CAGE Code: F6101
EMERGENCY FLOTATION SYSTEM
P/N : 200553-0
COMPONENT MAINTENANCE MANUAL
WITH
T - 2
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RECORD OF REVISIONS
MANAGEMENT OF REVISIONS:
• Revision number and validity: Revision 01
Ö
Initial project distribution
Revision 02 to 09
Ö
Project updating
Revision
10
Ö
First distribution of manual
Revision
11
Ö
First revision of manual
Revision
99
Ö
89
threvision 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 manager’s
initials.
REVISION
NUMBER
REVISION
DATE
CHECKED
BY
DESCRIPTION
OF REVISION
INSERTIO
N
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
RR - 2
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SERVICE BULLETIN RECORD
SBR - 2
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LIST OF EFFECTIVE PAGES
SECTION PAGE
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No
SECTION PAGE
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No
TITLE T-1
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Inspection/Check 501 REV
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T-2
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502 REV
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503 REV
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Record of Revisions
RR-1
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504 REV
11
RR-2
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505 REV
11
506 REV
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Service Bulletin Record
SBR -1 REV 11
507 REV 11
SBR -2 REV 11
508
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509
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List of Effective Pages
LEP-1
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510 REV
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LEP-2 REV 11
511 REV 11
512 REV
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Table of Contents
TC-1 REV 11
TC-2 REV 11 Repair
601 REV 11
602 REV
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Glossary of Abbreviations
GA-1 REV 11
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GA-2 REV 11
604 REV 11
605 REV
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Table of Vendor Codes
TVC-1 REV 11
606 REV 11
TVC-2 REV 11
607 REV 11
608 REV
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Description and
1 REV 11
609 REV 11
Operation
2 REV 11
610 REV 11
3 REV
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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
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Charging/Discharging
201 REV 11
709 REV 11
202 REV 11
710 REV 11
711 REV
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Disassembly
301 REV 11
712 REV 11
302 REV 11
713 REV 11
714 REV
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Cleaning
401 REV 11
715 REV 11
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CHAPTER PAGE
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CHAPTER PAGE
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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
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Fits and clearances
801 REV 11
1033 REV 10
802 REV 11
1034 REV 10
Special tools, fixtures
901 REV 11 Alphanumeric Index
1035 REV 10
and equipment materials
902 REV 11
1036 REV 10
903 REV 11
1037 REV 10
904 REV 11
1038 REV 10
1039
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Illustrated Parts List
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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
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Detailed Parts list
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1008
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1009
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1010
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1011
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1024
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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
TC - 2
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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 d’Entretien Équipement
• 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
GA - 2
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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
TVC - 2
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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 (N°2) 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.
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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
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
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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<P<399 hPa (5.5 PSI).
(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.
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Figure 2 – L/H float assembly
FWD
(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). 5 2 3 4 1
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(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 (N°3).
(6) One electrical circuit assembly (see IPL- Figure 2).
(7) One mechanical actuator assembly (see IPL- Figure 3).
Aft bracket Fwd bracket
Skid
10 13
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Figure 5 – Mechanical Actuator Assembly
In fla tion v a lv e R ele as e c ab le Ga s c y lin de r
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
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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
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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.
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.
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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.
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(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)
(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 +60°C.
(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.
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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
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 +5°C to +40°C. If the aircraft cannot be sheltered (if parked under intensive sunlight or bad weather conditions) the extreme temperature range should not exceed -40°C to +70°C, 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
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(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 cm², but free from pitting digs or crevices, must be removed, if the corrosion area is off the machined faces (see Section "REPAIR").
(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
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(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.
(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).
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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 = +5°C to T = +30°C
• 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.
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.
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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).
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
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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 15°C TO 25°C 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, 15°C and 30°C, 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).
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
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(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
(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
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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
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
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(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
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 re-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
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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 N°7 (NATO G.354).
D. Other small metal parts
Only coat the limited scratches with anticorrosive AEROSHELL compound 02 (NATO C.614).
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.
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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 N°7 (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.
(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:
α = 35° for the LH side of the helicopter (α = 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 Υ = 707mm and the second 270mm from the first along the landing strut.
• In the second case, the first clamp assembly must be located at Υ = 750mm and the second 350mm from the first along the landing gear strut.
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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 Υ = 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
