SD3-60 AIRCRAFT MAINTENANCE MANUAL 25.pdf25-10-01 Jun 30/01 EFFECTIVITY: All Page 201 z SD3-60...

Jun 30/0125-10-00 EFFECTIVITY: All

zSD3-60 AIRCRAFT MAINTENANCE MANUAL

AMM25-10-00 1.0.0.0FLIGHT COMPARTMENT FURNISHINGS - GENERAL

1. General

In the flight compartment there are two pilots seats and a supernumerary seat, each with its own safety harness. Both pilots seats are adjustable in height and position with retractable arm rests and are fitted either side of the central control console. The flight mechanics seat is positioned behind and to the left of the first pilots seat.

Other flight compartment furnishings include, for each pilot: a stowage recess (for maps, charts, check lists etc), a cup holder, an ashtray, a sun visor, and an air circulation fan.

The flight compartment is thermally and acoustically insulated and is separated from the main cabin by a bulkhead at station 74. The bulkhead comprises a centre panel with a sliding door behind each pilots seat for entry. The doors are sealed against the ingress of smoke from any fire in the main cabin.

Exposed structure and window posts etc. are furnished with composite panels.

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AMM25-10-01 2.0.0.0PILOT'S SEAT - MAINTENANCE PRACTICES

1. Removal/Installation

A. Remove complete harness assembly

(1) Release the buckle and separate the straps.

(2) Unclip the lap straps from the sides of the seat.

(3) Remove the bolts which hold the inertia reel and lock mechanism from below the seat.

(4) Withdraw the shoulder straps through the guide at the top of the seat and remove the reel and lock mechanism, taking care not to kink the cable linking the reel and lock mechanism.

NOTE: For details of the procedure to remove the lock mechanism from the harness refer to vendor's overhaul manual.

B. Install complete harness assembly.

(1) Clip the lap straps to the sides of the seat.

(2) Taking care not to kink the cable linking the reel and lock mechanism, secure the reel and lock to their mountings below the seat and tighten the bolts.

(3) Thread the shoulder straps through the guide at the top of the seat.

(4) Function check the harness (para 2.A.)

2. Adjustment/Test

A. Function check the harness

(1) Examine straps for frayed edges or nicks.

(2) Alter the lengths of the straps by sliding the clasps along the straps. Check that when retensioned the clasps lock at their new positions.

(3) Check that the shoulder straps reel in and out freely and lock when jerked.

(4) Clip together the lap and shoulder straps and check for positive engagement in the buckle by pulling strongly each strap in turn.

(5) Check that the straps release when the buckle release is operated.

(6) Check that the lock mechanism functions correctly.

B. Function check the seat adjustment.

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(1) With the seat in its lowest position check that the plunger is protruding forward through the lowest of its five holes and that the seat is steady.

(2) Depress the button in the handle, raise the seat slightly and release the button. Continue raising the seat and check that the plunger engages in and protrudes through the second hole. Check that the seat is steady.

(3) Repeat (2) with the third, fourth and fifth holes.



AMM25-10-06 3.0.0.0SUPERNUMERARY SEAT - MAINTENANCE PRACTICES

1. Adjustment/Test







(6) Check that the lock mechanism functions correctly.



AMM25-20-00 4.0.0.0PASSENGER COMPARTMENT FURNISHINGS - GENERAL

1. General

Compartment interior is fully furnished to airline passenger standard with composite hardwall trim panels. Floor panels are composite construction with carpet, and rails for cargo restraint or passenger seating are provided.

Other passenger compartment furnishings include Passenger Service Units, overhead lockers and buffet/galley.

Passenger Service Units, located above the seats provide

- Reading lights. Refer to 33-22-00, pb1.- a push/ pull switch - PASSENGER TO ATTENDANT call. Refer to 33-23-00, pb1.- air outlets (gaspers) for individual ventilation. Refer to 21-00-00, pb1.

The left and right P.S.Us are respectively single and double units to facilitate the seating configuration.



AMM25-20-01 5.0.0.0PASSENGER SEATS DESCRIPTION

1. General

A maximum of thirtysix airline standard passenger seats, with safety belts, can be fitted onto the seat rails in the aircraft floor and walls. A row of eleven double seat units (Aircraft Furnishings Ltd 4001-212F) are fixed to seat rails (right) of the aircraft centre and on the right hand cabin wall. A row of eleven single seat units (Aircraft Furnishings Ltd 4001-105F) are fixed to seat rails (left) of the aircraft centre and on the left hand cabin wall. Row twelve is a triple seat unit (Aircraft Furnishings Ltd 4001-105F) are fixed to seat rails (right) and the rear cabin bulkhead.



AMM25-20-01 6.0.0.0PASSENGER SEATS MAINTENANCE PRACTICES

1. Adjustment/Test

A. Function check the safety belt



(3) Clip together the straps and check for positive engagement by tugging.


2. Cleaning/Painting

A. Dry cleaning and flameproofing of seat fabric.

(1) Dry cleaning.

NOTE: Fabrics are originally flameproofed by zirconium treatment and can be dry cleaned 5 to 10 times with no loss of flame retardency.

It is recommended that dry cleaning be carried out by a good commercial dry cleaner, preferably with experience in cleaning flameproofed fabrics.

(2) Flameproofing

Re-treatment for fire retardency to meet FAA vertical burn specifications can be performed by

Kiesling-Hess Finishing Company, Inc.

519 West 38th Street

New York, New York 10018

Telephone (212) 736-4760

The above company's 'flamefoe kh' treatment is recommended (after which fabric will withstand up to 20 dry cleanings with no loss of fire retardency).



AMM25-20-06 7.0.0.0FLIGHT ATTENDANTS SEAT - MAINTENANCE PRACTICES

1. Adjustment/Test









AMM25-20-11 8.0.0.0CARPETS - MAINTENANCE PRACTICES

1. Cleaning

WARNING: ALKALINE DETERGENTS MUST NOT BE USED; THESE HAVE A DELETIVE EFFECT ON FLAMEPROOFING TREATMENT

It is recommended that carpets be cleaned using a neutral shampoo of the crystallising type, to which one teaspoonful of white vinegar is added per pint of shampoo solution.

A. Procedure:

(1) Thoroughly vacuum total area.

(2) Prepare shampoo solution to manufacturer's instructions and whip to a foamy consistency.

(3) Clean total carpet in manageable working areas as follows (starting furthest from intended exit):-

(a) Employing a circular motion, apply a sponge, dipped in shampoo suds to the area.

NOTE: To avoid subsequent shrinkage, avoid over-soaking.

(b) When fully covered, gently remove suds with a clean absorbent cloth.

(4) Allow to dry for several hours.

NOTE: Carpet should not be walked on until thoroughly dry.

(5) Finally brush and vacuum the carpet.



AMM25-20-16 9.0.0.0OVERHEAD LOCKERS - MAINTENANCE PRACTICES

1. Adjustment/Test

A. Function check of latches

(1) Open all lockers and visually check the latches.

(2) Close a locker, checking that the lock mechanism engages without forcing. Apply finger tip pressure to the inside of the locker cover to check that the locking mechanism is engaged. Access via the adjacent open locker.

(3) Repeat para (2) on all other overhead lockers.



AMM25-30-01 10.0.0.0BUFFET/GALLEY - MAINTENANCE PRACTICES

1. Adjustment/Test

A. Function check the latches

(1) Open all galley unit doors and examine the latches.

(2) Close each door and check that its latch positively engages.

(3) Examine the secondary locks (rotating keepers) for security of attachment.



AMM25-61-00 11.0.0.0EMERGENCY LOCATOR TRANSMITTER SYSTEM - DESCRIPTION AND OPERATION

1. General

Refer to Figure 1. The emergency locator transmitter (ELT) system (Type Dorne & Margolin) - comprises the following:-

A. a transmitter located in the rear fuselage roof right side between stations 508 and 535.

B. an antenna mounted on the upper fuselage at station 520.

C. a two-position remote control switch, annotated ON/TEST and AUTO, located on panel 1P at 2nd pilot's position.

D. a TRANSMITTER ON light, on panel 1P, which is supplied from the 28V DC left battery busbar via circuit breaker CB67 on panel 1D.

E. a circuit board located on the rear of panel 1P and the 2nd pilot's position.

NOTE: For aviation use only. Unlicenced operation unlawful. Operation in violation of FCC rules subject to fine or licence revocation.

Operation of system for test purposes may only take place with permission from and under instructions from the FAA/FCC or other applicable authority.

Allrelevant regulations pertaining to operation of the ELT must be adhered to.

2. Description

The system is designed to commence transmission automatically should it be subjected to a crash force of 5 ± 2 g. The system may also be switched on manually either by a remote switch on 1P panel, or by a selecting to ON the AUTO/OFF/ON switch on the transmitter.

NOTE: For remote operation via the remote switch on 1P panel the transmitter AUTO/OFF/ON switch must be left in the AUTO position.

Indication of ELT transmission is by an amber warning light, adjacent to the ON/TEST/ AUTO switch on 1P panel.

The transmitter is powered by its own battery pack. Upon being subjected to a force of 5 ± 2g, an integral inertia switch closes and completes circuitry to enable the system to transmit.

In the event of an emergency and if it is thought advisable, the system may be switched on manually by selecting to ON the ON TEST/AUTO remote switch on 1 P panel. The transmitter unit also has an AUTO/OFF/ON switch, adjacent to the antenna connector, which may be used in lieu of the 1 P panel switch. In both cases an amber warning light adjacent to the remote 1 P switch will light, to provide indication of system transmission.



The remote control switch, on 1 P panel, provides flight deck control of the transmitter. Two positions are available:-

ON/TEST - This position switches on the ELT, providing an inherent test capability, as the transmission may be verified on the aircraft VHF System. Refer to 23-11-00, pb1. This position also resets the system after an automatic transmission and is then immediately returned to AUTO.

AUTO - This position arms the system in readiness for an automatic transmission.

The transmission amber warning light is actuated by a circuit board, Shorts Pt. No. SD3-82-0845 detecting voltage changes in the transmitter. When the system is not transmitting, the board is supplied with 9 volts, which will fall to 0.5 volts on transmission. This voltage difference is 'sensed' by the circuit board when the decreasing voltage falls to approximately 5 volts. At this point the amber warning light will become lit.

3. Operation

A. Remote operation

The transmitter may be operated by selecting the ELT switch on 1P panel to ON/TEST, and switched off again by selecting AUTO.

NOTE: Should the transmitter have operated automatically, with the remote switch at AUTO, it may be reset by selecting ON/TEST then immediately reselecting AUTO.

B. Automatic operation

With the 1P panel ELT switch at AUTO the system will operate automatically if subjecterd to a force of 5 ± 2 g. Simultaneous transmission will occur on 121.5 MHz and 243 MHz. After automatic operation the system may be reset as detailed in the NOTE above.

C. Manual operation at the transmitter

The transmitter may be switched on with the AUTO/OFF/ON switch adjacent to its antenna connector.

NOTE: The system is powered by its own battery pack with the ELT warning light (amber) on 1P panel powered via circuit breaker CB67 on 1D panel.



Emergency Locator Transmitter - Component LocationFigure 1



AMM25-61-00 12.0.0.0EMERGENCY LOCATOR TRANSMITTER SYSTEM - MAINTENANCE PRACTICES

1. Removal/Installation

A. Remove ELT

(1) Set AUTO/OFF/ON switch on ELT to OFF.

(2) Disconnect antenna and remote connector (J1 and J2).

(3) Remove two nuts and bolts securing ELT to support bracket.

(4) Remove ELT.

B. Install ELT

(1) Ensure AUTO/OFF/ON switch is set to OFF.

(2) Position ELT on support bracket with direction of flight arrow facing forward.

(3) Secure ELT with two nuts and bolts.

CAUTION: IF J1 AND J2 ARE CROSS-CONNECTED ELT WILL TRANSMIT A DISTRESS SIGNAL. J1 SHOULD BE CONNECTED TO SOCKET ADJACENT TO ANTENNA, J2 SHOULD BE CONNECTED INTO SOCKET ADJACENT TO ON/OFF/AUTO SWITCH.

(4) Connect antenna and remote connector, (J1 and J2).

(5) Perform operational test (para 2.).

C. Remove ELT antenna

(1) Disconnect antenna lead.

(2) Remove bolts and lockwashers securing antenna.

(3) Remove antenna.

D. Install ELT antenna

(1) Locate antenna in hole in fuselage skin.

(2) Secure antenna with bolts and lockwashers.

(3) Connect antenna lead.




E. Replace battery pack

(1) Set ELT ON/OFF/AUTO switch to OFF.

(2) Disconnect antenna and remote connector (J1 and J2).

(3) Remove ELT securing nuts and bolts.

(4) Invert ELT and remove base plate.

(5) Disconnect battery plug.

(6) Remove battery pack by gripping between the pack and rubber cushion, on each end. Pull battery out, ensuring that rubber cushion remains in place.

(7) Install new battery pack and ensure that label on battery pack is visible when battery is installed.

(8) Connect battery plug.

(9) Secure base plate to ELT.

(10) Secure ELT to structure.

(11) Connect antenna and remote connector to J1 and J2.

(12) Set ON/OFF/AUTO switch to AUTO.


2. Adjustment/Test

A. Introduction

(1) Prior to commencing the tests detailed ensure that the following systems are operational and that the appropriate circuit breakers are closed:-

(a) VHF system. Refer to 23-11-00, pb1.

(b) Audio integrating system. Refer to 23-51-00, pb1.

(c) Central warning system. Refer to 31-50-00, pb1.

(2) Equipment and materials:-

Civil headset.



B. Preparation

NOTE: Transmissions from the ELT are at the distress frequencies of 121.5 and 243.0 MHz, therefore test should only be performed at the times allocated for such tests by local aviation authorities. For example the FAA/DOT allow such transmissions any time within the five minutes following each hour. The test time allowed is generally three sweeps of the warble tone (approximately 1 second). The control tower is to be informed that a test is about to be performed.

(1) Ensure that all electrical and avionic switches are at a neutral or OFF position.

(2) Connect external power supply. Refer to 12-09-03, pb301.

(3) Set ELECTRICAL MASTER switch to EXTERNAL POWER.

(4) Set AVIONICS MASTER switch to ON.

(5) Ensure that circuit breaker CB67 (1D) is closed.

(6) Tune VHF transceiver to 121.5 MHz. Refer to 23-11-00, pb1.

(7) Connect headset to 1st pilots MIC/TEL socket.

(8) On panel 11P set TEST/BRT/DIM switch to TEST.

(9) Ensure TRANSMITTER ON light on panel 1P is lit.

(10) Set TEST/BRT/DIM switch to BRT and ensure TRANSMITTER ON light is extinguished.

C. Operational test

NOTE: Ensure that all local restrictions have been observed.

Two persons will be required for steps (1) and (3).

(1) Set AUTO/OFF/ON switch on ELT momentarily to ON and check that ELT tone is present in headset and that TRANSMITTER ON light is lit.

(2) Set AUTO/OFF/ON switch on ELT to AUTO.

(3) Set remote ON/TEST and AUTO switch on panel 1P to ON/TEST and check that ELT tone is present in headset and that TRANSMITTER ON light is lit.

(4) Set ON/TEST and AUTO switch to AUTO.

(5) Verify with the control tower, via the VHF system, that the transmissions in (1) and (3) were received by them.

(6) Ensure that the transmissions on 121.5 MHz has cleared.



D. ELT Crash switch in-situ test

NOTE: Ensure that all local restrictions have been observed.

Two persons will be required for steps (4) to (8).

(1) Ensure that AUTO/OFF/ON switch on ELT is at AUTO.

(2) Ensure remote ON/TEST and AUTO switch on panel 1P is at AUTO

(3) Remove two nuts and bolts securing ELT to support bracket.

(4) While holding the ELT transmitter close to the antenna, strike the front of the transmitter sharply with heel of hand. i.e. along line of sight axis.

(5) Ensure TRANSMITTER ON light on panel 1P is lit during transmission.

(6) Verify with the control tower, via the VHF system, that the transmissions on 121.5 MHz in (4) were received by them.

(7) Set remote ON/TEST and AUTO switch on panel 1P to ON/TEST and then immediately return to AUTO.

(8) Ensure that the transmission on 121.5 MHz has stopped and the TRANSMITTER ON light is extinguished.

(9) Position ELT on support bracket with direction of flight arrow facing forward.

(10) Secure ELT with two nuts and bolts.

E. Completion

(1) Render aircraft electrically safe and disconnect external power supply. Refer to 12-09-03, pb301.

(2) Set ON/TEST and AUTO switch on panel 1P is set to AUTO.

(3) Ensure AUTO/OFF/ON switch on ELT is set to AUTO.

(4) Disconnect headset and stow.



AMM25-61-01 13.0.0.0CRASH AXE

1. Description

The flight compartment is equipped with a crash axe, for use in an emergency.

The crash axe is stowed behind an access panel just aft of station 37.5 on the R.H. side. The front of the access panel is appropriately labelled.

The crash axe, Part No. 443, is supplied by Van Dussen AC.



AMM25-61-11 14.0.0.0FIRST AID KIT

1. Description

The passenger cabin is equipped with a first aid kit for use in emergency.

The first aid kit is stowed on the L.H. side wall at the Flight attendants station.

The first aid kit Part No. 70004-00 is supplied by Scott Aviation.



AMM25-61-16 15.0.0.0FLOTATION CUSHIONS - PASSENGER SEATS MAINTENANCE PRACTICES

1. Adustment/Test

A. Perform buoyancy check.

NOTE: The following check is demanded by FAR 37-178 TSO C72b.

The required buoyancy is to be not less than 14 lb. in fresh water at 85° F.

For ease of accomplishment most closely related to required conditions, it is recommended that the check be performed in a heated swimming pool.

The check may be performed as detailed in (1) or (2).

(1) Preferred method:

(a) For a period of not less than 8 hours, submerge the cushion (complete with cover and straps) so that no part is less than 24 in. below the surface.

(b) Free the cushion and check by means of a spring balance or weighted net that the buoyancy is not less than 14 lb.

(2) Alternative method:

(a) For a period of not less than 30 minutes, submerge the cushion (complete with cover and straps) so that no part is less than 24 in. below the surface.

(b) Free the cushion and measure buoyancy.

(c) Repeat (a) and (b) to complete four consecutive buoyancy checks, ensuring that buoyancy stabilises at not less than 14 lb.

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