable towels, abrasive mats, and coverallsin a plastic bag marked, “Beryllium ContaminatedWaste”.
h. Close the plastic bag with SAE AMS-T-23397 (MIL-T-23397), Type II aluminum foil tape.
i. Discard all in accordance with local environmental di-rectives.
j. Wash hands with soap and water immediately aftercompletion of the task.
7.20.2 Depot Maintenance. If it is feasible, operationallyacceptable, and replacement parts are readily available, be-ryllium alloy parts should not be reworked to remove corro-sion by field/organizational level maintenance personnel. Theparts should be removed from the aircraft, missile, or pieceof equipment, properly packaged, and shipped to the respon-sible depot (ALC) for rework using the following procedures:
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a. Wear disposable coveralls, gloves, cartridge respiratorand other PPE, as required, by the local Bioenviron-mental Engineer.
b. Remove the corroded part, and place it in a plastic bagmarked, “Beryllium Alloy Part”.
c. Close the plastic bag with SAE AMS-T-23397 (MIL-T-23397), Type II aluminum foil tape.
d. Package the part for shipment to the responsible depot(ALC) for rework.
e. Clean the area from which the part was removed withdisposable towels dampened with A-A-59601 or MIL-PRF-680, Type II or III degreasing solvent and wipedry with a clean, dry towel.
f. Install a new replacement part in the area from whichthe old, corroded beryllium alloy part was removedper the appropriate system specific technical data.
g. Place disposable towels and coveralls in a plastic bagmarked, “Beryllium Contaminated Waste”.
h. Close the plastic bag with SAE AMS-T-23397 (MIL-T-23397), Type II aluminum foil tape.
i. Discard all in accordance with local environmental di-rectives.
j. Wash hands with soap and water immediately aftercompletion of the task.
7.21 EMI SEALS AND GASKETS.
Radiated electromagnetic fields (produced by radar antennas;aircraft, and missile transmitters; certain poorly designedavionics units; electric motors; lightning; or any other natu-ral effects), can interfere with aircraft avionics systems caus-ing electrical and/or electronic malfunctions. This radiationis known as electromagnetic interference (EMI). To preventmalfunctions caused by EMI, electrically conductive shield-
ing is either built into the avionic device or must be added toaccess panels, doors, or covers to prevent emission of EMIfrom its own circuits and prevent susceptibility to outsideEMI. EMI seals and gaskets may also act as environmentalseals in certain locations, especially around doors and accesspanels. Since aluminum surfaces oxidize very easily, thusbecoming much less conductive and/or non-conductive, othermaterials have been used to make electrical contacts (i.e.,beryllium-copper, titanium, silver-plated aluminum, and tin-zinc coatings). However, since these contacts must provide aconductive path to an aluminum or graphite/epoxy skin, cor-rosion often occurs at the junction of these dissimilar metals.When corrosion occurs, the conductive path is lost alongwith the EMI protection, making the aircraft susceptible toelectrical and electronic malfunctions caused by external ra-diation. Examples of system malfunctions are microproces-sor bit errors, computer memory loss, false indicators(alarms, lights, read-outs), CRT ripple, false signals andpower loss. The result of such malfunctions can be cata-strophic (e.g. EMI radiation was responsible for an aircraftjettisoning a bomb while taking off from a carrier). The fol-lowing are typical EMI shielding materials: elastomeric sealsand gaskets with an embedded or attached conductor (referto Figure 7-1), conductive elastomer gaskets (refer to Figure7-2), metallic screens installed under composite covers (referto Figure 7-3), bonding cables for access doors (refer to Fig-ure 7-4), and bonding washers for avionics enclosures, (referto Figure 7-5).
7.21.1 Treatment of EMI Seals and Gaskets. Whencorrosion is observed in such areas, disassemble only theaffected areas and remove the corrosion using the mildestavailable method necessary to remove the corrosion. Care-fully clean the area with a lint free cloth wet with TT-I-735isopropyl alcohol. Dry with a clean cloth. If replacementseals are available, install them in accordance with the ap-propriate aircraft, missile, or equipment system specificmaintenance manual. If replacement seals are not availableor do not exist, spray the contacting surfaces with a lightcoating of MIL-PRF-81309, Type III avionics grade, waterdisplacing CPC, and then reassemble. Periodically inspectrepaired areas and areas known to be chronic problems.
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7-15
Figure 7-1. Beryllium-Copper Spiral Contact with Environmental Fluorosilicone Seal
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7-16
Figure 7-2. Dorsal Longeron EMI Seal
Figure 7-3. Stainless Steel (CRES) EMI Screen
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7-17
Figure 7-4. Bonding Cable from Airframe to Graphite/Epoxy Avionics Bay Door
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Figure 7-5. EMI Bonding Washers in an Avionics Bay
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7-19/(7-20 blank)
CHAPTER 8EMERGENCY PROCEDURES
8.1 PURPOSE.
This chapter describes emergency procedures to be followedafter aircraft, missile, or equipment incidents or accidentsinvolving exposure to gross amounts of salt water or fireextinguishing agents. The procedures described are used toprevent further damage before more extensive cleanup at ei-ther organizational or intermediate maintenance can be per-formed and/or further treatment at depot level maintenancecan be accomplished.
8.2 RESPONSIBILITY.
• Failure to remove aircraft from dry/wet chemi-cal exposure and to remove dry/wet chemicaland dry powder agents from aircraft surfaceswill allow significant corrosion to occur on ex-posed metals.
• Failure to remove an aircraft from foam expo-sure and to remove foam from an aircraft willcompromise protective coatings on metal andallow corrosion/oxidation to occur.
• Exposure to salt water, purple K powder (PKP/potassium bicarbonate) and/or protein type firefighting foam require immediate action to pre-vent serious corrosion damage.
NOTE
In cases involving aircraft, missile, or equipmentaccidents, permission must be obtained from thesenior member of the accident investigation boardprior to the initiation of emergency procedures.
Under emergency conditions, all personnel are responsiblefor minimizing damage. Aircraft should be removed fromcontaminated aircraft hangars and other locations when ex-posed to firefighting agents as soon as approved by the BaseFire Department, Base Safety Office and BioenvironmentalOffice. Reclamation team personnel shall follow proceduresand directions as provided by the Base Safety Office. Re-moval of equipment shall be supervised by the organiza-tional unit maintenance officer in conjunction with the main-tenance superintendent. Removal of equipment shall besupervised by the organizational unit maintenance officer inconjunction with the maintenance superintendent. They shalldesignate an officer or senior NCO as the corrosion controlofficer, whose duties will include organizing and supervisingan emergency reclamation team and directing the team to
accomplish salvage operations or corrosion control action.The size and composition of the team depends on the ur-gency of the situation and/or workload. If required, addi-tional personnel from outside the maintenance squadron shallbe selected and placed under the direction of the corrosioncontrol officer. In case of fire damage, the aircraft SPD and/orthe missile or equipment SPM and cognizant ALC corrosionprevention and control manager must be contacted to deter-mine the effects of heat or excessive salt water and/or firefighting material contamination prior to continued use or re-pair of affected parts or components.
8.3 EMERGENCY PREPARATIONS.
Emergency preparations shall include the development ofpriority lists for removal of equipment, emergency reclama-tion team planning, and lists of required tools, materials, andequipment with notations of their location and availabilitywithin the organizational unit and/or where they can be ob-tained if not readily available at the unit.
NOTE
Each organizational unit maintenance officerand/or maintenance superintendent shall prepare orhave access to a list of installed equipment/com-ponents indicating removal priority from affectedaircraft, missiles, or equipment in emergency con-ditions.
8.3.1 Priority Removal List of Equipment and/or Com-ponents.
Magnesium parts are particularly susceptible tocorrosive attack when exposed to salt water or fireextinguishing materials. Avionic, electronic, elec-trical, and ordinance equipment known to containmagnesium components shall be given high prior-ity for cleaning. Contaminants shall be removedpromptly to prevent serious damage.
Table 8-1 is a tabulation of aircraft, missile, and equipmentcomponent groups arranged in order of suggested priority oftreatment. Among the factors considered in the developmentof the table were dollar value, corrosion rate, and probabilityof successful salvage. Whenever manpower or facility short-age prohibits simultaneous processing of all components,treatment shall be given in the order of the priority listing.The table should be considered as a guide and operationsmay deviate from the assigned priority when directed by
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Change 9 8-1
qualified organizational unit production planning personnelor maintenance officer and/or maintenance superintendent orthe cognizant ALC SPD and/or SPM engineering personnel.
NOTE
Table 8-1 is a priority guide for removing and pro-cessing equipment which has been exposed to cor-rosive salt water or fire fighting chemicals. Varia-tions in aircraft, missile, or equipment designconfigurations and mission equipment installationsmay make it necessary to contact the affected air-craft SPD and/or missile or equipment SPM andrequest them to furnish listings of equipment andpreferred priority of removal and treatment. Prior-ity of removal and treatment should always be ori-ented toward recovery of salvageable equipment.
8.3.2 Emergency Reclamation Team.
• High expansion foam solution may fill a hangarspace to 20 feet or more. The foam bubbleswill totally obscure vision and visual referencesin a “white-out” causing complete loss of di-rection and even vertigo.
• All foam firefighting solutions will create anextreme slipping hazard especially on highlyreflective hangar floor surfaces.
The emergency reclamation team will provide expertise andfacilities for processing equipment received from accident/incident sites at the operational unit. This team shall be re-sponsible for processing equipment received. The size of theteam, its organization, and the specific equipment require-ments will be geared to the size and needs of the reclamationoperation at hand. Recommended equipment includes wash/rinse facilities, drying ovens, dip tanks (for water displacingcompounds and preservatives), and cleaning compounds.
8.3.2.1 Personal Protection.
Personal protective equipment is required duringall reclamation and emergency cleaning opera-tions. Aircraft fuels/lubricants, cleaning soaps andsolvents, and firefighting chemicals have potentialfor adverse human exposure response and may bepresent under reclamation operations.
Under the advisement of the Base Safety Office and Bioen-vironmental, all reclamation team members shall wear theapproved required personal protective equipment to preventeye, dermal, and respiratory exposure. Refer to material andequipment lists in Table 8-2, Appendix A, and Appendix B.
The Base Safety Office and Bioenvironmental have the flex-ibility to modify personal protective equipment requirementsbased on the task and circumstances of the cleaning activity.Air Force approved firefighting proximity or structural per-sonal protective equipment (PPE) provides acceptable pro-tection for reclamation and cleaning operations. Individualcomponents of firefighting PPE may be combined with theTO identified PPE components during reclamation and clean-ing operations.
8.3.2.2 Personnel Decontamination.
Failure to decontaminate personnel engaged inreclamation and emergency cleaning operationsmay expose persons outside to irritating materials.
All personnel engaged in reclamation operations shall beprovided gross decontamination and disposal of all PPE be-fore leaving the reclamation area. Personnel shall also beprovided with personal showers before leaving the installa-tion and clean clothing.
8.3.2.2.1 Consult the Installation Bioenvironmental Flightfor proper cleaning and/or disposal of contaminated clothingmaterials generated during reclamation and cleaning opera-tions. Consult the Installation Bioenvironmental Flight andInstallation Environmental Flight for proper disposal of wastematerials generated during reclamation and cleaning opera-tions.
8.3.3 Emergency Reclamation Equipment. The avail-ability of the necessary tools, materials, and equipment forthe prompt removal, cleaning, and drying of avionic, elec-tronic, and electrical equipment will significantly aid in re-ducing damage. Refer to material and equipment lists inTable 8-2, Appendix A, and Appendix B. Certain useful itemsof equipment are:
• Drying ovens.
• Portable air blowers.
• Heaters.
• Backpack pumps.
• Vacuum cleaners.
• Hoses and washing equipment.
8.3.4 Production Planning. Whenever possible, all sal-vageable components of the affected aircraft, missile, orequipment shall be treated simultaneously. To minimize dam-age and ensure that the work is accomplished in a thoroughand competent manner, the most experienced personnelavailable shall be assigned to disassemble and process the
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8-2 Change 9
aircraft, missile, or equipment. Whenever possible, examina-tion and evaluation personnel shall be assigned to work withthe disassembly and preservation crew in order that thoseitems obviously beyond reclamation may be scrapped imme-diately and that only those areas exposed to corrosive saltwater or fire fighting chemicals are disassembled and treated.The time saved by this procedure may be utilized to accel-erate preservation of salvageable components.
8.4 GENERAL PROCEDURES.
Before starting emergency treatment, particularlyin those instances where fuel cells have been rup-tured and fuel or fuel vapors are present, it is im-perative that a fuel system specialist and/or thesafety officer supervise purging or inerting proce-dures and certify that the affected aircraft, missile,or equipment is fire and explosion safe. Qualifiedmissile and/or ordnance personnel shall be as-signed to handle all missiles, ordnance and associ-ated items, such as ammunition and pyrotechnics.
For cases involving aircraft, missile, or equipment accidents,permission for any treatment shall be obtained from the se-nior member of the accident investigation board prior to ini-tiating procedures for emergency reclamation to preventjeopardizing the ability to determine the cause of the inci-dent.
NOTE
Chemical, Biological and/or Radiological Con-taminated Assets. Any asset that has been contami-nated or potentially contaminated must be identi-fied, marked and decontaminated in accordancewith AFMAN 10-2503, Operations in a Chemical,Biological, Radiological, Nuclear, and High-YieldExplosive (CBRNE) Environment and TO 00-110A-1.
a. Determine from the local fire department which fireextinguishing agent was used. A review of photographstaken by public affairs and/or other media personnelmay provide information concerning areas that wereactually exposed to corrosive fire extinguishing mate-rials such as foam and purple K powder (PKP).
b. Ensure that the aircraft, missile, or equipment is safefor maintenance. Electrically ground the aircraft, mis-sile, or equipment by attaching the ground lead to theaircraft, missile, or equipment at a point outside thearea that could contain explosive vapors. Turn off allelectrical power and disarm all explosive and/or firingsystems on a missile or an aircraft, including the ejec-tion seat(s) on an aircraft.
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Change 15 8-2.1/(8-2.2 blank)
Table 8-1. Priority Guide for Emergency Treatment of Aircraft, Missiles, and Equipment
PriorityNumber Reciprocating Engine Gas Turbine Engine
Turboprop, Tur-boshaft Engine Helicopters
1 Engine, propeller,and accessories
Engine and accessories Engine, propeller,propeller drivegear mechanisms,and accessories
Rotor dynamic components
2 Avionic and fire con-trol equipment
Avionic and fire controlequipment
Avionic and fire con-trol equipment
Engine, rotors, and accessories
3 Instruments Instruments Instruments Avionic and fire control equip-ment
4 Fuselage, wings, andempennage
Fuselage, wings, and em-pennage
Fuselage, wings, andempennage
Instruments
5 Turrets, and rocketand missile launch-ers
Turrets, and rocket andmissile launchers
Turrets, and rocketand missilelaunchers
Fuselage
6 Drained fuel and oilsystems
Drained fuel and oil sys-tems
Drained fuel and oilsystems
Drained fuel and oil systems
7 Photographic equip-ment
Photographic equipment Photographic equip-ment
Photographic equipment
8 Landing and arrestinggear
Landing and arresting gear Landing and arrest-ing gear
Landing gear or floats
9 Safety and survivalequipment
Safety and survival equip-ment
Safety and survivalequipment
Safety and survival equipment
10 Electrical equipment Electrical equipment Electrical equipment Electrical equipment11 Armament equipment Armament equipment Armament equip-
mentArmament and rescue equipment
12 Fixed equipment(seats, etc.)
Fixed equipment (seats,etc.)
Fixed equipment(seats, etc.)
Fixed equipment (seats, etc.)
13 Miscellaneous equip-ment
Miscellaneous equipment Miscellaneous equip-ment
Miscellaneous equipment
1 Warheads Engines and accessories2 Engines and accesso-
riesInstruments
3 Guidance systemsand sensors
Electronic and electricalequipment
4 Electrical equipment Drained fuel and oil sys-tems
5 Miscellaneous equip-ment
Fixed equipment (seats,etc.)
6 Miscellaneous equip-ment
Suggested List of Emer-gency Reclamation Items
Table 8-2. Suggested List of Emergency Reclamation Items
PriorityNumber Accessories Specification or PN National Stock Number Unit of Issue
1 Aircraft Grounding Straps - - -2 Aircraft Washing Kits 3M Co., CAGE Code
#76381, PN 2517920-00-490-6046 KT
3 Pads, Cleaning and Polish-ing, Non-Metallic (forAircraft Washing Kits)
A-A-3100Type I (3⁄8 in thick) 7920-00-151-6120 PG (10 SH)Type II (1 in thick) 7920-00-171-1534 PG (10 SH)
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8-3
Table 8-2. Suggested List of Emergency Reclamation Items - Continued
PriorityNumber Accessories Specification or PN National Stock Number Unit of Issue
4 Soft Bristle Scrub Brushes A-A-2074Type I, Style A (Nylon) 7920-00-619-9162 EA (4 ½ in x 1 ¾
in)Type II, Style C (Tampico) 7920-00-282-2470 EA (10 ¾ in x 2 ¾
in)Type IV, Style B (Nylon) 7920-00-061-0037 EA (8 ½ in x 5 in)Type IV, Style D (Palmyra) 7920-01-067-6203 EA (8 ½ in diam-
eter)5 Backpack Pump (5 GL) PN 5100-254B, CAGE Code
#040244320-00-289-8912 EA
6 Spray Gun, Pneumatic SAE AMS-G-952 (supersedesMIL-G-952) Type I
4940-00-248-0866 EA
7 Drying Rags Flannel, Cot-ton
A-A-50129 (supersedes CCC-C-458)
8305-00-913-5817 BO (50 YD)
8 Leather Chamois KK-C-300, Grade B, Class 2(Small)
8330-00-823-7545 Bundle (5 EA)
9 Sponges, Synthetic Clean-ing
A-A-2073 7920-00-633-9915 EA (7 in L x 4 ¼in W x 2 3⁄8 inT)
10 Air Nozzle Gun (BlastCleaning)
A-A-55543 (supersedesGGG-G-770)
Type II (push down), Style B(3⁄8 in internal threads)
4940-00-223-8972 EA
Type II (push down), Style A(¼ in internal threads)
4940-00-333-5541 EA
11 Air Hose Assembly Gen-eral Purpose, Non-Metal-lic Spray
A-A-59613 (3⁄8 in ID x 50 ft) 4720-00-289-3429 FT
Rubber, Pneumatic (Yarnand Fabric Reinforced)
A-A-59565½ in ID x 50 ft 4720-00-278-4889 FT5⁄8 in ID x 50 ft 4720-00-278-4890 FT¾ in ID x 50 ft 4720-00-278-4891 FT
12 Vacuum Cleaner, Pneu-matic (Wet/Dry Vac)
PN AT560ACF-18, CAGECode #00784
5130-01-368-5861 EA
Vacuum Cleaner w/Attach-ments
PN 15-A1080, CAGE Code#58150 Pneumatic Type)
7910-00-807-3704 EA
PN C83985-01, CAGE Code#16893 (Electric Type) (A-A-54943)
7910-01-236-0893 EA
13 Utility Pails, Plastic A-A-59253, Size 4, Style B 7240-00-246-1097 EA14 LG Trash Can Plastic
Liners- Commercial Purchase -
15 Nozzles, Garden Hose (for5⁄8 and ¾ in hose) Ad-justable
A-A-50461 Straight, Adjust-able Spray (Brass)
4730-00-223-6731 EA
Pistol Grip, Adjustable (Cop-per Alloy) w/Rubber Cover,PN 10855, CAGE Code#97141
4730-00-900-0733 EA
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8-4
Table 8-2. Suggested List of Emergency Reclamation Items - Continued
PriorityNumber Accessories Specification or PN National Stock Number Unit of Issue
16 Hose and Hose Assem-blies, Non-Metallic
A-A-59270, Type I, Class I(Rubber)
5⁄8 in ID x 50 ft L 4720-00-203-3920 EA¾ in ID x 50 ft L 4720-00-203-3912 EAType II, Grade A (PVC)5⁄8 in x 50 ft L 4720-00-729-5334 EA¾ in x 50 ft L 4720-00-729-5338 EA
17 Goggles, Industrial, Plastic PN A-A-1110 (ANSI Z87.1Safety Standard)
Standard Safety Goggles 4240-00-052-3776 PRSplash Proof Goggles 4240-00-082-8928 PRChemical Splash Proof
GogglesCommercial Items -
18 Faceshield, Industrial PN L-F-36 (ANSI Z87.1Safety Standard)
9 in L x 18 in W Plastic Win-dow Lens
4240-00-542-2048 EA
19 Apron, Rubber (Black) PN A-A-3104 (45 in L x 35in W)
8415-00-634-5023 EA
20 Gloves, Rubber, Industrial MIL-G-12223, Type II (14 inGauntlet)
X-Small (8) 8415-00-753-6550 PRSmall (9) 8415-00-753-6551 PRMedium (10) 8415-00-753-6552 PRLarge (11) 8415-00-753-6553 PRX-Large (12) 8415-00-753-6554 PR
21 Gloves, Leather Palm (forHandling Composite Ma-terials)
A-A-50016Men’s Medium Size 8415-00-268-8350 PRWomen’s 8415-00-268-8351 PR
22 Barrier Material MIL-PRF-131Class 1 (Non-Woven Plastic
Back)8135-00-282-0565 RO (36 in x 200
YD)23 Tape, Pressure Sensitive,
Preservation and SealingSAE AMS-T-220851 in W x 36 YD 7510-00-852-8179 RO2 in W x 36 YD 7510-00-852-8180 ROType II (use w/ or w/o Over-
coating)2 ½ in W x 36 YD 7510-00-885-3510 RO3 in W x 36 YD 7510-00-926-8939 RO3M Co., CAGE Code
#52152, PN 4814 in W x 36 YD 7510-00-916-9659 RO6 in W x 36 YD 7510-00-926-8941 RO
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8-5
Table 8-2. Suggested List of Emergency Reclamation Items - Continued
PriorityNumber Accessories Specification or PN National Stock Number Unit of Issue
24 Respirator, Full Face piece 3M Co., CAGE Code#76381,
PN 7800S-M (Medium) 4240-01-342-5239 EAPN 7800S-L (Large) 4240-01-301-3200 EAPN 6700 (Small) 4240-01-454-8531 BX (4 EA)PN 6800 (Medium) 4240-01-454-8535 BX (4 EA)PN 6900 (Large) 4240-01-454-8538 BX (4 EA)
25 Cartridges, Filter ( 60007000 Series)
3M Co., CAGE Code#76381,
PN 60921 4240-01-455-7353 BX (60 EA)26 Lens Assembly (for Full
Face Respirator)PN 7884 (7800 Series) 4240-01-247-8929 BX (5 EA)PN 6898 (6000 Series) Open Purchase -
27 Coveralls, Disposable A-A-55196, Type I withHood
Small/Medium 8415-01-445-6565 EALarge/X-Large 8415-01-445-6568 EAXX-Large 8415-01-445-6588 EA
28 Heater Gun, Electric A-A-59435Type I (350° - 500° F) 4940-00-357-1369 EAType II (500° - 750° F) 4940-01-028-7493 EAType III (750° - 1000° F) 4940-01-391-7046 EA
29 Corrosion Preventive Com-pounds, Water Displac-ing, Ultra-Thin Film (5GL min)
MIL-PRF-81309, Type II(Soft Film), Class 1 (Non-pressurized container/bulk)
1 GL Can 8030-00-213-3279 CN (1 GL)5 GL Can 8030-00-262-7358 CN (5 GL)55 GL Drum 8030-00-525-9487 DR (55 GL)Class 2, Grade CO2 (Pressur-
ized container - CO2 pro-pellant) CN (1 GL)
8030-00-938-1947 CN (16 OZ)
Type III (Soft Film: AvionicGrade)
Class 1 (Non-pressurized/bulk) (1 GL)
8030-01-347-0978 CN (1 GL)
Class 2 (Pressurized Aerosol)16 OZ Can
8030-00-546-8637 CN (16 OZ)
30 Corrosion Preventive Com-pounds, Water Displac-ing, Synthetic (5 GLmin)
MIL-L-87177Type I (Pressurized Aerosol),
Grade B6850-01-528-0653 CN (16 OZ)
Type II (Non-pressurized/bulk), Grade B
6850-01-326-7294 CN (5 L)
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8-6 Change 3
Table 8-2. Suggested List of Emergency Reclamation Items - Continued
PriorityNumber Accessories Specification or PN National Stock Number Unit of Issue
31 Aircraft Cleaning Com-pound
MIL-PRF-87937, Type IV1 GL Can 6850-01-429-2368 CN (1 GL)5 GL Can 6850-01-433-0873 CN (5 GL)55 GL Drum 6850-01-429-2371 DR (55 GL)24 OZ Spray Trigger Bottle 6850-01-461-0060 BT (24 OZ)16 OZ Aerosol Can 6850-01-461-0070 CN (16 OZ)MIL-PRF-85570, Type II1 GL Can 6850-01-239-0571 CN (1 GL)5 GL Can 6850-01-235-0872 CN (5 GL)15 GL Drum 6850-01-248-9828 DR (15 GL)55 GL Drum 6850-01-236-0128 DR (55 GL)
32 Engine Gas Path Cleaner MIL-PRF-85704, Type II,Ready-To-Use
5 GL Can 6850-01-370-5245 CN (5 GL)55 GL Drum 6850-01-370-5244 DR (55 GL)
33 Degreasing Solvents A-A-59601, Type II1 PT Can 6850-00-110-4498 CN (1 PT)1 GL Can 6850-00-637-6135 CN (1 GL)5 GL Can 6850-00-274-5421 CN (5 GL)55 GL Drum 6850-00-285-8011 DR (55 GL)MIL-PRF-680, Type II1 GL Can 6850-01-474-2319 CN (1 GL)5 GL Can 6850-01-474-2317 CN (5 GL)55 GL Drum 6850-01-474-2316 DR (55 GL)MIL-PRF-32295, Type II1 GL 6850-01-606-8356 CN (1 GL)5 GL 6850-01-606-8357 CN (5 GL)15 GL 6850-01-606-3293 CN (15 GL)55 GL 6850-01-606-8358 DR (55 GL)
34 Isopropyl Alcohol (IPA) TT-I-735½ PT Can 6810-00-753-4993 CN (½ PT)1 QT Can 6810-00-983-8551 CN (1 QT)1 GL Can 6810-00-286-5435 CN (1 GL)5 GL Can 6810-00-543-7915 CN (5 GL)55 GL Drum 6810-00-586-6647 DR (55 GL)
35 Fire Extinguishing Agent(AFFF)
MIL-F-24385, Type 35 GL Can 4210-01-139-4972 CN (5 GL)55 GL Drum 4210-01-144-0291 DR (55 GL)Type 65 GL Can 4210-01-056-8343 CN (5 GL)55 GL Drum 4210-01-056-0883 DR (55 GL)
c. Closely inspect the aircraft, missile, or equipment todetermine areas affected. Traces of foam type extin-guishing agents may not be evident; however, moistresidues often indicate previous foam application. Dry
powders may be present in joints, faying surfaces, etc.,so a careful examination will be necessary to deter-mine if they are present.
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Change 5 8-7
d. Wherever possible, remove components from affectedareas. Open, loosen, or remove covers, access plates,inspection doors, etc. Allow any accumulated salt wa-ter or other liquids to drain off. If dry chemical fireextinguishing materials have been used, refer to Para-graph 8.5.3.
e. Remove gross amounts of contaminants by flushingwith fresh water and draining.
f. Remove components and process in accordance withParagraph 8.4.2 and Paragraph 8.4.3.
g. Clean the aircraft in accordance with Paragraph 8.5.
h. Inspect aircraft, missile, or equipment and determinewhether it can return to operational service followinglocal organizational level maintenance action orwhether additional higher level maintenance will benecessary. If aircraft is locally repairable, repairs mustbe permanent repairs before the aircraft, missile, orequipment is released for unrestricted operational ser-vice.
8.4.1 Removal of Contaminated Installed Equipment.After salt water immersion or entry, or exposure to any cor-rosive agents, equipment must be cleaned promptly and thor-oughly. Follow the procedures in this chapter for decontami-nating specific areas and equipment. Refer to Table 8-1 forassigning priority to equipment removal and treatment.
8.4.2 Disassembly/Removal of Components. The me-chanical cutting of fuel, hydraulic and oil lines, and electri-cal leads, and other drastic operations necessary to expediteremoval of parts are left to the discretion of the maintenanceofficer and/or maintenance superintendent directing the op-erations.
8.4.2.1 Aircraft Involved in Water Crashes. When air-craft are involved in water crashes, it shall be assumed thatall components, including hollow structural and mechanical
members, are contaminated internally. All components shallbe disassembled and treated or forwarded to the appropriateALC Depot for disassembly and treatment, as required. En-sure that all contaminants have been removed and that allcorroded surfaces have been effectively treated to inhibit fur-ther attack prior to returning the aircraft to operational ser-vice.
8.4.3 Clean. Equipment and components shall be cleanedby the team in accordance with Paragraph 8.5, Paragraph8.6, and Paragraph 8.7, and then delivered to the designatedshops for further inspection and maintenance. Equipment thatcannot be removed shall be cleaned in place and inspected.
NOTE
All equipment subject to emergency reclamationteam procedures must be certified operationallyready before returning to serviceable status. In-spect equipment for corrosion, cracks, and heatdamage. Obtain the maximum available engineer-ing assistance to evaluate the extent of damage.Particular attention shall be given to dissimilarmetal joints. Avionic, electronic, and electricalequipment usually contain dissimilar metals.
8.4.4 Tagging. All parts and components removed fromthe aircraft, missile, or equipment shall be “green” tagged(DD Form 1577-3) for identification, description of the acci-dent/incident experienced, listing of the contaminants andchemical materials to which they were exposed, and to indi-cate the type of CPC applied. CPC’s shall be removed priorto reusing the equipment.
8.5 GENERAL CLEANING PROCEDURES.
Contaminated areas may be cleaned by several methods. Theprimary method is fresh water flushing. Alternate methodsmay be used when fresh water is not available. Use themethods in Paragraph 8.6 and Paragraph 8.7 for emergency
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8-8
treatment of specific components. Do not use the followinggeneral methods when specific methods are available.
8.5.1 Primary Method.
Prolonged breathing of vapors from organic sol-vents or materials containing organic solvents isdangerous. Prolonged skin contact with many or-ganic solvents or solvent containing materials canhave toxic effect on exposed skin areas. Observeprecautions listed in previous chapters, referencedmanuals, and Safety Data Sheets (SDS) for clean-ing compounds, solvents, surface treatment chemi-cals, sealants, primers, and paints.
Do not expose plastic or rubber items; avionic,electronic, or electrical components; wiring; orother components susceptible to heat damage totemperatures in excess of 130° F (54° C) and any/all other areas to temperatures in excess of 150° F(66° C) during emergency cleaning procedures.
NOTE
Always use the mildest cleaning cycle availablethat will ensure proper decontamination. Eventhough fresh water/detergent wash should not sig-nificantly affect accident investigations, permis-sion must be obtained from the senior member ofthe appointed accident investigation board beforeperforming this operation.
The primary method of removing salt water is as follows:
a. Immerse removed unit or component in clean, freshwater whenever possible.
b. Flush all areas with clean, fresh water and allow themto drain.
c. Dry the item or areas by vacuum cleaning excess wa-ter and/or blotting with a cloth or paper towels, orblowing dry with compressed air at a pressure notgreater than 10 PSI. If visual evidence of salt remains,a second cleaning should be accomplished as follows:
(1) Mix a solution of one part of MIL-PRF-87937,Type IV or MIL-PRF-85570, Type II aircraftcleaning compound in nine parts water.
(2) Apply the solution to the affected areas and scrubwith bristle brushes, sponges, or cloths.
(3) Flush thoroughly with clean, fresh water and drainthoroughly.
(4) Dry the item or areas as before.
d. After flushing and drying, apply MIL-PRF-81309, TypeIII or MIL-L-87177, Type I or II, Grade B water dis-placing CPC/preservative on all avionic, electronic, orelectrical components and connectors. Ensure that allareas and crevices are coated. Apply a liberal amountof MIL-PRF-81309, Type II or MIL-L-87177, Type Ior II, Grade B water displacing CPC to all other areasthat cannot be properly drained or contain recesseswhich are difficult to reach. Ensure that all surfaces arecoated.
NOTE
MIL-PRF-81309, Type II water displacing CPCdeposits a thin, nonconductive film which must beremoved for proper function of contact points andother electromechanical devices where no slippingor wiping action is involved, but MIL-PRF-81309,Type III and MIL-L-87177, Type I or II, Grade Bneed not be removed as they do not interfere withproper function of these items. CPC is easily re-moved with A-A-59601, MIL-PRF-32295, Type II,or MIL-PRF-680, degreasing/dry cleaning solvent.Removal will be accomplished during subsequentmaintenance or functional test prior to issue foruse.
8.5.2 Alternate Methods. Use only when fresh water isnot available or is available only in limited supply or whentime prevents immediate flushing with fresh water.
8.5.2.1 Method One (Preferred). Spray, brush, or wipethe exterior of the affected areas and components with liberalamounts of MIL-PRF-81309, Type II or MIL-L-87177, TypeI or II, Grade B water displacing CPC/preservative.
8.5.2.2 Method Two (Alternate).
a. Apply a solution of one part MIL-PRF-87937, Type IVor MIL-PRF-85570, Type II aircraft cleaning com-pound in nine parts water by spray, brush, or cloth.
b. Brush affected areas until contaminants and cleanerbecome intermixed or emulsified.
c. Wipe off thoroughly with a clean cloth to remove bothcontaminants and cleaner.
TO 1-1-691
Change 15 8-9
d. Apply a liberal amount of MIL-PRF-81309, Type II orMIL-L-87177, Type I or II, Grade B water displacingCPC to affected areas.
8.5.3 Removing Fire Extinguishing Powder (O-D-1407Potassium Bicarbonate [Purple K{PKP}], Sodium Bicar-bonate, Ammonium Phosphate Monobasic) and/orOther Dry Chemical Agents. Remove powder as follows:
NOTE
Ammonium phosphate monobasic, often identifiedas Class ABC extinguishing agent, can be highlycorrosive to aircraft components; removal andcleaning should be addressed as an emergency.
a. Vacuum up as much of the loose powder as possible.Use a HEPA-filtered vacuum to prevent further con-tanimation.
b. Use a soft, bristle brush and air pressure not greaterthan 10 PSI to dislodge contaminants between close-fitting components.
c. Vacuum clean again.
d. Remove the residual film of dry powder adhering tothe surface by wiping, brushing, or spraying with asolution of one part of MIL-PRF-87937, Type IV orMIL-PRF-85570, Type II aircraft cleaning compoundin nine parts of water.
e. Rinse thoroughly with fresh water.
f. Dry with cloths or paper towels and/or blow dry withdry, oil free compressed air at a pressure not greaterthan 10 PSI.
g. Apply a liberal amount of MIL-PRF-81309, Type II orMIL-L-87177, Type I or II, Grade B water displacingCPC to the affected area.
h. Enter a notation defining the affected areas and whereand how they were treated in the appropriate aircraft,missile, or equipment forms with a requirement for aspecial inspection as corrosion prone areas at a speci-fied future time to determine if any corrosion has oc-curred.
8.5.4 Removing MIL-F-24385 Aqueous Film FormingFoam (AFFF) Fire Extinguishing Agent and Other Syn-thetic Based Foaming Agents Including High-Expansion(Hi-Ex) Foams. To remove residues of burned materials andfresh water solutions of AFFF and other synthetic foamingagents, use the following procedure:
NOTE
• Synthetic foaming agents and fresh water mix-tures act as soap solutions. While normally notbeing corrosive in and of themselves, they doremove most protective coating and expose thesurfaces to corrosive effects. Immediateclean-up of these solutions and any relatedburned materials is essential to corrosion pre-vention. Elimination of exposure and clean-upmust begin immediately once the area has beendetermined to be fire safe.
• Enter a notation defining areas and componentsthat are exposed to residue from burned mate-rials and fire extinguishing agent in the appro-priate aircraft, missile, or equipment forms witha requirement for a special inspection as corro-sion prone areas or components at a specifiedfuture time to determine if any corrosion hasoccurred.
a. Remove as much foam and foam/water solution aspossible with wet/dry vacuums and/or low pressure,clean, dry, oil-free compressed air or nitrogen.
b. Flush all affected areas with fresh, clean water whiledraining at the same time. Whenever possible, units orcomponents which have been removed, should be im-mersed in fresh water and then flushed thoroughly withfresh, clean water. Drain away the water.
c. Clean surfaces with a solution of one part MIL-PRF-87937, Type IV or MIL-PRF-85570, Type II aircraftcleaning compound in nine parts of water. Scrub af-fected areas and rinse with clean, fresh water. Drainaway excess water.
d. Dry with cloths, paper towels, and/or dry, oil free com-pressed air at a pressure not greater than 10 PSI.
e. Apply MIL-PRF-81309, Type III or MIL-L-87177,Type I or II, Grade B water displacing CPC to all avi-onic components and electrical connectors. Apply aliberal amount of MIL-PRF-81309, Type II or MIL-L-87177, Type I or II, Grade B water displacing CPC toall other areas that cannot be properly drained or con-tain recesses which are difficult to reach.
f. Enter information on affected areas and/or componentsin the appropriate aircraft, missile, or equipment formsper the instructions in the above NOTE.
g. Dismantle engine to piece part component level for allcomponents exposed to inlet flow path air.
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8-10 Change 1
h. Clean engine components exposed to AFFF or syn-thetic foaming agents per the appropriate depot levelcomponent cleaning procedure or clean per Paragraph8.7.3 through Paragraph 8.7.6.
8.5.5 Removal of Carbon Dioxide (CO2), HFC-125,Halon and 3M NOVEC 1230 Fire Extinguishing Agents.CO2, HFC-125 (Pentafluoroethane), Halon 1211 (MIL-DTL-38741, Bromochlorodifluoromethane), Halon 1301 (ASTMD 5632, Bromotrifluoromethane) and 3M NOVEC 1230evaporate rapidly. Therefore, no cleanup is required unlessmoisture or a high temperature was present at the area ofapplication; but ventilation should always be provided to re-move the vapors. If moisture or high temperature was pres-ent, use the following cleanup procedures:
NOTE
Even though carbon dioxide, HFC-125 Halon andNOVEC 1230 fire extinguishing agents leave noresidues; smoke, smudges, or other grime from afire should be removed from affected items thatare to be retained for future use.
a. After a fire has been extinguished, purge area and sur-faces with clean, dry air (dust and oil free, low mois-ture content, compressed air).
b. Clean surfaces with a solution of one part MIL-PRF-87937, Type IV or MIL-PRF-85570, Type II aircraftcleaning compound in nine parts of water. Scrub af-fected areas and rinse with clean, fresh water. Drainaway excess water.
c. Dry with cloths, paper towels, and/or dry, oil free com-pressed air at a pressure not greater than 10 PSI.
d. Apply MIL-PRF-81309, Type III or MIL-L-87177,Type I or II, Grade B water displacing CPC to all avi-onic components and electrical connectors. Apply aliberal amount of MIL-PRF-81309, Type II or MIL-L-87177, Type I or II, Grade B water displacing CPC toall other areas that cannot be properly drained or con-tain recesses which are difficult to reach.
e. Enter a notation defining the affected areas, and whereand how they were treated in the appropriate aircraft,missile, or equipment forms with a requirement for aspecial inspection as corrosion prone areas at a speci-fied future time to determine if any corrosion has oc-curred.
8.5.6 Removal of Protein Type Foam and Soda-AcidFire Extinguishing Agents. The residues left from the useof these materials can be very corrosive to aircraft, missiles,and equipment. Remove these residues as follows:
a. Thoroughly flush the affected area with fresh water.Ensure that the rinse water is completely flushed fromthe aircraft, missile, or equipment.
b. Clean surfaces with a solution of one part of MIL-PRF-87937, Type IV or MIL-PRF-85570, Type II air-craft cleaning compound in nine parts of water. Scrubaffected areas and rinse with clean, fresh water. Drainaway excess water.
c. Dry with cloths, paper towels, and/or dry, oil free com-pressed air at a pressure not greater than 10 PSI.
d. Apply MIL-PRF-81309, Type III or MIL-L-87177,Type I or II, Grade B water displacing CPC to all avi-onic components and electrical connectors. Apply aliberal amount of MIL-PRF-81309, Type II or MIL-L-87177, Type I or II, Grade B water displacing CPC toall other areas that cannot be properly drained or con-tain recesses which are difficult to reach.
e. Enter a notation defining the affected areas, and whereand how they were treated in the appropriate aircraft,missile, or equipment forms with a requirement for aspecial inspection as corrosion prone areas at a speci-fied future time to determine if any corrosion has oc-curred.
8.5.7 Treatment After Landing on a Foamed Runway.Materials used to foam runways are corrosive to aircraft. Assoon as possible after a landing on a foamed runway, exte-rior areas, wheel wells, any interior areas exposed, and en-gines shall be cleaned. Clean the exterior and wheel wells,interior areas, and engines in accordance with Section I ofChapter 3.
8.5.8 Treatment After Exposure to Volcanic Ash. Theprimary concern in removing volcanic ash is the extremeabrasiveness of the ash. It is not a significantly corrosivematerial. Aircraft, missiles, and equipment which have beenexposed to volcanic ash should be cleaned using the follow-ing procedures before the next aircraft, missile, or equipmentoperation.
a. All static ports, fuel vents, engine inlets, air condition-ing inlets, etc., should be vacuumed to remove as muchash as possible and then suitably covered to precludeadditional ash entry. Special emphasis should be placedon ducting supplying cooling air to avionics, electron-ics, and electrical equipment.
b. After covering all openings where ash may enter, theexterior of the airframe, missile, or equipment shouldhave ash removed initially using a vacuum, low pres-sure, compressed air (not to exceed 10 PSI), or bylightly dusting with clean rags. Avoid rubbing sincethis may damage painted and bare metal surfaces dueto the abrasiveness of the ash.
c. Wash entire aircraft, missile, or piece of equipment us-ing a mild MIL-PRF-87937, Type IV or MIL-PRF-85570, Type II alkaline cleaner and water solution (one
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Change 12 8-11
part cleaner to nine parts water) using procedures inSection I of Chapter 3 and rinse thoroughly with lowpressure water. Ensure that critical parts, such as flapscrews, tracks, and exposed hydraulic actuators are ad-equately cleaned. Again, caution should be taken whenwashing to avoid vigorous rubbing/scrubbing, since ashis even more abrasive when combined with water toform a slurry.
d. Check windshield wiper blades to ensure that all con-taminants are removed prior to operation.
e. If ash penetration is evident in the aircraft interior (thecockpit, cargo area, avionics compartments, and otheraccessible interior areas) or interior areas and compart-ments of missiles and equipment, they should be thor-oughly vacuumed.
f. Check lower aircraft, missile, and/or equipment struc-tures for volcanic matter and water entrapment.
g. Clear all drains and air dry structures as much as pos-sible.
h. Uncover all openings which were covered during stepa.
i. After washing, the aircraft, missile, or piece of equip-ment must be lubricated in accordance with applicablesystem specific maintenance manuals.
8.6 SPECIFIC INTERNAL AREAS.
The cockpit, ejection seats, avionic and electrical equipment,identification and modification plates, and photographicequipment require specific emergency cleaning procedures.
8.6.1 Aircraft Cockpit Area. Emergency cleaning proce-dures for the aircraft cockpit are as follows:
a. If the interior is undrainable, drill out a few fastenersat low points. If still undrainable, drill holes at lowpoints as approved and directed by the aircraft SPD.
b. Remove avionics equipment, relay boxes, circuitbreakers and switches, and clean as specified in TO1-1-689-3.
c. Clean ejection seats. (Refer to Paragraph 8.6.2).
d. Turn equipment over to the activity that has the au-thority and capability to disassemble, clean, and repairthe equipment.
e. Dry equipment that has been cleaned as much as pos-sible with dry, oil free compressed air at a pressureless than 10 PSI, drying machines, electric fans, orhand fans in a hot room of 150° F (66° C) maximumor in a well ventilated room where the humidity is low.
f. Apply MIL-PRF-81309, Type II or MIL-L-87177, TypeI or II, Grade B water displacing CPC by spraying orbrushing onto all areas that cannot be properly drainedor contain recesses which are difficult to reach.
8.6.2 Aircraft Ejection Seats.
Disarm ejection seat mechanism before cleaning.Ensure that only authorized personnel disarm seatsand perform cleaning operations.
The following emergency cleaning procedure shall be usedfor cleaning aircraft ejection seats.
a. Remove parachutes, drogue parachutes (where appli-cable), and seat pans. Return them to the local survivalequipment work center for cleaning and/or replace-ment.
b. Remove ejection seat in accordance with the applicablesystem specific maintenance manual.
c. Rinse seat thoroughly with fresh water. Continue rins-ing while directing water into crevices and close fittingparts until contaminants are removed.
d. All CAD/PAD Escape System components are consid-ered Critical Safety Items (CSI). Therefore any CAD/PAD escape system component suspected of coming incontact with fire suppression agent must be removedfrom the escape system and condemned. Disarm andremove any suspect CAD/PAD component from es-cape system in accordance with applicable technicalmanual. Suspect CAD/PAD items will be placed incondition code “P” with the following remarks “Itemhas been exposed to fire suppression agent”. Turn inremoved components to the appropriate munitions au-thorities to be reported for disposal. Contact OO-ALC/GHGJ Item Manager to requisition replacement CAD/PAD items.
e. Remove as much water as possible from equipmentwith vacuum or low pressure, clean, dry, oil free com-pressed air.
f. Dry off any remaining water with a clean cloth or pa-per towels.
g. Apply MIL-PRF-81309, Type II or MIL-L-87177, TypeI or II, Grade B water displacing CPC by either sprayor brush application to critical metal surfaces and re-cess areas which may not be completely dry. Waterdisplacing CPC protects equipment during necessaryinspections and/or inquiry and during transfer to thelocal survival equipment work center.
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8-12 Change 3
h. Wash all survival gear and pilot safety equipment withfresh water and dry thoroughly. Refer to applicablesystem specific maintenance requirements for detailedpreservation procedures. Lubricate and apply CPC’s inaccordance with the applicable system specific mainte-nance cards and Sections II and III of Chapter 3 in thismanual.
i. If necessary, send the entire ejection seat to the appro-priate ALC Depot for overhaul/repair.
8.6.3 Avionic, Electronic, and Electrical Equipment.
Ensure that all electrical power is disconnectedand all systems in the aircraft, missile, or equip-ment are deactivated before starting the cleaningoperation on avionics, electronic, or electricalequipment to prevent electrical shock.
Effective cleaning ensures that salt water, fire fighting chemi-cals, and other corrosive agents are completely removed toprevent corrosion damage. Refer to TO 1-1-689-3 for spe-cific cleaning procedures.
8.6.4 Photographic Equipment. Use the following pro-cedure for cleaning photographic equipment.
a. Immediately rinse with fresh water, drain, and rinseagain.
b. Apply MIL-PRF-81309, Type III or MIL-L-87177,Type I, Grade B water displacing CPC by spraying.
c. Return to the appropriate photographic equipment tech-nician for prompt servicing.
8.6.5 Graphite or Carbon Fiber/Epoxy, Boron Fiber/Epoxy, and Tungsten Fiber/Epoxy Composite Materials.
• The inhalation of graphite, boron, or tungstencomposite fibers resulting from aircraft, missile,or equipment fires and/or material damage maybe harmful to personnel. Wear a cartridge typerespirator and goggles when exposed to thesematerials, and, in addition, wear close weavecotton gloves when handling these materials.Request the assistance of the local Bioenviron-mental Engineer and safety officer to provide
specific information regarding hazards to per-sonnel during cleanup operations involvingthese materials and the required PPE.
• Do not put power to or start up any aircraft,missile, piece of equipment, or other avionic/electronic/electrical equipment which havebeen exposed to debris until decontaminationby vacuuming and/or washing is completed.Failure to observe these procedures may resultin electrical short circuits and fires.
Aircraft, missile, or equipment constructed utiliz-ing graphite, boron, or tungsten fiber compositematerials in contact with metal structures or sub-structures create a high potential for establishinggalvanic corrosion cells. This can result in corro-sion of the metal components if the structure isexposed to an electrolyte medium, such as saltwater.
The graphite, boron, and/or tungsten fibers of composite ma-terials may be released into the atmosphere if their epoxybinder burns; this occurs at temperatures in excess of 600º F(316º C). In addition, fibers may be released during an ex-plosion or a high impact crash. Since graphite, boron, andtungsten are very conductive, these fibers can damage unpro-tected avionic, electronic, and electrical equipment withinseveral miles of the incident site by settling on and shortingout electrical contacts. The procedures for treating damagedcomposite materials are listed below. Refer to TO 1-1-690for additional information.
8.6.5.1 Cleanup. When damaged aircraft, missiles, orequipment have graphite, boron, or tungsten fiber compositesurfaces which are broken or burned, follow these proce-dures.
a. If ventilation inlets are exposed to debris, take imme-diate action to ensure that the filtration system is prop-erly operating. If the system is not operating properly,shut down the system and provide temporary filtrationat outlets leading to compartments with electrical, avi-onic, and electronic equipment.
b. Warn the flight crew of adjacent in-flight aircraft andmaintenance control for flight line operations that thesmoke may contain hazardous electrical contaminants.
c. Spray MIL-PRF-81309, Type II or MIL-L-87177, TypeI, Grade B CPC on damaged composite surfaces. Thiswill prevent the spread of graphite, boron, or tungsten
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Change 3 8-13
fiber contamination by causing the fibers to stick to-gether and/or to the damaged surface. Cover damagedsurfaces with plastic sheet and tape it securely in place.
d. Aircraft, missiles, facilities, clothing, and equipmentthat have been exposed to debris from the aircraft,missile, or equipment fire must be vacuumed and/orwashed down prior to reuse or movement into a han-gar.
e. Decontamination of the immediate area of the aircraft,missile, or equipment wreckage may require vacuum-ing, washing, and bagging of composite material frag-ments. Use a sealed industrial vacuum and store thecollected debris in sealed plastic bags for the accidentinvestigation board. Dispose of the debris in accor-dance with applicable regulations when so directed bythe investigation team.
f. If wrapping and secure taping of the aircraft, missile,or equipment wreckage is not possible, transporting thewreckage must be planned to bypass heavily populatedand industrial areas. Aircraft, missiles, or equipmentparked or located along the planned route must havetheir canopies and access doors closed and their engineinlet and exhaust openings, air intakes and outlets, andall other vents and ports covered. In addition, the doorsand windows of surrounding buildings should be closedto minimize the probability of having wind-blown fi-bers enter areas containing electrical and electronicequipment.
8.7 SPECIFIC EXTERNAL AREAS OF AIRCRAFT.
The following external aircraft areas require emergencycleaning after exposure to fire and fire fighting agents.
8.7.1 Airframes. Use the following procedure for cleaningairframes.
a. Flush all areas with fresh, clean water while drainingat the same time. Whenever possible, units or compo-nents that have been removed from the aircraft shouldbe immersed in fresh water and then flushed thoroughlywith clean, fresh water. Drain away the water and drythe areas with cloths, paper towels, or dry, oil freecompressed air at a pressure of less than 10 PSI.
b. Clean with a solution of one part of MIL-PRF-87937,Type IV or MIL-PRF-85570, Type II aircraft cleaner innine parts of water. Scrub affected areas with the solu-tion. Flush thoroughly with fresh water and drain awaythe excess water. Dry with cloths, paper towels, or dry,oil free compressed air at a pressure of less than 10PSI.
c. Apply a liberal amount of MIL-PRF-81309, Type II orMIL-L-87177, Type I or II, Grade B water displacing
CPC by spraying or brushing to all other areas thatcannot be properly drained or contain recesses whichare difficult to reach, to aid in the removal of water.
d. If the aircraft fuselage, empennage, or wings are in arepairable condition, drain holes may be provided fordraining water by drilling out rivets at the lowestpoints. All repairable parts shall be collected and re-turned with the aircraft when shipment is made.
8.7.2 Antennas. Remove antennas per instructions in thesystem specific aircraft and/or specific equipment mainte-nance manual. Treat in accordance with TO 1-1-689-3. Ac-complish any in place cleaning as follows:
a. Check antenna insulators for damage or cracks.
b. Brush or spray a solution of one part MIL-PRF-87937,Type IV or MIL-PRF-85570, Type II aircraft cleaningcompound in nine parts water onto the antenna and theaffected adjacent area, and scrub the area with a small,soft brush or wiping cloth dipped in the above clean-ing solution.
c. Rinse with clean, fresh water.
d. Dry the area with a clean, dry cloth.
8.7.3 Reciprocating Engines.
a. Determine the extent of contamination.
b. Drain all fluids. Partial disassembly is authorized toaccomplish thorough draining. Ensure that pressuresystems and cylinders are drained.
c. Thoroughly flush all surfaces and passages with freshwater.
d. Apply A-A-59601, MIL-PRF-32295, Type II, or MIL-PRF-680, dry cleaning/degreasing solvent to the af-fected areas with a brush, cloth, or non-atomizingspray, and scrub the area with a brush or cloth.
e. Flush all accessible interior surfaces and all passageswith either a solution of one part MIL-PRF-85704,Type II turbine engine gas path cleaning compound infour parts fresh water or use the straight undiluted formof MIL-C-85704, Type II ready-to-use (RTU) cleaner.Both the Type II and Type II RTU are aqueous clean-ers without any hydrocarbon solvents.
f. Thoroughly rinse all areas with fresh water.
g. Allow to thoroughly drain. Dry, using paper towels,cloths, or dry, oil free compressed air at a pressure ofless than 10 PSI.
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8-14 Change 5
h. Apply a liberal amount of MIL-PRF-81309, Type II orMIL-L-87177, Type I or II, Grade B water displacing
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Change 3 8-14.1/(8-14.2 blank)
CPC to all surfaces. This may be accomplished by fill-ing and draining (preferred), flushing, or spraying. Ro-tate the propeller shaft to coat cylinder walls. Drainexcess CPC.
i. Reassemble engine finger tight.
j. Lubricate any pressure lubrication points to displaceall contaminated lubricant.
k. For shipping, place engine in an approved dehydratedmetal container, using twice the normal amount of des-iccant. Notify the engine SPM to arrange for specialhandling, as required.
8.7.4 Turbine Engines. Engines which are contaminatedwith small amounts of sea water entering the intake shall becleaned using MIL-PRF-85704 engine gas path cleaner inaccordance with Table 3-2 and the engine system specifictechnical/overhaul manuals. Decontaminate engines that havebeen completely submerged in fresh water or sea water asfollows:
a. Drain all fluids. Partial disassembly is authorized toaccomplish thorough draining.
b. Thoroughly flush all surfaces and passages with freshwater.
c. Flush all accessible interior surfaces and all passageswith either a solution of one part MIL-PRF-85704,Type II turbine engine gas path cleaning compound infour parts fresh water or use the straight undiluted formof MIL-C-85704, Type II RTU cleaner. Both Type IIand Type II RTU are aqueous cleaners without anyhydrocarbon solvents.
d. Thoroughly rinse all areas with fresh water.
e. Drain thoroughly.
f. Apply a liberal amount of MIL-PRF-81309, Type II orMIL-L-87177, Type I or II, Grade B water displacingCPC to all surfaces. This may be accomplished by fill-ing and draining (preferred), flushing, or spraying.Drain excess CPC. Repeat this procedure until alltraces of water have been removed.
g. Lubricate any pressure lubrication points to completelydisplace all contaminated lubricant.
h. For shipping, install in an approved dehydrated metalcontainer, using twice the normal amount of desiccant.Notify the engine SPM to arrange for special handling,as required.
8.7.5 Treatment for Engines Which Have Ingested FireExtinguishing Powder (Potassium Bicarbonate [PurpleK{PKP}], Sodium Bicarbonate, Ammonium PhosphateMonobasic) and/or Synthetic Foaming Agents (AFFF,Hi-Ex, AR).
NOTE
Ammonium phosphate monobasic, often identifiedas Class ABC extinguishing agent, can be highlycorrosive to aircraft components; removal andcleaning should be addressed as an emergency.
a. With the ignition off/disconnected, vacuum up as muchof the loose powder/foam as possible followed bycranking the engine and rinsing it thoroughly with wa-ter.
b. Wash the engine with MIL-PRF-85704 gas path cleanerper instructions in Table 3-2 and Paragraph 8.5.4 andParagraph 8.5.7.
c. Flush all accessible interior surfaces and all passageswith either a solution of one part MIL-PRF-85704,Type II turbine engine gas path cleaning compound infour parts fresh water or use MIL-PRF-85701, Type II,RTU cleaner undiluted. Both Type II and Type II RTUare aqueous cleaners without any hydrocarbon sol-vents.
d. Based on the high-temperatue metals and unique coat-ings/finishing materials used in the manufacturing ofthese end items, cleaning of engines exposed to anyfire or fire extinguishing products, requires consultingthe weapon system specific technical order, depot over-haul manual/procedures, original equipment manufac-turer (OEM) manual, and the appropriate engine engi-neering authority for potential additional actionsrequired such as dismantling of the engine.
e. Drain engine lubricant/oil and refill/service.
f. At the next inspection, recheck previously contami-nated areas and repeat the above procedure, ifnecessary.
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Change 1 8-15
8.7.6 Helicopter Transmission, Rotor Head, and RotorHub. Helicopter transmission, rotor head, and rotor hub casesare often constructed of magnesium. Magnesium parts ex-posed to salt water or fire fighting chemicals require imme-diate and thorough decontamination and preservation.
8.7.6.1 External Surface Contamination. Treat helicop-ter transmissions, rotor heads, and rotor hubs with externalsurface contamination as follows:
a. Rinse with fresh water.
b. Wash with a solution of one part MIL-PRF-87937,Type IV or MIL-PRF-85570, Type II aircraft cleaningcompound in nine parts fresh water or use A-A-59921(formerly MIL-C-43616), Class 1A aerosol type sol-vent emulsion aircraft cleaner per instructions in Sec-tion I of Chapter 3, and rinse thoroughly.
c. Apply a liberal amount of MIL-PRF-81309, Type II orMIL-L-87177, Type I, or II, Grade B, water displacingCPC to all affected areas by spraying or brushing.
d. Lubricate all pressure lubrication points to displace allcontaminated lubricant.
8.7.6.2 Internal Surface Contamination. If internal sur-face contamination of helicopter transmissions, rotor heads,and gearboxes is suspected, immediately contact the appro-priate helicopter SPD for assistance with decontaminationprocedures. Treat helicopter transmissions, rotor heads, rotorhubs, and gear boxes having internal contamination as fol-lows:
a. Drain all fluids. Partial disassembly is authorized toaccomplish thorough draining. Ensure that pressuresystems are drained.
b. Thoroughly flush all surfaces and passages with freshwater.
c. Flush all surfaces and passages with a solution of onepart MIL-PRF-87937, Type IV or MIL-PRF-85570,Type II aircraft cleaning compound in nine parts freshwater per instructions in Section I of Chapter 3.
d. Thoroughly rinse all areas with fresh water.
e. Allow to drain thoroughly.
f. Apply a liberal amount of MIL-PRF-81309, Type I orMIL-L-87177, Type I or II, Grade B water displacingCPC to all surfaces. This may be accomplished by fill-ing and draining (preferred), flushing, or spraying.With the housing full of preservative, rotate the main
shaft approximately five revolutions. After the preser-vative has remained in the housing for 4 hours, drain,and replace plugs.
g. Service the transmission, rotor head, rotor hub, and/orgear box in accordance with the applicable system spe-cific maintenance manual if going back in service orleave as preserved if the unit will be shipped out.
h. Lubricate all pressure lubrication points to displace allcontaminated lubricant.
8.7.7 Helicopter Main and Tail Rotor Blades. Helicop-ter blades that have been exposed to an excessive amount ofsalt water or to liquid fire fighting chemicals shall be treatedas follows:
NOTE
Some rotor blades have areas commonly knownas pockets or blade boxes with very small drainholes. The drain holes may require enlargement, ifblades were salt water immersed, to facilitate de-contamination of the blade spar. Enlarging drainholes destroys the affected pockets or blade boxesand requires Depot Level repair before the bladecan be reused. Enlargement of pocket access open-ings requires authorization from the appropriatehelicopter SPD and blade SPM for each blade in-volved. Where possible, flush pockets with MIL-PRF-81309, Type II or MIL-L-87177, Type II,Grade B water displacing CPC. Preserve and pack-age the blade properly before sending it to the ap-propriate ALC Depot for engineering evaluationand necessary repair.
a. Thoroughly flush all contaminated surfaces with freshwater. Pay particular attention to recesses that tend totrap debris such as mud, dirt, or salt deposits.
b. Wash with a solution of one part MIL-PRF-87937,Type IV or MIL-PRF-85570, Type II aircraft cleaningcompound in nine parts fresh water per instructions inSection I of Chapter 3.
c. Rinse thoroughly with fresh water.
d. Dry with a cloth, paper towels or dry, oil free com-pressed air at a pressure of less than 10 PSI.
8.7.8 Armament. The following instructions are for initialtreatment of armament equipment that has undergone saltwater immersion or been subjected to fire extinguishingchemicals.
TO 1-1-691
8-16 Change 5
8.7.8.1 Safety Precautions. Before performing anycleaning chores, make certain that preliminary safety precau-tions are followed.
a. Ensure that the aircraft, missile, or piece of equipmentis safe for maintenance.
b. Disconnect all electrical power and ensure that all ar-mament switches are in the OFF or SAFE positions.
NOTE
For removal of armament equipment, refer to ap-plicable system specific maintenance/technicalmanual for the respective aircraft, missile, or pieceof equipment.
c. Remove all ordnance from the aircraft or piece ofequipment and all warheads from the missile and prop-erly dispose of contaminated ammunition and war-heads, as required.
8.7.8.2 Cleaning Procedure. After complying with thesafety precautions, clean per the following procedure.
TO 1-1-691
Change 1 8-16.1/(8-16.2 blank)
a. Rinse equipment with fresh water.
b. Disassemble, as required, and wipe away excess greasewith clean cloth dampened with A-A-59601 or MIL-PRF-680, Type II or III dry cleaning/degreasing sol-vents.
c. Immerse and agitate parts in a solution of one partMIL-PRF-87937, Type IV or MIL-PRF-85570, Type IIaircraft cleaning compound in nine parts of fresh wa-ter.
d. Rinse parts with fresh water to ensure complete re-moval of contaminants.
e. Wipe away excess water with clean, dry cloth.
f. Blow dry the cleaned equipment/parts as thoroughly aspossible with clean, dry, oil free compressed air at apressure of less than 10 PSI.
g. Inspect the equipment to determine whether it shouldbe returned to service or forwarded to the appropriateALC Depot for overhaul or repair.
h. Apply a liberal amount of MIL-PRF-81309, Type II orMIL-L-87177, Type I or II, Grade B water displacingCPC by either spray, brush, dip, or fill and drain appli-cation.
i. If shipment to the prime ALC Depot for maintenanceis required, wrap the equipment in MIL-PRF-131, Class1 barrier material, package it per the applicable in-structions, and forward it to the depot as directed.
8.7.9 Aircraft Fuel Systems. For emergency treatment ofaircraft fuel systems contaminated with water through otherthan a water crash or fire damage, refer to TO 1-1-3.
TO 1-1-691
8-17/(8-18 blank)
CHAPTER 9SOUTHWEST ASIA ENVIRONMENTS
9.1 INTRODUCTION.
The Southwest Asia (SWA) Area of Responsibility (AOR)consists of various conditions ranging from seasonal highwinds and high humidity to arid areas and low winds. Inmany locations, there are negatively charged ions (called an-ions) in soils that when combined with aggressive sandstorms, can spread throughout SWA. (Refer to Figure 9-1).The extent that sand and dust can penetrate equipment isdependent on many variables such as wind speed and direc-tion, size of the dust particles, protective shelter availabilityat the site, and equipment problems such as bad seals, gas-kets, and bent doors. Although sandstorms are usually sea-sonal, during the periods of relative calm there can be asignificant amount of airborne dust seen as a general haze inthe atmosphere. (Refer to Figure 9-2).
NOTE
Asterisks before Air Base name and locationwithin Table 3-1 designate environments consid-ered as SWA.
9.1.1 Climatic Conditions. SWA contains varied climaticand environmental conditions. Temperatures can changedrastically from day to night. A desert environment is largelytypical of SWA with the exception of coastal areas and areaswith bodies of water close by such as rivers, streams, andlakes. In certain areas of SWA, where there is low relativehumidity and rainfall, the dry air tends to decrease the cor-rosion initiation and propagation action. In contrast, flightsover bodies of water, and operations near coastal areas withhigher humidity and recurring fog, provide moisture to ex-tract soluble anions. These environments assist in the devel-opment of electrolytes for corrosion initiation. The potentialfor corrosion increases when moisture in the form of highhumidity (greater than 70%), rainfall, dew, fog, etc., com-bine with fine dust and sand containing corrosive anions suchas chlorides, sulfates, nitrates and fluorides. During the day-light hours, the equipment stored outdoors will normally heatup causing expansion of panels allowing hot moist air tomigrate into enclosed areas or under non-breathable fabriccovers. When the equipment cools, moisture condenses andcombines with dust particles and sand settling on metal sur-faces which increases the potential for corrosion. The solublematerials in the sand form a crust as they dry, making re-moval difficult.
9.1.2 Aircraft Wash. Aircraft shall be washed in accor-dance with Table 3-1. If the water quality does not meetcriteria established in Paragraph 3.1.1, the unit must requesta waiver in accordance with the NOTE in Paragraph 3.2.2.1.
9.1.3 Aircraft Clear Water Rinse (CWR). CWR require-ments in Paragraph 3.2.3 are not applicable to SWA loca-tions. If units need to remove dust and sand for operationalor specific maintenance reasons, dry cleaning processes suchas vacuum, brush, compressed air, etc., should be used to thegreatest extent possible. In rare cases where rinse operationsmust be performed to remove accumulated dust and sand,water must meet the quality specified in Paragraph 3.1.1.After these limited rinse operations have been completed,accumulated water must be removed to minimize effects ofchlorides found in many of the dusts and sands of the SWAenvironment.
9.1.4 Effects of Desert Environment. Soils in many ofthe SWA operating locations will cause or accelerate existingcorrosion if left in contact with metal surfaces in high hu-midity conditions or in the presence of other moisture. How-ever, if some type of moisture is not present, these soils,although high in potentially corrosive salts, do not supportcorrosion cell initiation or propagation. In all cases, the soilsshould be considered suspect and be regularly removed whilein country, or as soon as practical after the equipment returnsto home station.
NOTE
Recommend specific System Program Director(SPD)/System Program Offices (SPO) in conjunc-tion with affected MAJCOM Corrosion FunctionalManagers to develop a detailed checklist for eachweapon system. Standardized checklists for eachphase of a deployment for aircraft and associatedequipment will greatly improve the overall condi-tion when operating in SWA environments and in-crease equipment survivability and serviceability.Some general requirements in the absence ofweapons systems guidance are included in Para-graph 9.3 and Paragraph 9.4. This list may not beinclusive of all tasks.
9.2 PRE-DEPLOYMENT RECOMMENDATIONS.
a. Inspect entire aircraft exterior for missing and chippedprimer and/or paint. Correct all discrepancies prior todeployment.
b. Inspect and replace any worn, torn or cracked sealsand gaskets that will allow sand and dust intrusion.
c. Accomplish a complete wash prior to deployment.
TO 1-1-691
Change 14 9-1
d. Remove all standing water.
e. Inspect all drain holes and unplug if needed.
f. Minimize aircraft lubrication by removing all excessgreases to limit sand and dust entrapment.
9.3 RECOMMENDED ACTIONS WHILE DE-PLOYED.
Soils in operating locations in SWA should be consideredsuspect and be regularly removed. A constant regimen ofvacuuming, brushing, etc., to remove dust and sand accumu-
lation is necessary to reduce potential corrosion problems.Limit the use of compressed air to areas that will not causethe sand and dust to migrate and settle on other areas andcomponents.
9.3.1 High Efficiency Particulate Air (HEPA) Filtration.HEPA filtration vacuum cleaners should be used to greatestextent because SWA sand and dust particulates are commonly10 microns or smaller. Numerous manufacturer’s producecommercial off-the-shelf vacuum systems that are suitablefor SWA sand and dust removal.
9.3.1.1 Pneumatic Wheeled Units. Air volume con-sumption is 30-60 CFM. Used for cargo decks or large sur-faces where space is available.
9.3.1.2 Pneumatic Backpack. Air volume consumptionis 70 CFM. Portable for difficult to access areas in flightdecks, latrines, and medium sized wheel wells. It can beremoved from the backpack frame for hand held use.
NOTE
The units above require large volumes of air andare used in situations where electricity is unavail-able or restricted for use.
a. Electric models in floor and backpack are available in110-460 Volts @ 60 Hertz.
b. Battery pack portable units, requires 12-18 Volt batterypacks. Used for extremely small/confined areas suchas cockpits, avionics bays, and main and nose landinggear of fighter aircraft.
9.3.2 Areas to be Checked and Cleaned. Listed beloware some of the areas that should be checked and cleaned.
• Wheel Wells.
• Exposed control cables, pulleys, and gears.
• Flap wells, control surface wells, personnel restraintattach points.
• Access doors and service compartments.
• Crew entry and exit doors. Latch release doors andpanels.
• Cockpit interior and flight decks.
• Inside engine pylons and lower sections of nacelles.
• Cargo ramps and recessed areas of cargo decks.
• Avionic instruments, electrical panels and bays (re-fer to Figure 9-3), especially those with coolingvents and intake fans.
Figure 9-1. Soil Makeup in the SWA Area
Figure 9-2. Global Dust Producing Regions
TO 1-1-691
9-2 Change 14
• All areas susceptible to standing water. Keep alldrain holes open by inserting a probe, such as apipe cleaner before and after vacuuming.
NOTE
If sand is hard and crusted, gently break up withnon-metallic tool and remove with vacuum.
9.4 POST DEPLOYMENT.
a. Inspect all areas listed in Paragraph 9.3.2.
b. Remove as much entrapped sand and dust as practicalwith dry cleaning processes such as vacuum, brush,compressed air, etc.
c. Perform thorough aircraft wash (NLT 30 days), afterarrival to home station.
d. Remove all standing water.
e. Inspect exterior surfaces for areas of missing primerand paint erosion. Correct all deficiencies.
9.5 CORROSION PREVENTIVE COMPOUNDS(CPC’S).
Corrosion preventive compounds are used to protect aircraft,missile, and equipment parts and components by preventingcorrosive materials from contacting and corroding bare metalsurfaces. Section IV, Chapter 3 of this TO lists CPC typesand applications. Recommend applying these products aheadof scheduled deployment if known.
9.5.1 Recommended CPC’s. Since general purpose, soft,oily CPC’s such as MIL-PRF-81309, Type II and MIL-PRF-16173, Grades 1, 2, and 4 have a tendency to attract andhold sand and dust particles, they should not be used in SWAenvironments unless mandated in weapons system specificTO’s. In all cases, CPC’s should be used sparingly and anyexcess removed at the time of application. MIL-L-87177 andMIL-PRF-81309, Type III deposit ultra-thin films that areless susceptible to sand and dust accumulation, so theyshould continue to be used in all the applications addressedin this TO, TO 1-1-689 series, and all weapons specific TO’s.MIL-DTL-85054 produces a dry, thin film that also does notattract and hold dust and sand particles. Apply this CPC toaircraft or equipment surfaces for temporary protection ifconventional primers and topcoats are not available or otherlimitations prevent their use. This CPC is not suitable for useon the interior of electrical or electronic equipment or con-nectors.
Figure 9-3. Open Circuit Board
TO 1-1-691
Change 14 9-3/(9-4 blank)
CHAPTER 10REMOTELY PILOTED AIRCRAFT CORROSION PREVENTION
10.1 REMOTELY PILOTED AIRCRAFT (RPA).
An unmanned aerial vehicle is capable of being controlledfrom a distant location through a communication link. RPAscan be expendable or recoverable; however most are nor-mally designed to be recoverable.
10.1.1 Definition. RPAs range in size from micro vehiclesmeasuring inches in size to large aircraft. The RPAs are cat-egorized in Tiers as shown in Table 10-1. The maintenancerequirements for a micro/small air vehicle cannot be equatedwith those for a Tier II or higher such as a Global Hawk.Tier II RPAs are generally disassembled between missions
for transport and storage. RPAs tend to make extensive useof composite materials. Repair and maintenance of these ma-terials may require special expertise and equipment to dealwith hazardous materials.
NOTE
There is a particular concern that frequent assem-bly and disassembly of these aircraft may damagethe composite structures. Maintainers should con-sult TO 1-1-690 for information directly related tomaintenance or repair of composite materials.
Table 10-1. Air Force RPA Tiers
RPA Tier Definition Example Role Operating Altitude (Ceiling)Tier N/A Micro/Small (Man-Portable) BATMAVTier I Low Altitude, Long Endurance Gnat 750Tier II Medium altitude, Long Endurance
(MALE)MQ-1 Predator MQ-9
Reaper Less than 18,000 ft
Tier II+ High Altitude, Long Endurance Conven-tional RPA (or HALE RPA) Comple-mentary to the Tier III aircraft
RQ-4 Global HawkLess than 18,000 ft * some air-
craft in this class will exceed18,000 ft
Tier III High Altitude, Long Endurance Low-Ob-servable RPA. Same Parameters as, andcomplementary to, the Tier II+ aircraft
RQ-170 Sentinel Less than 18,000 ft
10.2 CORROSION CONTROL PROGRAM.
A comprehensive corrosion control program is necessary forthe prevention, early detection, reporting, and repair of cor-rosion damage/material degradation. An effective corrosionprevention program shall include thorough cleaning and in-spections at specific intervals. All maintenance personnelshall report corrosion promptly, in accordance with estab-lished directives.
10.3 CARBON FIBER COMPOSITES AND CORRO-SION.
The advantages of composites are many, including lighterweight, the ability to tailor the layup for optimum strengthand stiffness, improved fatigue life, and corrosion resistance.Some disadvantages of composites include adverse effects oftemperature and moisture, susceptibility to impact damage
and delamination or ply separation. Composites may also bemore difficult to repair.
10.3.1 Corrosion Concerns. One of the most seriousproblems with the use of carbon/graphite is the interface be-tween the composite containing carbon fibers and any metal-lic materials. An electrical potential exists between the twomaterials, which can be aggravated by humidity or waterimmersion or intrusion. The electrical potential over timewill cause the carbon composite to act as a cathode, allowinggalvanic corrosion, unbonding and delaminations. Designersspecify separating the carbon composite and the metal bybarriers such as fiberglass, sealants, AV-Dec gaskets or paint.Unfortunately, this treatment merely slows down the corro-sion rate, not eliminate it. The potential difference betweensteel/aluminum fasteners in carbon/graphite composites canpromote severe galvanic corrosion in the alloys.
TO 1-1-691
Change 4 10-1
10.3.2 Moisture Absorption. Absorbed moisture andmoisture intrusion is a major concern for composite materi-als. The amount of absorbed moisture depends on the mate-rial and the relative humidity or exposure to other moisturesources. Elevated temperatures increase the rate of moistureabsorption. Absorbed moisture reduces the mechanical prop-erties and causes the material to swell, which can cause thematerial to delaminate.
10.4 CORROSIVE ENVIRONMENTS.
One advantage to RPAs and corrosion protection is that theyare generally stored indoors where they are not exposed tocorrosive effects of the environment. Corrosive environments(Refer to Paragraph 2.9), which are characterized by theirpH factor, temperature, UV exposure, and moisture, continu-ously degrade composites until they cannot sustain the loadthat they were initially designed for.
10.5 APPROVED CLEANING COMPOUNDS.
• Authorized cleaning agents and equipment arelisted in this chapter, Appendix A, and Appen-dix B. Order materials and equipment by NSNfrom the list in these appendices through regu-lar supply channels, or local purchase fromvenders listed on the most current QPL/QPD ofa specification or by vender part number listedin these appendices for an authorized non-specification material.
• Do not use unauthorized cleaners. Althoughother commercial cleaners may appear to per-form as well, or better than, approved products,these materials may accelerate degradation ofnon-metallic materials causing material failureswhich may result in fluid leakage, corrosion ofsurrounding metals, electrical shorts, crazing,and/or mechanical failure.
10.5.1 MIL-PRF-87937, Type IV and MIL-PRF-85570,Type II. MIL-PRF-87937, Type IV and MIL-PRF-85570,Type II are water dilutable and biodegradable materials andare the primary cleaners for washing the exterior of aircraft.They are excellent materials for removing light to mediumsoils (grease, oils, grime, etc.) from almost all surfaces. Sincethey contain no solvents, their use is not limited, except thatapproval by the SPO is required prior to use on transparentplastics and camera lenses. These cleaners may be used invarious dilutions for hand wipe cleaning of greasy and oilyareas. Apply them from a pump spray bottle followed bydrying with a clean lint free cloth (Appendix A). When ap-plied from a spray bottle the most dilute mixture is recom-mended.
10.5.2 MIL-PRF-87937, Type III and MIL-PRF-85570,Type V. MIL-PRF-87937, Type III and MIL-PRF-85570,Type V are gel type cleaners intended for full strength appli-cation with no dilution in areas requiring special cleaning.They contain small amounts of solvents, detergents, andthickening agents, which make them cling very well to ver-tical and overhead surfaces. To be most effective, these ma-terials are applied full strength with no pre-rinsing of thesurface, allowed to dwell 5 to 15 minutes, agitated with anon-metallic bristle brush, and then rinsed thoroughly withtap water. These cleaners are not intended for and shall notbe used on transparent plastic aircraft canopies, windows,windshields/windscreens and camera lenses.
10.5.3 A-A-59921 (Formerly MIL-C-43616), Class 1AEmulsion Cleaner. A-A-59921 (formerly MIL-C-43616),Class 1A (aerosol ready-to-use with no dilution) emulsioncleaner is very effective for removal of oily and greasy soilsfrom general exterior painted and unpainted areas.
NOTE
A-A-59921 (formerly MIL-C-43616), solventemulsion cleaners shall not be used on non-poly-urethane paint systems, transparent plastics, ormarkings as their high solvent content can causethem to fade and /or streak. These cleaners alsoleave a very thin oil and/or solvent film on thesurface, so they are not suitable for use as a finalcleaner prior to painting, sealing, or adhesivebonding.
10.6 AIRCRAFT CLEANING.
Aircraft cleaning is the first step in preventing aircraft corro-sion. Cleaning requires knowledge of the materials and meth-ods needed to remove corrosion contaminates and fluids,which tend to retain contaminates. Aircraft should be cleanedregularly to:
• Prevent corrosion by removing salt deposits, othercorrosive soils, electrolytes, and fungi microbialgrowth.
• Maintain visibility though windows (camera lenses).
• Allow a thorough inspection for corrosion and cor-rosion damage.
• Maintain engine efficiency
• Reduce fire hazards by removal of accumulatedleaking fluids.
• Ensure aerodynamic efficiency of the aircraft.
TO 1-1-691
10-2 Change 5
10.6.1 Frequency of Cleaning. All aircraft should becleaned depending on usage, storage and the local environ-ment. Due to the material makeup of RPAs and concerns ofmoisture intrusion or absorption, RPAs may require less fre-quent cleaning than metallic aircraft. A more relaxed washrequirement will reduce the risk of water intrusion into theaircraft avionics bays and other vital sections of the fuselageand engine. Due to relaxed wash requirements, an extra em-phasis should be placed on waterless wipe down (Refer toParagraph 10.6.2).
10.6.1.1 Assembled RPA. Table 3-1 specifies the base orenvironmental and pollution data at each base and/or loca-tion unless a different interval is specified in a system spe-cific technical order. All assembled RPAs, should be washedas follows:
• Severe Environment every 90 days.
• Moderate/Mild Environment every 180 days.
NOTE
Micro/Small RPAs, small enough to be man-por-table, do not require scheduled washes. A water-less wipe down is sufficient prior to long-termstorage or when continuously exposed to severelycorrosive environments.
10.6.1.2 Disassembled and Container Stored RPAs.RPAs, except micro RPAs, disassembled and stored in con-tainers shall be washed prior to disassembly and storage. Itis recommended that aircraft be vacuumed or wiped clean atconnecting points and interior access points to remove alldust and contaminates. The interior of the storage containershould be visually checked for sand and debris and vacu-umed or wiped clean to ensure all contaminates are removedprior to placing aircraft parts in them for storage.
NOTE
To prevent the growth of fungus and mold all partsof aircraft should be allowed to completely dryprior to storage in containers.
10.6.2 Wipe Down or Spot Cleaning. Wipe down or spotcleaning procedures are an important process in maintainingcomposite aircraft. Composite materials are more susceptibleto contamination absorption therefore spot cleaning is rec-ommended when:
• Areas of concern from water intrusion
• Excessive exhaust gases accumulate
• Fluid leakage (oil, gas, etc.) occurs
• Exposure to salt spray, salt water, or other corrosivematerials occur.
• Oils and contaminates from maintenance being per-formed such as fingerprints, grease, etc. is present.
10.6.2.1 Wipe Down or Spot Cleaning Method. Thewipe down or spot cleaning method is as follows:
a. Using a plastic spray bottle, apply MIL-PRF-87937,Type IV or MIL-PRF-85570, Type II, (mixed one partcleaner to nine parts water) to the exterior surfaces ofthe aircraft (several square feet at a time).
b. After 30 seconds, scrub, then wipe cleaner and soilfrom the surface with a clean moistened lint-free cloth(Appendix A).
TO 1-1-691
Change 4 10-3/(10-4 blank)
APPENDIX ACONSUMABLE MATERIALS
A.1 INTRODUCTION.
Table A-2 provides consumable materials used for aircraft,missile, and equipment cleaning and corrosion preventionand control. Nomenclatures, specifications/PN’s, nationalstock numbers, unit of issue, and intended use of materialsare provided. Items are located by function in the followinggroupings.
• Abrasives.
• Conversion coating materials.
• Cleaning compounds.
• Cleaning pads/cloths.
• Corrosion preventive compounds.
• Lubricants.
• Neutralizing agents.
• Protective materials.
• Sealants and sealant accessories.
• Solvents.
A.1.1 Shelf Life. Specific shelf life guidance is providedin AFI 23-101 and DoD 4140.27-M. Units should use theShelf Life Extension Document (SLED) to validate the ser-viceability of materials. TO 42C-1-12 covers quality controlprocedures for chemical materials.
A.1.2 Consumable Materials Containers. Consumablematerials of a particular specification are provided in varioussized containers. If the particular sized container required isnot available or listed, ask supply department to provide thenext size container under the same specification.
A.1.3 Local Purchase. When local purchase is specified,include all procurement information, source of supply, andGSA contract number available.
A.1.4 Local Environmental Laws and Regulations.Prior to the procurement/use of any of specified products forcleaning, corrosion prevention, touch-up painting, etc., deter-mine and comply with all local environmental requirements,i.e., laws and regulations.
A.1.5 Unit of Issue Codes. The unit of issue codes in theunit of issue column and their meaning are as follows inTable A-1.
Table A-1. Unit of Issue Codes
Code Unit Code Unit Code UnitBG Bag EA Each PG PackageBO Bolt FT Foot PR PairBT Bottle GL Gallon PT PintBX Box GR Gross QT QuartCA Cartridge JR Jar RO RollCB Carboy KG Kilogram SE SetCC Cubic Cent. KT Kit SH SheetCN Can L Liter TU TubeCO Container LB Pound YD YardCS Case LG LengthDR Drum MX ThousandDZ Dozen OZ Ounce
TO 1-1-691
Change 15 A-1
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seA
BR
ASI
VE
S1
Abr
asiv
eM
ats,
Alu
-m
inum
Oxi
de,
Non
-Wov
en,
Non
-M
etal
lic
A-A
-580
54(s
uper
sede
sM
IL-A
-996
2)Ty
peI,
Cla
ss1
(9x
11in
SH)
Alu
min
umox
ide
impr
eg-
nate
dny
lon
fiber
web
bing
used
for
rem
ovin
gco
rro-
sion
prod
ucts
and
for
pain
tsc
uffin
gan
dfe
athe
r-in
ged
ges
prio
rto
touc
h-in
gup
.
Gra
deA
(Ver
yFi
ne)
5350
-00-
967-
5089
PG(1
0SH
)G
rade
B(F
ine)
5350
-00-
967-
5093
PG(1
0SH
)
Gra
deC
(Med
ium
)53
50-0
0-96
7-50
92PG
(10
SH)
2A
bras
ive
Pape
r,A
lu-
min
umO
xide
,N
on-W
ater
proo
f
(9x
11in
SH)
240
Gri
t53
50-0
0-16
1-97
15PG
(50
SH)
Dry
sand
ing
tore
mov
elig
htto
mod
erat
eco
rros
ion
prod
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.18
0G
rit
5350
-01-
322-
1122
PG(5
0SH
)
3A
bras
ive
Pape
r,Si
li-co
nC
arbi
de,
Wa-
terp
roof
AN
SIB
74.1
8(s
uper
sede
sA
-A-1
047)
(9x
11in
SH)
180
Gri
t
5350
-00-
721-
8117
PG(5
0SH
)W
etor
dry
sand
ing
tore
-m
ove
light
tom
oder
ate
corr
osio
npr
oduc
ts.
240
Gri
t53
50-0
0-22
4-72
05PG
(50
SH)
320
Gri
t53
50-0
0-22
4-72
03PG
(50
SH)
4A
bras
ive
Pape
r,Si
li-co
nC
arbi
de,
Non
-W
ater
proo
f
220
Gri
t53
50-0
0-22
4-72
09PG
(50
SH)
Dry
sand
ing
tore
mov
elig
htto
mod
erat
eco
rros
ion
prod
ucts
.32
0G
rit
5350
-00-
867-
7665
PG(5
0SH
)
5A
bras
ive
Pape
rD
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,Pr
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reSe
nsiti
veB
acki
ng,
Silic
onC
arbi
de
AN
SIB
74.1
8(s
uper
sede
sA
-A-2
697)
(6in
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sc)
180
Gri
t
5345
-01-
074-
9404
RO
(250
EA
)D
rysa
ndin
gto
rem
ove
light
tom
oder
ate
corr
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npr
oduc
ts.
For
use
with
pneu
mat
icdr
ills
oror
bita
lsa
nder
sw
itha
6in
chdi
-am
eter
pad.
280
Gri
t53
45-0
1-07
4-94
06R
O(2
50E
A)
6A
bras
ive
Clo
th,A
lu-
min
umO
xide
,W
a-te
rpro
of
AN
SIB
74.1
8(s
uper
sede
sA
-A-1
048)
(9x
11in
SH)
240
Gri
t
5350
-00-
865-
5948
PG(2
5E
A)
Wet
ordr
ysa
ndin
gto
re-
mov
elig
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mod
erat
eco
rros
ion
prod
ucts
.32
0G
rit
5350
-00-
597-
5798
PG(2
5E
A)
7A
bras
ive
Clo
th,A
lu-
min
umO
xide
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on-W
ater
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f
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SIB
74.1
8(s
uper
sede
sA
-A-1
048)
180
Gri
t(9
x11
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)
5350
-00-
192-
5051
PG(5
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Dry
sand
ing
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mov
elig
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erat
eco
rros
ion
prod
ucts
.18
0G
rit
(3x
150
ftR
O)
5350
-00-
229-
3095
RO
(50
YD
)24
0G
rit
(9x
11in
SH)
5350
-00-
161-
9715
PG(5
0E
A)
240
Gri
t(3
x15
0ft
RO
)53
50-0
0-22
9-30
80R
O(5
0Y
D)
320
Gri
t(9
x11
inSH
)53
50-0
0-24
6-03
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(50
EA
)
TO 1-1-691
A-2
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se32
0G
rit
(2x
150
ftR
O)
5350
-00-
187-
6289
RO
(50
YD
)32
0G
rit
(3x
150
ftR
O)
5350
-00-
229-
3092
RO
(50
YD
)8
Abr
asiv
eC
loth
,Si
li-co
nC
arbi
de,
Non
-W
ater
proo
f
AN
SIB
74.1
8(s
uper
sede
sA
-A-1
200)
(9x
11in
SH)
180
Gri
t
5350
-00-
192-
5051
PG(5
0SH
)D
rysa
ndin
gto
rem
ove
light
tom
oder
ate
corr
osio
npr
oduc
ts.
240
Gri
t(9
x11
inSH
)53
50-0
0-16
1-97
15PG
(50
SH)
240
Gri
t(2
x15
0ft
RO
)53
50-0
0-25
6-51
62R
O(5
0Y
D)
320
Gri
t(2
x15
0ft
RO
)53
50-0
0-48
2-55
85R
O(5
0Y
D)
9A
lum
inum
Woo
lA
-A-1
044,
Type
II,
Cla
ss1,
Form
A(M
ediu
m)
5350
-00-
286-
4851
RO
(1L
B)
Rem
ovin
gco
rros
ion
from
alum
inum
allo
ysu
rfac
es.
Type
II,
Cla
ss3,
Form
A(F
ine)
5350
-00-
312-
6129
RO
(1L
B)
10C
oppe
rW
ool
A-A
-104
4,Ty
peI,
Cla
ss3
(Fin
e)53
50-0
0-25
5-77
36R
O(1
LB
)R
emov
ing
corr
osio
nfr
omco
pper
allo
y,br
onze
,an
dbr
ass
surf
aces
.11
Stee
lW
ool,
Stai
nles
sA
-A-1
043,
Type
IV,
Cla
ss1
5350
-00-
440-
5035
RO
(1L
B)
Rem
ovin
gco
rros
ion
from
stai
nles
sst
eel
surf
aces
.12
Gla
ssB
ead
Med
ia,
Cle
anin
gan
dPe
en-
ing
AM
S24
31(A
MS
2431
/6=
AG
B-6
)(s
uper
sede
sM
IL-G
-995
4,Si
ze13
)
5350
-00-
576-
9634
BG
(50
LB
)G
lass
bead
blas
ting
med
iaus
edfo
rre
mov
ing
corr
o-si
onfr
omal
umin
umsu
r-fa
ces
byab
rasi
vebl
astin
g.13
Pum
ice
Abr
asiv
e,Po
wde
rSS
-P-8
21,
Gra
deFF
F
5350
-00-
161-
9034
CN
(5L
B)
Rem
ovin
gst
ains
orco
rro-
sion
onth
inm
etal
sur-
face
s.C
HE
MIC
AL
CO
NV
ER
SIO
NC
OA
TIN
G,
CO
RR
OSI
ON
RE
MO
VA
L,A
ND
SUR
FAC
ET
RE
AT
ME
NT
MA
TE
RIA
LS
TO 1-1-691
A-3
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se14
Cor
rosi
onR
emov
ing
Com
poun
dfo
rA
ir-
craf
tSu
rfac
es
SAE
AM
S16
40(s
uper
-se
des
MIL
-C-3
8334
)68
50-0
0-52
7-24
26C
N(5
GL
)A
conc
entr
ated
phos
phor
icac
idso
lutio
nm
ixed
1:1
with
wat
erus
edon
alum
i-nu
mal
loy
surf
aces
tore
-m
ove
surf
ace
corr
osio
n/ox
idat
ion
and
corr
osio
npr
oduc
tsfr
omco
rros
ion
pits
inco
njun
ctio
nw
ithA
-A-5
8054
nylo
nab
rasi
vem
ats.
Itis
used
tore
mov
eth
eox
ide
film
from
alum
i-nu
mal
loy
surf
aces
prio
rto
appl
icat
ion
ofa
chro
-m
ate
conv
ersi
onco
atin
gdu
ring
pain
ting
oper
atio
ns.
6850
-00-
300-
9008
DR
(55
GL
)
15C
hem
ical
Con
vers
ion
Mat
eria
lsfo
rA
lu-
min
uman
dA
lum
i-nu
mA
lloys
MIL
-DT
L-8
1706
(sup
er-
sede
sM
IL-D
TL
-81
706)
Cla
ss1A
,Fo
rmII
I(R
eady
-to-
use
pre-
mix
edliq
uid)
8030
-00-
142-
9272
CN
(1PT
)T
reat
men
tof
clea
n,ba
real
umin
uman
dal
umin
umal
loys
toim
part
apr
otec
-tiv
ech
rom
ate
coat
ing.
Usa
ble
for
appl
icat
ion
Met
hod
B-b
rush
8030
-00-
065-
0957
CN
(1Q
T)
Form
II(P
owde
r)80
30-0
0-82
3-80
39C
N(1
GL
)C
lass
1Aco
atin
gspr
ovid
em
axim
umpr
otec
tion
agai
nst
corr
osio
nw
hen
left
unpa
inte
dan
dsu
peri
orad
hesi
onw
hen
pain
tsy
s-te
ms
are
appl
ied.
Usa
ble
for
appl
icat
ion
Met
hods
A,
B,
orC
-sp
ray,
brus
h,or
imm
er-
sion
8030
-01-
429-
9504
DR
(55
GL
)Po
wde
rfo
rms
(For
ms
IIan
dV
)ha
vean
inde
finite
shel
flif
eun
tilm
ixed
with
de-
ioni
zed
(DI)
wat
er.
Form
IV(R
eady
-to-
use
pre-
mix
edliq
uid;
thix
otro
pic
solu
tion)
8030
-00-
057-
2354
JR(4
OZ
)
TO 1-1-691
A-4
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seU
sabl
efo
rap
plic
atio
nM
etho
dB
-bru
sh80
30-0
0-92
6-91
31C
O(5
LB
)C
lass
3co
atin
gsar
ein
-te
nded
for
use
asa
corr
o-si
onpr
even
tive
film
for
elec
tric
alan
del
ectr
onic
appl
icat
ions
whe
relo
wer
resi
stan
ceco
ntac
tsar
ere
quir
ed.
Form
V(P
owde
r,pr
e-m
easu
red
amou
ntfo
rth
ixot
ropi
cso
lutio
ns)
8030
-00-
720-
9739
CN
(12
LB
)
Suita
ble
for
appl
icat
ion
Met
hod
B-b
rush
8030
-00-
663-
9847
DR
(60
LB
)
Touc
h-N
-Pre
p(T
NP)
Pen
with
Alo
dine
1132
Cla
ss3
8030
-01-
460-
0246
CS
(12
EA
)T
hese
appl
icat
orpe
nspr
o-vi
dea
clea
n,ea
sy,
read
y-to
-use
met
hod
for
appl
ica-
tion
ofM
IL-D
TL
-817
06,
Cla
ss1A
chem
ical
conv
er-
sion
coat
ing
mat
eria
lsto
alum
inum
allo
ysin
touc
h-up
oper
atio
ns.
The
trea
ted
surf
aces
dono
tre
quir
eri
nsin
gor
wip
eof
f.16
Che
mic
alC
onve
rsio
nM
ater
ials
for
Alu
-m
inum
and
Alu
mi-
num
Allo
ys(N
on-
ferr
icya
nide
Cat
alyz
ed)
MIL
-DT
L-8
1706
,C
lass
1A&
3A
lodi
ne60
0,C
lass
1A,
Form
II,
Met
hod
B-b
rush
8030
-00-
811-
3723
BT
(2L
B)
Non
-fer
ricy
anid
eco
nver
sion
coat
ing
for
the
trea
tmen
tof
clea
n,ba
real
umin
umal
loy
surf
aces
toim
part
ach
rom
ate
coat
ing
whe
refe
rric
yani
dem
ater
ials
caus
epr
oble
ms
for
the
loca
lw
aste
disp
osal
/trea
t-m
ent
(sew
er)
syst
em.
Alo
dine
600,
Cla
ss3,
Form
II,
Met
hod
B-
brus
h
8030
-01-
018-
2838
CO
(10
LB
)
Tur
coat
Alu
mig
old,
Cla
ss1A
,Fo
rmII
,M
etho
dB
-bru
sh
8030
-01-
341-
8609
CN
(5L
B)
TO 1-1-691
A-5
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se17
Mag
nesi
umA
lloy,
Proc
esse
sfo
rPr
e-tr
eatm
ent
and
Pre-
vent
ion
ofC
orro
-si
onon
(Hen
kel
Proc
ess)
SAE
AM
S-M
-317
1(s
u-pe
rsed
esM
IL-M
-31
71),
Type
VI
(Chr
o-m
icac
idbr
ush-
ontr
eatm
ent)
8030
-01-
512-
2416
CO
(1Q
T)
Tre
atm
ent
ofcl
ean,
bare
mag
nesi
uman
dits
allo
ysto
impa
rta
prot
ectiv
ech
rom
ate
coat
ing
usin
gth
isH
enke
lPr
oces
spr
e-m
ixed
read
y-to
-use
chro
-m
ium
trio
xide
and
cal-
cium
sulf
ate
mix
ture
.T
hein
stru
ctio
nsfo
rpr
epar
ing
this
solu
tion
from
pow
ders
(Chr
omiu
mT
riox
ide
and
Cal
cium
Sulf
ate)
liste
din
Item
No.
18an
dIt
emN
o.19
onsi
teca
nbe
foun
din
Cha
pter
5,Se
ctio
nII
ofth
ism
anua
l.18
Chr
omiu
mT
riox
ide,
Tech
nica
l(C
hrom
icA
cid)
A-A
-558
27(s
uper
sede
sO
-C-3
03)
6810
-00-
264-
6517
CN
(5L
B)
One
oftw
och
emic
als
used
topr
epar
ea
mag
nesi
umco
nver
sion
coat
ing
solu
-tio
n(S
AE
AM
S-M
-317
1,Ty
peV
I)pe
rC
hapt
er5,
Sect
ion
IIof
this
man
ual.
19D
esic
cant
,C
alci
umSu
lfat
e,A
nhyd
rous
,Te
chni
cal
O-D
-210
6810
-00-
242-
4066
CN
(1L
B)
One
oftw
och
emic
als
used
topr
epar
ea
mag
nesi
umco
nver
sion
coat
ing
solu
-tio
n(S
AE
AM
S-M
-317
1,Ty
peV
I)pe
rC
hapt
er5,
Sect
ion
IIof
this
man
ual.
TO 1-1-691
A-6
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se20
Cor
rosi
onR
emov
ing
and
Met
alC
ondi
-tio
ning
Com
poun
d(P
hosp
hori
cA
cid
Bas
e)
MIL
-C-1
0578
,Ty
peI
(Was
h-of
f)68
50-0
0-27
0-55
51B
T(1
GL
)A
conc
entr
ated
phos
phor
icac
idso
lutio
nw
hich
isdi
-lu
ted
with
wat
eran
dus
edto
rem
ove
corr
osio
n/ru
stfr
omfe
rrou
sm
etal
sur-
face
san
dsl
ight
lyet
chth
esu
rfac
eof
ferr
ous
and
som
eno
n-fe
rrou
ssu
rfac
esto
prom
ote
adhe
sion
ofpa
int
syst
ems
and
CPC
’s.
Type
sI
&II
are
used
for
rust
rem
oval
from
ferr
ous
met
als
afte
rhe
avy,
en-
crus
ted
rust
isre
mov
edm
echa
nica
llyan
das
asu
rfac
eco
nditi
oner
for
ferr
ous
and
som
eno
n-fe
rrou
sm
etal
surf
aces
prio
rto
pain
ting
orC
PCap
plic
atio
n.Ty
peI
re-
mov
esm
ore
rust
and
re-
quir
esri
nsin
gw
ithw
ater
,w
hile
Type
IIis
wip
edof
fw
ithcl
ean
rags
.Ty
peII
Iis
used
tore
mov
eru
stfr
omch
rom
ium
plat
edst
eel
surf
aces
.Ty
peV
isus
edto
rem
ove
rust
from
ferr
ous
met
alpa
rts
im-
mer
sed
ina
dip
tank
afte
ral
lgr
ease
and
oil
have
been
clea
ned
from
the
surf
aces
.
6850
-00-
656-
1291
DR
(5G
L)
6850
-00-
926-
5298
DR
(15
GL
)
Tank
Type
II(W
ipe-
off)
6850
-00-
174-
9672
BT
(1G
L)
6850
-00-
656-
1292
DR
(5G
L)
Type
III
(Inh
ibite
d)68
50-0
085
4-79
52D
R(5
GL
)
TO 1-1-691
A-7
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seTy
peV
(Im
mer
sion
)68
50-0
1-10
7-25
51C
O(4
GL
)
Do
not
use
thes
em
ater
i-al
son
high
stre
ngth
stee
lpa
rts
asth
eyca
nca
use
hydr
ogen
embr
ittle
men
t.
6850
-00-
551-
9577
DR
(15
GL
)
CL
EA
NIN
GC
OM
POU
ND
S21
Cle
anin
gC
ompo
und,
Air
craf
t,E
xter
ior
MIL
-PR
F-85
570,
Type
I(G
ener
alpu
rpos
e,ar
o-m
atic
solv
ent
base
d)
6850
-01-
237-
7482
CN
(5G
L)
Cle
anin
gof
pain
ted
and
un-
pain
ted
airc
raft
,m
issi
le,
and
equi
pmen
tsu
rfac
es.
Che
ckfo
rre
gula
tory
com
-pl
ianc
ebe
fore
usin
gTy
peI
beca
use
itco
ntai
nsar
o-m
atic
solv
ents
.
6850
-01-
237-
8003
DR
(15
GL
)68
50-0
1-23
7-80
04D
R(5
5G
L)
Type
II(G
ener
alpu
rpos
e,no
n-so
lven
tba
sed)
6850
-01-
239-
0571
GL
(1G
L)
Cle
anin
gof
pain
ted
and
un-
pain
ted
airc
raft
,m
issi
le,
and
equi
pmen
tsu
rfac
es.
Wat
erba
sed
form
ula
may
beus
edon
both
high
glos
san
dca
mou
flage
pain
tsy
stem
s.
6850
-01-
235-
0872
CN
(5G
L)
6850
-01-
248-
9828
DR
(15
GL
)68
50-0
1-23
6-01
28D
R(5
5G
L)
Type
III
(Abr
asiv
esp
otcl
eane
r)68
50-0
1-23
2-91
64C
N(5
GL
)U
seon
high
glos
spa
int
sche
me
coat
ings
tore
-m
ove
stub
born
cont
ami-
nant
ssu
chas
boot
mar
ksan
dsm
udge
sas
wel
las
gun
blas
tan
dex
haus
ttr
ack
soil.
Type
IV(R
ubbe
rize
dsp
otcl
eane
r)68
50-0
1-23
5-08
73C
N(5
GL
)U
seon
low
glos
s,ca
mou
-fla
gepa
int
sche
me
coat
-in
gsto
rem
ove
stub
born
cont
amin
ants
such
asbo
otm
arks
and
smud
ges
asw
ell
asgu
nbl
ast
and
ex-
haus
ttr
ack
soil.
6850
-01-
248-
9829
DR
(15
GL
)68
50-0
1-24
8-98
30D
R(5
5G
L)
TO 1-1-691
A-8
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seTy
peV
(Gel
-typ
ecl
eane
r)68
50-0
1-23
4-02
19C
N(5
GL
)C
lean
ing
ofw
heel
wel
ls,
win
gbu
tts,
and
othe
rar
-ea
sw
here
com
plet
eri
ns-
ing
with
wat
erca
nbe
tol-
erat
ed.
Thi
xotr
opic
clea
ner
clin
gsto
vert
ical
orov
er-
head
surf
aces
.
6850
-01-
248-
9831
DR
(15
GL
)68
50-0
1-23
5-74
58D
R(5
5G
L)
22C
lean
ing
Com
poun
d,A
eros
pace
Equ
ip-
men
t
MIL
-PR
F-87
937,
Type
I(T
erpe
neba
sed,
solv
ent
emul
sion
,w
ater
di-
luta
ble)
6850
-01-
390-
7808
CN
(1G
L)
Terp
ene
base
d.G
ood
gene
ral
clea
ner
for
heav
ilyso
iled
cam
oufla
gean
dhi
ghgl
oss
pain
ted
area
san
dun
-pa
inte
dm
etal
surf
aces
.R
equi
res
adeq
uate
vent
ila-
tion
and
com
plet
eri
nsin
gof
entr
apm
ent
area
s.M
ayre
quir
eai
rcra
ftSP
Dan
d/or
mis
sile
oreq
uip-
men
tSP
Map
prov
albe
-fo
reit
isus
ed.
6850
-01-
390-
7811
CN
(5G
L)
6850
-01-
390-
7816
DR
(55
GL
)68
50-0
1-46
1-00
65B
T(2
4O
Z)
Spra
yT
rigg
er
Type
III
(Gel
-typ
ecl
ean-
ing
com
poun
d)68
50-0
1-39
0-95
30C
N(5
GL
)V
isco
us,
thix
otro
pic
gel
clea
ner
for
very
heav
ilyso
iled
area
ssu
chas
air-
craf
tco
ntro
lsu
rfac
ean
dw
heel
wel
lsw
here
alo
ngdw
ell
time
isre
quir
ed.
Use
only
inar
eas
that
tol-
erat
ehe
avy
rins
ing.
6850
-01-
390-
9453
DR
(55
GL
)
Type
IV(H
eavy
duty
,w
ater
dilu
tabl
ecl
ean-
ing
com
poun
d)
6850
-01-
429-
2368
CN
(1G
L)
Hea
vydu
tycl
eane
req
ually
suite
dfo
rhe
avily
soile
dar
eas
and
asa
gene
ral
clea
ner
for
clea
ning
cam
-ou
flage
and
glos
spa
inte
dan
dba
rem
etal
surf
aces
ofai
rcra
ft,
mis
sile
s,an
deq
uipm
ent.
In20
05,
itw
illco
mpl
etel
yre
plac
eTy
peII
clea
ner.
6850
-01-
433-
0873
CN
(5G
L)
6850
-01-
429-
2371
DR
(55
GL
)68
50-0
1-46
1-00
60B
T(2
4O
Z)
Spra
yT
rigg
er68
50-0
1-46
1-00
70C
N(1
6O
Z)
Aer
osol
TO 1-1-691
A-9
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se23
Cle
anin
gC
om-
poun
ds,A
ircr
aft
Surf
ace
A-A
-599
21(f
orm
erly
MIL
-C-4
3616
),C
lass
1A
6850
-00-
005-
5305
CN
Aso
lven
tem
ulsi
onty
pecl
eane
rfo
rre
mov
alof
oily
and
grea
syso
ils.
The
Cla
ss1A
aero
sol
mat
eria
lis
anex
celle
ntsp
otcl
eane
rfo
rth
ese
type
sof
soils
.24
Cle
anin
gC
ompo
und,
Eng
ine
Gas
Path
Cle
aner
MIL
-PR
F-85
704
Rem
oves
accu
mul
ated
salt,
dirt
,an
doi
lyre
sidu
esfr
omth
ega
spa
thof
en-
gine
s.Ty
peI
(Sol
vent
emul
sion
clea
ner
conc
entr
ate
w/h
ydro
carb
onso
lven
t)
6850
-00-
181-
7594
CN
(5G
L)
Solv
ent
conc
entr
ate
for
clea
ning
the
com
pres
sor
sect
ion
ofga
stu
rbin
een
-gi
nes
(eng
ine
off-
line;
star
ter
cran
ked)
.
6850
-00-
181-
7597
DR
(55
GL
)
Type
II(A
queo
uscl
eane
rco
ncen
trat
e)68
50-0
1-37
2-83
03C
N(5
GL
)A
queo
usco
ncen
trat
efo
rcl
eani
ngth
eco
mpr
esso
rse
ctio
nof
gas
turb
ine
en-
gine
s(e
ngin
eof
f-lin
e;st
arte
rcr
anke
d).
6850
-01-
372-
8304
DR
(55
GL
)
Type
IIR
TU
(Rea
dy-t
o-us
e)68
50-0
1-37
0-52
45C
N(5
GL
)R
eady
-to-
use
aque
ous
clea
ner
for
clea
ning
gas
turb
ine
engi
nes
(eng
ine
off-
line;
star
ter
cran
ked)
.
6850
-01-
370-
5244
DR
(55
GL
)
Type
III
(Aqu
eous
clea
ner
conc
entr
ate
w/o
hydr
ocar
bon
solv
ent)
6850
-01-
433-
6436
CN
(5G
L)
Aqu
eous
conc
entr
ate.
With
nohy
droc
arbo
nso
lven
tsfo
ron
-lin
e(fi
red)
clea
ning
ofga
stu
rbin
een
gine
sin
acco
rdan
cew
ithsp
ecifi
cen
gine
mai
nten
ance
in-
stru
ctio
ns.
6850
-01-
433-
6438
DR
(55
GL
)
Type
III
RT
U(R
eady
-to-
use)
6850
-01-
472-
1845
CN
(5G
L)
6850
-01-
472-
1846
DM
(55
GL
)
TO 1-1-691
A-10 Change 5
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se25
Cle
anin
gC
ompo
und,
for
Part
sW
ashe
rsan
dSp
ray
Cab
inet
s
MIL
-PR
F-29
602
(SA
EA
MS-
C-2
9602
),Ty
peI
(Wat
erso
lubl
eliq
uid
conc
entr
ate)
6850
-01-
431-
2269
CN
(1G
L)
Det
erge
ntfo
rus
ein
part
sw
ashe
rsan
dsp
ray
cabi
-ne
tsto
clea
nav
iatio
nw
eapo
nssy
stem
s,en
gine
,an
dsu
ppor
teq
uipm
ent
com
pone
nts.
Rem
oves
grea
se,
oil,
and
dirt
whi
char
epr
esen
ton
disa
s-se
mbl
edco
mpo
nent
s.
6850
-01-
431-
2267
CN
(5G
L)
6850
-01-
431-
2268
DR
(55
GL
)
DSF
-1,
Tele
chem
Int’
lIn
c.68
50-0
1-52
4-29
56B
X(4
GL
Con
-ta
iner
s)
PND
SF-1
Hea
vyD
uty
6850
-01-
524-
2978
CO
(5L
B)
Aqu
eous
Part
sW
ashe
r,C
lean
eran
dD
egre
aser
6850
-01-
524-
2980
DR
(55
GL
)
.Ty
peII
(Wat
erso
lubl
epo
wde
r)T
HE
MA
TE
-R
IAL
SL
IST
ED
BE
-L
OW
AR
EA
P-
PR
OV
ED
FO
RU
SEO
NL
AN
DIN
GG
EA
RC
OM
PO
-N
EN
TS
AN
DIV
DC
OA
TE
DH
IGH
STR
EN
GT
HST
EE
LPA
RT
S.
6850
-01-
053-
2789
CO
(1L
B)
Do
not
use
thes
ecl
ean-
ers
onai
rcra
ftla
ndin
gge
arco
mpo
nent
s,w
heel
s,an
dbr
akes
,or
any
IVD
alum
inum
coat
edhi
ghst
reng
thst
eel
part
sas
they
may
caus
ehy
drog
enem
-br
ittle
men
t.U
seon
lym
ater
ials
appr
oved
byan
dlis
ted
onth
ela
test
revi
sion
ofap
plic
able
tech
nica
lor
der
onai
r-cr
aft
land
ing
gear
com
-po
nent
s,w
heel
s,an
dbr
akes
,an
don
any
othe
rIV
Dal
umin
umco
ated
high
stre
ngth
stee
lpa
rts.
6850
-01-
431-
9025
CO
(50
LB
)68
50-0
1-43
1-90
24D
R(4
00L
B)
(Zip
Che
mic
alPr
oduc
tsC
o.,
CA
GE
Cod
e#1
KQ
X9)
TO 1-1-691
A-11
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
sePN
Cal
la-2
96(C
once
n-tr
ated
emul
sify
ing
type
liqui
dcl
eane
r)
6850
-01-
485-
5972
CO
(1G
L)
6850
-01-
485-
5932
CO
(5G
L)
6850
-01-
485-
5950
DR
(55
GL
)PN
Cal
la60
2LF
(Con
-ce
ntra
ted
non-
emul
sify
-in
gty
peliq
uid
clea
ner)
6850
-01-
513-
5230
CO
(1G
L)
6850
-01-
513-
5237
CO
(5G
L)
6850
-01-
513-
5233
DR
(55
GL
)26
Dei
cing
/Ant
i-Ic
ing
Flui
d,A
ircr
aft,
SAE
,Ty
peI
SAE
AM
S14
24(s
uper
-se
des
MIL
-A-8
243)
6850
-01-
435-
6471
CO
(1G
L)
Flui
dis
gene
rally
used
heat
ed,
eith
erdi
lute
dw
ithw
ater
oras
supp
lied,
for
the
rem
oval
ofan
dtim
e-lim
ited
prot
ectio
nag
ains
tde
posi
tsof
fros
t,ic
e,an
dsn
owon
exte
rior
airc
raft
surf
aces
prio
rto
take
-off
.It
isal
sous
edm
ixed
with
MIL
-PR
F-87
937,
Type
IVor
MIL
-PR
F-85
570,
Type
IIso
lutio
nsfo
rlo
wte
m-
pera
ture
clea
ning
per
Para
grap
h3.
5.2.
6.
6850
-01-
435-
6468
CN
(5G
L)
6850
-01-
435-
6465
DR
(55
GL
)68
50-0
1-44
9-94
69C
O(2
75G
LTo
te)
27D
ishw
ashi
ngC
om-
poun
d,H
and
(Syn
-th
etic
Det
erge
nt,
Solid
and
Liq
uid
Form
)
P-D
-410
,Ty
peII
(Con
-ce
ntra
ted
liqui
d,cl
ear
orop
aque
lotio
n,no
n-ph
osph
ate)
7930
-00-
880-
4454
BT
(6E
A/1
GL
)Ty
peII
liqui
dm
ixed
with
fres
hw
ater
will
rem
ove
grea
se,
oil,
and
dirt
from
aw
ide
vari
ety
ofsu
rfac
es.
7930
-00-
899-
9534
CN
(5G
L)
28C
lean
ing
Com
poun
d,So
lven
tM
ixtu
res
A-A
-592
81(s
uper
sede
sM
IL-C
-387
37),
Type
I(S
olve
ntbl
end
that
cont
ains
anar
omat
icso
lven
t)
6850
-00-
611-
7993
CN
(1PT
)T
his
solv
ent
blen
dis
used
tocl
ean
all
type
sof
soils
(bot
hpo
lar
and
non-
po-
lar)
,fr
omsu
rfac
esbe
fore
appl
ying
seal
ants
.
6850
-00-
538-
0929
CN
(1G
L)
6850
-01-
016-
3482
DR
(55
GL
)
TO 1-1-691
A-12
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se29
Dis
infe
ctan
t,G
ener
alPu
rpos
e(L
iqui
dPh
enol
icTy
pe)
A-A
-143
968
40-0
0-59
8-73
26(G
L)
Tre
atm
ent,
disi
nfec
ting/
sani
-tiz
ing,
and/
orde
odor
izin
gof
relie
ftu
bear
eas,
latr
ine
area
s,ur
inal
s,to
ilet
bow
ls,
latr
ine
buck
ets,
garb
age
rece
ptac
les,
sink
s,ga
lley
area
,an
dot
her
airc
raft
inte
rior
area
sre
quir
ing
disi
nfec
tion.
6840
-00-
598-
7327
CN
(5G
L)
6840
-00-
721-
6054
DR
(55
GL
)
Sani
tizer
,Ph
enol
icTy
pe,
Con
cent
rate
O-D
-143
5Pr
e-m
ixed
Liq
uid
(eith
erm
ater
ial)
6840
-00-
530-
7109
BX
(4E
A/1
GL
CO
)D
ilute
with
tap
wat
eras
di-
rect
edby
the
man
ufac
ture
ron
the
cont
aine
rbe
fore
use.
Pow
der
(O-D
-143
5on
ly)
6840
-00-
753-
4797
BX
(12
EA
/8O
ZPG
)M
ixon
e8
OZ
PGin
2Q
Tta
pw
ater
for
clea
ning
la-
trin
ebu
cket
s,ur
inal
s,an
dto
ilets
,an
don
e8
OZ
PGin
4G
Lta
pw
ater
for
all
othe
rcl
eani
ngpr
oces
ses.
Dis
infe
ctan
tC
lean
erfo
rA
ircr
aft
Inte
rior
(Gen
eral
Purp
ose
Liq
uid)
Cal
la®
1452
(Zip
Che
mic
alPr
oduc
tsC
o.,
CA
GE
Cod
e#1
KQ
X9)
6840
-01-
561-
3126
BX
(Con
tain
ssi
x32
FLO
Zem
pty
spra
ybo
ttles
and
six
0.25
FLO
Zbo
ttles
ofco
ncen
trat
eddi
sinf
ecta
nt)
For
gene
ral
clea
ning
ofal
lai
rcra
ftin
teri
orar
eas
re-
quir
ing
disi
nfec
tion.
Fol-
low
the
man
ufac
ture
r’s
inst
ruct
ions
for
use.
Cal
la®
1452
(AN
DPA
K,
Inc.
,C
AG
EC
ode
#258
73)
6840
-01-
600-
4177
CN
(GL
)
Aer
oDis
®71
27(Z
ipC
hem
ical
Prod
ucts
Co.
,C
AG
EC
ode
#1K
QX
9)
6840
-01-
686-
9908
CS
(Con
tain
s10
0E
Ain
di-
vidu
ally
wra
pped
pre-
satu
rate
dw
ipes
)68
40-0
1-68
6-99
17C
S(C
onta
ins
twel
ve26
OZ
spra
ybo
ttles
)
TO 1-1-691
Change 18 A-13
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se30
Wat
erR
epel
lent
,W
indo
wan
dW
ind-
shie
ld,
Gla
ssan
dPl
astic
SAE
AS
6882
(sup
er-
sede
sM
IL-W
-688
2)68
50-0
0-13
9-52
97B
T(8
OZ
)A
nti-
wet
ting
film
for
exte
-ri
orgl
ass
orac
rylic
plas
ticw
indo
ws
and
win
dshi
elds
toas
sure
good
visi
bilit
yun
der
rain
yco
nditi
ons.
31Po
lish,
Met
al,A
lum
i-nu
mA
-A-5
9318
(sup
erse
des
MIL
-P-6
888)
,Ty
peI
(Liq
uid)
7930
-00-
266-
7131
CN
(1Q
T)
Polis
hing
unpa
inte
dal
umi-
num
surf
aces
ofai
rcra
ft.
The
abra
sive
qual
ityof
the
polis
hen
able
sit
tore
mov
eta
rnis
han
dpr
o-du
cea
high
last
ing
shin
e.T
hepo
lish
shal
lno
tbe
used
onal
umin
umai
rcra
ftsu
rfac
esth
atar
eto
bepa
inte
d.
7930
-00-
267-
1224
CN
(1G
L)
Type
II(P
aste
)79
30-0
0-73
4-40
10C
N(1
QT
)
32Po
lish,
Plas
ticP-
P-56
0,Ty
peI
(Liq
uid)
7930
-00-
634-
5340
BT
(1PT
)C
lean
ing
and
polis
hing
ofpl
astic
mat
eria
lsto
re-
mov
elig
htsc
ratc
hes,
and
inth
eap
plic
atio
nof
anan
tista
ticfil
mw
hich
will
prev
ent
the
elec
tros
tatic
attr
actio
nof
dust
,lin
t,as
h,et
c.,
toac
rylic
plas
ticsu
r-fa
ces.
7930
-00-
935-
3794
BX
(24
EA
/8O
Z)
7930
-01-
133-
5375
BX
(1D
Z)
33E
rase
rs,
Rub
ber
A-A
-132
(sup
erse
des
ZZ
-E-6
61)
Rec
tang
ular
with
beve
led
ends
(25/ 8
inL
x½
inW
x7/ 8
inT
)
7510
-00-
949-
5055
BX
(1D
Z)
Rem
oval
oflig
htta
rnis
hor
corr
osio
nfr
omel
ectr
ical
conn
ecto
rsan
dco
ntac
tsan
dot
her
avio
nics
com
po-
nent
s.R
ecta
ngul
ar(2
inL
x¾
inW
x7/ 8
inT
)75
10-0
0-32
3-87
88B
X(1
DZ
)
CL
EA
NIN
GPA
DS/
CL
OT
HS
34Fa
ceR
espi
rato
rC
lean
ing
Wip
e(T
owel
ette
s)
3MC
o.,
PN50
4,C
AG
EC
ode
#OT
1L6
11x
8.5
inW
ipes
4240
-01-
372-
3078
BX
(100
PK)
Hyg
ieni
ccl
eani
ngof
resp
i-ra
tors
and
othe
rpe
rson
alpr
otec
tive
gear
/equ
ipm
ent
(alc
ohol
-fre
efo
rmul
a).
35C
lean
ing
Com
poun
d,O
ptic
alL
ens
(Rea
dy-t
o-U
se)
A-A
-591
99(s
uper
sede
sM
IL-C
-434
54),
Type
I(2
0%al
coho
l)
6850
-00-
392-
9751
BT
(2O
Z)
Cle
anin
gof
expo
sed
optic
alsu
rfac
es.
6850
-00-
227-
1887
BT
(1Q
T)
Type
II(5
7%al
coho
l)68
50-0
0-18
8-98
75B
T(1
QT
)
TO 1-1-691
A-14 Change 18
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se36
Cle
aner
,Pi
pePN
8405
07,
CA
GE
Cod
e#6
4067
9920
-00-
292-
9946
BX
(134
4E
A)
Cle
anin
gsm
all
orifi
ces
and
crev
ices
.
TO 1-1-691
Change 18 A-14.1/(A-14.2 blank)
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se37
Pad,
Cle
anin
gan
dPo
lishi
ngN
on-
Met
allic
(for
air-
craf
tcl
eani
ngki
t)
A-A
-310
0(s
uper
sede
sM
IL-C
-839
57),
Type
I(3
/ 8in
T)
7920
-00-
151-
6120
PG(1
0SH
)N
on-w
oven
,no
n-m
etal
lic,
non-
abra
sive
,po
lyes
ter
clea
ning
and
polis
hing
pads
(12″
Lx
6″W
)fo
rus
eon
airc
raft
,m
issi
le,
and
equi
pmen
tsu
rfac
es.
Rep
lace
men
tpa
dsfo
rai
r-cr
aft
was
hki
t.(R
efer
toA
ppen
dix
B,
Tabl
eB
-2,
Item
No.
1).
Type
II(1
inT
)79
20-0
0-17
1-15
34PG
(10
SH)
38A
ircr
aft
Cle
anin
gPa
dsSc
otch
brite
®#3
3
3MC
o.,
PN61
-500
1-86
95-4
(3½
x5
inpa
d)
7920
-01-
519-
4141
CS
(200
EA
)N
on-w
oven
,no
n-m
etal
lic,
non-
abra
sive
,po
lyes
ter
clea
ning
and
polis
hing
pads
with
impr
egna
ted
rubb
erpa
rtic
les
for
clea
n-in
gof
airc
raft
,m
issi
le,
and
equi
pmen
tsu
rfac
es.
The
sepa
dspr
ovid
eim
-pr
oved
clea
ning
effic
ienc
yov
erth
eIt
emN
o.37
pads
.
CA
GE
Cod
e#7
6381
(Im
prov
edTy
pe)
3MC
o.,
#961
,PN
61-
5000
-461
5-8
(3½
x5
inpa
dho
lder
-ha
ndhe
ld)
7920
-01-
519-
4140
CS
(10
EA
)
3MC
o.,
PN61
-500
1-86
96-2
(45/ 8
x10
inpa
d)
7920
-01-
519-
4733
CS
(100
EA
)
3MC
o.,
#250
,PN
61-
5000
-491
3-7
(45/ 8
x10
inpa
dho
lder
-ha
ndhe
ld)
7920
-01-
519-
4142
CS
(5E
A)
3MC
o.,
PN61
-500
1-86
97-0
(6x
12in
pad)
7920
-01-
519-
4736
CS
(50
EA
)
3MC
o.,
#261
,PN
61-
5000
-323
5-6
(6x
12in
pad
hold
er-
hand
le)
7920
-01-
519-
4735
CS
(1E
A)
Mel
amin
ePa
ds3.
5″X
5″X
1.2″
7920
-01-
526-
9015
BX
(200
EA
)4.
625″
X10
″X
1.3″
7920
-01-
526-
9007
BX
(100
EA
)6″
X12
″X
1.3″
7920
-01-
526-
9003
BX
(50
EA
)3″
X5″
X1″
6850
-01-
525-
7684
BX
(6E
A)
3MJE
TPA
D6″
X12
″79
20-0
1-54
8-78
87B
ox(5
0E
A)
39C
ham
ois
Lea
ther
,Sh
eeps
kin,
Oil
Tann
ed
KK
-C-3
00,
Gra
deB
,C
lass
2,Si
zeSm
all
8330
-00-
823-
7545
PG(5
EA
)G
ener
alpu
rpos
ew
ashi
ngan
dpo
lishi
ng.
TO 1-1-691
Change 14 A-15
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se40
Che
esec
loth
,C
otto
n,B
leac
hed
and
Un-
blea
ched
CC
C-C
-440
,Ty
peI,
Cla
ss2
(Ble
ache
d)83
05-0
0-26
2-33
21B
O(3
6in
x50
YD
)C
lean
ing
and
polis
hing
air-
craf
t,m
issi
le,
and
equi
p-m
ent
surf
aces
.83
05-0
0-20
5-34
95B
O(3
6in
x10
0Y
D)
Type
I,C
lass
1(U
n-bl
each
ed)
8305
-00-
222-
2423
PG(3
8.5
inx
1Y
D)
Type
II,
Cla
ss2
(Ble
ache
d)83
05-0
0-20
5-34
96PG
(36
inx
10Y
D)
8305
-00-
267-
3015
PG(3
6in
x1
YD
)41
Clo
th,
Cle
anin
g,N
on-w
oven
Fabr
icC
CC
-C-4
6,Ty
peI
(Un-
trea
ted)
Cla
ss1
(Lig
htdu
ty)
8305
-00-
753-
2967
RO
(36
inx
50Y
D)
Gen
eral
clea
ning
(e.g
.w
ip-
ing
upgr
ease
and
liqui
dsp
ills)
whe
relo
wre
sidu
alsu
rfac
eco
ntam
inat
ion
isre
quir
ed.
Cla
ss4
(Ext
rahe
avy
duty
)79
20-0
0-29
2-92
04B
X(M
X)
-15
0in
2E
AC
lass
6(L
ight
duty
,pe
r-fo
rate
dor
non-
perf
o-ra
ted)
7920
-00-
401-
8034
BX
(HD
)-
150
in2
EA
Cla
ss7
(Air
craf
tso
lven
tw
iper
)79
20-0
1-18
0-05
5618
BX
(150
EA
-8
¾x
8¼
in)
7920
-01-
180-
0557
BX
(800
EA
-16
¾in
x20
¾in
)42
Clo
thes
,C
lean
ing
for
Air
craf
tPr
imar
yan
dSe
cond
ary
Stru
ctur
alSu
rfac
es
SAE
AM
S38
19,
Cla
ss2,
Gra
deA
(Dup
ont-
Sont
-ar
a®A
CT
MA
ircr
aft
Wip
es;
Dis
trib
utor
-C
AG
EC
ode
#1B
L94
)PN
AC
9165
6850
-01-
487-
2859
8B
X(1
00E
A-
9x
16½
in)
Use
dfo
rcl
eani
ngsu
rfac
esre
quir
ing
exce
ptio
nally
low
resi
dual
surf
ace
con-
tam
inat
ion.
PNA
C12
165
6850
-01-
487-
2861
BX
(250
EA
-12
x16
½in
)43
Clo
th,
Flan
nel,
Cot
-to
n(B
lue
inco
lor)
A-A
-501
29(s
uper
sede
sC
CC
-C-4
58)
8305
-00-
913-
5817
BO
(50
YD
)C
lean
ing
and
polis
hing
ofpl
astic
surf
aces
such
asca
nopi
es,
win
dscr
eens
,et
c.
TO 1-1-691
A-16
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se44
Clo
th,
Cle
anin
g,L
ow-L
int
(Whi
tein
colo
r)
A-A
-593
23(s
uper
sede
sM
IL-C
-850
43),
Type
I(C
lean
room
use,
ultr
a-cl
ean,
low
lint
wip
es)
7920
-00-
165-
7195
BX
(10
LB
)H
ydra
ulic
clea
nro
oman
d
fluid
syst
ems
clea
ning
.
Do
not
use
thes
ecl
oths
with
flam
mab
leso
lven
tsas
fire
may
resu
ltw
hen
used
with
thes
eso
lven
ts.
Type
II(G
ener
alus
ere
-qu
irin
glo
wlin
t,hi
ghly
abso
rben
tw
ipes
but
not
tocl
ean
room
stan
-da
rds)
7920
-00-
044-
9281
BX
(10
LB
)
CO
RR
OSI
ON
PRE
VE
NT
IVE
CO
MPO
UN
DS,
OIL
S,G
RE
ASE
S,A
ND
LU
BR
ICA
NT
S45
Cor
rosi
onPr
even
tive
Com
poun
d,So
lven
tC
utba
ck,
Col
dA
p-pl
icat
ion
MIL
-PR
F-16
173
(sup
er-
sede
sM
IL-C
-161
73),
Cla
ssII
,G
rade
1-
Har
dFi
lm(L
owV
OC
≤2.8
#/G
L)
8030
-01-
396-
5731
CN
(1PT
)T
hick
,w
ax-l
ike,
hard
film
cons
iste
ncy
for
long
term
prot
ectio
nof
met
alsu
r-fa
ces
agai
nst
corr
osio
nw
ithor
with
out
cove
ring
s(i
ndoo
rsor
outd
oors
).T
his
mat
eria
lw
illcr
ack
and
peel
off
the
surf
ace
ator
belo
wa
tem
pera
ture
of0°
F(-
18°
C).
8030
-01-
396-
5732
CN
(1G
L)
8030
-01-
347-
0970
CN
(5G
L)
8030
-01-
396-
5237
DR
(55
GL
)
TO 1-1-691
A-17
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seC
lass
I,G
rade
2-
Soft
film
(Hig
hV
OC
>2.
8#/
GL
)
8030
-00-
118-
0666
CN
(11
OZ
)A
eros
olT
hick
,gr
ease
-lik
eco
nsis
-te
ncy
for
prot
ectin
gm
etal
surf
aces
agai
nst
corr
osio
ndu
ring
rew
ork
orst
orag
e.In
clud
esex
tend
edin
door
prot
ectio
nof
inte
rior
orex
teri
orsu
rfac
esw
ithou
tth
eus
eof
barr
ier
mat
eri-
als.
For
outd
oor
prot
ec-
tion,
this
mat
eria
lca
non
lybe
used
for
alim
ited
time
whe
rete
mpe
ratu
reis
not
extr
emel
yho
t.It
will
ad-
here
tosu
rfac
esan
dpr
o-vi
depr
otec
tion
atte
m-
pera
ture
sdo
wn
to-4
0°F
(-40
°C
).
8030
-01-
149-
1731
CN
(1Q
T)
8030
-00-
244-
1297
CN
(1G
AL
)80
30-0
0-24
4-12
98C
N(5
GA
L)
8030
-00-
244-
1295
DR
(55
GL
)
Cla
ssII
,G
rade
3-
Soft
oily
film
(Low
VO
C≤2
.8#/
GL
)
8030
-01-
396-
5735
CN
(1PT
)So
ft,
oily
mat
eria
lus
edto
disp
lace
wat
er,
incl
udin
gsa
ltw
ater
,fr
omm
etal
sur-
face
san
djo
int
area
san
dto
prot
ect
them
from
cor-
rosi
onfo
rlim
ited
peri
ods
(30
days
orle
ss).
Use
dto
prot
ect
criti
cal
bare
stee
lan
dph
osph
ated
stee
lsu
r-fa
ces
ofpa
rts
awai
ting
repa
iror
bein
gsh
ippe
dto
ade
pot
for
repa
ir.Pr
o-vi
des
inde
finite
prot
ectio
nfo
rpa
rts
with
inse
aled
barr
ier
mat
eria
lco
ntai
ners
.
8030
-01-
396-
5748
CN
(1G
L)
8030
-01-
347-
0971
CN
(5G
L)
8030
-01-
396-
5734
DR
(55
GL
)
TO 1-1-691
A-18
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seC
lass
II,
Gra
de4
(Tra
ns-
pare
nt,
non-
tack
yso
ftfil
m)
8030
-01-
396-
5738
CN
(1PT
)T
hin,
tran
spar
ent,
wat
erdi
s-pl
acin
g,ta
ck-f
ree
prot
ec-
tive
film
for
prot
ectio
nof
met
alsu
rfac
esag
ains
tco
r-ro
sion
duri
ngin
door
stor
-ag
eor
whe
nlo
cate
din
inte
rior
area
sof
airc
raft
,m
issi
les,
oreq
uipm
ent
and
for
limite
dou
tdoo
rpr
eser
-va
tion.
Use
onco
ntro
lca
bles
,fa
sten
ers,
bare
met
alar
eas,
oran
ywhe
rete
mpo
rary
(30
days
orle
ss)
prot
ectio
nis
need
edan
dfo
rlo
ngte
rmst
orag
eof
part
sw
ithin
seal
edba
r-ri
erm
ater
ial
cont
aine
r.It
will
adhe
reto
surf
aces
and
prov
ide
prot
ectio
nat
tem
pera
ture
sdo
wn
to-4
0°F
(-40
°C
).
8030
-01-
396-
5743
CN
(1G
L)
8030
-01-
347-
0972
CN
(5G
L)
8030
-01-
396-
5736
DR
(55
GL
)
46C
orro
sion
Prev
entiv
eC
ompo
und
(AM
L-
GU
AR
D)
MIL
-DT
L-8
5054
,Ty
peI
(Pre
ssur
ized
/aer
osol
can)
Cla
ss13
4AH
CFC
prop
ella
nt
8030
-01-
347-
0979
CN
(14
OZ
)Te
mpo
rary
repa
irof
smal
lpa
int
dam
age
area
sfr
omch
ips,
scra
tche
s,or
crac
ks.
Inte
nded
for
use
onno
n-m
ovin
gpa
rts
not
requ
irin
ga
lubr
icat
edsu
rfac
e,su
chas
fast
ener
s,se
ams,
acce
sspa
nels
,jo
ints
,un
pain
ted
met
al,
etc.
Dri
esto
aha
rdfil
m.
Type
II(B
ulk
form
)80
30-0
1-34
7-09
83B
T(3
2O
Z-
Pum
psp
ray)
8030
-01-
347-
0981
CN
(1Q
T)
8030
-01-
347-
0982
CN
(5G
L)
TO 1-1-691
A-19
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se47
Cor
rosi
onPr
even
tive
Com
poun
ds,
Wat
erD
ispl
acin
g,U
ltra-
Thi
nFi
lm
MIL
-PR
F-81
309,
Type
II(S
oft
film
)W
ater
disp
laci
ngC
PCw
hich
may
beap
plie
dby
dip-
ping
,sp
rayi
ng,
brus
hing
,or
from
pres
suri
zed
con-
tain
ers.
Cla
ss1
(Non
-pre
ssur
ized
cont
aine
r/bu
lk)
8030
-00-
213-
3279
CN
(1G
L)
Suita
ble
for
use
onan
ym
etal
surf
ace
exce
ptav
i-on
ics/
elec
tron
ics
appl
ica-
tions
for
indo
oran
dsh
ort
term
outd
oor
prot
ectio
nw
here
surf
aces
can
bere
-coa
ted
whe
nre
quir
ed.
8030
-00-
262-
7358
CN
(5G
L)
NO
TE
Itsh
ould
not
beus
edar
ound
LO
Xfit
tings
.
8030
-00-
524-
9487
DR
(55
GL
)
Cla
ss2,
Gra
deC
O2
(Pre
ssur
ized
cont
aine
r-
CO
2pr
opel
lant
)
8030
-00-
938-
1947
CN
(16
OZ
)
Type
III
(Sof
tfil
m;A
vi-
onic
grad
e)C
lass
1(N
on-p
ress
uriz
edco
n-ta
iner
/bul
k)
8030
-01-
347-
0978
CN
(1G
L)
Wat
erdi
spla
cing
CPC
for
use
onex
teri
ors
ofav
ioni
ceq
uipm
ent,
elec
tric
alco
n-ne
ctor
plug
s,an
dco
ntac
tpo
ints
.C
lass
2(P
ress
uriz
edco
n-ta
iner
/aer
osol
-no
nO
DS
prop
ella
nt)
8030
-00-
546-
8637
CN
(16
OZ
)
TO 1-1-691
A-20 Change 10
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se48
Lub
rica
nts,
Cor
rosi
onPr
even
tive
Com
-po
und,
Wat
erD
is-
plac
ing,
Synt
hetic
MIL
-L-8
7177
A,
Type
I(P
ress
uriz
edca
n/ae
ro-
sol)
;G
rade
B(w
ithad
ded
corr
osio
nin
hibi
-to
r)
6850
-01-
528-
0653
CN
(16
OZ
)W
ater
disp
laci
ngC
PCw
hich
may
beap
plie
dby
dip-
ping
,br
ushi
ng,
orsp
ray-
ing
(pum
psp
raye
ror
aero
sol
spra
y).
Suita
ble
for
use
onan
ym
etal
sur-
face
incl
udin
gex
tern
alsu
rfac
esof
avio
nics
/ele
c-tr
onic
seq
uipm
ent,
elec
tri-
cal
conn
ecto
rs,
and
con-
tact
poin
tsfo
rin
door
and
shor
tte
rmou
tdoo
rpr
otec
-tio
nw
here
surf
aces
can
bere
-coa
ted
whe
nre
quir
ed.
Itca
nbe
used
asan
alte
r-na
te/s
ubst
itute
for
MIL
-PR
F-81
309,
Type
sII
and
III.
Type
II(N
on-p
ress
uriz
edco
ntai
ner/
bulk
);G
rade
B(w
ithad
ded
corr
o-si
onin
hibi
tor)
6850
-01-
326-
7294
CN
(5L
)
Do
not
use
arou
ndL
OX
fittin
gsas
fire
may
resu
lt.
49C
orro
sion
Prev
entiv
eC
ompo
und
(Hig
hZ
inc
Dus
tC
onte
ntPa
int)
Com
mer
cial
Prod
uct
ZR
CPr
od.
Co.
,C
AG
EC
ode
#079
57,
PN82
81-1
0000
8030
-01-
015-
1550
CN
(12
OZ
)A
eros
olA
high
zinc
dust
cont
ent
epox
ypa
int
type
corr
osio
npr
even
tive
com
poun
d(a
lso
know
nas
“col
dga
l-va
nize
”)us
edfo
rre
pair
ofde
fect
sin
galv
aniz
edco
at-
ings
,to
over
coat
wel
ded
area
son
galv
aniz
edst
eel,
and
topr
ovid
eco
rros
ion
for
area
sw
here
corr
osio
nw
asre
mov
edon
stee
lst
ruct
ures
ofsu
ppor
teq
uipm
ent,
elec
tron
icva
ns,
ante
nna
tow
ers,
and
vehi
cles
.
Dev
con
Cor
p.,
CA
GE
Cod
e#1
6059
8010
-00-
501-
5798
CN
(16
OZ
)A
eros
olPN
DE
VC
ON
Z&
NH
CC
orp.
,C
AG
EC
ode
#209
13,
PNH
Y-Z
INC
TO 1-1-691
Change 10 A-21
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seD
evco
nC
orp.
,C
AG
EC
ode
#160
59,
PN’s
1703
&12
030
8010
-00-
360-
3369
CN
(1G
L)
50L
ubri
catin
gO
il,G
en-
eral
Purp
ose,
Pre-
serv
ativ
e(W
ater
Dis
plac
ing,
Low
Tem
pera
ture
)
MIL
-PR
F-32
033
9150
-00-
836-
8641
BT
(½O
Z)
Age
nera
lpu
rpos
e,w
ater
disp
laci
ng,
low
tem
pera
-tu
rera
ted
(-40
°F/
-40°
C)
oil
that
can
beap
plie
dby
dipp
ing,
brus
hing
,or
spra
ying
for
lubr
icat
ing
and
shor
tte
rmco
rros
ion
prot
ectio
nof
met
alpa
rts;
airc
raft
,m
issi
le,
and
equi
pmen
thi
nges
;an
dsm
all
arm
s.
9150
-00-
261-
8146
BT
(1O
Z)
9150
-00-
273-
2389
CN
(4O
Z)
9150
-00-
458-
0075
CN
(16
OZ
)A
eros
ol
9150
-01-
374-
2021
BT
(16
OZ
)Pu
mp
Spra
y91
50-0
0-23
1-66
89C
N(1
QT
)91
50-0
0-23
1-90
45C
N(1
GL
)91
50-0
0-23
1-90
62C
N(5
GL
)91
50-0
0-28
1-20
60D
R(5
5G
L)
TO 1-1-691
A-22
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se51
Lub
rica
nt,
Cle
aner
and
Pres
erva
tive
for
Wea
pons
and
Wea
pons
Syst
ems
(CL
P)
MIL
-PR
F-63
460
9150
-01-
102-
1473
BT
(½O
Z)
Lub
rica
tion
and
shor
tte
rmpr
eser
vatio
nof
airc
raft
,m
issi
le,
and
equi
pmen
thi
nges
,an
dsm
all
and
larg
eca
liber
wea
pons
.C
anbe
used
asan
alte
r-na
teor
subs
titut
efo
rM
IL-
PRF-
3203
3.
9150
-01-
079-
6124
BT
(4O
Z)
9150
-01-
054-
6453
BT
(16
OZ
)Pu
mp
Spra
y
Do
not
use
MIL
-PR
F-63
460
onru
bber
orot
her
elas
tom
eric
mat
e-ri
als
asit
may
dam
age
them
.U
seon
lyin
area
sw
here
the
cont
aine
dso
lven
tsca
nre
adily
evap
orat
e.
9150
-01-
327-
9631
BT
(32
OZ
)Pu
mp
Spra
y
9150
-01-
053-
6688
BT
(1G
L)
TO 1-1-691
A-23
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se52
Cor
rosi
onPr
even
tive
Com
poun
d,Pe
tro-
leum
,H
otA
pplic
a-tio
n
MIL
-C-1
1796
,C
lass
1(H
ard
film
com
poun
d)80
30-0
0-23
1-23
54C
N(5
LB
)Pr
eser
vatio
nof
inte
rior
sur-
face
sof
unse
aled
stru
c-tu
ral
stee
lan
dal
umin
umal
loy
tubi
ngas
sem
blie
san
dot
her
met
alar
eas
that
mus
tre
mai
nba
rean
dar
eex
pose
dto
eith
erex
teri
oror
inte
rior
envi
ronm
ents
inse
rvic
e.C
lass
1an
d1A
mat
eria
lsca
nbe
used
topr
otec
tm
etal
part
sin
un-
shie
lded
outd
oor
stor
age
orus
efo
rlim
ited
peri
ods
(90
days
)an
dun
limite
din
door
use
orst
orag
eei
-th
erpa
ckag
edor
unpa
ck-
aged
.C
lass
3m
ater
ials
can
beus
edto
prot
ect
part
ssu
chas
anti-
fric
tion
bear
ings
inin
door
stor
age.
Pref
erab
ly,
use
only
Cla
ss1A
mat
eria
lson
inse
rvic
est
ruct
ures
asth
eyar
eno
n-sl
ick
and
won
’tco
llect
dirt
asw
ell
asre
sist
ing
high
eram
bien
t(r
oom
)te
mpe
ratu
res
(+15
0°F/
+66
°C
)w
ithou
tm
eltin
gan
dru
nnin
gof
fsu
rfac
esto
whi
chit
isap
plie
d.
8030
-00-
597-
3288
CN
(35
LB
)
8030
-00-
231-
2352
DR
(400
LB
)
Cla
ss1A
(Har
dfil
m,
non-
slic
kco
mpo
und)
8030
-00-
823-
8054
CN
(35
LB
)
8030
-00-
514-
1843
DR
(400
LB
)
Cla
ss3
(Sof
tfil
mco
m-
poun
d)80
30-0
0-59
8-59
15C
N(1
PT)
8030
-00-
231-
2353
CN
(5L
B)
8030
-00-
285-
1570
CN
(35
LB
)53
Lin
seed
Oil,
Boi
led
AST
MD
260
(sup
er-
sede
sA
-A-3
71),
Type
I80
10-0
0-24
4-89
61C
N(1
PT)
Pres
erva
tion
ofin
teri
orsu
r-fa
ces
ofse
aled
stru
ctur
alca
rbon
stee
ltu
bing
asse
m-
blie
s.
8010
-00-
152-
3245
CN
(1G
L)
8010
-00-
684-
8789
CN
(5G
L)
8010
-00-
242-
6114
DR
(55
GL
)L
UB
RIC
AN
TS
TO 1-1-691
A-24
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se54
Gre
ase,
Air
craf
t,G
ener
alPu
rpos
e,W
ide
Tem
pera
ture
Ran
ge;
NA
TO
Cod
eG
-395
(-65
°to
+35
0°F/
-54°
to+
177°
C)
MIL
-PR
F-81
322
(sup
er-
sede
sM
IL-L
-813
22)
NG
LI,
Gra
de1
9150
-01-
378-
0744
TU
(8O
Z)
Lub
rica
ting
airc
raft
arre
stin
gge
arsh
eave
spac
ers
and
othe
req
uipm
ent
that
oper
-at
eun
der
high
cont
act
load
san
dhi
ghsl
idin
gsp
eeds
.
9150
-01-
378-
0559
CN
(1.7
5L
B)
9150
-01-
378-
0693
CN
(6.5
LB
)
NG
LI,
Gra
de2
9150
-00-
181-
7724
TU
(8O
Z)
Lub
rica
ting
airc
raft
whe
elbe
arin
gsan
din
tern
albr
ake
whe
elas
sem
blie
s,an
ti-fr
ictio
nbe
arin
gs,
gear
boxe
s,an
dpl
ain
bear
-in
gs.
9150
-01-
262-
3358
CA
(14
OZ
)
9150
-00-
944-
8953
CN
(1.7
5L
B)
55G
reas
e,A
ircr
aft
and
Inst
rum
ent,
Gea
ran
dA
ctua
tor
Scre
w;
NA
TO
Cod
eG
-354
(-10
0°to
+25
0°F/
-73°
to+
121°
C)
MIL
-PR
F-23
827
(sup
er-
sede
sM
IL-G
-238
27),
Type
I(M
etal
licso
apth
icke
ned)
9150
-00-
985-
7244
TU
(4O
Z)
Lub
rica
ntfo
rus
ein
ball,
rolle
ran
dne
edle
bear
ings
,ge
ars,
and
onsl
idin
gan
dro
lling
surf
aces
ofsu
cheq
uipm
ent
asin
stru
men
ts,
cam
eras
,el
ectr
onic
gear
s,an
dai
rcra
ftco
ntro
lsy
s-te
ms
that
are
subj
ect
toex
trem
em
arin
ean
dlo
wte
mpe
ratu
reco
nditi
ons.
It’s
extr
emel
ylo
wvo
latil
-ity
prev
ents
itfr
omfo
g-gi
ngup
optic
alin
stru
-m
ents
.It
can
beus
edfo
rro
lling
and
slid
ing
sur-
face
sof
equi
pmen
tha
ving
low
mot
ivat
ing
pow
er(l
owto
rque
equi
pmen
t).
Als
oin
tend
edfo
rge
nera
lus
eon
airc
raft
,m
issi
le,
and
equi
pmen
tge
ars,
ac-
tuat
orsc
rew
s,an
dot
her
equi
pmen
tre
quir
ing
alu
-br
ican
tw
ithhi
ghlo
adca
rryi
ngca
paci
ty.
9150
-00-
985-
7245
TU
(8O
Z)
9150
-00-
935-
4017
CA
(14
OZ
)
9150
-00-
985-
7246
CN
(1.7
5L
B)
9150
-00-
985-
7247
CN
(6.5
LB
)
9150
-00-
985-
7248
CN
(35
LB
)
TO 1-1-691
A-25
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se56
Gre
ase,
Plug
Val
ve,
Gas
olin
eO
il,an
dW
ater
Res
ista
nt;
NA
TO
Cod
eG
-363
SAE
AM
S-G
-603
2(s
u-pe
rsed
esM
IL-G
-603
2),
Type
I(B
ulk
form
)
9150
-00-
190-
0926
CN
(8O
Z)
Lub
rica
tion
ofta
pere
dpl
ugva
lves
.T
hetw
oty
pes
pro-
vide
for
the
use
inhi
ghpr
essu
relu
bric
atio
neq
uip-
men
tor
for
serv
icin
gth
ose
valv
esw
hich
requ
ire
ast
ick
type
lubr
ican
t.A
lso
may
beus
edas
aga
sket
lubr
ican
tor
seal
and
for
gene
ral
plug
valv
ese
rvic
ein
syst
ems
whe
rega
solin
e,oi
l,al
coho
l,or
wat
erre
-si
stan
ceis
requ
ired
.
Type
II(S
tick
form
)91
50-0
0-25
7-53
60C
N(1
.75
LB
)C
lass
A(¼
Dx
7/ 8
inL
)91
50-0
0-26
1-82
87B
X(2
4E
A)
Cla
ssB
(13/
32D
x1
3/ 8
inL
)91
50-0
0-26
1-82
89B
X(2
4E
A)
Cla
ssC
(35/
64D
x2
inL
)91
50-0
0-26
1-82
90B
X(2
4E
A)
Cla
ssD
(21/
32D
x2
7/16
inL
)91
50-0
0-26
1-82
91B
X(2
4E
A)
Cla
ssG
(55/
64D
x3
3/ 8
inL
)91
50-0
0-26
1-82
92B
X(2
4E
A)
57G
reas
e,A
ircr
aft
and
Inst
rum
ent,
Fuel
and
Oxi
dize
rR
e-si
stan
t
MIL
-PR
F-27
617
(sup
er-
sede
sM
IL-G
-276
17),
Type
I-
NA
TO
Cod
eG
-397
(-65
°to
+40
0°F/
-54°
to+
204°
C)
9150
-01-
007-
4384
TU
(8O
Z)
Lub
rica
tion
ofta
per
plug
valv
es,
gask
ets,
and
bear
-in
gsin
fuel
syst
ems
ofai
rcra
ftan
dgr
ound
sup-
port
equi
pmen
t.A
lso
suit-
able
for
use
inL
OX
sys-
tem
sas
alu
bric
ant
for
valv
es,
thre
ads,
and
bear
-in
gsin
aero
spac
eve
hicl
esan
dsu
ppor
teq
uipm
ent.
May
not
besu
itabl
efo
ral
umin
uman
dm
agne
sium
dyna
mic
bear
ing
lubr
ica-
tion
beca
use
ofpo
ssib
leig
nitio
nha
zard
s.Ty
peII
Iis
mor
eco
mm
only
know
nas
“Kry
tox”
and
isL
OX
com
patib
le.
9150
-01-
311-
9771
CN
(1.7
5L
B)
9150
-01-
088-
0498
TU
(2O
Z)
Type
II-
NA
TO
Cod
eG
-398
(-40
°to
+40
0°F/
-40°
to+
204°
C)
9150
-00-
961-
8995
TU
(8O
Z)
9150
-01-
358-
5154
CN
(1L
B)
TO 1-1-691
A-26
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seTy
peII
I-
NA
TO
Cod
eG
-399
(-30
°to
+40
0°F/
-34°
to+
204°
C)
9150
-01-
353-
5788
CR
(1L
B)
Type
IV-
NA
TO
Cod
eG
-135
0(-
100°
to+
400°
F/-7
3°to
+20
4°C
)
9150
-01-
393-
1749
TU
(2O
Z)
58G
reas
e,M
olyb
denu
mD
isul
fide,
Low
and
Hig
hTe
mpe
ratu
res;
NA
TO
Cod
eG
-353
(-10
0°to
+25
0°F/
-73°
to+
121°
C)
MIL
-G-2
1164
9150
-00-
935-
4018
CA
(14
OZ
)L
ubri
cant
for
acce
ssor
ysp
lines
,he
avy
load
edsl
id-
ing
stee
lsu
rfac
es,
orfo
ran
ti-fr
ictio
nbe
arin
gsca
r-ry
ing
high
load
san
dop
er-
atin
gth
roug
hw
ide
tem
-pe
ratu
rera
nges
whe
rem
olyb
denu
mdi
sulfi
dew
illpr
even
tor
dela
yse
izur
ein
the
even
tof
inad
equa
telu
bric
atio
n.Sh
ould
not
beus
edfo
rw
heel
bear
ings
orfo
rot
her
than
stee
lsu
r-fa
ces
with
out
auth
oriz
a-tio
n.
9150
-00-
754-
2595
CN
(1.7
5L
B)
9150
-00-
223-
4004
CN
(6.5
LB
)91
50-0
0-96
5-20
03C
N(3
5L
B)
9150
-01-
219-
1629
DR
(20
KG
)
59G
reas
e,Pn
eum
atic
Syst
em;
NA
TO
Cod
eG
-392
SAE
AM
S-G
-434
3(s
u-pe
rsed
esM
IL-G
-434
3)91
50-0
0-11
9-92
91T
U(2
OZ
)L
ubri
cant
betw
een
rubb
eran
dm
etal
part
sof
pneu
-m
atic
syst
ems.
Itm
ayal
sobe
used
for
pres
suri
zed
cabi
nbu
lkhe
adgr
omm
ets
and
othe
rm
echa
nism
sre
quir
ing
rubb
erto
met
allu
bric
atio
n.
9150
-00-
269-
8255
CN
(1.7
5L
B)
60G
reas
e,A
ircr
aft,
He-
licop
ter
Osc
illat
ing
Bea
ring
;N
AT
OC
ode
G-3
66(-
65°
to16
0°F/
-54°
to+
71°
C)
MIL
-G-2
5537
9150
-00-
478-
0055
CA
(14
OZ
)L
ubri
catio
nof
bear
ings
hav-
ing
osci
llato
rym
otio
nof
smal
lam
plitu
de.
9150
-00-
616-
9020
CN
(1.7
5L
B)
9150
-00-
721-
8570
CN
(6.5
LB
)91
50-0
0-72
1-85
81C
N(3
5L
B)
TO 1-1-691
A-27
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se61
Gre
ase,
Air
craf
t,B
all
and
Rol
ler
Bea
ring
;N
AT
OC
ode
G-3
72(-
100°
to45
0°F/
-73
°to
+23
2°C
)
MIL
-G-2
5013
9150
-00-
823-
8048
TU
(8O
Z)
Bal
lan
dro
ller
bear
ing
lubr
i-ca
tion.
Itm
aybe
used
onai
rcra
ftac
tuat
ors
and
gear
boxe
s,an
dot
her
sim
ilar
equi
pmen
tan
dan
ti-fr
ic-
tion
bear
ings
whe
reop
era-
tion
oflo
wto
rque
equi
p-m
ent
requ
ires
lubr
icat
ion
for
exte
nded
peri
ods
oftim
ew
hen
auth
oriz
edby
the
appl
icab
lesy
stem
spe-
cific
mai
nten
ance
man
ual.
9150
-00-
935-
4019
CA
(14
OZ
)91
50-0
0-14
1-67
70C
N(1
.75
LB
)91
50-0
0-14
1-67
71C
N(3
5L
B)
62L
ubri
cant
,M
olyb
de-
num
Dis
ulfid
e,Si
li-co
ne;
NA
TO
Cod
eS-
1735
DO
D-L
-256
8191
50-0
0-54
3-72
20L
B(1
LB
)L
ubri
cant
for
use
onsl
ow-
spee
dsl
idin
gsu
rfac
esin
airc
raft
gas
turb
ine
en-
gine
san
dot
her
area
sof
airc
raft
,m
issi
les,
and
equi
pmen
tsu
bjec
tto
high
tem
pera
ture
sup
to+
752°
F/+
400°
Can
das
anan
ti-se
ize
com
poun
don
thre
aded
part
sw
hich
oper
-at
eat
tem
pera
ture
sup
to+
1400
°F
(760
°C
).
TO 1-1-691
A-28
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se63
Lub
rica
nt,
Solid
Film
,H
eat-
Cur
ed,
Cor
rosi
onIn
hibi
t-in
g
SAE
AS5
272,
Type
sI
&II
(rep
lace
sM
IL-P
RF-
4601
0,Ty
pes
I&
II)
Lub
rica
ntfo
rus
eto
redu
cew
ear
and
prev
ent
galli
ng,
corr
osio
n,an
dse
izur
eof
met
als.
Idea
lfo
rsl
idin
gm
otio
nap
plic
atio
nssu
chas
plai
nan
dsp
heri
cal
bear
ings
,fla
ptr
acks
,hi
nges
,th
read
,an
dca
msu
rfac
es.
Itis
also
usef
ulw
here
aso
lven
tre
sist
ant
coat
ing
isre
quir
ed,
lubr
i-ca
tion
and
corr
osio
npr
o-te
ctio
nfo
rar
eas
that
expe
-ri
ence
slig
htvi
brat
ory
mot
ion,
lubr
icat
ion
and
corr
osio
npr
otec
tion
ofm
echa
nism
sha
ving
infr
eque
ntop
erat
ion
inte
r-va
lsor
lifet
ime
lubr
ica-
tion,
and
whe
relo
ng-t
erm
corr
osio
npr
otec
tion
isne
eded
unde
rst
atic
cond
i-tio
ns.
TO 1-1-691
A-29
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seTy
peI
(cur
e@
+30
0°F/
+14
9°C
)91
50-0
0-83
4-56
08C
N(1
PT)
NO
TE
SAE
AS5
272,
Type
Ian
dM
IL-P
RF-
4601
0cu
red
at+
300°
F(+
149°
C)
are
usab
leon
all
met
alsu
rfac
es,
but
SAE
AS5
272,
Type
IIan
dM
IL-P
RF-
4601
0cu
red
at+
400°
F(+
204°
C)
shou
ldno
tbe
used
onal
umin
umal
loys
orot
her
met
als
adve
rsel
yaf
fect
edby
expo
sure
toth
ishi
gher
tem
pera
ture
.B
efor
eus
ing
MIL
-PR
F-46
010
(alo
wV
OC
ma-
teri
al)
inlie
uof
SAE
AS5
272,
Type
sI
and
II,
auth
oriz
atio
nfr
omth
eai
rcra
ftSP
Dor
the
mis
-si
leor
equi
pmen
tSP
Mis
requ
ired
.D
ono
tus
eth
ese
mat
eria
lson
rolle
rbe
arin
gsor
inar
eas
ex-
pose
dto
LO
X.
9150
-00-
985-
7255
CN
(1G
L)
Type
II(c
ure
@+
400°
F/+
205°
C)
9150
-00-
948-
6912
CN
(1Q
T)
9150
-00-
948-
7025
CN
(1G
L)
MIL
-PR
F-46
010
(sup
er-
sede
sM
IL-P
RF-
4601
0),
Type
III,
Col
or1
(Nat
ural
)
9150
-01-
416-
9506
CN
(1G
L)
Col
or2
(Bla
ck)
9150
-01-
416-
9509
CN
(1G
L)
TO 1-1-691
A-30
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se64
Lub
rica
nt,
Solid
Film
,Air
-Cur
ed,
Cor
rosi
onIn
hibi
t-in
g;N
AT
OC
ode
S-74
9
MIL
-L-2
3398
,Ty
peI
(Bul
k)91
50-0
0-95
4-74
22C
N(1
QT
)L
ubri
cant
can
beap
plie
dby
dipp
ing,
brus
hing
,or
spra
ying
for
use
onst
eel,
titan
ium
,or
alum
inum
bear
ing
surf
aces
whe
rem
oder
ate
wea
rlif
ean
dco
rros
ion
prot
ectio
nis
desi
red.
Itis
suita
ble
for
slid
ing
mot
ion
appl
ica-
tions
such
asin
plai
nsp
heri
cal
bear
ings
,fla
ptr
acks
,hi
nges
and
cam
surf
aces
,es
peci
ally
whe
reit
isno
tfe
asib
leto
use
the
type
ofso
lidfil
mlu
bric
ant
whi
chre
quir
esba
king
atan
elev
ated
tem
pera
ture
.U
sed
tore
pair
defe
cts
inSA
EA
S527
2an
dM
IL-
PRF-
4601
0co
atin
gs.
Type
II(P
ress
uriz
edSp
ray)
9150
-01-
260-
2534
CN
(16
OZ
)A
eros
olM
IL-P
RF-
4614
7,Ty
peI
(18
hour
cure
)Fo
rm1
(Bul
k)
9150
-01-
360-
1907
CN
(1Q
T)
Col
or1
(Nat
ural
)91
50-0
1-14
2-93
61C
N(1
GL
)
Col
or2
(Bla
ck)
9150
-01-
360-
1908
CN
(1Q
T)
9150
-01-
360-
1909
CN
(1G
L)
Form
2(P
ress
uriz
edSp
ray)
9150
-01-
360-
1903
CN
(12
OZ
)A
eros
olC
olor
1(N
atur
al)
9150
-01-
360-
1905
CN
(16
OZ
)A
eros
olC
olor
2(B
lack
)91
50-0
1-36
0-19
04C
N(1
2O
Z)
Aer
osol
9150
-01-
360-
1906
CN
(16
OZ
)A
eros
olN
EU
TR
AL
IZIN
GA
GE
NT
SA
ND
IND
ICA
TO
RM
AT
ER
IAL
S
TO 1-1-691
A-31
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se65
Fire
Ext
ingu
ishi
ngA
gent
,Aqu
eous
Film
Form
ing
Foam
(AFF
F)L
iq-
uid
Con
cent
rate
,fo
rFr
esh
and
Sea
Wat
er
MIL
-F-2
4385
,Ty
pe3
4210
-01-
139-
4972
CN
(5G
L)
Con
cent
rate
isin
tend
edfo
rus
ein
mec
hani
cal
foam
gene
ratin
geq
uipm
ent
such
asfir
efig
htin
gtr
ucks
orfo
amsp
rink
ler
syst
ems
for
extin
guis
hing
fires
.D
ilute
,an
dus
eth
eA
FFF
agen
tw
ithfr
esh
wat
erin
the
follo
win
gpr
opor
tion
toac
hiev
eop
timum
perf
or-
man
ce:
Type
3-3
part
sof
conc
entr
ate
to97
part
sw
ater
byvo
lum
ean
dTy
pe6-
6pa
rts
conc
entr
ate
to94
part
sw
ater
byvo
lum
e.
4210
-01-
144-
0291
DR
(55
GL
)
Type
642
10-0
1-05
6-83
43C
N(5
GL
)
4210
-01-
056-
0883
DR
(55
GL
)
66A
mm
oniu
mH
ydro
x-id
e,Te
chni
cal
A-A
-593
70(s
uper
sede
sO
-A-4
51),
Type
I(2
0to
30%
asam
mon
ia)
6810
-00-
584-
3793
BT
(1PT
)U
sed
asa
neut
raliz
ing
agen
tfo
rac
ids
inur
ine.
6810
-00-
817-
9929
BT
(1G
L)
Type
III
(9to
10%
asam
mon
ia)
6810
-00-
527-
2476
BT
(1Q
T)
67So
dium
Bic
arbo
nate
,Te
chni
cal
(Bak
ing
Soda
)
A-A
-374
(AST
MD
928)
6810
-00-
264-
6618
BX
(1L
B)
Use
dto
neut
raliz
esu
lfur
icac
idel
ectr
olyt
ede
posi
tsfr
omle
ad-a
cid
batte
ries
.68
10-0
0-29
7-00
92B
G(5
0L
B)
68So
dium
Phos
phat
e,M
onob
asic
,Anh
y-dr
ous,
Tech
nica
l
AN
SI/A
WW
AB
504
(su-
pers
edes
MIL
-S-1
3727
)68
10-0
0-28
1-18
58B
G(1
00L
B)
Use
dto
neut
raliz
epo
tass
ium
hydr
oxid
eel
ectr
olyt
ede
-po
sits
from
nick
el-c
ad-
miu
mba
tteri
es.
69B
oric
Aci
dA
-A-5
9282
(sup
erse
des
O-C
-265
)68
10-0
0-26
4-65
35B
T(5
00G
M)
Use
tone
utra
lize
pota
ssiu
mhy
drox
ide
elec
trol
yte
de-
posi
tsfr
omni
ckel
-cad
-m
ium
batte
ries
.
6810
-00-
824-
9090
BT
(3K
G)
6810
-00-
153-
0191
BX
(25
LB
)
TO 1-1-691
A-32
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se70
Phos
phor
icA
cid,
Tech
nica
l(O
r-th
opho
spho
ric
Aci
d)
A-A
-558
20(s
uper
sede
sO
-O-6
70),
Cla
ss1
(85%
acid
)
6810
-00-
264-
6722
BT
(7L
B)
One
oftw
oco
mpo
nent
sus
edto
mak
ebr
omot
hy-
mol
blue
indi
catin
gso
lu-
tion
tode
term
ine
the
loca
-tio
nof
cont
amin
atio
n(e
lect
roly
tesp
ills)
from
nick
el-c
adm
ium
batte
ries
and
toin
dica
tew
heth
erth
ese
area
sha
vebe
enco
mpl
etel
yne
utra
lized
.71
Bro
mot
hym
olB
lue
Indi
cato
rSo
lutio
nM
IL-B
-118
4568
10-0
0-28
1-42
70B
T(½
L)
One
oftw
oco
mpo
nent
sus
edto
mak
ean
indi
cato
rso
lutio
nfo
rde
tect
ing
nick
el-c
adm
ium
batte
rysp
ills
and
tode
term
ine
whe
ther
area
sha
vebe
enco
mpl
etel
yne
utra
lized
.
6810
-00-
281-
4271
BT
(4O
Z)
72L
itmus
Pape
rC
omm
erci
alIt
em-
CA
GE
Cod
e#2
2537
Blu
eL
itmus
Pape
r
6640
-00-
290-
0146
HD
(100
SH)
Col
orch
ange
tore
din
di-
cate
sac
idpr
esen
t(l
ead-
acid
batte
ries
).R
edL
itmus
Pape
r66
40-0
0-29
0-01
47H
D(1
00SH
)C
olor
chan
geto
blue
indi
-ca
tes
base
/alk
ali
pres
ent
(nic
kel-
cadm
ium
batte
r-ie
s).
PRO
TE
CT
IVE
MA
TE
RIA
LS
73B
arri
erM
ater
ials
,G
reas
epro
of,
Wa-
terp
roof
,Fl
exib
le,
Hea
t-Se
alab
le
MIL
-PR
F-12
1,Ty
peI
(Hea
vydu
ty)
Gra
deA
,C
lass
1
8135
-00-
292-
9719
RO
(36
inx
100
YD
)G
ener
alpu
rpos
em
aski
ngm
ater
ial
used
for
prot
ect-
ing
equi
pmen
tan
dsu
p-pl
ies
duri
ngtr
ansp
orta
tion
and
stor
age
unde
ral
lcl
i-m
ate
cond
ition
san
dm
ask-
ing
area
sre
quir
ing
prot
ec-
tion
duri
ngcl
eani
ng,
corr
osio
nre
mov
al,
surf
ace
trea
tmen
t,an
dpa
intin
gop
erat
ions
.
8135
-00-
233-
3871
RO
(36
inx
200
YD
)
8135
-00-
543-
6574
RO
(48
inx
100
YD
)
Type
II(M
ediu
mdu
ty)
Gra
deA
,C
lass
181
35-0
0-22
4-88
85R
O(3
6in
x20
0Y
D)
8135
-00-
543-
6573
RO
(12
inx
200
YD
)
TO 1-1-691
A-33
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se74
Bar
rier
Mat
eria
l,Fl
exib
le,
Gre
asep
roof
Wat
erR
esis
tant
,H
eat-
Seal
able
MIL
-PR
F-13
1(s
uper
-se
des
MIL
-B-1
31),
Cla
ss1
(Non
-wov
enpl
astic
back
)
8135
-00-
282-
0565
RO
(36
inx
200
YD
)U
sed
for
pres
erva
tion
(e.g
.se
alin
gai
rcra
ft,
mis
sile
,or
equi
pmen
top
enin
gs,
pro-
tect
ion
ofca
nopi
es,
tem
-po
rary
wal
kway
prot
ec-
tion)
duri
ngcl
eani
ng,
corr
osio
nre
mov
al,
surf
ace
trea
tmen
t,an
dpa
intin
gop
erat
ions
.It
isal
sous
edto
prot
ect
part
sin
stor
age
orbe
ing
tran
spor
ted
whi
chre
quir
ean
abso
lute
moi
s-tu
reva
por
proo
fba
rrie
r.
NO
TE
Alw
ays
inst
all
with
the
plas
ticco
ated
side
to-
war
dth
epa
rtan
d/or
surf
ace.
75K
raft
Pape
r,U
n-tr
eate
d,(B
row
nin
Col
or)
A-A
-203
(sup
erse
des
UU
-P-2
68),
Styl
e1
(She
ets)
30Po
und
ba-
sis
wei
ght
8135
-00-
290-
3408
SH(2
x3
ft;
850
EA
)G
ener
alw
rapp
ing
appl
ica-
tions
and
prot
ectio
nof
surr
ound
ing
surf
ace
area
sdu
ring
abra
sive
blas
ting,
spra
ypa
intin
g,se
alan
tap
plic
atio
n,et
c.,
whe
rea
wat
erpr
oof
and/
orm
ois-
ture
vapo
rpr
oof
mas
king
mat
eria
lis
not
requ
ired
.
70Po
und
basi
sw
eigh
t81
35-0
0-29
0-55
04SH
(3x
4ft
;20
0E
A)
Styl
e2
(Rol
ls)
50Po
und
basi
sw
eigh
t81
35-0
1-33
7-53
70R
O(3
x20
0ft
)
8135
-00-
160-
7764
RO
(3x
980
ft)
60Po
und
basi
sw
eigh
t81
35-0
0-16
0-77
68R
O(3
x82
0ft
)81
35-0
0-16
0-77
69R
O(4
x82
0ft
)70
Poun
dba
sis
wei
ght
8135
-00-
160-
7771
RO
(3x
700
ft)
8135
-00-
160-
7772
RO
(4x
700
ft)
80Po
und
basi
sw
eigh
t81
35-0
0-16
0-77
76R
O(3
x61
5ft
)81
35-0
0-16
0-77
78R
O(4
x61
5ft
)
TO 1-1-691
A-34
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se76
Pain
tM
aski
ngPa
per
with
Adh
esiv
eB
ack
(Lig
htB
row
nin
Col
or)
Rea
dy-M
askt
TM
3MC
o.,
CA
GE
Cod
e#5
2152
,PN
850D
C
Ope
nPu
rcha
seR
O(2
inx
180
ft)
Pape
rm
aski
ngta
pew
ithad
hesi
veal
ong
one
edge
.Pr
otec
tssu
rfac
esfr
ompa
int
spla
tters
and
over
-sp
ray.
Eas
yto
appl
yan
dco
mes
off
clea
nly
with
noad
hesi
vetr
ansf
er.
Ope
nPu
rcha
seR
O(3
inx
400
ft)
Ope
nPu
rcha
seR
O(3
¼in
x75
ft)
77Pl
astic
Shee
t,Po
ly-
olefi
n(C
lear
)A
-A-3
174
(sup
erse
des
L-P
-378
),Ty
peI
(Nor
-m
alst
reng
thpo
lyet
hyl-
ene)
,C
lass
1(n
on-f
ood
use)
,G
rade
A(l
owsl
ip),
Fini
sh1
(un-
trea
ted)
8135
-00-
584-
0610
RO
(8ft
x10
0ft
)Pr
otec
tion
ofac
rylic
airc
raft
cano
pies
duri
ngw
ashi
ngop
erat
ions
.
78Ta
pes,
Pres
sure
Sen-
sitiv
eA
dhes
ive,
Pres
erva
tion
and
Seal
ing
(Bla
ckin
Col
or)
SAE
AM
S-T-
2208
5(s
u-pe
rsed
esM
IL-T
-220
85)
7510
-00-
852-
8179
RO
(1in
x36
YD
)Pl
astic
pres
erva
tion
and
seal
ing
tape
used
for
hold
-in
gm
ost
barr
ier
mat
eria
lsin
plac
edu
ring
stor
age
orsh
ipm
ent
and
clea
ning
and
corr
osio
nre
mov
alop
era-
tions
.E
ffec
tive
for
man
you
tdoo
rap
plic
atio
nsan
dca
nbe
used
onm
etal
sor
pain
ted
surf
aces
with
clea
nre
mov
alup
to2
year
saf
ter
initi
alus
e.
7510
-00-
852-
8180
RO
(2in
x36
YD
)
Type
II(u
sew
/or
w/o
anov
erco
atin
g)75
10-0
0-88
5-35
10R
O(2
½in
x36
YD
)
7510
-00-
926-
8939
RO
(3in
x36
YD
)
3MC
o.,
CA
GE
Cod
e#5
2152
,PN
481
7510
-00-
916-
9659
RO
(4in
x36
YD
)
7510
-00-
926-
8941
RO
(6in
x36
YD
)N
OT
E
Do
not
use
onac
rylic
orpo
lyca
rbon
ate
cano
pies
and
win
dscr
eens
.
TO 1-1-691
A-35
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se79
Tape
s,Pr
essu
reSe
n-si
tive
Adh
esiv
e,M
aski
ng,
Non
-st
aini
ng,
for
Air
-cr
aft
Pain
ting
Ap-
plic
atio
ns
SAE
AM
S-T-
2159
5(s
u-pe
rsed
esM
IL-T
-21
595)
,Ty
peI
(Cre
pepa
per
back
ing)
3MC
o.,
CA
GE
Cod
e#5
2152
,PN
231/
Nat
u-ra
lC
olor
7510
-01-
371-
3239
RO
(½in
x60
YD
)C
onfo
rmab
lecr
epe
pape
rta
peus
edfo
rm
aski
ngof
eith
erfla
tor
cont
oure
dsu
rfac
espr
ior
topa
intin
gan
dse
alan
tap
plic
atio
ns.
Tape
can
beus
edat
bak-
ing
tem
pera
ture
sup
to+
250°
F(+
121°
C)
for
1ho
uran
dca
nbe
rem
oved
with
out
adhe
sive
tran
sfer
.Ta
pesh
all
not
besu
b-je
cted
topr
olon
ged
peri
-od
sof
outd
oor
expo
sure
orsu
nlig
htbe
caus
eit
will
beco
me
very
diffi
cult
tore
mov
ean
dw
illle
ave
tape
and
adhe
sive
resi
-du
es.
7510
-01-
371-
3234
RO
(¾in
x60
YD
)75
10-0
1-37
1-32
38R
O(1
inx
60Y
D)
7510
-01-
371-
3236
RO
(1½
inx
60Y
D)
7510
-01-
371-
3237
RO
(2in
x60
YD
)75
10-0
1-37
1-32
35R
O(3
inx
60Y
D)
Type
III
(Pla
stic
back
ing)
3MC
o.,
CA
GE
Cod
e#5
2152
,PN
218/
Lig
htG
reen
Col
or;
Fine
Lin
eTa
pe®
7510
-01-
158-
0035
RO
(¼in
x60
YD
)T
hin,
plas
ticta
peus
edfo
rfin
elin
em
aski
ng,
inpa
r-tic
ular
whe
reco
lor
sepa
ra-
tion
isin
volv
ed,
and
dur-
ing
pain
tto
uch-
up,
and
for
othe
rm
aski
ngan
dho
ldin
gap
plic
atio
ns.
Tape
shal
lno
tbe
subj
ecte
dto
pro-
long
edpe
riod
sof
outd
oor
expo
sure
orsu
nlig
htbe
-ca
use
itw
illbe
com
eve
rydi
fficu
ltto
rem
ove
and
will
leav
eta
pean
dad
he-
sive
resi
dues
.
7510
-01-
158-
6606
RO
(½in
x60
YD
)75
10-0
1-15
8-77
78R
O(¾
inx
60Y
D)
7510
-01-
158-
6605
RO
(1in
x60
YD
)75
10-0
1-15
8-66
04R
O(1
½in
x60
YD
)75
10-0
1-15
8-66
03R
O(2
inx
60Y
D)
7510
-01-
158-
6607
RO
(3in
x60
YD
)
TO 1-1-691
A-36
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se80
Tape
s,Pr
essu
reSe
n-si
tive
Adh
esiv
e,fo
rM
aski
ngD
urin
gPa
int
Rem
oval
Op-
erat
ions
SAE
AM
S-T-
2339
7(s
u-pe
rsed
esM
IL-T
-23
397)
,Ty
peII
(Alu
-m
inum
foil
back
ing
-72
hour
prot
ectio
n)
7510
-00-
806-
4669
RO
(½in
x60
YD
)A
lum
inum
foil
back
mas
k-in
gta
peus
edfo
rpr
otec
t-in
gsu
rrou
ndin
gsu
rfac
esdu
ring
pain
tre
mov
alop
-er
atio
nsan
dch
emic
alan
dso
me
mec
hani
cal
corr
o-si
onre
mov
alop
erat
ions
.A
lum
inum
back
ing
pro-
vide
sex
celle
ntre
flect
ion
ofbo
thhe
atan
dlig
ht.
Tape
can
beus
edei
ther
indo
ors
orou
tdoo
rsfo
rm
any
long
term
appl
ica-
tions
.U
seta
pean
dde
cal
appl
icat
or,
Item
No.
83,
toap
ply
this
tape
tosu
rfac
es.
7510
-00-
654-
9811
RO
(¾in
x60
YD
)75
10-0
0-72
0-75
16R
O(1
inx
60Y
D)
3MC
o.,
CA
GE
Cod
e#5
2152
,PN
425
7510
-00-
684-
8803
RO
(2in
x60
YD
)N
OT
E
Use
only
3MC
o.,
PN42
5ta
pefo
rai
rcra
ftch
emic
alpa
int
rem
oval
oper
atio
ns,
asal
lot
her
tape
sw
illno
tho
ldup
for
thes
eex
tend
eddw
ell
time
oper
atio
ns.
7510
-00-
816-
8077
RO
(3in
x60
YD
)75
10-0
0-98
2-39
55R
O(4
inx
60Y
D)
7510
-01-
179-
0662
RO
(6in
x60
YD
)
TO 1-1-691
A-37
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se81
Tape
s,Pr
essu
reSe
n-si
tive
Adh
esiv
e,M
aski
ng
A-A
-883
(sup
erse
des
PPP-
T-42
),Ty
peII
(Fla
tpa
per
back
ing)
7510
-01-
026-
4661
RO
(½in
x60
YD
)T
his
solv
ent
resi
stan
tta
peis
idea
lfo
rst
raig
htlin
epa
int
mas
king
oper
atio
ns.
The
1in
wid
thof
the
3MC
o.,
PN25
0ta
peis
the
re-
quir
edta
pefo
rpe
rfor
min
gth
epa
int
wet
tape
adhe
-si
onte
st.
Bec
ause
ofits
high
stre
ngth
,it
isgo
odfo
rho
ldin
g,bu
ndlin
g,an
dw
rapp
ing
ona
vari
ety
ofsu
rfac
es.
Itis
not
reco
m-
men
ded
for
outd
oor
expo
-su
rebe
caus
eit
beco
mes
very
diffi
cult
tore
mov
e.
7510
-00-
290-
2024
RO
(¾in
x60
YD
)
3MC
o.,
CA
GE
Cod
e#5
2152
,PN
250/
Tan
Col
or
7510
-00-
283-
0612
RO
(1in
x60
YD
)
7510
-00-
290-
2027
RO
(1½
inx
60Y
D)
7510
-00-
290-
2026
RO
(2in
x60
YD
)75
10-0
0-26
6-66
94R
O(3
inx
60Y
D)
82A
bras
ive
Bla
stin
gTa
pe,
Impa
ctR
e-si
stan
t(L
ight
Gre
enin
Col
or)
Com
mer
cial
Prod
uct
3MC
o.,
CA
GE
Cod
e#5
2152
,PN
500
7510
-01-
300-
2124
RO
(1in
x10
YD
)U
sed
for
mas
king
topr
otec
tai
rcra
ft,
mis
sile
,an
deq
uipm
ent
surf
aces
duri
ngab
rasi
vebl
astin
gco
rros
ion
rem
oval
oper
atio
ns.
7510
-01-
300-
2125
RO
(2in
x10
YD
)75
10-0
1-30
0-21
26R
O(3
inx
10Y
D)
7510
-01-
300-
2127
RO
(4in
x10
YD
)83
App
licat
or,
Tape
and
Dec
al(M
ade
ofH
ard
Plas
tic)
Com
mer
cial
Prod
uct
3MC
o.,
CA
GE
Cod
e#7
6381
,PN
P.A
.-1
5120
-00-
628-
5569
BX
(25
EA
)Id
eal
for
appl
ying
mas
king
tape
s(e
spec
ially
Item
No.
80al
umin
umfo
ilta
pe),
anti-
eros
ion
lead
ing
edge
tape
,de
cals
,et
c.(H
ard
plas
ticto
olw
ithta
pere
ded
ges;
4in
Lx
2¾
inW
)Ta
pe,
Pres
sure
Sens
i-tiv
e,fo
rW
etTa
pePa
intA
dhes
ion
Test
ing
3MC
o.,
CA
GE
Cod
e#7
8381
,PN
250
7510
-00-
266-
6694
RO
(1in
Wx
60Y
DL
)U
sed
tope
rfor
mw
etta
pead
hesi
onte
stin
gon
new
lyap
plie
dan
dol
dpa
int
sys-
tem
sto
dete
rmin
epr
oper
pain
tad
hesi
on.
TO 1-1-691
A-38
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seSE
AL
AN
TS
AN
DSE
AL
ING
AC
CE
SSO
RIE
SK
T-
Two-
Part
Can
Kit
(Bas
ean
dA
ccel
erat
or)
PMF
-Pr
e-m
ixed
and
Froz
enSC
-Se
mki
tC
artr
idge
84Se
alin
gan
dC
oatin
gC
ompo
und,
Cor
ro-
sion
Inhi
bitiv
e
MIL
-PR
F-81
733
(sup
er-
sede
sM
IL-S
-817
33),
Cla
ss1
(Pol
ysul
fide)
;G
rade
A(C
hrom
ate
Inhi
bito
rs),
Type
I(B
rush
able
)
Use
dfo
rse
alin
gfa
ying
sur-
face
san
dw
etin
stal
latio
nof
fast
ener
son
perm
anen
tst
ruct
ures
.It
isal
soth
epr
efer
red
seal
ant
for
form
-in
-pla
ce(F
IP)
seal
son
door
s,re
mov
able
pane
ls,
and
seal
ing
gaps
and
seam
s.I-
½80
30-0
0-00
8-72
07K
T(1
PT)
NO
TE
Do
not
use
onin
side
ofin
tegr
alfu
elta
nks.
8030
-00-
009-
5022
KT
(1Q
T)
I-2
8030
-00-
008-
7196
KT
(1PT
)80
30-0
0-76
2-88
07K
T(1
QT
)80
30-0
1-36
1-18
14SC
(3½
OZ
)Ty
peII
(Gun
orsp
atul
aap
plic
atio
n) II-½
8030
-00-
008-
7198
KT
(1PT
)80
30-0
1-09
7-45
19K
T(1
GL
)80
30-0
1-18
4-03
28SC
(2½
OZ
)80
30-0
1-18
4-03
29SC
(6O
Z)
II-2
8030
-01-
124-
7622
KT
(½PT
)80
30-0
0-00
9-50
23K
T(1
PT)
8030
-00-
008-
7200
KT
(1Q
T)
8030
-01-
333-
3954
PMF
(2½
OZ
CA
)80
30-0
1-33
3-48
21PM
F(6
OZ
CA
)80
30-0
1-19
6-19
58SC
(2½
OZ
)
TO 1-1-691
A-39
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se80
30-0
1-18
4-03
30SC
(6O
Z)
II-4
8030
-00-
008-
7201
KT
(1PT
)80
30-0
0-00
8-72
02K
T(1
QT
)Ty
peII
I(S
pray
gun
ap-
plic
atio
n) III-
180
30-0
0-00
8-72
03K
T(1
PT)
8030
-00-
871-
8489
KT
(1G
L)
Type
IV(F
ayin
gsu
rfac
eap
plic
atio
ns;
gun
orsp
atul
a;ex
tend
edcu
retim
e)IV
-12
8030
-01-
395-
2726
KT
(1PT
)80
30-0
0-15
1-99
73K
T(1
GL
)IV
-24
8030
-01-
395-
2728
KT
(1PT
)80
30-0
0-00
8-72
06K
T(1
QT
)80
30-0
1-36
3-65
04PM
F(6
OZ
CA
)IV
-48
8030
-01-
192-
2807
KT
(½PT
)80
30-0
1-39
5-27
29K
T(1
PT)
8030
-00-
028-
8495
KT
(1Q
T)
85Se
alin
gC
ompo
und,
Tem
pera
ture
Res
is-
tant
,In
tegr
alFu
elTa
nks
and
Fuel
Cel
lC
aviti
es,
Hig
hA
dhes
ion
(Pol
ysul
-fid
e)
SAE
AM
S-S-
8802
(su-
pers
edes
MIL
-S-8
802)
,Ty
peII
(Man
gane
sedi
oxid
ecu
red)
Cla
ssA
(Bru
shab
le)
Use
dfo
rfil
let
and
brus
hse
alin
gin
inte
gral
fuel
tank
san
dfu
elce
llca
vi-
ties.
Thi
sse
alan
tis
man
-ga
nese
diox
ide
cure
dan
ddo
esn’
tco
ntai
nan
ych
ro-
mat
esor
othe
rco
rros
ion
inhi
bito
rs.
A-½
8030
-00-
753-
4596
KT
(½PT
)80
30-0
0-96
5-20
04K
T(1
PT)
8030
-00-
842-
8127
KT
(1G
L)
8030
-00-
753-
5008
SC(2
½O
Z)
8030
-00-
753-
5010
SC(6
OZ
)A
-180
30-0
1-38
6-36
56K
T(1
QT
)A
-280
30-0
0-75
3-45
98K
T(½
PT)
8030
-00-
753-
5343
KT
(1PT
)
TO 1-1-691
A-40
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se80
30-0
0-72
3-53
44K
T(1
QT
)80
30-0
0-84
1-68
32K
T(1
GL
)80
30-0
1-36
3-66
71PM
F(2
½O
ZC
A)
8030
-01-
363-
6505
PMF
(6O
ZC
A)
8030
-00-
753-
5003
SC(2
½O
Z)
8030
-00-
753-
5009
SC(6
OZ
)C
lass
B(G
unan
dsp
atul
aap
plic
atio
n) B-½
8030
-00-
753-
4597
KT
(½PT
)80
30-0
0-17
4-25
99K
T(1
PT)
8030
-00-
080-
1549
KT
(1Q
T)
8030
-00-
841-
6831
KT
(1G
L)
8030
-00-
753-
5007
SC(2
½O
Z)
8030
-00-
753-
5004
SC(6
OZ
)B
-180
30-0
1-33
7-94
08SC
(2½
OZ
)80
30-0
1-37
6-85
04K
T(1
GL
)B
-280
30-0
0-75
3-45
99K
T(½
PT)
8030
-00-
723-
2746
KT
(1PT
)80
30-0
0-68
5-09
15K
T(1
QT
)80
30-0
0-57
9-84
53K
T(1
GL
)80
30-0
1-33
3-48
23PM
F(2
4E
A,
2½
OZ
CA
)80
30-0
1-33
3-48
22PM
F(2
4E
A,
6O
ZC
A)
8030
-00-
753-
5006
SC(2
½O
Z)
8030
-00-
753-
5005
SC(6
OZ
)B
-480
30-0
0-17
4-25
98K
T(1
PT)
8030
-00-
850-
5717
KT
(1Q
T)
8030
-00-
850-
0759
SC(2
.5O
Z)
8030
-00-
850-
0758
SC(6
OZ
)C
lass
C(E
xten
ded
as-
sem
bly
time)
TO 1-1-691
A-41
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seC
-20
8030
-01-
048-
3772
KT
(1PT
)80
30-0
0-42
7-26
61K
T(1
GL
)80
30-0
0-15
2-00
12SC
(6O
Z)
C-8
080
30-0
0-70
9-32
78K
T(1
QT
)80
30-0
0-43
2-15
44K
T(1
GL
)86
Seal
ing
Com
poun
d,In
tegr
alFu
elTa
nks,
and
Gen
eral
Purp
ose,
Inte
rmit-
tent
Use
to36
0°F
(182
°C
)(P
olys
ul-
fide)
SAE
AM
S32
76(s
uper
-se
des
MIL
-S-8
3430
),C
lass
A(B
rush
able
)
Use
for
fille
tse
alin
gof
join
tsan
dse
ams
and
brus
hse
alin
gor
over
coat
-in
gof
fast
ener
sin
inte
gral
fuel
tank
san
dfu
elce
llca
vitie
s,in
part
icul
arw
here
tem
pera
ture
sof
360°
F(1
82°
C)
are
expe
-ri
ence
don
anin
term
itten
tba
sis.
Thi
sse
alan
tis
man
-ga
nese
diox
ide
cure
dan
ddo
esn’
tco
ntai
nan
ych
ro-
mat
esor
othe
rco
rros
ion
inhi
bito
rs.
A-½
8030
-00-
602-
0107
KT
(½PT
)
8030
-01-
395-
5474
KT
(1PT
)
8030
-01-
036-
6936
KT
(1Q
T)
8030
-00-
312-
6128
SC(6
OZ
)A
-280
30-0
0-60
2-00
49K
T(½
PT)
8030
-00-
602-
0051
KT
(1G
L)
8030
-01-
387-
1001
PMF
(6O
Z)
Cla
ssB
(Gun
orsp
atul
aap
plic
atio
n) B-¼
8030
-01-
214-
0374
SC(6
OZ
)B
-½80
30-0
0-60
2-00
39K
T(½
PT)
8030
-00-
348-
7888
KT
(1PT
)80
30-0
1-25
2-79
63SC
(2½
OZ
)80
30-0
0-60
2-00
45SC
(6O
Z)
TO 1-1-691
A-42
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seB
-280
30-0
0-48
5-32
37K
T(1
PT)
8030
-01-
066-
6444
KT
(1Q
T)
8030
-00-
585-
4900
KT
(1G
L)
8030
-01-
383-
4185
PMF
(2½
OZ
)80
30-0
1-38
3-39
53PM
F(6
OZ
CA
)80
30-0
0-56
0-87
58SC
(6O
Z)
B-4
8030
-01-
195-
0655
KT
(1Q
T)
B-6
8030
-00-
602-
0035
SC(6
OZ
)80
30-0
1-38
7-10
61PM
F(6
OZ
CA
)C
-½80
30-0
1-31
1-56
53K
T(1
QT
)87
Seal
ing
Com
poun
d,L
owA
dhes
ion,
Cor
rosi
onIn
hibi
t-in
g(N
on-C
hro-
mat
e),
Poly
sulfi
de
PNPR
-177
3(s
uper
sede
sPR
-140
3G)
CA
GE
Cod
e#8
3574
Thi
sm
ater
ial
isa
two-
part
,no
n-ch
rom
ate
type
corr
o-si
onin
hibi
ting,
low
adhe
-si
on,
fuel
resi
stan
tse
alan
tus
edfo
rfa
ysu
rfac
ese
al-
ing
ofac
cess
door
s,re
-m
ovab
lepa
nels
and
stru
c-tu
res,
and
the
head
sof
thei
rat
tach
ing
fast
ener
s.It
can
also
beus
edto
mak
eFI
Pga
sket
san
dre
pair
dam
aged
area
sof
FIP
gas-
kets
.It
shou
ldno
tbe
used
for
seal
ing
insi
dein
tegr
alfu
elta
nks,
inhi
ghte
m-
pera
ture
area
s,or
onpe
r-m
anen
tlyin
stal
led
stru
c-tu
res.
Cla
ssB
(Gun
orsp
atul
aap
plic
atio
n) B-½
8030
-01-
418-
5414
SC(2
½O
Z)
8030
-01-
418-
5418
SC(6
OZ
)
B-2
8030
-01-
104-
5396
KT
(1Q
T)
8030
-01-
418-
5415
SC(2
½O
Z)
8030
-01-
418-
5417
SC(6
OZ
)
TO 1-1-691
A-43
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se88
Seal
ing
Com
poun
d,L
owA
dhes
ion,
Cor
rosi
onIn
hibi
t-in
g,fo
rR
emov
able
Pane
lsan
dFu
elTa
nkIn
spec
tion
Plat
es
SAE
AM
S32
67(s
uper
-se
des
MIL
-S-8
784)
Thi
sm
ater
ial
isa
two-
part
,lo
wad
hesi
on,
fuel
resi
s-ta
ntse
alan
tth
atdo
esn’
tco
ntai
nan
yco
rros
ion
in-
hibi
tors
.It
can
beus
edfo
rfa
ysu
rfac
ese
alin
gof
re-
mov
able
stru
ctur
essu
chas
acce
ssdo
ors,
floor
pane
lsan
dpl
ates
,fu
elta
nkin
-sp
ectio
npl
ates
,an
dot
her
rem
ovab
lepa
nels
.It
shou
ldno
tbe
used
for
seal
ing
insi
dein
tegr
alfu
elta
nks,
inhi
ghte
mpe
ratu
rear
eas,
oron
perm
anen
tlyin
stal
led
stru
ctur
es.
Cla
ssA
(Bru
shab
le)
A-½
8030
-00-
291-
8380
KT
(½PT
)
A-2
8030
-00-
584-
4399
KT
(½PT
)
8030
-01-
127-
8281
KT
(1PT
)80
30-0
0-15
2-00
62SC
(2½
OZ
)C
lass
B(G
unor
spat
ula
appl
icat
ion) B-½
8030
-00-
598-
2910
KT
(½PT
)80
30-0
0-88
1-39
33K
T(1
PT)
8030
-01-
028-
4336
KT
(1Q
T)
8030
-01-
065-
0306
KT
(1G
L)
8030
-00-
152-
0022
SC(2
.5O
Z)
8030
-01-
365-
3912
SC(6
OZ
)80
30-0
0-15
2-00
21SC
(8O
Z)
B-2
8030
-00-
616-
9191
KT
(½PT
)80
30-0
0-68
0-20
41K
T(1
PT)
8030
-01-
371-
9247
PMF
(24
EA
,2½
OZ
CA
)80
30-0
1-37
1-92
46PM
F(2
4E
A,
6O
ZC
A)
8030
-01-
383-
4993
SC(6
OZ
)
TO 1-1-691
A-44
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se89
Seal
ing
Com
poun
d,A
ircr
aft,
Fire
wal
lSA
EA
MS
3374
(sup
er-
sede
sM
IL-S
-382
49),
Type
1(O
neco
mpo
-ne
nt;
silic
one)
8040
-01-
168-
0077
CA
(12
OZ
)Se
alin
gai
rcra
ftfir
ewal
lst
ruct
ures
expo
sed
tove
ryhi
ghte
mpe
ratu
res
topr
e-ve
ntth
epa
ssag
eof
air
and
vapo
rs.
Itw
illw
ith-
stan
d40
0°F
(204
°C
)co
ntin
uous
lyan
d20
00°
F(1
093°
C)
for
atle
ast
15m
inut
es.
Type
4(T
wo
com
pone
nt;
SAE
AM
S33
74/4
and/
orM
IL-S
-382
49,
Type
I)
8030
-00-
783-
8898
KT
(½PT
)
8030
-00-
723-
5345
KT
(1PT
)
8030
-01-
033-
3485
KT
(1G
L)
8030
-01-
364-
7362
PMF
(24
EA
,2
½O
ZC
A)
8030
-01-
365-
0049
PMF
(24
EA
,6
OZ
CA
)80
30-0
1-36
4-73
59SC
(2½
OZ
)80
30-0
0-78
3-88
86SC
(6O
Z)
90Se
alin
gC
ompo
und,
Poly
thio
ethe
r,fo
rA
ircr
aft
Stru
ctur
es,
Fuel
and
Hig
hTe
mpe
ratu
reR
esis
-ta
nt,
Fast
Cur
ing
atA
mbi
ent
(Roo
m)
and
Low
Tem
pera
-tu
res
SAE
-AM
S327
7,G
rade
A,
Type
I(F
uel
resi
s-ta
nt-
use
at-8
0°to
+30
0°F/
-62°
to+
149°
Cco
ntin
uous
and
inte
r-m
itten
tto
+40
0°F/
+20
4°C
)
Use
dfo
rfa
ysu
rfac
ese
alin
gan
dre
pair
ing
fille
tan
dfa
sten
erse
als
inin
tegr
alfu
elta
nks.
Itca
nal
sobe
used
for
over
coat
ing
fas-
tene
rsan
dse
alin
gse
ams
and
join
ts.
Cla
ssA
(Bru
shab
le)
NO
TE
•Ty
peI
com
poun
dsre
quir
eth
eus
eof
anad
hesi
onpr
omot
er(e
.g.
PR-1
86)
whe
reas
Type
IIco
mpo
unds
dono
t.
•N
otfo
rus
eon
air-
craf
tw
inds
hiel
dsan
dca
nopi
es.
A-½
8030
-01-
330-
6568
SC(2
½O
Z)
8030
-01-
330-
0730
SC(6
OZ
)
A-1
8030
-01-
330-
0735
SC(2
½O
Z)
Cla
ssB
(Gun
orsp
atul
aap
plic
atio
n)
TO 1-1-691
A-45
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seB
-¼80
30-0
1-29
0-51
34SC
(2½
OZ
)80
30-0
1-29
0-51
35SC
(6O
Z)
B-½
8030
-01-
290-
5136
SC(2
½O
Z)
8030
-01-
290-
5137
SC(6
OZ
)B
-280
30-0
1-29
0-51
38SC
(2½
OZ
)80
30-0
1-29
0-51
39SC
(6O
Z)
Type
II(F
uel
resi
stan
t,co
rros
ion
inhi
bitin
g;us
eat
-80°
to+
300°
F/-
62°
to+
149°
Cco
n-tin
uous
and
inte
rmit-
tent
to+
360°
F/+
182°
C)
Cla
ssB
(Gun
orSp
atul
aap
plic
atio
n) B-¼
8030
-01-
364-
3883
SC(2
½O
Z)
8030
-01-
364-
3886
SC(6
OZ
)B
-½80
30-0
1-36
4-38
82SC
(2½
OZ
)80
30-0
1-36
4-38
85SC
(6O
Z)
B-2
8030
-01-
364-
3881
SC(2
½O
Z)
8030
-01-
364-
3884
SC(6
OZ
)
TO 1-1-691
A-46
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se91
Adh
esiv
es-S
eala
nts,
Silic
one,
RT
V,
Non
corr
osiv
e(f
orU
sew
ithSe
nsiti
veM
etal
san
dE
quip
-m
ent)
MIL
-A-4
6146
,G
roup
I(G
ener
alpu
rpos
e)Ty
peI
(Thi
xotr
opic
/pas
tety
pe)
Whi
te
8040
-01-
331-
7133
TU
(3O
Z)
The
sear
ero
omte
mpe
ratu
revu
lcan
izin
g(R
TV
)si
li-co
nese
alan
tsus
edon
sen-
sitiv
em
etal
san
deq
uip-
men
t,in
part
icul
aron
elec
tron
ics
equi
pmen
tan
dan
tenn
as,
atte
mpe
ratu
res
upto
+40
0°F
(204
°C
).T
hey
cure
atro
omte
m-
pera
ture
upon
cont
act
with
moi
stur
ein
the
air.
Toim
prov
ead
hesi
on,
use
thes
ese
alan
tsaf
ter
appl
y-in
ga
prim
er(I
tem
No.
92)
spec
ified
byth
em
anuf
ac-
ture
rto
the
surf
aces
.K
it(K
T)
incl
udes
the
requ
ired
prim
er,
but
tube
(TU
)an
dca
rtri
dge
(CA
)do
not.
Whi
te80
40-0
1-33
1-80
46C
A(1
2O
Z)
Whi
te80
40-0
0-11
8-26
95K
T(3
OZ
TU
w/½
OZ
BT
prim
er)
Whi
te80
40-0
1-93
8-15
35K
T(1
2O
ZC
Aw
/10
OZ
BT
prim
er)
NO
TE
The
sese
alan
tsar
eno
tfu
elre
sist
ant
and
they
shal
lno
tbe
used
infu
elw
etar
eas
Gra
y80
40-0
1-05
7-00
91C
N(1
PT)
Gra
y80
40-0
1-39
4-20
26K
T(5
GL
CO
w/½
GL
BT
prim
er)
Cle
ar80
40-0
1-14
8-17
59C
N(1
PT)
Cle
ar80
40-0
1-38
0-64
28T
U(3
OZ
)C
lear
8040
-00-
845-
4304
PT(1
6O
Z)
Cle
ar80
40-0
1-39
4-20
24K
T(5
GL
CO
w/½
GL
BT
prim
er)
Type
II(S
elf-
leve
ling
liqui
dty
pe)
Cle
ar80
40-0
1-33
1-71
27T
U(3
OZ
)
Cle
ar80
40-0
1-33
1-71
34C
N(1
PT)
TO 1-1-691
A-47
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seC
lear
8040
-00-
927-
1513
KT
(1PT
CN
w/1
0O
ZB
Tpr
imer
)C
lear
8040
-01-
009-
1562
KT
(3O
ZT
Uw
/½O
ZB
Tpr
imer
)G
roup
II(H
igh
stre
ngth
),Ty
peII
I;Ty
peI
for
old
spec
ifica
tion;
(Thi
xo-
trop
ic/p
aste
type
)C
lear
8040
-00-
117-
8510
TU
(3O
Z)
Cle
ar80
40-0
1-39
4-37
35T
U(3
OZ
)C
lear
8040
-01-
450-
4013
TU
(3O
Z)
Cle
ar80
40-0
1-37
5-48
03C
A(6
OZ
)C
lear
8040
-01-
082-
9128
CA
(12
OZ
)G
ray
8040
-00-
145-
0020
TU
(3O
Z)
Gra
y80
40-0
1-37
5-48
05T
U(3
OZ
)G
ray
8040
-01-
331-
7128
CA
(12
OZ
)G
ray
8040
-01-
275-
5052
KT
(12
OZ
CA
w/1
OZ
BT
prim
er)
Tra
nslu
cent
8040
-01-
450-
5419
CA
(6O
Z)
Tra
nslu
cent
8040
-01-
450-
9184
KT
(5G
LC
Ow
/½G
LB
Tpr
imer
)Ty
peII
(Sel
f-le
velin
gliq
uid
type
)C
lear
8040
-01-
441-
0671
KT
(3O
ZT
Uw
/½O
ZB
Tpr
imer
)G
roup
III
(Hig
hte
mpe
ra-
ture
)Ty
peI
(Thi
xo-
trop
ic/p
aste
type
)G
ray
8040
-01-
450-
6545
TU
(3O
Z)
92Pr
imer
for
RT
VSi
li-co
neA
dhes
ive-
Seal
ants
(for
Use
with
Item
No.
91)
GE
Co.
,C
AG
EC
ode
#011
39,
PNSS
4004
Stra
w
8040
-00-
893-
4815
CN
(1PT
)U
sed
for
impr
ovin
gad
he-
sion
ofR
TV
silic
one
ad-
hesi
ve-s
eala
nts
(Ite
mN
o.91
).PN
SS40
04Pi
nk80
40-0
0-08
3-84
03C
N(1
PT)
Dow
Cor
ning
Co.
,C
AG
EC
ode
#719
84,
PND
C12
00R
ed
8040
-00-
111-
2682
CN
(1PT
)
TO 1-1-691
A-48
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
sePN
DC
1200
Cle
ar80
40-0
0-84
5-43
04C
N(1
PT)
PND
C12
00R
ed80
40-0
0-87
0-08
77C
N(1
QT
)PN
DC
1200
Pink
8040
-00-
914-
6970
CN
(1G
L)
PND
C12
04C
lear
8040
-01-
042-
1422
CN
(1PT
)PN
DC
1204
Cle
ar80
40-0
1-06
3-75
09C
N(1
GL
)93
Seal
ing
Tape
,Po
lyte
t-ra
fluor
oE
thyl
ene,
Exp
ande
d(E
PTFE
)O
ilan
dW
ater
Re-
sist
ant
(Sky
flex
Tape
-W
.L
.G
ore
Ass
ocia
tes
Inc.
,C
AG
EC
ode
#0A
MD
8&
1721
7)
SAE
AM
S32
55,
Cla
ss1
(Rib
bed)
PNG
UA
-10
01-1
8030
-01-
367-
7357
RO
(15/ 8
inx
100
ft)
Seal
ing
offa
ying
surf
aces
,pr
essu
rize
dan
dno
n-pr
es-
suri
zed
acce
sspa
nels
,flo
orbo
ards
,an
dw
ind-
scre
ens
whe
nap
prov
edby
the
airc
raft
SPD
orth
em
issi
leor
equi
pmen
tSP
M.
Do
not
use
inin
te-
gral
fuel
tank
s,fu
elso
aked
orhi
ghte
mpe
ra-
ture
appl
icat
ions
(+25
0°F/
+12
1°C
orhi
gher
).E
n-vi
ronm
enta
llypr
efer
red
nonh
azar
dous
alte
rnat
ive
totw
o-co
mpo
nent
,so
l-ve
nt-b
ased
seal
ants
.T
heC
lass
1/R
ibbe
dta
pes
are
pref
erre
dfo
rm
ost
seal
ing
oper
atio
nsw
here
thes
eta
pes
are
appr
oved
for
use.
PNG
UA
-100
1-2
8030
-01-
475-
1368
RO
(1½
inx
100
ft)
PNG
UA
-101
7-1
8030
-01-
368-
7208
RO
(1in
x10
0ft
)
PNG
UA
-140
1-1
(3ri
bs)
8030
-01-
454-
7419
RO
(1.1
inx
100
ft)
PNG
SC-2
1-80
767-
00(5
ribs
)80
30-0
1-45
4-74
18R
O(1
.1in
x10
0ft
)C
lass
2(N
on-r
ibbe
d)PN
GU
A-1
003-
180
30-0
1-36
8-72
07R
O(¼
inx
100
ft)
Com
pens
atio
nta
pe:
fills
gaps
and
repa
irs
min
orse
alde
fect
s.PN
GU
A-1
058-
180
30-0
1-38
1-15
84R
O(½
inx
100
ft)
Thi
n:us
eas
shim
topr
even
tch
afing
.PN
GU
A-1
057-
180
30-0
1-37
7-30
84R
O(1
inx
100
ft)
Thi
n:us
eas
shim
topr
even
tch
afing
.
TO 1-1-691
A-49
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
sePN
GU
A-1
038-
180
30-0
1-46
3-64
59R
O(1
.42
inx
100
ft)
Thi
n:us
eas
shim
topr
even
tch
afing
.PN
GU
A-1
059-
1O
pen
Purc
hase
RO
(1½
inx
100
ft)
Thi
n:us
eas
shim
topr
even
tch
afing
.PN
GU
A-1
301-
1O
pen
Purc
hase
RO
(1in
x10
0ft
)T
hick
:us
efo
rfa
ying
sur-
face
sw
ithw
ide
gaps
.94
Av-
Dec
®Po
lyur
e-th
ane
Tape
s&
Seal
ants
,C
AG
EC
ode
#1N
PE1
Hi-
TakT
MPo
lyur
etha
neTa
pew
ithA
dhes
ive
onB
oth
Side
s
PNH
T39
35-7
-100
8030
-01-
494-
5206
RO
(1in
x12
ft)
Fay
surf
ace
seal
ing
area
sw
here
fluid
intr
usio
nis
apr
oble
mbu
tea
seof
com
-po
nent
rem
oval
isre
-qu
ired
,su
chas
airc
raft
floor
pane
lsan
dtie
dow
nfit
tings
.Fo
rm
axim
umse
alin
g,re
mov
eth
ere
-le
ase
film
sobo
thsi
des
ofth
eta
pead
here
toth
esu
r-fa
ces.
For
easi
erpa
nel
rem
oval
,le
ave
the
rele
ase
film
inpl
ace
onth
esi
deof
the
tape
inco
ntac
tw
ithth
ere
mov
able
pane
l.D
amag
edar
eas
are
easi
lyre
pair
edas
the
tape
ad-
here
sw
ell
toits
elf.
PNH
T39
35-7
-150
8030
-01-
494-
5209
RO
(1½
inx
12ft
)PN
HT
3935
-7-2
0080
30-0
1-49
4-52
07R
O(2
inx
12ft
)PN
HT
3935
-7-2
5080
30-0
1-49
4-41
36R
O(2
½in
x12
ft)
TO 1-1-691
A-50
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seT
ufSe
alFR
TM
Poly
-ur
etha
neTa
pew
ithPe
rman
ent
Teflo
n®B
acki
ngon
One
Side
PNH
T30
00-1
00O
pen
Purc
hase
RO
(1x
12ft
)Fa
ysu
rfac
ese
alin
gof
non-
perm
anen
tst
ruct
ures
such
asac
cess
and
insp
ectio
npa
nels
/cov
ers
onai
rcra
ft,
mis
sile
s,an
deq
uipm
ent
topr
even
tflu
iden
try
into
the
fayi
ngsu
rfac
ear
eas
and
the
cavi
ties
cove
red
byth
ein
stal
led
pane
ls/c
over
s.T
heTe
flon®
back
ing
ishi
ghly
abra
sion
resi
stan
tan
dpe
rmits
slig
htm
ove-
men
t(v
ibra
tion,
etc.
,)of
the
pane
ls/c
over
sw
ithou
tda
mag
ing
the
stru
ctur
eto
whi
chth
eyar
eat
tach
ed.
Thi
sta
peis
very
dura
ble,
soit
can
bere
used
inpl
ace
man
ytim
esaf
ter
initi
alin
stal
latio
n.D
am-
aged
sect
ions
are
easi
lyre
pair
edby
cutti
ngth
emou
tan
dsp
licin
gin
ane
wse
ctio
nth
atsl
ight
lyov
er-
laps
onto
the
cut
edge
sof
the
old
tape
seal
.
PNH
T30
00-1
50O
pen
Purc
hase
RO
(1½
inx
12ft
)PN
HT
3000
-200
Ope
nPu
rcha
seR
O(2
inx
12ft
)PN
DR
4000
FR-1
0080
30-0
1-49
8-90
79R
O(1
x12
ft)
PND
R40
00FR
-150
8030
-01-
498-
8779
RO
(1½
inx
12ft
)PN
DR
4000
FR-2
0080
30-0
1-49
8-90
78R
O(2
inx
12ft
)PN
DR
4000
FR-2
5080
30-0
1-49
8-90
76R
O(2
½in
x12
ft)
Self
Lev
elin
gTM
Gre
enPo
lyur
etha
neSe
alan
t
PNH
T33
26-5
-50
8030
-01-
494-
9650
CA
(50
CC
)T
his
seal
ant
isin
tend
edfo
rfil
ling
void
s/ca
vitie
son
hori
zont
alsu
rfac
es,
such
asai
rcra
ftse
attr
ack
de-
pres
sion
s,to
prev
ent
fluid
from
accu
mul
atin
gin
them
and
caus
ing
corr
o-si
onw
hile
still
bein
gea
syto
rem
ove
for
requ
ired
insp
ectio
nsan
d/or
oper
a-tio
nal
use.
Itis
also
usef
ulfo
rfil
ling
cavi
ties
arou
ndan
tenn
aco
nnec
tors
.
TO 1-1-691
A-51
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seT
hixo
flexT
MO
rang
ePo
lyur
etha
neSe
al-
ant
PNT
F221
9-50
8030
-01-
494-
7677
CA
(50
CC
)T
his
seal
ant
isin
tend
edfo
rfil
ling
the
sam
ety
pes
ofvo
ids/
cavi
ties
asth
eSe
l-fL
evel
ingT
MG
reen
seal
-an
t,bu
tit
can
also
beus
edon
vert
ical
and
over
-he
adsu
rfac
esas
itis
ave
ryth
ick
mat
eria
lth
atw
illre
mai
nin
plac
ew
ith-
out
runn
ing
whi
leit
cure
s.It
isal
soea
sily
rem
oved
for
requ
ired
insp
ectio
nsan
d/or
oper
atio
nal
use.
Seal
ant
Dis
pens
erPN
UG
9811
08-0
1(5
0C
Cca
paci
ty)
5120
-01-
494-
7678
EA
95A
dhes
ion
Prom
oter
for
Poly
sulfi
deSe
alin
gC
om-
poun
dsSo
lven
tB
ased
(Blu
eso
lu-
tion)
SAE
AM
S31
00/1
,PN
PR-1
48,
CA
GE
Cod
e#8
3574
8030
-00-
560-
8756
CN
(1PT
)So
lven
tba
sed
solu
tion
for
enha
ncin
gth
ead
hesi
onof
poly
sulfi
deco
mpo
unds
toa
wid
eva
riet
yof
sub-
stra
tes
(e.g
.in
tegr
alfu
elta
nks)
.App
lyby
brus
hor
clea
ncl
oth.
Mat
eria
ldr
ies
atro
omte
mpe
ratu
rein
appr
oxim
atel
y30
min
utes
leav
ing
atit
anat
efil
mon
the
surf
ace
that
enha
nces
seal
ant
adhe
sion
.W
ater
Bas
ed(P
ink
solu
tion)
SAE
AM
S31
00/3
,PN
PR-1
82,
CA
GE
Cod
e#8
3574
8030
-01-
131-
3228
CN
(1PT
)V
OC
com
plia
ntso
lutio
nfo
ren
hanc
ing
adhe
sion
ofpo
lysu
lfide
seal
ants
tow
ide
vari
ety
subs
trat
es(e
.g.
inte
gral
fuel
tank
s).
App
lyby
brus
hor
clea
ncl
oth.
Itdr
ies
atro
omte
mpe
ratu
rein
30m
inut
esle
avin
gan
adhe
sion
en-
hanc
ing
film
.
TO 1-1-691
A-52
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se96
Adh
esio
nPr
omot
erfo
rPo
lyth
ioet
her
Seal
ing
Com
-po
unds
Solv
ent
Bas
edSi
lane
Solu
-tio
n(Y
ello
wso
lu-
tion)
PNPR
-186
,C
AG
EC
ode
#835
7480
30-0
1-36
3-66
82B
T(1
OZ
)So
lven
tba
sed
sila
neso
lutio
nfo
ren
hanc
ing
the
adhe
-si
onof
poly
thio
ethe
rse
al-
ants
tocu
red
poly
sulfi
deor
poly
thio
ethe
rse
alan
tsan
da
vari
ety
ofco
ated
met
alsu
rfac
es(e
.g.
inte
-gr
alfu
elta
nks)
.App
lyby
brus
hor
clea
ncl
oth.
Ma-
teri
aldr
ies
atro
omte
m-
pera
ture
inap
prox
imat
ely
30m
inut
esle
avin
ga
si-
lane
film
that
enha
nces
seal
ant
adhe
sion
.
8030
-01-
363-
6679
BT
(2O
Z)
8030
-01-
363-
6678
BT
(16
OZ
)
97Pl
astic
Adh
esiv
efo
rSA
EA
MS
3255
EPT
FE(S
kyfle
x®)
Seal
ing
Tape
with
noA
dhes
ive
Bac
k-in
g(R
ed-b
row
nin
Col
or)
Scot
ch-G
rip
847
(Liq
uid)
CA
GE
Cod
e#1
A9T
380
40-0
1-03
3-75
07T
U(5
OZ
)U
seto
hold
EPT
FEse
alin
gta
pew
ithno
adhe
sive
back
ing
inpl
ace.
Fast
dry-
ing
and
resi
sts
wea
ther
ing,
wat
er,
oil,
plas
ticiz
erm
i-gr
atio
nan
dal
ipha
ticfu
els.
(Am
ber
inC
olor
)M
MM
-A-1
89Sc
otch
-Gri
p10
99(B
rush
orSp
ray)
CA
GE
Cod
e#1
A9T
3
8040
-01-
126-
1422
CN
(1Q
T)
Scot
ch-G
rip
1099
-L(B
rush
)C
AG
EC
ode
#1A
9T3
8040
-00-
043-
1717
TU
(2O
Z)
SOLV
EN
TS
98D
ryC
lean
ing
and
Deg
reas
ing
Sol-
vent
s
A-A
-596
01,
Type
II68
50-0
0-11
0-44
98C
N(1
PT)
Gen
eral
purp
ose
clea
ning
solv
ent
for
rem
ovin
goi
l,gr
ease
,pa
intin
gpr
eser
va-
tion
com
poun
ds,
etc.
,fr
ompa
inte
dor
unpa
inte
dm
etal
surf
aces
.D
ono
tus
eas
afin
alcl
eane
rpr
ior
to.
(Hig
hFl
ash
Poin
t+
140°
F/+
61°
C)
6850
-00-
637-
6135
GL
(1G
L)
6850
-00-
274-
5421
CN
(5G
L)
6850
-00-
285-
8011
DR
(55
GL
)
TO 1-1-691
A-53
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
seTy
peII
I68
50-0
1-37
7-19
16C
N(4
OZ
)Id
eal
for
use
inlo
calit
ies
whe
reTy
peII
ofth
ism
a-te
rial
isre
stri
cted
orpr
o-hi
bite
ddu
eto
itshi
gher
VO
Cco
nten
t,va
por
pres
-su
re,
and/
orlo
wer
flash
poin
t.(V
ery
Hig
hFl
ash
Poin
t+
200°
F/+
93°
C)
6850
-01-
377-
1811
CN
(1PT
)N
OT
E
Thi
sso
lven
tm
ust
bew
iped
off
the
surf
ace
com
plet
ely
asit
has
ave
rysl
owev
apor
atio
nra
te.
6850
-01-
377-
1808
CN
(1Q
T)
6850
-01-
377-
1809
CN
(1G
L)
6850
-01-
331-
3349
CN
(5G
L)
6850
-01-
331-
3350
DR
(55
GL
)
MIL
-PR
F-68
0,Ty
peII
Gen
eral
purp
ose
clea
ning
solv
ent
for
rem
ovin
goi
l,gr
ease
,et
c.,
from
met
alsu
rfac
es.
Do
not
use
asa
final
clea
ner
prio
rto
pain
ting
orap
plyi
ngpr
es-
erva
tion
com
poun
ds,
etc.
,on
pain
ted
orun
pain
ted
surf
aces
.Sa
me
asA
-A-
5960
1,Ty
peII
.
(Hig
hFl
ash
Poin
t+
140°
F/+
61°
C)
6850
-01-
474-
2319
CN
(1G
L)
6850
-01-
474-
2317
CN
(5G
L)
6850
-01-
474-
2316
DR
(55
GL
)
Type
III
6850
-01-
474-
2318
CN
(1G
L)
Idea
lfo
rus
ein
loca
litie
sw
here
Type
IIof
this
ma-
teri
alis
rest
rict
edor
pro-
hibi
ted
due
toits
high
erV
OC
cont
ent,
vapo
rpr
es-
sure
,an
d/or
low
erfla
shpo
int.
Sam
eas
A-A
-59
601,
Type
III.
TO 1-1-691
A-54
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se(V
ery
Hig
hFl
ash
Poin
t+
200°
F/+
93°
C)
6850
-01-
474-
2320
CN
(5G
L)
NO
TE
Thi
sso
lven
tm
ust
bew
iped
off
the
surf
ace
com
plet
ely
asit
has
ave
rysl
owev
apor
atio
nra
te.
6850
-01-
474-
2321
DR
(55
GL
)
99W
ipe
Solv
ent,
Low
Vap
orPr
essu
reP-
W-2
891,
Type
I(F
ast
Eva
pora
tion;
Flas
hPo
int
+10
0°F/
+38
°C
min
imum
)C
lass
A(i
ncom
patib
lew
/acr
yl-
ics
&po
lyca
rbon
ates
)
7930
-01-
436-
8085
CN
(1PT
)C
lean
ing
ofai
rcra
ftsu
rfac
espr
ior
topa
intin
g,se
alin
g,no
n-st
ruct
ural
adhe
sive
bond
ing,
etc.
,as
anal
ter-
nativ
efo
rM
EK
,M
IBK
,M
IL-T
-817
72,
and
A-A
-59
281.
Type
II,
Cla
ssB
mat
eria
lsar
esa
feto
use
onw
indo
ws,
win
dshi
elds
/w
inds
cree
ns,
and
cano
-pi
es.
7930
-01-
436-
8023
CN
(1Q
T)
7930
-01-
436-
8077
CN
(1G
L)
7930
-01-
436-
7959
CN
(5G
L)
7930
-01-
436-
8019
DR
(55
GL
)Ty
peII
(Slo
wE
vapo
ra-
tion;
Hig
hFl
ash
Poin
t+
140°
F/+
61°
Cm
ini-
mum
)C
lass
B(A
cryl
ican
dpo
lyca
rbon
ate
com
patib
le)
7930
-01-
436-
8024
CN
(1Q
T)
7930
-01-
436-
7904
CN
(1G
L)
7930
-01-
436-
7953
BX
(4E
A,
1G
LB
T)
7930
-01-
436-
7944
CN
(5G
L)
7930
-01-
436-
8013
DR
(55
GL
)M
IL-P
RF-
3229
5,Ty
peII
;68
50-0
1-60
6-83
561
GL
Gen
eral
purp
ose
clea
ning
solv
ent
for
rem
ovin
goi
l,gr
ease
,et
c.fr
omm
etal
surf
aces
.D
ono
tus
eas
afin
alcl
eane
rpr
ior
topa
intin
gor
appl
ying
pres
-er
vatio
nco
mpo
unds
,et
c.,
onpa
inte
dor
unpa
inte
dsu
rfac
es.
Hig
hFl
ash
Poin
t14
2°F
6850
-01-
606-
8357
5G
L(6
1.1°
C)
6850
-01-
606-
3293
15G
L68
50-0
1-60
6-83
5855
GL
TO 1-1-691
Change 5 A-55
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
se10
0So
lven
ts,
Cle
anin
g,fo
rC
lean
ing
Prio
rto
Seal
antA
pplic
a-tio
n
SAE
AM
S31
66,
PND
S-10
8,C
AG
EC
ode
#302
56
7930
-01-
367-
0994
BX
(24
EA
,1
PTB
TSq
ueez
eT
rig-
ger)
Cle
anin
gof
airc
raft
,m
issi
le,
and
equi
pmen
tpr
imar
yan
dse
cond
ary
stru
ctur
al(i
.e.,
met
alan
dco
mpo
site
)su
rfac
espr
ior
tose
alin
g,bo
ndin
g,an
dap
plic
atio
nof
adhe
sion
prom
oter
s,et
c.
7930
-01-
367-
0995
BX
(4E
A,
1G
LB
T)
7930
-01-
367-
0996
CO
(5G
L)
7930
-01-
367-
0997
DR
(55
GL
)10
1Is
opro
pylA
lcoh
ol,
Tech
nica
l(I
PA,
2-Pr
opan
ol,
and/
orIs
opro
pano
l)
TT-
I-73
568
10-0
0-75
3-49
93C
N(½
PT)
Use
dfo
rre
mov
alof
fung
i(m
olds
)an
dcl
eani
ngof
elec
tric
alan
del
ectr
onic
com
pone
nts
and
conn
ec-
tors
.
6810
-00-
983-
8551
CN
(1Q
T)
6810
-00-
286-
5435
CN
(1G
L)
Do
not
use
onac
rylic
plas
ticm
ater
ials
asit
may
caus
ecr
azin
g.
6810
-00-
543-
7915
CN
(5G
L)
6810
-00-
586-
6647
DR
(55
GL
)
102
Alip
hatic
Nap
htha
TT-
N-9
5,Ty
peII
(for
Cle
anin
gA
cryl
icPl
as-
tics)
6810
-00-
238-
8119
CN
(1G
L)
Use
dfo
rcl
eani
ng/d
egre
asin
gac
rylic
plas
tics
(i.e
.,w
ind-
scre
ens
and
cano
pies
).68
10-0
0-26
5-06
64C
N(5
GL
)68
10-0
0-23
8-81
17D
R(5
5G
L)
103
Seal
ant
Rem
over
,C
hem
ical
Type
Aer
osaf
ePr
oduc
tsIn
c.,
CA
GE
Cod
e#1
LFP
0C
omm
erci
alIt
ems
Sky
Res
tore
®,
PNL
M30
6/1
(Thi
nso
lu-
tion)
8030
-01-
466-
4432
PG(6
EA
,1
LB
T)
Use
dto
assi
stin
poly
sulfi
dese
alan
tre
mov
alby
soft
en-
ing
the
seal
ant
befo
reus
-in
ga
plas
ticsc
rape
ror
tool
.App
lied
byno
n-m
e-ta
llic
brus
h,cl
oth,
orpu
mp
spra
y.
TO 1-1-691
A-56 Change 5
Tabl
eA
-2.
Con
sum
able
Mat
eria
ls-
Con
tinu
ed
Item No.
Nom
encl
atur
eSp
ecifi
catio
n/PN
Nat
iona
lSt
ock
Num
ber
Uni
tof
Issu
eIn
tend
edU
sePN
LM
307/
1(T
hick
so-
lutio
n)80
30-0
1-46
6-44
33PG
(6E
A,
1L
BT
)
Thi
sm
ater
ial
has
anob
noxi
ous
odor
.U
sein
aw
ell
vent
ilate
dar
eaan
d/or
requ
ire
pers
onne
lto
wea
ran
appr
opri
ate
resp
irat
orif
ina
con-
fined
area
.
Sky
Was
h®,P
NL
M30
8/1
8030
-01-
466-
4431
PG(6
EA
,1
LB
T)
Use
dto
neut
raliz
eth
ear
eafr
omw
hich
seal
ant
was
rem
oved
with
the
abov
em
ater
ial.
App
lied
byno
n-m
etal
licbr
ush,
clot
h,or
pum
psp
ray,
scru
bbed
with
ano
n-m
etal
licbr
ush
ora
clot
han
dth
enw
iped
dry
with
acl
oth.
PNL
M60
2/4
8030
-01-
477-
7897
EA
(100
EA
)
TO 1-1-691
Change 5 A-57/(A-58 blank)
APPENDIX BEQUIPMENT FOR CLEANING AND CORROSION PREVENTION AND
CONTROL
B.1 INTRODUCTION.
Table B-2 provides a list of accessories used for aircraft,missile, and equipment cleaning and corrosion preventionand control. Refer to AFI 23-101 for EAID authorization ofadditional equipment. The Table B-2 column headings list:Nomenclature, Specifications/PN’s, National Stock Numbers,Unit of Issue, and Intended Use. Items are divided into func-tional groupings as follows:
• Cleaning accessories.
• Corrosion removal accessories.
• Conversion coating accessories.
• Lighting accessories.
• Safety accessories.
• Sealing accessories.
B.1.1 Unit of Issue Codes. The unit of issue codes usedunder the unit of issue column are shown and explained asfollows in Table B-1.
Table B-1. Unit of Issue Codes
Code Unit Code Unit Code UnitBG Bag EA Each PG PackageBO Bolt FT Foot PR PairBT Bottle GL Gallon PT PintBX Box GR Gross QT QuartCA Cartridge JR Jar RO RollCB Carboy KG Kilogram SE SetCC Cubic Cent. KT Kit SH SheetCN Can L Liter TU TubeCO Container LB Pound YD YardCS Case LG LengthDR Drum MX ThousandDZ Dozen OZ Ounce
TO 1-1-691
Change 15 B-1
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
CL
EA
NIN
GE
QU
IPM
EN
T1
Air
craf
tW
ashi
ngK
it,E
xter
ior,
Con
form
able
3MC
o.,
CA
GE
Cod
e#7
6381
,PN
251
(Con
-fo
rmab
leap
plic
ator
head
&2
EA
ofea
chty
peof
pad)
7920
-00-
490-
6046
KT
Gen
eral
clea
ning
ofai
rcra
ft,
mis
sile
,an
deq
uipm
ent
surf
aces
.U
ses
12in
Lx
6in
Wx
1in
orus
ere
-pl
acem
ent
pads
liste
din
App
endi
xA
,Ta
ble
A-2
,It
emN
o.37
.2
Spon
ge,
Synt
hetic
L-S
-626
,C
lass
1,G
rade
Bor
A-A
-207
3,Ty
peI,
Styl
eB
,C
lass
1
7920
-00-
633-
9915
EA
(7in
Lx
4¼
inW
x2
3⁄8
inT
)
Fine
pore
synt
hetic
spon
gefo
rap
plic
atio
nof
clea
ning
com
poun
dson
and
scru
b-bi
ngof
pain
ted
and
un-
pain
ted
surf
aces
byha
nd.
3Sc
rub
Bru
shA
-A-2
074
(sup
erse
des
H-B
-149
0),
Type
I,St
yle
A(N
ylon
Bri
stle
s)
7920
-00-
619-
9162
EA
(4½
inx
1¾
in)
App
licat
ion
ofcl
eani
ngco
mpo
unds
and
scru
bbin
gof
pain
ted
and
unpa
inte
dai
rcra
ft,
mis
sile
and
equi
p-m
ent
surf
aces
.Ty
peII
,St
yle
C(T
ampi
coB
rist
les)
7920
-00-
282-
2470
EA
(10
¾in
x2
¾in
)Ty
peIV
,St
yle
B(N
ylon
Bri
stle
s)79
20-0
0-06
1-00
37E
A(8
½in
x5
in)
Type
IV,
Styl
eD
(Pal
myr
aB
rist
les)
7920
-01-
067-
6203
EA
(8½
inD
)
4B
rush
,Air
craf
tC
lean
ing
MIL
-B-2
3958
,Ty
peI
(Ny-
lon
Bri
stle
s)St
yle
179
20-0
0-05
4-77
68E
A(5
3⁄8
inD
)A
pplic
atio
nof
clea
ning
com
poun
dsan
dsc
rubb
ing
ofpa
inte
dan
dun
pain
ted
airc
raft
,m
issi
lean
deq
uip-
men
tsu
rfac
es.
Styl
e2
7920
-00-
051-
4386
EA
(6in
x2
in)
Styl
e3
7920
-00-
051-
4383
EA
(12
inx
3½
in)
Type
II(T
ampi
coB
rist
les)
Styl
e2
7920
-00-
957-
5945
EA
(6in
x2
½in
)Ty
peII
I(N
ylon
/Tam
pico
Bri
stle
s)St
yle
179
20-0
0-05
1-43
84E
A(5
3⁄8
inD
)
Styl
e2
7920
-00-
051-
4387
EA
(6in
x2
in)
Styl
e3
7920
-00-
051-
4385
EA
(12
inx
3½
in)
TO 1-1-691
B-2
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
5W
indo
wB
rush
,W
ater
proo
f(H
orse
hair
Bri
stle
s)
Type
I(R
ound
)79
20-0
0-24
0-71
76E
A(4
.5in
D)
Scru
bbin
gai
rcra
ft,
mis
sile
,an
deq
uipm
ent
pain
ted
and
unpa
inte
dsu
rfac
es,
win
dow
s,w
inds
hiel
ds,
and/
orw
inds
cree
ns.
7920
-00-
297-
1509
EA
(8in
D)
Type
II(R
ecta
ngul
ar)
7920
-01-
136-
8892
EA
(6in
x4
in)
6To
othb
rush
,So
ftB
rist
le,
Stra
ight
Lin
eD
esig
n
A-A
-59
(Chi
ldre
n’s
-30
Tuf
ts)
8530
-01-
293-
1388
DZ
Cle
anin
gin
tric
ate
part
s.B
e-fo
reus
ing,
ensu
rech
emi-
cals
will
not
diss
olve
orso
ften
brus
hha
ndle
and
bris
tles.
A-A
-123
(Adu
lt’s
-30
Tuf
ts)
8530
-01-
293-
1387
DZ
7H
andl
es,
Woo
d,A
cme
Thr
eade
dan
dTa
pere
dE
nds
A-A
-308
2(s
uper
sede
sN
N-
H-1
04),
Type
I(T
hrea
ded
met
alen
d)7/ 8
inD
x4
ftL
7920
-00-
982-
6512
EA
Han
dles
for
use
with
scru
b/cl
eani
ngbr
ushe
s(I
tem
No.
3an
dIt
emN
o.4)
,an
dai
rcra
ftw
ashi
ngki
t(I
tem
No.
1).
Type
II(T
aper
eden
d)15
/16
inD
x4
½L
7920
-00-
177-
5106
EA
15/1
6in
Dx
5ft
L79
20-0
0-26
3-03
28E
A1
inD
x4
½L
7920
-00-
141-
5452
EA
1in
Dx
8ft
L79
20-0
0-26
3-03
27E
A1
inD
x4
¼ft
L79
20-0
0-26
3-03
24E
A8
Han
dle,
Acm
eT
hrea
ded
End
(Tel
esco
pic)
A-A
-146
4(7
/ 8in
D)
7920
-00-
926-
5146
EA
A5
ftto
10ft
exte
ndab
leal
umin
umha
ndle
for
scru
b/cl
eani
ngbr
ushe
s(I
tem
No.
3an
dIt
emN
o.4)
,or
airc
raft
was
hing
kit
(Ite
mN
o.1)
,to
clea
nhi
ghsu
rfac
eson
airc
raft
oreq
uipm
ent.
9N
ozzl
es,
Gar
den
Hos
e(f
or5/ 8
and
¾in
Hos
e)A
d-ju
stab
le
A-A
-504
61St
raig
ht,A
d-ju
stab
leSp
ray
(Bra
ss)
4730
-00-
223-
6731
EA
Spra
ying
and
rins
ing
ofai
r-cr
aft,
mis
sile
s,an
deq
uip-
men
tdu
ring
clea
ning
op-
erat
ions
.Pi
stol
Gri
p,A
djus
tabl
e(C
oppe
rA
lloy
w/R
ubbe
rC
over
)PN
1085
5,C
AG
EC
ode
#971
41
4730
-00-
900-
0733
EA
TO 1-1-691
B-3
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
10H
ose
and
Hos
eA
s-se
mbl
ies,
Non
-M
etal
lic(R
ubbe
r,Pl
astic
)
A-A
-592
70(s
uper
sede
sL
-H-5
20),
Type
I,C
lass
I(R
ubbe
r)5/ 8
inID
x50
ftL
4720
-00-
203-
3920
EA
Spra
ying
and
rins
ing
ofai
r-cr
aft,
mis
sile
s,an
deq
uip-
men
tdu
ring
clea
ning
op-
erat
ions
.¾
inID
x50
ftL
4720
-00-
203-
3912
EA
Type
II,
Gra
deA
(PV
C)
5/ 8
inx
50ft
4720
-00-
729-
5334
EA
¾in
x50
ft47
20-0
0-72
9-53
38E
A11
Pum
p,B
ackp
ack
(5G
Lca
paci
ty)
PN51
00-2
54B
,C
AG
EC
ode
#040
2443
20-0
0-28
9-89
12E
AL
ocal
ized
smal
lar
eacl
ean-
ing
and
rins
ing
ofai
rcra
ft,
mis
sile
,an
deq
uipm
ent
surf
aces
.12
Spra
yers
Inse
cti-
cide
,M
anua
lly-
Car
ried
,H
and
Ope
rate
d-C
om-
pres
sion
A-A
-557
48(s
uper
sede
sM
IL-S
-141
02)
3740
-00-
191-
3677
EA
(1G
Lca
pac-
ity)
Use
dto
appl
yso
ilba
rrie
rm
ater
ial
onai
rcra
ftsu
r-fa
ces.
3740
-00-
641-
4719
EA
(2G
Lca
pac-
ity)
13G
uns,
Spra
y,O
ilsan
dSo
lven
tSA
EA
MS-
G-9
52(s
uper
-se
des
MIL
-G-9
52),
Type
I
4940
-00-
248-
0866
EA
Non
-ato
miz
ing,
trig
ger
oper
-at
edsp
ray
nozz
lefo
rsp
rayi
ngcl
eani
ngco
m-
poun
dson
airc
raft
,m
is-
sile
s,an
deq
uipm
ent.
14C
lean
ing
Uni
t,Po
r-ta
ble,
Foam
Gen
-er
atin
gSt
ainl
ess
Stee
lTa
nk(P
orta
-Fo
amer
)
PN00
20SS
,C
AG
EC
ode
#213
6149
40-0
1-05
8-52
67E
A(1
5G
Lca
-pa
city
)Fo
amap
plic
ator
for
MIL
-PR
F-87
937
and
MIL
-PR
F-85
570
clea
ning
com
-po
unds
for
clea
ning
airc
raft
,m
issi
le,
and
equi
pmen
tex
teri
ors.
Use
sco
mpr
esse
dai
rto
spra
yw
ater
dete
rgen
tso
lutio
ns.
May
also
beus
edto
appl
ycl
eani
ngso
lven
tsfo
rcl
eani
ngen
gine
san
dot
her
equi
pmen
t.A
gun
type
spra
yw
and
and
nozz
leis
incl
uded
.
PN94
88-7
023,
CA
GE
Cod
e#8
5884
4940
-01-
041-
5680
EA
(45
GL
ca-
paci
ty)
TO 1-1-691
B-4
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
15C
lean
er,
Pres
sure
,So
lven
t-W
ater
(Uni
vers
alW
ash
Uni
t)
PN21
C24
38G
01,
CA
GE
Cod
e#9
9207
4940
-01-
185-
6215
EA
Use
dto
appl
ycl
eani
ngco
m-
poun
dso
lutio
nsin
ano
n-fo
amst
ate
toai
rcra
ft,
mis
-si
le,
and
equi
pmen
tex
teri
orsu
rfac
esat
ara
teof
2½
GL
/min
at30
PSI
pres
sure
.16
Car
t,C
orro
sion
Con
trol
(Tur
bine
Eng
ine
Cle
anin
g)
Mod
el#6
2555
,PN
65A
102J
1,C
AG
EC
ode
#0G
ZN
8
4920
-00-
930-
1801
EA
Port
able
clea
ning
mac
hine
for
clea
ning
and
rins
ing
airc
raft
turb
ine
engi
nes.
17D
eice
r,A
ircr
aft
(Tru
ckM
ount
ed)
Mod
el#5
8323
,PN
D40
-D,
CA
GE
Cod
e#5
8323
&93
408
1730
-01-
093-
6517
EA
Tru
ckm
ount
edsp
ray
unit
used
tosp
ray
deic
ing
and
anti-
icin
gflu
ids
onai
rcra
ftex
teri
orsu
rfac
es.
18H
eate
r,G
un,
Ele
c-tr
icTy
peA
-A-5
9435
,Ty
peI
(350
°-5
00°
F)49
40-0
0-35
7-13
69E
ATo
thaw
ordr
yeq
uipm
ent/
com
pone
nts
orto
shri
nkhe
atsh
rink
type
insu
latin
gtu
bing
asso
ciat
edw
ithel
ectr
ical
appl
icat
ions
.
Type
II(5
00°
-750
°F)
4940
-01-
028-
7493
EA
Type
III
(750
°-1
000°
F)49
40-0
1-39
1-70
46E
A
19V
acuu
mC
lean
er,
Pneu
mat
icPN
AT
560A
CF-
18,
CA
GE
Cod
e#0
0784
5130
-01-
368-
5861
EA
Smal
l,lig
htw
eigh
t,al
umi-
num
,ve
ntur
ity
pe,
hand
held
vacu
umcl
eane
rw
ith18
inL
flexi
ble
hose
for
rem
ovin
gdi
rtan
dde
bris
from
airc
raft
,m
issi
le,
and
equi
pmen
tin
teri
ors.
20V
acuu
mC
lean
er(w
ithA
ttach
-m
ents
)
Pneu
mat
icTy
pe,
PN15
-A
1080
,C
AG
EC
ode
#581
50
7910
-00-
807-
3704
EA
For
rem
ovin
gdi
rt,
debr
is,
and
fluid
sfr
omai
rcra
ft,
mis
sile
,an
deq
uipm
ent
inte
rior
s.E
lect
ric
Type
(A-A
-549
43),
PNC
8398
5-01
,C
AG
EC
ode
#168
93
7910
-01-
208-
6017
EA
For
rem
ovin
gdi
rt,
debr
is,
and
fluid
sfr
omai
rcra
ft,
mis
sile
,an
deq
uipm
ent
inte
rior
s.T
his
vacu
umcl
eane
rca
nal
sobe
used
tore
mov
ein
fect
ious
was
tem
ater
ials
.
TO 1-1-691
B-5
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
21B
ottle
,App
licat
or,
16O
ZC
apac
ity(A
djus
tabl
eSp
ray
Noz
zle)
A-A
-280
681
25-0
0-48
8-79
52E
ASp
rayi
ngof
clea
ning
com
-po
und
solu
tions
onsm
all
area
sof
airc
raft
,m
issi
le,
and
equi
pmen
tsu
rfac
es.
22Sp
ray
Kit,
Self
Pres
suri
zed
Tri
g-ge
rSp
ray,
Poly
-et
hyle
neB
ottle
(32
OZ
Cap
acity
)
PN43
82T
1,C
AG
EC
ode
#394
2849
40-0
1-36
4-87
61E
ASp
rayi
ngof
clea
ning
com
-po
und
solu
tions
onsm
all
area
sof
airc
raft
,m
issi
le,
and
equi
pmen
tsu
rfac
es.
23U
tility
Pail,
Plas
tic(3
GL
Cap
acity
)A
-A-5
9253
(sup
erse
des
L-P
-65)
,Si
ze4,
Styl
eB
7240
-00-
246-
1097
EA
Con
tain
erfo
rho
ldin
gw
ater
and
chem
ical
solu
tions
for
clea
ning
and
corr
osio
ntr
eatm
ent
oper
atio
ns.
CO
NV
ER
SIO
NC
OA
TIN
GE
QU
IPM
EN
T24
Bru
sh,A
cid
Swab
-bi
ng(M
etal
Han
dle/
Hor
seha
ir&
Hog
Bri
stle
Bru
sh)
A-A
-289
,Ty
peII
,C
lass
1,Si
ze1
7920
-00-
514-
2417
GR
(5¾
inL
x3⁄8
inW
)D
ispo
sabl
ebr
ush
for
appl
y-in
gch
emic
alco
nver
sion
coat
ing
solu
tions
and
som
ebr
usha
ble
seal
ants
.
25M
oist
ener
,Pa
per
Seal
ing,
Foun
-ta
in-T
ype
(Spo
nge
Moi
st-
ener
Stic
k)
A-A
-137
(sup
erse
des
GG
-M
-571
)75
20-0
0-24
1-29
81E
AA
pplic
atio
nof
chem
ical
conv
ersi
onco
atin
gso
lu-
tions
tosm
all
area
s.
26W
ash
Bot
tle,
Lab
o-ra
tory
,Po
lyet
hyl-
ene
(250
ml.
Ca-
paci
ty)
Com
mer
cial
Item
,C
AG
EC
ode
#255
1866
40-0
0-29
9-84
93E
AB
X(1
2E
A)
Use
dfo
rri
nsin
gch
emic
ally
trea
ted
surf
aces
.
CO
RR
OSI
ON
RE
MO
VA
LE
QU
IPM
EN
T27
Dri
ll,Pn
eum
atic
,Po
rtab
le(¼
inC
huck
;32
00R
PM)
OO
-D-6
91,
Type
I,St
yle
C(S
trai
ght
Dri
ve,
Pist
olG
rip)
5130
-00-
294-
9511
EA
Cor
rosi
onre
mov
alan
dsc
uff
sand
ing.
Type
I,St
yle
A(9
0°A
ngle
Dri
ve,
Bod
yG
rip)
5130
-00-
293-
1977
EA
28K
ey,
Dri
llC
huck
(¼in
Dri
ve)
A-A
-509
66,
PNK
1,C
AG
EC
ode
#750
7834
60-0
0-26
4-55
77E
ASe
curi
ngor
rele
asin
gdr
illbi
t.Fo
rus
ew
ithIt
emN
o.27
drill
mot
or.
TO 1-1-691
B-6
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
29Sa
nder
,Pa
d,Pn
eu-
mat
ic(O
rbita
lM
otio
n)6,
000
-9,
000
RPM
A-A
-268
7(O
O-S
-101
,Ty
peI,
Styl
e1)
5130
-00-
606-
9694
EA
Cor
rosi
onre
mov
alan
dbl
end
out
asw
ell
assc
uff
sand
ing,
finis
hsa
ndin
g,an
dfe
athe
red
ging
/ble
nd-
ing
ofpa
int
surf
aces
.30
Sand
er,
Dis
c,Pn
eu-
mat
ic,
Port
able
(Ran
dom
Orb
ital)
Dua
lM
otio
n,V
ertic
alD
rive
with
6in
Dm
axPa
d&
7000
RPM
max
(Unl
oade
d)
A-A
-269
0(O
O-S
-101
,Ty
peII
,St
yle
3)51
30-0
0-20
4-06
23E
AC
orro
sion
rem
oval
and
blen
dou
tas
wel
las
scuf
fsa
ndin
g,fin
ish
sand
ing,
and
feat
her
edgi
ng/b
lend
-in
gof
pain
tsu
rfac
es.
The
sand
er’s
rand
omor
bita
lac
tion
prev
ents
scra
tche
san
dsw
irl
mar
ks.
31Sa
nder
,D
isc,
Pneu
-m
atic
,Po
rtab
le(R
ight
Ang
le)
Rig
htA
ngle
Dri
vew
ith7
inD
Pad
max
&60
00R
PMm
ax(U
n-lo
aded
)
A-A
-268
9(O
O-S
-101
,Ty
peII
,St
yle
2)51
30-0
0-59
6-11
76E
AC
orro
sion
rem
oval
and
blen
dou
t.R
ight
angl
edr
ive
mak
esit
easi
erto
use
inco
rner
s,al
ong
edge
s,an
din
tight
spac
es.
32D
ryH
onin
gM
a-ch
ine,
Port
able
,A
ir-O
pera
ted
(Vac
u-B
last
er)
PN41
303
CA
GE
,C
ode
#625
5549
40-0
0-87
2-17
12E
AA
com
pact
,se
lf-c
onta
ined
,lig
htw
eigh
tab
rasi
vebl
astin
gun
itus
edfo
rth
esa
fean
dco
nven
ient
re-
mov
alof
corr
osio
npr
od-
ucts
from
airc
raft
,m
issi
lean
deq
uipm
ent
surf
aces
and
thei
rco
mpo
nent
sw
ithno
haza
rdou
spa
rtic
leem
issi
ons.
All
abra
sive
part
icle
s,co
rros
ion
prod
-uc
ts,
and
pain
tch
ips
are
draw
nba
ckin
toth
em
a-ch
ine
whe
rere
sidu
esar
efil
tere
dou
tan
dco
llect
edfo
rdi
spos
al,
and
the
abra
-si
vepa
rtic
les
are
recy
cled
.
TO 1-1-691
B-7
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
33E
lect
rica
lPu
mp
Kit
for
Dry
Hon
ing
Mac
hine
(Ite
mN
o.32
)
PN91
8708
,C
AG
EC
ode
#625
5549
40-0
0-94
8-38
10E
AT
heel
ectr
icpu
mp
for
the
Dry
Hon
ing
Mac
hine
al-
low
sus
eof
low
pres
sure
/lo
wvo
lum
eai
rto
oper
ate
inst
ead
ofth
elo
wpr
es-
sure
/hig
hvo
lum
eai
rre
-qu
ired
toop
erat
eun
itseq
uipp
edw
ithth
eai
rej
ec-
tor
pum
p.34
Gun
,Air
Blo
w(B
last
Cle
anin
g)A
-A-5
5543
(sup
erse
des
GG
G-G
-770
),Ty
peII
(Pus
hbu
tton)
,St
yle
B(3
⁄8in
Int.
Thd
.)
4940
-00-
223-
8972
EA
Use
tore
mov
ech
ips,
dirt
,an
dw
aste
mat
eria
lfr
omm
achi
nes,
wor
kpi
eces
,or
benc
hes.
Type
II(P
ush
butto
n),
Styl
eA
(¼in
Int.
Thd
.)49
40-0
0-33
3-55
41E
A
35A
irH
ose
Ass
em-
blie
s,G
ener
alPu
rpos
eH
ose
and
Hos
eA
ssem
blie
s,N
on-M
etal
licSp
ray
A-A
-596
13,
3⁄8
inID
x50
ft47
20-0
0-28
9-34
29FT
Hos
eas
sem
blie
sus
edw
ithpn
eum
atic
tool
s,pa
int
spra
ygu
ns,
and
dry
hon-
ing
mac
hine
s.
Hos
e,R
ubbe
r,an
dH
ose
Ass
embl
ies,
Rub
ber,
Pneu
-m
atic
(Yar
nan
dFa
bric
Rei
n-fo
rced
)
A-A
-595
65,
½in
IDx
50ft
4720
-00-
278-
4889
FT
5/ 8
inID
x50
ft47
20-0
0-27
8-48
90FT
¾in
IDx
50ft
4720
-00-
278-
4891
FT
36C
oupl
ing
Hal
ves,
Qui
ck-D
isco
nnec
tA
-A-5
9439
(sup
erse
des
MIL
-C-4
109)
,Ty
peII
(Mal
e)¼
inN
PT/M
end
(Sty
le1)
4730
-00-
494-
3271
EA
Mal
equ
ick
disc
onne
ctha
lves
for
use
with
pneu
-m
atic
tool
san
dpa
int
spra
ygu
ns.
3⁄8
inN
PT/F
end
(Sty
le2)
4730
-00-
293-
7182
EA
3⁄8
inSh
ank
end
(Sty
le3)
4730
-00-
277-
5679
EA
½in
NPT
/Men
d(S
tyle
1)47
30-0
0-29
3-71
65E
AM
ale
quic
kdi
scon
nect
halv
esfo
rus
ew
ithpo
r-ta
ble
dry
honi
ngm
a-ch
ines
.
½in
NPT
/Fen
d(S
tyle
2)47
30-0
1-23
3-34
34E
A¾
inN
PT/M
end
(Sty
le1)
4730
-00-
293-
7180
EA
TO 1-1-691
B-8
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
Type
I(F
emal
e)¼
inN
PT/F
end
(Sty
le2)
4730
-01-
177-
0987
EA
Fem
ale
quic
kdi
scon
nect
halv
esfo
rus
ew
ithpn
eu-
mat
icto
ols
and
pain
tsp
ray
guns
.3⁄8
inN
PT/M
end
(Sty
le1)
4730
-00-
203-
0178
EA
3⁄8
inSh
ank
end
(Sty
le3)
4730
-00-
494-
3272
EA
½in
NPT
/Men
d(S
tyle
1)47
30-0
0-20
3-48
47E
AFe
mal
equ
ick
disc
onne
ctha
lves
for
use
with
por-
tabl
edr
yho
ning
ma-
chin
es.
½in
Shan
ken
d(S
tyle
3)47
30-0
0-90
5-97
94E
A¾
inN
PT/M
end
(Sty
le1)
4730
-00-
293-
7043
EA
37H
ose
Cla
mp
A-A
-525
06(s
uper
sede
sW
W-C
-440
)47
30-0
0-90
8-31
94E
AM
etal
hose
clam
pus
edfo
rat
tach
ing
flexi
ble
duct
sor
hose
son
toeq
uipm
ent.
38H
and
Pad
Hol
der
(for
Use
with
App
endi
xA
,Ta
ble
A-2
,It
emN
o.1)
3MC
o.,
PN95
2(I
NST
A-
LO
K),
CA
GE
Cod
e#2
8124
Com
mer
cial
Item
Ope
nPu
rcha
seE
AH
and
tool
for
hold
ing
abra
-si
vepa
ds.
39H
olde
r,D
isk
Pad,
Hoo
kan
dL
oop
Type
(for
Use
with
Item
No.
47)
3MC
o.,
CA
GE
Cod
e#2
8124
,PN
9215
Com
mer
cial
Item
EA
Bac
kup
pad
toru
nsu
rfac
eco
nditi
onin
gdi
scs
ona
drill
mot
or.
(1½
inD
on¼
insh
ank)
Ope
nPu
rcha
sePN
0480
11-0
7494
-8C
omm
erci
alIt
emC
S(1
0E
A)
(2in
Don
¼in
shan
k)O
pen
Purc
hase
PN92
3(3
inD
on¼
insh
ank)
5345
-01-
342-
5932
EA
PN04
8011
-074
92-4
Com
mer
cial
Item
CS
(5E
A)
(4in
Don
¼in
shan
k)O
pen
Purc
hase
PN04
8011
-056
80-7
Com
mer
cial
Item
EA
(5in
Don
¼in
shan
k)O
pen
Purc
hase
40Pa
d,A
bras
ive
Dis
kH
olde
r(f
orU
sew
ithA
ppen
dix
A,
Tabl
eA
-2,
Item
No.
5)
3MC
o.,
CA
GE
Cod
e#2
8124
,PN
0511
44-
0557
6
5130
-01-
075-
8137
EA
Bac
kup
pad
toru
n6
inD
abra
sive
pape
rdi
scs
ona
dual
mot
ion
type
sand
er.
41M
andr
els
(for
Use
with
Item
No.
42an
dIt
emN
o.43
)
3MC
o.,
CA
GE
Cod
e#2
8124
,PN
990
(3⁄8
insh
ank)
Ope
nPu
rcha
seB
X(5
EA
)Fo
rus
ew
ith2
to3
inD
radi
albr
istle
disc
sst
acke
dfr
om1⁄8
to½
inW
.
TO 1-1-691
B-9
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
PN99
1(3
⁄8in
shan
k)O
pen
Purc
hase
BX
(5E
A)
For
use
with
2to
3in
Dra
dial
bris
tledi
scs
stac
ked
from
¾in
to1
inW
.PN
933
(2in
L;
¼in
shan
kw
/1in
Dw
ashe
r)34
60-0
1-04
4-26
26E
AFo
rus
ew
ith2
to3
inD
abra
sive
disc
s.PN
934
(31/
16in
L;
¼in
shan
kw
/2½
inD
was
her)
3460
-00-
150-
7164
EA
For
use
with
3to
6in
Dab
rasi
vedi
scs.
PN93
5,Sp
litM
ini
Man
-dr
el(2
inL
;¼
insh
ank)
3460
-00-
150-
7163
EA
For
use
with
1in
Wx
1½
inL
piec
esof
abra
sive
mat
eria
lto
fitin
totig
htar
eas
for
corr
osio
nre
-m
oval
.42
Rol
ocT
MD
isc
Pad
Hol
ders
for
In-
line
Bri
stle
Dis
cs(I
tem
No.
45)
and
Rol
ocT
MC
oate
dA
bras
ive
Dis
cs(I
tem
No.
46)
3MC
o.,
CA
GE
Cod
e#2
8124
Com
mer
cial
Item
sU
sed
toho
ldR
oloc
TM
in-
line
bris
tledi
scs
and
coat
edab
rasi
vedi
scs
for
inst
alla
tion
onei
ther
in-
line
orri
ght
angl
edr
illm
otor
s.
PN05
1144
-451
01(1
inD
Hol
der)
Ope
nPu
rcha
seB
X(5
EA
)
PN05
1144
-450
95-4
(2in
DH
olde
r)O
pen
Purc
hase
BX
(5E
A)
PN05
1144
-450
92-3
(3in
DH
olde
r)O
pen
Purc
hase
BX
(5E
A)
PN05
1144
-451
79-1
(4in
DH
olde
r)O
pen
Purc
hase
BX
(5E
A)
PN05
1144
-451
02-9
(¼in
Dth
read
edsh
aft)
Ope
nPu
rcha
seE
A
43W
heel
,Fl
apB
rush
,A
bras
ive
(Non
-W
oven
Nyl
onFl
aps
with
Alu
mi-
num
Oxi
deA
bra-
sive
;M
aroo
nin
Col
or)
(6in
Dx
1in
Wx
2in
arbo
rho
le)
3MC
o.,
CA
GE
Cod
e#2
8124
Com
mer
cial
Item
sR
emov
ing
mild
corr
osio
nfr
oman
dpo
lishi
ngof
sur-
face
s.A
lso
for
mec
hani
cal
rem
oval
and
feat
heri
ngof
pain
tsy
stem
s.M
axim
umop
erat
ing
spee
d(M
OS)
is34
00R
PM.
Use
don
PN93
4m
andr
el(I
tem
No.
41ab
ove)
.
PN5A
FN6X
1X2
(Fin
egr
it)53
45-0
0-15
1-79
36E
A
PN5A
MD
6X1X
2(M
e-di
umgr
it)53
45-0
0-15
7-97
90E
A
TO 1-1-691
B-10
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
44St
acka
ble
Rad
ial
Bri
stle
Dis
cs,
(Reg
alite
TM
/Alu
-m
inum
Oxi
de&
Cub
itron
Abr
a-si
ve)
3MC
o.,
CA
GE
Cod
e#2
8124
,3
inD
-M
an-
drel
Mou
nted
Com
mer
cial
Item
sR
emov
ing
mild
corr
osio
nan
dpo
lishi
ngsu
rfac
esan
dde
-bur
ring
.Als
ofo
rm
e-ch
anic
alre
mov
alof
cure
dse
alan
ts,
adhe
sive
s,pa
ints
,an
dfe
athe
ring
ofpa
int
syst
ems.
Use
with
adr
illan
da
#934
,99
0,or
991
man
drel
,as
appr
opri
ate.
Can
beus
edto
reac
hin
tode
epde
pres
sion
san
dca
vi-
ties.
Can
beus
edon
in-
line
orri
ght
angl
edr
illm
otor
s.T
heM
OS
is25
,000
RPM
.
PN04
8011
-242
79-8
(Gra
de50
-G
reen
Col
or)
Ope
nPu
rcha
seC
S(4
0E
A)
PN04
8011
-242
80-4
(Gra
de80
-Y
ello
wC
olor
)O
pen
Purc
hase
CS
(40
EA
)
PN04
8011
-242
81-1
(Gra
de12
0-
Whi
teC
olor
)O
pen
Purc
hase
CS
(40
EA
)
PN05
1131
-075
44-3
(Gra
de12
0-
Whi
teC
olor
;T
hick
Bri
stle
s)
3460
-01-
509-
1789
CS
(40
EA
)
Rol
ocT
MD
isc
Pad
Hol
der
Mou
nted
,PN
0480
11-
2427
6-7
(Gra
de50
-G
reen
Col
or)
Ope
nPu
rcha
seS
(40
EA
)
PN04
8011
-242
77-4
(Gra
de80
-Y
ello
wC
olor
)O
pen
Purc
hase
CS
(40
EA
)
PN04
8011
-242
78-1
(Gra
de12
0-
Whi
teC
olor
)O
pen
Purc
hase
CS
(40
EA
)
Rol
ocT
MD
isc
Pad
Hol
der
for
thes
eR
adia
lB
rist
leD
iscs
,PN
0511
44-
4510
1-2
Ope
nPu
rcha
seB
X(5
EA
)
TO 1-1-691
B-11
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
45R
oloc
TM
In-l
ine
Bri
stle
Dis
cs(R
e-ga
liteR
oloc
TM
/A
lum
inum
Oxi
de&
Cub
itron
Abr
a-si
ve)
3MC
o.,
CA
GE
Cod
e#2
8124
,1
inD
w/
5/ 8
inL
bris
tles
Com
mer
cial
Item
sR
emov
ing
mild
corr
osio
nan
dpo
lishi
ngsu
rfac
esan
dde
-bur
ring
.Als
ofo
rm
e-ch
anic
alre
mov
alof
cure
dse
alan
ts,
adhe
sive
s,an
dpa
ints
and
feat
heri
ngof
pain
tsy
stem
s.C
anbe
used
onin
line
orri
ght
angl
edr
illm
otor
saf
ter
mou
ntin
gon
anap
prop
ri-
ate
Rol
ocT
Mdi
scpa
dho
lder
(Ite
mN
o.42
).T
hem
axim
umop
erat
ing
spee
d(M
OS)
depe
nds
onth
edi
amet
erof
the
disc
.
PN04
8011
-186
98-6
(Gra
de50
-G
reen
Col
or)
Ope
nPu
rcha
seC
S(8
0E
A)
PN04
8011
-187
06-8
(Gra
de80
-Y
ello
wC
olor
)O
pen
Purc
hase
CS
(80
EA
)
PN04
8011
-187
10-5
(Gra
de12
0-
Whi
teC
olor
)2
inD
w/5
/ 8in
Lbr
istle
s
Ope
nPu
rcha
seC
S(4
0E
A)
PN04
8011
-187
30-3
(Gra
de50
-G
reen
Col
or)
Ope
nPu
rcha
seC
S(4
0E
A)
PN04
8011
-187
32-7
(Gra
de80
-Y
ello
wC
olor
)53
45-0
1-43
2-30
32C
S(4
0E
A)
PN04
8011
-187
33-4
(Gra
de12
0-
Whi
teC
olor
)3
inD
w/5
/ 8in
Lbr
istle
s
3460
-01-
509-
1806
PN04
8011
-187
34-1
(Gra
de50
-G
reen
Col
or)
Ope
nPu
rcha
seC
S(4
0E
A)
PN04
8011
-187
36-5
(Gra
de80
-Y
ello
wC
olor
)O
pen
Purc
hase
CS
(40
EA
)
PN04
8011
-187
37-2
(Gra
de12
0-
Whi
teC
olor
)34
60-0
1-50
9-18
29C
S(4
0E
A)
TO 1-1-691
B-12
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
46R
oloc
TM
Coa
ted
Abr
asiv
eD
iscs
(Reg
alite
TM
/Alu
-m
inum
Oxi
de&
Cub
itron
Abr
a-si
ve)
and
Nyl
onM
atD
iscs
(Alu
-m
inum
Oxi
deA
bras
ive)
(for
Use
with
Item
No.
42)
3MC
o.,
CA
GE
Cod
e#2
8124
Com
mer
cial
Item
sFo
rre
mov
alof
mod
erat
eto
seve
reco
rros
ion
from
thic
kcr
oss
sect
ion
alum
i-nu
m,
stee
l,an
dm
agne
-si
umst
ruct
ures
whe
nm
ount
edon
Item
No.
42di
scpa
dho
lder
san
din
-st
alle
don
eith
erin
-lin
eor
righ
tan
gle
drill
mot
ors.
Use
ofth
ese
abra
sive
disc
ssh
ould
befo
llow
edby
smoo
thin
gou
tth
ear
eaw
itha
less
aggr
essi
veab
rasi
vedi
scsu
chas
anIt
emN
o.47
surf
ace
con-
ditio
ning
disc
(ver
yfin
egr
it).
Gra
de-
80gr
itPN
0511
44-1
4661
-1(2
inD
disc
)53
45-0
1-42
0-14
57C
S(2
00E
A)
PN-0
5114
4-76
634-
5(3
inD
disc
)O
pen
Purc
hase
CS
(200
EA
)
PN05
1144
-836
93-2
(4in
Ddi
sc)
Ope
nPu
rcha
seC
S(1
00E
A)
Gra
de-
100
grit
PN05
1144
-805
08-2
(2in
Ddi
sc)
Ope
nPu
rcha
seC
S(2
00E
A)
PN05
1144
-805
09-9
(3in
Ddi
sc)
Ope
nPu
rcha
seC
S(2
00E
A)
PN05
1144
-836
94-9
(4in
Ddi
sc)
Ope
nPu
rcha
seC
S(1
00E
A)
Gra
de-
120
grit
PN05
1144
-805
12-9
(2in
Ddi
sc)
5345
-01-
420-
1453
CS
(200
EA
)
PN05
1144
-805
13-6
(3in
Ddi
sc)
Ope
nPu
rcha
seC
S(2
00E
A)
PN05
1144
-836
95-6
(4in
Ddi
sc)
Ope
nPu
rcha
seC
S(1
00E
A)
Ver
yFi
neG
rit
(Blu
eC
olor
)PN
0480
11-0
5523
(2in
D-S
cotc
hB
rite
Dis
c)53
45-0
1-36
7-76
80C
S(2
00E
A)
PN04
8011
-055
30(3
inD
-Sco
tch
Bri
teD
isc)
5345
-01-
397-
5253
CS
(100
EA
)
TO 1-1-691
B-13
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
47Su
rfac
eC
ondi
tion-
ing
Dis
cs,A
lum
i-nu
mO
xide
(for
Use
with
Item
No.
39)
3MC
o.,
CA
GE
Cod
e#2
8124
Com
mer
cial
Item
sC
orro
sion
rem
oval
and
sur-
face
prep
arat
ion.
The
disc
spr
oduc
em
inim
alm
etal
/su
bstr
ate
rem
oval
.T
hey
perf
orm
best
onri
ght
angl
ety
pedr
illm
otor
sbu
tca
nbe
used
succ
essf
ully
onin
-lin
edr
illm
otor
s.D
iscs
are
mou
nted
onth
eap
prop
riat
esi
zed
disc
pad
hold
er(I
tem
No.
39),
whi
chis
then
mou
nted
into
eith
eran
in-l
ine
ora
righ
tan
gle
drill
mot
or.
Ver
yFi
neG
rit
(Blu
eC
olor
)PN
0480
11-0
4T75
-6(1
½in
D)
Ope
nPu
rcha
seC
S(2
00E
A)
PN04
8011
-04T
77-0
(3in
D)
Ope
nPu
rcha
seC
S(1
00E
A)
PN04
8011
-042
78-7
(4in
D)
Ope
nPu
rcha
seC
S(1
00E
A)
PN04
8011
-043
03-6
(5in
D)
Ope
nPu
rcha
seC
S(5
0E
A)
Med
ium
Gri
t(M
aroo
nC
olor
)PN
0480
11-0
4122
-3(1
½in
D)
Ope
nPu
rcha
seC
S(2
00E
A)
PN04
8011
-074
59-7
(2in
D)
Ope
nPu
rcha
seC
S(2
00E
A)
PN04
8011
-041
24-7
(3in
D)
Ope
nPu
rcha
seC
S(1
00E
A)
PN04
8011
-074
51-1
(4in
D)
Ope
nPu
rcha
seC
S(1
00E
A)
PN04
8011
-006
43-7
(5in
D)
Ope
nPu
rcha
seC
S(5
0E
A)
48C
OM
BI-
SW
heel
with
Spin
dle
Mou
nt,A
lum
i-nu
mO
xide
,M
a-ro
onC
olor
(3in
Dx
1¾
inW
w/¼
inD
shan
k)
3MC
o.,
CA
GE
Cod
e#2
8124
,12
0gr
it,PN
0511
44-8
0678
Ope
nPu
rcha
seE
AC
ombi
natio
nof
alum
inum
oxid
eco
ated
abra
sive
and
non-
wov
enny
lon
mat
eria
lus
edfo
rfin
ishi
ng,
blen
d-in
g,an
dre
mov
ing
light
tom
ediu
mco
rros
ion.
MO
Sis
8000
RPM
.
180
grit,
PN05
1144
-807
99O
pen
Purc
hase
EA
TO 1-1-691
B-14
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
49A
bras
ive
Whe
els,
Non
-Wov
enN
y-lo
n,R
esin
Rei
n-fo
rced
(Alu
mi-
num
Oxi
deA
bras
ive)
A-A
-592
92(s
uper
sede
sM
IL-W
-813
19),
Type
I,C
lass
2(L
amin
ated
)G
rade
C(M
ediu
m)
-15
0gr
it(3
inD
x¾
inW
on¼
inD
shaf
t)
5345
-00-
732-
9989
EA
Rem
ovin
gm
ediu
mto
seve
reco
rros
ion
(e.g
.in
terg
ranu
-la
r,ex
folia
tion)
from
thic
km
ater
ials
.
Gra
deA
(Ver
yFi
ne)
-28
0gr
it(2
inD
x½
inW
on¼
inD
shaf
t)
5345
-00-
935-
7869
EA
The
sew
heel
sar
eve
ryag
gres
sive
and
will
re-
mov
em
etal
subs
trat
eas
wel
las
corr
osio
npr
oduc
ts.
Gra
deB
(Fin
e)-
180
Gri
t(6
inD
x¾
inW
with
½in
arbo
rho
le)
3460
-01-
479-
5941
EA
50A
bras
ive
Dis
kK
it(C
ompo
site
Mat
e-ri
alR
epai
r)
PN65
001,
CA
GE
Cod
e#0
0179
5345
-01-
015-
1419
KT
For
use
inre
pair
ofco
mpo
s-ite
and
hone
ycom
bm
ater
i-al
sO
NLY
.C
omes
with
3di
scho
lder
s(1
in,
2in
,an
d3
inD
size
s)an
d15
0di
scs
ofas
sort
edgr
its(5
0in
each
size
).
TO 1-1-691
B-15
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
51Fi
les,
Rot
ary,
Con
eSh
ape,
Hig
hSp
eed
Stee
lor
Tun
gste
nC
arbi
de
A-A
-511
76,
Type
II(T
ung-
sten
Car
bide
)St
yle
A(R
Hsp
iral
flute
)C
lass
B(M
ediu
m),
Size
5(¼
inD
x½
inL
)
3455
-00-
293-
3560
EA
Rem
ovin
gse
vere
corr
osio
n(e
.g.
inte
rgra
nula
ran
dex
folia
tion)
and
unde
rly-
ing
met
al;
atta
chto
ast
raig
htin
-lin
epn
eum
atic
drill
.St
yle
B(R
Hsp
iral
flute
w/c
hip
brea
ker)
,C
lass
C(F
ine)
,Si
ze6
(¼in
Dx
¾in
L)
3455
-00-
293-
3559
EA
Rot
ary
files
are
ex-
trem
ely
aggr
essi
veto
ols
and
can
easi
lyre
mov
eto
om
uch
met
alsu
b-st
rate
.Pa
yst
rict
atte
n-tio
nan
dta
keex
tra
care
whe
nus
ing
thes
eto
ols.
Styl
eA
,C
lass
C,
Size
7(¼
inD
x1
inL
)34
55-0
0-29
3-35
61E
A
52A
ircr
aftA
dhes
ive
and
Dec
alR
e-m
oval
Dis
c(A
AD
R),
Non
-A
bras
ive
3MC
o.,
CA
GE
Cod
e#5
2152
Com
mer
cial
Item
sU
sed
ona
pneu
mat
icdr
illto
rem
ove
adhe
sive
s,se
al-
ants
,de
cals
,gr
aphi
cs,
vi-
nyl
stri
ppin
gta
pes,
doub
le-s
ided
mol
ding
tape
s,an
dle
adin
ged
geta
pes
with
out
rem
ovin
g/da
mag
ing
the
unde
rcoa
t-in
gs.
Rec
omm
ende
dop
er-
atin
gsp
eed
is26
00R
PM;
dono
tex
ceed
4000
RPM
.
PN05
1131
-074
98(6
inD
x5⁄8
inW
onR
oloc
TM
Hol
der
w/3
⁄8in
Dsh
ank)
3460
-01-
447-
8021
CS
(5E
AD
iscs
w/1
Hol
der)
PN04
8011
-241
05-0
(1E
A2
in,
3in
,4,
5,6
inD
x5⁄8
inW
Dis
cw
/1E
AR
oloc
TM
Hol
der
w/3
⁄8in
Dsh
ank)
Ope
nPu
rcha
seC
S(5
EA
Dis
csw
/1H
olde
r)N
OT
E
Do
not
use
onac
rylic
lacq
uer
pain
tsan
dpo
ly-
carb
onat
eor
acry
licpl
astic
s(c
anop
ies,
win
-do
ws,
and
win
dscr
eens
).
TO 1-1-691
B-16
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
53Se
alan
t(M
astic
)R
emov
alK
itsK
ell-
Stro
mTo
olC
o.In
c.,
CA
GE
Cod
e#7
5245
Com
mer
cial
Item
sU
sed
tore
mov
ecu
red
seal
-an
tth
atov
erco
ats
fast
ener
patte
rns
orfil
let
seal
sat
stru
ctur
eed
ges
with
shar
pene
dpl
astic
and/
orst
eel
blad
esm
ount
edin
apn
eum
atic
pow
ered
vibr
a-to
ryto
olor
am
anua
lha
ndhe
ldsu
ppor
tha
ndle
.C
anal
sobe
used
tore
mov
ean
ti-sk
idm
ater
ials
from
airc
raft
floor
s/de
cks.
Pneu
mat
icV
ibro
Gun
Seal
ant
Re-
mov
alK
it-
Cas
eC
onta
inin
g1
Vi-
bro
Gun
with
Air
Hos
e,B
lade
Shar
pene
rw
ithA
ggre
gate
Dis
can
dV
acuu
m,
Ex-
tra
Dis
c(P
NO
Z70
05)
and
Vac
uum
Bag
s(P
NO
Z70
04),
6E
A1
inW
(PN
OZ
7001
)&
2E
A½
inW
(PN
OZ
7002
)R
igid
Plas
ticB
lade
s,&
1E
A2
inW
(PN
OZ
7003
)Fl
exib
leSt
eel
Bla
de
PNO
Z70
00(V
ibro
Gun
Seal
ant
Rem
oval
Kit)
4920
-01-
500-
8087
EA
PNO
Z70
06(V
ibro
Gun
only
)49
20-0
1-50
0-80
84E
A
PNO
Z70
07(H
and
Type
Seal
ant
Rem
oval
Kit)
4920
-01-
500-
8090
EA
TO 1-1-691
B-17
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
Han
dTy
peSe
alan
tR
emov
alK
it-
Cas
eC
onta
inin
g1
EA
Padd
edPa
lmSu
ppor
tH
andl
e(P
NO
Z70
08),
6E
A1
inW
(PN
OZ
7001
),3
EA
½in
W(P
NO
Z70
02),
3E
A1
½in
W(P
NO
Z70
10),
&3
EA
1in
W(B
ut-
ton
Hea
dR
ivet
Ada
ptab
le)
Rig
idPl
astic
Bla
des,
2E
ASh
arpe
ning
Ston
es(P
NO
Z70
09),
&2
EA
Smal
lC
lean
-in
gB
rush
es
Ant
iSt
atic
Air
Hos
es,
PNO
Z70
13(5
0ft
L)
Ope
nPu
rcha
seE
A
PNO
Z70
14(1
00ft
L)
Ope
nPu
rcha
seE
AR
epla
cem
ent
part
s-
use
PN’s
atle
ftto
orde
rO
pen
Purc
hase
TO 1-1-691
B-18
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
54Se
alan
tR
emov
alTo
ols
(Dri
llM
o-to
rM
ount
edSR
Cut
ters
&D
iscs
)
3MC
o.,
CA
GE
Cod
e#7
6381
Com
mer
cial
Item
sT
hese
plas
ticcu
tters
and
smal
lbr
istle
disc
sar
epa
r-tic
ular
lyus
eful
for
re-
mov
alof
seal
ant
coat
ings
onan
dar
ound
prot
rudi
ngfa
sten
ers
and
lap
type
seam
s.T
hey
prov
ide
ef-
fect
ive
seal
ant
rem
oval
whi
lem
inim
izin
gco
n-ta
min
atio
nof
the
sur-
roun
ding
area
and
the
sub-
sequ
ent
requ
ired
clea
nup
.
PN61
-500
1-75
76-7
(#8
SRC
utte
r-
1in
D)
3455
-01-
509-
1769
BX
(40
EA
)
PN61
-500
1-75
77-5
(#3
SRR
otar
yC
utte
r)34
55-0
1-50
9-17
79B
X(4
0E
A)
PN61
-500
1-75
78-3
(#2
inSR
Rad
ial
Bri
stle
Dis
c)34
60-0
1-50
9-17
94B
X(4
0E
A)
PN61
-500
1-75
79-1
(#3
inSR
Rad
ial
Bri
stle
Dis
c)34
60-0
1-50
9-17
91B
X(4
0E
A)
PN61
-500
0-78
16-9
(Ro-
locT
MPa
d&
#1Pl
astic
Hol
der)
3460
-01-
509-
1784
BX
(5E
A)
PN61
-500
0-74
12-7
(Ro-
locT
MPa
d&
#7Pl
astic
Red
But
ton
for
Hol
der)
3460
-01-
509-
1812
BX
(5E
A)
PN61
-500
0-73
34-3
(#99
0M
andr
el)
3460
-01-
493-
7924
BX
(5E
A)
Env
isio
nPn
eum
atic
Seal
ant
Rem
oval
Kit
(Inc
lude
s:1
EA
Inge
rsol
l-R
and
1000
RPM
Rig
htA
ngle
Dri
ve,
¼in
Thr
eade
dC
huck
Pneu
mat
icD
rill
Mot
or;
1T
ube
with
5E
A#8
SRC
utte
rs;
and
1T
ube
with
5E
A#3
SRC
utte
rs
PNQ
A08
59D
-1,
CA
GE
Cod
e#2
A17
851
30-0
1-51
4-08
53K
it
Aer
owin
gR
apid
Des
ealin
gSy
stem
(RD
S)
RD
S001
6635
-01-
572-
5251
EA
TO 1-1-691
Change 2 B-19
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
55O
ptic
alD
epth
Mi-
crom
eter
Kit
(Dig
ital
Rea
dout
)PR
EFE
RR
ED
TO
OL
PN84
00K
,C
AG
EC
ode
#659
5666
50-0
1-22
0-89
42E
AIn
spec
tion
ofan
dde
pth,
wid
th,
and
leng
thm
ea-
sure
men
tsof
corr
osio
nda
mag
ean
dco
rros
ion
grin
dou
tar
eas.
56O
ptic
alD
epth
Mi-
crom
eter
Kit
(Ana
log,
Me-
chan
ical
Rea
dout
)A
LTE
RN
AT
ET
OO
L
PN96
6A1,
CA
GE
Cod
e#9
2541
6650
-00-
831-
5532
EA
Insp
ectio
nof
and
dept
h,w
idth
,an
dle
ngth
mea
-su
rem
ents
ofco
rros
ion
dam
age
and
corr
osio
ngr
ind
out
area
s.
57D
epth
Gau
ge,
Nee
dle
Poin
tD
ial
Indi
cato
r
PN65
2728
1,C
AG
EC
ode
#701
6852
10-0
0-71
0-43
59E
APr
ecis
ion
mea
sure
men
tof
corr
osio
nda
mag
ean
dco
r-ro
sion
grin
dou
tde
pth
with
ina
rang
eof
0.0
into
0.12
5in
.58
Mag
nify
ing
Gla
ss,
Fold
ing
Pock
etT
ripl
eL
ens
Type
(Cir
cula
rsh
ape
-½
inD
)
PN81
-23-
95,
CA
GE
Cod
e#0
6175
6650
-00-
530-
1880
EA
Insp
ectio
nof
corr
osio
n.M
agni
fyin
gpo
wer
ofth
ele
nses
are
5X,
7X,
and,
10X
.L
ense
spi
vot
for
ei-
ther
sing
leor
com
bina
tion
use.
59In
spec
tion
Mir
ror
GG
G-M
-350
,Ty
peII
(Plu
nger
Act
ivat
ed),
Cla
ss3
(Rec
tang
ular
)Si
ze1
(1½
inL
x1
¼in
W)
5120
-00-
278-
9926
EA
Aid
for
insp
ectin
gha
rdto
see
area
sfo
rco
rros
ion.
Size
2(2
inL
x1
¾in
W)
5120
-00-
618-
6902
EA
60W
ritin
gIn
stru
men
t,A
ircr
aft
Mar
king
(Non
-cor
rosi
ve)
A-A
-87,
Red
7510
-00-
174-
3205
DZ
Iden
tifica
tion/
mar
king
ofco
rrod
edar
eas.
A-A
-87,
Whi
te75
10-0
0-24
0-15
25D
ZA
-A-8
7,B
lack
7510
-01-
240-
1526
DZ
A-A
-87,
Yel
low
7510
-01-
264-
4612
DZ
A-A
-87,
Blu
e75
10-0
1-43
6-52
10D
ZPN
SAN
1340
1,C
AG
EC
ode
#86
874
7520
-01-
478-
9942
EA
PN16
001,
CA
GE
Cod
e#
8687
4,05
360
7520
-01-
004-
7846
DZ
TO 1-1-691
B-20 Change 18
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
61B
rush
,Pl
ater
’sH
and
Type
(Cur
ved
Han
dle
Styl
e)
A-A
-311
8(s
uper
sede
sH
-B-1
78),
Type
I,C
lass
2
7920
-00-
244-
7431
EA
A13
inov
eral
lle
ngth
brus
hw
itha
5¼
inL
x1
¼in
Wbr
ush
area
havi
ng4
row
sof
1in
Lbr
istle
sus
edto
rem
ove
loos
eco
r-ro
sion
prod
ucts
and
flak-
ing
pain
tan
dto
appl
ycl
eani
ngso
lven
tsan
dco
mpo
unds
.
TO 1-1-691
Change 18 B-20.1/(B-20.2 blank)
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
62H
and
Bru
sh,
Woo
den
Han
dle,
(Sta
inle
ssSt
eel
Fill)
PN15
SS,
CA
GE
Cod
e#1
7987
7920
-00-
900-
3577
EA
A7
¾in
over
all
leng
thbr
ush
with
abr
ush
area
of7/
16in
used
tore
mov
eco
rros
ion
from
alum
inum
allo
ysu
rfac
es.
63Fl
ashl
ight
,Adj
ust-
able
Bea
m,
Met
al/P
last
icC
ase,
Non
-Re-
char
geab
le
PN10
1-00
0-00
2,C
AG
EC
ode
#061
3462
30-0
1-24
7-75
49E
AU
sefo
rco
rros
ion
insp
ectio
n.
Rec
harg
eabl
ePN
106-
000-
003,
CA
GE
Cod
e#0
6134
6230
-01-
152-
5952
EA
64Sh
ears
and
Scis
sors
GG
G-S
-278
Stra
ight
Shea
rs(9
inL
)51
10-0
0-16
1-69
12E
AC
uttin
gta
pes,
chee
secl
oth,
mas
king
mat
eria
ls,
elec
tri-
cal
wir
es,
etc.
Ele
ctri
cian
’sSc
isso
rs(5
inL
w/w
ire
Stri
pN
otch
es)
5110
-00-
212-
7455
EA
65Se
para
tors
,Air
and
Wat
er,
Com
-pr
esse
dA
ir(A
irR
egul
ator
Ass
em-
bly)
A-A
-594
36(s
uper
sede
sM
IL-S
-129
28),
Cla
ss1
(1R
egul
ator
,2
Out
lets
)
4940
-00-
242-
4100
EA
Wal
l-m
ount
edse
para
tors
desi
gned
tore
mov
eoi
l,w
ater
,an
dfo
reig
npa
r-tic
les
from
com
pres
sed
air,
and
tore
gula
teth
ede
liver
ypr
essu
reof
air
used
for
spra
ypa
int
guns
and
pneu
mat
icto
ols.
Cla
ss2
(2R
egul
ator
s,4
Out
lets
)49
40-0
0-24
2-41
01E
A
66Pa
int
Bru
sh,
Flat
,M
etal
Bou
nd,
Synt
hetic
Fibe
r
H-B
-420
,Ty
peII
,G
rade
B,
1in
W80
20-0
0-26
3-38
66E
AU
sed
toap
ply
brus
habl
ese
alan
tsan
dad
hesi
ves.
2in
W80
20-0
0-55
0-83
59E
A67
Mix
ers,
Liq
uid,
Re-
volv
ing
Shaf
tan
dA
gita
tor
Type
s
A-A
-594
33(s
uper
sede
sM
IL-M
-307
0),
Type
I-
Rev
olvi
ngSh
aft,
Cla
ss1
-½
hp(1
15V
)E
lect
ric
Mot
or
4940
-00-
221-
1707
EA
Use
dto
mix
two
com
pone
ntse
alan
tsbe
fore
appl
ica-
tion.
TO 1-1-691
B-21
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
68Sp
ray
Kit,
Self
Pres
suri
zed
(Kit
Con
tain
s4
EA
Spra
yD
evic
es,
20E
AD
ipT
ubes
,4
EA
Jar
Con
tain
-er
sfo
rM
ater
ials
,an
d10
EA
cans
ofN
on-C
lass
1O
DS
Prop
ella
nt)
SAE
AS2
2805
(sup
erse
des
MIL
-S-2
2805
),M
odel
8011
Pow
erPa
k
4940
-00-
803-
6444
KT
Use
for
appl
ying
pain
ts,
degr
easi
ngco
mpo
unds
,pr
eser
vativ
es(C
PC’s
),an
dot
her
touc
h-up
mat
eria
lsw
hen
othe
rsp
ray
appl
ica-
tion
equi
pmen
tis
impr
ac-
tical
.
69Ps
ychr
omet
erA
-A-2
579
Slin
g,Po
cket
Type
6685
-00-
826-
1662
EA
Mea
sure
men
tof
rela
tive
hum
idity
and
dew
poin
tto
assi
stin
dete
rmin
atio
nof
cure
time
for
seal
ants
,ad
hesi
ves,
and
pain
ts.
Psyc
hro-
Dyn
e,PN
WE
-22
014,
CA
GE
Cod
e#6
6420
6685
-01-
263-
8370
EA
SAFE
TY
EQ
UIP
ME
NT
(Ref
erto
Figu
reB
-1th
roug
hFi
gure
B-3
atth
een
dof
this
appe
ndix
for
illus
trat
ion
ofso
me
item
sin
this
sect
ion)
.
NO
TE
Con
sult
loca
lSa
fety
and
Bio
envi
ronm
enta
lE
ngin
eeri
ngO
ffice
sfo
rPe
rson
alPr
otec
tive
Equ
ipm
ent
(PPE
)re
quir
emen
ts.
The
seof
fices
have
auth
ority
tosu
bstit
ute
equi
vale
ntsa
fety
equi
pmen
tw
hen
appr
opri
ate.
70Pa
rtic
ulat
eR
espi
ra-
tor
(½Fa
cepi
ece
Mas
k),
Dis
pos-
able
Type
3MC
o.,
CA
GE
Cod
e#5
0378
,PN
8511
4240
-01-
247-
2348
BX
(80
EA
)Pe
rson
nel
prot
ectio
nfr
omin
hala
tion
ofdu
stan
dpa
r-tic
ulat
esdu
ring
light
sand
-in
gan
dgr
indi
ngop
era-
tions
.71
Full
Face
piec
eR
es-
pira
tor,
Air
Filte
r-in
g(w
/oC
ar-
trid
ges
orR
etai
ners
)
3MC
o.,
CA
GE
Cod
e#5
0378
,PN
7800
S-S
(Sm
all)
4240
-01-
314-
2780
EA
Pers
onne
lpr
otec
tion
from
inha
latio
nof
orga
nic
va-
pors
,du
st,
part
icul
ates
,an
dpa
int
spra
ysin
non-
confi
ned
area
sdu
ring
spra
ying
,sa
ndin
g,an
dgr
indi
ngop
erat
ions
.
PN78
00S-
M(M
ediu
m)
4240
-01-
342-
5239
EA
PN78
00S-
L(L
arge
)42
40-0
1-30
1-32
00E
A
TO 1-1-691
B-22
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
72Fu
llFa
cepi
ece
Res
-pi
rato
r,A
irFi
lter-
ing
(w/o
Car
-tr
idge
sor
Ret
aine
rs)
3MC
o.,
CA
GE
Cod
e#5
0378
,PN
6700
(Sm
all)
4240
-01-
454-
8531
BX
(4E
A)
Pers
onne
lpr
otec
tion
from
inha
latio
nof
orga
nic
va-
pors
,du
st,
part
icul
ates
,an
dpa
int
spra
ysin
non-
confi
ned
area
sdu
ring
spra
ying
,sa
ndin
g,an
dgr
indi
ngop
erat
ions
.
PN68
00(M
ediu
m)
4240
-01-
454-
8535
BX
(4E
A)
PN69
00(L
arge
)42
40-0
1-45
4-85
38B
X(4
EA
)
73H
alf
Face
piec
eR
es-
pira
tor,
Air
Filte
r-in
g(w
/oC
ar-
trid
ges
orR
etai
ners
)
3MC
o.,
CA
GE
Cod
e#5
0378
,PN
6100
(Sm
all)
4240
-01-
342-
2852
BX
(24
EA
)Pe
rson
nel
prot
ectio
nfr
omin
hala
tion
ofor
gani
cva
-po
rs,
dust
,pa
rtic
ulat
es,
and
pain
tsp
rays
inno
n-co
nfine
dar
eas
duri
ngsp
rayi
ng,
sand
ing,
and
grin
ding
oper
atio
ns.
PN62
00(M
ediu
m)
4240
-01-
342-
2853
BX
(24
EA
)PN
6300
(Lar
ge)
4240
-01-
342-
2854
BX
(24
EA
)
74Fi
lter
Car
trid
ges
(Org
anic
Vap
or/
P100
Type
)
3MC
o.,
CA
GE
Cod
e#5
0378
,PN
6092
142
40-0
1-45
5-73
53B
X(6
0E
A)
For
use
with
3MC
o.ha
lfan
dfu
llfa
cepi
ece
(600
0&
7000
Seri
es)
resp
irat
ors.
75R
espi
rato
rL
ens
Ass
embl
yfo
r3M
Co.
Full
Face
-pi
ece
Res
pira
tors
(with
Plas
ticFi
lmC
over
s)
3MC
o.,
CA
GE
Cod
e#5
0378
,PN
7884
4240
-01-
247-
8929
BX
(5E
A)
Rep
lace
men
tle
nsfo
r78
00S
Seri
esre
spir
ator
s.PN
6898
Ope
nPu
rcha
seB
X(5
EA
)R
epla
cem
ent
lens
for
6000
Seri
esre
spir
ator
s.
76L
ens
Cov
ers
for
3MC
o.Fu
llFa
ce-
piec
eR
espi
rato
rs(P
eel-
Aw
ayPl
as-
ticFi
lm)
3MC
o.,
CA
GE
Cod
e#5
0378
,PN
7899
-25
4240
-01-
248-
4634
PK(1
00E
A)
Len
sco
vers
for
7800
SSe
-ri
esre
spir
ator
s.PN
7899
-100
4240
-01-
248-
6435
BX
(100
EA
)L
ens
cove
rsfo
r78
00S
Se-
ries
resp
irat
ors.
PN68
8542
40-0
1-45
5-27
87B
X(1
00E
A)
Len
sco
vers
for
6800
Seri
esre
spir
ator
s.77
Inha
latio
nV
alve
for
3MC
o.Fu
llFa
cepi
ece
Res
pi-
rato
rs
3MC
o.,
CA
GE
Cod
e#5
0378
,PN
7282
4240
-01-
248-
2607
BX
(200
EA
)R
epla
cem
ent
valv
esfo
r78
00S
Seri
esre
spir
ator
s.PN
6893
4240
-01-
455-
2811
BX
(200
EA
)R
epla
cem
ent
valv
esfo
r68
00Se
ries
resp
irat
ors.
78E
xhal
atio
nV
alve
for
3MC
o.Fu
llFa
cepi
ece
Res
pi-
rato
rs
3MC
o.,
CA
GE
Cod
e#5
0378
,PN
7283
4240
-01-
248-
2608
BX
(50
EA
)R
epla
cem
ent
valv
esfo
r78
00S
Seri
esre
spir
ator
s.PN
6889
4240
-01-
455-
2809
BX
(10
EA
)R
epla
cem
ent
valv
esor
6800
Seri
esre
spir
ator
s.
TO 1-1-691
B-23
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
79Ty
vekT
MSh
roud
for
3MC
o.Fu
llFa
cepi
ece
Res
pi-
rato
rs
3MC
o.,
CA
GE
Cod
e#5
0378
,PN
7915
-542
40-0
1-32
0-19
57PG
(5E
A)
Use
dw
ithfu
llfa
cepi
ece
resp
irat
ors
topr
otec
tth
ehe
adan
dne
ckfr
ompa
int-
ing
and/
orab
rasi
vebl
ast-
ing
over
spra
y.80
Spec
tacl
eK
itfo
r3M
Co.
Full
Face
piec
eR
espi
-ra
tors
3MC
o.,
CA
GE
Cod
e#5
0378
Con
sist
sof
fram
ean
dre
-ta
iner
clip
.PN
6878
4240
-01-
455-
2346
EA
For
use
on60
00Se
ries
full
face
piec
ere
spir
ator
s.PN
7925
4240
-01-
395-
4128
EA
For
use
with
pres
crip
tion
lens
esw
ith78
00S
Seri
esfu
llfa
cepi
ece
resp
irat
ors.
81R
espi
rato
rC
lean
ing
Wip
es(A
lcoh
ol-
Free
Tow
elet
tes)
3MC
o.,
CA
GE
Cod
e#5
0378
&O
T1L
6,PN
504
4240
-01-
372-
3078
BX
(100
EA
)H
ygie
nic
clea
ning
ofre
spi-
rato
rsan
dot
her
pers
onal
prot
ectiv
ege
ar/e
quip
men
t.65
10-0
1-39
7-43
39B
X(5
00E
A)
Do
not
use
shop
air
for
brea
thin
gor
asin
let
air
for
thes
ebr
eath
able
air
pum
ps.
Itco
ntai
nsoi
l,pa
rtic
ulat
es,
and
harm
ful
gase
s.R
ead
and
follo
weq
uipm
ent
inst
ruct
ions
tode
term
ine
the
max
imum
num
ber
ofai
rlin
esto
beus
edw
itha
sing
lepu
mp.
82Pu
mp/
Com
pres
sor,
Bre
atha
ble
Air
,Pn
eum
atic
(Air
Mot
or)
Dri
ven,
Port
able
Rhi
neA
ir,
Inc.
,C
AG
EC
ode
#585
01,
PNN
F-11
00su
pers
edes
PNN
F15-
3
4240
-01-
363-
4699
EA
Use
dto
supp
lybr
eath
able
air
toho
ods
and
full
face
-pi
ece
resp
irat
ors
for
abra
-si
vebl
astin
gan
dot
her
corr
osio
nre
mov
alop
era-
tions
,as
requ
ired
,an
dpa
intin
gop
erat
ions
.T
hese
smal
l,ai
rdr
iven
,po
rtab
leco
mpr
esso
rsar
eve
ryco
n-ve
nien
tas
they
may
beea
sily
tran
spor
ted
and
set
upal
mos
tan
ywhe
reto
supp
lybr
eath
able
air.
Bul
lard
Co.
,C
AG
EC
ode
#097
29,
PNA
DP-
16/
AD
P-20
4310
-01-
168-
7302
EA
TO 1-1-691
B-24
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
NO
TE
Use
MIL
-PR
F-32
033
oil
(NSN
9150
-00-
231-
6689
/1Q
TC
N)
orM
IL-H
-176
72hy
drau
licflu
id/1
0w
t.oi
leq
uiva
lent
(NSN
9150
-00-
985-
7231
/1Q
TC
N)
tofil
lin
-lin
eoi
ler
ofai
rm
otor
afte
rea
chus
e,as
requ
ired
,to
mai
ntai
nlu
bric
atio
nan
dpr
even
tm
otor
oxid
atio
n.
83R
epla
cem
ent
Filte
rC
artr
idge
sfo
rB
reat
habl
eA
irPu
mps
Rhi
neA
ir,
Inc.
,C
AG
EC
ode
#585
01,
PNC
F808
0
4240
-01-
084-
0921
BX
(10
EA
)R
epla
cem
ent
filte
rsfo
rus
ew
ithR
hine
Air
’sN
F-11
00an
dN
F15-
3pu
mps
.
84C
ompr
esse
dA
irIn
let
Hos
eA
s-se
mbl
y,½
inI
DH
ose
w/3
⁄8in
ID
Ori
fice
Fitti
ngs
Rhi
neA
ir,
Inc.
,C
AG
EC
ode
#585
01,
PNE
D13
13B
-50
(50
ftL
)
4240
-01-
251-
8159
EA
Use
don
lyfo
rsu
pply
ing
fres
h,br
eath
able
air
toth
eai
rm
otor
onth
ebr
eath
-ab
leai
rpu
mp
unit.
PNE
D13
13B
-100
(100
ftL
)42
40-0
1-25
1-81
60E
AT
hese
inle
tho
seas
sem
blie
sca
nbe
used
with
both
Rhi
neA
iran
dB
ulla
rdun
its.
85Q
uick
Dis
conn
ect
Fitti
ngs
for
Inle
tH
ose
CA
GE
Cod
e#7
3992
,3L
25(M
ale
Plug
)47
30-0
1-44
2-18
09E
AR
epla
cem
ent
fittin
gsfo
rth
eR
hine
Air
,PN
ED
1313
Bin
let
air
hose
asse
mbl
ies.
3R25
(Fem
ale
Cou
pler
)47
30-0
1-44
2-18
08E
A86
Out
let
Man
ifol
d,Q
uick
Dis
conn
ect
(Fem
ale
Cou
pler
Ass
embl
y)
Rhi
neA
ir,
Inc.
,C
AG
EC
ode
#585
01,
PNE
D-
06-4
30
Ope
nPu
rcha
seE
AC
onne
cts
resp
irat
orai
rho
seas
sem
blie
sto
the
brea
th-
able
air
pum
p.C
anbe
used
with
both
Rhi
neA
iran
dB
ulla
rdun
its.
87G
love
s,M
en’s
&W
omen
’s(W
ork
Cot
ton
Flan
nel;
Nat
ural
inC
olor
)
A-A
-166
5,St
yle
1(K
nit
Cuf
f/R
eg.)
8415
-00-
268-
8330
PRG
ener
alpu
rpos
epr
otec
tive
wor
kgl
oves
for
hand
pro-
tect
ion
duri
ngva
riou
sm
aint
enan
ceop
erat
ions
.St
yle
2(G
aunt
let/R
eg.)
8415
-00-
634-
5027
PRSt
yle
3(R
ever
sibl
ePa
lm/
Kni
tC
uff/
Lar
ge)
8415
-00-
559-
5613
PR
88G
love
s,C
loth
,V
i-ny
lD
ippe
d(B
lack
inC
olor
)
A-A
-503
70(s
uper
sede
sM
IL-G
-822
53),
Type
1(G
aunt
let/M
ediu
m)
8415
-00-
916-
2817
PRG
ener
alpu
rpos
elig
htdu
tyty
pech
emic
alan
doi
lpr
o-te
ctiv
egl
oves
used
for
hand
prot
ectio
ndu
ring
clea
ning
and
chem
ical
,so
lven
t,an
doi
l/pre
serv
a-tiv
eap
plic
atio
ns.
Rub
ber-
ized
for
bette
rgr
ip.
Type
1(G
aunt
let/L
arge
)84
15-0
0-91
6-28
18PR
Type
2(K
nit
Wri
st/U
nive
r-sa
lon
e-si
zefit
sal
l)84
15-0
0-93
5-28
33PR
TO 1-1-691
B-25
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
89G
love
s,To
xico
logi
-ca
lAge
nts,
Pro-
tect
ive
(Bla
ckin
Col
or)
MIL
-G-1
2223
,Ty
peII
(14
inG
aunt
let)
X-S
mal
l(8
)84
15-0
0-75
3-65
50PR
Hea
vydu
tyin
dust
rial
grad
esy
nthe
ticru
bber
glov
esus
edfo
rha
ndpr
otec
tion
whi
leha
ndlin
gso
lven
ts,
chem
ical
pain
tre
mov
ers,
pain
ts,
seal
ants
,or
othe
rm
ater
ials
whi
chm
aybe
inju
riou
sto
the
skin
.
Smal
l(9
)84
15-0
0-75
3-65
51PR
Med
ium
(10)
8415
-00-
753-
6552
PRN
OT
E
The
segl
oves
are
not
desi
gned
for
prot
ectio
nin
elec
tric
alap
plic
atio
nsor
chem
ical
war
fare
activ
ities
.
Lar
ge(1
1)84
15-0
0-75
3-65
53PR
X-L
arge
(12)
8415
-00-
753-
6554
PR
90G
love
s,C
hem
ical
and
Oil
Prot
ectiv
e(G
reen
inC
olor
)
MIL
-G-8
7066
(Gau
ntle
tC
uff;
Floc
kL
inin
g)X
X-
Smal
l(7
)
8415
-01-
147-
6263
PRSy
nthe
ticru
bber
glov
esw
itha
high
degr
eeof
abra
sion
resi
stan
cean
dre
sist
ance
toch
emic
als
such
asw
a-te
r,ga
solin
e,oi
ls,
alka
lis,
and
acid
s.T
hey
are
used
topr
otec
tth
eha
nds
dur-
ing
airc
raft
,m
issi
le,
and
equi
pmen
tw
ashi
ngop
era-
tions
.
X-S
mal
l(8
)84
15-0
1-14
7-95
40PR
Smal
l(9
)84
15-0
1-01
2-92
94PR
Med
ium
(10)
8415
-01-
013-
7382
PRL
arge
(11)
8415
-01-
013-
7384
PR
91G
love
s,D
ispo
sabl
e,N
itrile
Rub
ber,
Pre-
Pow
dere
d,A
mbi
dext
rous
(Lig
htB
lue
inC
olor
)
CA
GE
Cod
e#6
2538
&4X
954,
PN70
05S
(Sm
all)
8415
-01-
352-
6556
PG(2
0B
X/1
00E
A)
Gen
eral
purp
ose
prot
ectiv
ew
ear
for
the
hand
sdu
ring
vari
ous
clea
ning
and
cor-
rosi
ontr
eatm
ent
oper
a-tio
ns.
The
segl
oves
are
heav
ier
duty
and
have
bette
rre
sist
ance
toso
me
chem
ical
sth
anth
ela
tex
rubb
ergl
oves
(Ite
mN
o.92
).
PN70
05M
(Med
ium
)84
15-0
1-35
2-65
53PG
(20
BX
/100
EA
)PN
7005
L(L
arge
)84
15-0
1-35
2-65
54PG
(20
BX
/100
EA
)PN
7005
XL
(X-L
arge
)84
15-0
1-35
2-65
55PG
(20
BX
/100
EA
)
TO 1-1-691
B-26
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
92G
love
s,D
ispo
sabl
e,L
atex
Rub
ber,
Pre-
Pow
dere
d,A
mbi
dext
rous
(Nat
ural
inC
olor
)
A-A
-535
13,
Smal
l65
15-0
1-36
5-61
83PG
(100
EA
)G
ener
alpu
rpos
epr
otec
tive
wea
rfo
rth
eha
nds
duri
ngva
riou
scl
eani
ngan
dco
r-ro
sion
trea
tmen
top
era-
tions
.T
hese
glov
esar
elig
hter
duty
and
have
som
ewha
tle
ssre
sist
ance
toso
me
chem
ical
sth
anth
eni
trile
rubb
ergl
oves
(Ite
mN
o.91
).
Med
ium
6515
-01-
364-
8553
PG(1
00E
A)
Lar
ge65
15-0
1-36
4-85
54PG
(100
EA
)
93C
over
alls
,C
otto
n,H
ook-
Pile
Fas-
tene
rTa
pe(G
reen
inC
olor
)
MIL
-C-2
202,
Type
I(O
live
Gre
en)
Smal
l(4
2)84
05-0
0-13
1-65
07E
APr
otec
tive
clot
hing
for
cor-
rosi
onm
aint
enan
cean
din
spec
tion
pers
onne
l.D
e-si
gned
prim
arily
for
wea
rov
erre
gula
r/st
reet
clot
h-in
g.
Med
ium
(46)
8405
-00-
131-
6508
EA
Lar
ge(5
0)84
05-0
0-13
1-65
09E
AX
-Lar
ge(5
4)84
05-0
0-13
1-65
10E
AX
X-L
arge
(58)
8405
-00-
131-
6511
EA
94C
over
alls
,D
ispo
s-ab
le,
Gen
eral
Purp
ose
(Whi
tein
Col
or)
A-A
-503
58,
X-S
mal
l84
15-0
0-60
1-07
92E
APr
otec
tive
clot
hing
for
cor-
rosi
onm
aint
enan
cepe
r-so
nnel
topr
otec
tag
ains
tdi
rt,
grea
se,
pain
t,an
dlo
w-h
azar
dco
ntam
inan
ts.
The
yar
eon
e-pi
ece,
fron
top
enin
g(s
lide
type
clo-
sure
)co
vera
llsm
ade
offir
ere
sist
ant
and
wat
erre
pelle
ntm
ater
ials
,an
dth
eyar
ein
tend
edto
beth
row
naw
ayw
hen
dirt
y.
Smal
l84
15-0
0-60
1-07
93E
AM
ediu
m84
15-0
0-60
1-07
94E
AL
arge
8415
-00-
601-
0797
EA
X-L
arge
8415
-00-
601-
0801
EA
XX
-Lar
ge84
15-0
0-60
1-08
02E
A
95C
over
alls
,D
ispo
s-ab
le(W
hite
inC
olor
)
A-A
-551
96(s
uper
sede
sM
IL-C
-870
69),
Type
I(w
ithH
ood)
Smal
l/Me-
dium
8415
-01-
445-
6565
EA
Prot
ectiv
eol
efin
cove
ralls
with
anat
tach
edho
odha
ving
adr
awst
ring
clo-
sure
and
atta
ched
boot
ies
for
mai
nten
ance
pers
onne
lpe
rfor
min
gw
ork
arou
ndas
best
osm
ater
ials
orw
ithfib
ergl
ass
and
othe
rco
m-
posi
tem
ater
ials
.T
hey
are
inte
nded
tobe
thro
wn
away
afte
rus
e.
Lar
ge/X
-Lar
ge84
15-0
1-44
5-65
68E
AX
X-L
arge
8415
-01-
445-
6588
EA
TO 1-1-691
B-27
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
96T
rous
ers,
Wet
Wea
ther
(Gre
enin
Col
or)
MIL
-T-8
7099
(sup
erse
des
MIL
-O-2
2776
)X
X-
Smal
l
8405
-01-
276-
1532
PRW
ater
proo
fch
loro
pren
eru
b-be
rco
ated
nylo
ntw
illtr
ouse
rsfo
rus
ein
con-
junc
tion
with
aw
etw
eath
erpa
rka
(Ite
mN
o.97
),fo
rai
rcra
ft,
mis
sile
,an
deq
uipm
ent
mai
nte-
nanc
eop
erat
ions
for
per-
sonn
elpr
otec
tion
inw
etor
wet
/col
dco
nditi
ons.
X-S
mal
l84
05-0
1-27
6-15
33PR
Smal
l84
05-0
1-27
6-15
34PR
Med
ium
8405
-01-
276-
1535
PRL
arge
8405
-01-
276-
1536
PRX
-Lar
ge84
05-0
1-27
6-15
37PR
NO
TE
Com
mer
cial
Equ
ival
ent
Wet
Wea
ther
Gea
rca
nbe
use
prov
idin
glo
cal
bio-
envi
ronm
ent,
safe
tyan
dfir
efu
nctio
nsap
prov
al.
Tro
user
s,Im
prov
edW
etW
eath
er:
light
wei
ght
Bre
atha
ble
(Woo
dlan
dco
lor)
Non
-Spe
c/
SSN
C-I
CT
heIm
prov
edR
ain
Suit
(IR
S)is
mad
eof
Sym
pa-
Tex,
alig
htw
eigh
tbr
eath
-ab
le,
wat
erpr
oof
mat
eria
lm
ade
bySy
mpa
Tex
Tech
-no
logi
esG
mbH
.Sy
mpa
-Te
xis
any
lon
mat
eria
lth
atis
plia
ble
and
moi
s-tu
re-v
apor
-sem
i-pe
rme-
able
.It
resi
stex
tern
alw
a-te
rw
hile
allo
win
gpe
rspi
ratio
nor
othe
rm
ois-
ture
totr
ansf
erfr
omin
-si
deto
outs
ide,
ther
eby
keep
ing
the
wea
rer
dry
and
com
fort
able
.
XX
-SM
AL
L84
05-0
1-44
3-94
30E
AX
-SM
AL
L84
05-0
1-44
3-94
36E
ASM
AL
L84
05-0
1-44
3-94
49E
AM
ED
IUM
8405
-01-
443-
9487
EA
LA
RG
E84
05-0
1-44
3-94
88E
AX
-LA
RG
E84
05-0
1-44
3-94
93E
AX
X-L
AR
GE
8405
-01-
443-
9498
EA
Tro
user
s,Im
prov
edW
etW
eath
er:
light
wei
ght
Bre
atha
ble
(Uni
-ve
rsal
Cam
ou-
flage
colo
r)
Non
-Spe
c/
PD99
20T
heIR
Str
ouse
rsha
vea
draw
-str
ing
atth
ew
aist
,a
cent
erzi
pper
,pa
ssth
roug
hpo
cket
s,V
elcr
ocl
osur
esat
the
ankl
es,
and
long
leg
zipp
ers
for
easy
on-o
ff.
The
seat
and
knee
sar
ere
info
rced
.
XX
-SM
AL
L84
15-0
1-52
7-15
37E
AX
-SM
AL
L84
15-0
1-52
7-15
41E
ASM
AL
L84
15-0
1-52
7-15
45E
AM
ED
IUM
8415
-01-
527-
1551
EA
LA
RG
E84
15-0
1-52
7-15
55E
AX
-LA
RG
E84
15-0
1-52
7-15
60E
AX
X-L
AR
GE
8415
-01-
527-
1561
EA
TO 1-1-691
B-28 Change 8
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
Tro
user
s,Im
prov
edW
etW
eath
er:
light
wei
ght
Bre
atha
ble
(Woo
dlan
dco
lor)
Non
-Spe
c/
SSN
C-I
CT
heIR
Str
ouse
rsfo
rma
wat
erpr
oof
oute
rsh
ell
wor
nov
erot
her
clot
hing
and
gear
.It
islig
htw
eigh
tho
wev
er;
IRS
func
tions
stri
ctly
asa
rain
barr
ier,
offe
ring
little
prot
ectio
nfr
omth
eco
ld.
XX
-SM
AL
L84
05-0
1-44
3-94
30E
AX
-SM
AL
L84
05-0
1-44
3-94
36E
ASM
AL
L84
05-0
1-44
3-94
49E
AM
ED
IUM
8405
-01-
443-
9487
EA
LA
RG
E84
05-0
1-44
3-94
88E
AX
-LA
RG
E84
05-0
1-44
3-94
93E
AX
X-L
AR
GE
8405
-01-
443-
9498
EA
Tro
user
s,Im
prov
edW
etW
eath
er:
light
wei
ght
Bre
atha
ble
(Uni
-ve
rsal
Cam
ou-
flage
colo
r)
Non
-Spe
c/
PD99
20X
X-S
MA
LL
8415
-01-
527-
1537
EA
X-S
MA
LL
8415
-01-
527-
1541
EA
SMA
LL
8415
-01-
527-
1545
EA
ME
DIU
M84
15-0
1-52
7-15
51E
AL
AR
GE
8415
-01-
527-
1555
EA
X-L
AR
GE
8415
-01-
527-
1560
EA
XX
-LA
RG
E84
15-0
1-52
7-15
61E
A97
Park
a,W
etW
eath
er(G
reen
inC
olor
)M
IL-P
-870
98(s
uper
sede
sM
IL-P
-822
77)
XX
-Sm
all
8405
-01-
276-
4187
EA
Wat
erpr
oof
chlo
ropr
ene
rub-
ber
coat
edny
lon
twill
park
afo
rus
ein
conj
unc-
tion
with
wet
wea
ther
trou
sers
(Ite
mN
o.96
)fo
rai
rcra
ft,
mis
sile
,an
deq
uipm
ent
mai
nten
ance
oper
atio
nsfo
rpe
rson
nel
prot
ectio
nin
wet
orw
et/
cold
cond
ition
s.
X-S
mal
l84
05-0
1-27
6-41
88E
ASm
all
8405
-01-
276-
4189
EA
Med
ium
8405
-01-
276-
4190
EA
Lar
ge84
05-0
1-27
6-41
91E
AX
-Lar
ge84
05-0
1-27
6-41
92E
A
TO 1-1-691
Change 8 B-29
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
Park
a,Im
prov
edW
etW
eath
er:
light
wei
ght
Bre
atha
ble
(Woo
dlan
dco
lor)
Non
-Spe
c/
SSC
NC
-IC
The
Impr
oved
Rai
nSu
it(I
RS)
ism
ade
ofSy
mpa
-Te
x,a
light
wei
ght
brea
th-
able
,w
ater
proo
fm
ater
ial
mad
eby
Sym
paTe
xTe
ch-
nolo
gies
Gm
bH.
Sym
pa-
Tex
isa
nylo
nm
ater
ial
that
ispl
iabl
ean
dm
ois-
ture
-vap
or-s
emi-
perm
e-ab
le.
Itre
sist
exte
rnal
wa-
ter
whi
leal
low
ing
pers
pira
tion
orot
her
moi
s-tu
reto
tran
sfer
from
in-
side
toou
tsid
e,th
ereb
yke
epin
gth
ew
eare
rdr
yan
dco
mfo
rtab
le.
XX
-SM
AL
L84
05-0
1-44
3-96
06E
AX
-SM
AL
L84
05-0
1-44
3-96
12E
ASM
AL
L84
05-0
1-44
3-96
18E
AM
ED
IUM
8405
-01-
443-
9622
EA
LA
RG
E84
05-0
1-44
3-96
26E
AX
-LA
RG
E84
05-0
1-44
3-96
30E
AX
X-L
AR
GE
8405
-01-
443-
9633
EA
Park
a,Im
prov
edW
etW
eath
er:
light
wei
ght
Bre
atha
ble
(Uni
-ve
rsal
Cam
ou-
flage
colo
r)
Non
-Spe
c/
CO
/PD
-992
0T
heIR
Spa
rkas
have
roll-
upho
odw
itha
viso
ran
ddr
awst
ring
clos
ure.
The
rear
ear
mpi
tzi
pper
sfo
rve
n-til
atio
n,a
heav
yfu
ll-le
ngth
zipp
erin
fron
tco
v-er
edby
ast
orm
flap
that
clos
esw
ithsn
aps.
The
pock
ets
are
pass
-thr
ough
toin
ner
garm
ents
.T
heel
bow
sar
ere
info
rced
and
Vel
cro
clos
ures
atth
ecu
ffs
mak
ea
tight
fit.
XX
-SM
AL
L84
15-0
1-52
7-46
10E
AX
-SM
AL
L84
15-0
1-52
7-46
11E
ASM
AL
L84
15-0
1-52
7-46
12E
AM
ED
IUM
8415
-01-
527-
4614
EA
LA
RG
E84
15-0
1-52
7-46
16E
AX
-LA
RG
E84
15-0
1-52
7-46
17E
AX
X-L
AR
GE
8415
-01-
527-
4618
EA
The
IRS
park
asfo
rma
wa-
terp
roof
oute
rsh
ell
wor
nov
erot
her
clot
hing
and
gear
.It
islig
htw
eigh
tho
wev
er;
IRS
func
tions
stri
ctly
asa
rain
barr
ier,
offe
ring
little
prot
ectio
nfr
omth
eco
ld.
TO 1-1-691
B-30 Change 8
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
98Pa
rka
and
Tro
user
s,W
etW
eath
er(W
oodl
and
Cam
-ou
flage
Patte
rn)
MIL
-P-4
3907
,C
lass
2(W
dld
Cam
Pat)
Park
a-
XX
-Sm
all
8405
-01-
053-
9202
EA
Wat
erpr
oof
poly
uret
hane
coat
edny
lon
twill
park
a(w
ithho
od)
and
trou
sers
for
use
over
oute
rga
r-m
ents
(hot
orco
ldw
eath
er)
duri
ngai
rcra
ft,
mis
sile
,an
deq
uipm
ent
mai
nten
ance
oper
atio
nsfo
rpe
rson
nel
prot
ectio
nin
wet
orw
et/c
old
cond
ition
sw
hen
cam
oufla
gepa
ttern
clot
hing
isre
quir
ed.
X-S
mal
l84
05-0
0-00
1-15
47E
ASm
all
8405
-00-
001-
1548
EA
Med
ium
8405
-00-
001-
1549
EA
Lar
ge84
05-0
0-00
1-15
50E
AX
-Lar
ge84
05-0
0-00
1-15
51E
AT
rous
ers
-X
X-S
mal
l84
05-0
1-05
3-94
00PR
X-S
mal
l84
05-0
0-00
1-80
25PR
Smal
l84
05-0
0-00
1-80
26PR
Med
ium
8405
-00-
001-
8027
PRL
arge
8405
-00-
001-
8028
PRX
-Lar
ge84
05-0
0-00
1-80
29PR
Park
aan
dT
rous
ers,
Wet
Wea
ther
(Woo
dlan
dC
am-
oufla
gePa
ttern
)
MIL
-P-2
8958
/MIL
-P-
4390
7W
ater
proo
fpo
lyur
etha
neco
ated
nylo
ntw
illpa
rka
(with
hood
)an
dtr
ouse
rsfo
rus
eov
erou
ter
gar-
men
ts(h
otor
cold
wea
ther
)du
ring
airc
raft
,m
issi
le,
and
equi
pmen
tm
aint
enan
ceop
erat
ions
for
pers
onne
lpr
otec
tion
inw
etor
wet
/col
dco
nditi
ons
whe
nca
mou
flage
patte
rncl
othi
ngis
requ
ired
.
SMA
LL
8405
-01-
443-
9449
EA
ME
DIU
M84
05-0
1-44
3-94
87E
AL
AR
GE
8405
-01-
443-
9488
EA
X-L
AR
GE
8405
-01-
443-
9493
EA
TO 1-1-691
Change 8 B-30.1
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
99Ja
cket
,E
xtre
me
Col
dW
eath
er,
Impe
rmea
ble
(Gre
enin
Col
or)
MIL
-J-8
2299
,Sm
all
8415
-00-
349-
9313
EA
Prot
ectiv
eou
terw
ear
for
air-
craf
t,m
issi
le,
and
equi
p-m
ent
mai
nten
ance
oper
a-tio
nsat
tem
pera
ture
sbe
low
+14
°F
(-10
°C
).U
sed
inco
njun
ctio
nw
ithex
trem
eco
ldw
eath
ertr
ouse
rs(I
tem
No.
100)
and
aho
od.
X-L
arge
8415
-00-
349-
9316
EA
100
Tro
user
s,E
xtre
me
Col
dW
eath
er,
Impe
rmea
ble
(Gre
enin
Col
or)
MIL
-T-2
1705
,Sm
all
(Siz
e27
to30
)84
15-0
0-57
5-12
25E
APr
otec
tive
oute
rwea
rfo
rai
r-cr
aft,
mis
sile
,an
deq
uip-
men
tm
aint
enan
ceop
era-
tions
atte
mpe
ratu
res
belo
w+
14°
F(-
10°
C).
Use
din
conj
unct
ion
with
anex
trem
eco
ldw
eath
erja
cket
(Ite
mN
o.99
)an
da
hood
.
X-L
arge
(Siz
e39
to42
)84
15-0
0-57
5-12
46E
AX
X-L
arge
(Siz
e43
to46
)84
15-0
0-57
5-12
47E
A
101
Pads
,K
nee,
Indu
s-tr
ial
PN31
861,
CA
GE
Cod
e#5
5799
4240
-00-
595-
3861
PRK
nee
prot
ectio
ndu
ring
mai
nten
ance
oper
atio
ns.
Mad
eof
hard
rubb
erw
itha
spon
geru
bber
liner
and
atta
ched
with
two
adju
st-
able
web
stra
psw
ithre
-ta
inin
gbu
ckle
s.
PN54
02T
13,
CA
GE
Cod
e#3
9428
Sam
e
PN71
H17
18,
CA
GE
Cod
e#5
3800
Sam
e
102
Fire
men
’sB
oots
(Bla
ckin
Col
or)
A-A
-503
71,
Type
II(K
nee
Len
gth
-13
½in
Hig
h)-
Size
5
8430
-00-
753-
5935
PRPr
otec
tive
oute
rfo
otw
ear
for
airc
raft
mai
nten
ance
op-
erat
ions
such
asai
rcra
ft,
mis
sile
,an
deq
uipm
ent
was
hing
.Si
ze6
8430
-00-
753-
5936
PRSi
ze7
8430
-00-
753-
5937
PRSi
ze8
8430
-00-
753-
5938
PRSi
ze9
8430
-00-
753-
5939
PRSi
ze10
8430
-00-
753-
5940
PRSi
ze11
8430
-00-
753-
5941
PRSi
ze12
8430
-00-
753-
5942
PRSi
ze13
8430
-00-
753-
5943
PRSi
ze14
8430
-00-
753-
5944
PRSi
ze15
8430
-00-
753-
5945
PR
TO 1-1-691
B-30.2 Change 8
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
Type
I(¾
Len
gth
-29
inH
igh)
-Si
ze5
8430
-00-
753-
6105
PR
Size
684
30-0
0-14
7-10
32PR
Size
784
30-0
0-14
7-10
33PR
Size
884
30-0
0-14
7-10
34PR
Size
984
30-0
0-14
7-10
35PR
Size
1084
30-0
0-14
7-10
36PR
Size
1184
30-0
0-29
9-03
42PR
Size
1284
30-0
0-14
7-10
38PR
Size
1384
30-0
0-08
2-54
90PR
Size
1484
30-0
0-08
2-54
91PR
Size
1584
30-0
0-08
2-54
92PR
103
Foot
wea
rC
over
s,A
ircr
aft
Was
h-do
wn
(Cha
rcoa
lG
ray
inC
olor
)
PNM
,C
AG
EC
ode
#292
23,
Med
ium
8430
-00-
911-
2458
PRW
ater
repe
llent
cove
rsw
orn
over
boot
sto
incr
ease
trac
tion
and
prev
ent
mak
-in
gbo
otm
arks
onai
rcra
ftsu
rfac
esw
hen
wal
king
onth
emdu
ring
mai
nten
ance
and
was
hing
oper
atio
ns.
Lar
ge84
30-0
0-91
1-24
59PR
X-L
arge
8430
-00-
911-
3771
PR
104
Foot
wea
rC
over
,C
hem
ical
Prot
ec-
tive
Ove
rboo
ts(B
lack
inC
olor
)
MIL
-F-4
3987
,Sm
all
8430
-01-
118-
8712
PRO
verb
oots
for
foot
wea
r(s
hoes
and
boot
s)us
edto
prot
ect
them
from
chem
i-ca
lat
tack
duri
ngm
aint
e-na
nce
oper
atio
nsw
hich
requ
ire
use
ofch
emic
als.
The
yar
eac
id,
fuel
,oi
l,an
dfir
ere
sist
ant.
The
smal
lsi
zeis
for
use
over
size
s3
to7
½co
mba
tbo
ots
and
the
larg
esi
zeis
for
use
over
size
s8
to14
com
bat
boot
s.
Lar
ge84
30-0
1-02
1-59
78PR
TO 1-1-691
Change 8 B-30.3/(B-30.4 blank)
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
105
Ove
rsho
es,
Men
’sR
ubbe
r,5
Buc
kle
Type
(Bla
ckin
Col
or)
A-A
-503
62(s
uper
sede
sM
IL-O
-836
),Si
ze5
8430
-00-
144-
1672
PRM
ediu
mw
eigh
tov
ersh
oes
topr
otec
tre
gula
rfo
otw
ear
from
wat
eran
dot
her
liq-
uids
duri
ngm
aint
enan
ceop
erat
ions
orou
tsid
eac
-tiv
ities
duri
ngin
clem
ent
wea
ther
cond
ition
s.
Size
684
30-0
0-14
4-16
73PR
Size
784
30-0
0-14
4-16
74PR
Size
884
30-0
0-14
4-16
43PR
Size
984
30-0
0-14
4-16
44PR
Size
1084
30-0
0-14
4-16
45PR
Size
1184
30-0
0-14
4-16
46PR
Size
1284
30-0
0-14
4-16
47PR
Size
1384
30-0
0-14
4-16
48PR
Size
1484
30-0
0-14
4-16
49PR
Size
1584
30-0
0-14
4-16
82PR
106
Apr
on,
Util
ity(L
abor
ator
yB
lack
inC
olor
)
A-A
-310
4(s
uper
sede
sZ
Z-
A-6
05)
(45
inL
x35
inW
)
8415
-00-
634-
5023
EA
Afu
llle
ngth
chlo
ropr
ene
rubb
er(a
cid
resi
stan
t)pr
o-te
ctiv
eap
ron
used
topr
o-te
ctco
rros
ion
mai
nten
ance
pers
onne
lan
dth
eir
clot
h-in
gag
ains
tch
emic
alsp
lash
esw
hen
hand
ling
chem
ical
s.10
7Fa
ceSh
ield
,In
dus-
tria
l,(A
djus
tabl
eSt
rap,
Cle
arle
ns)
AN
SIZ
87.1
(sup
erse
des
L-F
-36)
(9in
Lx
18in
WPl
astic
Win
dow
/Len
s)
4240
-00-
542-
2048
EA
Use
dto
prov
ide
eye
and
face
prot
ectio
nw
hen
cut-
ting,
grin
ding
,or
chip
ping
met
alor
whe
nha
ndlin
gha
zard
ous
chem
ical
s.
NO
TE
Face
shie
ldis
not
for
prim
ary
prot
ectio
nan
dsh
ould
alw
ays
beus
edw
ithgo
ggle
s.
TO 1-1-691
B-31
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
108
Gog
gles
,In
dust
rial
,Pl
astic
Stan
dard
Safe
tyG
oggl
es(A
djus
tabl
eH
ead-
band
,Si
ngle
Cle
arPo
lyca
rbon
-at
ePl
astic
Len
s,V
ente
dC
lear
Plas
ticFr
ame)
AN
SIZ
87.1
(sup
erse
des
A-A
-111
0)42
40-0
0-05
2-37
76PR
Topr
ovid
eey
epr
otec
tion
from
flyin
gpa
rtic
les
inin
dust
rial
envi
ronm
ents
.C
anbe
wor
nov
erey
e-gl
asse
s.G
oggl
esar
eve
nti-
late
dto
redu
cefo
ggin
g.
Spla
sh-P
roof
Gog
gles
(Adj
ust-
able
Hea
dban
d,Si
ngle
Gre
enPo
lyca
rbon
ate
Plas
ticL
ens,
Lig
ht-g
reen
Plas
-tic
Fram
ew
ithIn
dire
ctV
entin
g)
4240
-01-
082-
8928
PRTo
prot
ect
eyes
from
chem
i-ca
lsp
lash
es,
impa
cts,
and
spar
ks.
Can
bew
orn
over
eyeg
lass
es.
Ven
tilat
edfo
rco
mfo
rtan
dto
prov
ide
airfl
owto
min
imiz
ele
nsfo
ggin
g.
109
Gog
gles
,C
hem
ical
Spla
shPr
oof
Type
(Adj
usta
ble
Hea
dban
d,D
oubl
eC
lear
Gla
ssL
ens,
Un-
vent
edC
lear
Plas
ticFr
ame
with
Rub
ber
Face
Pads
)
AN
SIZ
87.1
Com
mer
cial
Item
sC
omm
only
know
nas
“Nod
and
Shak
e”go
ggle
s,th
eyar
epa
rtic
ular
lyus
eful
for
eye
prot
ectio
ndu
ring
air-
craf
t,m
issi
le,
and
equi
p-m
ent
was
hing
oper
atio
ns.
The
yal
sopr
ovid
eex
cel-
lent
eye
prot
ectio
ndu
ring
chem
ical
corr
osio
nre
-m
oval
and
met
alsu
rfac
etr
eatm
ent
oper
atio
ns.
PNA
883F
,C
AG
EC
ode
#6M
644
Ope
nPu
rcha
sePR
PN55
1,C
AG
EC
ode
#160
29O
pen
Purc
hase
PR
110
Plug
,E
arD
ispo
s-ab
le(Y
ello
win
Col
or)
PN4-
375,
CA
GE
Cod
e#8
9875
&U
3216
6515
-00-
137-
6345
BX
(400
EA
)(2
00E
Aw
rapp
edpa
irs)
Com
pres
sibl
evi
nyl
foam
mat
eria
lth
atex
pand
sto
fitth
eea
rca
nal
and
prov
ide
am
oder
ate
degr
eeof
hear
ing
prot
ectio
nin
high
nois
ein
dust
rial
envi
ron-
men
ts.
TO 1-1-691
B-32
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
111
Prot
ecto
r,H
eari
ng(H
eadp
hone
Cir
-cu
mau
ral/e
arm
uff
Styl
e,C
omes
with
Ext
raSe
tof
Seal
s)
A-A
-580
8442
40-0
0-02
2-29
46E
AFi
tsse
cure
lyov
erth
eea
rsto
prov
ide
ahi
ghde
gree
ofhe
arin
gpr
otec
tion
tohe
lppr
even
the
arin
glo
ssor
dam
age
inlo
udw
ork
ar-
eas.
112
Aur
alPr
otec
tor,
Soun
dSA
EA
S23
899
(sup
erse
des
MIL
-A-2
3389
)E
arm
uff
asse
mbl
y
4240
-00-
759-
3290
EA
Fits
secu
rely
over
the
ears
topr
ovid
ea
high
degr
eeof
hear
ing
prot
ectio
nto
help
prev
ent
hear
ing
loss
orda
mag
ein
loud
wor
kar
-ea
s.
Rep
lace
men
tSe
als
4240
-00-
979-
4040
PR
SEA
LA
NT
APP
LIC
AT
ION
EQ
UIP
ME
NT
(TO
OL
S)11
3Se
alan
tD
ispe
nsin
gG
unw
ith2.
5O
ZM
etal
Ret
aine
r(M
anua
lTy
pe)
CA
GE
Cod
e#9
2108
,PN
2218
24,
(Sem
co®
Mod
el#8
50-2
.5M
)
5120
-01-
135-
8344
EA
App
licat
ion
ofse
alan
tsan
dad
hesi
ves.
114
Seal
ant
Dis
pens
ing
Gun
with
6O
ZM
etal
Ret
aine
r(M
anua
lTy
pe)
CA
GE
Cod
e#9
2108
,PN
2218
30,
(Sem
co®
Mod
el#8
50-6
M)
5120
-00-
952-
3507
EA
App
licat
ion
ofse
alan
tsan
dad
hesi
ves.
115
Seal
ant
Dis
pens
ing
Gun
with
12O
ZM
etal
Ret
aine
r(M
anua
lTy
pe)
CA
GE
Cod
e#9
2108
,PN
2218
36,
(Sem
co®
Mod
el#8
50-1
2M)
5120
-01-
373-
3805
EA
App
licat
ion
ofse
alan
tsan
dad
hesi
ves.
116
Seal
ant
Dis
pens
ing
Gun
with
2.5
OZ
Met
alR
etai
ner
(Pne
umat
icTy
pe)
CA
GE
Cod
e#9
2108
,PN
2502
55,
(Sem
co®
Mod
el#2
50A
-2½
)
5130
-00-
323-
2287
EA
App
licat
ion
ofse
alan
tsan
dad
hesi
ves.
Gun
hand
leis
rem
ovab
leto
allo
wfo
rea
sier
acce
ssin
confi
ned
area
s.R
efer
toFi
gure
6-1.
117
Seal
ant
Dis
pens
ing
Gun
with
6O
ZM
etal
Ret
aine
r(P
neum
atic
Type
)
CA
GE
Cod
e#9
2108
,PN
2500
65,
(Sem
co®
Mod
el#2
50A
-6)
5130
-00-
924-
6396
EA
App
licat
ion
ofse
alan
tsan
dad
hesi
ves.
Gun
hand
leis
rem
ovab
leto
allo
wfo
rea
sier
acce
ssin
confi
ned
area
s.R
efer
toFi
gure
6-1.
TO 1-1-691
B-33
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
118
Seal
ant
Dis
pens
ing
Gun
with
12O
ZM
etal
Ret
aine
r(P
neum
atic
Type
)
CA
GE
Cod
e#9
2108
,PN
2501
25,
(Sem
co®
Mod
el#2
50A
-12)
Ope
nPu
rcha
seE
AA
pplic
atio
nof
seal
ants
and
adhe
sive
s.G
unha
ndle
isre
mov
able
toal
low
for
easi
erac
cess
inco
nfine
dar
eas.
Ref
erto
Figu
re6-
1.11
9R
epai
rK
itfo
rSe
al-
ant
Dis
pens
ing
Gun
(Pne
umat
icTy
pe)
CA
GE
Cod
e#9
2108
,PN
2400
20O
pen
Purc
hase
KT
Val
vere
pair
kit
for
Sem
co®
Mod
el#2
50-A
seal
ant
disp
ensi
nggu
ns.
120
Rep
lace
men
tC
ar-
trid
geR
etai
ners
for
Sem
co®
Mod
el#8
50M
anua
lSe
alan
tD
ispe
nsin
gG
uns
CA
GE
Cod
e#9
2108
Sem
co®
Mod
el#8
50R
etai
ners
,PN
2268
19
5120
-01-
247-
1639
EA
Rep
lace
men
tm
etal
reta
iner
;2.
5O
Zgu
ns.
PN22
6820
5340
-01-
384-
6120
EA
Rep
lace
men
tm
etal
reta
iner
;6
OZ
guns
.PN
2268
22O
pen
Purc
hase
EA
Rep
lace
men
tm
etal
reta
iner
;12
OZ
guns
.12
1R
epla
cem
ent
Car
-tr
idge
Ret
aine
rsfo
rSe
mco
®M
odel
#250
-APn
eum
atic
Seal
-an
tD
ispe
nsin
gG
uns
CA
GE
Cod
e#9
2108
Sem
co®
Mod
el#2
50A
Ret
aine
rs,
PN22
0256
5120
-00-
693-
8069
EA
Rep
lace
men
tm
etal
reta
iner
;2.
5O
Zgu
ns.
PN22
0928
5120
-00-
693-
8070
EA
Rep
lace
men
tm
etal
reta
iner
;6
OZ
guns
.PN
2209
2351
20-0
0-69
3-80
71E
AR
epla
cem
ent
met
alre
tain
er;
12O
Zgu
ns.
122
Hos
eA
ssem
blie
sfo
rSe
mco
®M
odel
#250
-APn
eum
atic
Seal
-an
tD
ispe
nsin
gG
uns
CA
GE
Cod
e#9
2108
,H
ose
Ass
embl
yw
ithH
anse
nC
onne
ctor
Ass
embl
y,(5
ftL
)PN
2800
00
Ope
nPu
rcha
seE
AR
epla
cem
ent
hose
asse
m-
blie
san
dfit
tings
for
Sem
co®
Mod
el#2
50-A
pneu
mat
icse
alan
tdi
spen
s-in
ggu
ns.A
llho
seas
sem
-bl
ies
com
ew
itha
B-n
utfit
ting
and
aqu
ick
disc
on-
nect
atta
chm
ent
(10
ftL
)PN
2800
0147
20-0
0-95
6-53
13E
A(1
5ft
L)
PN28
0002
Ope
nPu
rcha
seE
A(2
0ft
L)
PN28
0003
4720
-01-
329-
8602
EA
(25
ftL
)PN
2800
0447
20-0
0-08
0-51
59E
A(3
0ft
L)
PN28
0005
Ope
nPu
rcha
seE
AH
anse
nC
onne
ctor
Ass
em-
bly,
PN22
9186
Ope
nPu
rcha
seE
A
B-N
utA
ssem
bly
(Gun
End
),PN
2291
8947
30-0
1-26
7-53
07E
A
TO 1-1-691
B-34
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
123
Wre
nch
for
Sem
co®
Mod
el#2
50-A
Pneu
-m
atic
Seal
ant
Dis
pens
ing
Gun
s
CA
GE
Cod
e#9
2108
,PN
2400
1851
20-0
0-99
6-15
65E
ASe
rvic
ew
renc
hfo
rad
just
ing
Sem
co®
Mod
el#2
50-A
pneu
mat
icse
alan
tdi
spen
s-in
ggu
ns.
124
Sem
co®
Dis
posa
ble
Plas
ticC
artr
idge
s,Pl
unge
rs,
Seal
s,an
dC
aps
for
Man
ual
and
Pneu
mat
icSe
al-
ant
Dis
pens
ing
Gun
s
CA
GE
Cod
e#9
2108
,C
ar-
trid
ges
(HD
Poly
ethy
l-en
e),
PN22
0316
(2.5
OZ
)
5120
-00-
694-
9082
EA
Em
pty
cart
ridg
esfo
rfil
ling
with
and
disp
ensi
ngof
two-
part
seal
ants
usin
gth
eSe
mco
®M
odel
#’s
250-
Aan
d85
0se
alan
tdi
spen
sing
guns
.PN
2203
17(6
OZ
)51
20-0
0-67
3-18
86E
APN
2203
18(1
2O
Z)
5120
-01-
454-
4210
EA
Wip
erPl
unge
rs(L
DPo
ly-
ethy
lene
),PN
2202
5951
20-0
0-27
6-94
22E
AU
sed
toas
sure
com
plet
edi
spen
sing
ofse
alan
tsan
del
imin
atio
nof
was
tean
d/or
leak
age
from
the
back
end
ofth
eca
rtri
dge.
Fits
eith
er2.
5O
Z,
6O
Z,
or12
OZ
cart
ridg
es.
WP
(Wip
erPl
unge
r)T
hrea
ded
Cap
,PN
2344
11
5365
-01-
107-
7863
EA
Use
dto
scre
win
toan
dca
pth
ene
ckor
fron
ten
dof
the
cart
ridg
eto
prev
ent
leak
age.
Fits
eith
er2.
5O
Z,
6O
Z,
or12
OZ
car-
trid
ges.
TC
-Sea
lC
ap,
Flan
geC
ap,
PN22
0238
8125
-00-
410-
8501
EA
Use
dto
snap
onto
the
back
end
ofth
eca
rtri
dge
topr
even
tco
ntam
inat
ion
ofth
ese
alan
t.Fi
tsei
ther
2.5
OZ
,6
OZ
,or
12O
Zca
r-tr
idge
s.F-
Flan
ge(S
nap
On)
Cap
125
Mec
hani
cal
Bea
mA
naly
tical
Bal
-an
ce(O
haus
Dia
l-O
-Gra
mB
alan
ce)
CA
GE
Cod
e#8
5973
(Oha
usC
orp.
),PN
1650
6670
-00-
957-
3781
EA
Use
for
wei
ghin
gou
tth
epr
oper
ratio
ofba
sean
dac
cele
rato
rco
mpo
unds
topr
epar
ean
dm
ixtw
oco
m-
pone
ntse
alan
ts.
TO 1-1-691
B-35
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
126
Sem
co®
Seal
ant
Smoo
thin
gTo
ols
(Fib
ergl
ass
Rei
n-fo
rced
Plas
tic)
CA
GE
Cod
e#9
2108
,Se
al-
ant
Spat
ulas
,PN
2313
4951
20-0
1-33
7-94
15E
ASp
atul
asan
dsp
read
ers
for
tool
ing
and
smoo
thin
gse
alan
tsan
dad
hesi
ves.
For
addi
tiona
lin
form
atio
n,re
fer
toFi
gure
6-5.
9½
inL
;ro
unde
den
ds-
9/16
inD
&¼
inD
.PN
2262
4151
20-0
1-29
7-70
15E
A7
¼in
L;
sqen
d-3
/16
inW
&rd
.en
d-
3⁄8
inD
.PN
2262
4251
20-0
1-29
7-70
16E
A7
¼in
L;
sqen
d-9
/32
inW
&rd
.en
d-
1⁄8
inD
.PN
2262
4351
20-0
1-29
7-70
17E
A7
¼in
L;
sqen
ds-
3⁄8
inW
&15
/32
inW
.Sp
atul
aK
it,PN
2262
4451
20-0
0-05
6-32
37K
TT
heki
tin
clud
essp
atul
asPN
s22
6241
,22
6242
,an
d22
6243
spat
ulas
.Se
alan
tSc
rape
r,PN
2343
5051
20-0
1-29
8-61
21E
AU
sed
for
eith
ersp
read
ing
orre
mov
alof
seal
ant
from
all
surf
aces
(513
/16
inL
;on
esq
end
-¾
inW
).Se
alan
tSp
read
er,
PN22
9394
5120
-01-
337-
9416
EA
Use
dfo
rsp
read
ing
seal
ants
orad
hesi
ves
onto
flat
sur-
face
s,in
part
icul
aron
ala
rge
area
(4in
Lx
23/
16in
W).
Com
bSp
read
er,
PN22
9395
Ope
nPu
rcha
seE
AU
sed
tosp
read
seal
ants
orad
hesi
ves
whi
lem
aint
ain-
ing
aun
ifor
mth
ickn
ess
and
agr
oove
dpa
ttern
(3in
Lx
3in
Ww
ithsa
wto
oth
edge
s).
127
Plas
ticN
ozzl
es,
Dis
posa
ble
(¼in
or½
inN
PTM
ale
Thr
eade
dE
nd)
CA
GE
Cod
e#9
2108
(Sem
co®
Mod
el#’
s)N
ozzl
esus
edfo
rdi
spen
sing
seal
ants
whe
nat
tach
edto
Sem
co®
cart
ridg
es(I
tem
No.
124)
.R
efer
toFi
gure
6-2
for
nozz
lesh
apes
tode
term
ine
the
appr
opri
ate
Mod
el#
for
the
job.
TO 1-1-691
B-36
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
Stan
dard
Noz
zles
No.
252
(PN
2205
38)
5120
-00-
167-
0150
EA
App
lyin
gse
alan
tin
butt
seam
gaps
.St
2½
inL
with
1/16
inor
ifice
.N
o.25
4(P
N22
0540
)51
20-0
0-67
3-18
85E
ASt
2½
inL
with
1⁄8
inor
i-fic
e.N
o.25
5(P
N23
3495
)O
pen
Purc
hase
EA
St2
½in
Lw
ithno
orifi
ce(c
utto
suit)
.N
o.41
0(P
N22
0542
)51
20-0
0-80
1-09
49E
ASt
4in
Lw
ith1/
32in
ori-
fice.
No.
410
(PN
2205
43)
5120
-00-
055-
4063
EA
45°
angl
ew
ith1/
32in
ori-
fice.
No.
415
(PN
2276
13)
5120
-01-
386-
4480
EA
St4
inL
with
noor
ifice
(cut
tosu
it).
No.
420
(PN
2205
44)
5120
-00-
042-
6577
EA
St4
inL
with
1/16
inor
i-fic
e.N
o.43
0(P
N22
0548
)51
20-0
0-96
7-81
51E
ASt
4in
Lw
ith3/
32in
ori-
fice.
No.
430
(PN
2205
49)
5120
-00-
055-
4062
EA
45°
angl
ew
ith3/
32in
ori-
fice.
No.
440
(PN
2205
50)
5120
-00-
773-
3791
EA
St4
inL
with
1⁄8
inor
ifice
.N
o.62
0(P
N22
0553
)51
20-0
0-16
7-01
52E
ASt
6in
Lw
ith1/
16in
ori-
fice.
No.
620
(PN
2205
54)
5120
-00-
966-
5373
EA
45°
angl
ew
ith1/
16in
ori-
fice.
No.
640
(PN
2205
55)
5120
-00-
822-
7194
EA
St6
inL
with
1⁄8
inor
ifice
.N
o.64
0(P
N22
0556
)51
20-0
0-16
7-01
53E
A30
°an
gle
with
1⁄8
inor
ifice
.N
o.64
0(P
N22
0551
)51
20-0
0-67
0-11
86E
A45
°an
gle
with
1⁄8
inor
ifice
.N
o.65
0(P
N22
4494
)O
pen
Purc
hase
EA
St6
inL
with
1⁄8
inor
ifice
.N
o.82
0(P
N22
0557
)51
20-0
0-96
6-82
70E
ASt
8in
Lw
ith1/
16in
ori-
fice.
No.
820
(PN
2205
58)
5120
-00-
966-
5371
EA
45°
angl
ew
ith1/
16in
ori-
fice.
No.
840
(PN
2205
59)
5120
-00-
966-
5372
EA
St8
inL
with
1⁄8
inor
ifice
.N
o.84
0(P
N22
0560
)51
20-0
0-96
6-53
82E
A45
°an
gle
with
1⁄8
inor
ifice
.N
o.86
90(P
N22
0606
)51
20-0
0-96
6-82
43E
A9
inve
ntdu
ckno
zzle
with
3/32
inor
ifice
.
TO 1-1-691
B-37
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
No.
1002
(PN
2205
61)
5120
-00-
055-
4055
EA
St10
inL
with
1/16
inor
i-fic
e.N
o.10
04(P
N22
0563
)51
20-0
0-05
5-40
54E
ASt
10in
Lw
ith1⁄8
inor
ifice
.N
o.10
10(P
N22
0565
)51
20-0
0-05
5-40
58E
ASt
10in
Lw
ith5/
16in
ori-
fice.
Fille
tN
ozzl
es,
No.
425
(PN
2324
99)
5120
-01-
386-
4274
EA
App
lyin
gse
alan
tfil
lets
over
lap
join
ts.
St4
inL
with
3⁄8
inx
1⁄8
inor
ifice
.N
o.42
6(P
N23
2500
)O
pen
Purc
hase
EA
St4
inL
with
3⁄8
inx
1⁄8
inor
ifice
.N
o.42
7(P
N23
2501
)O
pen
Purc
hase
EA
St4
inL
with
3⁄8
inx
1⁄8
inor
ifice
.N
o.42
8(P
N23
2502
)O
pen
Purc
hase
EA
St4
inL
with
3⁄8
inx
1⁄8
inor
ifice
.N
o.42
9(P
N23
2590
)O
pen
Purc
hase
EA
St4
inL
with
1/16
inx
½in
orifi
ce.
Rib
bon
Noz
zles
,N
o.86
07(P
N22
0568
)51
20-0
0-96
6-53
81E
AA
pply
ing
seal
ant
for
fay
surf
ace
seal
ing.
St57
/ 8in
Lw
ith1/
16in
x¼
inor
i-fic
e.N
o.86
08(P
N22
0569
)51
20-0
0-96
6-82
44E
ASt
4in
Lw
ith11
/64
inor
i-fic
e(fl
ared
tip).
No.
8610
(PN
2205
70)
5120
-00-
299-
6790
EA
St41
⁄8in
Lw
ith3/
64in
x9/
64in
orifi
ce.
No.
8613
(PN
2205
72)
5120
-00-
966-
5379
EA
St5
inL
with
3/64
inx
3⁄8
inor
ifice
.N
o.86
15(P
N22
0574
)51
20-0
0-96
6-53
78E
ASt
4in
Lw
ith1/
16in
x½
inor
ifice
.N
o.86
16(P
N22
0577
)51
20-0
1-38
5-50
74E
A2
3/16
inL
with
7/32
inor
ifice
(for
win
dshi
eld
fille
ts).
No.
8630
(PN
2205
89)
5120
-00-
966-
5377
EA
St4
inL
with
1⁄8
inx
1¾
inor
ifice
.N
o.86
30-9
(PN
2205
82)
5120
-00-
966-
5376
EA
St47
⁄8in
Lw
ith1⁄8
inx
1¾
inor
ifice
and
anat
tach
edbr
ush
spre
ader
.
TO 1-1-691
B-38
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
No.
8642
(PN
2205
85)
5120
-00-
293-
4676
EA
St4
inL
with
3/16
inor
i-fic
e.N
o.86
43(P
N22
0586
)51
20-0
0-77
5-16
70E
ASt
43⁄8
inL
with
1⁄8
inx
¾in
orifi
cean
dsp
atul
alik
eex
tens
ion
spre
ader
.N
o.86
45(P
N22
0587
)51
20-0
0-13
8-16
58E
ASt
43/
16in
Lw
ith1⁄8
inx
1in
orifi
cean
dsp
atul
alik
eex
tens
ion
spre
ader
.N
o.86
46(P
N22
0588
)51
20-0
0-96
6-53
74E
ASt
315
/16
inL
with
1⁄8
inx
¾in
orifi
cean
dsa
wto
oth
trow
elex
tens
ion
spre
ader
.N
o.86
48(P
N22
0589
)51
20-0
0-96
6-53
75E
ASt
53/
16in
Lw
ith1⁄8
inx
¾in
orifi
cean
dsp
atul
alik
eex
tens
ion
spre
ader
.E
xten
sion
Noz
zle,
No.
600E
(PN
2205
52)
5120
-00-
670-
1187
EA
63⁄8
inL
roun
dex
tens
ion
tube
.Fl
oorb
oard
Noz
zle,
PN23
1674
Ope
nPu
rcha
seE
AA
pply
ing
seal
ant
onflo
orbo
ard
fayi
ngsu
rfac
es.
St1
3⁄8
inL
with
½in
Dct
r.bu
tton
surr
ound
edw
ith12
EA
1/32
inor
ifice
s.Fu
nnel
Noz
zle,
1in
(PN
2317
18)
Ope
nPu
rcha
seE
AFi
lling
larg
eca
vitie
sw
ithse
alan
t.St
13⁄8
inL
with
½in
funn
elty
peor
ifice
.2
in(P
N23
1348
)O
pen
Purc
hase
EA
St3
1⁄8
inL
with
127
/32
infu
nnel
type
orifi
ce.
Noz
zle
Ada
pter
,PN
2293
06O
pen
Purc
hase
EA
¼in
NPT
mal
eth
read
and
½in
NPT
fem
ale
thre
adto
rece
ive
½in
NPT
thre
adno
zzle
.E
dge
Fill
Noz
zle,
No.
444
(PN
2341
64)
Ope
nPu
rcha
seE
AA
0.40
inth
ick
flang
egu
ides
ital
ong
apa
nel
edge
/cor
-ne
rto
prov
ide
asl
ight
lyro
unde
ded
ge/c
orne
rfil
l.
TO 1-1-691
B-39
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
128
Fast
ener
Seal
ing
Noz
zles
(Cou
nter
-si
nkN
ozzl
es)
CA
GE
Cod
e#9
2108
,PN
2332
44,
Size
:3/
32in
-1⁄8
in(R
ed)
Ope
nPu
rcha
seE
AU
sed
toap
ply
the
requ
ired
amou
ntof
seal
ant
inth
eco
unte
rsin
kar
eaof
fas-
tene
rho
les
prio
rto
inst
al-
latio
nof
the
fast
ener
s.T
hey
have
thre
aded
ends
tofit
into
the
Sem
co®
plas
ticca
rtri
dges
(Ite
mN
o.12
4).
The
nozz
les
are
colo
rco
ded
for
iden
tifica
-tio
n.R
efer
toFi
gure
6-3
tode
term
ine
the
appr
opri
-at
eno
zzle
confi
gura
tion
and
size
for
the
job
asw
ell
asop
erat
ion
inst
ruc-
tions
.
PN23
3243
,Si
ze:
3/16
in-¼
in(W
hite
)O
pen
Purc
hase
EA
PN23
3451
,Si
ze:
5/16
in-
3⁄8
in(B
lue)
Ope
nPu
rcha
seE
A
PN23
1319
,Si
ze:
¼in
hole
(Yel
low
)O
pen
Purc
hase
EA
PN23
1320
,Si
ze:
5/16
inho
le(G
rey)
Ope
nPu
rcha
seE
A
PN23
1321
,Si
ze:
3⁄8
inho
le(G
reen
)O
pen
Purc
hase
EA
PN23
1560
,Si
ze:
7/16
inho
le(R
ed)
Ope
nPu
rcha
seE
A
PN23
1559
,Si
ze:
½in
hole
(Blu
e)O
pen
Purc
hase
EA
TO 1-1-691
B-40
Tabl
eB
-2.
Equ
ipm
ent
for
Cle
anin
gan
dC
orro
sion
Pre
vent
ion
and
Con
trol
-C
onti
nued
Item No.
Nom
encl
atur
eSp
ecifi
catio
ns/P
NN
atio
nal
Stoc
kN
umbe
rU
nit
ofIs
sue
Inte
nded
Use
129
Riv
etN
ozzl
esC
AG
EC
ode
#921
08,
PN23
4285
,Si
ze:
3/32
in(G
erm
aine
Gre
en)
Ope
nPu
rcha
seE
AU
sed
toap
ply
the
requ
ired
amou
ntof
seal
ant
inth
eco
unte
rsin
kan
dho
lepr
ior
tofa
sten
ing
part
sw
ithri
vets
.T
hesp
ring
-loa
ded
tipof
the
nozz
leac
tsas
ach
eck
valv
eal
low
ing
pre-
cise
shot
sof
mat
eria
lto
bedi
spen
sed.
The
yha
veth
read
eden
dsto
fitin
toth
eSe
mco
®pl
astic
car-
trid
ges.
The
nozz
les
are
colo
rco
ded
for
iden
tifica
-tio
n.R
efer
toFi
gure
6-4
tode
term
ine
the
appr
opri
-at
eno
zzle
confi
gura
tion
and
size
for
the
job
asw
ell
asop
erat
ion
inst
ruc-
tions
.
PN22
6837
,Si
ze:
1⁄8
in(B
lue)
5130
-01-
413-
8733
EA
PN22
6838
,Si
ze:
5/32
in(B
lack
)O
pen
Purc
hase
EA
PN22
6839
,Si
ze:
3/16
in(W
hite
)O
pen
Purc
hase
EA
PN23
4260
,Si
ze:
3/16
info
r12
0°co
unte
rsin
k(G
reen
)
Ope
nPu
rcha
seE
A
PN23
4284
,Si
ze:
7/32
in(L
ight
Blu
e)O
pen
Purc
hase
EA
PN22
6840
,Si
ze:
¼in
(Red
)51
20-0
1-41
6-16
83E
A
PN23
3051
,Si
ze:
5/16
in(O
rang
e)O
pen
Purc
hase
EA
PN:
2330
52,
Size
:3⁄8
in(Y
ello
w)
Ope
nPu
rcha
seE
A
130
Rol
ler
Noz
zles
(¼in
NPT
mal
eth
read
eden
d)
CA
GE
Cod
e#9
2108
,R
olle
rN
ozzl
eA
ssem
bly,
PN23
2693
(1in
WR
olle
r)
Ope
nPu
rcha
seE
AU
sed
toap
ply
adhe
sive
san
dse
alan
tsev
enly
over
wid
ear
eas
ofsu
bstr
ate
(e.g
.fa
ying
surf
ace)
.T
hey
have
thre
aded
ends
tofit
into
the
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TO 1-1-691
B-41
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TO 1-1-691
B-42 Change 2
Figure B-1. Back Mounted Full Facepiece Respirator
TO 1-1-691
Change 15 B-43
Figure B-2. Front Mounted Full Facepiece Respirator
TO 1-1-691
B-44
Figure B-3. Hooded Air Respirator System
TO 1-1-691
B-45/(B-46 blank)
GLOSSARY
A
ACTIVE METAL — A metal prone to corrode or beingcorroded.
ADDITIVE — A compound added for a particular purpose;for example, additives in fuel and lubricants can prevent cor-rosion, gum formation, varnishing, sludge formation, andknocking.
AERATION (OXYGEN CONCENTRATION)CELL — An electrolytic cell in which the driving force tocause corrosion results from a difference in the amount ofoxygen in solution at one point as compared to another. Cor-rosion is accelerated in areas where the oxygen concentratedis least, for example, in a crevice or under packing or gas-kets.
ALKALINE — Having a pH of more than 7.
ALLOY — A combination of two or more metals.
ANAEROBIC — A process which is capable of occurringin the absence of oxygen.
ANION — A negatively charged ion of an electrolyte whichmigrates toward the anode. The chloride ion in sea water isan anion.
ANODE — The electrode of a corrosion cell at which oxi-dation or corrosion occurs. It may be a small area on thesurface of a metal or alloy, such as that where a pit develops,or it may be the more active metal in a cell composed of twodissimilar metals, (i.e., the one with the greater tendency togo into solution). The corrosion process involves the changeof metal atoms into cations with a liberation of electrons thatmigrate through the metal to the cathode of the cell.
ANODIC PROTECTION — The reduction or eliminationof corrosion of a metal achieved by making current flowfrom it to the solution by connecting it to the positive pole ofa source of current. Under most conditions, as the potentialof an initially active metal is gradually shifted in a morenoble direction, such as by potentiostatic means, the corro-sion current gradually increases. However, with suitablecombinations of metal and solution, a critical potential issoon reached. Imposing a potential higher than the criticalpotential, causes the current to drop to a very low value, and
the metal becomes passive. The potential of metal has to beregulated by a potentiostat.
ANODIZE — To subject (a metal) to electrolytic action asthe anode of a cell in order to coat with a protective ordecorative film (anodic oxidation film).
AUSTENITIC — A term applied to that condition of ironassociated with a change in crystal structure that makes itnon-magnetic. This occurs with ordinary iron at an elevatedtemperature. When sufficient chromium and nickel are pres-ent, steel becomes austenitic (non-magnetic) at atmospheretemperatures. This is the case with the many stainless alloysthat combine about 18% chromium and 8% or more nickelwith iron.
C
CATHODE — The less active electrode of a corrosion cell,where the action of the current causes reduction and nearlycomplete elimination of corrosion.
CATHODIC PROTECTION — The reduction or elimina-tion of corrosion of a metal that is achieved by making cur-rent flow to it from a solution, such as connecting it to thenegative pole of some source current. The source of the pro-tective current may be sacrificial metal, such as magnesium,zinc, or aluminum. The current may also be derived from arectifier, generator, or battery applied through an appropriateanode which may be connected by the applied current (as inthe case of steel), or which remains substantially unaffectedby the current, as in the case of platinum. Cathodic protec-tion becomes complete when anodic reactions are completelysuppressed and only cathodic reactions occur on the metalsurface.
CATION — A positively charged ion in an electrolyte whichmigrates toward the cathode. Metallic ions, such as iron orcopper, are cations.
CAUSTIC EMBRITTLEMENT — The result of the com-bined action of tensile stress and corrosion in an alkalinesolution that causes embrittlement. This is the most fre-quently encountered in the laps of riveted boilers where therequired concentration of the alkali in the boiler water oc-curs.
CELL — In corrosion processes, a cell is a source of elec-trical current that is responsible for corrosion. It consists of
TO 1-1-691
Glossary 1
an anode and a cathode immersed in an electrolyte and elec-trically joined together. The anode and cathode may be sepa-rate metals dissimilar areas on the same metal.
CHEMICAL CONVERSION COATING — A film delib-erately produced on a metal by immersing it in, brushing itwith, or spraying it with a selected chemical solution for thepurpose of providing improved corrosion resistance to themetal or increasing the adhesion of organic coatings to beapplied later. Coatings covered by MIL-DTL-5541 are ex-amples.
CLEAR WATER — Colorless water containing no visiblesuspended particles.
COMBUSTIBLE LIQUID — Any liquid having a flash-point at or above 100° F, but below 200° F.
CONCENTRATION CELL — An electrolytic cell consist-ing of an electrolyte and two electrodes of the same metal oralloy that develops a difference in potential as a result of adifference in concentration of ions (most often metal ions) oroxygen at different points in a solution.
CORROSION FATIGUE — A reduction in the ability of ametal to withstand cyclic stress caused by its exposure to acorrosive environment.
CORROSION RATE — The speed of corrosion attack. It isusually expressed in terms of weight loss per unit of time.
COUPLE — Two or more metals or alloys in electrical con-tact with each other so that they can act as the electrodes ofa cell if they are immersed in an electrolyte.
CRACKING — Localized breaking of a paint film to ex-pose the underlying material and breaking of metal or alloyin a brittle fashion along a narrow path or network.
CREVICE CORROSION — Corrosion occurring within acrevice formed by two or more parts of the same or differentmetals or formed by a metal and non-metallic material.Stainless steel and aluminum alloys are particularly suscep-tible to crevice corrosion.
CRITICAL HUMIDITY — The relative humidity, under aspecific set of conditions, at which a metal or an alloy willbegin to corrode. In the presence of hygroscopic (moistureabsorptive) solids or corrosion products, the critical humid-ity will be lowered. Steel will not corrode if the relativehumidity is less than 30% in a marine atmosphere.
D
DEPOSIT ATTACK — When foreign material (dirt, corro-sion products, etc.,) is deposited on the surface of a metal, itmay shield the metal from the oxygen necessary to regener-ate a protective oxide layer. An oxygen concentration cell isformed, and serious corrosion may result. Also called an ac-tive-passive cell.
E
ELECTROCHEMICAL CORROSION — Corrosionwhich occurs when current flows between cathodic and an-odic areas on metallic surfaces.
ELECTRODE — A metal or alloy that is in contact withelectrolyte and serves as the site where electricity passes ineither direction between the electrolyte and metal. The cur-rent in the electrode itself is a flow of electrons, whereas, inthe electrolyte, ions carry electric charges and their orderlymovement in solution constitutes a flow of current in theelectrolyte.
ELECTROLYSIS — In the strict sense of the term, elec-trolysis concerns chemical changes in the solution or electro-lyte due to the passage of current. Its relation to corrosionarises only if the corrosion process alters the makeup of thesolution. Hence, since the term is most closely related to thesolution phenomena than to corrosion, its use to indicate cor-rosion should be discouraged.
ELECTROLYTE — Any substance which, in solution orfused, exists as electrically charged ions that render the liq-uid capable of conducting a current. Soluble acids, bases,and salts, such as sea water, are electrolytes.
ELECTROMAGNETIC INTERFERENCE (EMI) — Ra-diation generated from electromagnetic fields which are pro-duced by radar antennas, Radio Frequency (RF) antennas,on-board transmitters, certain poorly designed avionics units,electric motors, and lightning and other natural effects. Thistype of radiation can interfere with aircraft avionics systemscausing electrical malfunctions.
ELECTROMOTIVE FORCE (EMF) SERIES — A list ofelements according to their standard electrode potentials. Themore negative the potential the greater the tendency of themetal to corrode. This series is useful in studies of thermo-dynamic properties, but does not indicate the rates of corro-sion. A hydrogen gas electrode is the standard reference andits potential is designated as zero. All potentials are positiveor negative with respect to the hydrogen electrode. In this
TO 1-1-691
Glossary 2
country, the potentials of zinc and iron are designated asnegative and those of copper and platinum as positive.
EMBRITTLEMENT — Severe loss of ductility of a metalalloy that results in a brittle fashion.
EROSION — Destruction of a metal by the combined ac-tion of corrosion and abrasion or attrition by a liquid or gaswith or without suspended matter.
EXFOLIATION — The breaking away of material from itssurface in flakes or layers.
F
FAYING SURFACES — The common surfaces betweenmating parts.
FILIFORM CORROSION — Corrosion that develops un-der coatings on metals in fine ragged hairlines, usually wavyor curved and randomly distributed.
FILM — A thin layer of material that may or may not bevisible.
FLAMMABLE LIQUID — Any liquid having a flash pointof 100° F or less.
FLASHPOINT — The minimum temperature at which aliquid gives off an ignitable vapor in any one of the closedcup flashpoint testers (Penssky-Martens, Taglibue, or Seta-Flash).
FRETTING CORROSION — Corrosion at the interface oftwo connecting surfaces, usually under high pressure andsubject to very minute slippage due to relative vibration ofsurfaces that ordinarily are not supposed to move relative toeach other, such as a shrink fit.
G
GALVANIC — The flow of direct current between dissimi-lar metals.
GALVANIC CORROSION — The accelerated corrosion ofan active metal caused by the presence of a less active metalin the same solution and in contact with the more activemetal.
GALVANIC SERIES — A list of metals and alloys arrangedin order of their relative potentials in a given environment.The order of their arrangement in this list may be different inother environments.
H
HAZARDOUS MATERIAL — A material which may posea threat to human health or the environment when improp-erly handled or disposed of.
HAZARDOUS WASTE — Waste which is characterized bythe Environmental Protection Agency (EPA) as 1) ignitable,2) corrosive, 3) reactive, or 4) toxic, as defined in 40 CFR261, or is a listed hazardous waste identified in that regula-tion.
HYDROGEN EMBRITTLEMENT — Loss of ductility ofa metal, caused by the entrance or absorption of hydrogenions into the metal, as in the pickling of metal.
I
INHIBITOR — As applied to corrosion, a chemical sub-stance or mixture which, when added in small amounts to asolution, markedly decreases corrosion.
INORGANIC COATINGS — Electroplated coatings, con-version coatings, anodic coatings, phosphate coatings, andoxide coatings.
ION — An electrically charged atom or group of atoms. Thesign of the charge is positive in the case of cations and nega-tive in the case of anions.
L
LOCAL CELL — A cell in which the driving force is dueto a difference in potential between areas on a metal or alloysurface immersed in an electrolyte. The potential differencemay be due to inclusions, lack of homogeneity, varying con-centration of the solution with respect to oxygen or metalions, etc.
M
METAL ION CONCENTRATION CELL — A cell estab-lished on a metal surface due to different concentrations ofits ions in the electrolyte which is in contact with the metal
TO 1-1-691
Glossary 3
surface. These variations in concentration result in local dif-ferences in potential, thus allowing the establishment of alocal cell.
MILL SCALE — The heavy oxide layer formed during hotfabrication or heat treatment of metals. The term is mostfrequently applied to the scale of mixed iron oxides on ironand steel.
MOTTLING — Appearance of spotting or blotches of dif-ferent color or shades of coloring.
N
NOBLE METAL — A metal usually found as an uncom-bined metal in nature. Platinum, gold, and silver are noblemetals.
NON-DESTRUCTIVE INSPECTION — A method usedto check the soundness of a material or a part without im-pairing or destroying the serviceability of the part.
O
ORGANIC COATINGS — Paints, lacquers, plastics,greases, etc.
OXIDATION — Any change involving the loss of electronsby an atom. Any corrosion process involves oxidation of themetal in a true chemical sense. It also may imply the de-struction of metal or alloy as a result of the direct action ofoxygen on the metal, e.g., the scaling of steel at high tem-peratures.
OZONE — A triatomic (O3) form of oxygen.
R
ROOM TEMPERATURE VULCANIZING (RTV) — Aprocess for curing of synthetic rubber or plastic materialswhich occurs at room temperature.
S
SOLVENT — A liquid substance capable of dissolving ordispersing one or more other substances.
T
THIXOTROPIC — Gel-like in physical property.
TITRATION — A method or the process of determining theconcentration of a dissolved substance in terms of the small-est amount of reagent of known concentration required tobring about a given effect or reaction with a known volumeof the test solution.
U
ULTRAVIOLET (UV) LIGHT — Light (electromagneticradiation) of a wavelength shorter than visible light but lon-ger than X-ray radiation. Long wavelength UV from the suncauses sunburn. Short wavelength UV from unfiltered UVlamps can damage unprotected eyes.
UNIFORM SURFACE CORROSION — Corrosive etch-ing of metal involving only the surface.
W
WORDING — The following definitions are adhered to inpreparing this manual:
MAY — is used only when a procedure is optional.
SHALL — is used only when a procedure is mandatory.
SHOULD — is used only when a procedure is recommendedbut not mandatory.
WILL — is used to indicate future action but never to indi-cate a mandatory procedure.
TO 1-1-691
Glossary 4
INDEX
Paragraph, Figure,Subject Table Number
AAIR INTAKE DUCTS FOR JET AIRCRAFT. . . . . . 7.15AIRCRAFT CLEANING. . . . . . . . . . . . . . . . . . . . 10.6
Assembled RPA . . . . . . . . . . . . . . . . . . . . . 10.6.1.1Disassembled and Container Stored RPAs . . . . 10.6.1.2Frequency of Cleaning . . . . . . . . . . . . . . . . . . 10.6.1Wipe Down or Spot Cleaning . . . . . . . . . . . . . 10.6.2Wipe Down or Spot Cleaning Method . . . . . . 10.6.2.1
APPLICATION OF POLISH AND WAX . . . . . . . . . 3.8APPLICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . 6.2APPROVED CLEANING COMPOUNDS . . . . . . . . 10.5
A-A-59921 (Formerly MIL-C-43616), Class 1A Emul-sion Cleaner . . . . . . . . . . . . . . . . . . . . . . . . . 10.5.3MIL-PRF-87937, Type III and MIL-PRF-85570, TypeV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.5.2MIL-PRF-87937, Type IV and MIL-PRF-85570, TypeII . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.5.1
BBATTERY COMPARTMENTS, BOXES, AND ADJA-CENT AREAS . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.2
Boric Acid and/or Monobasic Sodium Phosphate Neu-tralizing Solutions . . . . . . . . . . . . . . . . . . . . . 7.2.1.4Bromothymol Blue Indicating Solution. . . . . . . 7.2.1.2Cleaning and Neutralizing Procedures. . . . . . . . . 7.2.2Litmus Indicating Solution . . . . . . . . . . . . . . . 7.2.1.1Paint Systems . . . . . . . . . . . . . . . . . . . . . . . . . 7.2.3Preparation of Solutions for Cleaning and NeutralizingBattery Electrolytes . . . . . . . . . . . . . . . . . . . . . 7.2.1Sodium Bicarbonate Neutralizing Solution . . . . 7.2.1.3
BERYLLIUM-COPPER ALLOYS, BERYLLIUM-ALU-MINUM ALLOYS, AND BERYLLIUM OXIDE . . . 7.20
Corrosion Removal and Treatment . . . . . . . . . . 7.20.1Depot Maintenance . . . . . . . . . . . . . . . . . . . . 7.20.2
CCARBON FIBER COMPOSITES ANDCORROSION . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.3
Corrosion Concerns . . . . . . . . . . . . . . . . . . . . 10.3.1Moisture Absorption. . . . . . . . . . . . . . . . . . . . 10.3.2
CHEMICAL DEFINITIONS . . . . . . . . . . . . . . . . . . 2.3Atom. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3.1Electrolyte . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3.4Electron . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3.2Ions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.3.3
CLEANING COMPOUNDS . . . . . . . . . . . . . . . . . . 3.3A-A-59921, (Formerly MIL-C-43616), Class1A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.2.2Aliphatic Naphtha . . . . . . . . . . . . . . . . . . . . . 3.3.4.4Alkaline Cleaners . . . . . . . . . . . . . . . . . . . . . . 3.3.1Aqueous Parts Washer Cleaning Solutions . . . . . . 3.3.3
Paragraph, Figure,Subject Table Number
ASTM D 740 Methyl Ethyl Ketone (MEK) . . . 3.3.4.3Cleaning of Specific Areas and Components . . . . T 3-2Deicing/Anti-Icing Fluid Residue Inspection and Clean-ing Procedures . . . . . . . . . . . . . . . . . . . . . . . . T 3-3Dilution . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.7General Disinfectants. . . . . . . . . . . . . . . . . . . 3.3.5.1MIL-PRF-680 Degreasing Solvent and A-A-59601 DryCleaning and Degreasing Solvent, P-D-680. . . . 3.3.4.1MIL-PRF-85570, Type III . . . . . . . . . . . . . . . 3.3.1.6MIL-PRF-85570, Type IV . . . . . . . . . . . . . . . 3.3.1.5MIL-PRF-85704, Type I. . . . . . . . . . . . . . . . . 3.3.2.1MIL-PRF-87937, Type I and MIL-PRF-85570, TypeI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.1.1MIL-PRF-87937, Type III and MIL-PRF-85570, TypeV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.1.3MIL-PRF-87937, Type IV . . . . . . . . . . . . . . . 3.3.1.4MIL-PRF-87937, Type IV and MIL-PRF-85570, TypeII . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.1.2MIL-T-81772, Type I (Polyurethane) and Type II (Ep-oxy) Thinner . . . . . . . . . . . . . . . . . . . . . . . . 3.3.4.5Miscellaneous Cleaning Agents . . . . . . . . . . . . . 3.3.5Solvent Emulsion and Aqueous Cleaners for TurbineEngine Gas Path and General Area Cleaning . . . . 3.3.2Solvents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3.4Steam Cleaning. . . . . . . . . . . . . . . . . . . . . . . . 3.3.6TT-I-735 Isopropyl Alcohol . . . . . . . . . . . . . . 3.3.4.2
CLEANING EQUIPMENT . . . . . . . . . . . . . . . . . . . 3.4Aqueous Parts Washers . . . . . . . . . . . . . . . . . . 3.4.9Determination of Capacity of the Aqueous PartsWasher . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.9.2Effectiveness of Cleaning in Aqueous PartsWashers. . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.9.1Foam Generating Cleaning Unit (15 Gallons) . . . F 3-1Foam Generating Cleaning Unit (45 Gallons) . . . F 3-2Front Loading Type . . . . . . . . . . . . . . . . . . . . F 3-5High Pressure/Hot Water Wash Equipment . . . . . 3.4.1Miscellaneous Equipment . . . . . . . . . . . . . . . . 3.4.10Miscellaneous Large Cleaning Equipment . . . . . . 3.4.5Pneumatic Vacuum Cleaner. . . . . . . . . . . . . . . . 3.4.7Portable, 15 Gallon, Foam Generating, CleaningUnit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.2Portable, 45 Gallon, Foam Generating CleaningUnit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.3Spray Cleaning Guns for Solvents . . . . . . . . . . . 3.4.6Top Loading Type. . . . . . . . . . . . . . . . . . . . . . F 3-4Turbine Engine Compressor CleaningEquipment . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.4.4Universal Wash Unit . . . . . . . . . . . . . . . . . . . . F 3-3Universal Wash Unit . . . . . . . . . . . . . . . . . . . . 3.4.8
CLEANING PROCEDURES . . . . . . . . . . . . . . . . . . 3.5
TO 1-1-691
Change 18 Index 1
Paragraph, Figure,Subject Table Number
Aircraft Cleaning Procedure . . . . . . . . . . . . . . . F 3-7Alkaline Detergent and/or Solvent Emulsion Cleaning,Painted and Unpainted Surfaces; Fresh Water ReadilyAvailable . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.2.1Alkaline Detergent Cleaning with Only Limited FreshWater Available . . . . . . . . . . . . . . . . . . . . . . 3.5.2.3Application . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.7.2Automatic Water Spray Nozzle . . . . . . . . . . . . . F 3-8Bird Strike Cleaning . . . . . . . . . . . . . . . . . . . . 3.5.8Bird Strike Cleanup. . . . . . . . . . . . . . . . . . . . 3.5.8.1Bodily Fluid Cleanup . . . . . . . . . . . . . . . . . . 3.5.9.2Bodily Fluid Containment During Flight. . . . . . 3.5.9.1Bodily Fluids Contamination Cleanup. . . . . . . . . 3.5.9Cleaning Methods . . . . . . . . . . . . . . . . . . . . . . 3.5.2Clear Water Rinsing of Aircraft . . . . . . . . . . . . . 3.5.3Disinfection of Contaminated Areas . . . . . . . . . 3.5.9.3Electrical . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.1.1Fungus Growth Removal . . . . . . . . . . . . . . . . . 3.5.6Fungus Growth Removal from OrganicMaterials . . . . . . . . . . . . . . . . . . . . . . . . . . T 3-4.1Interior Cleaning (Vacuum) . . . . . . . . . . . . . . 3.5.2.5Internal/Enclosed (Water Sensitive) AreaCleanup. . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.8.2Low Temperature Cleaning. . . . . . . . . . . . . . . 3.5.2.6Manual Application . . . . . . . . . . . . . . . . . . . . 3.5.3.3Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.7.1Oxygen Systems . . . . . . . . . . . . . . . . . . . . . . 3.5.1.6Personal Protection . . . . . . . . . . . . . . . . . . . . 3.5.1.2Post Cleaning Procedures . . . . . . . . . . . . . . . . . 3.5.4Post Cleaning Task Sequence . . . . . . . . . . . . . 3.5.4.1Pre-Wash Lubrication Point Protection . . . . . . . 3.5.1.9Preparation for Cleaning . . . . . . . . . . . . . . . . 3.5.1.8Recommended Dilution of Low TemperatureCleaner . . . . . . . . . . . . . . . . . . . . . . . . . . . . . T 3-4Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.7.3Requirements . . . . . . . . . . . . . . . . . . . . . . . . 3.5.3.1Rinsing Procedures . . . . . . . . . . . . . . . . . . . . 3.5.3.4Soil Barriers . . . . . . . . . . . . . . . . . . . . . . . . . . 3.5.7Solvent Cleaning. . . . . . . . . . . . . . . . . . . . . . 3.5.2.4Special Precautions . . . . . . . . . . . . . . . . . . . . 3.5.1.7Taxi-Through Rinsing . . . . . . . . . . . . . . . . . . 3.5.3.2Treatment and Disposal of Wash Rack Waste. . . . 3.5.5Use of Aircraft Washing Applicator . . . . . . . . . . F 3-6Use of Cleaners . . . . . . . . . . . . . . . . . . . . . . 3.5.1.4Use of Solvents . . . . . . . . . . . . . . . . . . . . . . 3.5.1.3Warnings and Cautions. . . . . . . . . . . . . . . . . . . 3.5.1Water Intrusion. . . . . . . . . . . . . . . . . . . . . . . 3.5.1.5Water/Cleaning Compound Intrusion . . . . . . . 3.5.1.10Waterless Wipe Down . . . . . . . . . . . . . . . . . . 3.5.2.2
CLOSELY COILED SPRINGS . . . . . . . . . . . . . . . 7.16COMMON AREAS . . . . . . . . . . . . . . . . . . . . . . . . 4.5
Battery Compartment. . . . . . . . . . . . . . . . . . . F 4-25Battery Compartments and Battery VentOpenings . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.14Bilge Areas. . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.13
Paragraph, Figure,Subject Table Number
Bilge Areas . . . . . . . . . . . . . . . . . . . . . . . . . F 4-24Common Water Entrapment Areas . . . . . . . . . . F 4-23Control Cables . . . . . . . . . . . . . . . . . . . . . . . 4.5.10Control Cables . . . . . . . . . . . . . . . . . . . . . . . F 4-21Corrosion Around Fasteners . . . . . . . . . . . . . . . F 4-6Corrosion in Air Intake Duct . . . . . . . . . . . . . F 4-17Corrosion Prone Point of Air Inlet . . . . . . . . . . F 4-16Electrical Connectors and Other Components . . . 4.5.16Engine Exhaust and Gun Gas ImpingementAreas. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.4Engine Frontal Areas and Air Inlet Ducts . . . . . . 4.5.7Exhaust Trail Area Corrosion Points. . . . . . . . . F 4-11F-15 Nose Landing Gear Wheel Well . . . . . . . . F 4-12Fasteners . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.1Faying Surfaces and Crevices . . . . . . . . . . . . . . 4.5.2Flap and Slat Recesses . . . . . . . . . . . . . . . . . . . 4.5.6Flaps Lowered to Expose Recess Areas . . . . . . F 4-13Galvanic Corrosion of Aluminum Adjacent to SteelFasteners . . . . . . . . . . . . . . . . . . . . . . . . . . . . F 4-7Gun Blast Area Corrosion Points . . . . . . . . . . . F 4-10Hinge Corrosion Points . . . . . . . . . . . . . . . . . F 4-19Hinges . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.5.9Jet Engine Frontal Area Corrosion Points . . . . . F 4-15Magnesium Parts . . . . . . . . . . . . . . . . . . . . . . 4.5.15Personnel Relief Tube Vent. . . . . . . . . . . . . . . F 4-22Piano Hinge Lugs . . . . . . . . . . . . . . . . . . . . . F 4-20Reciprocating Engine Frontal Area CorrosionPoints . . . . . . . . . . . . . . . . . . . . . . . . . . . . . F 4-14Relief Tube Outlets . . . . . . . . . . . . . . . . . . . . 4.5.11Spot Weld Corrosion . . . . . . . . . . . . . . . . . . . . F 4-8Spot Welded Assemblies. . . . . . . . . . . . . . . . . . 4.5.3Spot Welded Skin Corrosion Mechanism . . . . . . F 4-9Water Entrapment Areas . . . . . . . . . . . . . . . . . 4.5.12Wheel Wells and Landing Gear . . . . . . . . . . . . . 4.5.5Wing Fold Joint . . . . . . . . . . . . . . . . . . . . . . F 4-18Wing/Fin-Fold Joints and Wing and Control SurfaceLeading Edges . . . . . . . . . . . . . . . . . . . . . . . . 4.5.8
CORRECTIVE ACTIONS. . . . . . . . . . . . . . . . . . . . 5.3CORROSION CONTROL PROGRAM . . . . . . . . . . . 1.1
Facilities . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.1.3Maintenance . . . . . . . . . . . . . . . . . . . . . . . . . . 1.1.2Training . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.1.1
CORROSION CONTROL PROGRAM . . . . . . . . . . 10.2CORROSION PREVENTION ON ASSEMBLIES ANDPARTS REMOVED FROM AIRCRAFT DURING MAIN-TENANCE, 30 DAY SHORT TERM STORAGE, ANDOVER 30 DAY LONG TERM STORAGEREQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . 7.17
Long Term Storage . . . . . . . . . . . . . . . . . . . . 7.17.2Short Term Storage . . . . . . . . . . . . . . . . . . . . 7.17.1
CORROSION PREVENTIVE COMPOUNDS(CPC’s) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.5
Recommended CPC’s. . . . . . . . . . . . . . . . . . . . 9.5.1CORROSION REMOVAL . . . . . . . . . . . . . . . . . . . 5.5
3M Co. Inline Bristle Disc . . . . . . . . . . . . . . . . F 5-5
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Index 2 Change 17
Paragraph, Figure,Subject Table Number
3M Co. Radial Bristle Disc . . . . . . . . . . . . . . . F 5-33M Co. Roloc Discs . . . . . . . . . . . . . . . . . . . . F 5-43M Co. RolocTM Disc and Radial DiscAbrasives. . . . . . . . . . . . . . . . . . . . . . . . . . . 5.5.3.83M Co. Scotch-BriteTM Flap Brush andMandrel . . . . . . . . . . . . . . . . . . . . . . . . . . . . F 5-13M Co. Scotch-BriteTM Finishing FlapBrushes . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.5.3.3Abrasive Blasting . . . . . . . . . . . . . . . . . . . . . . 5.5.4Abrasive Blasting Equipment . . . . . . . . . . . . . . F 5-6Abrasive Cloth . . . . . . . . . . . . . . . . . . . . . . . 5.5.2.2Abrasive Cloth and Paper. . . . . . . . . . . . . . . . 5.5.3.5Abrasive Flap Wheels . . . . . . . . . . . . . . . . . . 5.5.3.4Abrasive Flap Wheels with Spindle Mount . . . . . F 5-2Abrasive Mats . . . . . . . . . . . . . . . . . . . . . . . 5.5.2.1Abrasive Paper . . . . . . . . . . . . . . . . . . . . . . . 5.5.2.3Conventional Equipment . . . . . . . . . . . . . . . . 5.5.4.1Grades of Abrasive Mats . . . . . . . . . . . . . . . . . T 5-1Grades of Steel Wool . . . . . . . . . . . . . . . . . . . T 5-2Material Compatibility . . . . . . . . . . . . . . . . . . 5.5.1.2Mechanical Compatibility. . . . . . . . . . . . . . . . 5.5.1.1Mechanical Methods . . . . . . . . . . . . . . . . . . . . 5.5.1Metallic Wools . . . . . . . . . . . . . . . . . . . . . . . 5.5.2.4Non-Powered Tools and Materials . . . . . . . . . . . 5.5.2Pneumatic Drill Motors . . . . . . . . . . . . . . . . . 5.5.3.1Pneumatic Sanders . . . . . . . . . . . . . . . . . . . . 5.5.3.2Portable Vacuum Abrasive Blast Equipment . . . 5.5.4.2Power Tools and Materials . . . . . . . . . . . . . . . . 5.5.3Powered Wire Brushes. . . . . . . . . . . . . . . . . . 5.5.3.6Pumice Powder. . . . . . . . . . . . . . . . . . . . . . . 5.5.2.6Recommended Non-Powered Abrasives for CorrosionRemoval . . . . . . . . . . . . . . . . . . . . . . . . . . . . T 5-4Recommended Powered Abrasives for CorrosionRemoval . . . . . . . . . . . . . . . . . . . . . . . . . . . . T 5-3Rotary Files . . . . . . . . . . . . . . . . . . . . . . . . . 5.5.3.7Scrapers . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.5.2.7Wet Abrasive Blasting Equipment . . . . . . . . . . 5.5.4.3Wire Brushes . . . . . . . . . . . . . . . . . . . . . . . . 5.5.2.5
CORROSION REMOVAL-CHEMICAL . . . . . . . . . . 5.9Aluminum Alloys . . . . . . . . . . . . . . . . . . . . . . 5.9.1Application of Organic Coatings . . . . . . . . . . . 5.9.1.3Application of Organic Coatings . . . . . . . . . . . 5.9.2.3Application of Organic Coatings . . . . . . . . . . . 5.9.3.3Application of Organic Coatings . . . . . . . . . . . 5.9.4.4Application of Organic Coatings . . . . . . . . . . . 5.9.5.3Application of Organic Coatings . . . . . . . . . . . 5.9.6.3Application of Organic Coatings . . . . . . . . . . . 5.9.7.5Chemical Corrosion Removal Materials for AluminumAlloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.1.2Chemical Corrosion Removal Materials for MagnesiumAlloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.2.2Chemical Corrosion Removal Materials for Titaniumand Titanium Based Alloys. . . . . . . . . . . . . . . 5.9.6.2Chemical Corrosion Removing Materials for Copperand Copper Based Alloys . . . . . . . . . . . . . . . . 5.9.5.2
Paragraph, Figure,Subject Table Number
Chemical Corrosion Removing Materials for FerrousMetal Alloys Other Than Stainless Steels(CRES) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.3.2Chemical Corrosion Removing Materials for StainlessSteel (CRES) and Nickel Based Alloys. . . . . . . 5.9.4.2Control of Corrosion Removal/Pickling Action of Ni-tric-Acid-Hydrofluoric Solutions . . . . . . . . . . . . T 5-9Copper and Copper Based Alloys. . . . . . . . . . . . 5.9.5Ferrous Metal (Steel) Alloys Other Than StainlessSteels (CRES). . . . . . . . . . . . . . . . . . . . . . . . . 5.9.3Magnesium Alloys. . . . . . . . . . . . . . . . . . . . . . 5.9.2Passivation of Stainless Steel (CRES) AlloyParts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.4.3Plated and Phosphated Surfaces . . . . . . . . . . . . . 5.9.7Preparation . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.1.1Preparation . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.2.1Preparation . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.3.1Preparation . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.4.1Preparation . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.5.1Preparation . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.6.1Preparation . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.7.1Stainless Steel (CRES) and Nickel BasedAlloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.4Titanium and Titanium Based Alloys . . . . . . . . . 5.9.6Treatment of Corroded Areas on Cadmium or ZincPlated Surfaces . . . . . . . . . . . . . . . . . . . . . . . 5.9.7.2Treatment of Corroded Areas on PhosphatedSurfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.9.7.4Treatment of Corroded Areas on Plated Surfaces ExceptCadmium or Zinc Plating . . . . . . . . . . . . . . . . 5.9.7.3Typical Chemical Corrosion Removal of Titanium andTitanium Base Alloys . . . . . . . . . . . . . . . . . . T 5-11Typical Chemical Corrosion Removal Procedures forAluminum Alloy Parts and Assemblies. . . . . . . . T 5-5Typical Chemical Corrosion Removal Procedures forCopper and Copper Alloys . . . . . . . . . . . . . . . T 5-10Typical Chemical Corrosion Removal Procedures forFerrous Metals Other Than Stainless Steel(CRES) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . T 5-7Typical Chemical Corrosion Removal Procedures forMagnesium Alloys . . . . . . . . . . . . . . . . . . . . . T 5-6Typical Chemical Corrosion Removal Procedures forPlated and Phosphated Surfaces . . . . . . . . . . . T 5-12Typical Chemical Corrosion Removal Procedures forStainless Steel (CRES) and Nickel BasedAlloys. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . T 5-8
CORROSION REMOVAL FROM THIN METAL (0.0625INCH THICKNESS AND LESS) . . . . . . . . . . . . . . 7.14CORROSION REMOVALPROCEDURES-MECHANICAL . . . . . . . . . . . . . . . 5.8
Abrasive Blasting Corrosion Removal . . . . . . . . 5.8.4Abrasive Blasting Procedures . . . . . . . . . . . . . 5.8.4.1Acceptable Clean-Up of Pitting Corrosion on CriticalStructure . . . . . . . . . . . . . . . . . . . . . . . . . . . . F 5-8Limited Clearance. . . . . . . . . . . . . . . . . . . . . . F 5-9
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Change 17 Index 3
Paragraph, Figure,Subject Table Number
Mechanical Damage . . . . . . . . . . . . . . . . . . . 5.8.1.2Non-Powered Mechanical Corrosion Removal . . . 5.8.2Personal Protection . . . . . . . . . . . . . . . . . . . . 5.8.1.1Powered Mechanical Corrosion Removal . . . . . . 5.8.3Shaping Reworked Areas . . . . . . . . . . . . . . . . . F 5-7Warnings and Cautions. . . . . . . . . . . . . . . . . . . 5.8.1
CORROSION TREATMENT FOR STEELCABLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.4CORROSIVE ENVIRONMENTS. . . . . . . . . . . . . . . 2.9
Animal Damage . . . . . . . . . . . . . . . . . . . . . . 2.9.14Bacteria . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.15.1Climate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.8Condensed Moisture . . . . . . . . . . . . . . . . . . . 2.9.1.1Desert . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.8.1Effect of Moisture . . . . . . . . . . . . . . . . . . . . . 2.9.1.2Factors of Influence in Tropical Environments . . . 2.9.9Failed Chromium Plating . . . . . . . . . . . . . . . . F 2-23Industrial and Ship Emitted Air Pollutants . . . . . 2.9.13Manufacturing . . . . . . . . . . . . . . . . . . . . . . . . 2.9.10Microbial Growth Requirements . . . . . . . . . . 2.9.15.2Microbial Nutrients . . . . . . . . . . . . . . . . . . . 2.9.15.3Microorganisms . . . . . . . . . . . . . . . . . . . . . . . 2.9.15Moisture . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.1Other Industrial Pollutants . . . . . . . . . . . . . . . . 2.9.5Ozone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.4Salt Atmospheres. . . . . . . . . . . . . . . . . . . . . . . 2.9.3Sand, Dust, and Volcanic Ash . . . . . . . . . . . . . . 2.9.6Shipment . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.12Solar Radiation . . . . . . . . . . . . . . . . . . . . . . . . 2.9.7Storage. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.11Temperate Zones. . . . . . . . . . . . . . . . . . . . . . 2.9.8.2Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.2Tropics . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.9.8.3
CORROSIVE ENVIRONMENTS. . . . . . . . . . . . . . 10.4
DDEFINITION OF CORROSION . . . . . . . . . . . . . . . 2.2DEGRADATION OF NON-METALS . . . . . . . . . . . 2.10DEGREES OF CORROSION . . . . . . . . . . . . . . . . . 4.4
Light Corrosion. . . . . . . . . . . . . . . . . . . . . . . . 4.4.1Moderate Corrosion . . . . . . . . . . . . . . . . . . . . . 4.4.2Optical Depth Micrometer (Analog Mechanical ReadOut Type) . . . . . . . . . . . . . . . . . . . . . . . . . . . F 4-3Optical Depth Micrometer (Digital Read OutType) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . F 4-4Severe Corrosion. . . . . . . . . . . . . . . . . . . . . . . 4.4.3Typical Use of a Straight Edge to Determine if SuspectAreas Have Been Previously Reworked . . . . . . . F 4-5
DEPLETED URANIUM COUNTERWEIGHTS . . . . 7.18Corrosion and Finish Damage TreatmentProcedures . . . . . . . . . . . . . . . . . . . . . . . . . . 7.18.1
DEVELOPMENT OF CORROSION. . . . . . . . . . . . . 2.5Corrosion Under Painted Surfaces . . . . . . . . . . . 2.5.1
Paragraph, Figure,Subject Table Number
EELECTRICAL AND ELECTRONICEQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.11
Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.11.6Conduit and Junction Boxes . . . . . . . . . . . . . . 7.11.2Deleted . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.11.4Grounding and Bonding Connections . . . . . . . . 7.11.1Moisture and Fungus Proofing of Electrical and Elec-tronic Equipment . . . . . . . . . . . . . . . . . . . . . . 7.11.5Wires and Cables . . . . . . . . . . . . . . . . . . . . . . 7.11.3
EMERGENCY PREPARATIONS . . . . . . . . . . . . . . . 8.3Emergency Reclamation Equipment . . . . . . . . . . 8.3.3Emergency Reclamation Team. . . . . . . . . . . . . . 8.3.2Personal Protection . . . . . . . . . . . . . . . . . . . . 8.3.2.1Personnel Decontamination. . . . . . . . . . . . . . . 8.3.2.2Priority Removal List of Equipment and/orComponents . . . . . . . . . . . . . . . . . . . . . . . . . . 8.3.1Production Planning. . . . . . . . . . . . . . . . . . . . . 8.3.4
EMI SEALS AND GASKETS . . . . . . . . . . . . . . . . 7.21Beryllium-Copper Spiral Contact with EnvironmentalFluorosilicone Seal . . . . . . . . . . . . . . . . . . . . . F 7-1Bonding Cable from Airframe to Graphite/Epoxy Avi-onics Bay Door . . . . . . . . . . . . . . . . . . . . . . . F 7-4Dorsal Longeron EMI Seal. . . . . . . . . . . . . . . . F 7-2EMI Bonding Washers in an Avionics Bay . . . . . F 7-5Stainless Steel (CRES) EMI Screen . . . . . . . . . . F 7-3Treatment of EMI Seals and Gaskets . . . . . . . . 7.21.1
EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.4Application Nozzles. . . . . . . . . . . . . . . . . . . . . 6.4.2Injection Gun . . . . . . . . . . . . . . . . . . . . . . . . . 6.4.3Sealant Gun . . . . . . . . . . . . . . . . . . . . . . . . . . 6.4.1Sealant Kits (Semkits®) . . . . . . . . . . . . . . . . . . 6.4.4Sealant Removal and Application Tools . . . . . . . 6.4.5
EVALUATION OF CORROSION DAMAGE. . . . . . . 4.3
FFACTORS INFLUENCE CORROSION . . . . . . . . . . 2.6
Anode and Cathode Surface Area. . . . . . . . . . . . 2.6.3Biological Organisms . . . . . . . . . . . . . . . . . . . . 2.6.9Dissimilar Metal Coupling (GalvanicCorrosion) . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.2Effect of Area Relationship in Dissimilar MetalContacts . . . . . . . . . . . . . . . . . . . . . . . . . . . . F 2-5Effect of Sea Water on Galvanic Corrosion . . . . . F 2-3Electrolyte Concentration . . . . . . . . . . . . . . . . . 2.6.8Electrolytes . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.6Elimination of Corrosion by Application of an OrganicFilm to a Metal Surface. . . . . . . . . . . . . . . . . . F 2-2Galvanic Corrosion in a Flashlight Battery . . . . . F 2-4Heat Treatment and Grain Direction . . . . . . . . . . 2.6.5Mechanical Stress . . . . . . . . . . . . . . . . . . . . . 2.6.10
TO 1-1-691
INDEX - CONTINUED
Index 4 Change 17
Paragraph, Figure,Subject Table Number
Oxygen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.7Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.4
TO 1-1-691
INDEX - CONTINUED
Change 9 Index 4.1/(Index 4.2 blank)
Paragraph, Figure,Subject Table Number
Time . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.11Type of Metal . . . . . . . . . . . . . . . . . . . . . . . . . 2.6.1
FAYING SURFACES AND ATTACHMENTPOINTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.7
Attaching Parts and Hardware . . . . . . . . . . . . . . 7.7.2Faying Surfaces, Joints, and Seams . . . . . . . . . . 7.7.1Severely Corroded (Rusted) Hardware . . . . . . . . 7.7.3
GGENERAL CLEANING PROCEDURES . . . . . . . . . 8.5
Alternate Methods . . . . . . . . . . . . . . . . . . . . . . 8.5.2Method One (Preferred) . . . . . . . . . . . . . . . . . 8.5.2.1Method Two (Alternate). . . . . . . . . . . . . . . . . 8.5.2.2Primary Method . . . . . . . . . . . . . . . . . . . . . . . 8.5.1Removal of Carbon Dioxide (CO2), HFC-125, Halonand 3M NOVEC 1230 Fire ExtinguishingAgents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.5.5Removal of Protein Type Foam and Soda-Acid FireExtinguishing Agents . . . . . . . . . . . . . . . . . . . . 8.5.6Removing Fire Extinguishing Powder (O-D-1407 Potas-sium Bicarbonate [Purple K{PKP}], Sodium Bicarbon-ate, Ammonium Phosphate Monobasic) and/or OtherDry Chemical Agents . . . . . . . . . . . . . . . . . . . . 8.5.3Removing MIL-F-24385 Aqueous Film Forming Foam(AFFF) Fire Extinguishing Agent and Other SyntheticBased Foaming Agents Including High-Expansion (Hi-Ex) Foams . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.5.4Treatment After Exposure to Volcanic Ash . . . . . 8.5.8Treatment After Landing on a FoamedRunway . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.5.7
GENERAL PROCEDURES. . . . . . . . . . . . . . . . . . . 8.4Aircraft Involved in Water Crashes . . . . . . . . . 8.4.2.1Clean. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.4.3Disassembly/Removal of Components . . . . . . . . 8.4.2Priority Guide for Emergency Treatment of Aircraft,Missiles, and Equipment . . . . . . . . . . . . . . . . . T 8-1Removal of Contaminated InstalledEquipment . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.4.1Suggested List of Emergency ReclamationItems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . T 8-2Tagging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.4.4
IINSPECTION METHODS . . . . . . . . . . . . . . . . . . . 4.2
Analog Mechanical Read-Out Type . . . . . . . . . 4.2.4.1Depth Dimension of Corrosion Pits . . . . . . . . . . F 4-1Depth Gauge . . . . . . . . . . . . . . . . . . . . . . . . . 4.2.2Digital Read-Out Type. . . . . . . . . . . . . . . . . . 4.2.4.2Eddy Current Inspection . . . . . . . . . . . . . . . . . . 4.2.6Evidence of Corrosion . . . . . . . . . . . . . . . . . . 4.2.1.1Fiber Optic Borescope . . . . . . . . . . . . . . . . . . . F 4-2Fluorescent Penetrant Inspection . . . . . . . . . . . . 4.2.5Limitations of Penetrant Inspection . . . . . . . . . 4.2.5.1
Paragraph, Figure,Subject Table Number
NDI Inspection Tools for Various Types ofCorrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . T 4-1Optical Depth Micrometers . . . . . . . . . . . . . . . . 4.2.4Radiographic Inspection . . . . . . . . . . . . . . . . . . 4.2.8Ultrasonic Inspection . . . . . . . . . . . . . . . . . . . . 4.2.7Use of Depth Gauges . . . . . . . . . . . . . . . . . . 4.2.2.1Visual inspection . . . . . . . . . . . . . . . . . . . . . . . 4.2.1Visual Inspection with aBorescope/Videoscope . . . . . . . . . . . . . . . . . . . 4.2.3
INTEGRAL AND EXTERNAL FUEL TANKS ANDDROP TANKS . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.6
Corrosion Removal and Rework of Pitted Areas of Inte-gral Fuel Tanks . . . . . . . . . . . . . . . . . . . . . . . . 7.6.1Removal of Corrosion and Rework of Aluminum Exter-nal Fuel Tanks/Drop Tanks . . . . . . . . . . . . . . . . 7.6.2Tank Exterior Surfaces. . . . . . . . . . . . . . . . . . 7.6.2.1Tank Interior Surfaces . . . . . . . . . . . . . . . . . . 7.6.2.2
INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . 3.2Aircraft Clear Water Rinse (CWR)Requirements . . . . . . . . . . . . . . . . . . . . . . . . . 3.2.3Aircraft Stationed Within 1.25 Miles of SaltWater . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.2.3.1Cleaning Frequency. . . . . . . . . . . . . . . . . . . . 3.2.2.1Deployed Aircraft Wash Requirements . . . . . . . . 3.2.5Immediate Cleaning . . . . . . . . . . . . . . . . . . . . . 3.2.4Low Level (Below 3,000 Feet) Salt Water RunwayApproach. . . . . . . . . . . . . . . . . . . . . . . . . . . 3.2.3.2Reasons for Cleaning . . . . . . . . . . . . . . . . . . . . 3.2.1Search, Rescue, and Recovery Missions and Low-LevelFlight Operations Under 3,000 Feet . . . . . . . . . 3.2.3.3When to Accomplish Work . . . . . . . . . . . . . . . . 3.2.2
INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . 3.6Application of Conventional Lubricants . . . . . . . 3.6.3Common Military Greases and Their Uses . . . . . T 3-5Conventional Lubricants . . . . . . . . . . . . . . . . . . 3.6.1Grease Gun Application . . . . . . . . . . . . . . . . . 3.6.3.1MIL-PRF-46147 and/or MIL-L-23398 . . . . . . . 3.6.2.3SAE AS5272 (MIL-PRF-46010) . . . . . . . . . . . 3.6.2.2Solid Film Lubricants. . . . . . . . . . . . . . . . . . . . 3.6.2Surface Preparation for Solid Film Lubricants . . 3.6.2.1
INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . 3.7Brushing . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7.7.1Corrosion Preventive Compounds . . . . . . . . . . . T 3-7Description of CPC’s . . . . . . . . . . . . . . . . . . . . 3.7.5Dipping . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7.7.2MIL-DTL-85054, Corrosion Preventive Compound,Clear. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7.5.2MIL-PRF-16173, Corrosion Preventive Compound, Sol-vent Cutback, Cold Application. . . . . . . . . . . . 3.7.5.3MIL-PRF-32033, Lubricating Oil, General Purpose,Preservative, Water Displacing . . . . . . . . . . . . 3.7.5.5MIL-PRF-63460, Lubricant, Cleaner, and Preservativefor Weapons and Weapon Systems. . . . . . . . . . 3.7.5.4
TO 1-1-691
INDEX - CONTINUED
Change 17 Index 5
Paragraph, Figure,Subject Table Number
MIL-PRF-81309, Corrosion Preventive Compound, Wa-ter Displacing, Ultra Thin Film and MIL-L-87177, Lu-bricants, Corrosion Preventive, Water Displacing,Synthetic . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7.5.1Non-Operational Preservation . . . . . . . . . . . . . . 3.7.2Non-Water Displacing Compounds . . . . . . . . . 3.7.3.2Operational Preservation. . . . . . . . . . . . . . . . . . 3.7.1Preservation Application Methods . . . . . . . . . . . 3.7.7Preservation of Specific Areas . . . . . . . . . . . . . . 3.7.6Preservation of Specific Areas andComponents. . . . . . . . . . . . . . . . . . . . . . . . . . T 3-8Spraying . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.7.7.3Time Limitations for CPC’s . . . . . . . . . . . . . . . T 3-6Time Limitations of CPC’s . . . . . . . . . . . . . . . . 3.7.4Types of CPC’s. . . . . . . . . . . . . . . . . . . . . . . . 3.7.3Water Displacing Compounds . . . . . . . . . . . . . 3.7.3.1
INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . 7.1INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . 9.1
Aircraft Clear Water Rinse (CWR) . . . . . . . . . . . 9.1.3Aircraft Wash . . . . . . . . . . . . . . . . . . . . . . . . . 9.1.2Climatic Conditions . . . . . . . . . . . . . . . . . . . . . 9.1.1Effects of Desert Environment . . . . . . . . . . . . . . 9.1.4
INTRODUCTION. . . . . . . . . . . . . . . . . . . . . . . . . A.1Consumable Materials. . . . . . . . . . . . . . . . . . . T A-2Consumable Materials Containers . . . . . . . . . . . A.1.2Local Environmental Laws and Regulations . . . . A.1.4Local Purchase . . . . . . . . . . . . . . . . . . . . . . . . A.1.3Shelf Life . . . . . . . . . . . . . . . . . . . . . . . . . . . A.1.1Unit of Issue Codes . . . . . . . . . . . . . . . . . . . . A.1.5Unit of Issue Codes . . . . . . . . . . . . . . . . . . . . T A-1
INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . B.1Back Mounted Full Facepiece Respirator . . . . . . F B-1Equipment for Cleaning and Corrosion Prevention andControl. . . . . . . . . . . . . . . . . . . . . . . . . . . . . T B-2Front Mounted Full Facepiece Respirator. . . . . . F B-2Hooded Air Respirator System . . . . . . . . . . . . . F B-3Unit of Issue Codes. . . . . . . . . . . . . . . . . . . . . B.1.1Unit of Issue Codes . . . . . . . . . . . . . . . . . . . . T B-1
INTRODUCTION TO CORROSION THEORY . . . . . 2.1
MMATERIALS . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.3METALS AFFECTED BY CORROSION . . . . . . . . . 2.8
Aluminum . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.3Aluminum Surface Corrosion Products . . . . . . . F 2-21Anodized Aluminum . . . . . . . . . . . . . . . . . . . . 2.8.4Cadmium . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.7Cadmium Plated Surface Conditions . . . . . . . . F 2-22Copper and Copper Alloys . . . . . . . . . . . . . . . . 2.8.6Corrosion of Metals - Type of Attack and Appearanceof Corrosion Products . . . . . . . . . . . . . . . . . . . T 2-1CRES/Stainless Steel . . . . . . . . . . . . . . . . . . . . 2.8.8Graphite/Carbon Fiber Composites . . . . . . . . . . 2.8.11
Paragraph, Figure,Subject Table Number
Magnesium. . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.1Magnesium Corrosion Products . . . . . . . . . . . . F 2-19Nickel and Chromium . . . . . . . . . . . . . . . . . . . 2.8.9Silver, Platinum, and Gold . . . . . . . . . . . . . . . 2.8.10Steel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.2Steel Corrosion Products (Rust). . . . . . . . . . . . F 2-20Titanium . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8.5
MONEL RIVETS. . . . . . . . . . . . . . . . . . . . . . . . . 7.19
NNATURAL AND SYNTHETIC RUBBERPARTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.8NON-STRUCTURAL TUBING MEMBERS ANDASSEMBLIES. . . . . . . . . . . . . . . . . . . . . . . . . . . 7.13
Aluminum Alloy Tubing . . . . . . . . . . . . . . . . . 7.13.1Cadmium Plated Steel Tubing . . . . . . . . . . . . . 7.13.3Removable Installations . . . . . . . . . . . . . . . . . 7.13.5Special Instructions for Tubing Fittings andSleeves . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.13.4Stainless Steel (CRES) Tubing. . . . . . . . . . . . . 7.13.2
PPAINT REMOVAL . . . . . . . . . . . . . . . . . . . . . . . . 5.4PIANO TYPE HINGES . . . . . . . . . . . . . . . . . . . . . 7.5PITTING ON CRITICAL STRUCTURE . . . . . . . . . . 5.7POST DEPLOYMENT . . . . . . . . . . . . . . . . . . . . . . 9.4POTABLE WATER TANKS . . . . . . . . . . . . . . . . . . 7.9PRE-DEPLOYMENT RECOMMENDATIONS . . . . . 9.2
Global Dust Producing Regions . . . . . . . . . . . . F 9-2Soil Makeup in the SWA Area . . . . . . . . . . . . . F 9-1
PREVENTIVE MAINTENANCE . . . . . . . . . . . . . . 2.11PREVENTIVE MAINTENANCE PROGRAM . . . . . . 3.1
Aircraft Wash Intervals . . . . . . . . . . . . . . . . . . T 3-1Preventive Maintenance . . . . . . . . . . . . . . . . . . 3.1.1
Purpose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.1Detailed Inspections. . . . . . . . . . . . . . . . . . . . . 4.1.4Frequency of Inspections . . . . . . . . . . . . . . . . . 4.1.2General Inspections . . . . . . . . . . . . . . . . . . . . . 4.1.3Responsibility . . . . . . . . . . . . . . . . . . . . . . . . . 4.1.1
PURPOSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.1PURPOSE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10
A Water-Break Free Surface Compared with One withBreaks. . . . . . . . . . . . . . . . . . . . . . . . . . . . . F 5-10Application of Surface Treatments . . . . . . . . . . 5.10.4Chemical Prepaint Treatments . . . . . . . . . . . . . 5.10.1Conversion Coating Using TNP Pens . . . . . . . 5.10.4.1MIL-DTL-81706 Chemical Conversion Materials forCoating Aluminum and Aluminum Alloys . . . . 5.10.1.1Notes on Conversion Coating/SurfaceTreatment . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.5Post Treatment . . . . . . . . . . . . . . . . . . . . . . . 5.10.6Precautions . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.3
TO 1-1-691
INDEX - CONTINUED
Index 6 Change 17
Paragraph, Figure,Subject Table Number
Prepaint Treatments for Metal Surfaces . . . . . . T 5-13SAE AMS-M-3171 (MIL-M-3171), Type VI Magne-sium Alloy, Processes for Pretreatment and Preventionof Corrosion on; Chromic Acid Brush-OnTreatment. . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.1.2Surface Preparation . . . . . . . . . . . . . . . . . . . . 5.10.2Temporary Preservation . . . . . . . . . . . . . . . . . 5.10.7
PURPOSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.1PURPOSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.1
RRECOMMENDED ACTIONS WHILEDEPLOYED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.3
Areas to be Checked and Cleaned . . . . . . . . . . . 9.3.2High Efficiency Particulate Air (HEPA)Filtration . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.3.1Open Circuit Board. . . . . . . . . . . . . . . . . . . . . F 9-3Pneumatic Backpack . . . . . . . . . . . . . . . . . . . 9.3.1.2Pneumatic Wheeled Units. . . . . . . . . . . . . . . . 9.3.1.1
RELIEF TUBE AREAS . . . . . . . . . . . . . . . . . . . . . 7.3REMOTELY PILOTED AIRCRAFT (RPA) . . . . . . . 10.1
Air Force RPA Tiers . . . . . . . . . . . . . . . . . . . T 10-1Definition . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.1.1
REQUIREMENTS FOR SHOT PEENING. . . . . . . . 5.11RESPONSIBILITY . . . . . . . . . . . . . . . . . . . . . . . . 5.2RESPONSIBILITY . . . . . . . . . . . . . . . . . . . . . . . . 8.2ROTO-PEENING (ROTARY FLAP PEENING) . . . . 5.13
“A” Test Strip Arc Height Magnetic to SAE J442 Stri-pholder Conversion Chart, 0.001 Inch . . . . . . . F 5-13“A” Test Strip Magnetic to SAE J442 Stripholder ArcHeight Conversion Graph . . . . . . . . . . . . . . . . F 5-12“N” Arc Height Magnetic to SAE J442 StripholderConversion Chart, 0.001 Inch . . . . . . . . . . . . . F 5-15“N” Arc Height Magnetic to SAE J442 StripholderConversion Graph . . . . . . . . . . . . . . . . . . . . . F 5-14Arc Height Conversion. . . . . . . . . . . . . . . . . 5.13.2.1Arc Height Plotting Chart. . . . . . . . . . . . . . . . F 5-16Coverage . . . . . . . . . . . . . . . . . . . . . . . . . . 5.13.3.3Determining Peening/Intensity . . . . . . . . . . . . . 5.13.2Equipment . . . . . . . . . . . . . . . . . . . . . . . . . 5.13.1.1Example of Coverage . . . . . . . . . . . . . . . . . . F 5-17Flap Deflection Ranges . . . . . . . . . . . . . . . . . F 5-18Flap Operation . . . . . . . . . . . . . . . . . . . . . . 5.13.3.2Magnetic Almen Strip Holder . . . . . . . . . . . . . F 5-11Part Peening Time . . . . . . . . . . . . . . . . . . . . 5.13.3.4Peening Process Preparation . . . . . . . . . . . . . . 5.13.3Post Peening Surface Finish . . . . . . . . . . . . . . 5.13.4Rotary Tool Speed. . . . . . . . . . . . . . . . . . . . 5.13.3.1Roto-Peening Procedures . . . . . . . . . . . . . . . . 5.13.1Standard Peening Intensity (Isp) for Complete CoverageArc-Height (All Numbers in Inches) . . . . . . . . T 5-15Surface Preparation Procedure . . . . . . . . . . . . 5.13.1.2
Paragraph, Figure,Subject Table Number
Tool Speed Operation Requirements . . . . . . . . T 5-14
SSAFETY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.2
Materials Handling . . . . . . . . . . . . . . . . . . . . . 1.2.2Responsibility of Supervisors . . . . . . . . . . . . . . 1.2.1
SEALANT APPLICATION PROCEDURES. . . . . . . . 6.6Adhesion Promoters. . . . . . . . . . . . . . . . . . . . . 6.6.3Brush Spatula or Caulking Gun Application. . . . . 6.6.4Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.6.1Masking. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.6.2Non-Metallic Spatula. . . . . . . . . . . . . . . . . . . . F 6-8Peel and Stick Application; SAE AMS 3255 EPTFESkyflex® and Av-Dec® HT3935-7 and HT3000 SealingTapes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.6.6Spray Gun Application . . . . . . . . . . . . . . . . . . . 6.6.5Time Requirements for Sealants When Used at 75° F(24° C) and 50% RH . . . . . . . . . . . . . . . . . . . T 6-2
SEALANT MIXING . . . . . . . . . . . . . . . . . . . . . . . 6.5Application Life . . . . . . . . . . . . . . . . . . . . . . . 6.5.1Countersink Application Nozzles. . . . . . . . . . . . F 6-3Enhancement of Sealant Curing. . . . . . . . . . . . 6.5.1.1Injection Style Semkit®. . . . . . . . . . . . . . . . . . F 6-7Mixing MIL-PRF-81733, Type III Sprayable SealantCoating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.5.3Pneumatic Sealant Gun . . . . . . . . . . . . . . . . . . F 6-1Rivet Application Nozzles . . . . . . . . . . . . . . . . F 6-4Sealant and Adhesive Smoothing Tools . . . . . . . F 6-5Sealant Application Nozzles . . . . . . . . . . . . . . . F 6-2Sealant Injection Guns. . . . . . . . . . . . . . . . . . . F 6-6Sealing Compounds . . . . . . . . . . . . . . . . . . . . T 6-1Storage Instructions . . . . . . . . . . . . . . . . . . . . . 6.5.2
SEALING COMPOUNDS. . . . . . . . . . . . . . . . . . . . 6.3Adhesion Promoters. . . . . . . . . . . . . . . . . . . . . 6.3.4Av-Dec® Polyurethane Sealant Tapes and Two Compo-nent Sealants . . . . . . . . . . . . . . . . . . . . . . . . . 6.3.6Cartridge (CA) . . . . . . . . . . . . . . . . . . . . . . . 6.3.1.2Polysulfide, Polyurethane, and Polythioether SealingCompounds . . . . . . . . . . . . . . . . . . . . . . . . . . 6.3.2Pre-Mixed and Frozen (PMF) . . . . . . . . . . . . . 6.3.1.3SAE AMS 3255 Oil and Water Resistant, ExpandedPolytetrafluoroethylene Sealing Tape (EPTFE)Skyflex . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.3.5Sealant Packaging . . . . . . . . . . . . . . . . . . . . . . 6.3.1Silicone Sealing Compounds . . . . . . . . . . . . . . . 6.3.3Two-Part Kit (KT) . . . . . . . . . . . . . . . . . . . . 6.3.1.1
SEALING OF SPECIFIC AREAS . . . . . . . . . . . . . . 6.7Damaged Sealant . . . . . . . . . . . . . . . . . . . . . . 6.7.10Depressions . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.9Extensive Repair . . . . . . . . . . . . . . . . . . . . . . 6.7.11External Aircraft Structure . . . . . . . . . . . . . . . . 6.7.8Fastener Sealing . . . . . . . . . . . . . . . . . . . . . . . 6.7.4
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Change 17 Index 7
Paragraph, Figure,Subject Table Number
Faying Surface Sealing. . . . . . . . . . . . . . . . . . . 6.7.1Faying Surface Sealing . . . . . . . . . . . . . . . . . . F 6-9Fillet Sealing . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.2Form-In-Place (FIP) Gasket Sealant Repair . . . . . 6.7.6High Temperature Areas . . . . . . . . . . . . . . . . . 6.7.12Injection Sealing . . . . . . . . . . . . . . . . . . . . . . . 6.7.3Integral Fuel Cells/Tanks and Removable FuelTanks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.5Low Temperature Curing . . . . . . . . . . . . . . . . 6.7.13SAE AMS 3255 EPTFE (Skyflex®) and Av-Dec®HT3000 and HT3935-7 Sealing Tape GasketRepair . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.7.7Typical Fillet Seal . . . . . . . . . . . . . . . . . . . . . F 6-10Typical Injection Seal . . . . . . . . . . . . . . . . . . F 6-11Typical Methods of Sealing Fasteners. . . . . . . . F 6-12
SHOT PEENING OF METAL SURFACES . . . . . . . 5.12Metallic, Glass, or Ceramic Shot Peening . . . . 5.12.1.1Shot Peening Application . . . . . . . . . . . . . . . . 5.12.2Types of Peening . . . . . . . . . . . . . . . . . . . . . . 5.12.1
SPECIFIC EXTERNAL AREAS OF AIRCRAFT . . . . 8.7Aircraft Fuel Systems. . . . . . . . . . . . . . . . . . . . 8.7.9Airframes. . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.7.1Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.7.2Armament . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.7.8Cleaning Procedure . . . . . . . . . . . . . . . . . . . . 8.7.8.2External Surface Contamination . . . . . . . . . . . 8.7.6.1Helicopter Main and Tail Rotor Blades . . . . . . . . 8.7.7Helicopter Transmission, Rotor Head, and RotorHub. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.7.6Internal Surface Contamination . . . . . . . . . . . . 8.7.6.2Reciprocating Engines . . . . . . . . . . . . . . . . . . . 8.7.3Safety Precautions. . . . . . . . . . . . . . . . . . . . . 8.7.8.1Treatment for Engines Which Have Ingested Fire Extin-guishing Powder (Potassium Bicarbonate [PurpleK{PKP}], Sodium Bicarbonate, Ammonium PhosphateMonobasic) and/or Synthetic Foaming Agents (AFFF,Hi-Ex, AR). . . . . . . . . . . . . . . . . . . . . . . . . . . 8.7.5Turbine Engines . . . . . . . . . . . . . . . . . . . . . . . 8.7.4
SPECIFIC INTERNAL AREAS . . . . . . . . . . . . . . . . 8.6Aircraft Cockpit Area. . . . . . . . . . . . . . . . . . . . 8.6.1Aircraft Ejection Seats . . . . . . . . . . . . . . . . . . . 8.6.2Avionic, Electronic, and Electrical Equipment . . . 8.6.3Cleanup. . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.6.5.1Graphite or Carbon Fiber/Epoxy, Boron Fiber/Epoxy,and Tungsten Fiber/Epoxy CompositeMaterials . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.6.5Photographic Equipment. . . . . . . . . . . . . . . . . . 8.6.4
STORAGE/SHELF LIFE CONTROL OFSEALANTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.8
Sealing of Access Doors . . . . . . . . . . . . . . . . F 6-16Sealing Procedures for Typical Aircraft Fitting. . F 6-14Typical Lap Skin Sealing . . . . . . . . . . . . . . . . F 6-13Typical Spar Cap Sealing . . . . . . . . . . . . . . . . F 6-15
STRUCTURAL TUBING MEMBERS ANDASSEMBLIES. . . . . . . . . . . . . . . . . . . . . . . . . . . 7.12
Paragraph, Figure,Subject Table Number
Exterior . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.12.4.1Interior . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.12.4.2Sealing . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.12.4.3Structural Aluminum Alloy Tubing . . . . . . . . . . 7.12.1Structural Carbon Steel Tubing . . . . . . . . . . . . 7.12.4Structural Copper Alloys, Stainless Steel (CRES) Al-loys, and Heat Resistant Alloy Tubing. . . . . . . . 7.12.3Structural Magnesium Alloy Tubing . . . . . . . . . 7.12.2
SURFACE FINISH . . . . . . . . . . . . . . . . . . . . . . . . 5.6SURFACES AND COMPONENTS EXPOSED TO EX-HAUST GASES, GUN GASES, AND ROCKETBLAST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.10
TTHEORY OF CORROSION . . . . . . . . . . . . . . . . . . 2.4
Anode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4.1Cathode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4.2Electrical Contact . . . . . . . . . . . . . . . . . . . . . . 2.4.4Electrolyte . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.4.3Elimination of Anode, Cathode, Electrolyte, or Electri-cal Contact . . . . . . . . . . . . . . . . . . . . . . . . . 2.4.4.1Simplified Corrosion Cell . . . . . . . . . . . . . . . . F 2-1
TYPES OF CORROSION. . . . . . . . . . . . . . . . . . . . 2.7Active/Passive Cells . . . . . . . . . . . . . . . . . . . 2.7.6.3Another Example of Exfoliation . . . . . . . . . . . F 2-13Associated Hazards . . . . . . . . . . . . . . . . . . . . 2.7.6.5Causes . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.7.6.6Concentration Cell Corrosion . . . . . . . . . . . . . F 2-14Corrosion Fatigue . . . . . . . . . . . . . . . . . . . . . . 2.7.7Crevice/Concentration Cell Corrosion . . . . . . . . . 2.7.6Cross-Section of 7075-T6 Aluminum Alloy. . . . . F 2-9Cross-Section of Corrosion Pits . . . . . . . . . . . . F 2-8Example of Exfoliation . . . . . . . . . . . . . . . . . F 2-12Exfoliation Corrosion . . . . . . . . . . . . . . . . . . . . 2.7.5Filiform Corrosion. . . . . . . . . . . . . . . . . . . . . . 2.7.8Filiform Corrosion Found Under Paint Coating on aMagnesium Panel . . . . . . . . . . . . . . . . . . . . . F 2-17Fretting Corrosion . . . . . . . . . . . . . . . . . . . . . . 2.7.9Galvanic Corrosion . . . . . . . . . . . . . . . . . . . . . 2.7.2Galvanic Corrosion of Magnesium Adjacent to a SteelFastener . . . . . . . . . . . . . . . . . . . . . . . . . . . . F 2-6Galvanic Series of Metals and Alloys in SeaWater . . . . . . . . . . . . . . . . . . . . . . . . . . . . . F 2-16Grain Structure of a Corroding AluminumSurface . . . . . . . . . . . . . . . . . . . . . . . . . . . . F 2-10High Temperature Oxidation (Hot Corrosion) . . . 2.7.10Intergranular Corrosion. . . . . . . . . . . . . . . . . . . 2.7.4Intergranular Corrosion of 7075-T6 Aluminum Adjacentto Steel Fastener . . . . . . . . . . . . . . . . . . . . . . F 2-11Metal Ion Concentration Cells. . . . . . . . . . . . . 2.7.6.1Oxygen Concentration Cells . . . . . . . . . . . . . . 2.7.6.2Pitting Corrosion . . . . . . . . . . . . . . . . . . . . . . . 2.7.3Pitting of an Aluminum Wing Assembly. . . . . . . F 2-7
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Index 8 Change 18
Paragraph, Figure,Subject Table Number
Schematic of the Development of Filiform Corrosionon an Aluminum Alloy . . . . . . . . . . . . . . . . . F 2-18Stress Corrosion Cracking . . . . . . . . . . . . . . . 2.7.6.4
Paragraph, Figure,Subject Table Number
Stress Corrosion Cracking . . . . . . . . . . . . . . . F 2-15Uniform Surface Corrosion . . . . . . . . . . . . . . . . 2.7.1
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Change 17 Index 9/(Index 10 blank)