Ata 25 Equipment and Furnishing

Training Manual ATA 25 – EQUIPEMENT & FURNISHING

Boeing 737-300/400/500 737-300/400/500 –CFM56-3 ATA 104 – Level 1 C

ATA 25 EQUIPMENT AND FURNISING Revision 1/ October 2011

1



For training purposes only. only. Copyright by Jat Tehnika/Solinair Technical Training. Jat Tehnika/Solinair Tehnika/Solinair is the owner of all rights to training documents. Any use outside the training measures, especially reproduction and/or copying of training documents − also extracts thereof −in any format all (photocopying, ( photocopying, using electronic systems or with the aid of other methods) is prohibited. Passing on training material to third parties for the purpose of reproduction and/or copying is prohibited without the express written consent of Jat Tehnika/Solinair . Legal requirements under copyright and criminal law, apply.

2



For training purposes only. only. Copyright by Jat Tehnika/Solinair Technical Training. Jat Tehnika/Solinair Tehnika/Solinair is the owner of all rights to training documents. Any use outside the training measures, especially reproduction and/or copying of training documents − also extracts thereof −in any format all (photocopying, ( photocopying, using electronic systems or with the aid of other methods) is prohibited. Passing on training material to third parties for the purpose of reproduction and/or copying is prohibited without the express written consent of Jat Tehnika/Solinair . Legal requirements under copyright and criminal law, apply.

2



ATA ATA 25 EQUIPMENT / FURNISHING……………………… FURNISHING………………………………………… …………………………………… ……………………………………… ……………………………..6 ………..6 25-00 GENERAL…………………………………………………………………………………………………………………..6 INTRODUCTION…………………………………………………………………………………………………………………..6 25-10 FLIGHT COMPARTMENT………………………………………………………………………………………………..8 FLIGHT COMPARTMENT EQUIPMENT LOCATION………………………………………………………………………...8 PILOTS’ SEAT……………………………………………………………………………………………………………………10 PILOTS’ SEAT REMOVAL & INSTALLATION………………………………………………………………………………..12 OBSERVER’S SEAT……………………………………………………………………………………………………………..14 25-20 PASSENGER COMPARTMENT………………………………………………………………………………………..16 COMPONENT FUNCTIONAL DESCRIPTION………………………………………………………………………………..16 PASSENGER COMPARTMENT COMPARTMENT SEATS………………………………………………………………………………………18 SEATS……………………………………………………………………… ………………18 PASSENGER COMPARTMENT COMPARTMENT SEATS (CONT)…………………………………………………………………………….20 (CONT)……………………………………………… …………………………….20 SIDEWALL LININGS……………………………………………………………………………………………………………..22 WINDOW REVEAL ASSEMBLY………………………………………………………………………………………………..24 SIDEWALL RISER PANELS AND AIR GRILLES…………………………………………………………………………….26 GRILLES……………………………………… …………………………………….26 SCULPTURED CEILING PANELS……………………………………………………………………………………………..28

3



CEILING PANEL HINGE ASSEMBLY…………………………………………………………………………………… ASSEMBLY…………………………………………………………………………………………28 ……28 PASSENGER SERVICE UNITS………………………………………………………………………………………………..30 OVERHEAD STOWAGE COMPARTMENT…………………………………………………………………………………..31 OVERHEAD STOWAGE COMPARTMENTS COMPARTMENTS (CONT)……………………………………………………………………….35 (CONT)………………………………………………………………………. 35 25-30 B UFFET / GALL EY……………………………………… EY………………………………………………………… ……………………………………… ……………………………………… ………………………37 ……37 GALLEY LOCATIONS AND IDENTIFICATION……………………………………………………………………………….37 GALLEY INSTALLATION………………………………………………………………………………………… INSTALLATION………………………………………………………………………………………………………..39 ……………..39 GALLEY SERVICE POWER (CONFIG. 1)…………………………………………………………………………………….41 GALLEY SERVICE POWER (CONFIG. 2)…………………………………………………………………………………….42 25-40 LAVATORIES……………………………………………………………………………………………………………..45 LAVAT LAVATORIY ORIY EQUIPMENT…………………………………………………………………………… EQUIPMENT………………………………………………………………………………………………………45 …………………………45 25-50 CARGO COMPARTMENTS……………………………………………………………………………………………..47 CARGO COMPARTMENTS……………………………………………………………………………………………………..47 CARGO NET………………………………………………………………………………………………………………………49

4



25-60 EMERGENCY……………………………………………………………………………………………………………..51 EMERGENCY EQUIPMENT…………………………………………………………………………………………………….51 ESCAPE STRAP………………………………………………………………………………………………………………….53 DOOR MOUNTED ESCAPE SLIDES…………………………………………………………………………………………..55 ESCAPE SLIDE MAINTENANCE PRACTICES……………………………………………………………………………….57

5


Boeing 737-300/400/500 –CFM56-3 ATA 104 – Level 1 C

ATA 25 EQUIPMENT / FURNISHING 25-00 GENERAL INTRODUCTION

Equipment and furnishings provide for the comfort and convenience of passengers and crew m embers, for handling and stowing cargo, and for ensuring p assenger and crew safety in an emergency. Equipment and furnishings are located in the flight compartment and the passenger compartment. Cargo nets are around the door opening in each cargo compartment to prevent cargo from blocking the doors. Emergency equipment is throughout the airplane including slides on each door and escape straps.

6



Equipment and Furnishi ng

FIGURE 1 7



25-10 FLIGHT COMPARTMENT FLIGHT COMPARTMENT EQUIPMENT L OCATION

The flight compartment provides stations for the captain, first officer, and observers. The flight compartment is air conditioned, which is controlled separately from the passenger cabin. The captain’s seat is on the left and the first officer’s seat is on the right. Aft of the center console and forward of the flight compartment entrance door is a first observer seat; the seat folds and stows behind the P6 panel. An optional second observer’s seat is fixed behind the captain between the P18 panel and the first observer ’s station.

8



Control Cabin Equipm ent Lo cation

FIGURE 2 9



PILOTS’ SEAT The purpose of the pilots’ seat is to provide a safe and comfortable crew station for the captain and the first o fficer. The captain’s seat is on the left side of th e flight compartment, and the first officer ’s seat is on the right side. The captain’s and first officer’s seats are opposite hand assemblies. The main elements of each seat are the base, the seat bottom, the seat back, a support linkage and safety harness. A metal frame forms the main structure of the seat back. An improved back and seat bottom cushion is fastened to the frame and a sheepskin cover 15 attached to the cushion. The seat back includes a dense, thick f oam cushion, and an inflatable lumbar support. Adjustment of the lumbar support is accomplished with the aid of an air valve on the inboard side of each seat, integral with the seat back cushion. Three relief valves are provided to automatically compensate for changes in cabin pressure. The seat can be adjusted fore and af t, and up and down; the angles of the seat back and bottom can also be independently varied. The adjustment control levers are on the inboard side of each seat.

10



Pilot’s Seat

FIGURE 3 11



PILOTS’ SEAT REMOVAL & INSTALLATION Maintenance Practices The pilots’ seats are mounted on floor tracks and adjust fore and aft. Re moval Procedure (Curved tracks): - Remove the forward travel limit stops from the floor tracks. - Actuate the fore-aft control lever. - Move the seat forward until all of the bogie unit rollers are free from the tracks. - Release the fore-aft control lever. Installation Installation is the reverse of the removal. Align each bogie unit so the tapered roller and adjustment nut face inboard. Adjust men t Tapered rollers are adjusted after the seat is fully assembled and installed on floor tracks. All operational checks should be accomplished with a person in the seat (170 pounds, 77 Kg minimum weight). Seats should move freely without racking or binding.

12



Pilot’s Seat Removal & Inst allation

FIGURE 4 13



OBSERVER’S SEAT First Observer’s Seat The first observer’s seat is erected in the entryway in front of the control cabin door. The right wall of the entryway has a recess into which the seat can be folded. The seat must be folded to allow persons to enter or leave the control cabin. The main elements of the seat are the bottom, the back, and the safety harness. The seat bottom is a cushion fastened to a metal framework. A hinge on the right side fastens the seat bottom to the wall of the control cabin entryway. There are two retractable pins on the left side of the seat bottom. The pins fit into holes in a support bracket on the aft left control cabin bulkhead and hold the seat bottom in its unfolded position. The seat bottom cushion is made of a buoyant material and is certified as a flotation device. The seat back is hinged to the seat bottom. When erected, the seat back must be f astened to the sides of the doorway to provide rigidity to the seat assembly. Before returning the seat to the recess in the entryway, the seat back must be folded forward onto the seat bo ttom. bottom. The pins fit into holes in latch plates on the lef t wall of the control cabin entryway, and thus hold the seat bottom in its unf olded position. The seat bottom cushion is made of a buoyant material and is certified as a flotation device. The seat back is hinged to the seat bottom. The back must be f olded onto the seat before the bottom is folded into the recess in the entryway wall. Second Observer’s Seat The second observer’s seat is fixed to the aft compartment wall behind the captain’s seat; the seat is adjacent to the P18 panel but recessed. The seat bottom is adjustable, fore and aft, on t racks. The seat back has upper and lower sections joined by straps. The sections are attached to the wall by Velcro tape. A shoulder harness and lap belt are provided. The shoulder harness is fixed.

14



Observer’s Seats

FIGURE 5 15



25-20 PASSENGER COMPARTMENT COMPONENT FUNCTIONAL DESCRIPTION

The passenger compartment contains seats, floor coverings, sidewall and ceiling panels, provisions for equipment and luggage stowage, service units, and emergency equipment for th e comfort and convenience of the passengers. The passenger compartment is located between the aft end of the f light compartment, at the forward end of the airplane, and the pressure bulkhead at the aft end of t he airplane.

16



FIGURE 6 17



PASSENGER COMPARTMENT SEATS

Passenger seats attach to tracks on the compartment floor. The tracks are continuous extrusions with circular cutouts which receive the seat attachment fittings a nd allow them to be positioned in 1-inch increments. The seats have reclining backrests and lap belts. The actuating button for the seatback is on the armrest. Most seats have tables, in the seatback, which fo ld down. The seats are two and three u nit assemblies. Seat cushions can be used as flotation devices.

18



FIGURE 7 19



PASSENGER COMPARTMENT SEATS (CONT) An attendant seat is mounted on the aft wall structure of the forward lavatory. One seat mounts on the forward side of each aft lavatory. The seat bottom folds vertically when stowed. Each attendant seat has a shoulder harness and a lap belt. Flashlight and life vest stowage is in a compartment below the seat bottom. The headrest can be used as a flotation device. A communication handset is installed adjacent to the headrest.

20



FIGURE 8 21



SIDEWALL LININGS Sidewall Panels - The sidewall panels are fire-resistant fiberglass-fabric covered. The exposed surface is scratch—resistant and washable. The window lights fit through a cutout near the top of the panel. Passenger window reveal assemblies mount in cutouts near the middle of each panel and are removable with the panel and seats in place. The majority of the panels are 2-bay 2-window; however, there are also 2—bay 1—window and 1-bay and 1-window panels. The sidewall panels attach to structure with support brackets on each panel retainer along the vertical sides. Decorative trim strips fit in grooves in the panel retainer and cover the fasteners. The inboard edge of the panel slides into the air conditioning extrusion. Insulation - Fiberglass insulation blankets with moisture impervious coverings are in the sidewall. The blankets thermally and acoustically insulate the compartment. Maintenance Practices To remove the panel, pull the decorative strip down and out of each side of the panel to be removed. Release the five fasteners on each side securing the panel to the airplane structure. The panel can now be lifted to clear the bottom retaining spring clips then pulled out and down to slip the top out of the channel in the air conditioning extrusion. Disconnect all window light electrical connections.

22



Side Wall Linings

FIGURE 9 23



WINDOW REVEAL ASSEMBLY

The window reveal assembly consists of the trim ring, shade, inner pane, and reveal. It can be removed without removing the sidewall panel. Normally, there are two window reveal assemblies per sidewall panel. Maintenance Practices To remove the reveal assembly, insert latch release tool (3/32-inch (2 mm) rod) downward into the hole on the bottom of the trim ring. Push down firmly to release the latch. With the latch released, pull inboard on the bottom of the window reveal assembly until the bottom clears the sidewall panel. Pull window shade full down. Lower the assembly enough to clear the two top securing stops from the sidewall panel. To install the reveal, use the reverse procedure.

24



Window Reveal

FIGURE 10 25



SIDEWALL RISER PANELS AND AIR GRILLES

Carpet Riser Panel - The riser panel is a nome x honeycomb-covered panel with the exposed surface covered with carpet. The panel is secured to the airplane structure with two screws at each circumferential. Air Grilles - Air grilles are located in the majority of the riser panels. They permit air f rom the passenger compartment to circulate around the cargo compartments. The back of the air grille is covered with a screen to prevent lint and debris from being drawn through into the space between the fuselage and the cargo compartment. Maintenance Practices To remove the panel, remove the carpet to expose the screws. After removing the screws, the pan el is lifted slightly to clear the floor carpet. Pull the bottom out and lower the panel to free it from the spring clips on the lower edge of the sidewall panel. The panel is replaced in reverse order. The grille is removed by two push-push fasteners.

26



Sidewall Riser Panels and Air Grill s

FIGURE 11 27



SCULPTURED CEILING PANELS Sculptured panels line the ceiling over the passenger compartment aisles. They have a scratch-resistant exposed surface. The panels pivot on releasable hinge mechanisms on the two outboard corners. The inboard edge slides into and is secured by a groove in the conditioned air outlet extrusion. A lanyard connected between the airplane structure and the panel limits downward movement when opened. The panel can be removed by disconnecting the lanyard and releasing the two hinges. CEILING PANEL HINGE ASSEMBLY Maintenance Practices Lower/Raise Panel - To lower the sculptured ceiling panels release the hinge by pressing down on the release lever on each hinge assembly. - The ceiling panel hinge-half can now be moved outboard in the slots in the stowage bin hinge-half. This frees the inboard edge of the sculptured ceiling panel from the groove in the air outlet extrusion. The inboard edge can be lowered, and the outboard edge pivots on the ceiling panel hinge-half. The restraining lanyard on the panel inboard side restricts downward movement to prevent damage. Raising the panel is done in reverse order. Panel Removal - To remove the panel, it is necessary to lower the panel first. After the panel is lowered, press down and hold the release lever. The ceiling panel hinge-half can be drawn inboard and clear o f the stowage bin hinge-half. When both hinge-halves are clear, the panel can be removed.

28



FIGURE 12 29



PASSENGER SERVICE UNITS Passenger service units (PSU) are above each passenger seat row. Each PSU contains emergency oxygen equipment, speaker, reading lights, gasper air outlets, life vest stowage, and information signs. The PSU panel assembly is hinged outboard and has a lanyard to limit the lowering distance when opened. The latches are on the inboard side and are released by inserting a small round rod through the two small holes in the panel and pushing up on the latch. The speaker, information signs (NO SMOKING, FASTEN SEAT BELT), life vest stowage, gasper air and reading light assemblies are all on one panel. The PSU can be positioned longitudinally in one inch increments. PSUs are interchangeable only forward and aft, not from left to right sides. Individual reading lights are controlled by switches on the PSU. An attendant call light and switch is located between the reading lights.

30



FIGURE 13 31



Passenger Service Unit s

FIGURE 14 32



OVERHEAD STOWAGE COMPARTMENT The overhead stowage compartments extend the length of the passenger compartment above the seats. They vary in length and width depending on the installation locations. The compartments are secured to structure with turnbuckles. A diagonal turnbuckle prevents forward and aft movement. The bins are correctly positioned with alignment pins. The door is attached by hinges to the bin. The latch handle, when pressed, rotates a torque tube that releases the latches at both ends of the door. A mechanical actuator on each hinge assembly assists in door opening and maintains the door in the open position.

33



Overhead Stowage Compartments

FIGURE 15 34



OVERHEAD STOWAGE COMPARTMENTS (CONT) Removal - Remove ceiling panel(s) mounted on stowage compartment. - Remove fluorescent light and disconnect electrical connector. Remove PSU and spacer panels to access lower turnbuckles. - Remove fasteners on outboard side of bullnose, remove emergency aisle light and zone temperature sensor if installed and remove bullnose. Remove alignment pins between adjacent stowage bins. - Remove bolts to disconnect turnbuckles at lower, outboard side of stowage bin. - Support stowage bin and remove bolts to disconnect upper turnbuckles. Remove overhead stowage bin. Installation - Position overhead stowage bin between adjacent stowage bins or structure - and install alignment pin(s). - Install each turnbuckle. - Adjust turnbuckles to support stowage bins weight while maintaining alignment with adjacent stowage bins. - Install ceiling panel(s). - Install fluorescent light if required. - Attach inboard edge of bullnose to extrusion. - Install emergency aisle light or zone temperature sensor as required. - Raise bullnose and install fasteners. - Install PSU and spacer panels.

35



FIGURE 16 36



25-30 BUFFET / GAL LEY GALLEY LOCATIONS AND IDENTIFICATION The purpose of the galleys is to provide food and beverage preparation facilities. The number and location of the galleys is determined by the customer. There are seven possible locations.

37



Galley Location

FIGURE 17 38



GALLEY INSTALLATION Structure Attachments - Each galley is attached to the airplane structure with four plunger-type floor attachments. The recesses are filled with grease to waterproof the connections. The grease, MIL-C-11796, Class 3, is liquified by heating it to 65C (15OF); it is then poured into the recess and allowed to solidify. The gasket and cover are installed to complete the installation. - At the top of the galley, a tie rod assembly is attached to galley structure and to a ceiling attachment fitting. An access plate in the upper compartment of the galley allows access to the tie rod assembly. Galley Utilities - Water and electrical power are supplied to some galley units. The connections to the potable water system and electrical power system are in the top of the galley unit.

39



FIGURE 18 40



GALLEY SERVICE POWER (CONFIG. 1) Power Three-phase, 115 volt, 400 Hertz, ac power is supplied to galley units for ovens, coffee makers, or other electrically powered units. Control The control switch for galley electrical power, located on the P-5 panel, provides a ground for the galley power relays. 28 volts dc for the relays comes from opposite generator control units. Loss of either generator will automatically cause a loss of power to all galleys.

41



FIGURE 19 42



GALLEY SERVICE POWER (CONFIG. 2) Power Three-phase, 115 volt ac power from the number 1 and 2 generator busses operates the galley units. The number 1 and 2 generator busses are powered by the engine driven generators, the APU, or external power. Control The galley switch on the P5 panel controls electrical power to the galleys. In order to preserve power for critical systems, all galley power will be lost automatically if a generator bus loses power. Also, all galley power will be lost if the total electrical load on the APU exceeds the maximum. Operation The galley switch provides power to energize the galley power relay which provides electrical grounds for relays R61 and R62. The galley relays will be energized if the appropriate engine generator breaker (EGB), APU generator breaker (APU GB), or external power contactor (EPC) is closed. When R61 and R62 are energized, the galleys are connected to the respective generator busses. The galley powered by one generator bus is enabled by the control devices of the other generator bus. The loss of either generator bus causes a loss of power to all galleys. For example, if the num ber 1 generator fails, power will no longer be available to the forward galley even though galley relay R61 remains energized. At the same time, EGB 1 will open, de-energize galley relay R62, and remove power from the aft galley. If the APU is turned on and connected to number 1 generator bus, the forward galley will be powered. Also, APU GB1 will close, energize galley relay R62, and allow the number 2 generator to power the aft galley. The galley load shed sensor module senses the phase current generated by the APU. If the current in an y phase exceeds 162 amps, switch S1 will be energized. The higher the current, the f aster S1 will be energized. W hen switch S1 is energized, current through the galley switch solenoid on the P5 panel will exceed 0.8 amps and turn the galley switch OFF.

43



FIGURE 20 44



25-40 LAVATORIES LAVATORIY EQUIPMENT The lavatories provide sanitary facilities on the airplane. Lavatories are located in the forward and aft ends of the passenger compartment. Each lavatory contains a toilet, wash basin, mirror, and all the necessary vanity items and disposal units. Ventilation is provided through the service unit. Air exhausts through overboard vents in each lavatory. Structure in the lavatory area is painted with a protective coating to prevent corrosion. Water is supplied from the potable water system.

45



FIGURE 21 46



25-50 CARGO COMPARTMENTS CARGO COMPARTMENTS The lower cargo compartments provide space f or carrying luggage, freight, equipment, and cargo. The cargo compartments are located below the passenger compartment. One compartment is forward of the center wing section, and the other is aft of the main wheel well. The forward compartment volume is 425 cubic feet and the af t compartment volume is 643 cubic feet. The compartments are pressurized class D (smother type) compartments for fire protection. Any fire starting in the compartment will consume the oxygen and extinguish itself. An inward-opening door is in the right side wall of each compartment. The forward compartment has an access panel in the ceiling through which the compartment can be entered from the passenger cabin. Access is also possible through the E & E compartment by removing the bulkhead blowout panel. There is no airflow through the cargo compartments during flight. Airflow goes around the compartments in the space between the fuselage and the compartment lining. A pressure equalization valve is located in the aft bulkhead of each compartment. The valves allow air flow into or out of the compartments to keep the compartment pressure the same as cabin pressure. Each compartment has blowout panels. The blowout panels are pushed out of their supports by a differential pressure of 1.0 psi. Air can then f low into or out of the compartment at a greater rate than the pressure equalization valves would allow.

47



Cargo Compartments

FIGURE 22 48



CARGO NET A cargo net suspended across the compartment prevents cargo from shifting when the airplane is in flight. One-inch wide fabric straps form the webbing. Quick-release tie-down fasteners are sewed to the strap ends in some places on the outboard edges of the nets. Other strap ends have snap latches or buckles. The webbing is attached to anchor-plates on the sidewalls and loop fittings on the ceilings.

49



Cargo Nets

FIGURE 23 50



25-60 EMERGENCY EMERGENCY EQUIPMENT The emergency equipment provides a means for the flight attendants to assist passengers and passengers to assist themselves in the event of an emergency. Escape slides are located on each entry and service door. Escape straps in the overhead above the captain’s and first officer’s seats. An optional escape strap may be installed at the overwing escape hatch.

51



Emergency Equipment

FIGURE 24 52



ESCAPE STRAP Control Cabin Escape Straps An escape strap is stowed in panel receptacles above the captain’s and first officer’s seats. The fixed end of the strap is anchored to overhead structure. Access to the strap is gained by unlatching the receptacle cover. Egress is through the No. 2 sliding windows.

53



Escape Strap Locatio n

FIGURE 25 54



DOOR MOUNTED ESCAPE SLIDES The escape slides provide a means of emergency egress from the airplane. The slides can also be separated from the airplane and used as flotation devices. An escape slide is mounted on each entry and service door. Each escape slide assembly consists of an escape slide package, an escape slide compartment, and two floor brackets. The escape slide package is stowed in the escape slide compartment which is fastened to the lower inboard face of each entry and service door. The floor brackets are located at the forward and aft ends of the doorways, inboard of the door sill. The escape slide package consists of an escape slide, a detachable girt, girt bar, gas cylinder, and valise. The gas cylinder contains high pressure gas for inflating the slide. The valise holds the slide in the stowed position, and opens to deploy the slide. For automatic escape slide deployment, the slide must be placed in the operation readiness mode by securing the girt bar in the floor brackets. W hen the door is opened, tension on the girt and latch cable will cause the cover latch to separate, allowing the escape slide compartment to open and the slide to deploy. Inflation by the gas cylinder and aspirator is triggered by tension on the inflation cable secured to the girt bar an d the gas cylinder discharge valve. One end of a detachable fabric girt is attached to the slide with the opposite end attached to the girt bar. Removing the parachute-type pin causes the slide to separate from the airplane. The slide can be used as a f lotation device.

55



Door Mount ed Escape Slide

FIGURE 26 56



ESCAPE SLIDE MAINTENANCE PRACTICES To ensure that the slide is ready for use, check the pressure gage reading at regular intervals as required by each airline’s operating procedures. The temperature compensating pressure gage needle should be within, or not more than one needle width above, the green band. Although the slide will be usable following inflation with the bottle pressure at the minimum safe level, it is recommended that the pressure should be no less than 3000 psig (at 21C, 70F) for initial installation of the slide on the airplane, and that the bottle be recharged before the pressure drops below the minimum safe level.

57

Ata 25 Equipment and Furnishing

Recommend Documents