ATA 25-00
ATA 25-00
Equipment and Furnishing
Equipment and Furnishing
ATA 25-00 Equipment & Furnishing ATA 25-00 Equipment & Furnishing
Cockpit
Cockpit / / Flight Flight Deck ...Deck ...3...3 Passenger
Passenger Cabin Cabin ...3...3 Galleys Galleys ...3....3 Lavatories Lavatories ...33 Emergency Emergency ...3...3 Insulation Insulation ...33 Maintenance
Maintenance Precautions Precautions ...33 ATA 25-10 Cockpit/Flight Deck
ATA 25-10 Cockpit/Flight Deck Introduction
Introduction ...1...1 ATA 25-11 COCKPIT SEATS
ATA 25-11 COCKPIT SEATS Description
Description ...3....3 Components
Components ...33 Pilot
Pilot / / Copilot Copilot Seat ...Seat ...3.3 Observer
Observer Seat Seat ...5...5 Cockpit
Cockpit Linings Linings ...7...7 Cockpit
Cockpit Consoles Consoles ...7...7 Operation
Operation ...9...9 Pilot
Pilot / / Copilot Copilot Seat ...Seat ...9.9 Seat
Seat Height Height Adjustment ...Adjustment ...9...9 Backrest
Backrest Inclination Inclination Adjustment ...Adjustment ...9...9 Thightrest
Thightrest adjustment ...adjustment ...9...9 Lumbar
Lumbar Adjustment Adjustment ...9...9 Inertial
Inertial Reel Reel Locking ...Locking ...9...9 Armrest Adjus
Armrest Adjustment tment ...9...9 Seat Fore,
Seat Fore, Aft and Aft and Lateral Adjustment ..Lateral Adjustment ... 1111 Backup Operation
Backup Operation of the of the Pilot Seats ...Pilot Seats ... 1111 Pilot Seat
Pilot Seat Adjustment – Eye Adjustment – Eye Locator ...Locator ... 1313 Observer
Observer Seat Seat ... 1515
ATA 25-20 PASSENGER CABIN ATA 25-20 PASSENGER CABIN
Description
Description ... 11 ATA 25-21 PASSENGER SEATS
ATA 25-21 PASSENGER SEATS Description Description ... 33 Components Components ... 33 Operation Operation ... 33 Seatback: Seatback: ... 33 Armrest: Armrest: ... 33 ATA 25-21 FLIGHT ATTENDANT SEATS
ATA 25-21 FLIGHT ATTENDANT SEATS Description Description ... 55 Components Components ... 55 Operation Operation ... 55 ATA 25 -22 PASSENGER CABIN CEILING
ATA 25 -22 PASSENGER CABIN CEILING Description Description ... 77 Components Components ... 77 Operation Operation ... 77 Passenger
Passenger service service Unit Unit (PSU) ...(PSU) ... 77 Overhead
Overhead Bin Bin ... 77 ATA 25-23 SIDEWALL PANELS
ATA 25-23 SIDEWALL PANELS Description
Description ... 99 Components
Components ... 1111 Sidewall
Sidewall Panels Panels ... 1111 DADO
DADO Panels ...Panels ... 1111 Door
Door Linings Linings ... 1111 ATA 25-24 PASSENGER-CABIN FLOOR FINISH
ATA 25-24 PASSENGER-CABIN FLOOR FINISH Description
Description ... 1313 Components
Components ... 1313 Passenger- Cabin
Passenger- Cabin Floor Floor Finishing ...Finishing ... ... 1313 Lavatory
Lavatory Floor Floor Finishing ...Finishing ... ... 1313 ATA 25-25 FLIGHT ATTENDANT PANEL
ATA 25-25 FLIGHT ATTENDANT PANEL Description
Description ... 1515 Operation
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ATA 25-00
ATA 25-00
Equipment and Furnishing
Equipment and Furnishing
ATA 25-26 Closets ATA 25-26 Closets Description Description ... 1717 Components Components ... 1717 ATA 25-27 Partitions ATA 25-27 Partitions Description Description ... 1919 Operation Operation ... 1919 FWD FWD Windscreen Windscreen ... 1919 Aft Windscreen Aft Windscreen ... 2121 Curtain Curtain ... 2121 ATA 25-30 Galley ATA 25-30 Galley Description Description ...1.1 ATA 25-31 FORWARD GALLEYS
ATA 25-31 FORWARD GALLEYS Description
Description ...3.3 ATA 25-34 AFT GALLEY
ATA 25-34 AFT GALLEY Description
Description ...5..5 ATA 25-36 G
ATA 25-36 G ALLEY ELECTRICAL SYSTEMALLEY ELECTRICAL SYSTEM Description
Description ...7..7 Operation
Operation ...7...7 ATA 25-37 GALLEY INSERTS
ATA 25-37 GALLEY INSERTS Description
Description ...7.7 Components
Components ...7...7 Hot
Hot Jug Jug ...7....7 Coffee
Coffee Maker ...Maker ...7..7 ATA 25-40 Lavatory
ATA 25-40 Lavatory Description
Description ...1.1 Forward
Forward lavatory ...lavatory ...1..1 Aft lavatory
Aft lavatory ...1...1 ATA 25-60 Emergency Equipment
ATA 25-60 Emergency Equipment Description
Description ...1.1 ATA 25-61 Emergency Locator
ATA 25-61 Emergency Locator Transmitter SystemTransmitter System Description
Description ...3.3 ELT
ELT Transmitter Transmitter Unit ...Unit ...5...5 ELT
ELT Switch Switch ...5...5
ELT
ELT Remote Remote Switch Switch Panel Panel ... 55 ELT
ELT Antenna Antenna ... 55 ELT
ELT Battery Battery ... 55 ELT
ELT Buzzer Buzzer ... 55 ELT/NAV
ELT/NAV Interface Interface Unit ...Unit ... 77 Operation
Operation ... 99 ATA 25-62 EMERGENCY-EVACUATION SLIDE SYSTEM
ATA 25-62 EMERGENCY-EVACUATION SLIDE SYSTEM Description
Description ... 1111 Components
Components ... 1111 Slide
Slide Assembly ...Assembly ... 11... 11 Slide
Slide Lighting Lighting system system ... 11.... 11 Inflation
Inflation System ...System ... 1313 Packboard
Packboard Plate ...Plate ... 1313 Operation
Operation ... 1515 Abnormal Operation
Abnormal Operation ... 1515 ATA 25-66 LIFE RAFTS SYSTEM
ATA 25-66 LIFE RAFTS SYSTEM Description
Description ... 1717 Components
Components ... 1717 Life
Life Raft Raft Assembly ...Assembly ... 1717 Inflation
Inflation System ...System ... 1717 Survival
Survival Kit Kit ... 1717 Carrying
Carrying Case Case ... 1717 ATA 25-80 INSULATION ATA 25-80 INSULATION Description Description ... 11 Components Components ... 33 Insulation
Insulation System ...System ... 33 Sound
Sound Dampener Dampener System ...System ... 55 Nose
Nose Treatment Treatment Felt Felt System .System ... 55 Soft
Soft Blue Blue Sound Sound dampener System ...dampener System ... 55 Smoke
Smoke Seal Seal System ...System ... 77 ATA 25 Master Minimum Equipment List FAA/EASA
ATA 25-00 EQUIPMENT &
ATA 25-00 EQUIPMENT &
FURNISHING
FURNISHING
This system contains the items that provide safety in an emergency This system contains the items that provide safety in an emergency condition, as well as comfort and convenience for passengers and crew condition, as well as comfort and convenience for passengers and crew members.
members.
The EQUIPMENT/FURNISHINGS includes these
The EQUIPMENT/FURNISHINGS includes these subsystems:subsystems:
COCKPIT / FLIGHT DECK
COCKPIT / FLIGHT DECK
The cockpit is a
The cockpit is a″″Quiet and DarkQuiet and Dark″″type and accommodates two pilots andtype and accommodates two pilots and one observer with comfort during all flight phases, with minimum one observer with comfort during all flight phases, with minimum workload and maximum safety. The cockpit is separated from the workload and maximum safety. The cockpit is separated from the passenger cabin by a partition with
passenger cabin by a partition with a lockable door.a lockable door.
PASSENGER CABIN
PASSENGER CABIN
The passenger cabin is designed to provide spacious and visually The passenger cabin is designed to provide spacious and visually attractive accommodation for passengers and flight crew.
attractive accommodation for passengers and flight crew.
GALLEYS
GALLEYS
The galleys are locations where the flight attendants perform their duties The galleys are locations where the flight attendants perform their duties and stow miscellaneous items. Their duties include activities such as and stow miscellaneous items. Their duties include activities such as preparing food and beverage, making flight safety announcements, and preparing food and beverage, making flight safety announcements, and controlling the audio
controlling the audio entertainment.entertainment.
LAVATORIES
LAVATORIES
The lavatories provide facilities for the passengers and for
The lavatories provide facilities for the passengers and for the flight crewthe flight crew to get the minimum hygiene and
to get the minimum hygiene and amenity conditions.amenity conditions.
EMERGENCY
EMERGENCY
This subsystem includes the equipment aimed at assisting the crew This subsystem includes the equipment aimed at assisting the crew members and passengers in the event of
members and passengers in the event of an emergency condition.an emergency condition.
INSULATION
INSULATION
The insulation is
The insulation is composed of cockpit/passenger cabin insulation system,composed of cockpit/passenger cabin insulation system, sound dampener system, and noise
sound dampener system, and noise treatment felt system. The insulationtreatment felt system. The insulation is installed to help stabilize the air temperature and reduce the noise is installed to help stabilize the air temperature and reduce the noise levels in the
levels in the aircraft.aircraft.
MAINTENANC
MAINTENANCE
E PRECAUTIONS
PRECAUTIONS
•
• MAKE MAKE SURE THAT SURE THAT THE AIRCRAFT THE AIRCRAFT IS IS IN A IN A SAFE CONDITIONSAFE CONDITION BEFORE YOU DO THE MAINTENANCE PROCEDURES. THIS BEFORE YOU DO THE MAINTENANCE PROCEDURES. THIS IS TO PREVENT INJURY TO PERSONS AND/OR DAMAGE TO IS TO PREVENT INJURY TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT.
THE EQUIPMENT.
•
• USE ONLUSE ONLY PROTECTIVY PROTECTIVE CAPE CAPS FOR S FOR THE PROTECTITHE PROTECTION OFON OF CONNECTOR PINS OR SOCKETS IN ELECTRICAL CONNECTOR PINS OR SOCKETS IN ELECTRICAL CONNECTORS. OTHER MATERIALS CAN CAUSE DAMAGE CONNECTORS. OTHER MATERIALS CAN CAUSE DAMAGE TO THE CONNECTOR PINS OR SOCKETS, OR LET TO THE CONNECTOR PINS OR SOCKETS, OR LET UNWANTED MATERIALS STAY IN THE CONNECTOR.
UNWANTED MATERIALS STAY IN THE CONNECTOR.
•
• EXAMINE EXAMINE ALL THE ALL THE WORK ARWORK AREAS TO EAS TO MAKE MAKE SURE THASURE THAT YOUT YOU REMOVED ALL TOOLS AND EQUIPMENT AFTER YOU REMOVED ALL TOOLS AND EQUIPMENT AFTER YOU COMPLETED THE WORK. IF YOU DO NOT OBEY THIS COMPLETED THE WORK. IF YOU DO NOT OBEY THIS PROCEDURE, DAMA
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ATA 25-00
Equipment and Furnishing
FIGURE 1:EQUIPMENT/FURNISHING
ATA 25-10 COCKPIT/FLIGHT DECK
INTRODUCTION
The cockpit is a “Quiet and Dark” type and accommodates two pilots end one observer with comfort during all flight phases, with minimum workload and maximum safety. The cockpit is separated from the passenger cabin by a partition with a lockable door.
The COCKPIT includes these subsystems:
• COCKPIT SEATS • COCKPIT LININGS • COCKPIT CONSOLES
The cockpit is provided with thermal and acoustic insulation for noise and temperature comfort. Adjustable sun visors are installed on front windows to protect pilot’s eyes from g lare. Direct vision windows are featured with curtains. Both sun visors and curtains are easily stowed when not in use. There are dome lights and chart lights in the cockpit to provide sufficient illumination under normal and emergency electrical conditions. These lights enable the crew to perform normal activities in the cockpit. Stowage areas for the applicable emergency equipment are provided.
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ATA 25-10
Cockpit/Flight Deck
ATA 25-11 COCKPIT SEATS
DESCRIPTION
The cockpit is equipped with a pilot seat, a copilot seat, and an observer seat.
The pilot and copilot seats allow the pilots a smooth interface with the cockpit environment and ensure safety in normal and emergency flight conditions.
The observer seat is positioned across the cockpit doorway to provide the observer with a clear view of the aircraft controls and avionics. In addition, the seat allows the observer to monitor the crew’s actions in the cockpit. The observer seat provides a comfortable seated position for up to three hours of continuous flight. The pilot seat is on the LH side and the copilot seat is on the RH. The observer seat is installed in the LH cockpit bulkhead,
COMPONENTS
PILOT / COPILOT SEATThe pilot and copilot seats are identical in their design and operation, differing only in the symmetrical arrangement of the controls. The pilot seats have mechanical, electrical and hydromechanical commands. These are some of the commands:
• Handle for the thighrest support adjustment, with mechanical
operation;
• Adjustable armrests and headrest, with mechanical operation; • Longitudinal/lateral adjustment lever, with mechanical operation;
• Control switch for electrical actuation of the seat height
adjustment;
• Control for backrest reclining, with hydromechanical operation; • Handle for harness inertial device manual locking;
• Pushbutton actuator for lumbar support, which actuates a foam
bag with air in it, allowing different adjustments.
The pilot seats can be operated with or without electrical power. Some commands have backups, such as:
• Lateral adjustment, through a spare lateral handle located at the
aft part of the lower structure.
• Longitudinal adjustment, through a spare longitudinal handle
located at the middle of the rear crosspiece of the lower structure.
• Backrest adjustment, through an override system that allows
manual tilting of the backrest to the upright position in case of failure of the controls or recline actuator.
• Height adjustment, through a crank handle attached below the
seat pan and used in the electrical actuator override manual control.
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ATA 25-10
Cockpit/Flight Deck
OBSERVER SEAT
The observer seat has two positions: stowed and deployed.
When the observer seat is stowed, it folds up and rotates away from the door area to the cockpit bulkhead behind the pilot seat. When the observer seat is deployed, it occupies a position immediately forward of the cockpit door. The cockpit door can be opened and closed when the observer seat is deployed.
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ATA 25-10
Cockpit/Flight Deck
COCKPIT LININGS
The function of the cockpit linings is to create a visual, thermal and acoustic separation between the aircraft structure and systems and the interior of the cockpit. The linings are designed to operate within the specified cabin pressure requirements.
COCKPIT CONSOLES
The cockpit has three consoles. They are open or closed compartments used to stow convenience items, gadgets and emergency equipment. The cockpit consoles are:
• LH Console • RH Console • RH Aft Console
Complementary consoles extend forward from each lateral console. These consoles comprise blow-out panels. Each lateral console has a gutter, which drains the condensation from the sidewalls, supporting structure, or rain from the direct vision window.
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ATA 25-10
Cockpit/Flight Deck
PILOT / COPILOT SEAT
Most of the pilot seat adjustment controls are located on the RH and LH trim panels of the seats for best ergonomics.
SEAT HEIGHT ADJUSTMENT
The electrical actuator control switch has three positions:
• The neutral position locks the height adjustment (provided by
electrical actuator irreversibility).
• The up position lifts up the seat. • The down position lowers the seat. BACKREST INCLINATION ADJUSTMENT
The backrest recline lever has three positions:
• The neutral position locks the backrest recline.
• The up position allows backrest recline setting from 5 degrees to
25 degrees (20 degrees range).
• The down position locks the backrest in the upright position 5
degrees (in case of recline actuator or control cable failure).
THIGHTREST ADJUSTMENT
The thightrest system is located in front of the seat pan. An angle setting system provides support as required. While turning the knob, the two thightrest structures rotate together from -27 degrees up to 27 degrees, taking 8-degree seat pan tilt as a reference. A break over system allows pilot thigh support without discomfort while pushing the rudder pedal.
LUMBAR ADJUSTMENT
The lumbar support valve pushbutton is pressed to open the valve and release the air contained in the pouch while the pilot is pushes with his back to obtain to required setting. Then the push button is released to lock the setting.
INERTIAL REEL LOCKING
The inertial reel locking lever has two positions:
• Locked when pushed forward • Released when pushed backward ARMREST ADJUSTMENT
The armrest adjustment control is located under the forward end of the armrest, and includes a roller that controls the height of the armrest.
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ATA 25-10
Cockpit/Flight Deck
SEAT FORE, AFT AND LATERAL ADJUSTMENT
The longitudinal (fore and aft) and lateral locking pins are linked to the same command handle, which has 3 positions:
• The neutral position locks the seat.
• The up position unlocks the longitudinal locking pins and allows
seat adjustment fore and aft along the seat tracks between the stops.
• The down position unlocks the lateral locking pins and allows seat
outboard stowage when the seat is at the rear stop level.
• The lateral locking pins pull the lateral cables, which pull both
locking pins; the seat is then free to slide laterally.
When the lateral locking pins are released, both locking pins engage in holes in the rail through the action of their return springs; then the seat is locked in position.
Manual adjustments of the pilot seat are possible for height, lateral, aft, and fore adjustments. An override manual control allows the seat to be adjusted in case of electrical motor failure or in case of electrical supply failure.
• A crank handle is located under the seat and allows adjustments
by attaching it to the plug at the lower part of the seat.
• Connect the crank handle to the manual backup plug.
• Then, turn the crank handle counterclockwise to lift the seat and
clockwise to lower the seat.
The manual longitudinal backup handle allows aft and fore adjustments.
• Push the manual longitudinal backup handle to unlock the seat
and enable longitudinal movement.
• Adjust the seat position as required. Then, release the handle in
the desired position.
Lateral movement is provided actuating both lateral locking pins.
• Push the pins to unlock the seat and enable lateral movement. • Adjust the seat position as required. Then, release the pins to
lock the seat in the desired position.
BACKUP OPERATION OF THE PILOT SEATS
For Longitudinal Movement (Fore/Aft):
• The manual longitudinal backup handle allows aft and fore
adjustments.
• Pull the manual longitudinal backup handle (on the right side of
the seat) to unlock the seat and enable longitudinal movement.
• Adjust the seat position as required.
• R elease manual longitudinal backup handle to neutral position.
For Lateral Movement (Inboard/Outboard):
• Pull both manual pins on front and aft of seat at floor level to
unlock the seat and enable lateral movement when the seat is at the rear stop level.
• Adjust the seat position as required and then release the pins to
lock the seat in the desired position. For Recline (Backrest) Control:
• A spare Backrest Locking System allows manual tilting of the
backrest to the up-right position (fixed 5 degrees from up-right position) in case of failure of the controls or recline actuator.
• Set backrest recline handle to DOWN position (on the left side of
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ATA 25-10
Cockpit/Flight Deck
PILOT SEAT ADJUSTMENT – EYE LOCATOR
Adjust the seat to pilot’s eyes optimum position, moving the seat up or down so that the pilot’s line of sight reaches the same horizontal plane of the black and white balls indicators that are factory adjusted (14 mm from their installation base).
Then, move the seat fore and aft so that the opposite white balls indicator becomes aligned with the black ball indicator.
This position will be the most appropriate for the best control column actuation.
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ATA 25-10
Cockpit/Flight Deck
OBSERVER SEAT
The procedure to use the observer seat is as follows:
• To use the seat, the user (in front of the seat) releases the latch
that holds the seat in the folded position.
• Then rotate counterclockwise to start the procedures to unfold the
seat.
• To reach the other bulkhead bracket, the user continues the
rotating movement until it reaches the bracket on the RH cockpit bulkhead.
• Then start the procedure to unfold the seat bottom, that simply
rotates down and forward.
• The seat backrest is pulled up with both hands until it reaches the
locking points.
• The user may then insert the attaching points into the holes
specially made to hold the backrest in position.
• The seat is then ready for use.
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ATA 25-10
Cockpit/Flight Deck
ATA 25-20 PASSENGER CABIN
DESCRIPTION
The passenger cabin is 274cm (9ft.) wide at shoulder level and 200cm (6ft.7in.) high. The aisle is 48.9cm (19.25in.) wide. The overhead storage compartments are large enough for roll-on bags (61x40x25cm).
The passenger seats are left hand and right hand double configuration, and are 46.3cm (18.25in.) wide. Each seat has a baggage restraint device capable of restraining items 3x12x17cm and weighting 10kg, a life jacket stowage area under the seat and a seat belt.
The passenger cabin is designed to provide spacious and visually attractive accommodation for passengers and flight crew.
PASSENGER CABIN SEATS
The passenger cabin seats provide restraint and protection for passengers.
They are also designed to be attractive, comfortable and to fit in with the rest of the interior design. The flight attendant seats provide restraint and support for the flight attendants and access to required safety and communication equipment while seated.
PASSENGER CABIN CEILING
The passenger cabin ceiling consists of forward, central and aft ceiling panels. The ceiling panels cover the fuselage structure, thermal acoustic insulation, and components of the electrical, air-conditioning and ventilation systems.
PASSENGER CABIN SIDEWALL PANELS
The passenger cabin sidewall panels function as aesthetic barriers between the passenger cabin and the aircraft systems and structure. PASSENGER-CABIN FLOOR FINISH
The passenger-cabin floor finishing provides protection to the floor panels, cushion for the passenger feet, absorption of sound and aesthetically pleasing.
The lavatory floor finishing provides protection to the lavatory floor panel. FLIGHT ATTENDANT PANELS
The flight attendant panels control the functions of the passenger cabin. There are two flight attendant panels installed on the aircraft, one on the forward work area and the other on the aft work area of the passenger cabin.
CLOSETS
The closets provide storage provisions for items carried by the passengers and flight attendants. The closets may also have storage space for emergency equipment.
PARTITIONS
Partitions and curtains are installed to isolate the passenger cabin from the cockpit, galley work areas, and lavatory.
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ATA 25-20
Passenger Cabin
FIGURE 1: PASSENGER CABIN
ATA 25-21 PASSENGER SEATS
DESCRIPTION
The passenger cabin seats are located forward facing throughout the passenger cabin providing minimum legal aisle and unrestricted access to exits. They are attached to seat tracks provided on the floor and sidewalls. The aisle side armrests can be folded up to permit access to the seat by handicapped persons.
The seats in the first row are equipped with armrest-mounted food tables. All other passenger seats are provided with seat back mounted sliding food tables. A back mounted literature pocket is mounted under the table.
The seats are capable of quick release to enable a carry-on stretcher to be brought on board the airplane.
COMPONENTS
The passenger cabin seats comprise the following components:
• Foodtable • Literature pocket • Seat back cushion • Seat bottom cushion • Paper clip
• Armrest
• Baggage restraint bar • Seat belt
• Life vest pouch
OPERATION
SEATBACK:
The seat back recline position is controlled by depressing a control button on the respective armrest and applying force against the back cushion until the desired recline is obtained and then releasing the button. The seat back may be returned to the upright position by removing all force from the back and depressing the recline control button.
ARMREST:
The aisle armrests fold and lock in the down position for normal use. The button just below the armrest when pushed unlatch it and allow it to move up providing space for access to the seat by an individual seated in a wheel chair in the aisle.
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ATA 25-20
Passenger Cabin
FIGURE 2: PASSENGER SEATS
ATA 25-21 FLIGHT ATTENDANT
SEATS
DESCRIPTION
The flight attendant seats are mounted on cabin monuments. The seats and their restraint system are completely self-stowing to avoid interference with emergency evacuation from the passenger cabin.
COMPONENTS
These are the components of the flight attendant seats:
• Headrest • Seat back • Seat bottom
• Restraint system: comprised of a shoulder harness with inertial
reel and a seat belt.
OPERATION
The flight attendant seat is manually deployed by rotating the seat bottom down into position, sitting down and putting on the restraint system. The flight attendant seat stows automatically when the seat occupant releases the restraint system and stands up.
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ATA 25-20
Passenger Cabin
FIGURE 3:FLIGHT ATTENDANT SEAT
ATA 25 -22 PASSENGER CABIN
CEILING
DESCRIPTION
The passenger cabin ceiling consists of FWD (Forward), central and aft ceiling panels. The ceiling panels cover the fuselage structure, thermal acoustic insulation, and components of the electrical, air conditioning and ventilation systems.
COMPONENTS
The passenger cabin ceiling include:
• PSU STRUCTURE • OVERHEAD BIN • PSU’S
• BIN AND PSU TUBES
OPERATION
PASSENGER SERVICE UNIT (PSU)
The LH (Left-Hand) and RH (Right-Hand) PSU structures are comprised of air duct assemblies. The air duct assemblies are comprised of gasper line and air conditioning duct. The LH and RH PSU structures are located above the PSUs. The LH and RH PSU structures are used to mount the PSUs of the passenger compartment.
The PSU is a unit above every passenger seat, providing comfort conditions for the passengers. The PSUs are secured to the PSU structures with latchs. The standard LH and RH PSUs are comprised of a oxygen box, reading lights, air outlet, button of attendant call and loudspeakers.
OVERHEAD BIN
The overhead bins are provided for the stowage of luggage. The overhead bins are located above the passenger seats. The door opens upwards, by spring action, when the latch is actuated.
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ATA 25-20
Passenger Cabin
FIGURE 4: CABIN CEILING
ATA 25-23 SIDEWALL PANELS
DESCRIPTION
The passenger cabin sidewall panels function as aesthetic barriers between the passenger cabin and the aircraft systems and structure. The passenger cabin sidewall panels include:
• SIDEWALL PANELS • DADO PANELS • DOOR SURROUNDS • DOOR LININGS
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ATA 25-20
Passenger Cabin
FIGURE 5:CABIN SIDE AND DADO PANELS
COMPONENTS
SIDEWALL PANELS
The sidewall panels provide:
• An aesthetically appealing interior; • Acoustic dampening;
• Protection for the aircraft structure against passenger contact.
They also incorporate an integral reveal and shade assembly. The window reveal assembly provides an aesthetic transition between the window panel and the structural forging/glass components. Except for the mounting base parts, which are bonded to the composite panel, this assembly can be serviced.
DADO PANELS
The dado panels provide:
• A close-out between the sidewall panel and the aircraft floor. • A path for air to move between the passenger cabin and cargo
compartment in the event of a rapid decompression.
• A method of balancing the airflow for the environmental control
system.
In addition, the dado panels are placed in a decompression chamber to ensure that the air baffle dislodges and provides an air path when the pressure is less than 2.41 kPa (0.35 psig).
DOOR LININGS
The primary intent of the pax and service door linings is:
• To protect the door mechanism.
• To cover and protect the evacuation slide.
• To provide visual indication of slide girt bar arm/disarm.
• To provide a visual indication within the door bustle of the
pressure in the air cylinder.
• To provide a visual indication of door lock and latch.
Each door lining is divided into four panels:
• Main lining • Hinge cover • Lower lining • Bustle
The primary intent of the escape hatch linings is:
• To protect the door mechanism and surrounding structure. • To provide a visual indication of door latched and closed status.
The overwing escape hatch lining consists of:
• Plastic panel • Shroud assembly
• Window reveal and shade assembly
The lower handle is used during evacuation and maintenance. The upper latch cover is quickly opened to expose the latch handle during an emergency evacuation.
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ATA 25-20
Passenger Cabin
FIGURE 6: DOOR LININGS
ATA 25-24 PASSENGER-CABIN
FLOOR FINISH
DESCRIPTION
The passenger-cabin floor finishing is installed on the floor panels and it is divided into carpet and floor mats. Both are sealed in their periphery and in the region of contact with the monuments to prevent moisture intrusion to the structure and consequent corrosion processes.
A monument can be a galley, lavatory, closet or partition.
The lavatory floor finishing has a filler panel and a floor pan installed on the lavatory floor panel to protect the aircraft structure against liquids eventually spilled in the lavatory.
COMPONENTS
PASSENGER-CABIN FLOOR FINISHING
The passenger-cabin floor finishing is composed of segments of carpet and floor mat. Carpet is used on the aisle and in the LH (Left-Hand) and RH (Right-Hand) areas under the passenger seats. Floor mats are used in the entry and service areas.
Each finishing carpet and floor mat segments are cutout to fit the area to which it is installed. In the intersection of the carpet and floor mat there are thresholds.
LAVATORY FLOOR FINISHING
The lavatory floor finishing is composed of a filler panel and a floor pan. The filler panel is a Nomex honeycomb plate attached to the lavatory structure by means of screws. The floor pan is an integral part made of gray plastic which fits to the inner side of the lavatory. In the intersection of the lavatory and floor mat there is a lavatory threshold.
Training Information Points
In the removal/installation procedures, be careful to use a polyethylene spatula to remove all remaining sealant around the floor mats and clean the panel surfaces to remove grease, dirt, oil, or other contamination. The procedure of the sealant application must be done with care to prevent any infiltration.
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ATA 25-20
Passenger Cabin
FIGURE 7:PASSENGER-CABIN FLOOR FINISH
PANEL
DESCRIPTION
The following systems are related to the flight attendant panels:
• TEMPERATURE CONTROL
• PSU TEST (Passenger System Unit) • LAVATORY SMOKE DETECTION SYSTEM • CABIN LIGHTS
• ATTENDANT CALL INDICATORS • COURTESY LIGHTS
• EMERGENCY LIGHTING • POTABLE WATER SYSTEM • VACCUM WASTE SYSTEM
OPERATION
Some functions can be controlled either through the FWD f light attendant panel or the AFT flight attendant panel. These are:
• Temperature Setting: An analog potentiometer adjusts
continuously the temperature of different areas of the passenger cabin. The LED (Light-Emitting Diode) ENABLED next to the cabin temperature button shows the status of the cabin temperature control.
• Emergency Light: The button ON/ARMED turns on the
emergency lights. To prevent unintentional operation, the button is protected with a switch guard. The button TEST tests the
• Courtesy Light: A switch toggles the operating mode of the
courtesy lights between AUTO and OFF. The RESET button resets the operating mode.
• Galley Master: The button OFF turns the galley master off. To
prevent unintentional operation, the button is protected with a switch guard. The LED next to the button is on if the galley master is off.
• Panel Lights: The button TEST tests the panel lights. • Attendant Call: The button RESET resets the attendant call. • Cabin Lighting: The buttons ON and BRIGHT/DIM turn on/off and
regulate the intensity of the ceiling lights, sidewall lights, FWD or AFT entrance light and FW D galley area light. LEDs next to the buttons show the present status (ON, BRIGHT and DIM) of each group of lights.
Some functions can only be controlled through the FWD flight attendant panel. These are:
• Lavatory Smoke Test: This button tests the smoke detector
system installed in the lavatory.
• PSU: The buttons TEST and RESET test and reset the
passenger reading lights, attendant call indicators, zonal attendant-call lights, lavatory dome lights and lavatory occupied signs.
Some functions can only be controlled through the AFT flight attendant panel. These are:
• Waste System: 5 LEDs show the status of the waste system:
lavatory fault, tank full, service tank and fault.
• Water System: 6 LEDs show the status of the water system: fault
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ATA 25-20
ATA 25-20
Passenger Cabin
Passenger Cabin
FIGURE 8: FLIGHT ATTENDANT PANEL
DESCRIPTION
DESCRIPTION
The closets provide storage provisions for items carried by the The closets provide storage provisions for items carried by the passengers and flight attendants. The closets may also have storage passengers and flight attendants. The closets may also have storage space for emergency equipment.
space for emergency equipment.
The closets are used for the stowage of passenger garments, The closets are used for the stowage of passenger garments, miscellaneous items, and some emergency equipment. They are miscellaneous items, and some emergency equipment. They are installed in the work
installed in the work areas to facilitate the work of the fareas to facilitate the work of the f light attendants.light attendants.
COMPONENTS
COMPONENTS
The LH FWD stowage unit is used for storage of garments and The LH FWD stowage unit is used for storage of garments and emergency equipment. On the aft side, it may have
emergency equipment. On the aft side, it may have literature pockets.literature pockets. On the aft side, there are literature pockets. On the FWD side, there is On the aft side, there are literature pockets. On the FWD side, there is one access door to
one access door to compartments in which emergency equipment can becompartments in which emergency equipment can be stowed.
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ATA 25-20
ATA 25-20
Passenger Cabin
Passenger Cabin
FIGURE 9:CLOSETS
FIGURE 9:CLOSETS
DESCRIPTION
DESCRIPTION
The partitions comprise the following: The partitions comprise the following:
•
• COCKPIT COCKPIT BULKHEADBULKHEAD •
• AFT AFT LH LH (Left-Hand) (Left-Hand) WINDSCREENWINDSCREEN •
• AFT AFT RH RH (Right-Hand) (Right-Hand) WINDSCREENWINDSCREEN
As
As applicable applicable to to the the aircraft aircraft configuration, follows configuration, follows others others partitions partitions thatthat can be find into
can be find into the aircraft:the aircraft:
•
• CURTAINS CURTAINS •
• FWD FWD (Forward) (Forward) LH LH WINDSCREENWINDSCREEN •
• FWD FWD RH RH WINDSCREENWINDSCREEN •
• MOVABLE MOVABLE CLASS CLASS DIVIDERDIVIDER •
• CLASS CLASS DIVIDERDIVIDER •
• FIRST FIRST CLASS CLASS WINDSCREENWINDSCREEN
OPERATION
OPERATION
FWD WINDSCREEN
FWD WINDSCREEN
The FWD RH
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ATA 25-20
Passenger Cabin
FIGURE 10: COCKPIT BULKHEAD AND WINDSCREEN
AFT WINDSCREEN
A left hand and right hand windscreen separate the aft galley area from the cabin. The left hand windscreen has a large cutout with a drop down window, so that the cabin crew member seated in the forward facing cabin crew seat is able to see more than 50% of the seated passengers. This window has to be latched during takeoff and landing.
CURTAIN
The curtains are used to separate different areas of the aircraft. The curtains are installed in the curtain tracks with snap carriers.
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ATA 25-20
Passenger Cabin
FIGURE 6:AFT WINDSCREEN AND CURTAIN
ATA 25-30 GALLEY
DESCRIPTION
The galleys are locations where the flight attendants perform their duties and stow miscellaneous items. Their duties include activities such as preparing food and beverage, making flight safety announcements, and controlling the audio entertainment.
The FWD (Forward) galley(s) provide(s) to the flight attendants all the facilities to prepare the in-flight meals and beverages. The FWD galley(s) is (are) located in the FWD work area (between the cockpit and the passenger seats).
The aft galley provides the flight attendants with all facilities to prepare the in-flight meals and beverages. The galley is also used as a place for storage of trolleys and miscellaneous items.
The galley electrical system is comprised of a galley control module designed to provide electrical load to control the operation of the galley inserts.
The major components of the galley electrical system are the galley inserts. They are used by the flight attendants to provide the passengers with meals and beverages. The galley electrical inserts can include ovens and mini-ovens, coffee makers, water boilers, hot jugs and air chillers.
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ATA 25-30
Galley
ATA 25-31 FORWARD GALLEYS
DESCRIPTION
The FWD galleys consist of:
• FWD RH G1 galley; • FWD RH G2 galley.
The FWD galley(s) is (are) equipped with a set of facilities that minimize the flight attendant’s workload. Each one of the galley inserts is controlled by one circuit breaker installed on the galley control module. Each circuit breaker is rated in accordance with the galley inserts current, thus preventing the possibility of an overload condition in the aircraft power system due to an insert failure. The galley lower portion provides sufficient room for the accommodation of the trolley(s) used to serve the meals and beverages to the passengers. The galley(s) also (has) have some compartments used for storing miscellaneous items or emergency equipments.
These pieces of equipment include a coffee maker, a hot jug and a work light to illuminate the sink area. The galley is provided with a sink and a faucet used for cleaning purposes. The galley water system is protected by a manual shutoff valve that can be closed when desired, as in a maintenance situation or in a failure condition. There is a pull-out table to increase the flight attendant work area when desired or needed.
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ATA 25-30
Galley
ATA 25-34 AFT GALLEY
DESCRIPTION
The aft galley is provided with a set of equipment that minimizes the flight attendants’ workload. These pieces of equipment include a hot jug, a coffee maker, two ovens and a work light to illuminate the galley work desk.
An easily accessible AC outlet is installed for maintenance or other purposes that can require a source of electrical power. The galley work desk is provided with a sink and a faucet used for cleaning purposes. The galley water system is protected by a manual shutoff valve that can be closed when desired, as in a maintenance situation or in a failure condition.
Each of the galley inserts is controlled by one circuit breaker installed on the galley control module. Each circuit breaker is rated in accordance with the galley insert current, thus preventing an overload of the aircraft power system due to an insert failure. The galley lower portion provides sufficient room for accommodating the trolleys used to serve meals and beverages to the passengers, and incorporates a door that gives access to the aft avionics compartment. The galley also has some compartments used for storing miscellaneous items.
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ATA 25-30
Galley
ATA 25-36 GALLEY ELECTRICAL
SYSTEM
DESCRIPTION
The galley electrical system is comprised of a galley control module designed to provide electrical load to control the operation of the galley inserts.
The galley control module is installed on the outboard side of the working face of the galley. It consists of circuit breakers to protect the circuitry of the galley inserts and switches to operate them.
OPERATION
The electrical system can be operated when the galley is powered up. This is ensured when the circuit breakers are armed and all the inserts work correctly.
Abnormal operation of the galley electrical system consists of loss of power to any of the inserts due to wiring, electrical hardware or inserts internal fault. The tripping of the circuit breakers might be an indication of such failures. Also, any individual insert not operating can contribute to an abnormal operation.
ATA 25-37 GALLEY INSERTS
DESCRIPTION
The major components of the galley electrical system are the galley inserts. They are used by the flight attendants to provide the passengers with meals and beverages. The galley electrical inserts can include ovens and mini-ovens, coffee makers, water boilers, hot jugs and air chillers. The flight attendants control the galley inserts through the galley control module.
COMPONENTS
HOT JUG
The hot jug has a capacity to hold 7.57 L (2 gal.) of liquid. It does not heat the liquid, it only maintains the temperature of the content. Before the flight, the hot jug must be removed from the galley and f illed with pre-heated beverage, then it is reinstalled in the galley to maintain the temperature of the beverage during the flight.
COFFEE MAKER
The coffee maker is used by the flight attendants to serve freshly brewed coffee, as well as hot and cold water. It is mounted on a mounting rail that supports the electrical connector and the water supply coupling. The coffee maker is capable of brewing 1.6 L (0.42 gal.) of coffee in about 2 min and 45 s. The time delay between the end of one brew cycle and the start of the next is approximately 1 min. This coffee maker is available with an extended, manual faucet/tap.
A heater plate, mounted on the base of the coffee maker, will maintain the brewed coffee above 77 °C (170 °F) for approximately 30 min.
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ATA 25-30
Galley
ATA 25-40 LAVATORY
DESCRIPTION
The lavatories provide facilities for the passengers and for the flight crew to get the minimum hygiene and amenity conditions. The EMBRAER 170 standard configuration has two lavatories - one in the forward area and another in the aft area. The forward left hand lavatory is located just aft of the left hand flight deck bulkhead. The aft lavatory is located just aft of the aft passenger door.
FORWARD LAVATORY
The FWD lavatory is accessed by means of one hinged door that is locked by a latch.
The perimeter of the aft lavatory is sealed to avoid the contamination of the other parts of the aircraft with water.
Access to the lavatory is facilitated by a door threshold attached to the floor panel. In an emergency situation, when an occupant cannot open the lavatory door from inside, the slide latch cover outside the lavatory door can be lifted up to give access to the lavatory door latch to unlock the door.
The FWD lavatory comprises these components:
• Mirror above sink • Faucet
• Soap dispenser • Sink
• Waste compartment door to give access to the waste
compartment
• Service door
• Exhaust air to renew the air of the interior of the lavatory • Toilet with toilet shroud
• Amenity door/box • Toilet roll holder
• Cold air duct to supply cold air to the interior of the lavatory • Towel paper door
• Assist handles • Ashtray • Corner lamp • Smoke detector • Loudspeaker • Oxygen box AFT LAVATORY
The aft lavatory is similar in construction and in operation to the forward one, the location is different.
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ATA 25-40
Lavatory
ATA 25-60 EMERGENCY EQUIPMENT
DESCRIPTION
This subsystem includes the equipment aimed at assisting the crew members and passengers in the event of an emergency condition. The emergency equipment comprises individual safety devices for the flight crew and passengers. These items of equipment are installed in a manner that they can be quickly accessed, without putting persons at risk or causing damage to the aircraft systems during in-flight emergency conditions. There are placards to indicate their locations.
EMERGENCY LOCATOR TRANSMITTER SYSTEM
The function of the ELT (Emergency Locator Transmitter) is to make the aircraft search and rescue operations easier, facilitating aircraft location. The ELT provides automatic transmission of the standard swept tone and encoded digital message sent to a satellite (COSPAS & SARSAT (Search and Rescue Satellite-Aided Tracking)) in the event of a crash. The emergency locator transmitter sub-subsystem transmits signals through emergency frequencies of 121.5 MHz, 243.0 MHz and 406.025 MHz.
EMERGENCY-EVACUATION SLIDE SYSTEM
The emergency-evacuation slide system makes it possible for the passengers and crew members to safely leave the aircraft during an emergency evacuation.
LIFE RAFTS SYSTEM
The life raft system is designed to provide a safe and reliable flotation system for up to 36 persons in the event of ditching.
In the cockpit, the emergency equipment comprises life vests for the crew members, located on the back of each pilot and copilot seat. Escape ropes are installed just above each direct-vision window. The escape ropes allow the evacuation of the cockpit crew through the window. A crash axe is also available.
In the passenger cabin, the emergency equipment comprises megaphones, crew and passenger life vests, seat belt extensions, a wheelchair, and a defibrillator.
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ATA 25-60
Emergency Equipment
ATA 25-61 EMERGENCY LOCATOR
TRANSMITTER SYSTEM
DESCRIPTION
The ELT transmits the standard emergency swept tone on 121.5 and 243.0 MHz and the aircraft identification code or serial number of the transmitter, country code and the ID code on the 406.025 MHz.
The 406.025 MHz transmitter transmits for 24 hours every 50 seconds for 520 ms and then is automatically shut down and has an average error of 1 to 2 km.
The 121.5 MHz/243.0 MHz transmitter transmits continuously until the battery is drained which takes approximately 72 hours, and has an error of 15 to 20 km.
The information sent to the satellite is programmed at the factory and contains a unique number that can be used to identify the beacon. ELT/NAV (Navigation) Interface Unit (new)
When the ELT is coupled to an ELT/NAV interface unit, it also will transmit the position coordinates (longitude and latitude) of the aircraft in the encoded digital message, in the event of a crash. This results in a better accuracy of the position, which is approximately 100 m.
The ELT/NAV interface unit will also be able to automatically reprogram the ELT with the aircraft 24-bit address in the event of an ELT replacement. One of the connectors of the ELT/NAV interface unit is wired, according to the aircraft 24-bit address.
Upon power-up, the ELT/NAV interface unit reads the ELT's 24-bit address data and compares it to the 24-bit address data hardwired to the ELT/NAV interface unit. If there is a difference, the ELT/NAV interface unit reprograms the ELT according to the connector straps. If the two sets of data are identical, no action is taken.
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ATA 25-60
Emergency Equipment
ELT TRANSMITTER UNIT
The transmitter unit is housed in a high impact fire resistant polycarbonate plastic case, which is installed in the aft avionics compartment and it has the internal components that follow:
• G-Switch • Transmitter • Microprocessor • Miscellaneous components • “ON” light • Battery
The transmitter is an electronic circuit which transmits RF (Radio Frequency) signals on the frequencies of 121.5 MHz, 243.0 MHz and 406.025 MHz.
ELT SWITCH
The ELT unit has an ON/OFF switch which has the f unctions that follow: Emergency Locator Transmitter System-ELT-ON/OFF Switch
• ON – The transmitter starts its operation manually
• OFF - The unit is OFF but it can start operation automatically
through the G-Switch operation ELT REMOTE SWITCH PANEL
The ELT remote switch panel is located on the main instrument panel, in the cockpit. It has an ON/ARM switch and a red LED (Light-Emitting Diode) which indicates if the ELT is activated or not activated. The ON/ARM switch has the following functions:
• ON - The transmitter starts its operation manually • ARM - It is the normal position for an automatic operation
ELT ANTENNA
The ELT antenna is a blade antenna installed on the top of the center fuselage III.
ELT BATTERY
The battery pack for the ELT consist of 4 “D” size lithium manganese dioxide cells connected in series. The expiration date of the battery is printed on the label attached to the unit. T he battery pack expires 5 years from the date (month) it is shipped from ELTA. The battery pack must be replaced with a new one in the following cases:
• After use in an emergency.
• After an inadvertent activation of unknown duration.
• When the total of all known transmissions exceeds one hour. • On or before the battery replacement (expiration) date.
ELT BUZZER
The ELT buzzer is located next to the ELT unit, in the aft avionics compartment. It is fed by the ELT and therefore is not dependent upon the aircraft battery for operation. The ELT buzzer provides an aural sound to alert the pilot when the ELT has been activated and is transmitting. Its signal is loud enough to be heard outside the aircraft when the engines are off. It enables a search and rescue team to easily locate an aircraft with a transmitting ELT in a confined area with a large number of aircraft (i.e. such as an airport) so that they can disable the offending ELT without a great deal of effort.
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ATA 25-60
Emergency Equipment
The ELT/NAV interface unit is also installed next to the ELT unit, in the aft avionics compartment.
The ELT/NAV interface unit gives to the ELT the capability of interfacing with the aircraft navigation system.
It receives the position coordinates from the GPS (Global Positioning System) 1 receiver module through the generic I/O (Input/Output) module, both installed in the MAU (Modular Avionics Unit) 1, and send this information to the ELT.
In the event of a crash, the ELT will transmit the position information from the navigation system. The crash site is instantly known due to the aircraft navigation system position data communication with the ELT via ELT/NAV interface unit. Without this interface, in the worst case, the time to locate the aircraft could take until 3 or 4 hours. In addition, the accuracy of the position fix is better than a system which does not use this interface (i.e. 100 m versus 1 or 2 km).
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ATA 25-60
Emergency Equipment
OPERATION
The ELT signals transmitted on 121.5 and 243.0 MHz are modulated in AM. They are designated with the carrier amplitude modulated with an audio frequency sweeping downward over a range of not less than 700 Hz, within the range of 1600 to 300 Hz. The sweep repetition rate is between 2 and 4 Hz with a modulation factor of at least 0.85.
The ELT signal transmitted in 406.025 MHz is a digital information message. The modulation is phase modulated and classified as 16K0G1D.Every 47.5 to 52.5 seconds the 5 W transmitter is turned on for 440 ms (short message) or 520 ms (short message).
The transmitter has a G-Switch that senses the aircraft longitudinal deceleration. The G-Switch shall activate the ELT in accordance with the requirements as depicted in the response curve of the G-Switch.
Two criteria govern the performance of the G-Switch sensor:
• A threshold force level (G th) below which the G-Switch sensor
will not respond.
• A minimum velocity change (V min) before the G-Switch sensor
will activate.
The ELT can be operated either manually or automatically.
Under normal conditions, the ON/ARM switch of the ELT remote switch panel is in the ARM position and the ON/OFF switch of the ELT unit is in the OFF position. Upon impact (a change velocity of 4.5 +/- 0.5 ft/s or if subjected to 30 G’s of cross axis forces) the G-Switch will automatically activate, activating the ELT. The LED, in the ELT remote switch panel, will continuously flash and the swept tone will be audible.
For manual operation, the ON/OFF switch of the ELT unit or the ON/ARM switch of the ELT remote switch panel must be at the ON position. These switches can also be used to do the test of the ELT, which must be
performed within the first five minutes after the hour UTC (Universal Time Coordinated) and cannot exceed 30 seconds. After approximately 47 seconds the satellite system will consider the transmission as a valid distress signal. If the ELT is activated accidentally, it can be reset through the ON/ARM switch. The resetting is done when the switch is set to the ON position and then immediately set again to the ARM position. It is also possible to reset the ELT at the unit itself by positioning the ON/OFF switch on the ELT unit to ON position, then immediately back down to the OFF position. The ELT cannot be reset if either the ON/ARM switch of the ELT remote switch panel or the ON/OFF switch of the ELT unit is in the ON position.
The DC ESS BUS 2 supplies power for the LED of the ELT remote switch panel.
The status of the ELT, active or not active, is indicated on the ELT remote switch panel. When the ELT is active, a continuous flashing light will be present on the ELT remote switch panel. If a problem is detected, the light provides a coded signal following the initial 1-second pulse. The coded signal and related problems are as follows:
• 1 flash indicates a G-Switch loop open failure.
• 3 flashes indicates a 406.025 MHz transmitter problem. • 5 flashes indicates there is no navigation data present. • 7 flashes indicates a battery problem.
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ATA 25-60
Emergency Equipment
ATA 25-62
EMERGENCY-EVACUATION SLIDE SYSTEM
DESCRIPTION
The emergency-evacuation slide system makes it possible for the passengers and crew members to safely leave the aircraft during an emergency evacuation. This system consists of inflatable slide units packed on each of the four exit doors of the aircraft.
COMPONENTS
SLIDE ASSEMBLY
The slide assembly contains the inflatable portion of the system and other components necessary for the system to operate. The major components of the slide assembly are described below:
• Inflatable assembly: it consists in an inflatable tube structure that
forms the slide upon inflation.
• Girt assembly: it provides the attachment of the slide to the
aircraft. The status of the girt bar is indicated at each door, with one visual indicator, located near the lower corner of the decorative bustle. When the door slide system is not armed, there is no color shown on the visual indicator. When the door slide system is armed, a red color indication shows on the visual indicator.
When the door slide system is not armed, the lower indicator window and the top indicator window are green. When the door slide system is armed, the lower viewing window shows two indicators with aligned red lines and the top viewing window shows an armed indication.
• Slide surface assembly: it provides the sliding surface that
controls the path of the evacuees.
• Lifeline: it goes along the forward and aft main slide tubes. It is
colored red to contrast with the color of the inflatable assembly. It is used in the event of a ditching and provides evacuees with something to hold on to while in the water.
• Pressure relief valve: it is used to control the inflation pressure
inside the slide during and after the inflation process.
• Manual inflation handle: it is used after the evacuation slide
deploys from the door but the inflation system does not fire automatically.
SLIDE LIGHTING SYSTEM
The slide lighting system provides illumination in the area where evacuees touch the ground and along the sliding lane. The slide lighting system is described below:
• Battery: it supplies electrical power to the slide lighting system
through a series array of four AA alkaline cells, and operates well in temperatures ranging from -40 °C (-40 °F) to 71 °C (160 °F).
• Lights harness: they are LED (Light-Emitting Diode)s
encapsulated in a transparent housing installed on the slide structure. These lights are positioned so as to give a good visibility in any condition.
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ATA 25-60
Emergency Equipment
The inflation system is actuated automatically when the packed slide is ejected out of the aircraft exit door. The inflation system is described below:
• High-pressure cylinder: it supplies high-pressure gas to the
aspirators which then aspirate ambient air (secondary flow) along with stored gas from the cylinder (primary flow) to inflate the slides.
• Regulator: it is used to reduce the pressure in the high-pressure
cylinder to the inlet pressure required by the aspirator. The regulator contains a pressure gauge with a green GO and red NO GO indication. The indicator is used by the flight attendant to check if the inflation cylinder is ready.
• Hose: it delivers the high-pressure gas from the regulator to the
aspirator.
• Aspirator: it is an air pump that aspirates ambient air using high
pressure gas energy. The aspirator is equipped with a one-way check valve to prevent gas in the slide from leaking through the hose inlet port.
PACKBOARD PLATE
The packboard plate is used to retain the slide in the packed state. It contains the following components:
• Packboard: it consists of a composite flat plate and attachment
hardware. There are three attachment points to fasten the slide assembly to the door structure, two at the bottom and one at the top of the packboard.
• Soft cover: it is a fabric component that restrains the packed slide
onto the packboard. The soft cover is used to compress the slide into the required envelope and hold it there.
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ATA 25-60
Emergency Equipment
OPERATION
The emergency-evacuation slide system is armed or disarmed by moving the arm/disarm handle located on the door to the appropriate position. When the arm/disarm handle is moved to the armed position, the girt bar engages to the floor fittings. When the arm/disarm handle is moved to the unarmed position, the girt bar disengages from the floor fittings.
EMERGENCY EVACUATION CONDITION
With the emergency-evacuation slide system armed:
• The exit door pulls the primary release cable and pin when it is
opened. This causes the slide pack to drop from the packboard.
• As the slide pack drops a preset distance, the firing cable pulls
the firing pin from the regulator assembly to release the high pressure gas from the cylinder.
• The high pressure gas flows through the hose assembly to the
aspirator and inflates the slide.
• The pressure relief valve opens at a preset pressure to maintain
the correct inflation pressure of the inflation tubes.
• When fully inflated, the slide is ready to be used for aircraft
evacuation.
The emergency-evacuation slide system can operate in an abnormal mode as follows:
• In case the inflation system does not actuate automatically, the
flight attendant or another person has to pull the manual inflation handle.
• The manual inflation handle activates the inflation system and
fully inflates the slide.
If the evacuation slide is damaged, punctured or torn, which makes it unable to hold air and inflate properly; it can be used as a non inflatable device, provided there is ground personnel assistance.
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ATA 25-60
Emergency Equipment
ATA 25-66 LIFE RAFTS SYSTEM
DESCRIPTION
The life raft system is designed to provide a safe and reliable flotation system for up to 36 persons in the event of ditching.
The life raft system consists of a life raft assembly, inflation system, survival kit including canopy, and a carrying case in which all components are packed.
The life raft incorporates means for manual deployment and inflation.
COMPONENTS
LIFE RAFT ASSEMBLY
The life raft assembly consists of two structurally joined, independent, hexagonal shaped, inflatable tubes that are fully reversible. A no inflatable fabric floor, attached and suspended between the tubes, incorporates a manually inflatable deck float at the centre for additional buoyancy. Boarding handles and boarding ladders are located at each end of the life raft to enable survivors to climb aboard.
A mooring line is provided to attach the life raft to the fuselage to prevent the life raft from blowing away from survivors as they are boarding. A floating knife can be used to cut the mooring line and life raft loose from the aircraft if the aircraft is sinking or on fire. Outside lifelines are provided to help survivors to grasp from the water. A heaving ring and line is provided as a rescue aid that can be thrown to survivors in the water who are unable to reach the life raft. A sea anchor is used to control the drift rate and orientation of the life raft from the water. Two locator lights provide aid in locating the life raft at night. The lights are operated by water-activated batteries stored in pockets, one on the
topside and one on the underside of the life raft. The lights are installed in light holders attached to the tubes opposite the battery pockets. INFLATION SYSTEM
The inflation system consists of one 300 in3reservoir charged with a
mixture of CO2and N2to enhance raft inflation/round-out performance. Air
aspirators are utilized to combine stored gas with outside air to minimize reservoir size while still meeting tube operating pressure requirements. SURVIVAL KIT
The survival kit consists of first aid equipment, tube repair kit, hand pump with adapter and signalling devices such as flashlight and flares. A lightweight, bright orange canopy is packed in the survival kit to provide protection against environmental conditions and a high degree of visibility in the water.
CARRYING CASE
The carrying case provides protection to the packed life raft, survival kit and components. The carrying case has a window to view the pressure gage on the reservoir and valve assembly and monitor the gas charge pressure in the bottle. There are handles on the outside of the case to provide easy installation, removal and transporting of the packed life raft. An inflation pocket is located on the front right side of the case for stowing the mooring line. Lacing strips are located on the top and bottom of the case to compress the packed life raft to pack
Page 18
ATA 25-60
Emergency Equipment
ATA 25-80 INSULATION
DESCRIPTION
The insulation is composed of cockpit/passenger cabin insulation system, sound dampener system, and noise treatment felt system. The insulation is installed to help stabilize the air temperature and reduce the noise levels in the aircraft.
The INSULATION includes these subsystems:
• COCKPIT/PASSENGER CABIN INSULATION SYSTEM • SOUND DAMPENER SYSTEM
• NOISE TREATMENT FELT SYSTEM • SMOKE SEAL SYSTEM