ecmm_256914_emergency float

2 rue Maurice Mallet 92130 Issy les Moulineaux France Tel: + 33 1 41 23 23 23 Fax: + 33 1 46 78 74 79 http://www.zodiacaerospace.com CAGE Code: F6101

This document is AERAZURs property. It can neither be copied nor divulged without AERAZURs consent. T - 1 25-69-14 REV 12

EMERGENCY FLOTATION SYSTEM

P/N : 200553-0

COMPONENT MAINTENANCE MANUAL

WITH

ILLUSTRATED PARTS LIST

This page is printed under user's responsibility and must not be retained for reference

AERAZUR COMPONENT MAINTENANCE MANUAL


T - 2 25-69-14 REV 12

PAGE INTENTIONALLY LEFT BLANK




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RECORD OF REVISIONS

MANAGEMENT OF REVISIONS: Revision number and validity: Revision 01 Initial project distribution

Revision 02 to 09 Project updating Revision 10 First distribution of manual Revision 11 First revision of manual Revision 99 89th revision of manual

Keep this list at the beginning of the manual. When receiving a revision, insert the modified pages in the existing manual, record the revision number; write the date and the managers initials.

REVISION NUMBER

REVISIONDATE

CHECKED BY

DESCRIPTION OF REVISION

INSERTION

DATE BY

(INITIALS)

REV 10 11/81 DPG/JCL Original issue. REV 11 04/08 DSE/ NFE Re-issue and complete revision of

the manual. Application of ECN 00017A. Routine inspection precisions.

REV 12 03/10 DSE Addition of pressure relief valve test to section INSPECTION/CHECK




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SBR - 1 25-69-14 REV 11

SERVICE BULLETIN RECORD

Service bulletins Insertion in revision number




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LIST OF EFFECTIVE PAGES

SECTION PAGE REV No

SECTION PAGE REV No

TITLE T-1 REV 12 Inspection/Check 501 REV 11 T-2 REV 12 502 REV 11 503 REV 11Record of Revisions RR-1 REV 12 504 REV 11 RR-2 REV 12 505 REV 11 506 REV 11Service Bulletin Record SBR -1 REV 11 507 REV 11 SBR -2 REV 11 508 REV 12 509 REV 12List of Effective Pages LEP-1 REV 12 510 REV 11 LEP-2 REV 11 511 REV 11 512 REV 11Table of Contents TC-1 REV 11 TC-2 REV 11 Repair 601 REV 11 602 REV 11Glossary of Abbreviations GA-1 REV 11 603 REV 11 GA-2 REV 11 604 REV 11 605 REV 11Table of Vendor Codes TVC-1 REV 11 606 REV 11 TVC-2 REV 11 607 REV 11 608 REV 11Description and 1 REV 11 609 REV 11Operation 2 REV 11 610 REV 11 3 REV 11 4 REV 11 Assembly (Including storage) 701 REV 11 5 REV 11 702 REV 11 6 REV 11 703 REV 11 7 REV 11 704 REV 11 8 REV 11 705 REV 11 9 REV 11 706 REV 11 10 REV 11 707 REV 11 708 REV 11Charging/Discharging 201 REV 11 709 REV 11 202 REV 11 710 REV 11 711 REV 11Disassembly 301 REV 11 712 REV 11 302 REV 11 713 REV 11 714 REV 11Cleaning 401 REV 11 715 REV 11 402 REV 11




LEP - 2 25-69-14 REV 11

CHAPTER PAGE NREV CHAPTER PAGE NREV

Assembly (Including storage) 716 REV 11 Detailed Parts List 1027 REV 10 717 REV 11 1028 REV 10 718 REV 11 1029 REV 10 719 REV 11 1030 REV 10 720 REV 11 1031 REV 10 1032 REV 10Fits and clearances 801 REV 11 1033 REV 10 802 REV 11 1034 REV 10 Special tools, fixtures 901 REV 11 Alphanumeric Index 1035 REV 10and equipment materials 902 REV 11 1036 REV 10 903 REV 11 1037 REV 10 904 REV 11 1038 REV 10 1039 REV 10Illustrated Parts List 1001 REV 11 1040 REV 10 1002 REV 11 1041 REV 10 1003 REV 11 1042 REV 10 1004 REV 11 1043 REV 10 1005 REV 11 1044 REV 10 1006 REV 11 Detailed Parts list 1007 REV 10 1008 REV 10 1009 REV 10 1010 REV 10 1011 REV 10 1012 REV 10 1013 REV 10 1014 REV 10 1015 REV 10 1016 REV 10 1017 REV 10 1018 REV 10 1019 REV 10 1020 REV 10 1021 REV 10 1022 REV 10 1023 REV 10 1024 REV 10 1025 REV 10 1026 REV 10




TC - 1 25-69-14 REV 11

TABLE OF CONTENTS

PAGE

DESCRIPTION AND OPERATION .................................................................................................1 TESTING AND FAULT ISOLATION............................................................................................N/A CHARGING / DISCHARGING.....................................................................................................201 DISASSEMBLY...........................................................................................................................301 CLEANING..................................................................................................................................401 INSPECTION/CHECK.................................................................................................................501 REPAIR.......................................................................................................................................601 ASSEMBLY (INCLUDING STORAGE) .......................................................................................701 FITS AND CLEARANCES...........................................................................................................801 SPECIAL TOOLS, FIXTURES AND EQUIPMENT MATERIALS................................................901 ILLUSTRATED PARTS LIST ....................................................................................................1001 DETAILED PARTS LIST ...........................................................................................................1007




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GLOSSARY OF ABBREVIATIONS

AMM - Aircraft Maintenance Manual APPL - Application to AR - As Required ARZ - AERAZUR Company ASSY. - Assembly CMM - Component Maintenance Manual EAS - Electrical Actuation System ECN - Engineering Change Notice EFS - Emergency Flotation System FIG - Figure FK - Figure of Knots GA - Glossary of Abbreviations IPL - Illustrated Parts List LEP - List of Effective Pages LOG - Log Card MAS - Manual Actuation System MEE - Manuel dEntretien quipement MFR - Manufacturer MSR - Master Servicing Recommendation NP - Not Procurable P/N - Part Number Qty - Quantity R or REV - Revision RF or REF - Reference RR - Record of Revisions SB - Service Bulletin SBR - Service Bulletin Record SRU - Shop Replaceable Unit = require its own documentation T - Title TC - Table of Contents




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TABLE OF VENDOR CODES

Vendor code Name Address

80205 NATIONAL AEROSPACE STANDARDS COMMITTEE AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA INC 1725 DE SALES N W WASHINGTON DC 20036 USA

88044 AERONAUTICAL STANDARDS FROM DEPT OF NAVY AND AIR FORCE WASHINGTON DC 10001 USA

96906 MILITARY STANDARDS PROMULGATED BY MILITARY DEPARTMENTS UNDER AUTORITY OF DEFENSE STANDARDIZATION MANUAL 4120 3-M USA

F0110 AFNOR (ASSOCIATION FRANCAISE DE NORMALISATION) TOUR EUROPE 92080 PARIS LA DEFENSE CEDEX 7 FRANCE

F0111 BNAE (BUREAU DE NORMALISATION DE L'AERONAUTIQUE ET DE L'ESPACE) TECHNOPOLIS 54 199 RUE JEAN JACQUES ROUSSEAU 92130 ISSY LES MOULINEAUX FRANCE

F0280 TELEFLEX - SYNERVIA 15 RUE ANTONY 94152 RUNGIS FRANCE

F6101 AERAZUR 2 RUE MAURICE MALLET 92130 ISSY LES MOULINEAUX FRANCE




TVC - 2 25-69-14 REV 11





25-69-14 REV 11 PAGE 1

DESCRIPTION AND OPERATION

1. General

The EFS is an optional equipment.

The helicopter must therefore be provided with the fittings required for the installation of the EFS, i.e., the equipment (including the electrical circuitry and the mechanical actuator assembly) permanently installed on the helicopter (FIXED PART) and the removable equipment, as required, (REMOVABLE PART) both supplied by AERAZUR.

The basic EFS included in the removable part (mainly packed inflatable floats) comprise the following sub-assemblies: One L/H float assembly, One R/H float assembly, Two inflation subsystems, One bag (N2) containing the requisite hardware. A. Purpose of the equipment and operation

The AERAZUR EFS fitted to the helicopter is intended for use as an emergency equipment to maintain the helicopter on the surface of the water in the event of ditching. In a ditching situation, the inflation system is actuated immediately by an electrical switch by the pilot. The stored high pressure gas flows from the cylinder through the hoses to the chambers of the floats. The build-up of gas in the floats opens simultaneously the covers and the floats continue to inflate until they assume their design shape.

B. General description of the EFS (see Fig. 1)

Two symmetrical floats are provided to give buoyancy to the helicopter, i.e., one L/H cylindrical float and one R/H cylindrical float.

Each float is attached by textile girt and patches to a manifold bar which is in turn attached to the helicopter skid, by means of fittings.

NOTE : The manifold bars and theirs fittings are provided with the containers. Two helium-filled cylinders mounted on the helicopter airframe by means of clamps are fixed by airframe manufacturer mountings.

Each cylinder is fitted with an inflation valve assembly, which opens rapidly when electrical power is applied to its redundant electrical fuse disc.

In view of back-up operation the inflation valve is equipped with a manual control which is fitted to a mechanical actuator assembly and initiated from the cockpit.

The cylinder is connected to the corresponding float by suitable banjo, couplings and supply hose assemblies.

The inflation subsystems are fitted to the helicopter skid and airframe by means of multiple clamps and hardware.

The fixed part comprises footstep blocks to be installed onto the front skid tube. They prevent tearing of floats during inflation.

The containers are provided with hinge device and holding system with a view to holding the packed flotation assembly raised at the rear. Holding system is used when helicopter taxiing system must be carried out.




25-69-14 REV 11 PAGE 2

A. Flight configuration C. Overhead view, flotation gear inflated

B. Ground configuration D. Afloat

(back part of float raised = for use of taxiing system)

Figure 1 Emergency flotation system (schematic)

A

B

C

D




25-69-14 REV 11 PAGE 3

C. Characteristics

(1) Total weight

Component weight in kg Qty per assy. Description

APPL. A APPL. B

1 L/H Float assembly 22.5

1 R/H Float assembly 22.5

Gas cylinder assy. - 9.01 l. APPL.A 9.2 2

- 9.42 l. APPL.B 6.2

1 Removable parts 2.7

1 Fixed parts (attachment fittings, clamps, hardware, electrical circuitry, mechanical actuator) 6.6

Total weight : 72.7 approx. 66.7 approx.

(2) Floats

The shape of the symmetrical L/H and R/H floats is an open ended cylinder with the following dimensions:

Diameter (front).................... D = 650 mm Diameter (rear)..................... D = 800 mm Length .................................. L = 4 250 mm Nominal volume ................... V = 1 615 dm3 approx.

(3) Gas cylinder (refer to CMM 25-69-11 for additional information concerning the cylinder assembly)

type : composite construction pressure cylinder conforming to DOT specifications. capacity : APPL.A : 9.01 dm3

APPL.B : 9.42 dm3

gas used : helium




25-69-14 REV 11 PAGE 4

2. Description

A. The complete removable part (EFS) includes the following subassemblies. It may be removed when the mission assigned to the helicopter does not require flight over water.

(1) L/H float assembly (see Figure 2)

The L/H float assembly mainly includes an equipped float (fully packed in a textile cover assembly and attached to a manifold bar), five float supply hoses, a L/H supply hose connected to the gas cylinder banjo and two manifold bar fittings (with quick release pins onto front and rear brackets).

This assembly is mounted on the helicopter skid by means of the brackets fixed at the ends of the manifold bar. It includes the following components:

(a) A L/H inflatable (1) made of polyamide fabric both side coated with polyurethane. It is cylindrical in shape, with a restricted diameter at the front place.

It is closed at rear end by flat end piece (globe shaped when inflated) and at front end by spherical end piece. The float is divided into five sealed chambers of equal volume, separated by means of four bulkheads made of the same fabric.

1 girt (2), 2 fastening tabs (3) and 2 bar locating tabs (4) made of polyamide-backed tape and fabric coated each side with polyurethane, are fixed to the float. The purpose of these patches is to transmit all the forces produced upon impact during ditching to the skid of the helicopter via the manifold bar (5). 16 eyelets (6) allow to fit the float with the cover assembly.

Various reinforcement patches made of wear resisting film bonded along the float, are designed to protect the inflatable structure in areas subjected to fretting.

Two tensioning straps (7) correctly position the inflated float against the helicopter skid.

The buoyancy chambers of the float are each equipped with: One supply coupling (8) equipped with a non-return valve, connected to the inflation system by

means of a float supply hose assembly (9). One manual inflating/deflating valve (10) designed to inflate or deflate the float externally from

a source of de-oiled compressed air. Five pressure relief valves (11) are used to limit the internal gage pressure in the rear fifth

chamber to 359



25-69-14 REV 11 PAGE 5

(b) A cover assembly (12) made of polyester fabric coated with PVC and internal overlapped with reinforcement polycarbonate foil is equipped peripherically with snaps. It allows the path of fitting rear bracket and of the supply outlet of the manifold bar. When the EFS is not in use, the cover assembly holds the folded float against the manifold bar. Its length matches that of the folded float. It is longitudinally closed with snaps and VELCRO strips. Its ends are inwardly equipped with protection foam plates.

(c) L/H manifold metallic bar (5)

It is equipped with: Two attachment parts to the skid, as:

One to the front attachment fitting by a male rod end (13), One to the rear attachment fitting by attachment lugs (14).

A general supply outlet coupling (15). Five supply couplings (16) connected to the five float chambers. 17 attachment parts to the container, as:

16 welded threaded inserts (17), 1 tapped thread in rear attachment fitting (18).

Sealed end fitting (19) screwed in place. All of these parts are designed to ensure the manifold filling and to connect main supply hose assembly from gas cylinder and also to connect the five float hose assemblies supplying the five float chambers.

In addition to these functions, the manifold bar is mainly used to support the float and transmit all the loads on the float during ditching to the skid.

(d) One main supply hose.

(e) One bag of hardware (N2).




25-69-14 REV 11 PAGE 6

Figure 2 L/H float assembly

FWD




25-69-14 REV 11 PAGE 7

(f) Gas Cylinder assembly (see Figure 3)

It includes:

(2) Cylinder (1)

This lightweight cylinder, because of its design and construction, requires strict adherence to the safety instructions relative to handling, shipping and storage.

The cylinder assembly is provided with the following labels: - A cylinder type approval label. - An adhesive label showing the charge data. - An adhesive pressure reading label. Note the same label must be fixed on special helicopter

place. - A fourth label is cemented to the body and shows the group references: it is installed only for the

Appl.B.

(3) Inflation valve assembly (2)

The inflation valve assembly is screwed onto the cylinder (1) and designed to make the cylinder fully gas-tight when not in use and also to enable total and immediate discharge of the gas contained in the cylinder to the inflation system when actuated.

The inflation valve assembly comprises a body which accommodates accessories, each having a specific function a described below: Pressure gauge (3), to show the gas charge. Others specific and safety components as charging valve, burst disc, electrical fuse disc, etc.(refer

to the CMM 25-69-11 for additional information). Interface components as :

Outlet fitting (4) used to discharge the gas to the inflation device. Electrical connector connecting the electrical fuse disc. Manual control (5).

Figure 3 Gas cylinder assembly

5 2 3 4

1




25-69-14 REV 11 PAGE 8

(4) R/H float assembly

The R/H float assembly is symmetrical versus the L/H float assembly, as described above. All the inflation system components are strictly identical.

B. The complete fixed part (EFS) includes the following assemblies.

(1) Manifold bar fittings (see Figure 4)

These interface parts used for attaching the containers to the helicopter skid comprise: - Two forward attachment fittings (1), (2) including:

Bushing (3) used as a hinge for the manifold bar front. Snap fastener housing (4). Two attaching bolts (5) fitted through the bar.

- Two aft attachment fittings (6), (7) including:

Hinge pin (8). Attachment bolt (9) fitted through the bar.

(2) System for holding the containers raised at the rear (in view with the helicopter taxiing use) (see Figure 4)

Two clamps (10) are mounted at the top on the skid cross-tube. They include a hook into which a cable (13) mounted on the containers is inserted to lift them.

A set of spring loaded turn lock fastener pins is used for unfastening the manifold bar from the skid (see Figure 2- item 20).

NOTE : THIS SYSTEM IS NOT COMPATIBLE WITH DART STEP

(3) Two footsteps blocks (see Figure 4- item 11).

They serve also to fill in the empty space between the footstep and the helicopter skid tube on which it is mounted.

(4) Two gas cylinder stops (see Figure 4- item 12).

(5) One bag of hardware (N3).

(6) One electrical circuit assembly (see IPL- Figure 2).

(7) One mechanical actuator assembly (see IPL- Figure 3).




25-69-14 REV 11 PAGE 9

Figure 4 Mechanical fixed part of the EFS

Aft bracket Fwd bracket

Skid

10

13




25-69-14 REV 11 PAGE 10

Figure 5 Mechanical Actuator Assembly

Infla

tion

valv

e

Rel

ease

cab

le

Gas

cyl

inde

r




25-69-14 REV 11 PAGE 201

CHARGING/DISCHARGING

1. Charging

CAUTION : THE CHARGING PROCEDURES MUST BE CARRIED OUT IN SUITABLE CHARGING STATIONS BY PERSONNEL SPECIALLY TRAINED FOR THIS KIND OF EQUIPMENT.

WARNING

Have the gas cylinder charged in a suitable charging station.

2. Discharging

Whereas the gas cylinder weight adjustment calls for the use of the special tooling to discharge gas at a slow rate, complete discharge can be readily carried out the gas cylinder assembly alone using the charging valve of the inflation valve.

Secure the gas cylinder in a rigid fixture which does not subject the gas cylinder to any harmful strain (clamping the gas cylinder directly in a vise is forbidden)

Slightly loosen charging valve nut at the beginning of the operation and then gradually unscrew it until the gas cylinder is fully discharged.

CAUTION : DO NOT CONFUSE THE CHARGING VALVE NUT WITH THE WIDE NUT SAFETY-LOCKED BY A LENGTH OF LOCKWIRE AND USED TO SECURE THE CHARGING VALVE TO THE INFLATION VALVE BODY.

WARNING

OPEN

CLOSE

Wrench (Typ.)

Cap

Inflation valve

Body (charging valve)

Charging valve nut

Charging valve nut




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25-69-14 REV 11 PAGE 301

DISASSEMBLY

1. EFS removal conditions

If no flight over maritime or flooded regions is planned in the near future, all the assemblies supplied by AERAZUR and included in the removable equipment of the EFS fitted to the helicopter can be removed and stored.

2. Removal of equipment from helicopter

To remove the EFS from the helicopter, carry out the procedure described AMM.

However, proceed as follows for the specific removal of subassemblies from the helicopter:

A. Removal of the inflation cylinder assembly, electrical cable, and manual control cable.

Check in cockpit that the EFS control system is inoperative (refer to AMM). Remove the mechanical actuator cable from the actuator system on the inflation valve by raising the

cover of the actuator system after removing the fastening pin.

Remove the electrical cable from the inflation valve. B. Remove L/H and/ or R/H supply hoses which are connected on the cylinders banjos outlets..

CAUTION : DO NOT LOOSEN ANY ASSEMBLIES SAFETIED BY LOCKWIRES.

Except in approved workshops, it is strictly prohibited to remove any parts from the inflation valve assembly (with the exception of the main hose banjo from the inflation valve outlet), especially when the cylinder assembly is charged.

WARNING

C. Mount the mechanical actuator cable end and the electrical connector on the supports (blanking plug and bracket) provided for this purpose on the helicopter structure.

D. Remove the cylinder from its supports (two clamps), as instructed in the AMM.

CAUTION : BEFORE REMOVING THE CYLINDER ASSEMBLY, CHECK FOR THE PRESENCE OF THE LOWER SAFETY PIN/ STREAMER ON THE INFLATION VALVE.




25-69-14 REV 11 PAGE 302

E. Handling of removed cylinder

After removal of the cylinder assembly from the helicopter, cover it with a thick sheath or covering sheet made of plastic (or any other non-abrasive material) to prevent scratching and damage to the outer surface.

As a safety measure, never hand carry a charged cylinder over a long distance, as the cylinder would be extremely hazardous if accidentally dropped. Use either a suitable shock-proof packaging or, preferably, a partitioned carriage with stable rollers to transport the cylinder.

F. Removal of the float assembly

Disengage the float assembly form the front and rear brackets. Liberate the float assembly from the helicopter.

G. Removal of the supply device and others.




25-69-14 REV 11 PAGE 401

CLEANING

1. General Observe all shop safety precautions and practices. As applicable, parts should be dried

using an oil and moisture free compressed air source which is filtered through a 20-micron filter.

Used a neutral or slightly alkaline detergent solution (as TEEPOL or equivalent), diluted to 10%.

2. Washing of the EFS. The washing schedule may be given in the AMM. The EFS must also be washed at the end of the day after low altitude flight over the sea.

3. Washing of the metal parts Cleaning all the metal parts with a detergent solution, Rinse with water and dry. The metal parts shall be slightly greased with NATO G354 grease. When used, coat with MASTINOX paste the relevant parts specified in Section

"ASSEMBLY (INCLUDING STORAGE)".

4. Washing of cover assemblies Cleaning the cover assemblies with a detergent solution, Rinse with water and dry.

5. Washing of gas cylinder assembly Wash the outside of gas cylinder and the inflation valve with a detergent solution. Rinse with water and dry. CAUTION : IT IS STRICTLY FORBIDDEN TO REMOVE ANY PART FROM THE INFLATION

VALVE, PARTICULARLY WHEN THE CYLINDER IS CHARGED.

WARNING

Coat with MASTINOX the cylinder lockwire after cleaning the cylinder. CAUTION : DO NOT IMMERSE PRESSURE GAUGE IN CLEANING SOLUTION.

USE DRY CLEANING SOLVENTS ONLY IN WELL VENTILATED AREAS.




25-69-14 REV 11 PAGE 402





25-69-14 REV 11 PAGE 501

INSPECTION/ CHECK

1. General

The inspection/ check consist of:

Pre-flight and post-flight inspections. Routine inspection. Standard proof pressure test. Major overhauls.

2. Inspection schedules

Refer to the MSR.

Only the equipment manufacturing date is considered when applying the inspection schedules.

3. Pre/ post flight inspections

A. Pre flight inspection

(1) Checking the bar fittings and the cylinder assembly

Check that the bar fittings and cylinder assembly are correctly fitted to the skid and to the airframe and that all fixing hardware is tightened and locked as specified in the AMM.

Check for correct installation of electrical connectors and cables from the mechanical control on the gas cylinder valves.

(2) Checking the closing flap attachments to container assemblies

Check that all the snap fasteners are correctly closed from closing flaps and end caps. Fold back the flaps with VELCRO after inspection.




25-69-14 REV 11 PAGE 502

(3) Checking the cylinder gas charge

(a) Checking the pressure of the cylinder fitted with pressure gauge

Check pressure gauge reading. The indicator pointer should be in the range maxi/ mini of the pressure versus the ambient temperature as defined in the table of the label affixed near the cylinder on the helicopter and also on the same label cemented on the cylinder body (see Table 501).

If the reading is out of the range indicated in the table 501 (or in the pressure vs temperature label), remove the cylinder from the helicopter and carry out the following operations.

Use either weighing method and/ or digital pressure method

CAUTION : EXERCISE EXTREME CARE WHEN HANDLING CHARGED GAS CYLINDER.

TEMPERATURE C -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70

FAHRENHEIT DEGREE -58 -40 -22 -4 14 32 50 68 86 104 122 140 158

PRESSURE, MAXI, BARS 245 256 266 277 287 298 309 321 332 344 356 367 379

MAX PRESSURE, PSI 3553 3713 3858 4018 4163 4322 4482 4656 4815 4989 5163 5323 5497

PRESSURE, MINI, BARS 228 238 248 258 268 279 290 301 312 324 335 347 359

MINI PRESSURE, PSI 3307 3452 3597 3742 3887 4047 4206 4366 4525 4699 4859 5033 5207

APPL. A 200877-1: Table 501a - Gas cylinder pressure vs ambient temperature (pressure gauge reading)

TEMPERATURE C -45 -40 -30 -20 -10 0 10 20 30 40 50 60 70

FAHRENHEIT DEGREE -49 -40 -22 -4 14 32 50 68 86 104 122 140 158

PRESSURE, MAXI, BARS 242 247 257 268 278 288 298 308 318 328 339 349 362

MAX PRESSURE, PSI 3501 3582 3728 3887 4032 4177 4322 4467 4612 4757 4917 5062 5250

PRESSURE, MINI, BARS 224 229 239 249 259 269 279 289 299 309 319 329 339

MINI PRESSURE, PSI 3249 3321 3466 3611 3757 3902 4047 4192 4337 4482 4627 4772 4917

APPL. B 200877-2 and upper: Table 501b - Gas cylinder pressure vs ambient temperature (pressure gauge reading)




25-69-14 REV 11 PAGE 503

(b) Weighing the gas cylinder:

Weigh the gas cylinder assembly after removing the protective plastic caps, and the protective sheath on the outlet.

The gas cylinder weight does not include the weight of the transport box, but includes the weights of the pressure reading label cemented onto the cylinder body and the retaining ring from outlet.

The total weight should be in the tolerances (+0 / -4 g) of the service weight (indicated on the charging pressure sensitive label cemented on the cylinder body - see marking "charged cylinder weight" on this label). If the weight is out of the tolerances, carry on the digital pressure checking.

(c) Checking the pressure by digital pressure gauge:

Because the wrapping of the liner can in certain cases cause variation in weight up to 50g, carry out this test with the aide of the special tool AERAZUR P/N 299897 (see Table 501, see Section "SPECIAL TOOLS, FIXTURES AND EQUIPMENT MATERIALS"), reading the pressure via the charging valve of the inflation valve.

The gas cylinder must be stabilized in temperature 4 hours minimum in the test location. Record the temperature of the test location.

Maintain the gas cylinder in a vice fitted with semi cylindrical jaws (with the same curvature as the cylinder) internally lined with rubber pads.

Using a 10 mm open end wrench remove protective cap (1) of the charging valve. Cut the lockwire between the nut (2) and the body of the valve. Connect the digital pressure gauge by its electrical connection to the pressure sensor. Screw manually the milled nut of the tool to the inflation valve. Set the digital pressure gauge to zero. Whilst holding the body of the valve with a 21 mm wrench, unscrew (at left) the nut (2) with

a 21 mm wrench. Unscrewing the nut lifts the poppet in the valve off its seat and put the inside of the cylinder in communication with the pressure sensor.

After stabilization of the display on the digital pressure gauge, record the pressure and close the valve. The nut must be screwed at a torque of 2 daN.m and lockwired (moderately coat the lockwire with MASTINOX paste).

Unscrew the milled nut of the tool. Verify on the gas cylinder label (or as Table 501) if the pressure taken at a temperature of

the test is in the maxi/ mini range. If yes, put the gas cylinder back in service. Do not forget to record on the log card the pressure/temperature values taken.

NOTE : The pressure sensor must be used within the temperature range of 0 to +60C.

(d) If by weighing and by digital pressure gauge, the measures are not within the tolerance limits, discharge the gas cylinder assembly and return it to a workshop approved by the manufacturer or to the manufacturer for overhaul.




25-69-14 REV 11 PAGE 504

Figure 501 - Digital pressure gauge

Digital pressure gauge

Pressure sensor

Milled nut

Charging valve

Body (charging valve)

CLOSE

OPEN

Wrench (Typ.)

Cap (1)

Fitting valve nut (2)

Inflation valve

2

1




25-69-14 REV 11 PAGE 505

B. Post flight inspection (See Section "SPECIAL TOOLS, FIXTURES AND EQUIPMENT MATERIALS").

(1) Equipment protection against environmental conditions (cold, heat, sun, humidity)

In case of normal landing when the EFS has not been used during the flight, the aircraft should be parked, whenever possible, in a sheltered area in which temperature variations are within the range +5C to +40C. If the aircraft cannot be sheltered (if parked under intensive sunlight or bad weather conditions) the extreme temperature range should not exceed -40C to +70C, and 90% relative humidity.

(2) Possible removal of equipment

If no flights are planned over water in a close future, the equipment can be removed from the aircraft and stored after inspection (refer to the corresponding notice).

(3) Washing the equipment, the cylinders and other metal parts

The equipment and its subassemblies must be washed after low altitude flight over water. Refer to "CLEANING" section.

4. Routine inspection

Routine inspection involves inspections between flights as described in the Pre/ post flight inspections section.

A. General visual inspection

(1) Floats visual inspection

(a) Open the cover flaps of containers by unfastening the VELCRO strips then the snaps. Release (slip them) the end caps.

(b) Unfold and visually inspect the float (assemblies ...). Check the cover and the rubber caps for cuts, tears, punctures and abrasion. Replace the cover if:

The internal polycarbonate sheet is cut or show cut parts or The cover itself is cut or punctured (via tears or abrasion) or The cover cannot assure the correct and complete protection of the float (defective or missing

attachment).

(c) Manually check for the valve opening (float not inflated, through the fabric; check that the valve is not blocked, by pushing the axle).




25-69-14 REV 11 PAGE 506

(d) Lightly inflate the floats: P < 50 hPa through the manual inflating/ deflating valves. Dry them if necessary.

(e) Inspect fabric panels and girts for cuts, tears, punctures, abrasion. Mark with chalk if discrepant and then repair. Refer to "REPAIR" section.

(f) Inspect particularly the seams for unbonding. Check that there are no traces of wear or damage on the seams. Pay particular attention to the delamination (blistering) and seam separation. Inspect the external seams, valve flaps, load patches, girts attachments, etc. as following.

Unbonded areas can be identified by gently following the joint lines with a rounded end of a spatula. Do not use any sharp tool as it may damage the fabric.

If an unbonded zone is detected, it must be repaired as described in "REPAIR" section. If there is no unbonded zone, carry on normal maintenance.

With a moderate level of effort peel back the fabric in the unbonded area until, with this moderate level of effort, the fabric can no longer be peeled back.

NOTE : Should the joint open to the inside of the float during this operation (i.e. the inner tape delaminates) then the float repair is not possible and the float should be scrapped.

Re-bond the peeled back fabric (see Section "REPAIR"). NOTE : Addressing small unbonded areas punctually in this manner will help to keep the float in

an airworthy state and will contribute to the optimum life of the product.

(g) If the cords tying the float and cover to the bar present some abrasion, remove them and change the cords. Refer to ASSEMBLY (INCLUDING STORAGE)"section.

(2) Mechanical parts visual inspection

Inspect mechanical parts (metallic parts as clamps, clevis, pins, bars, tube ends, brackets, mechanical actuator assembly) for scratches, distortion, dents, nicks, corrosion, digs, gouges, bulges, showing bare metal. Any scratches not exceeding 0.1 mm in depth and showing bare metal must be repaired or

touched up. (See Section "REPAIR"). Any dents (rounded deformation): replace the parts. Any nicks, digs, gouges, burrs, not exceeding 0.3 mm in depth and 1 mm in span must be

repaired (see Section "REPAIR"). Any superficial corrosion not exceeding 1 cm, but free from pitting digs or crevices, must be

removed, if the corrosion area is off the machined faces (see Section "REPAIR").




25-69-14 REV 11 PAGE 507

(3) Gas cylinder visual inspection

Please refer to the American Rules: CGA C 6-2 (current revision) "Guidelines for visual inspection and requalification of fiber reinforced high pressure cylinders".

Check/inspect gas cylinder valve and inflation valve assembly for defects (dents, nicks, scratches, wear, and corrosion). None of the damaged components of the inflation valve assembly can be repaired.

If there is some defects, discharge gas cylinder (refer to "CHARGING/DISCHARGING" section) and return it to the manufacturer or to an approved servicing agent for decision or overhaul.

NOTE : In case of discharging, secure the gas cylinder in appropriate fixture/vise which does not subject the cylinder to any harmful strain then discharge gradually using the charging valve (see section CHARGING / DISCHARGING).

B. Testing the float assy (leak test)

Every test must be noted on the corresponding log-card

Carry out a leak test on each float, thermally insulated from the ground and sheltered from the sun and draughts, as described below:

(1) Inflate the float to a pressure of 50 hPa (the acceptable ambient temperature range for the test should be 15 to 25 degrees C.).

NOTE : Only inflate through the manual inflating/ deflating valves.

(2) Check the seal of the supply couplings, pressure relief valves and manual inflating/ deflating valves (soapy water or leak detection fluid).

(3) A leak may be detected on a supply coupling. Additional inflation through this plug (corresponding to operation in service) should suppress this leak.

(4) Continue inflation, up to 240 hPa (operating pressure +20%). After 30 minutes, adjust the pressure to 200 hPa, and note the ambient temperature and barometric pressure.




25-69-14 REV 12 PAGE 508

(5) After three hours, check the pressure drop, which should not exceed 50 hPa, making allowance for variations in barometric pressure and ambient temperature, as follows.

Correct pressure reading : The following data will be used to correct the final pressure reading:

(a) initial barometric pressure (b) initial temperature (c) final barometric pressure (d) final temperature (e) final gauge pressure

Corrected gauge pressure (hPa) : (b) + 273 ( (c) + (e) ) - (a) (d) + 273

with units: (b),(d) in (C) and (a),(c),(e) in (hPa).

Micro leaks are acceptable all the float (mechanical parts and fabric), providing they fall within the accepted pressure drop.

(6) If the leaks exceed accepted tolerances, then the float must be removed from its attaching parts, to find the leak(s) and carry out a repair See "DISASSEMBLY" and "ASSEMBLY (INCLUDING STORAGE)" section.

5. Standard proof pressure test and pressure relief valve test

TESTS MUST BE NOTED ON THE CORRESPONDING LOG-CARD.

These tests must be carried out: either in the user's workshops (it is highly recommended for the staff to be specifically trained by the

manufacturer), or in an approved servicing agent shop (or in the manufacturer workshops). A. Standard proof pressure test

CAUTION : THE FLOAT MUST BE REMOVED FROM THE BAR/ HOSES AND COVERS.

Prior to proof pressure test, visually inspect the floats in accordance with Routine inspection paragraph.

The equipment must be tested as follows:

(1) Place the stripped float without its associated subassemblies in a sheltered room, in the open air and with efficient protection for the safety of the operators in the event of a bursting (or cover the float with a close-meshed net).

(2) Use ear protection.




25-69-14 REV 12 PAGE 509

(3) Plug the pressure relief valves with adhesive tape.

(4) Then, using a source of dry and degreased compressed air, inflate the float through the various manual inflating/ deflating valves simultaneously, until pressure is stabilized at the standard test value of 400 hPa.

(5) Maintain the pressure during 10 minutes.

(6) Drop the pressure at 50 hPa and carefully inspect the float surface, particularly around the assemblies.

NOTE : If major loosenings, slips, lifts, beginning of tear and shape defect such as twist or curve are detected on the seams, floats must imperatively be sent to an AERAZUR approved workshop who decides:

either to repair on the site, or to send the equipment back to the manufacturer for further investigation, or to discard the equipment.

NOTE : In case of minor unbonded seams area, check then repair as specified in the Routine inspection paragraph.

NOTE : After the tests, let the floats relaxed during 12 hours then carry out a leak test.

B. Pressure relief valve test

(1) After proof pressure test, re-inflate the float (all chambers simultaneously) until pressure relief valves open (opening pressure: 360 to 400 hPa). Note the effective opening pressures on the log card.

(2) Using soapy water or leak detection fluid, detect opening start.

(3) Note the opening values.

(4) After valve opening, blow off the soapy water.

(5) Slowly deflate the float.

(6) Note the valve closing values (260 hPa mini).

(7) Using soapy water or leak detection fluid, note the closing.

(8) Blow off the soapy water.

(9) Carefully dry the valve to prevent seal sticking on its flange.

C. Refitting check

Refer to the "ASSEMBLY (INCLUDING STORAGE)" section.

When repacking the floats, moderately dust with talc the fabric and set the supply couplings, pressure relief valves and manual inflating/ deflating valves flat (no wrinkles).




25-69-14 REV 11 PAGE 510

6. Checking the electrical fuse disc

CAUTION : THE CURRENT VALUE SHOULD BE 10 MILLIAMPS OR LESS.

Connect the ohmmeter probe tips to pins B and F, then C and E on the electrical connector plugged into the electrical fuse disc receptacle. Note that the shunt A-D is fitted ensuring the connector to be plug-in during the check list

The measured resistance value during all the tests should be 0.9 to 1.4 ohms.

If the resistance value exceeds these limits, the electrically fuse disc must be replaced. The cylinder must be send to the service center for replacement.

7. Checking the electrical control circuits

Check the electrical circuit according to the instructions of the AMM.

8. Periodic inspection of stored equipment

A. Generally store the equipment in service packaging state according to the "ASSEMBLY (INCLUDING STORAGE)" section.

The packed equipment must be stored in an appropriate store under the following conditions: Temperature range : T = +5C to T = +30C Relative humidity less than RH = 70%. Equipment stored in an aired room, sheltered from sun and protected from rodents. If the equipment is restored from the assembly line, visually inspect it before repacking. If foreign objects are observed (shaving or metal cutting, signs of impact, stain or tear, etc), a Routine maintenance must be carried out.




25-69-14 REV 11 PAGE 511

B. Storage before use

(1) Storage from 0 to 2 years

If storage conditions as defined above are respected, overhauls are not necessary during this period. But, when used for the first time, a Routine inspection must be carried out. For a storage from 0 to 3 months: no Routine inspection, but visually inspect the equipment before first use.

(2) Storage after 2 years

The equipment is considered as being in use and must therefore undergo the inspection schedules as defined in the MSR. If the storage conditions are respected, apply the Normal Climatic Conditions inspection schedules.

C. Storage after first use

Before storage, perform a visual inspection. The equipment is considered as remaining in use and inspection schedules must be respected.

NOTE : On each intervention, apply talc on the floats. Only the equipment manufacturing date is considered when applying inspection schedules. When removing an equipment from storage, the inspection schedules are quoted from the equipment manufacturing date and not from the date of removal from storage.

CAUTION : DO NOT REMOVE THE PLASTIC PROTECTIVE SHEATH FROM THE OUTLET OF THE CYLINDER INFLATION VALVE UNTIL THE GAS CYLINDER ASSEMBLY IS INSTALLED ON HELICOPTER AND THE HOSES ARE CONNECTED

9. Major overhauls

A. Floats overhaul

They have to be returned to the Manufacturer for any of the following reasons:

(1) In case of ditching.

(2) In case of serious defects found during the Routine inspections: leak tests, movement of seams, worn fabric, major wear or warping on metallic parts, etc.

(3) After 120 months.




25-69-14 REV 11 PAGE 512

B. Cylinder overhaul

They must be returned to the manufacturer for a major overhaul after ditching.

C. Cylinder hydrostatic retest

APPL.A: Overwrapped cylinder in accordance with DOT E8059, E8162 and E8391 specifications. Cylinder must be retested every 3 years.

APPL.B: Overwrapped cylinder in accordance with DOT E10945 specifications. Cylinder must be retested every 5 years.

10. Checking the transport arrangement

When transporting equipment (for instance, for return to the Manufacturer or to an approved servicing agent), some precautions must be applied:

A. If the equipment is packed (folded float in container), check that it is wrapped with bull pack and placed in a crate with appropriate wedging.

B. If the equipment is unpacked, check for:

(1) Float: protected from rough metal parts, dusted with talc and all air removed. Roll the floats tight, wrap them in bull pack (or corrugated cardboard) and pack them.

Never place the packed floats close to metal parts with sharp edges.

(2) Metal parts:

Carefully packed. Openings blanked with plastic plugs.

(3) Cylinders:

Carefully packing the cylinders. Wedging them and blanking the openings with plastic sheaths.

If the cylinders are charged, use IATA packaging (International Air Transport Association) complying with the Regulation on transport of hazardous products.

Do not forget to join the log-cards when returning the equipment (cylinder, floats).




25-69-14 REV 11 PAGE 601

REPAIR

1. General

Every repair must be noted on the corresponding log-card.

Replace parts that are damaged beyond the repair limits.

See Section "SPECIAL TOOLS, FIXTURES AND EQUIPMENT MATERIALS"

2. Repair of floats

A. Type of repair

Depending on the type of defect in the fabric of a damaged float, there are four possible repair procedures.

(1) For tears less than 30 mm long and punctures, the repair may be carried out in a normal workshop, using the repair kit components.

(2) For minor defects (as local abrasion, permanent stain) which not involve the fabric structure integrity (i.e. non-presence of tear or puncture), the repair may be carried out in a normal workshop, using the repair kit components. Repair is a simple overlap patching. Use a round patch on the outer fabric surface only.

(3) For tears more than 30 mm long, the repair should be carried out in an approved service center or by the manufacturer.

(4) Unbonding (refer to the relevant paragraph).

B. Adhesives

(1) Use

Types of repair as above para A.(2) and A.(4) : the AD16 referenced adhesive (as one part adhesive without hardener) must be used.

Types of repair as above para A.(1) and A.(3) : the AD13 referenced adhesive (as two parts adhesive-cement / accelerator hardener) must be used.

(2) Preparation

See the label which is fixed on the container of the adhesive.




25-69-14 REV 11 PAGE 602

C. Bonding procedure (case of tears less than 30 mm)

(1) General

CAUTION : CEMENTING OPERATIONS SHOULD BE CARRIED OUT IN DRY PREMISES AT TEMPERATURE WITHIN A RANGE OF 15C TO 25C AND A RELATIVE HUMIDITY BELOW 60%. THE SOLVENTS AND ADHESIVES USED ARE FLAMMABLE AND TOXIC TO THE EYES, SKIN AND RESPIRATORY SYSTEM. THE EYES AND THE SKIN NEED PROTECTION (GOGGLES, VINYL GLOVES, ETC). AVOID PROLONGED AND REPEATED CONTACTS WITH THESE MATERIALS. WORK IN A VENTILATED ROOM AWAY FROM ANY HEAT SOURCE, SPARKS OR FLAMES. DISCARD UNUSED CEMENT 2 HOURS (POT LIFE) AFTER MIXING.

(2) Storage

The adhesive base and hardener should be stored in a room where the temperature is maintained between, 15C and 30C, maximum. These materials should be used within life limitation which is precised on the label that is fixed on the adhesive delivery container.

(3) Preparing the repair patch

(a) Use repair kit.

(b) Case of punctures: use round patch on the outer float surface only.

Cut patch of appropriate fabric to allow 30 mm overlap beyond puncture edges.

(c) Case of tears less than 30 mm long: use a rectangular patch on the outer float surface only.

Cut patch of appropriate fabric to the same size as the tear plus 30 mm in all directions. Round the patch corners (Ref. figure 601).




25-69-14 REV 11 PAGE 603

Figure 601 - Preparing the repair patch

(4) Preparing the surfaces

(a) Clean the areas to be cemented on the float and the patch as following.

NOTE : Surface preparation is an essential step for good adhesion. Surface should be free of grease, oil, dust, fungus, etc.

(b) If necessary, abundantly rinse the torn area with fresh water, in particular to dissolve any salt. Carefully dry (the area to be repaired must be free of moisture before undertaking the repair work).

(c) If the impregnated fabric of the float body is greasy:

Thoroughly clean the area surrounding the tear by scrubbing with soapy water.

Thoroughly rinse and dry as previously.

Patch of float body fabric

Tear (30 mm maxi)




25-69-14 REV 11 PAGE 604

(d) Prepare the surfaces to be cemented by rubbing them with a clean soft cloth lightly dampened with MEK solvent (see Figure 602).

CAUTION : AVOID SOLVENT ENTERING THE FLOAT THROUGH THE TEAR.

NOTE : Change the solvent and the cloth when they become dirty.

CAUTION : ONCE THE AREAS HAVE BEEN CLEANED, DO NOT TOUCH THEM; ANY FOREIGN MATTER MAY IMPEDE ADHESION. FOR THE SAME REASON, DO NOT LEAVE CLEANED AREAS IN OPEN AIR FOR MORE THAN A FEW MINUTES.

Figure 602 - Cleaning

Clean the surface of the repair patch to be cemented

Tear in float body fabric

Clean the area surrounding the tear




25-69-14 REV 11 PAGE 605

(5) Adhesive application

CAUTION : DO NOT LET ADHESIVE ENTER THE FLOAT THROUGH THE TEAR.

(a) Spread the adhesive on the surfaces to be cemented using an artist brush. Carry out this operation in the same way as for a brush-coat of paint (see Figure 603).

(b) Let the adhesive become tack-free before applying a second coat (after about 15 minutes).

(c) Let the second coat dry until the required tackiness is obtained (adhesive has dry appearance but is still tacky).

NOTE : Independently of the puncture repair and in the case of tear repair the two coats of adhesive on the float should be smooth and even and extend by 10 mm the patch edges (see Figure 604).

CAUTION : AVOID AIR DRAFTS WHICH CAUSE THE ATMOSPHERIC MOISTURE TO CONDENSE ON THE ADHESIVE-COATED AREA (AS A RESULT OF THE ACCELERATED EVAPORATION OF THE SOLVENTS).

Figure 603 - Adhesive application

Adhesive coat on repair patch

Float body fabric

Adhesive-coated area around the tear

Brush




25-69-14 REV 11 PAGE 606

Figure 604 - Cementing tolerances

NOTE : Remove the frost or condensation (mat or whitish appearance) by wiping the area with a cloth lightly moistened with MEK solvent.

CAUTION : DO NOT WAIT MORE THAN ONE HOUR BETWEEN ADHESIVE APPLICATION AND ASSEMBLY OF THE SURFACES. APPLY A THIRD COAT TO SURFACES IF TIME IS EXCEEDED.

(6) Patching

(a) Assemble the adhesive-coated parts when the tackiness is as required (see para. 5. (c)).

(b) Gradually put the surfaces in contact with each other applying hand pressure from the center towards the edges of the repair patch, taking care not to entrap air bubbles (see Figure 605).

Repair patch

Adhesive-coated float area extending from the repair patch

Float body fabric




25-69-14 REV 11 PAGE 607

Figure 605 Patching

(c) Drive out air bubbles and smooth out any folds by pressing with a spatula from the center outwards and firmly press down for correct adhesion of both surfaces (see Figure 606).

Figure 606 - Patching (cont'd)

NOTE : Pressing is essential for correct adhesion.

Adhesive-coated area

Float body fabric

Adhesive-coated area centerline

Repair patch

Spatula

Float body fabric

Patch




25-69-14 REV 11 PAGE 608

(d) Once air bubbles are removed, evenly roll down the cemented area using a hand roller (see Figure 607).

Figure 607 - Patching (cont'd)

NOTE : If the adhesive film has dried beyond the required tackiness, the cemented surfaces can be reactivated before assembly by wiping the adhesive surface with a clean cloth lightly dampened with MEK solvent (see Figure 602).

(e) Lightly dust the repaired areas with talc (see Figure 608). Moderately inflate the float to separate the float fabric. The float should be kept slightly inflated just at desired shape.

(f) Let the adhesive cure for at least 24 hours at ambient temperature without applying any stress (such as folding or inflation to the service pressure).

(g) Carry out a proof pressure test (see Section "INSPECTION/ CHECK").

(h) 12 hours after the proof pressure test, perform a leak test (see Section "INSPECTION/ CHECK").

Roller

Float body fabric

Patch




25-69-14 REV 11 PAGE 609

Figure 608 - Final step

D. Case of unbonding (repairing seams)

Perform the delamination repairs to floats in accordance with the following instructions:

After identification and fault localization of unbonded area (see Section "INSPECTION/ CHECK"), re-bond the peeled back fabric with AD16 adhesive in accordance with the bonding instructions in the above paragraph 2.C.

CAUTION : WHEN WASHING FLOAT FABRIC, DO NOT ALLOW EXCESS SOLVENT TO COLLECT AT EDGES OF SEAMS. DO NOT APPLY SOLVENT TO DECALS OR STENCIL MARKINGS (WHENEVER POSSIBLE) AS SOLVENT WILL DISSOLVE STENCIL MARKINGS AND DECALS. TAKE CARE TO ALLOW SUFFICIENT TIME FOR EVAPORATION OF SOLVENTS AND DRYING OF ADHESIVE.

Talc

Float body fabric

Repair patch Adhesive-coated area exposed around the patch




25-69-14 REV 11 PAGE 610

3. Repair of mechanical parts (see Section "SPECIAL TOOLS, FIXTURES AND EQUIPMENT MATERIALS").

A. Repairing criteria (as defects showing the bare metal)

Refer to the limits which are precised in section "INSPECTION/ CHECK".

NOTE : Outside these limits, change the damaged component.

B. Reworking the defects

Scrape and smooth the defects with abrasive paper or emery cloth No 400 and 600.

Clean the reworked surfaces with dry cleaning solvent (see Section "SPECIAL TOOLS, FIXTURES AND EQUIPMENT MATERIALS").

C. Post protection after reworking (see Section "SPECIAL TOOLS, FIXTURES AND EQUIPMENT MATERIALS").

(1) Case of aluminum parts:

Coat with ALODINE 1200 using a brush.

Paint with primer coating, Epoxy following MIL P23377

Paint with coating Polyurethane following MIL PRF 85285

(2) Case of steel parts:

Coat with DALIC brush plating using dabber.

Paint with the same set of paints as specified on the above paragraph.

(3) In final coat the repair with a fine coating of AEROSHELL grease N7 (NATO G.354).

D. Other small metal parts

Only coat the limited scratches with anticorrosive AEROSHELL compound 02 (NATO C.614).




25-69-14 REV 11 PAGE 701

ASSEMBLY (INCLUDING STORAGE)

1. Installation of the EFS on the helicopter

Installation of the fixed parts and removable parts (see section DESCRIPTION AND OPERATION) listed hereafter is to be carried out referring where required to the instructions given in the helicopter manual:

Attachment clamps (see section DESCRIPTION AND OPERATION). Main supply hose assembly (see section DESCRIPTION AND OPERATION). Cylinder assemblies, capacity = 9.01 dm3 or 9.42 dm3 (see section DESCRIPTION AND

OPERATION).

Installation of the electrical and mechanical actuator circuits in the fixed part and connection to the cylinder assembly inflation valve (using SOCAPEX connectors) must be carried out following all the instructions given in the helicopter manual.

The other fixed and removable parts of the EFS include the attachment fittings mounted on the helicopter landing skids and the LH and RH container assemblies.

They are installed as follows:

REMARK:

As the same procedures are applied for installation of the LH and RH assemblies only the procedure for the LH side is described below (item numbers refer to Figure 1 of the section ILLUSTRATED PARTS LIST).

NOTE : The LH and RH main supply hoses assemblies are not identical. The assembly including the elbow union must mandatorily be installed on the RH side of the helicopter.

A. Installation of attachment fittings on helicopter landing skids (see IPL- Figure 1)

(1) Position forward LH attachment fitting assembly (210) on the front part of the skids, placing the offset clevis of the attachment fitting on the side opposite the helicopter centerline. Align the attaching holes and install the two shoulder bolts (280) held in place by the two washers (330) and two nuts (310) tightened to a torque of 7.9 0.6 daN.m and lock with LOCTITE 243 thread locking compound.

(2) Position aft LH attachment fitting assembly (230) under the same conditions on the helicopter skid and attach it with bolt (290) fitted with its washer (300) and tightened by nut (310) to a torque of 7.9 0.6 daN.m.




25-69-14 REV 11 PAGE 702

B. Installation of LH container assembly on helicopter landing gear (see IPL- Figure 1)

(1) Position the tab on the forward bracket of the container assembly manifold in the slot in forward attachment fitting (210). The container must be slightly tilted forward and its axis must be in a vertical plane which is roughly parallel to the helicopter landing gear skid.

(2) Insert the tab in the slot after checking that ball joint (710) included in the tab of the manifold is correctly positioned.

(3) Insert bolt (540) through the hole in the attachment fitting. The parts must be lightly coated with grease (see note at the end of this paragraph).

(4) Install nut (550) and tighten it to a torque of 1 to 1.5 daN.m to allow insertion of cotter pin (560).

(5) Then pivot the container around the forward attachment piece so that the aft attachment piece fits into aft attachment fitting (230). To carry out this step, it is necessary to insert the bolt integral with the attachment fitting into the slots in the manifold hook.

(6) Complete the attachment of the container to the helicopter skid by installing one of the two spring pins (660) fitted with its safety pin (640) in the aft attachment fitting.

(7) Then install float retaining strap (520) located aft using the second spring pin (660) fitted with its safety pin (640).

(8) Also attach retaining strap (520) located forward as above, using a spring pin (660) fitted with a safety pin (640). A female snap is provided on the strap near the end loop. This female snap must be assembled with the male snap located on the top and in the center of forward attachment fitting (210). Carry out this step.

NOTE : Prior to installation, lightly coat all mechanical parts to be assembled (except those to which LOCTITE thread locking compound is to be applied) with AEROSHELL GREASE N7 (NATO code G.354).

C. Installation of cylinder assembly in the helicopter fuselage (see IPL- Figure 1)

(1) Under the helicopter floor, in the section reserved for the inflation cylinder, position stop (270) with its rubber pad facing forward. Align the holes in the plate with the holes provided in the helicopter floor and attach with bolts (320), washers (330) and self-locking nuts (340), tightening to a torque of 1.2 0.2 daN.m.

CAUTION : THE HEADS OF BOLTS (320) MUST BE PLACED IN THE BAGGAGE HOLD LOCATED ABOVE THE FLOOR.

(2) Fit the two clamps (80) under the two metal support plates (parts of the helicopter structure, located under the floor), placing the end of the clamp equipped with locking screw underneath to facilitate tightening after installation of a cylinder.




25-69-14 REV 11 PAGE 703

(3) Position cylinder (180) equipped with its two seals (140) and valve outlet banjo fitting (60), held in place by retaining ring (190).

CAUTION : THE BANJO FITTINGS MUST ALWAYS BE INSTALLED SO THAT THE OUTLET IS FACING FORWARD ON THE HELICOPTER AND THE OFFSET IS FACING OUTWARDS (OPPOSITE FROM THE PRESSURE GAUGE).

(4) Apply the cylinder bottom against the stop and position the axis of the pressure gauge (located on the opposite side from the helicopter centerline) so that it is facing downward with respect to horizontal as follows:

= 35 for the LH side of the helicopter ( = 0 for the RH side of the helicopter)

(5) Close clamps (80) and position them with the attachment on the helicopter longeron side. Fasten the clamps with their screws, tightening to a torque of 2 0.2 daN.m and lock with lock wire.

D. Installation of main supply hose assembly on the helicopter (see IPL- Figure 1)

NOTE : The procedure of installation is identical on the RH an LH sides.

(1) Unscrew cap (690) located at the end of the supply fitting of manifold (460) included in the container and insert on the end the banjo fitting of main supply hose (50) equipped with O- ring (150). Then screw cap (690) on the end piece, first coating the threads of these parts with LOCTITE 243 thread locking compound. Cap (690) must be tightened to a torque of 2 daN.m.

(2) Mount the coupling at the other end of the main supply hose assembly of cylinder valve outlet banjo fitting (60), passing the hose above the forward helicopter landing gear strut. Tighten the coupling to 3 daN.m and lock the two parts together with lock wire.

CAUTION : BE CARREFUL DURING INSTALLATION NOT TO TWIST THE HOSE ASSEMBLY.

(3) Position hose assembly (50) along the front of the strut and attach it with two clamp assemblies (90 and 100) fitted with attaching parts (110, 120 and 130). Tighten nut (130) to a torque of 1.2 0.2 daN.m.

The position of the clamps on the landing gear strut differs for a helicopter equipped with a LOW landing gear from that with a HIGH landing gear (Ref. Fig. 701).

In the first case, the first clamp assembly must be located at = 707mm and the second 270mm from the first along the landing strut.

In the second case, the first clamp assembly must be located at = 750mm and the second 350mm from the first along the landing gear strut.




25-69-14 REV 11 PAGE 704

Figure 701 Location of main supply hose attaching clamp

E. Installation of electrical circuit blanking plugs (see IPL- Figure 2)

Blanking plug (410) designed for connector (210) when the cylinder assemblies are removed, are mounted on the outer surface of the beam located at = 398.5mm and their axis is located under the baggage hold floor at distance D = 45mm. The axis of the plugs, the base of which is inclined 45 with respect to vertical, is located towards the aft section at a distance L = 160mm from frame X = 2700mm. The square base of the blanking plug is drilled with four 3.5mm diameter holes spaced 18.3mm apart. These holes are for attaching parts (420, 430 and 440).

F. Installation of footstep block (see IPL- Figure 1)

In order to prevent the float fabric from catching under the footstep plate during automatic inflation of the float, provision has been made for filling the space with blocks installed on the helicopter at the same time as the fixed parts of the flotation gear.

These blocks (made of wood or isocyanate alkyd) (260) are slipped under the aft part of the footstep base-plate and attached by two screws (350 and 360).

CAUTION : THE TIGHTENING OF THIS SCREW IS ADAPTED TO THE MATERIAL OF WHICH THE BLOCKS ARE MADE.

GROUND




25-69-14 REV 11 PAGE 705

G. Installation of attaching clamps (see IPL- Figure 1)

These clamps are designed to support the raised container assemblies at the rear to allow installation of taxiing fixtures on the helicopter skids. They are mounted on the struts of the aft crosspiece of the helicopter landing gear.

(1) The hooks on clamps (250) must be on the opposite side from the aircraft centerline. These clamps must be installed on the struts at a theoretical height of 561mm with respect the plane under the landing gear skids. The attaching screws of clamps (250) are to be tightened to a torque of 0.6 15.00

+ daN.m.

H. Installation of Mechanical Actuator Assembly (see IPL- Figure 3)

The mechanical actuator assembly is installed under the helicopter cockpit floor. It leads from the cockpit to each of the gas cylinder valves.

The helicopter structure must be fitted out for installation of the mechanical actuator assembly (if the structure has not been fitted out by the air frame manufacturer, AERAZUR can supply drawing 200938 to the user on request. This drawing shows the location and size of the holes to be provided in the helicopter structure.

The mechanical actuator is installed on the helicopter in the following sequence:

(1) Install the four nuts (30) in the four holes provided aft o the control console in the cockpit and tighten them with the suitable SHUR-LOK nut (P/N SLTG36 and SLT850-5M.

(2) Install bracket (20) against the console and attach it with washers (40) and bolts (50).

(3) Install grommet (250) under bracket (20) in the hole provided in the floor of the cockpit. Also install three other grommets (250) in the holes provided in the frames located under the floor.

(4) Remove the cover, held in place by four screws, from housing assembly (80) and attach housing assembly (80) with three screws (90) and three nuts (100) on the structural plate located under the helicopter back of the forward landing gear crosspiece, near the helicopter center line.

(5) Fit the end of sheath (110) fitted with the longest end fitting (with one of the two nuts (130) removed) through the hole in the frame at X = 1790.15 mm of the structure and position it below grommet (250) in the floor. Then push on the sheath so that the end fitting goes through the grommet and fits into the hole in bracket (20). Position the threaded part of the end fitting in medium position in bracket (20) and attach it either with two nuts (130) to be locked with lockwire.

(6) Install cable (200) in handle (60) such that the crimped end fitting is correctly located in the slot in the handle. Then engage the smooth end of cable (200) in the end fitting of sheath (110) and insert the cable until handle (60) fits into the bracket (20). Position the handle to facilitate locating of pin (70) in bracket (20). Then secure handle (60) on bracket (20) with lockwire (320), sealed with lead seal (330).




25-69-14 REV 11 PAGE 706

(7) Install sheath (110) fitted with cable (200) under the floor through the three grommets already housing assembly (80). The short end fitting of the sheath is installed either with an internally self-locking nut (120).

(8) Attach sheath assembly (110) on the helicopter structure with three clamps (260) installed with screws (270) and nuts (280).

(9) Attach the short end fitting of RH sheath (140) equipped with cable (210) and LH sheath (170) equipped with cable (220) in the locations provided in housing assembly (80). These end fittings are each attached with an internally self-locking nut (150 or 180).

(10)Attach the long end fittings of sheaths (140) and (170) to the manual actuator systems located in the cylinder inflation valve assemblies, proceeding as follows:

Remove the pins holding each of the covers on the mechanical actuating systems closed and open the covers.

CAUTION : DURING THIS PROCEDURE, DO NOT REMOVE THE SAFETY PIN FITTED WITH STREAMER, AS THIS SAFETY PIN PREVENTS ROTATION OF THE ACTUATING CAM IN THE ACTUATING SYSTEM.

Fit the end fittings of each of the sheaths with washer (310) and square lock-nut (300) and install the end fittings on the slotted holes located at the end of the actuating system body. Lock in place with the two nuts (160) and (190).

Insert the ball crimped to end of the cable in the recess provided in each of the actuator cams, then close the actuator cover. Hold the cover in place by raising the pin.

(11)Attach sheath assemblies (140) and (170) on the helicopter structure with four clamps (260), attached by screws (270) and nuts (280).

(12)The cables are then installed and adjusted on the lever in housing assembly (80) as follows:

Place the end of the longest lever arm in the internal area of the housing assembly case which is painted white. Hold the lever firmly in this position. Fit the end of cable (200) from the handle into the hole provided at the end of the lever, install cable clamp (230) and tighten the screw(s) on the cable clamp so that the cable is correctly held, without slack or tension.

Repeat this procedure with cables (210) and (220) from the actuator systems in the cylinder valve assemblies, to install them on the lever.

Release the lever, install the cover on the housing assembly and tighten it with the four screws provided, which are locked in place with lockwire.

NOTE : For removal of the cylinder assemblies, the long end fittings of cables (210) and (220) are removed from the actuator systems in the cylinder inflation valve assemblies and installed on support brackets (290) mounted under the electrical support connectors on the helicopter structure (for installation, see 1.H. (10)).




25-69-14 REV 11 PAGE 707

2. Packaging of container assemblies

The RH and LH container assemblies are packaged in the same way, using identical or symmetrical parts. Therefore, only the assembly and folding procedures for packaging of the LH container is described below.

NOTE : Refer to figure 708 for knots used.

A. Manpower:

Although a highly qualified operator can pack the container assemblies alone, it has proven more efficient to use two operators. This is therefore the manpower recommended.

B. Set of necessary tools and materials:

See Section SPECIAL TOOLS, FIXTURE AND EQUIPMENT MATERIALS. Furthermore, it is recommended to provide the following additional, accessories and tools : (1) A work surface with minimum dimensions of:

Width approx. 1 m

Height approx. 0.80 m

Length approx. 3 m

(2) A source of de-oiled , dry, low pressure compressed air (1-7 bars) with a sufficient capacity (0.5 to 1m3 per min. approximately), and filtered (20 microns filter is recommended).

C. Assembly of L/H container assembly (Ref. Fig.702)

To assemble the component parts of the LH container assembly, proceed as follows:

(1) Install 2 o-rings (160) on each of fittings (a, b, c, d and e) welded on filling manifold assembly (100), greasing them moderately (see note at end of paragraph).

(2) On each on the above fittings, install the banjo fitting on one end of the 5 hose assemblies (170) and secure it with stop screw (150) coated with LOCTITE 243 thread locking compound. This screw is to be tightened to a torque of 0.8 daN.m.

(3) Install float (70) deflated and unfolded on the work surface, placing the main flap on the top.

(4) Insert the front end (fitted with a ball joint) of manifold assembly (100) at the rear of float (70) and under the main flap (Ref. Fig.703-1)

(5) Install 2 o-rings (160) on each of supply couplings (f, g, h, k and l) located in float (70), applying a light coat of grease.




25-69-14 REV 11 PAGE 708

(6) Insert the banjo fitting on the order end of supply hose (170) on each of the above couplings and secure it with stop screw (90) coated with LOCTITE 243 thread locking compound. It should be tightened to a torque of 0.8 daN.m (Ref. Fig.703-2).

(7) Position manifold (100) with respect to the float flap so that the following parts protrude from the flap through the opening provided for this purpose:

Main supply coupling (m) welded to manifold (Ref. Fig.703-3), Hooking lugs (n) welded to manifold (Ref. Fig.703-4), The 16 locating lugs (p) also used for attaching the closing flap.

(8) Attach the manifold in its position (Ref. Fig.703-5 and 6) with respect to the float by tying the 2 locating tabs (9) glued to the float with cords (180) 600mm long (two turns of cord, two HH knot followed by a L knot secured by an O knot).

(9) Then install the following assemblies on the outside (grey side of the float cover (200), on the third hole from the rear, equipped with an eyelet (Ref. Fig.703-7).

Yoke (350) in which cable assembly (340) is inserted in the middle and which is attached on the cover by bolt (360), washer (370) and nut (380). The nut is installed with LOCTITE 243 thread locking compound and tightened to a torque of 0.25 daN.m.

then install cable assembly (340) equipped on the ends with two spring pins (330) secured by the rings, two flexible cables (320) and two safety pins (310).

(10)When installation of this assembly is completed, position float cover (200) on the float equipped with its manifold. Fit the supply coupling welded to the manifold through the hole provided in the cover. Also fit the lugs of the aft attachment piece welded to the manifold through the cover and position the cover so that the 16 lugs welded to manifold (100) are aligned with the holes in the middle of the cover. Then temporarily secure the cover to the manifold at the front and back, by means of two screws (220) and two washers (240). Place in the next to last holes. These screws must be coated with LOCTITE 243 thread locking compound and tightened to a torque of 0.25 daN.m.




25-69-14 REV 11 PAGE 709

Figure 702 LH container assembly




25-69-14 REV 11 PAGE 710

(11)Finish attaching the cover to the manifold included i the float proceeding as follows:

(a) Align the loop on the ends of a cable (340) with the 4th (middle of aft manifold attachment fitting) and 5th holes from the rear of the cover and attach the cable and cover by means of two screws (230) equipped with two washers (240) in the two holes. These screws are first coated with LOCTITE 243 thread locking compound and are tightened to a torque of 0.25 daN.m.

(b) The 6th to the 16th holes from the rear of the cover are secured with screws (220) equipped with washers (240). The screw thread are first coated with LOCTITE 243 thread locking compound and are tightened to a torque of 0.25 daN.m.

(c) The first hole located at the aft end of the cover is used to secure the cover and the aft LH cap assembly (290) on which the fastening tab must be inserted between the manifold and the cover. The assembly is attached by a screw (230) fitted with a washer (240). The screw threads are covered with LOCTITE 243 thread locking compound and tightened to a torque of 0.25 daN.m.

(d) The last hole at the forward end of the cover is used to secure cover (200), forward LH cap (270) (first inserted on manifold (100)) on which the fastening tab must be inserted between the bar and cover and one of the end loops of flexible cable assembly is also fastened with a screw (230). The screw is coated with LOCTITE 243 thread locking compound and tightened to a torque of 0.25 daN.m (Ref. Fig.703-8).

(e) At the other end of above flexible cable assembly (320) must be installed spring pin (330), flexible cable assembly (320) and safety pin (310). The ring on the spring pin is used to connect the two flexible cable assemblies.

(12)Overturn the fully secured float/ manifold/ cover assembly on the work surface to gain access to the manual inflation/ deflation couplings. Then supply each of the 5 manual coupling with compressed air, see para.2-A(2)), inflate the float to a pressure of about 50 hPa.




25-69-14 REV 11 PAGE 711

Figure 703 Assembly of LH container assembly

1 2 3

4

5

6

7

8

910




25-69-14 REV 11 PAGE 712

(13)Attach two tie straps (190) to the fastening tab provided on the float, one at the location of the aft manifold attachment fitting (r) and the other at the location of the forward manifold attachment fitting (s), proceeding as follows (Ref. Fig.703-9 and 10) :

(a) At the forward end, position the loop end of tie strap (190) 60mm below the loop of the tap mounted on the float, directing the other end of the strap toward the manifold. The strap must be positioned so that the active part of snaps are directed toward the float. Next, tie the two turns of cord (180) fastened by two HH knots followed by an L knot secured by an O knot.

(b) Repeat the above procedure for the aft attachment fitting, except with a distance between loops of 100mm.The assembly is also secured with cord (180).

(14)After carrying out this procedure, the float can be folded and the cover closed continuing as described below.

NOTE : Prior to assembly, lightly coat all metal parts and the o-rings to be installed (except those to which LOCTITE is to be applied) with AEROSHELL GREASE N7 (NATO code G.354) or DOW CORNING 33 MEDIUM.

D. Folding of the float and closing of the container

To complete preparation of the container assembly, proceed as follows:

(1) Place the fully equipped assembly on the work surface, placing in contact with it the cover laid out flat, with the manifold and float located on the top (Ref. Fig.704-1).

(2) Open the manual inflation /deflation valves of three center compartments of the float by pressing with the thumb on the central plunger of each coupling and turning a quarter turn (Ref. Fig.704-2).

(3) Inflate the two end compartments of the float with compressed air to a pressure of 60 hPa gauge. Then, after pressurising, close the inflation valve of the a

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