sa4047-s70b-mrc-300

TECHNICAL MANUALDAILY MAINTENANCE REQUIREMENTS CARDS

MODELS S-70B-2S70B6/S-70B

S70B7AIRCRAFT

This manual supersedes SA4047-S70B-MRC-300 dated 1 January 1997, with change information. Change 3, 30 April 2003,has been incorporated in this issue and makes this a complete manual.

THIS DOCUMENT IS THE PROPERTY OF UNITED TECHNOLOGIES CORPORATION AND IS DELIVERED ON THE EXPRESSCONDITION THAT IT IS NOT TO BE DISCLOSED REPRODUCED IN WHOLE OR IN PART, OR USED FOR MANUFACTUREFOR ANY OTHER THAN UNITED TECHNOLOGIES CORPORATION WITHOUT ITS WRITTEN CONSENT; AND THAT NORIGHT IS GRANTED TO DISCLOSE OR SO USE ANY INFORMATION CONTAINED IN SAID DOCUMENT. THISRESTRICTION DOES NOT LIMIT THE RIGHT TO USE INFORMATION OBTAINED FROM ANOTHER SOURCE.

COPYRIGHT R 1994 SIKORSKY AIRCRAFT CORPORATION.

SA4047-S70B-MRC-300

1 January 1997Change 3 - 30 April 2003

Insert latest changed cards; dispose of superseded cards in accordance with applicable regulations.

NOTE: That portion of text affected by the change is indicated by a vertical line.

Dates of issue for original and changed cards:

Original . . . . . . . . . . . . . . . 0 ............. 1 January 1997Change . . . . . . . . . . . . . . . 1 ............. 31 March 1999

(T-REV 7, 9, 13 Inc)

Change . . . . . . . . . . . . . . . 2 ............. 15 June 2001Change . . . . . . . . . . . . . . . 3 ............. 30 April 2003

(T-REV 24 Inc)

Total number of cards in this manual is 126.

CARD NO.CHANGE

NO.Title............................... 3A - B............................. 3C Blank ......................... 3HMWS-1 - HMWS-13 ... 3HMWS-14 Blank ........... 3i - xii............................. 3

CARD NO.CHANGE

NO.1 - 1.4 .......................... 31.5 Blank ...................... 32 - 2.2 .......................... 32.3 Blank ...................... 33 - 3.3 .......................... 34 - 4.11 ........................ 3

CARD NO.CHANGE

NO.5 - 5.1 .......................... 06 - 6.8 .......................... 36.9 Blank ...................... 37 .................................. 07.1 Blank ...................... 08 - 8.2 .......................... 3

LIST OF EFFECTIVE CARDSSA4047-S70B-MRC-300

A

CARD NO.CHANGE

NO.8.3 Blank ...................... 39 - 9.2 .......................... 39.3 Blank ...................... 310 - 10.10 .................... 310.11 Blank .................. 311 - 11.2 ...................... 311.3 Blank .................... 3

CARD NO.CHANGE

NO.12 - 12.6 ...................... 012.7 Blank .................... 013 - 13.2 ...................... 013.3 Blank .................... 014 - 14.10 .................... 314.11 Blank .................. 315 ................................ 0

CARD NO.CHANGE

NO.15.1 Blank .................... 016 - 16.2 ...................... 016.3 Blank .................... 017- 17.1 ....................... 0

LIST OF EFFECTIVE CARDS (Cont)SA4047-S70B-MRC-300

B/C Blank

Warnings in this manual alert personnel to hazards associated with the use of hazardous materials. Additional information related tohazardous materials is provided in OPNAVINST 5100.23, Navy Occupational Safety and Health (NAVOSH) program manual,NAVSUPINST 5100.27, Navy Hazardous Material Control Program, and the DOD 6050.5, Hazardous Material Information System (HMIS)series publications. For each hazardous material used within the Navy, a Material Safety Data Sheet (MSDS) must be provided and availablefor review by users. Consult your local safety and health staff concerning any questions regarding hazardous materials, MSDS, personalprotective equipment requirements, appropriate handling and emergency procedures, and disposal guidance.

Under the heading, 9HAZARDOUS MATERIALS WARNINGS9, complete warnings, including related Icon(s), are provided for hazardousmaterials used in this manual.

In the text of the manual, the caption 9WARNING9 may be used for hazardous personnel dangers. Hazards are cited with appropriateIcon(s), the nomenclature of the hazardous material, and the numeric identifier to the complete warning. Users of hazardous materials shallrefer to the complete warning, as necessary.

CARD CHANGE NO. HAZARDOUS MATERIALDATE: WARNINGSSA4047-S70B-MRC-300

HMWS-1 1 January 1997 3

Continued

Biological

The abstract symbol bug shows that a material may contain bacteria or viruses that present a danger to life or health.

Chemical

The symbol of a liquid dripping onto a hand shows that the material will cause burns or irritation to human skin or tissue.



Continued

Explosion

This rapidly expanding symbol shows that the material may explode if subjected to high temperature, source of ignition, or high pressure.

Eye Protection

The symbol of a person wearing goggles shows that the material will injure the eyes.



Continued

Fire

The symbol of a fire shows that the material may ignite and cause burns.

Poison

The symbol of a skull and crossbones shows that the material is poisonous or is a danger to life.



Continued

Radiation

The symbol of three circular wedges shows that a material emits radioactive energy and can injure human tissue or organs.

Vapor

The symbol of a human figure in a cloud shows that material vapors present a danger to life or health.



Continued

Cryogenic

The symbol of a hand in a block of ice shows that the material is extremely cold and can injure human skin or tissue.



Continued

Isopropyl Alcohol, TT-I-735 25

Isopropyl alcohol, TT-I-735, is flammable - do not use near open flames, near welding areas, or on hot surfaces. Do not smoke when usingit, and do not use it where others are smoking. Metal containers of liquid must be grounded to maintain electrical continuity. Bond metalcontainers during transfer to prevent ignition through static discharge. Store solvent and dispose of liquid-soaked clothes in approved metalsafety container. Contact of liquid with skin may cause dermatitis and irritation. May irritate eyes on contact. If any liquid contacts skin oreyes, immediately flush affected area thoroughly with water. Remove solvent-saturated clothing. Inhalation of vapors can cause drowsiness,dizziness, headache, nausea, and respiratory irritation. If vapors cause drowsiness, go to fresh air. When handling large quantities (greaterthan one gallon), work at air-exhausted workbench or covered tank. Protection: chemical goggles; nitrile/neoprene gloves; NIOSH/MSHAapproved respirator if vapors exceed established limits.



Continued

Corrosion Preventive Compound,MIL-C-81309 36

Corrosion preventive compound, MIL-C-81309, is combustible − keep it away from heat, sparks, and open flames. Do not smoke when usingit. Use in a well-ventilated area. Inhalation of vapors is harmful. Wear oil impervious gloves, chemical splashproof goggles (or face shield),and protective apron. If splashed on clothing or in eyes, remove clothing immediately and flush skin/eyes with clear water for 15 minutes.If vapors cause light-headedness, move to fresh air. If liquid is swallowed, do not induce vomiting. Get prompt medical attention. Useabsorbent to soak up spilled solution. Dispose of absorbent in accordance with local, state, and federal regulations. Keep solution away fromoxygen and strong oxidants. Store in approved metal safety container. Keep containers closed when not in use.



Continued

Hydraulic Fluid, MIL-PRF-83282 55

Hydraulic fluid, MIL-PRF-83282, releases toxic gases when decomposed by heat. Prolonged contact with liquid or mist can cause dermatitisand irritation. If there is any prolonged contact with skin, wash contacted area with soap and water. If liquid contacts eyes, flush eyes withwater immediately for 15 minutes. Remove saturated clothing. If fluid is swallowed, do not induce vomiting. Get immediate medical attention.When handling liquid, wear rubber gloves. Inhalation of vapors should be avoided.



Continued

Lubricant, MIL-PRF-32033 75

Lubricant, MIL-PRF-32033, is combustible - keep away from ignition sources (heat, flame). Keep container closed. Keep lubricant off skin,eyes, and clothes. Direct contact may severely irritate the eyes. Prolonged or repeated contact may irritate the skin. Do not breathe vapors.Breathing mists may cause headache, dizziness, nausea, and respiratory irritation. Protection: chemical splashproof goggles, neoprene orpolyvinyl gloves, impervious clothing, NIOSH/MSHA approved respirator if mists exceed established exposure limits and good ventilation.



Continued

Dry-Cleaning Solvent, MIL-PRF-680 101

Dry-cleaning solvent, MIL-PRF-680, is manufactured by several companies, and its composition varies. Therefore, it is very important that yourefer to the warnings on the container used, and also consult the material safety data sheet (MSDS) before using this solvent. Dry-cleaningsolvent may be combustible − do not use near open flames, near welding areas, or on hot surfaces. Prolonged contact of skin with liquidcan cause dermatitis. Repeated inhalation of vapor can irritate nose and throat and can cause dizziness. If any liquid contacts skin or eyes,immediately flush affected area thoroughly with water. Remove solvent-saturated clothing. If vapors cause dizziness, go to fresh air. Whenhandling liquid or when applying it in an air-exhausted, partially covered tank, wear approved gloves and chemical splashproof goggles.When handling liquid or when applying it at unexhausted, uncovered tank or workbench, wear NIOSH/MSHA approved respirator andgoggles.



Continued

Grease, MIL-G-81827 116

Grease, MIL-G-81827, may irritate eyes and skin from prolonged or repeated contact. Avoid any skin contact with grease/lubricantmaterial. Prolonged or repeated contact may irritate the eyes and skin. Breathing vapor may irritate the upper respiratory tract. If swallowed,do not induce vomiting; aspiration may damage the lungs. Wash hands thoroughly prior to eating, drinking, or smoking. Do not apply tohot surfaces; toxic gases may be released. Protection: safety goggles, approved gloves, NIOSH/MSHA approved respirator if vapors exceedestablished exposure limits.



Continued

Corrosion Preventive Compound,MIL-DTL-85054 455

Avoid contact. May irritate the eyes. Prolonged or repeated contact may irritate the skin. Long term use without proper hand protection maycause dermatitis. May be absorbed through the skin in levels that could affect certain 9target9 organs. If splashed on clothing or eyes, removeclothing immediately and flush the eyes and skin with water for 15 minutes. Avoid breathing vapor. Keep containers closed when not in use;use in a well-ventilated area. Inhalation may cause headache, dizziness, nausea, and respiratory irritation; acute overexposures may causeheart irregularities. If these symptoms occur, seek fresh air and possible medical attention. If swallowed, do not try to vomit; chemical mayenter the lungs, causing damage; seek immediate medical attention. Protection: approved gloves, chemical splashproof goggles, full bodyprotective clothing, NIOSH/MSHA approved respirator if vapors exceed established exposure limits.



End of Card(Card HMWS-14 Blank)

INTRODUCTION

This manual contains the minimum Daily requirements necessary to assure the helicopter is safe for flight. Clearances, pressures, tolerances,illustrations, support equipment required, and manual references are presented where pertinent.

Daily requirements include inspections for defects, and system degradation at a greater depth than the Turnaround Checklist. Do not ignoresigns of corrosion during visual inspections of components.

APPLICATION

The daily inspection is valid for a period of 72 hours, provided no flight occurs during this period and no maintenance other than servicinghas been performed. Aircraft may be flown for 24 hours without another daily. This 24 hour period begins with the first launch followingaccomplishment of the daily inspection. The 24 hours cannot exceed the 72 hour expiration of the daily unless the expiration occurs duringa mission. In this case the aircraft will require a daily before the next flight. Turnaround requirements are not included in the daily inspectionand must be accomplished separately. Accomplishment of a turnaround does not affect the 72 hour validity of the daily inspection.

The symbol LOT I indicates that text within applies to helicopters serial Nos 51 thru 58.The symbol LOT II indicates that text within applies to helicopter serial No. 59 and subsequent.

CARD CHANGE NO.DATE:SA4047-S70B-MRC-300

31 January 1997i

Continued

MRC FORMAT DESCRIPTION

CARD - Assigned card number.

TECHNICAL MANUAL NUMBER/CARD SET DATE - Identifies individual manual and basic issue or revision date of this manual.

CHANGE NO. - Number of change. This block shall be left blank for basic issue and all revisions.

NOMENCLATURE - Heading used to designate particular card interval/function, such as Special 28-Day Corrosion Inspection, Daily,Post Launch, Calendar.

ELEC/HYD PWR/COND AIR - Power ON or OFF as it pertains to tasks contained on card. NA is placed in this block when power is notrequired and its application would not be dangerous to personnel or damaging to the equipment.

WORK ZONE(S) - Assigned zones(s) in which tasks are to be accomplished.

CRN - Corrosion inspection requirements are to be accomplished.

TIME - Total elapsed time in hours and tenths required to do the tasks listed on the basic and decimal cards.


31 January 1997ii

Continued

MRC FORMAT DESCRIPTION (Cont)

RTG/MOS AND NO. - Rating/Military Occupational Specialty assigned to accomplished tasks. Each specialist with same rating isassigned an identifying number.

TASK TITLE - Brief descriptive title identifying tasks on card.

WARNING - Indicates danger to personnel. The warning precedes the item to which it refers.

CAUTION - Indicates danger to system. The caution precedes the item to which it refers.

DAMAGE - A harmful condition caused by an abnormal force or object.

EVIDENCE - An indication of an existing condition, such as hydraulic fluid dripping from the lower wing surface is evidence of a leak.

NOTE - An information item. The note precedes the item to which it refers.

OBVIOUS - Easily seen or understood, clear to the eye or mind, not to be doubted.


31 January 1997iii

Continued

MRC FORMAT DESCRIPTION (Cont)

SECURITY - An item firmly, positively, and safely attached in the approved manner.

SPECIFIED - Refers to a definite amount, operation or limitation.

VISIBLE or EXPOSED - The term applied when inspection requires no further disassembly or movement of equipment and no removal ofdoors or panels other than that specifically detailed.


31 January 1997iv

Continued

ABBREVIATIONS

APU - Auxiliary Power Unit

ASC - Armament System Controller

ASO - Acoustic Sensor Operator

BATT - Battery

BIMT - Blade Inspection Method

ECS - Environmental Control System

FOD - Foreign Object Damage

HIFR - Helicopter In Flight Refueling

IGB - Intermediate Gear Box

MGB - Main Gear Box

RAST - Recovery Assist Securing Traversing

RSD - Rapid Securing Device

SO - Sensor Operator

TGB - Tail Gear Box

TSO - Tactical Sensor Operator


31 January 1997v

Continued

INDEX

CARD TITLE CARD NUMBERS

DAILY 1 THROUGH 17

SPECIAL TOOLS/SUPPORT EQUIPMENT REQUIRED

The following Special Tools/Support Equipment, or its equivalent, are necessary to accomplish the requirements containedin this manual.

NOMENCLATURE PART NO., TYPE OR MODEL NO. QUANTITY REQUIRED

Back Pack Pump 5100-2548 1Flashlight - 1Inspection Mirror - 1Lab Bottle MS36070-1 1Magnifying Glass (10X) 1Stopwatch S-10 1Tire Pressure Gage A-A-1726 1


31 January 1997vi

Continued

SPECIAL TOOLS/SUPPORT EQUIPMENT REQUIRED (Cont)

NOMENCLATURE PART NO., TYPE OR MODEL NO. QUANTITY REQUIRED

Tread Depth Gage MIL-I-18422 1

CONSUMABLE MAINTENANCE MATERIALS LIST

The following consumable maintenance materials are necessary to accomplish the requirements contained in this manual.

NOMENCLATURE PART NO., TYPE, OR SPECIFICATION NO.,

Acid Brush H-B-63Cleaning Cloth CCC-C-46Corrosion Preventive Compound MIL-C-81309, Type IICorrosion Preventive Compound MIL-DTL-85054Dry-Cleaning Solvent MIL-PRF-680, Type IIIGrease MIL-G-81827


31 January 1997vii

Continued

CONSUMABLE MAINTENANCE MATERIALS LIST (Cont)

NOMENCLATURE PART NO., TYPE, OR SPECIFICATION NO.,

Hydraulic Fluid MIL-PRF-83282Isopropyl Alcohol TT-I-735Low-Lint Cloth A-A-59323, Type IILubricant MIL-PRF-32033


31 January 1997viii

Continued

NOSE DOORACCESS (1.0.1)

LEFT FLOATACCESS (2.1.1)

ANIT−ICEACCESS(6.1.5)

AVIONICSACCESS (2.1.8)

GRAVITY FUELACCESS (3.1.2)

LHACCESS(3.1.5)

PNEUMATIC GROUNDSTART (3.1.4)

NO. 1 TAIL ROTOR DRIVESHAFT ACCESS (4.0.1)

NO. 2 TAIL DRIVESHAFT ACCESS (4.0.2)

TAIL ROTORGEARBOXACCESS

PYLON TRAILINGEDGE ACCESS(5.0.3)

PYLON TAIL DRIVESHAFT ACCESS (5.0.4)

(5.0.5)

TAIL SKIDSTRUT ACCESS(5.0.2)

IGB ACCESS(5.0.1)

NO. 3 TAIL DRIVESHAFT ACCESS (4.0.3)

FLUX VALVE / COMPASSSWING ACCESS (4.0.4)

TAILWHEELEXTENSIONDOOR (3.1.1)SECTION

AVIONICS

ENGINE WATERWASHACCESS (2.1.6)LH MLG

STRUT ACCESS(2.1.5)

ICS / ARM GROUNDCONNECTION ACCESS(2.1.4)

LH JUNCTIONBOX ACCESS(2.1.3)

CONTROLS /ACCESSORIESACCESS (6.0.1)

FLOTATION BOTTLEFILL ACCESS(2.1.2)

FLOTATION BOTTLESACCESS COVER(2.0.1)

EXTENDEDPYLONACCESS(2.1.7)

PRESSURE FUEL /LH FUEL CELL ACCESS(3.1.3)

SAFG1513

FLUX VALVEACCESS (4.0.5)

LOT I

LOT II

TRANSITION

ACCESS (3.0.1)(4.0.4)LOT II


31 January 1997ixACCESS PANELS AND DOORS(LH)

Continued

PYLON FLIGHT CONTROLCABLES ACCESS (5.2.1)

NO. 3 TAILROTOR DRIVEACCESS (4.0.3)


RH PANELACCESS(3.2.5)

RH FUEL CELLACCESS (3.2.3)

ANTI−ICE VALVE /DETECTOR ACCESS(6.2.2)

RH JUNCTIONBOX ACCESS (2.2.3)

VIDS / SDCACCESS(1.0.2)

RH FLOATACCESS (2.2.1)

A.C. EXT POWER RECEPTACLEACCESS (2.2.4)

RH MLGSTRUT ACCESS(2.2.5)

RH FUEL SUMPPUMP ACCESS(3.2.1)

EXTERNAL FUELR.H. (3.2.6)

ECS INLET(3.2.4)

BLADE FOLDSUPPORT COVERFWD (4.2.2)

BLADE FOLDSUPPORT COVERAFT (4.2.3)

TAIL CONEFLIGHT CONTROLACCESS (4.2.1)

ESM AMPRECEIVERACCESS(5.2.2)

RESCUE HOISTACCESS (2.2.2)


SAFG1514


31 January 1997xACCESS PANELS AND DOORS(RH)

Continued

NOSE DOORACCESS (1.0.1)

FLIGHT CONTROL RODS /ACCESSORIES ACCESS (6.0.1)

NO. 2 WORK PLATFORM / ENGINEACCESSORIES ACCESS (6.2.3)

4TH HYDRAULIC RESERVOIRACCESS (6.2.4)

RH TORPEDOLATCH ACCESS (3.2.2)

SYSTEM ACCESS(6.2.1)

ENGINE FIRE BOTTLEACCESS (6.1.4)

(6.1.3)

OIL COOLERACCESS (6.1.2)

NO. 1 WORK PLATFORM / ENGINEACCESSORIES ACCESS (6.1.1)

LH TORPEDOLATCH ACCESS(2.1.9)

SAFG1515

LH TORPEDOLATCH ACCESS(2.1.9)

LH TORPEDOLATCH ACCESS(2.1.10)LOT I

LOT II

LOT II

ELECTRONICS /

ENVIRONMENTAL CONTROL

UNIT ACCESSAUXILIARY POWER


31 January 1997xiACCESS PANELS AND DOORS(TOP)

Continued

RIGHT SIDE

BOTTOM VIEW

ANTENNA LOCATION DIAGRAM

DOPPLER

LOCATORTRANSMITTER

RECEIVERANTENNA

RADAR ALTIMETER ANTENNA

TACAN ANTENNA

IFF

VHF / UHF / L BANDANTENNA

VHF / UHF DF

HF LONGWIREANTENNA MAST

ESM ANTENNA(BOTH SIDES)

ESM ANTENNA(BOTH SIDES)

LF / ADF ANTENNA

SEARCH RADARAND RADOME

VHF / UHF / L BANDANTENNA

ANTENNA

SAFG1516

LOT II

LOT II

LOT IILOT II

LOT II

LOT I

HFANTENNA

EMERGENCY

ANTENNA

GPSANTENNA

SONOBUOY

ANTENNA

GLIDE SLOPEANTENNA

ANTENNA ANTENNAMARKERBEACON

VORCOMPASS


31 January 1997xiiANTENNA LOCATIONS

End of Card

CONSUMABLES/REPLACEMENT PARTS

Hydraulic Fluid MIL-PRF-83282Isopropyl Alcohol TT-I-735Low-Lint Cloth A-A-59323, Type II

WARNING: Area must be free of foreign objects and these safety items installed/removed or properly positioned asapplicable:

a. wheels chocked.b. static ground wire.c. tiedowns (as required).d. protective covers (as required).e. tailwheels locked.f. parking brake set.g. rotor brake set.

CARD CHANGE NO.DATE: ELEC PWR

WORK C TIME RTG MOS.AREA/ R NO. NO. HYD PWRZONE S

N COND AIR

DAILYSA4047-S70B-MRC-300

31 January 1997 ON

OFF

NA

0.4PC

1

1

Continued

1. ESM/RADALT antenna fairings and attaching hardware for cracks, delamination, and security.

1.1 2. Left cockpit door emergency jettison handle for shearwire; door for operation; seals for deterioration.

1.1 3. Copilot restraint system:a. place inertia reel control lever aft.b. pull out shoulder harness: inertia reel for freedom of movement and locking.c. shoulder harness for rips and tears.d. release shoulder harness; place inertia reel control lever forward.e. lap and crotch belts for rips and tears.f. rotary buckle for operation and freedom of movement.g. attenuator for cracks, dents, extension, and missing hardware.

WARNING: To prevent damage to equipment and injury to personnel do not release handle unless seat is occupied.Keep fingers away from seat frame while adjusting seat.

1.1 4. Vertical and horizontal locking pins on copilot seat for cracks, security, and proper operation.



N COND AIR

DAILY3SA4047-S70B-MRC-300

1 January 1997 ON

OFF

NA

PC

1

1.1

Continued

1.1 5. Copilot cyclic stick:a. open zipper on copilot cyclic stick boot.b. supports, bellcranks, levers, control rods, and cyclic control for cracks and security.c. close zipper on copilot cyclic stick boot.

1.1 6. Pedal adjustor for cracks and security.

1.1 7. Copilot collective stick:a. open zipper on copilot collective stick boot.b. supports, bellcranks, levers, control rods, yoke housing, and collective controls for cracks and security.c. close zipper on copilot collective stick boot.

1.1 8. Copilot main landing gear brake master cylinders:a. open zippers on copilot pedal boots.



N COND AIR


1 January 1997 ON

OFF

NA

PC

1

1.2

Continued


b. wipe exposed piston rod with low-lint cloth, dampened with hydraulic fluid.c. cylinders for evidence of leakage.d. close zippers on copilots pedal boots.

1.1 9. All fire extinguisher T-handles for cracks, security, and proper position.



N COND AIR


1 January 1997 ON

OFF

NA

PC

1

1.3

Continued


NOTE: Commercial nonabrasive glass cleaner may be used in place of isopropyl alcohol.

10. Wipe control box faceplates and flight instruments display screens with isopropyl alcohol.



N COND AIR


1 January 1997 ON

OFF

NA

PC

1

1.4

End of Card(Card 1.5 Blank)


Tire Pressure Gage A-A-1726Tread Depth Gage MIL-I-18422


Low-Lint Cloth A-A-59323, Type IILubricant MIL-PRF-32033

2.1 1. Left main landing gear:a. brake hoses, lines, fittings, and unions for evidence of leakage.

NOTE: Discs require replacement when indicator is pressed flush with bushing.

b. brake discs for wear by pressing wear pin indicators.



N COND AIR


31 January 1997 NA

NA

NA

0.4PC

1

2

Continued

c. wheel brake assembly for evidence of leakage.d. brake housing for cracks, damage, and security.e. brake to mounting bracket bolts for torque stripe or torque stripe slippage.f. drag beam for cracks (particularly in area of jack pad).g. weight-on-wheels switch for security.


h. wipe shock strut piston with low-lint cloth, dampened with lubricant.i. shock strut for evidence of leakage, scoring on piston, and cracks.j. strut boot for tears and security of mounting.k. air servicing valve and cap for security.l. axle attach bolts for cracks and security.

m. hub halves for missing hardware and security.n. wheels for damage.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

2.1

Continued

NOTE: Reject tire when tread is worn to bottom of any tread groove for continuous length of 12 inches or when wearhas reached first fabric ply past bottom of tread groove, whichever comes first. Reject any tire when sidewall cutis deeper than 1/8 inch.

o. tire for damaged tread and sidewall and correct pressure (95-100 psi).p. static ground cable for security.

2. LF/ADF antenna radome seal for deterioration, cracks, unobstructed drain hole; attaching hardware for security.

3. VHF/UHF DF antenna for cracks and attaching hardware for security.

4. Doppler antenna for cracks and attaching hardware for security.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

2.2



Back Pack Pump 5100-2548Lab Bottle MS36070-1Tire Pressure Gage A-A-1726Tread Depth Gage MIL-I-18422



WARNING: When manually actuated, RAST probe extends with sufficient force to seriously injure personnel. Alwaysremain clear of area directly under probe in case of inadvertent release.

3.1 1. Open tailwheel extension door.



N COND AIR


31 January 1997 NA

NA

NA

PC

1

3

Continued

a. tail strut X-dimension and gage pressure for proper servicing.b. close tailwheel extension door.c. hinge and latch components for security.

NOTE: If operating aircraft in a corrosive environment perform steps 2.a. through 2.c.

3.1 2. Tail landing gear:a. using back pack pump or lab bottle with fresh water and a clean low-lint cloth, completely flush/clean grease,

dirt, debris, sand, salts, or other foreign objects from exposed area of piston covered by gland nut.


b. after piston is clean, apply lubricant to entire unexposed area by using back pack pump or lab bottle.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

3.1

Continued

c. using low-lint cloth, wipe off excess lubricant that drains from unexposed area of piston, leaving a thin film oflubricant on exposed piston and gland nut.

d. tailwheel shock strut for nicks, scratches, and evidence of leakage.e. torque arm assembly for cracks.f. apex attach pin, upper and lower torque arm pins, and caps for cracks and security.

NOTE: Reject tire when worn to bottom of groove in any spot or when sidewall is cut more than 1/8 inch.

g. tires (slip marks) for slippage, damaged sidewall or tread, and proper pressure (75-85 psi).h. wheels for damage.i. lower tail RAST probe (if installed). Refer to applicable maintenance manual.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

3.2

Continued


j. wipe tail RAST probe (if installed) with low-lint cloth dampened with lubricant.k. raise tail RAST probe (if installed). Refer to applicable maintenance manual.

3. Lower VHF/UHF antenna for damage, cleanness, and security.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

3.3

End of Card


Back Pack Pump 5100-2548Flashlight -Inspection Mirror -Lab Bottle MS36070-1


Corrosion Preventive Compound MIL-C-81309Grease MIL-G-81827Hydraulic Fluid MIL-PRF-83282Low-Lint Cloth A-A-59323, Type IILubricant MIL-PRF-32033

5.1 1. Intermediate gear box:



N COND AIR


31 January 1997 ON

NA

NA

0.6PC

1

4

Continued

a. remove IGB access; attaching hardware for security; seals for evidence of leakage.b. drive shaft and flexible couplings for damage, buckling, and separation.c. mounting feet for cracks.d. sealant for deterioration.e. hydraulic lines for evidence of leakage and chafing.f. electrical harness for chafing and security.g. install IGB access.

5.1, 5.2 2. Stabilator:


a. wipe all exposed piston rods with low-lint cloth, dampened with lubricant.b. actuator and attaching hardware for security.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

4.1

Continued

c. position sensor arm for security.d. fold hinge bolt for security.e. center stabilator assembly for lug and skin cracks and security.

NOTE: Following step must be done with stabilator in both full up and full down positions.

f. center stabilator assembly lug areas and forward spar fitting for any indications of cracks. Using flashlight andmirror, view forward spar web for integrity of all bushings, bearings, and associated attachment hardware. Alsoview mating pylon attach fitting for indications of cracking and integrity of all associated attachment hardware.If any indications exist, fluorescent penetrant inspect prior to flight. Notify cognizant field activity if cracks arefound.

g. stabilator outboard section fold lugs and skin for cracks and security.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

4.2

Continued


h. lubricate stabilator to pylon attaching bolts using a lab bottle or back pack pump and lubricant.i. isolator mount for disbonding.j. static wicks for security.k. tail position light for security.

5.1 3. Tail gear box/tail rotor servo.a. remove tail gear box access; attaching hardware for security.

(1) no corner fasteners are permitted to be popped out.(2) no two fasteners in a row shall be unfastened.(3) no more than three fasteners popped at any one time.

b. drive shaft and TGB input flexible coupling for damage, buckling, and separation.c. tail gear box seals for evidence of leakage; sealant for deterioration.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

4.3

Continued

d. tail gear box mounting feet for cracks.e. tail rotor index actuator for security.f. all lines and hoses for chafing or frayed wire braids.


g. wipe all exposed piston rods with low-lint cloth, dampened with hydraulic fluid.h. first and second stage hydraulic seals of tail rotor servo for evidence of leakage.i. first stage pressure and return hydraulic hoses of tail rotor servo for chafing and clamping hardware for security.j. electrical harness for chafing and security.k. centering springs for security and cotter pins.l. all cables and cable pulleys for wear, security, and cotter pins.

m. tail rotor pylon skin for cracks at approximately STA 710. If cracks are found, TGB support fitting must beinspected.

n. install tail gear box access.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

4.4

Continued

5.2 4. Tail rotor:a. tail rotor pitch beam retainer nut for cracks.b. tail rotor pitch beam retaining nut (set screws) for security and safety wire.c. tail rotor pitch change links and bonding wires for security and cotter pins.d. tail rotor blade boots for rips and tears.e. tail rotor blade leading and trailing edges for disbonds and cracking.f. tip cap for cracks and security.g. upper anticollision light for cleanness and security.h. tail rotor deice wiring and bracket for security beneath wiring harness for chafing.


i. pitch change shaft for damage; wipe with low-lint cloth, dampened with hydraulic fluid.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

4.5

Continued

5.1, 5.2 5. Tail rotor drive shaft (section VI):a. open pylon tail drive shaft access; attaching hardware for security.b. drive shaft section and flexible coupling for damage, buckling, and separation.c. top stabilator piston mounting bolt for, security, and cotter pin.d. hydraulic lines for chafing and security.e. electrical harnesses for chafing and security.f. close pylon tail drive shaft access.

4.2 6. HF antenna:a. standoffs and clamps for security.b. wires for chafing, fraying, proper tension, and security.

4.2 7. Tail rotor drive shaft (Section II through V):a. open No. 2/No. 3 tail drive shaft access; attaching hardware for security.b. drive shaft sections and flexible couplings for damage, buckling, and separation.

WARNING: Puddling of grease beneath new viscous damper bearing should not occur after 10 flight hours. Purgedgrease can sling out onto seals, adjacent components, cowlings, or anywhere within 360° plane of bearing



N COND AIR


1 January 1997 ON

NA

NA

PC

1

4.6

Continued

rotation. Majority of grease purging should abate within 100 flight hours. A thin film of grease uniformlyaround full 360° of bearing seal is acceptable for life of bearing.

c. viscous damper bearings for evidence of abnormal leakage or distressed grease (discolored with burnt orpeculiar odor and may appear oily in appearance).

d. wipe down bearing and surrounding area with clean dry low-lint cloth.e. viscous damper tube assembly for debonding of damper tube (bladder assembly) from liner.f. bearing seals for damage, deterioration, and proper installation.g. supports for cracks, distortion, and proper oil level (air bubble less than one inch is acceptable).h. disconnect coupling support bearings for discoloration or loss of grease.i. viscous damper bearing on disconnect coupling drive shaft assembly (output drive shaft on disconnect jaws) for

extrusion of Teflon liner on outer race of ball bearing. Extrusion of more than 1/4 inch will require replacementof disconnect coupling drive shaft assembly before further flight. Extrusion of 1/4 inch or less will requirereplacement of disconnect coupling drive shaft assembly at earliest practical opportunity.

j. disconnect coupling housing seal for cracks at input jaw assembly attachment points.k. close No. 2 tail drive shaft access.l. fold pylon. Refer to applicable maintenance manual.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

4.7

Continued

NOTE: Steps m. and n. are to be performed daily while at sea.

m. using soap and water, clean salt encrustation from canted bulkhead.


n. spray canted bulkhead area with corrosion preventive compound.o. canted bulkhead area exposed fittings and hardware for damage and security. Lockpin lugs for displaced

bushing, indicated by gap beneath bushing flange or broken or disturbed sealant.p. pylon lockpin lug bushings for displacement, indicated by gap beneath bushing flange or broken or disturbed

sealant.q. pulleys for wear, security, and cotter pins.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

4.8

Continued

r. cables for fraying, wear, and security.s. electrical switches for security.

NOTE: Proper lubrication for disconnect coupling and disconnect shaft jaws consists of grease in void between jaw teethand outer rim of seal and in jaw teeth, forming a continuous ring and filling in all tooth spaces.

t. disconnect coupling (forward) jaw for lubrication.u. disconnect shaft (aft) jaw for lubrication.v. disconnect couplings for cracks. Refer to applicable maintenance manual.


w. if lubrication is required, hand pack jaws with grease.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

4.9

Continued

CAUTION: Fluids (including water) can dissolve grease and cause premature wear of disconnect coupling components.Use only a clean dry rag for cleaning.

NOTE: Specific area to be inspected is at base of fillet radius on disconnect coupling shaft viewed through first andsecond forward-most coils of spring.

x. using a clean low-lint cloth, clean fillet radius of shaft by rubbing back and forth in gap between first and secondforward most coils of spring.

y. visually inspect shaft diameter at base of fillet radius for circumferential cracks. Crack may appear as a thincircumferential line at base of radius. Use a flash light and mirror as required.

NOTE: If entire circumference of shaft cannot be seen because of spring end coil, rotate spring enough to see entirecircumference.

z. if cracks are found, remove jaw and spring, clean shaft and repeat inspection. If cracks are still found, replacedisconnect coupling. Refer to applicable maintenance manual. If no cracks are found, inspection is complete.

aa. close No. 3 tail drive shaft access.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

4.10

Continued

5.2 8. Tail pylon bottom step assembly:

CAUTION: Bottom step assembly can be viewed while pylon is folded. If guide pin moves inward, damage may resultto cable guide pulley. If guide pin moves outboard and drops out of installation, this could allow stepassembly to depart aircraft or cause injury to personnel.

a. check guide pin for looseness, proper seating, and cracks.b. spread pylon. Refer to applicable maintenance manual.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

4.11

End of Card

3.1 1. Fuel system components:a. open transition section access; attaching hardware for security.b. transition section bilges: wipe dry accumulated moisture.c. transition section fuel dump pump support brackets, fuel hoses, lines, fittings, mount brackets, and connectors for

cracks, evidence of leakage, and fumes.d. dump/transfer pump(s), manifold assemblies, transfer valves, dump valves, and all external breakaway valves

for evidence of leakage or premature activation of external breakaway valve.e. APU accumulator start valve, lines, and connectors for evidence of hydraulic leaks.f. fuel cell upper surface; wipe dry accumulated moisture, especially in recess of upper fuel cell panel.g. tail rotor flight control guide tube passing through ECS duct (STA 405, BL 14 RH, WL 267) for security.

3.1 2. ASC (Armament System Controller) mounts for cracks, security, and cotter pin.

3.1 3. Tail wheel shock strut hydraulic indication for proper servicing.

3.1 4. Remove thermal barrier:a. hydraulic lines for leakage, chafing, and security.b. tail pulleys and cables for wear, security, and cotter pins.



N COND AIR


1 January 1997 NA

NA

NA

0.2PC

1

5

Continued

c. all components for security.d. pylon cone ribs for cracks.e. tail section mounting bolts for security and slipmarks.f. install thermal barrier.g. close transition section access.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

5.1

End of Card

Assisted by PC #2 (0.1 Hr)


Corrosion Preventive Compound MIL-DTL-85054Dry-Cleaning Solvent MIL-PRF-680, Type IIIIsopropyl Alcohol TT-I-735Low-Lint Cloth A-A-59323, Type II

2.1, 2.2 1. Cabin:a. open cabin door; latch and attaching hardware for security; window and seal for deterioration/condition.b. cabin door:

(1) for operation, seals, and deterioration.(2) emergency jettison handle shearwire.

NOTE: Maximum continuous length of track where retention of door flange is missing or damaged is limited to 3.5



N COND AIR


31 January 1997 ON

NA

NA

0.5PC

1

6

Continued

inches. Minimum distance between damaged sections is 4 inches. No damage allowed on flange mating withairframe structure.

(3) lower track and retention flange for damage and cracks.c. ASO/TSO restraint system:

(1) place inertia reel control handle aft.(2) pull out shoulder harness; inertia reel for freedom of movement and locking.(3) shoulder harness for rips and tears.(4) release shoulder harness; place inertia reel control lever forward.(5) lap and crotch belts for rips and tears.(6) rotary buckle for operation and freedom of movement.

d. vertical and horizontal locking pins on ASO/TSO seat for cracks and security.e. ASO window:

(1) emergency jettison handle shearwire.(2) window and seal for deterioration/condition.

f. passenger/instructor seat (if installed):(1) seats for proper operation.(2) rotary buckles for operation, freedom of movement.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

6.1

Continued

(3) harness for rips and tears.(4) cables for fraying.(5) seat attenuators for integrity/actuation.

g. RAST probe and hoist assembly (if installed) for security, ratchet, and extension bar for security.h. main RAST probe for following (only if using RAST for shipboard operations):

WARNING: To prevent injury to personnel, keep area under RAST probe clear when system is activated. Beforeperforming any maintenance on probe assembly make sure it is in extended position. Probe is equippedwith two 80 pound springs. Use extreme caution. If rapid security device (RSD) is being utilized to secureaircraft, beams must be opened and safety bar installed prior to performing this inspection.

(1) if utilized, open RSD beams and install safety bar. Lower RAST probe. Refer to applicable maintenancemanual.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

6.2

Continued

Dry-Cleaning Solvent, MIL-PRF-680 101

(2) clean main RAST probe lower housing with dry-cleaning solvent.

NOTE: Set screw is installed from inside inner bore of lower RAST probe adapter.

(3) lower RAST probe housing set screw for backing out/missing.(4) lower RAST probe housing for longitudinal cracks. Pay particular attention to area where RSD beams make

contact.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

6.3

Continued

Corrosion Preventive Compound,MIL-DTL-85054 455

(5) if no cracks are present, protect lower RAST probe barrel assembly with two coats of corrosion preventivecompound.

(6) RAST probe lower housing ring for freedom of movement cracks.(7) RAST probe barrel housing for cracks and Teflon guides for wear.(8) raise RAST probe. Refer to applicable maintenance manual. If utilized, remove RSD safety bar and close

RSD beams.

NOTE: A small cotter pin is inserted through cutter housing just forward of where cartridge activated device (CAD) isinserted. Cotter pin must have slight freedom of rotation. If cotter pin is seized or missing, CAD has been fired.

(9) missing or seized cotter pin.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

6.4

Continued

i. APU handpump handle for security.j. hoist pendant for security.k. rescue hoist control panel back-up control switch cover assembly for security.l. soundproofing for security and attaching hardware for security.

m. sonar reeling machine/pedestal/glass housing for security, damage, and cracks.n. sonar funnel housing boot for security, rips, and tears.o. sonar drift sensor connectors for security.p. sonar triaxial connectors for security.q. sheave and swivel assembly for freedom of movement, salt encrustation, damage, and security.r. reeling machine hydraulic lines for leaks and security.s. TSO sliding console for proper sliding operation, without binding harness.t. TSO sliding console tracks for security.u. TSO sliding console lockpins for cracks and security.v. internal auxiliary fuel cell for security, damage, and leaks (forward cabin).w. remove soundproofing panel on top of auxiliary tank as follows:

(1) loosen stud fasteners securing soundproofing panel to ceiling and fuel tank. Remove panel.(2) fuel lines and fittings above internal auxiliary tank for evidence of fraying, chafing, cracks, or fuel stains.(3) fuel tank for cracks and evidence of fuel leakage.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

6.5

Continued

(4) breakaway valve for evidence of leakage or premature activation.x. install soundproofing panel as follows:

(1) before installing soundproofing panel, make sure area is clean and free of FOD.(2) position soundproofing panel against ceiling and fuel tank.(3) secure soundproofing to ceiling and fuel tank with stud fasteners.

y. main fuel cells:(1) remove HIFR soundproofing panels.(2) fuel transfer line above starboard fuel tank for evidence of fraying, chafing, cracks, or fuel stain.

NOTE: On Spectrum and Textron starboard breakaway valve, premature activation can be determined by alignmentof indicator screw. If screw slot is perpendicular to direction of flow, valve has closed. On Aeroquip breakawayvalve, activation can be detected by appearance of yellow band around frangible section of valve.

(3) breakaway valve above right fuel tank for evidence of leakage or premature activation.(4) vent tube fitting for looseness.(5) transfer check valve for evidence of leakage.(6) proper stowage and security of HIFR line.(7) HIFR Go/No-Go gage for leaks; security drain valve closed.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

6.6

Continued

(8) ECS ducts for cracks and security.(9) install soundproofing panels.


NOTE: Commercial nonabrasive glass cleaner may be used in place of isopropyl alcohol.

2. Wipe control box faceplates and display screens with isopropyl alcohol.

3. Helicopter emergency egress lighting system (HEELS) (if installed):a. control units battery test:

(1) on right side control unit (located aft of cabin door), place control unit ENABLE/DISABLE switch to ENABLE



N COND AIR


1 January 1997 ON

NA

NA

PC

1

6.7

Continued

position. Depress BATTERY TEST switch for 6 seconds and release. GREEN indicator light shall light andmaintain initial intensity for full 6 seconds.

(2) repeat step a. for left control unit, located in recessed compartment below and forward of SO window.(3) if lamps fail to illuminate or do not maintain initial intensity, batteries should be replaced or charged prior

to any flight requiring HEELS lighting.b. HEELS lighting strips test:

(1) make sure CB marked NO. 1 DC BUSS HEELS (SO CB panel) is pushed in.(2) place HEELS switch located on SO lighting panel to ARM.(3) place HEELS TEST switch, momentarily to TEST, then return to NORMAL.(4) lighting strips should illuminate once switch is returned to normal.(5) set HEELS switch to OFF.(6) lighting strips should extinguish.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

6.8


2.1, 2.2 1. General condition of portable fire extinguishers.a. missing or broken shear wire.b. loose or broken horn.c. proper attachment.d. head assembly for security.e. inspection due date.

2.1, 2.2 2. Helicopter mounted first aid kit:a. general condition of first aid kit.b. missing or broken shear wire.c. proper attachment.d. inspection due date.



N COND AIR


1 January 1997 NA

NA

NA

0.1PC

1

7



Hydraulic Fluid MIL-PRF-83282Low-Lint Cloth A-A-59323, Type II

1.2 1. Right cockpit door:a. latches and attaching hardware for security.b. emergency jettison handle for security and shearwire; door for operation; seals for deterioration.

1.2 2. Pilot restraint system:a. place inertia reel control lever aft.b. pull out shoulder harness: inertia reel for freedom of movement and locking.c. shoulder harness for rips and tears.d. release shoulder harness; place inertia reel control lever forward.e. lap and crotch belts for rips and tears.f. rotary buckle for operation and freedom of movement.g. attenuator for cracks, dents, extension, and missing hardware.



N COND AIR


31 January 1997 ON

OFF

NA

0.4PC

1

8

Continued

WARNING: To prevent damage to equipment and injury to personnel do not release handle unless seat is occupied.Keep fingers away from seat frame while adjusting seat.

1.2 3. Vertical and horizontal locking pins on pilot seat for cracks, security, and proper operation.

1.2 4. Pilot cyclic stick:a. open zipper on pilot cyclic stick boot.b. supports, bellcranks, levers, control rods, and cyclic control for cracks and security.c. close zipper on pilot cyclic stick boot.

1.2 5. Pedal adjustor for cracks and security.

1.2 6. Pilot collective stick:a. open zipper on pilot collective stick boot.b. supports, bellcranks, levers, control rods, yoke housing, and collective controls for cracks and security.c. close zipper on pilot collective stick boot.



N COND AIR


1 January 1997 ON

OFF

NA

PC

1

8.1

Continued

1.2 7. Pilot main landing gear brake master cylinders:a. open zippers on pilot pedal boots.


b. wipe exposed piston rod with low-lint cloth, dampened with hydraulic fluid.c. cylinders for evidence of leakage.d. close zippers on pilot pedal boots.



N COND AIR


1 January 1997 ON

OFF

NA

PC

1

8.2



Tire Pressure Gage A-A-1726Tread Depth Gage MIL-I-18422



2.2 1. Right main landing gear:a. brake hoses, lines, fittings, and unions for evidence of leakage.

NOTE: Discs require replacement when indicator is pressed flush with bushing.

b. brake discs for wear by pressing wear pin indicators.



N COND AIR


31 January 1997 NA

NA

NA

0.4PC

1

9

Continued

c. wheel brake assembly for evidence of leakage.d. brake housing for cracks, damage, and security.e. brake to mounting bracket bolts for torque stripe or torque stripe slippage.f. drag beam for cracks (particularly in area of jack pad).


g. wipe shock strut piston with low-lint cloth, dampened with lubricant.h. shock strut for evidence of leakage, scoring on piston, and cracks.i. strut boot for tears and security of mounting.j. air servicing valve and cap for security.k. axle attach bolts for cracks and security.l. hub halves for missing hardware and security.

m. wheels for damage.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

9.1

Continued

NOTE: Reject tire when tread is worn to bottom of any tread groove for continuous length of 12 inches, or when wearhas reached first fabric ply past bottom of tread groove, whichever comes first. Reject any tire when sidewall cutis deeper than 1/8 inch.

n. tire for damaged tread and sidewall and correct pressure (95-100 psi).

2. Lower IFF antenna for cracks, and attaching hardware for security.

3. HF long wire antenna:a. standoffs and clamps for security.b. wires for chafing, fraying, proper tension and security.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

9.2



Flashlight -Inspection Mirror -Magnifying Glass (10X)Stopwatch S-10


Grease MIL-G-81827Low-Lint Cloth A-A-59323, Type IILubricant MIL-PRF-32033

6.1, 6.2 1. Swashplate and scissors for cracks, dents, distortion, and security.

6.1, 6.2 2. Pitch control rods for damage, cracks, and looseness.



N COND AIR


31 January 1997 NA

NA

NA

0.5PC

1

10

Continued

a. grasp main rotor pitch control rod assembly and move control rod in all directions. Motion between pitch controllink, jam nut/rod ends is not acceptable.

NOTE: On main rotor pitch control rod assemblies with Teflon lined bearings, make sure motion is not movementbetween spherical bearing and outer race before replacing components.

b. if motion is detected, remove and install new pitch control link, jam nut/rod ends as required. Refer to applicablemaintenance manual.

WARNING: Components identified with an asterisk (*) contain bushings made of copper beryllium. A light tarnish isnormal; dust is toxic, do not attempt to clean. Wash hands thoroughly after handling.

6.1, 6.2 3. Spindle and hinge assemblies:a. (*) pitch horns for cracks/gouges especially at inboard surface from pitch control rod attachment to spindle

attachment.b. spindle flange bolts for cracks.c. hinge lockpin lug areas for cracks and damage.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

10.1

Continued

d. (*) lockpin puller assembly for security.e. hinge areas for cracks.f. hinge pin attach lugs for cracks.g. lockpin attach lugs for cracks.h. journal bearing inner race for rotation (discontinuity of white stripe) or axial movement.i. spindle shaft for damage from contact with lead stop or with elastomeric bearing. No dents, nicks, or gouges

permitted. Minor surface polishing is acceptable.j. blade fold and deice harness for chafing and security.k. bumper pad for security of rubber (black blade only).l. main rotor head damper for evidence of leakage.

m. main rotor elastomeric bearing assembly:

NOTE: Elastomer extrusion is a layer of elastomer that has squeezed out from between two shims or between shim andendplate. Bearing is inspected through two 2.0 in. diameter side inspection holes (two per hub arm) and 2.0 in.diameter drain hole (one per hub arm). Overlap of elastomer on end plate outer diameter, from manufacturingprocess, is not cause for rejection of bearing. Peeling of rubber mold lines running from inboard of bearing isalso not cause for rejection.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

10.2

Continued

(1) elastomeric thrust bearing:(a) using a flashlight and mirror visually inspect thrust bearing surface, four per aircraft, for elastomer

extrusion.(2) elastomeric spherical bearing:

(a) using a flashlight and mirror visually inspect inner and outer surfaces of spherical bearing, four peraircraft, for wear, laminate separations and shim cracks.


n. lubricate fold hinge bushing and spindle with light coat of grease to prevent lockpin binding.

6.1, 6.2 4. (*) Droop stops and anti-flap assemblies:a. springs broken, and missing.b. attaching hardware for security.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

10.3

Continued

c. cam, pin, and support for cracks and damage.


d. apply thin film of lubricant, wipe excess with low-lint cloth.

6.1, 6.2 5. Main rotor blade:a. cuff for cracks, damage, and security, especially surface between each bolt, forward and aft edges of cuff plate

on upper and lower surfaces and between blade attachment and flange.b. blade to cuff attaching bolts for security.c. servicing valve for security and cap.d. root surfaces for disbonding.e. tip cap (See illustration Card 10.8):

(1) for paint buckle, hole elongation, screw back-out, security.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

10.4

Continued

CAUTION: It is essential that area around bend radius and adjacent screws be carefully inspected to prevent cracksfrom enlarging to allow tip cap to separate from blade.

(2) for cracks in upper and lower surfaces, pay particular attention to attachment screw area.(3) using flashlight and 10X magnifying glass, carefully inspect following screw areas; no visually detected

cracks are allowed.(a) at attachment hole number 4 and attachment hole number 5.(b) approximately 1/2 in. inboard of hole number 6.(c) between attachment hole number 6 and attachment hole number 7, approximately 1 in. aft of

attachment hole number 6.(4) remainder of tip cap for cracks and security; nickel abrasion strip for cracks and disbonds.

f. composite tip cap (See illustration Card 10.9):(1) for cracks, disbonds, delaminations, damage around attachment holes, and presence of screws. Pay

particular attention to cross hatched area in illustration, both upper and lower areas.(2) remainder of tip cap for erosion, cracks, disbonds, delaminations, or other damage.

g. BIMT indicator (See illustration Card 10.10):(1) BIMT for cracks and security.(2) BIMT indicator for white indications, no black permitted.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

10.5

Continued

CAUTION: Do not hold indicator. Heat from hand is enough to change internal reference pressure. Erroneous indicatorreading will result.

NOTE: When testing pressure indicator, valve plunger under handle must be pushed fully down. This will shut off allspar pressure. It may be necessary to use both thumbs to do this. Also, press on ridged part of handle, not onsmooth tip. A partly pressed plunger may cause loss of spar pressure and a slow indication, or no indicationat all. If indicator is operating properly, a full black (unsafe) indication must show within 10 - 30 seconds. Usestopwatch sweep-second hand to time test.The 10 to 30-second time limit applies when temperature is 20°F (-6.7°C) or above. At any lower temperature,extend upper limit to corresponding time listed below:

(3) BIMT indicator for proper operation:(a) press in and hold manual lever (grenade-type handle). Do not place hand on glass bulb.(b) release lever; indication must snap back immediately, leaving an all-white (safe) condition.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

10.6

Continued

TEMPERATURE TIME19° to 0°F (-7.2° to -17.8°C) 35 seconds-1° to -20°F (-18.3° to -28.9°C) 40 seconds-21° to -40°F (-29.4° to -40°C) 50 seconds-41° to -60°F (-40.5° to -51.1°C) 60 seconds

6.1, 6.2 6. Blade deice distributor for security.

6.1, 6.2 7. Pitch lock mechanism fully retracted into housing.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

10.7

Continued

HOLE 4

HOLE 5

HOLE 6

HOLE 7

HOLE 12

4 INCHES

REPAIR AREAUP TO 1 INCH CRACKSMAY BE REPAIRED

SANC1244

CARD CHANGE NO.10.8

SA4047-S70B-MRC-300DATE: 1 January 1997 3

DAILY

Continued

SANC2968

HOLE #1

HOLE #6

HOLE #5

HOLE #4

LIPREGION

NICKELABRASIONSTRIP

TIP FAIRINGSKIN

1.25

.30(TYPICAL)

COMPOSITE TIP CAP

CARD CHANGE NO.10.9


DAILY

Continued

SANC1245

SPAR

MANUAL TESTLEVER

WHITE

BIM INDICATORR

BLACK

SPAR

FULL BLACKINDICATION(SEE NOTE)

MANUAL TESTLEVER FULLYDEPRESSED

NOTEONLY FULL BLACK INDICATION ISACCEPTABLE DURING TEST.INDICATOR MUST RETURNIMMEDIATELY TO NORMAL WHITEINDICATION FOLLOWING TEST.

PRESSURE NORMAL LOW PRESSURE INDICATOR TEST RESPONSE

CARD CHANGE NO.10.10


DAILY



Acid Brush H-B-63Cleaning Cloth CCC-C-46Grease MIL-G-81827Lubricant MIL-PRF-32033

NOTE: Compliance with this card is required when main rotor blades are folded.

6.1, 6.2 1. Using cleaning cloth, remove grease and dirt from following items and inspect:a. main rotor blade lockpin.b. lockpin assembly.c. hinge lockpin bushing.d. hinge lockpin outer edges.



N COND AIR


31 January 1997 NA

OFF

NA

0.5PC

1

11

Continued


6.1, 6.2 2. Using acid brush, apply light coat of grease to:a. main rotor blades lockpins.b. lockpin assembly.c. hinge lockpin bushing.d. hinge lockpin outer edges.



N COND AIR


1 January 1997 NA

OFF

NA

PC

1

11.1

Continued


NOTE: To be performed prior to all auto blade spreads.

6.1, 6.2 3. Spray spring washers with lubricant.

6.1, 6.2 4. Inspect fold hinge gear assembly and detent by looking through top of cover. If detent is flat against spindleassembly, detent has engaged gear assembly and blades can be spread automatically.

6.1, 6.2 5. If detent is not flat against spindle assembly and is about 1/8-1/4 inch away, refer to applicable maintenancemanual, to rotate gear and contact spindle assembly. If detent engages gear and contacts spindle assembly,blades can be spread automatically. If detent does not contact spindle and engage, blades must be spread usingblade fold test set, refer to applicable maintenance manual.



N COND AIR


1 January 1997 NA

OFF

NA

PC

1

11.2


Assisted by PC #2 (0.5 Hrs)


Flashlight -Inspection Mirror -

6.1, 6.2 1. Engine fire bottles:a. open fire bottle access; attaching hardware for damage.b. gage on fire bottles for pressure within limits on decal.

6.1, 6.2 2. Fire detectors:a. open No. 1 and No. 2 work platform/engine access and APU access.b. for cleanness and security.c. for proper operation:

(1) turn BATT switch ON.(2) shine flashlight, with red filter, on No. 1 fire detector.(3) No. 1 engine T-handle light and both copilot, and pilot master warning FIRE lights will go on.



N COND AIR


1 January 1997 ON

NA

NA

0.8PC

1

12

Continued

(4) remove flashlight, all warning lights will go off.(5) repeat steps 2 through 4 for No. 2 engine and APU.(6) turn BATT switch OFF.

6.1, 6.2 3. Tail rotor drive shaft:a. No. 2 drive shaft and aft flexible coupling for damage, cracks, and separation.b. viscous damper bearing for evidence of leakage and proper oil level (bubble not greater than 1 inch).c. support for cracks and distortion.d. close fire bottle access.

6.1, 6.2 4. APU:a. attaching hardware for security and cleanness.b. fuel line fittings for evidence of fuel leakage.c. bleed air clamps for damage and security; safety wire for security.d. APU inlet screen for FOD.e. fire extinguisher discharge lines for chafing and security.f. all lines for chafing and security.g. starter and generator for security.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

12.1

Continued

h. exhaust pipe and clamp for security and cracks.

6.1, 6.2 5. ECS compartment:a. open ECS access; attaching hardware for security.b. No. 2 drive shaft and forward flexible coupling for cracks, damage, and separation.c. oil cooler output viscous damper bearing for evidence of leakage, proper oil level, and evidence of over

temperature.d. bleed air clamps for damage and security; safety wire for security (Particular attention to J tube).e. support for cracks and distortion.f. oil level on air-cycle machine.g. close ECS access.h. close APU access.

6. Oil cooler access:a. open right and left oil cooler/utility hydraulic reservoir accesses; attaching hardware for security. Airframe latch

angles and support structure for damage and security.b. rotor brake supports and spark shield for cracks or loose and missing hardware.c. rotor brake accumulator for evidence of leakage.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

12.2

Continued

d. rotor brake lines and valves for evidence of leakage.e. rotor brake disc for evidence of scoring, cracks, or warping.f. wear indicator pins (See illustration Card 12.5).

(1) brake lining needs replacement if 1/4 inch diameter pin is less than 3/16 inch from housing.g. No. 1 drive shaft section and flexible couplings for cracks, damage, and separation.h. rotor brake housing for damage and evidence of leakage.

NOTE: If index motor not installed, check security of spark shield.

i. indexing motor for damage and security.

NOTE: Chafing of braided oil (radiator) lines occurs most often against lip and stator vanes on fan housing, corner offan mount bracket, No. 2 engine fuel selector valve, fuel line joint below valve, and fuel line beneath oil hoses(See illustration Card 12.6).

j. bleed air ducting, air start lines, braided fuel and oil lines, fire extinguisher discharge lines for clamps, attachinghardware, and chafing.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

12.3

Continued

CAUTION: Do not remove epoxy in pockets which is used for balancing rotor.

k. fan rotor for debris trapped inside pockets between fan blades.l. utility hydraulic lines and valves for evidence of leakage.

m. utility hydraulic reservoir for evidence of leakage.n. utility hydraulic pump (gear box mounted) for evidence of leakage. PDI filter button popped on utility hydraulic

manifold.o. oil cooler for damage and FOD.p. fan intake for obstruction, using flashlight and inspection mirror.

NOTE: Heat exchanger is checked through exhaust port in cover, using flashlight and inspection mirror.

q. for obstruction in air flow, distortion to radiator core, and dents.r. close and secure oil cooler/hydraulic reservoir accesses and No. 2 tail drive shaft access.

7. VHF/UHF and emergency locator antennas for damage, cleanness, and security.



N COND AIR


1 January 1997 ON

NA

NA

PC

1

12.4

Continued

SANC0227B

TORQUELESS GRIPSEATING TOOL

ROTOR BRAKEHOUSING

SEATINGTOOL

SUPPORTSURFACE

TORQUELESSGRIPS, 2 REQ’D6 PLACES (TYP)

REPLACE BRAKE LININGSWHEN 1/4-INCH DIAMETERPIN IS LESS THAN 3/16-INCH FROM HOUSING

CARD CHANGE NO.12.5

SA4047-S70B-MRC-300DATE: 1 January 1997

DAILY

Continued

NOTE

POTENTIAL CHAFING LOCATIONS.

FAN

VANES ONOUTSIDE

OIL INLET HOSE(FROM MAIN

OIL OUTLET HOSE(RETURN TO MAINTRANSMISSION)

CORNER OF FANMOUNT BRACKET

LIP OF FANSTATOR

NO. 2 FUELSELECTOR

FUEL LINE JOINTBELOW VALVE

FUEL LINEBENEATH

(SEE NOTE)

(SEE NOTE)

(SEE NOTE)

(SEE NOTE)

(SEE NOTE)

(SEE NOTE)

TRANSMISSION)

OF FAN

OIL HOSES

VALVE

RADIATOR

STATOR

SANC1247

CARD CHANGE NO.12.6


DAILY


6.1 1. No. 1 engine:a. open No. 1 work platform/engine accesses and intake fairing.b. No. 1 work platform/engine access door vertical stiffeners FWD and AFT, particularly in area two - four inch

outboard of hinge attach points for cracks/delaminations/gouges through rib surface (doors may fail duringmaintenance if cracks are present in this area).

c. engine access door attaching hardware and latches for general security; ribs for structural integrity.d. engine aft mount strut and deck fitting bearings for looseness/displacement.e. engine exterior for oil or evidence of fuel leakage. Inlet for damage and FOD.

NOTE: Leakage appears as dark stain below LDS/PAS rotary input.

f. hydromechanical control unit for evidence of leakage.g. oil cooler for evidence of leakage.h. fuel filter and fuel pressure switch for evidence of leakage.i. starter reservoir for proper oil level (Garrett starters only). Starter housing for cracked inlet housing.j. fire extinguisher discharge lines for damage, chafing, and security.k. firewall and firewall brackets, stiffeners, supports, and attachment hardware for cracks and security.l. all lines and connectors for security and leakage.



N COND AIR


1 January 1997 NA

NA

NA

0.4PC

1

13

Continued

m. electrical wiring for security and damage.n. bleed air clamps for damage and security; safety wire for security.o. engine mounts for cracks and security.p. combustion section for cracks and hot spots.q. engine/compartment components for cracks and security.r. close No. 1 work platform/engine access.

6.2 2. No. 2 engine:a. open No. 2 work platform/engine accesses and intake fairing.b. No. 2 work platform/engine access door vertical stiffeners FWD and AFT, particularly in area two - four inch

outboard of hinge attach points for cracks/delaminations/gouges through rib surface, (doors may fail duringmaintenance if cracks are present in this area).

c. engine access door attaching hardware and latches for security; ribs for structural integrity.d. engine aft mount strut and deck fitting bearings for looseness/displacement.

NOTE: Leakage appears as dark stain below LDS/PAS rotary input.

e. engine exterior for oil or evidence of fuel leakage. Inlet for damage and FOD.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

13.1

Continued

f. hydromechanical control unit for evidence of leakage.g. oil cooler for evidence of leakage.h. fuel filter and fuel pressure switch for evidence of leakage.i. starter reservoir for proper oil level (Garrett starters only). Starter housing for cracked inlet housing.j. fire extinguisher discharge lines for damage, chafing, and security.k. firewall and firewall brackets, stiffeners, supports, and attachment hardware for cracks and security.l. all lines and connectors for security and leakage.

m. electrical wiring for security and damage.n. bleed air clamps for damage and security; safety wire for security.o. engine mounts for cracks and security.p. combustion section for cracks and hot spots.q. engine components for cracks and security.r. close No. 2 work platform/engine access.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

13.2



Corrosion Preventive Compound MIL-C-81309, Type IIHydraulic Fluid MIL-PRF-83282Low-Lint Cloth A-A-59323, Type II

WARNING: Opening access panels in high wind can result in door separating from aircraft.

6.1, 6.2 1. Open flight controls/accessories access; attaching hardware and latches for security.

6.1, 6.2 2. Pilot assist module:a. coupling and mating surfaces for evidence of leakage.b. pressure reducer failure indicators for actuation.

6.1, 6.2 3. Trim/boost servos:



N COND AIR


31 January 1997 NA

NA

NA

0.4PC

1

14

Continued


a. wipe all exposed pistons with a low-lint cloth and hydraulic fluid.b. roll trim assembly for evidence of leakage.c. pitch trim assembly for evidence of leakage.d. yaw boost servo for evidence of leakage:

(1) power piston shaft (both sides of shaft at each end of servo) for cracks or a complete fracture, particularlyin area where output clevis attaches and imperfect threads are located.

(2) redundant link for damage.e. collective boost servo for evidence of leakage:

(1) power piston shaft (both sides of shaft at each end of servo) for cracks or a complete fracture, particularlyin area where output clevis attaches and imperfect threads are located.

(2) redundant link for damage.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

14.1

Continued

6.1, 6.2 4. Transfer modules for evidence of leakage and security.

NOTE: Primary servos have a slight natural hydraulic weepage when static. Suspected leakage shall be verified bydynamic leak test. Refer to applicable maintenance manual.

6.1, 6.2 5. Primary servo assemblies for evidence of leakage, cracks, and security.a. power piston shaft for cracks or a complete fracture, particularly in area where output clevis attaches and

imperfect threads are located.


b. wipe all exposed pistons with a low-lint cloth and hydraulic fluid.

6.1, 6.2 6. Mixer assembly output levers/bellcranks for cracking, deformation, or cocking.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

14.2

Continued

6.1, 6.2 7. Mixer mounting bolts for torque stripe and evidence of rotation.

6.1, 6.2 8. Pitch bias actuator for cracks.

6.1, 6.2 9. Yaw and collective trim servo for cracks and security.

6.1, 6.2 10. Hydraulic refill reservoir for cracks.

6.1, 6.2 11. All flight control rods and linkage for security and proper attachment.

6.1, 6.2 12. No. 1 accessory module:a. for cracks and water entrapment.b. mating/mounting surfaces for evidence of leakage.

6.1, 6.2 13. No. 1 hydraulic pump module:a. bleed valve for evidence of leakage.b. self-sealing coupling and quick-disconnect for evidence of leakage.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

14.3

Continued

c. filter housings for evidence of leakage.d. reservoir housing for evidence of leakage.e. drive shaft face seal for evidence of leakage.f. drain lines for obstruction.

6.1, 6.2 14. No. 2 accessory module:a. cracks and water entrapment.b. mating/mounting surfaces for evidence of leakage.

6.1, 6.2 15. No. 2 hydraulic pump module:a. bleed valve for evidence of leakage.b. self-sealing couplings and quick-disconnects for evidence of leakage.c. filter housings for evidence of leakage.d. reservoir housing for evidence of leakage.e. drive shaft face seal for evidence of leakage.f. drain lines for obstruction.

6.1, 6.2 16. Main module:



N COND AIR


1 January 1997 NA

NA

NA

PC

1

14.4

Continued

a. housing and mounting feet for cracks.b. mating lines, mast area, tail takeoff flange area for leakage.c. module for water entrapment.d. torque stripe and evidence of slippage on mounting bolts.

6.1, 6.2 17. Torque shaft lever upper support bearing:a. bearings in upper support of torque shaft levers for FOD and proper lubrication with grease.b. clean area with clean cloth; area for FOD.

6.1, 6.2 18. Backup pump module:a. bleed valve for evidence of leakage.b. self-sealing couplings and quick-disconnects for evidence of leakage.c. filter housing for evidence of leakage.d. drive shaft face seal for leakage.e. reservoir housing for evidence of leakage.f. electrical connectors for security.g. motor for cracks, evidence of overheating and security.h. drain lines for obstruction.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

14.5

Continued

6.1, 6.2 19. No. 1 and No. 2 input module assemblies:a. modules for cracks, damaged sealant, and evidence of leakage. Housing for paint discoloration from

aluminized gray to brown.b. mating/mounting flange for evidence of leakage.c. gimbal for separation.d. oil return lines for evidence of leakage.e. moisture entrapment areas for moisture (See illustration).

(1) wipe moisture dry from entrapment areas using clean dry cloth.


(2) preserve moisture entrapment areas with corrosion preventive compound.f. flight control installation:

(1) dowel pin sealant for bulging, blistering, or cracking.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

14.6

Continued

(2) bolts and retaining angles for deformation and security of installation.g. wipe out any water from around dowel pins and sealant.h. for minor nicks, gouges, scratches, and pitting.

NOTE: Corrosion in this area will appear as white powdery snow like mounds or white spots on surface.

i. for deterioration and debonding of sealant around pad and on hardware (2 bolts and dowel pins).j. for chipping of paint or protective finish.


k. spray area with corrosion preventive compound to remove moisture.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

14.7

Continued

6.1, 6.2 20. Close flight controls/accessories access.



N COND AIR


1 January 1997 NA

NA

NA

PC

1

14.8

Continued

SANC1250

LH TIE RODDOWEL PIN

AFT CONTROL BRIDGEDOWEL PIN

RH TIE RODDOWEL PIN

FWD CONTROL BRIDGEDOWEL PIN

AFT CONTROL LINKDOWEL PIN

CARD CHANGE NO.14.9


DAILY

Continued

SANC1251

FWD

MOISTUREENTRAPMENTAREAS



CARD CHANGE NO.14.10


DAILY


2.1, 2.2 1. External auxiliary fuel tanks (if installed):a. evidence of leakage.b. fin, tank, connector, and hardware for damage and security.c. tank for damage, fuel leakage, and quick-disconnect for proper position and movement.d. sway braces for proper adjustment.

2.1, 2.2 2. Fuel samples:

NOTE: Fuel samples shall be taken prior to first flight of day.

a. take fuel from low-point drains of each fuel cell/tank (including auxiliary fuel tanks if installed) forcontamination.



N COND AIR


1 January 1997 NA

NA

NA

0.7PC

1

15


1. BRU-14/A bomb rack(s), if installed. (Refer to NAVAIR 11-5E-18):a. open stores latch access.

WARNING: If auxiliary tanks not installed; make sure electrical connector is connected to upper shorting plug. Incorrectfuel reading could result.

b. cables for fraying/damaged wiring, and damaged connectors.c. bomb rack installation for damage, security, and cleanness.d. hook toe and throat for cracks, chips, and galling; lubricate.e. hook springs for security and damage.f. Linear Electromechanical Actuator (LEMA) for damage, proper clearance from bellcrank, and security.g. arming units for damage, security, and shearwire.h. In-Flight Operable Bomb Rack Lock (IFOBRL) for damage, security, and proper operation.i. secondary release assembly for fired condition and damage.j. auxiliary unlock assembly for fired condition and damage.k. close stores latch access.



N COND AIR


1 January 1997 NA

NA

NA

0.2PC

1

16

Continued

ELECTRICALCONNECTOR

ELECTRICALCABLE

HOOKASSEMBLY

ARMINGUNIT

LINEARELECTROMECHANICALACTUATOR (LEMA)

HOOKASSEMBLY

BOMB RACK − MODEL BRU−14/ASA

NC1252

CARD CHANGE NO.16.1


DAILY

Continued

WEAPON PYLONACCESS PANEL

SECONDARYRELEASEASSEMBLYBRU−14 / A

BOMB RACK

STORESSUSPENSIONHOOK

AUXILIARYUNLOCKASSEMBLY

MANUALACTIVATIONKNOB

TAIL NOSEFRONT

HOOK

LATCH COCK

LOCK

UNLK

HOOKLATCH

SEAR

J521

J522

P526

J507 P520

J523

RIGHT STATION

NOTEBOTH LEFT STATIONS SIMILARTO RIGHT STATION.

P527 RHP347 LH INBOARD2P347 LH OUTBOARD


BRU−14 / A CADELECTRICALHARNESS


SANC1253A

P521 RH INBOARDP341 LH INBOARD2P341 LH OUTBOARDIFOBRL

TORPEDO PRESETCABLE JACK

LEMAS ARMINGUNIT ELECTRICALHARNESS

TORPEDOPRESET CABLE

STOWAGE FORP382 RH INBOARDP381 LH INBOARD

DUMMYRECEPTACLEAND CAP

P522 RH INBOARDP342 LH INBOARD2P342 LH OUTBOARD

CARD CHANGE NO.16.2


DAILY


NOTE: A disconnected battery stored at 77°F (25°C) may be left unattended for up to six months before it must becharged. Batteries which are installed in transducers require 90 minutes of charging either by sonar operationsor as described in step 2.

1. Maintain sonar battery charge as follows:

Battery Charge Intervals

Ambient Temp Interval40°F (4.4°C) 38 days59°F (15°C) 14 days77°F (25°C) 7 days95°F (35°C) 4 days112°F (45°C) 2 days130°F (55°C) 1 days



N COND AIR


1 January 1997 ON

NA

NA

1.7AT

1

SONAR BATTERY CHARGING

17

Continued

Ambient Temp Interval157°F (65°C) 12

hours

2. Static charging:a. connect external electrical power. Refer to applicable maintenance manual.b. perform sonar initial control settings. Refer to applicable testing and troubleshooting manual.c. depress power indicator switch on azimuth-range indicator (ARI). Adjust intensities as desired. Leave all switches

at initial settings and operate sonar set in passive mode only for a minimum of 90 minutes.d. depress power indicator switch on ARI and turn sonar set off.e. disconnect external electrical power. Refer to applicable maintenance manual.



N COND AIR


1 January 1997 ON

NA

NA

AT

1

SONAR BATTERY CHARGING

17.1

End of Card

sa4047-s70b-mrc-300

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