AMET Ltd
B737 NG SERIES
REFRESHER COURSE
B737 NG
GEN FAM
REFRESHER COURSE
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CONTENTS
ATA 00 – GEN FAM
GEN FAM ................................................................................................................................................................................................................................................................ 8
-800 STRUCTURE DIMENSIONS ..................................................................................................................................................................................................................... 10
GENERAL ............................................................................................................................................................................................................................................................. 10
-700 STRUCTURE DIMENSIONS ..................................................................................................................................................................................................................... 12
GENERAL ............................................................................................................................................................................................................................................................. 12
TURNING RADIUS................................................................................................................................................................................................................................................. 12
FUSELAGE DIMENSIONS ................................................................................................................................................................................................................................. 14
GENERAL ............................................................................................................................................................................................................................................................. 14
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 14
WINGLETS ........................................................................................................................................................................................................................................................... 16
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 16
POWERPLANT ENGINE HAZARDS ............................................................................................................................................................................................................... 18
GENERAL ............................................................................................................................................................................................................................................................. 18
INLET SUCTION .................................................................................................................................................................................................................................................... 18
EXHAUST HEAT ................................................................................................................................................................................................................................................... 18
EXHAUST VELOCITY ............................................................................................................................................................................................................................................ 18
ENGINE NOISE ..................................................................................................................................................................................................................................................... 18
ENGINE ENTRY/EXIT CORRIDOR.......................................................................................................................................................................................................................... 18
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 18
ANTENNA LOCATIONS .................................................................................................................................................................................................................................... 20
ANTENNA LOCATIONS ......................................................................................................................................................................................................................................... 20
FLIGHT COMPARTMENT PANELS ............................................................................................................................................................................................................... 22
GENERAL ............................................................................................................................................................................................................................................................. 22
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MAIN INSTRUMENT PANEL ........................................................................................................................................................................................................................... 24
GENERAL ............................................................................................................................................................................................................................................................. 24
FUNCTIONAL DESCRIPTION.................................................................................................................................................................................................................................. 24
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 24
P7 GLARESHIELD PANEL ................................................................................................................................................................................................................................ 26
GENERAL ............................................................................................................................................................................................................................................................. 26
P2 CENTER INSTRUMENT AND P9 FORWARD ELECTRONICS ........................................................................................................................................................... 28
PANEL ................................................................................................................................................................................................................................................................... 28
GENERAL ............................................................................................................................................................................................................................................................. 28
CONTROL STAND .............................................................................................................................................................................................................................................. 30
GENERAL ............................................................................................................................................................................................................................................................. 30
P8 AFT ELECTRONICS PANEL ....................................................................................................................................................................................................................... 32
GENERAL ............................................................................................................................................................................................................................................................. 32
P5 AFT OVERHEAD PANEL ............................................................................................................................................................................................................................. 34
GENERAL ............................................................................................................................................................................................................................................................. 34
P5 FORWARD OVERHEAD PANEL ................................................................................................................................................................................................................ 36
GENERAL ............................................................................................................................................................................................................................................................. 36
AFT FLIGHT COMPARTMENT PANELS ...................................................................................................................................................................................................... 38
GENERAL ............................................................................................................................................................................................................................................................. 38
LOADABLE SOFTWARE ................................................................................................................................................................................................................................... 40
GENERAL ............................................................................................................................................................................................................................................................. 40
SYSTEMS .............................................................................................................................................................................................................................................................. 40
LOADABLE SOFTWARE BINDER ........................................................................................................................................................................................................................... 40
LOCATION OF JUNCTION BOXES ................................................................................................................................................................................................................ 42
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 42
ELECTRONIC EQUIPMENT COMPARTMENT ........................................................................................................................................................................................... 44
GENERAL ............................................................................................................................................................................................................................................................. 44
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ELECTRONIC EQUIPMENT RACKS E1, E8 ................................................................................................................................................................................................. 46
E1 RACK .............................................................................................................................................................................................................................................................. 46
E8 RACK .............................................................................................................................................................................................................................................................. 46
PROGRAM SWITCH MODULES .............................................................................................................................................................................................................................. 46
ELECTRONICS EQUIPMENT RACKS E2, E3, & E4 .................................................................................................................................................................................... 48
GENERAL ............................................................................................................................................................................................................................................................. 48
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 48
ELECTRONIC EQUIPMENT RACK E5 .......................................................................................................................................................................................................... 50
GENERAL ............................................................................................................................................................................................................................................................. 50
ELECTRONIC EQUIPMENT RACK E6 .......................................................................................................................................................................................................... 52
GENERAL ............................................................................................................................................................................................................................................................. 52
PASSENGER COMPARTMENT - PASSENGER SERVICE UNITS ............................................................................................................................................................ 54
PURPOSE .............................................................................................................................................................................................................................................................. 54
PHYSICAL DESCRIPTION/LOCATION .................................................................................................................................................................................................................... 54
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 54
EXTERIOR LIGHTING ...................................................................................................................................................................................................................................... 56
PURPOSE .............................................................................................................................................................................................................................................................. 56
LANDING LIGHTS .............................................................................................................................................................................................................................................. 58
PURPOSE .............................................................................................................................................................................................................................................................. 58
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 58
LOCATION ............................................................................................................................................................................................................................................................ 58
EMERGENCY LIGHTING ................................................................................................................................................................................................................................. 60
POWER SUPPLIES ................................................................................................................................................................................................................................................. 60
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 60
LOCATION ............................................................................................................................................................................................................................................................ 60
EMERGENCY LIGHTING - FUNCTIONAL DESCRIPTION ...................................................................................................................................................................... 62
OPERATION .......................................................................................................................................................................................................................................................... 62
FUNCTIONAL DESCRIPTION.................................................................................................................................................................................................................................. 62
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 62
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FLIGHT CREW OXYGEN ................................................................................................................................................................................................................................. 64
PURPOSE .............................................................................................................................................................................................................................................................. 64
SYSTEM PLUMBING .............................................................................................................................................................................................................................................. 64
SHUTOFF VALVE .................................................................................................................................................................................................................................................. 64
PRESSURE INDICATION ........................................................................................................................................................................................................................................ 64
OVERPRESSURE DISCHARGE AND INDICATION .................................................................................................................................................................................................... 64
FLIGHT CREW COMMUNICATIONS SYSTEMS........................................................................................................................................................................................................ 64
FLIGHT CREW ORONASAL MASK ......................................................................................................................................................................................................................... 64
FLIGHT CREW OXYGEN - OXYGEN CYLINDER ...................................................................................................................................................................................... 66
PURPOSE .............................................................................................................................................................................................................................................................. 66
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 66
LOCATION ............................................................................................................................................................................................................................................................ 66
PASSENGER OXYGEN - OXYGEN GENERATOR ....................................................................................................................................................................................... 68
PURPOSE .............................................................................................................................................................................................................................................................. 68
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 68
LOCATION ............................................................................................................................................................................................................................................................ 68
POTABLE WATER - FUNCTIONAL DESCRIPTION ................................................................................................................................................................................... 70
FUNCTIONAL DESCRIPTION.................................................................................................................................................................................................................................. 70
LOCATION ............................................................................................................................................................................................................................................................ 70
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 70
WATER TANK PRESSURIZATION ................................................................................................................................................................................................................. 72
PURPOSE .............................................................................................................................................................................................................................................................. 72
GENERAL ............................................................................................................................................................................................................................................................. 72
LOCATION ............................................................................................................................................................................................................................................................ 72
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 72
PASSENGER WATER - WATER HEATER ..................................................................................................................................................................................................... 74
PURPOSE .............................................................................................................................................................................................................................................................. 74
LOCATION ............................................................................................................................................................................................................................................................ 74
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 74
FUNCTIONAL DESCRIPTION.................................................................................................................................................................................................................................. 74
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VACUUM WASTE - FUNCTIONAL DESCRIPTION .................................................................................................................................................................................... 76
VACUUM TOILET ASSEMBLIES ............................................................................................................................................................................................................................ 76
WASTE TANK ASSEMBLY .................................................................................................................................................................................................................................... 76
INTERFACES ......................................................................................................................................................................................................................................................... 76
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 76
VACUUM TOILET ASSEMBLY ....................................................................................................................................................................................................................... 78
PURPOSE .............................................................................................................................................................................................................................................................. 78
LOCATION ............................................................................................................................................................................................................................................................ 78
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 78
FUNCTIONAL DESCRIPTION............................................................................................................................................................................ ERROR! BOOKMARK NOT DEFINED.
WASTE TANK QUANTITY INDICATION ...................................................................................................................................................................................................... 80
GENERAL ............................................................................................................................................................................................................................................................. 80
AFT ATTENDANT PANEL WASTE QUANTITY INDICATION ................................................................................................................................................................................... 80
PURPOSE .............................................................................................................................................................................................................................................................. 80
LOCATION ............................................................................................................................................................................................................................................................ 80
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 80
OPERATION .................................................................................................................................................................................................... ERROR! BOOKMARK NOT DEFINED.
VACUUM WASTE - COMPONENT LOCATIONS - AFT CARGO COMPARTMENT ............................................................................................................................ 82
LOCATION ............................................................................................................................................................................................................................................................ 82
MAINTENANCE DOCUMENTS – INTRODUCTION ................................................................................................................................................................................... 84
GENERAL ............................................................................................................................................................................................................................................................. 84
SCHEDULED MAINTENANCE ................................................................................................................................................................................................................................ 84
UNSCHEDULED MAINTENANCE ........................................................................................................................................................................................................................... 84
MAINTENANCE PLANNING DOCUMENT ............................................................................................................................................................................................................... 84
AIRPLANE MAINTENANCE MANUAL .................................................................................................................................................................................................................... 84
SYSTEM SCHEMATICS MANUAL........................................................................................................................................................................................................................... 86
WIRING DIAGRAM MANUAL ................................................................................................................................................................................................................................ 86
ILLUSTRATED PARTS CATALOGUE ....................................................................................................................................................................................................................... 86
STANDARD WIRING PRACTICES MANUAL ........................................................................................................................................................................................................... 86
FAULT REPORTING MANUAL ............................................................................................................................................................................................................................... 86
FAULT ISOLATION MANUAL ................................................................................................................................................................................................................................ 86
STRUCTURAL REPAIR MANUAL ........................................................................................................................................................................................................................... 86
MECHANICAL DISPATCH MANUAL ...................................................................................................................................................................................................................... 86
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DISPATCH DEVIATION PROCEDURES GUIDE .......................................................................................................................................................................................... 88
GENERAL ............................................................................................................................................................................................................................................................. 88
INTRODUCTION .................................................................................................................................................................................................................................................... 88
MINIMUM EQUIPMENT LIST ITEMS ...................................................................................................................................................................................................................... 88
CONFIGURATION DEVIATION LIST ITEMS ............................................................................................................................................................................................................ 90
FERRY ITEMS ....................................................................................................................................................................................................................................................... 90
MISCELLANEOUS ITEMS....................................................................................................................................................................................................................................... 90
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 90
FAULT ISOLATION MANUAL ......................................................................................................................................................................................................................... 92
GENERAL ............................................................................................................................................................................................................................................................. 92
FIM INTRODUCTION ............................................................................................................................................................................................................................................ 92
FIM CHAPTER SUBJECTS ..................................................................................................................................................................................................................................... 92
- MAINTENANCE MESSAGE INDEX ........................................................................................................................................................................................................................ 92
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 92
AIRPLANE MAINTENANCE MANUAL - AMM PART I ............................................................................................................................................................................. 94
GENERAL ............................................................................................................................................................................................................................................................. 94
PURPOSE .............................................................................................................................................................................................................................................................. 94
ORGANIZATION .................................................................................................................................................................................................................................................... 94
DIVISIONS ............................................................................................................................................................................................................................................................ 94
AIRPLANE MAINTENANCE MANUAL - AMM PART II ............................................................................................................................................................................ 96
GENERAL ............................................................................................................................................................................................................................................................. 96
CHAPTER NUMBERING SYSTEM ........................................................................................................................................................................................................................... 96
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 96
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ATA 00-00-00
GEN FAM
The 737-6/7/800 is a two engine airplane. It is for short to medium range
flights with a capacity of up to 189 passengers. The Delta Air Lines
configuration has a capacity of 154 passengers, with 16 in first class and
138 in coach class.
The Next Generation 737-6/7/800 aircraft has many new features. These
new features increase the airplane payload, service ceiling, and range.
The airplane has a design max range of 2,900 nautical miles.
- Zero fuel weight - 136,000 lbs.
- Max. Landing weight - 144,000 lbs.
- Max. Takeoff weight - 172,500 lbs.
- Max. Taxi weight - 173,000 lbs.
- Total useable fuel - 45,275 lbs.
- Service ceiling - 41,000 ft.
Turning Radius 737-800
- Outer wing Arc - 47.9 yds (143.7 ft)
- Minimum pavement for a 180 degree turn - 25.7 yds (77 ft)
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Figure 1
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-800 STRUCTURE DIMENSIONS
General
These are the structure dimensions of the B-737-800 airplane:
- Length; 129 feet 6 inches
- Wing span; 112 feet 7 inches (117 feet 2 inches with winglets)
- Tail height; 41 feet 2 inches
- Horizontal stabilizer span; 47 feet 1 inch
- Top of fuselage 18 feet
- Bottom of passenger doors 9 feet
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Figure 2
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-700 STRUCTURE DIMENSIONS
General
These are the structure dimensions of the 737-700 airplane:
- Length; 110 feet 4 inches, 33.69meters
- Wing span; 117 feet 2 inches, 35.7 meters (with winglets)
- Tail height; 41 feet 2 inches, 12.5 meters
- Horizontal stabilizer span; 47 feet 1 inch, 14.4 meters
- Top of fuselage 18 feet, 6 meters
- Bottom of passenger doors 9 feet, 3 meters
Turning Radius
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Figure 3
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FUSELAGE DIMENSIONS
General
Dimensions give locations on the fuselage. The scale for each dimension
is inches.
You use these dimensions to find components on the fuselage:
- Body station line
- Body buttock line
- Water line
The body Station line (STA) is a horizontal dimension. It starts at station
line zero. You measure the body station line from a vertical reference
plane that is forward of the airplane.
The Buttock Line (BL) is a lateral dimension. You measure the buttock line
to the left or right of the airplane centre line.
The Water Line (WL) is a height dimension. You measure the water line
from a horizontal reference plane below the airplane.
Training Information Point
A stretch section was added to the fuselage at station 500 and at station
727.
The station numbers in these stretch sections have a letter after the
number.
The fuselage plugs on the -800 aircraft are 198in at station 500 and 212in
at station 727.
The fuselage plugs on the -700 aircraft are 88in at station 500 and 90in at
station 727.
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Figure 4
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WINGLETS
General Description
The upper and lower skin panels of the winglets are made of composite
fibreglass/graphite/epoxy honeycomb material with an aluminium leading
edge and aluminium ribs. The winglet has anti-collision lights and forward
and aft position lights.
An access panel on the bottom of the winglet gives access to the electrical
connectors from the wing and the electrical connectors inside the winglet
for the anti-collision lights and forward position lights. Access for the aft
position light is in the winglet aft canoe.
Older winglets have a single lens and a single mount bracket for the
forward position lights and the anti-collision lights.
Newer winglets have two lenses and two mount brackets for separate
forward position lights and a separate anti-collision light in each winglet.
Weight added to the winglet can cause a safety condition. The old paint
must be removed before new paint is applied to the winglet. No new paint
or logos may be applied over the old paint.
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Figure 5
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POWERPLANT ENGINE HAZARDS
General
Engine Entry/Exit Corridor
Two CFM56-7B engines supply thrust for the airplane. The CFM56-7B is a
high bypass ratio, dual rotor, turbo fan engine.
Use the entry/exit corridor when the engine is in operation. Stay out of the
inlet and exhaust areas when the engine is in operation.
These are some of the hazards around an operating engine:
Engine entry/exit corridors are between the inlet hazard area and the
exhaust hazard area. You should only go near an engine that is operating
when:
- Inlet suction
- Exhaust heat
- Exhaust velocity
- Engine noise
Training Information Point
- The engine is at idle
- You are in contact with the people in the flight compartment
When the engine is in operation, the anti-collision lights should be on.
Inlet Suction
Engine inlet suction can pull people and large objects into the engine. At
idle power, the inlet hazard area is a 13 ft. radius around the inlet. If the
wind is over 25 knots, increase the inlet hazard area by 20 %.
Exhaust Heat
The engine exhaust is very hot for a long distance behind the engine. This
can cause damage to personnel and equipment.
Exhaust Velocity
The exhaust velocity is very high for a long distance behind the engine.
This can cause damage to personnel and equipment.
Engine Noise
Engine noise can cause temporary and permanent loss of your ability to
hear. You must wear ear protection when near an engine in operation.
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Figure 6
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ANTENNA LOCATIONS
Antenna Locations
- Weather radar
- Traffic alert and collision avoidance system (TCAS)
- Air traffic control (ATC)
- Global positioning system (GPS)
- Very high frequency (VHF) communication
- Automatic direction finder (ADF)
- VHF omni range (VOR) / localizer
- Marker beacon
- Radio altimeter
- Distance measuring equipment (DME)
- Localizer
- Glideslope
- High frequency (HF) communication
- ELT (-700 aircraft only)
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Figure 7
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FLIGHT COMPARTMENT PANELS
General
These are the major panels in the flight compartment:
- P1 Captain instrument panel
- P2 Centre instrument panel
- P3 First officer instrument panel
- P5 Aft overhead panel
- P7 Glareshield panel
- P8 Aft electronic panel
- P9 Forward electronic panel
- Control stand
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Figure 8
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MAIN INSTRUMENT PANEL
General
In the TEST position, a ground is supplied to make all of the indicators
come on in the BRIGHT mode.
Each type of indicator light assembly has a press to test switch circuit.
This does a test of the lamps.
The lens of each indicator light assembly is coloured.
The controls and displays on the main instrument panels (P1 and P3)
include these components:
- Clock (2)
- Display unit (4)
- Display select panel (2)
- Master dim and test switch
- Brake pressure indicator
- Auto flight status annunciator (2)
- GPWS control panel
- Lighting control (2)
- Conditioned air outlet control (2)
- Alternate nose wheel steering switch
The lens colour means:
- Red; warning
- Amber; caution
- Blue; position
- Green; power on
- White; information
Master Dim and Test
The Master Dim and Test (MD&T) system lets you do these tasks:
Training Information Point
- Do a test of the flight compartment annunciators and lighted push-button
switches
- Set annunciators and lighted push-button switches to the bright or dim
mode
The fire warning indicators are not part of the MD&T system. The fire
warning system has its own test switch on the P8 panel.
There are two types of lamps that you can install in the indicator lights.
If you use the wrong lamp, damage to the lens cover can occur.
Functional Description
When the MD&T switch is in the bright (BRT) position, power goes directly
to the indicators.
When the MD&T switch is in the DIM position, a relay energizes, power
goes through a dim diode. This decreases the voltage to the system
indicator light. This causes the light to be dim.
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Figure 9
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P7 GLARESHIELD PANEL
General
The controls and displays on the P7 glare shield include these components:
- Master caution annunciator (2)
- System caution annunciator (2)
- Mode control panel (MCP)
- EFIS control panel (2)
- Fire warning light (2)
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Figure 10
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P2 CENTER INSTRUMENT AND P9 FORWARD ELECTRONICS
PANEL
General
The controls and displays on the P2 centre instrument panel include these components:
- Yaw damper indicator
- Standby instruments
- Engine display control panel
- Antiskid and autobrake switch and lights
- Flap position indicator
- Landing gear lever and position indicator
- Upper centre display unit
The controls and displays on the P9 forward electronics panel include these components:
- Lower centre display unit
- Multifunction Control Display Unit (MCDU) (2)
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Figure 11
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CONTROL STAND
General
The controls and indicators on the control stand include these components:
- Forward thrust lever (2)
- Reverse thrust lever (2)
- Speed brake handle
- Horizontal stabilizer trim wheel (2) and indicator (2)
- Parking brake lever and indication light
- Flap lever
- Stabilizer trim cut out switch (2)
- Start lever (2)
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Figure 12
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P8 AFT ELECTRONICS PANEL
General
The P8 aft electronics panel has these components:
- Dual weather radar control panel
- Overheat / fire protection panel
- ATC / TCAS control panel
- VHF radio control panel
- Navigation control panel
- Audio control panel
- Aileron / rudder trim panel
- ADF control panel
- ACMS printer
- Lighting control
- Cargo fire control panel
- Heads-up guidance system control panel
- ACMS print event panel
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Figure 13
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P5 AFT OVERHEAD PANEL
General
The controls and displays on the P5 aft overhead panel include these components:
- Inertial system display unit
- IRS mode select unit
- Engine panel
- Observer audio control panel
- Oxygen panel
- Landing gear indicator lights (secondary)
- White dome light switch
- Service interphone switch
- Proximity Switch Electronics Unit (PSEU) light
- Leading edge devices annunciator panel
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Figure 14
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P5 FORWARD OVERHEAD PANEL
General
The controls and displays on the P5 forward overhead panel include these
components:
- APU control switch
- APU indicator panel
- Fuel control panel
- Ground power and bus switching panel
- Equipment cooling panel
- Generator drive and standby power panel
- AC and DC meter panel
- Flight control panel
- Air-conditioning / bleed-air control panels
- Hydraulic control panel
- Cabin altitude panel
- Cabin pressure control panel
- Engine start panel
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Figure 15
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AFT FLIGHT COMPARTMENT PANELS General
The main circuit breaker panels are located behind the first officer’s and
captain’s seats. The P6 and P18 panels have the component load circuit
breakers. Circuit breakers are organized by airplane systems.
The P61 panel has the airborne data loader controls.
Located below the P61 panel is a area for the following manuals:
- Mechanical Dispatch Manual (MDM)
- Pilot Operation Manual (POM)
- Fault Reporting Manual (FRM)
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Figure 16
Figure 16
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LOADABLE SOFTWARE
General
Some of the LRU’s (line replaceable units) in the B-737NG need both
hardware and software. Without the software, the logic circuits in the
LRU’s can not do their specified function. They must have the proper
software loaded.
You can load the software in the LRU at the shop or you can load it at the
airplane.
Systems
These LRU’s have loadable software features:
- FMC (flight management computer)
- DEU (display electronics unit)
- ACARS (ARINC communications addressing and reporting system)
- FDAU (flight data acquisition unit)
- ACMS (airplane condition monitoring system)
- AIRSHOW
- APU ECU (engine control unit)
- EEC (electronic engine control)
The airborne data loader on the P61 panel will load the software to all of
these components, except the EEC.
The EEC software is loaded at the engine with a portable data loader.
Loadable Software Binder
A binder is located in the book storage compartment at the bottom of the
P61.The binder has all of the software that you can load at the airplane.
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LOCATION OF JUNCTION BOXES
General Description
The electrical system has many Junction (J) boxes. The junction boxes
contain many different relays for the AC and DC loads on the airplane.
Most of the junction boxes are in the E/E compartment or in the forward
fuselage, below the flight compartment.
These are the major junction boxes on the airplane:
- J4
- J5
- J9
- J19
- J20
- J22
- J23
- J24
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ELECTRONIC EQUIPMENT COMPARTMENT
General
The electronic equipment compartment is below the main cabin floor, aft of
the nose wheel well. On the ground, you enter this compartment through a
door on the bottom of the fuselage. The door is just aft of the nose landing
gear.
There are five standard equipment racks. These are the E1, E2, E3, E4,
and E5 racks.
There is one optional equipment rack. The E8-1 rack is installed above the
E1 rack.
Shelf assemblies have equipment mounts, interconnect wiring, and
accessory boxes. Most equipment rack shelves are cooled with air. Air is
blown through or drawn through the equipment racks.
There is a drip shield over the racks to protect the equipment from
moisture.
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ELECTRONIC EQUIPMENT RACKS E1, E8
E1 Rack
System LRU’s have program pins to set up the instructions for that LRU.
The program switch modules set these program pins.
A seal plug is installed over the switches to keep the switches stationary.
A security cover holds the seal plug in place.
The program switch module gives this information to an LRU:
The equipment on the E1 rack includes electronics for these functions:
- Autothrottle
- Autopilot
- Communications
- Navigation
- Flight control
- Equipment physical orientation (left, right, upper, lower)
- Airplane type
- Number of units installed
- Customer specific options
E8 Rack
The E8-1 electronic equipment rack is installed above the E1 rack.
The E8-1 is an optional equipment rack for airplanes that do not have
airstairs installed, and need expanded space for optional systems.
The equipment on the E8-1 rack includes electronics for these functions:
See the Standard Wiring Practices Manual for more information on the
program switch module.
- HF Communications
- IFE
- Flight data recording (QAR)
- ACARS
Program Switch Modules
Many of the Line Replaceable Units (LRU’s) are controlled by internal
digital computers. These computers follow instructions (or programs) to do
a certain task.
The program switch module gives an external method to customize a
computer’s program.
The program switch module has these components:
- Switches
- Pin contacts
- Switch seal plug
- Security cover
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ELECTRONICS EQUIPMENT RACKS E2, E3, & E4
General
The E2, E3, & E4 racks include electronics for these functions:
- Window heat
- Communications
- Electrical power
- Common display system
- Flight control
- Fire detection
- Auxiliary power unit
Training Information Point
The E2, E3, & E4 racks are mounted across the aft wall of the E/E
compartment.
The E/E compartment light switch is located on a panel just aft of the access
door opening.
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ELECTRONIC EQUIPMENT RACK E5
General
The equipment in the E5 rack includes electronics for these functions:
- Air Data Inertial Reference System (ADIRS)
- Flight Management Computer System (FMCS)
- FMC transfer relays
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ELECTRONIC EQUIPMENT RACK E6
General
The electronic E6 rack is located in the aft bag bin, just aft of the cargo
door.
The equipment in the E6 rack includes electronics for these functions:
- Voice recorder
- APU electronic control unit
- Airfone
The APU ECU is accessed from the forward end of the E6 rack. The voice
recorder and Airfone boxes are located on the inboard side of the E6 rack.
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PASSENGER COMPARTMENT - PASSENGER
SERVICE UNITS
Purpose
Passenger Service Units (PSUs) provide these functions for passengers:
- Advisory information
- Call switches
Physical Description/Location
PSUs are above each row of seats.
PSUs include these features:
- FASTEN SEAT BELT and NO SMOKING signs
- Individual air outlets
- Passenger address loudspeakers
- Attendant call switches and lights
- Oxygen masks
- Reading lights
- Oxygen generator
PSUs have inboard and outboard support rails. They have hinges on the
outboard side and latches on the inboard side. Small holes in the PSU
face panels give access to the release latches. A lanyard limits movement
as the unit swings open.
Training Information Point
To open passenger service units, insert a small allen key or other
applicable tool into the latch release hole. Then lower the service unit.
It is not necessary to lower the PSU to relamp a reading light. Firmly grasp
the inner ring of the light bezel and turn counter clockwise.
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EXTERIOR LIGHTING
Purpose
The exterior lights supply light for airplane identification, direction, and to
aid in the safe operation of the airplane.
These are the exterior lights on the airplane:
- Wing illumination
- Landing lights
- White anti-collision lights
- Red anti-collision lights
- Position lights
- Taxi and runway turnoff lights
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LANDING LIGHTS
Purpose
The landing lights help the pilots to see the runway for takeoff and landing.
Physical Description
There are two types of landing lights, fixed and retractable.
The fixed landing light has these parts:
- Lens assembly
- Lamp
- Step down transformer
The retractable landing light has these parts:
- Lens assembly
- Lamp
- Retainer screws
- Extend/retract motor
Location
The fixed landing lights are in the wing root area of each wing.
The retractable landing lights are on the fuselage, adjacent to the ram air
inlet panels.
The control switches for the fixed and retractable landing lights are on the
P5 panel forward.
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EMERGENCY LIGHTING
Power Supplies
The power supplies give power to internal and external emergency lights.
Physical Description
The power supplies have these components:
- Battery pack
- Test switch
- Electrical connector
- Control logic and charging circuit
Location
The power supplies are at these locations:
- Behind the ceiling panels at the forward entry area (2)
- Behind the ceiling panels at the aft entry area (2)
- Behind the carpet riser near station 500C, right side only
- Behind the carpet risers near the emergency escape hatches (2)
- Behind the carpet risers near body station 727 (2)
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EMERGENCY LIGHTING - FUNCTIONAL
DESCRIPTION
Operation
With the P5 switch in the ARM position, the power supply makes the
emergency lights come on when one of these conditions occur:
You use the emergency exit light switch on the P5 forward overhead panel
or the emergency exit switch on the attendant panel. These switches
control the emergency lights.
- The attendant panel emergency exit switch is in the ON position
- 28vdc bus 1 power drops below 12 volts
The emergency exit light switch on the P5 panel has these positions:
Training Information Point
- ON, makes emergency lights come on
- OFF, prevents automatic operation
- ARM, prepares system for automatic operation
If you remove all power from the airplane, the P5 emergency exit light
switch must be in the OFF position and the attendant's switch in the
NORM position.
This prevents the emergency lights operation so the batteries do not
discharge.
The NOT ARMED and MASTER CAUTION lights illuminate when the
emergency light switch on the P5 panel is in the ON or the OFF positions.
The 28vdc bus 1 supplies power to these indication lights.
The emergency exit switch on the attendant panel has ON and NORMAL
positions. The ON position makes the emergency lights come on. The
NORMAL position sets automatic operation. The attendant panel switch
will cause the lights to come on even if the P5 switch is OFF.
Functional Description
The power supplies use 28vdc for their charge and control logic circuits.
The charge circuits charge the battery packs when these conditions exist:
- The P5 emergency exit light switch is in the OFF or ARM position
- 28vdc bus 1 has power
- The P14 attendant panel emergency exit light switch is in the NORMAL
Position
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FLIGHT CREW OXYGEN
Purpose
oxygen will flow overboard. This flow will blow out a green indication disk
on the airplane fuselage. The cylinder discharge works with the cylinder
shutoff valve open or closed. If the cylinder shutoff valve is open, oxygen
from the cylinder and the system supply tubing flows overboard.
The schematic below shows the interfaces of the flight crew oxygen
system. The flight crew oxygen system has these interfaces:
Flight Crew Communications Systems
- System supply tubing
- Shutoff valve
- Pressure indication
- Overpressure discharge and indication
- Flight crew communications systems
The flight crew oxygen masks have internal microphones. These
microphones are part of the communications system. See the
communications systems chapter for more microphone information.
Flight Crew Oronasal Mask
System Plumbing
The crew oxygen masks are diluter/demand masks. Controls on each
mask determine the mode of oxygen delivery. In the demand mode, a
mask regulator supplies oxygen to the crew member only when the crew
member inhales. To select continuous flow mode, rotate the
EMERGENCY/TEST knob to EMERGENCY.
The masks have a goggle vent valve for smoke clearance. A push-pull
slider on the top of the mask controls a goggle vent valve. Push this slider
toward the face to close the vent valve. Pull it away from the face to open
the vent valve. An open vent valve clears smoke from the goggles when
the user exhales.
The boxes have these features:
The system plumbing has these components:
- Corrosion resistant, seamless stainless steel tubing
- Flareless fittings
- Bayonet type quick disconnect connectors
- Flexible silicon rubber hoses with braided sheathing
Shutoff Valve
A shutoff valve on the cylinder head opens or closes the cylinder to the
supply system.
Pressure Indication
- A shutoff valve
- A RESET/TEST lever (red)
- An OXY-ON flag (white)
- An oxygen flow indication blinker (yellow cross)
A mechanical pressure gage on the oxygen cylinder shows the cylinder
pressure. The gage shows pressure regardless of the cylinder shutoff
valve position.
An electrically powered gage on the P5 panel shows the pressure at the
cylinder outlet coupling. A pressure transducer on the cylinder coupling
supplies a signal to the gage. The system uses 28vdc from the battery
bus.
The box shutoff valve is closed when the mask is stowed. It opens when
the mask is removed. The blinker is a visual indication of oxygen flow to
the mask. The RESET/TEST lever is used to test the system and reset the
shutoff valve when the mask is stowed.
Overpressure Discharge and Indication
A frangible (breakable) disk on the oxygen cylinder protects the cylinder
from overpressure. If an overpressure condition breaks this disk, the
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FLIGHT CREW OXYGEN - OXYGEN CYLINDER
Purpose
The oxygen cylinder stores the oxygen for the flight crew system.
Physical Description
The oxygen cylinder is made of steel and is painted aviator green.
The cylinder assembly has these features:
- A slow opening shutoff valve
- A cylinder pressure gage
- An overpressure safety relief device
- A pressure reducing regulator
Location
The crew oxygen cylinder is located in the E/E compartment, in the lower
right area of the transverse rack.
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PASSENGER OXYGEN - OXYGEN GENERATOR
Purpose
The oxygen generators supply emergency oxygen to the passengers and
flight attendants.
Physical Description
The oxygen generators are metal cased cylindrical devices. At one end of
the generator is a spring loaded firing mechanism. At the other end is an
output manifold and a relief valve. The oxygen generator output manifolds
have 4,3, or 2 ports. The size of the generator determines the number of
output manifold ports.
Location
The oxygen generators are in these units:
- The Passenger Service Units (PSUs)
- The lavatory service units
- The attendant service units
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POTABLE WATER - FUNCTIONAL DESCRIPTION
Training Information Point
Functional Description
When you drain the water system, you must drain water from these two
areas:
The water system has one tank that holds potable water.
You fill and drain the water tank at the water service panel. There are
control handles for the fill/overflow valve and the water tank drain valve.
The water drains overboard through drain fittings.
The water tank supplies water to these locations:
- The water service panel
- The forward lavatory
The water service panel lets you drain the water tank and aft supply lines.
- Galley faucets
- Lavatory faucets
- Lavatory toilets
The forward lavatory has a drain valve downstream of the water supply
shutoff valve. The forward lavatory drain valve lets you drain the forward
water supply lines. When you drain water from the forward lavatory, you
must have the water supply shutoff valve open.
Each lavatory has a water supply shutoff valve. The valve lets you isolate
the water supply to the sink or to the toilet. The valve also lets you isolate
both the sink and toilet at the same time.
The forward lavatory has a drain valve. This valve drains water from the
forward water supply lines.
A water heater in each lavatory increases the temperature of the water.
The water goes to the hot side of the faucet.
The water tank level sensor sends the water quantity data to a water
quantity transmitter. The transmitter sends the information to a water
quantity indicator at the aft attendant's panel. The water quantity indicator
shows the level of water in the tank
It is necessary to fully drain the water system before you add a
disinfectant. Also, drain the water system fully when you park the airplane
in cold weather.
B737-800 aircraft are equipped with a gray water drain valve. This directs
water to drain from the fwd drain fitting on the ground and to the fwd drain
mast in the air.
Location
The potable water tank is located behind the aft wall in the aft cargo bin.
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WATER TANK PRESSURIZATION
Purpose
The water tank pressurization system pressurizes the potable water tank.
General
Pressure for the water tank comes from the air compressor or the system.
The water tank pressurization has these functions:
- Controls the air pressure that goes into the water tank
- Selects the source of the pressurized air
- Prevents contamination from unwanted material in the air
Location
When the potable water air compressor is fitted it is located on the left side
of the aircraft behind the waste tank.
Training Information Point
You can release pressure from the water tank by opening the fill and
overflow valve. Use the handle at the water service panel.
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PASSENGER WATER - WATER HEATER
Purpose
The lavatory water heaters increase the temperature of water for use in
the lavatory sink.
Location
There is a water heater in each lavatory. You open the sink cabinet door to
get access to it.
The overheat switch is under the water heater cover.
Physical Description
The water heater has these parts:
- Power switch
- Indicator light
- Cover
- Overheat switch
- Pressure relief valve (inside tank)
- Heater elements (inside tank)
- HIGH/LOW/MEDIUM switch
The power switch has ON and OFF positions.
Functional Description
The heater operates when 115vac power is available and there is not an
over temp. You can see the orange indicator light is on when the heater
operates.
The pressure relief valve opens if pressure inside the water heater is
greater than 140 psi.
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VACUUM WASTE - FUNCTIONAL DESCRIPTION
Interfaces
Vacuum Toilet Assemblies
The flush switch sends a signal to operate the vacuum blower. The signal
goes through the waste drain ball valve and the barometric switch. The
waste drain ball valve must be closed. The barometric switch disables the
vacuum blower when the airplane is above 16,000 ft.
Operation of the toilet flush switch sends a signal through the logic control
module to the Flush Control Unit (FCU) and the vacuum blower. The FCU
sends an open signal to the rinse valve to supply a quantity of potable
water to the toilet bowl. After the rinse valve closes, the FCU opens the
toilet flush valve for four seconds and closes it.
Training Information Point
Waste Tank Assembly
The waste tank must be rinsed at every service interval. If the waste tank
is not serviced properly, unwanted waste material can collect on the point
level sensors. The collection of material on the point level sensors can
cause a tank full signal. This will stop operation of the lavatory toilets.
You should flush crushed ice down the toilets at regular intervals. This will
help to prevent the collection of unwanted material in the vacuum tubing.
Do not use ice cubes at a substitute for crushed ice. Ice cubes can cause
damage to the point level sensors.
Differential pressure causes the toilet bowl contents to flow from the toilet
to the waste tank. The vacuum blower or ambient pressure pulls air out of
the waste tank through a water separator. This causes the tank to have a
lower pressure than the cabin pressure.
The waste tank collects the waste from all the lavatory toilet assemblies.
Servicing the waste tank is from the waste service panel. You attach the
service hose and open the waste tank drain valve. When the tank is
empty, you attach the rinse hose and supply water pressure. Water flows
through two filters and two rinse nozzles. The rinse nozzles spray water
around the inside of the tank to clean the inside components. The
chemical precharge is put in after the tank is fully drained, and flushed.
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VACUUM TOILET ASSEMBLY
Purpose
The vacuum toilet assembly collects human waste material. It operates the
vacuum waste system to send the waste to the waste tank.
Location
There is a vacuum toilet assembly in each lavatory.
Physical Description
The vacuum toilet assembly has these parts:
- Rinse ring
- Toilet bowl
- Anti-siphon valve
- Rinse valve
- Flush valve
- Manual shutoff valve
- Manual shutoff valve handle
- Assembly mounting stand
- Flush Control Unit (FCU)
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WASTE TANK QUANTITY INDICATION
Physical Description
General
The attendant panel waste quantity indicator is part of the waste system
module. The waste system module has these indications:
The waste tank quantity indication system does these functions:
- Monitors and displays the level of waste in the waste tank
- Stops operation of the vacuum toilets when the tank is full
- Gives indication when the lavatories stop operation for waste tank full
condition
- Gives indication when the sensors are dirty
- BITE
- Waste tank quantity indicator
- CLEAN/CHECK SENSOR light
- LAVS INOP test switch
These components are in the waste tank quantity indication system:
- Waste tank point level sensor (2)
- Waste tank continuous level sensor
- Logic Control Module (LCM)
- Attendant panel waste quantity indicator
Aft Attendant Panel Waste Quantity Indication
Purpose
The attendant panel waste quantity indicator gives information about the
waste tank.
Location
The attendant panel waste quantity indicator is at the aft attendant station.
It is on the partition, adjacent to the aft entry door.
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VACUUM WASTE - COMPONENT LOCATIONS AFT CARGO COMPARTMENT
Location
These components are in the aft cargo compartment, left side, behind the
cargo lining:
- Liquid separator
- Waste drain ball valve and pull rod
- Vacuum blower and filter
- Vacuum check valve
- Waste tank
- Waste drain valve assembly
- Waste tank rinse fitting assembly
- Waste tank rinse filter
- Waste tank point level sensor
- Waste tank continuous level sensor
- Logic control module
The liquid separator is on top of the waste tank.
The waste tank ball valve is below outboard, and forward of the waste
tank.
The vacuum check valve and vacuum blower are forward of the waste
tank.
They are behind the sidewall panels in the aft cargo compartment.
The waste drain valve assembly and the waste drain rinse fitting assembly
are on the waste service panel. You can access them from below the floor.
The waste tank rinse nozzles are on the top of the waste tank.
The waste tank rinse filters are along the inboard side of the waste tank.
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MAINTENANCE DOCUMENTS – INTRODUCTION
General
- Service problems
- Structural damage
The maintenance documents for the B-737 Next Generation and B-777
supply help for maintenance activities. Many different documents work
together to permit you to maintain the airplane. The maintenance
documents will help you perform scheduled and unscheduled
maintenance.
You use these documents to perform unscheduled maintenance:
- Fault Reporting Manual (FRM)
- Fault Isolation Manual (FIM)
- Structural Repair Manual (SRM)
- Mechanical Dispatch Manual (MDM)
- Airplane Maintenance Manual (AMM)
Scheduled Maintenance
These are examples of scheduled maintenance:
- Through service checks
- Layover checks
- Service checks
- Letter checks
Maintenance Planning Document
The Maintenance Planning Document (MPD) defines the tasks for each
type of scheduled maintenance check. Airlines use the MPD to make task
cards that the technician uses during the maintenance checks.
You use these documents to perform scheduled maintenance:
Airplane Maintenance Manual
- Maintenance Planning Document (MPD)
- Airplane Maintenance Manual (AMM)
The Airplane Maintenance Manual (AMM) has two parts. Part I is the
Systems Description Section (SDS). This section replaces the Description
and Operation (D and O) section of older Boeing airplane models.
Part II is Practices and Procedures.
The practices and procedures section has data related to these functions:
These documents supply supporting data to perform scheduled
maintenance:
- System Schematics Manual (SSM)
- Wiring Diagram Manual (WDM)
- Structural Repair Manual (SRM)
- Illustrated Parts Manual (IPC)
- Removal / Installation of components
- Component location
- Maintenance practices
- Servicing
- Adjustment / Test
- Inspection / Check
- Cleaning / Painting
- Repair
Unscheduled Maintenance
These are examples of unscheduled maintenance:
- Flight faults
- Ground faults
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INTRODUCTION pt 2 System Schematics Manual
The fault code permits faster maintenance when the airplane lands. FRM
fault codes refer you to the FIM.
The System Schematic Manual (SSM) gives the user an understanding of
system operation and helps in the fault isolation process. It supplies the
interconnection of all LRU’s of a system or subsystem. It also supplies a
general knowledge about system operation.
Fault Isolation Manual
You use the Fault Isolation Manual (FIM) to repair airplane faults. You
start the fault isolation process with FRM fault codes or a fault description.
The FIM will identify the maintenance action(s) to correct the fault.
Wiring Diagram Manual
The Wiring Diagram Manual (WDM) supplies details of the point-to-point
wiring on the airplane.
Structural Repair Manual
Illustrated Parts Catalogue
The Structural Repair Manual (SRM) supplies descriptive information and
specific instructions to help in field repairs of the airplane structure. The
SRM is not customized.
It has data relative to these areas:
The Illustrated Parts Catalogue (IPC) supplies part replacement data.
This data includes:
- Replacement part number
- Part illustrations
- Supplier data
- Specification numbers
- Recommended spares
- Service bulletin activity
- Allowable damage evaluation
- Typical repairs
- Material identification
- Material substitution
- Fastener Installation
- Alignment check
- Planning
Standard Wiring Practices Manual
Mechanical Dispatch Manual
The Standard Wiring Practice Manual has instructions for maintenance
and repair of the wiring of all Boeing airplanes. It is not customized.
The Mechanical Dispatch Manual (MDM) supplies minimum equipment
required for dispatch. It also supplies the procedures for dispatch with a
fault if permitted.
Fault Reporting Manual
The flight crew uses the Fault Reporting Manual (FRM) to improve
communication with maintenance personnel. The flight crew uses the FRM
to get fault codes for airplane faults. These faults can be flight deck effects
or other faults. The FRM has standard log book write-ups for each fault
code.
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DISPATCH DEVIATION PROCEDURES GUIDE
These are the parts of the minimum equipment list items:
General
- Item
- Repair interval
- Number installed
- Number required for dispatch
- Remarks or exceptions
- Placard
- Maintenance procedure (optional)
- Operations procedure (optional)
The Dispatch Deviation Procedures Guide (DDG) helps airlines make the
procedures needed to operate their aircraft in the different nonstandard
configurations. This manual shows permitted nonstandard configurations.
It has these sections:
- Introduction
- Minimum Equipment List Items
- Configuration Deviation List Items
- Ferry Items
- Miscellaneous Items
The item is the equipment, system, or function installed in the airplane.
The repair interval shows when you must repair the item. Repair intervals
are specified in the front section of the MEL.
These letter codes show the time interval:
Introduction
The Introduction section gives the purpose, background, contents, and
organization of the DDG.
- A; as shown in the remarks or exceptions column
- B; within 3 consecutive calendar days
- C; within 10 consecutive calendar days
- D; within 120 consecutive calendar days
Minimum Equipment List Items
The CAA publishes a Master Minimum Equipment List (MMEL). The
operator can add to the MMEL. Then it is the operator’s Minimum
Equipment List (MEL).
The MMEL tells you the minimum equipment and procedures necessary to
operate the aircraft. The operator’s MEL cannot be less restrictive than the
Master Minimum Equipment List.
The MEL has an ATA index of MEL items and a list of definitions.
The MEL items are in ATA sequence. There is a general system
schematic at the start of each ATA chapter.
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Repair intervals are specified in the front section of the MMEL.
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DISPATCH DEVIATIONS PROCEDURES GUIDE (CONT.) Miscellaneous Items
Minimum Equipment List (continued)
The Miscellaneous items section contains a list of other items that are
unique.
The number installed is the quantity usually installed in the airplane. A
dash (-) shows if the quantity can change.
The number required for dispatch is the minimum quantity necessary for
operation if you meet the conditions in the remarks of exemptions column.
The MMEL may show a dash (-) in this column. The MEL must show
actual quantity required.
The remarks or exemptions column shows what you must do to release
the airplane. It may also show operations notes and limits.
The placard section shows the placard and where you must put it when
this item does not operate.
Some MEL items have a maintenance procedure that you must do to
release the airplane. The maintenance procedure is listed in the MEL if it
is simple. A reference to the procedure in the 900 page block of the
Airplane Maintenance Manual (AMM) is listed if the procedure is more
complex. Some MEL items have an operations procedure. The flight crew
must do this procedure if your airline operates the airplane when this item
does not operate.
Training Information Point
Some airlines have combined the MMEL and CDL into one onboard
manual and call it the Mechanical Dispatch Manual (MDM).
Configuration Deviation List Items
The Configuration Deviation List (CDL) is an appendix to the approved
Aircraft Flight Manual (AFM). It includes secondary airframe and engine
parts which you do not have to have for dispatch.
Ferry Items
The ferry items section contains information for dispatch with configuration
deviation for which revenue passengers are not permitted by the MMEL or
the CDL. A ferry flight occurs when it is necessary to fly the aircraft back to
a maintenance base for repairs.
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FAULT ISOLATION MANUAL
General
These are the chapter subjects:
You use the Fault Isolation Manual (FIM) to isolate and correct airplane
faults. To isolate a fault, you must get a FIM task number. You use
different sections of the FIM along with airplane data to identify the correct
task number.
The FIM has these parts:
- How to use the FIM
- Fault code index
- Introduction
- Front subjects
- Chapter subjects
- Fault isolation tasks
- Task support pages
FIM Introduction
Training Information Point
- Maintenance message index
The introduction is a very important part of the FIM. It explains the parts of
the FIM and tells how to use them. FIM Front Subjects
You use the front subjects to find a task number. With a fault description or
a cabin fault code, you can find which tasks in the FIM you must do to
correct the fault.
These are the front subjects:
The flight crew uses the Fault Reporting Manual (FRM) to find the fault
code. If the flight crew does not supply a fault code, you can use the front
subjects of the FIM to find the task number.
Lists are used if you have a fault, but do not have a fault code or FIM task
number. Index’s are used if you have a fault code and are looking for the
FIM task number.
- Observed fault list in alphabetical order
- Observed fault list in system order
- Cabin fault list
- Cabin fault code index
FIM Chapter Subjects
The chapter subjects have two types of information. The subjects have the
fault isolation tasks. They also have information that help you identify the
correct task.
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AIRPLANE MAINTENANCE MANUAL - AMM
PART I
General
Each subject of the SDS has this information:
The Airplane Maintenance Manual (AMM) Part I is the first of two parts of
the AMM. It is called the System Description Section (SDS). This section
replaces the Description and Operation (D & O) section of older Boeing
AMM’s. Both Part I and Part II of the AMM show the configuration of the
airplanes in an operator’s fleet. They have frequent revisions for
improvements and for configuration changes.
- Purpose/Introduction
- General description
- Component location
- Interface
- Operation
- Functional description
- Training Information Points (TIPs)
Purpose
The SDS gives descriptions of the interfaces, function, and operation of
the airplane systems and subsystems. You use these descriptions to
become familiar with the airplane systems so that you can do fault
isolation and system maintenance.
The SDS (AMM Part I) content can be used as a training manual.
Organization
The SDS uses text/graphic Para visuals (page sets). Each graphic has
one or more pages of text that describe the information on the graphic.
The graphic has the primary information and the associated text pages (s)
have the support information or explanations.
The SDS uses a horizontal (sometimes called landscape) format. All
pages (Graphic and text) are 8-1/2 by 11 inches. The graphic page is
always on the bottom (odd numbered page) of the text/graphic Para
visual. The text pages have a double galley (two columns) format.
Divisions
The SDS organization is by ATA chapter (system) or chapter/section
(Subsystem). Each ATA chapter/ section usually defines an airplane
system or subsystem.
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AIRPLANE MAINTENANCE MANUAL - AMM
PART II
General
Part II of the AMM contains the maintenance practices and procedures to
do maintenance on the airplane.
If all of the topics for an ATA chapter, subsystem, or sub-subsystem are
brief, all of the topics will be in a single maintenance practice page block.
The dispatch deviation guide page block has procedures with
maintenance tasks that prepare the airplane for flight with certain systems
and or components inoperative. It also has tasks that put the airplane back
to its usual condition.
Chapter Numbering System
The manual has a tab section for each ATA chapter.
Within each tab section, the manual has more divisions that use the
assigned subject number (ASN). Example: XX-YY-ZZ,
Training Information Point
- XX is the ATA chapter
- YY is the subsystem or sub-subsystem
- ZZ is the unit (component)
Each chapter in Part II of the AMM has a list of effective pages at the
beginning of each chapter.
The table of contents for each chapter lists the maintenance procedures in
numerical order for each subsystem and sub-subsystem. The
maintenance tasks are in alphabetical order based on the page number
sections described below.
Page Type Page Block
Maintenance Practices (MP) 201-299
Servicing (SRV) 301-399
Removal/Installation (R/I) 401-499
Adjustment/Test (A/T) 501-599
Inspection/Check (I/C) 601-699
Cleaning/Painting (C/P) 701-799
Repairs (AR) 801-899
Dispatch Deviation Guide (DDG) 901-999
Dispatch Deviation Guide
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AIR CONDITIONING
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CONTENTS
ATA 21 – AIR CONDITIONING
GENERAL DESCRIPTION - CONTROL - 800/900 .......................................................................................................................................................................................... 6
GENERAL ............................................................................................................................................................................................................................................................... 6
AIR CONDITIONING ACCESSORY UNIT................................................................................................................................................................................................................... 6
PACK FLOW CONTROL AND PACK COOLING -......................................................................................................................................................................................... 8
LOCATIONS ............................................................................................................................................................................................................................................................ 8
GENERAL DESCRIPTION - AIR FLOW ......................................................................................................................................................................................................... 10
GENERAL ............................................................................................................................................................................................................................................................. 10
PACK FLOW CONTROL ......................................................................................................................................................................................................................................... 10
PACK COOLING SYSTEM ...................................................................................................................................................................................................................................... 10
ZONE TEMPERATURE CONTROL ........................................................................................................................................................................................................................... 10
GENERAL DESCRIPTION - AIR FLOW (CONT.) ........................................................................................................................................................................................ 12
RECIRCULATION .................................................................................................................................................................................................................................................. 12
AIR DISTRIBUTION ............................................................................................................................................................................................................................................... 12
PACK FLOW CONTROL – INTRODUCTION ............................................................................................................................................................................................... 14
AIR SUPPLY ......................................................................................................................................................................................................................................................... 14
COMPRESSION ...................................................................................................................................................................................................................................................... 14
CONDENSE ........................................................................................................................................................................................................................................................... 14
WATER REMOVAL ............................................................................................................................................................................................................................................... 14
REHEAT ............................................................................................................................................................................................................................................................... 14
EXPANSION .......................................................................................................................................................................................................................................................... 14
PACK FLOW CONTROL AND PACK COOLING - RAM AIR .................................................................................................................................................................... 16
GENERAL ............................................................................................................................................................................................................................................................. 16
GROUND MODE ................................................................................................................................................................................................................................................... 16
FLIGHT (FLAPS NOT UP) ...................................................................................................................................................................................................................................... 16
FLIGHT CRUISE (FLAPS UP) ................................................................................................................................................................................................................................. 16
INDICATION.......................................................................................................................................................................................................................................................... 16
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TEMPERATURE CONTROL – OPERATION ................................................................................................................................................................................................ 18
GENERAL ............................................................................................................................................................................................................................................................. 18
TEMPERATURE SELECTORS .................................................................................................................................................................................................................................. 18
DUCT OVERHEAT LIGHT ...................................................................................................................................................................................................................................... 18
TRIM AIR SWITCH ................................................................................................................................................................................................................................................ 18
TEMPERATURE CONTROL - GENERAL DESCRIPTION ......................................................................................................................................................................... 20
TRIM AIR ............................................................................................................................................................................................................................................................. 20
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 20
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 20
PACK/ZONE TEMPERATURE CONTROLLER - GENERAL ..................................................................................................................................................................... 22
PURPOSE .............................................................................................................................................................................................................................................................. 22
LOCATION ............................................................................................................................................................................................................................................................ 22
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 22
DISTRIBUTION - GENERAL DESCRIPTION ................................................................................................................................................................................................ 24
GENERAL ............................................................................................................................................................................................................................................................. 24
MAIN AIR DISTRIBUTION ..................................................................................................................................................................................................................................... 24
FLIGHT COMPARTMENT DISTRIBUTION ............................................................................................................................................................................................................... 24
PASSENGER COMPARTMENT DISTRIBUTION ........................................................................................................................................................................................................ 24
RECIRCULATION SYSTEM .................................................................................................................................................................................................................................... 24
VENTILATION....................................................................................................................................................................................................................................................... 24
EQUIPMENT COOLING SYSTEM ............................................................................................................................................................................................................................ 24
RECIRCULATION SYSTEM – INTRODUCTION ......................................................................................................................................................................................... 26
PURPOSE .............................................................................................................................................................................................................................................................. 26
RECIRCULATION .................................................................................................................................................................................................................................................. 26
ACCESS ................................................................................................................................................................................................................................................................ 26
RECIRCULATION AIR FILTERS.............................................................................................................................................................................................................................. 26
EQUIPMENT COOLING SYSTEM - GENERAL DESCRIPTION ............................................................................................................................................................... 28
GENERAL ............................................................................................................................................................................................................................................................. 28
SUPPLY ................................................................................................................................................................................................................................................................ 28
EXHAUST ............................................................................................................................................................................................................................................................. 28
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PRESSURIZATION CONTROL - GENERAL DESCRIPTION .................................................................................................................................................................... 30
PURPOSE .............................................................................................................................................................................................................................................................. 30
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 30
AUTOMATIC PRESSURIZATION CONTROL ............................................................................................................................................................................................................ 30
MANUAL PRESSURIZATION CONTROL ................................................................................................................................................................................................................. 30
COMPONENT LOCATION ................................................................................................................................................................................................................................ 32
GENERAL ............................................................................................................................................................................................................................................................. 32
CABIN PRESSURE CONTROL MODULE AND CABIN .............................................................................................................................................................................. 34
ALTITUDE PANEL .............................................................................................................................................................................................................................................. 34
PURPOSE .............................................................................................................................................................................................................................................................. 34
LOCATION ............................................................................................................................................................................................................................................................ 34
CABIN PRESSURE CONTROL MODULE – GENERAL .............................................................................................................................................................................................. 34
AIR CONDITIONING - GENERAL DESCRIPTION - 600/700 ..................................................................................................................................................................... 36
GENERAL ............................................................................................................................................................................................................................................................. 36
AIR-CONDITIONING CONTROL PANELS ................................................................................................................................................................................................................ 36
CABIN TEMPERATURE PANEL .............................................................................................................................................................................................................................. 36
AIR CONDITIONING/BLEED AIR CONTROLS PANEL ............................................................................................................................................................................................. 36
EQUIPMENT COOLING PANEL .............................................................................................................................................................................................................................. 36
CABIN PRESSURE SELECTOR PANEL/CABIN ALTITUDE PANEL ............................................................................................................................................................................ 36
COOLING - GENERAL DESCRIPTION .......................................................................................................................................................................................................... 38
GENERAL ............................................................................................................................................................................................................................................................. 38
AIR CONDITIONING/BLEED AIR CONTROLS PANEL ............................................................................................................................................................................................. 38
FLOW CONTROL SHUTOFF VALVE ....................................................................................................................................................................................................................... 38
PRIMARY HEAT EXCHANGER ............................................................................................................................................................................................................................... 38
AIR CYCLE MACHINE............................................................................................................................................................................................................................................ 38
SECONDARY HEAT EXCHANGER .......................................................................................................................................................................................................................... 38
RAM AIR SYSTEM ................................................................................................................................................................................................................................................ 38
LOW LIMIT (35F) SYSTEM ................................................................................................................................................................................................................................... 38
WATER SEPARATOR............................................................................................................................................................................................................................................. 38
TEMPERATURE CONTROL – OPERATION ................................................................................................................................................................................................ 42
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GENERAL ............................................................................................................................................................................................................................................................. 42
CONTROLS ........................................................................................................................................................................................................................................................... 42
INDICATIONS ........................................................................................................................................................................................................................................................ 42
CABIN TEMPERATURE CONTROLLER ................................................................................................................................................................................................................... 42
LOCATION ............................................................................................................................................................................................................................................................ 42
TEMPERATURE CONTROL - CABIN TEMP SENSOR -............................................................................................................................................................................. 44
PURPOSE .............................................................................................................................................................................................................................................................. 44
LOCATION ............................................................................................................................................................................................................................................................ 44
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 44
FUNCTIONAL DESCRIPTION.................................................................................................................................................................................................................................. 44
DISTRIBUTION - GENERAL DESCRIPTION – COMPONENET .............................................................................................................................................................. 46
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 46
MAIN AIR DISTRIBUTION ..................................................................................................................................................................................................................................... 46
FLIGHT COMPARTMENT CONDITIONED AIR DISTRIBUTION ................................................................................................................................................................................. 46
PASSENGER COMPARTMENT CONDITIONED AIR DISTRIBUTION .......................................................................................................................................................................... 46
RECIRCULATION SYSTEM .................................................................................................................................................................................................................................... 46
VENTILATION....................................................................................................................................................................................................................................................... 46
EQUIPMENT COOLING SYSTEM ............................................................................................................................................................................................................................ 46
DISTRIBUTION COMPONENT LOCATION ............................................................................................................................................................................................................... 46
COOLING SYSTEM COMPONENT LOCATION ......................................................................................................................................................................................................... 46
RECIRCULATION SYSTEM – INTRODUCTION ......................................................................................................................................................................................... 48
PURPOSE .............................................................................................................................................................................................................................................................. 48
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 48
LOCATION ............................................................................................................................................................................................................................................................ 48
OPERATION .......................................................................................................................................................................................................................................................... 48
AIR CONDITIONING - FUNCTIONAL DESCRIPTION ............................................................................................................................................................................... 50
GENERAL ............................................................................................................................................................................................................................................................. 50
PACK FLOW CONTROL ......................................................................................................................................................................................................................................... 50
PACK COOLING SYSTEM ...................................................................................................................................................................................................................................... 50
ZONE TEMPERATURE CONTROL ........................................................................................................................................................................................................................... 50
RECIRCULATION .................................................................................................................................................................................................................................................. 50
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GENERAL DESCRIPTION - CONTROL - 800/900
General
These flight compartment panels let you control the Air Conditioning
system:
- Air conditioning/bleed air control panel
- Temperature control panel
- Equipment cooling control panel
- Cabin pressure control panel
These components in the E/E compartment control the functions of the air
conditioning system:
- Two pack/zone temperature controllers
- Two Air Conditioning Accessory Units (ACAU)
- Two Cabin Pressure Controllers (CPC)
Pack/Zone Temperature Controllers
The pack/zone temperature controllers control these functions of the air
conditioning system:
- Pack cooling temperature
- Trim air, regulation (on or off)
- Zone temperature
Air Conditioning Accessory Unit
The Air Conditioning Accessory Units (ACAU) are the interface for airplane
operational logic and the air systems.
Cabin pressure Controller
The cabin pressure controller controls the cabin pressure function of the
air conditioning system.
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PACK FLOW CONTROL AND PACK COOLING A/C COMPARTMENT COMPONENT LOCATIONS Locations
These are the air conditioning components that are in the air conditioning
compartments:
- Heat exchanger (primary/secondary)
- Heat exchanger clean out access panel
- Plenum/diffuser assembly
- Fan bypass check valve
- Air Cycle Machine (ACM)
- Ram air control temperature sensor
- Turbine inlet overheat switch
- Compressor discharge overheat switch
- Standby temperature control valve
- Temperature control valve
- Condenser
- Reheater
- Water extractors
- Trim air modulating valves
- Trim air pressure regulating valve
- Flow control and shutoff valve
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GENERAL DESCRIPTION - AIR FLOW
Pack Cooling System
General
This part of the A/C system removes water as necessary and controls the
temperature of fresh air before it flows into the distribution part of the air
conditioning system. The primary components are the left and right packs.
The normal control for the left pack makes sure that it supplies air at a
temperature that gives the necessary cooling for the flight compartment.
The normal control for the right pack makes sure that it supplies air at a
temperature that gives necessary cooling for the mix manifold.
These are the primary parts of the Air Conditioning (A/C) system that have
an effect on the supply of fresh air or recirculation of conditioned air:
- Pack flow control
- Pack cooling system
- Zone temperature control
- Recirculation
- Air distribution
Zone Temperature Control
This part of the A/C system increases the temperature of the conditioned
air that flows into the occupied areas of the airplane. It also gives pressure
regulation and on/off control for the trim air part of the system.
These are the primary components:
The primary parts of the A/C system have these functions:
- Control fresh air flow for the airplane pressurization and ventilation
system
- Control the flight compartment and passenger cabin temperature
- Recirculate cabin air for ventilation
- Trim air pressure regulating and shutoff valve
- Zone trim air modulating valves
- Temperature sensors
Pack Flow Control
This part of the A/C system controls the quantity of fresh air that flows into
the airplane.
This is the primary component:
-
The system calculates the necessary pack outlet temperatures to satisfy
the cooling needs of the flight compartment and the mix manifold. The
system also calculates the heating necessary for each temperature control
zone.
These are the temperature control zones:
Flow control and shutoff valve
The quantity of fresh air necessary for ventilation is more than for
pressurization. The ventilation quantity is based on a fixed value for the
crew, allowable leakage, and on the number of passenger seats. Usually,
the left and right flow control systems provide the same quantity of fresh
air. Fresh air flow changes when airplane conditions change.
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- Flight control zone
- Forward cabin zone
- Aft cabin zone
Air from the pneumatic system adds heat to a zone that needs warm air.
The trim air pressure regulating and shutoff valve gives on/off control and
keeps trim air pressure at a preset limit.
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GENERAL DESCRIPTION - AIR FLOW (CONT.)
The zone trim air modulating valves control the heat added to the
conditioned air for each zone.
Recirculation
This part of the A/C system recycles approximately 50 percent of the cabin
air for ventilation purposes. This reduces the quantity of air needed from
the pneumatic system for ventilation.
These are the primary components:
-
Left and right recirculation fans and filters
Air Distribution
This part of the A/C system moves conditioned air from the packs or
ground air sources to the temperature control zones.
These are the primary components:
- Ground air connection
- Mix manifold
- Distribution ducts/risers
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PACK FLOW CONTROL – INTRODUCTION
Air Supply
Reheat
Preconditioned engine bleed air or APU bleed air passes through the Flow
Control and Shutoff Valve (FCSOV) which regulates airflow into the pack.
It also functions as a shutoff valve. The air initially enters the pack at the
primary heat exchanger.
The dry air leaving the extractor is heated again on the second pass
through the reheater, recovering the energy that normally would be added
to the turbine exhaust in the cold side of the condenser. The function of
the reheater is to minimize the temperature difference between the
secondary heat exchanger outlet and the turbine inlet, thereby reducing
the amount of warm air that needs to be added to the pack discharge air.
Compression
Expansion
The air passes through the primary heat exchanger where it is cooled by
ram air. It then enters the compressor section of the Air Cycle Machine
(ACM) where pressure and temperature are increased. The compressor
discharge air is cooled by ram air in the secondary heat exchanger and
then enters the reheater.
After passing through the reheater, the dry air enters the turbine section of
the Air Cycle Machine (ACM). The ACM has three rotating sections all
mounted on a common shaft supported by air bearings.
The three rotating sections are:
Condense
- Turbine
- Compressor
- Fan
The air passes through the reheater hot side and is cooled by transferring
heat to the colder air passing through the cold side. After leaving the
reheater, the air passes through the condenser where further temperature
reduction takes place, lowering it to the level required for moisture
condensation. The air is cooled in the condenser by cold turbine exhaust
air.
In expanding through the turbine, the air delivers power to drive the
compressor and fan. The energy lost from the turbine airflow causes a
temperature reduction resulting in turbine discharge air well below ram air
temperature. The cold discharge air passes through the condenser on its
way to the mix manifold. The cold air may cause condensation to form on
the inlet of the condenser. This is regulated by the introduction of warm air
from the standby temperature control valve.
The fan section of the ACM is used to bring cooling air into the ram air
duct when the aircraft is on the ground.
Water Removal
Condensed water droplets are removed by an inertial process in the water
extractor. Water removed by high pressure through the extractor is routed
to the water spray injector in the ram air inlet for the primary and
secondary heat exchangers. The spray cools the ram air and increases
the systems cooling capacity.
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PACK FLOW CONTROL AND PACK COOLING RAM AIR
SYSTEM -­‐ RAM AIR INLET – OPERATION Flight Cruise (Flaps Up)
General
In flight, when the flaps are at the full up position, the pack/zone
temperature controller has control of the ram air actuator.
The pack/zone controller opens or closes the ram air inlet modulation
panels to control the pack temperature.
The ram air system controls the airflow through the primary and secondary
heat exchangers.
The ram air inlet assembly has these two major assemblies:
Indication
- Ram air inlet modulation panel
- Ram air inlet deflector door
The RAM DOOR FULL OPEN (Blue) light on the Air Conditioning/Bleed air
panel illuminates anytime the ram air inlet actuator is driven to the full
open position.
These are the three modes of control for the ram air system:
- Ground
- Flight (flaps not up)
- Flight cruise (flaps up)
The Air Conditioning Accessory Units (ACAU) relays control power to the
pack zone temperature controllers for ram air actuation and control.
Ground Mode
When the airplane is on the ground, the ram air inlet actuator is in the fully
retracted position. When the actuator is in the fully retracted position, the
ram air deflector door is in the extend position, and the ram air inlet
modulation panel is in the open position.
The RAM DOOR FULL OPEN lights are on.
Flight (Flaps Not Up)
At takeoff, the actuator moves the ram air deflector door out of the
airstream.
The ram air modulation panel stays open.
The RAM DOOR FULL OPEN lights are on.
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TEMPERATURE CONTROL – OPERATION
General
The temperature controls panel is the air conditioning indication and
control interface for the flight crew.
Temperature Selectors
The three temperature selectors give automatic temperature control for
their related zones. The selector has these temperature set points:
- C (cool) sets a temperature of 65F
- W (warm) sets a temperature of 85F
- Intermediate selector positions set proportionate temperature
Turn selector to the OFF position to close the related trim air modulating
valve.
Duct Overheat Light
The three duct overheat lights show over temperature or control channel
fault/failures:
Trim Air Switch
The trim air switch controls the trim air pressure regulating and shutoff
valve
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TEMPERATURE CONTROL - GENERAL
DESCRIPTION
Trim Air
The temperature control system automatically controls the temperature in
these three airplane air conditioning zones:
- Flight compartment zone
- Forward passenger compartment zone
- Aft passenger compartment zone
Physical Description
The temperature control system uses these components:
- Temperature control panel
- Sensors and overheat switches
- Digital pack/zone controllers
- Pack temperature control valves (normal and standby)
- Trim air system valves
- Air Conditioning Accessory Units (ACAUs)
General Description
The temperature control system is automatic. The flight crew makes the
required selections on the temperature control panel to operate the
system. During operation, the digital pack/zone controllers modulate the
temperature control valve. They control pack discharge temperature to the
requirements of the zone that requires the most cooling.
The pack/zone controllers modulate the trim air modulating valves to inject
hot trim air into the ducts of the other zones. This increases the
temperature of the air supply to the other zones.
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PACK/ZONE TEMPERATURE CONTROLLER GENERAL
Purpose
The pack/zone temperature controllers do these things:
- Control their related air conditioning pack
- Give automatic standby control to the opposite air conditioning pack
- Control two zone trim air control channels
- Control their related air conditioning pack ram air actuators
- Give maintenance crews automatic built in test equipment (BITE) that
isolates faults to the line replaceable unit (LRU) level
Location
The controllers are in the EE compartment in the transverse racks
Training Information Point
The pack/zone temperature controllers are electrostatic discharge
sensitive (ESDS) devices. Use ESDS safe handling techniques.
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DISTRIBUTION - GENERAL DESCRIPTION
General
Ventilation
The A/C distribution system supplies conditioned air to the passenger and
flight compartments.
The ventilation system uses differential pressure to pull air out of the
airplane. The air moves through overboard vents from the cabin, galley,
and the lavatory areas.
Main Air Distribution
Equipment Cooling System
The main air distribution system gets air from these sources:
The equipment cooling system removes heat from the equipment in the
main equipment centre and the flight compartment.
- Air conditioning packs
- Ground conditioned air
- Recirculation system
The main mix manifold collects and mixes air from any combination of
these sources.
Flight Compartment Distribution
The flight compartment gets conditioned air from the left pack or the mix
manifold. A duct on the left side of the airplane transmits the air. The flight
compartment has supply ducts and outlets to control the airflow at each
station.
Passenger Compartment Distribution
The passenger conditioned air distribution system gets air from the mix
manifold. The air goes through riser ducts and up sidewalls to an
overhead distribution duct. Outlets along the sidewalls and the center of
the ceiling divide the air for symmetrical supply.
Recirculation System
The recirculation system uses two fans to move air from the passenger
compartment to the mix manifold. This system reduces the amount of air
that the packs need to supply.
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RECIRCULATION SYSTEM – INTRODUCTION
Purpose
The recirculation system recirculates the conditioned air from the collector
shroud and distribution bay. This reduces the requirement for bleed air
from the engines for air conditioning to the cabins.
Recirculation
The recirculation system has these components in the distribution
compartment (aft of the forward cargo compartment):
- Recirculation air filters
- Recirculation fans
- Recirculation fan check valves
Access
Access is through the bulkhead in the aft section of the forward cargo
compartment.
Recirculation Air Filters
The recirculation air filters clean the air as it enters the recirculation
system. The filters cannot be bypassed. This maintains the quality of the
air in the air conditioning distribution system.
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EQUIPMENT COOLING SYSTEM - GENERAL
DESCRIPTION
General
The overboard exhaust valve lets exhaust air go overboard when the
airplane is on the ground (unpressurised). The exhaust air supplements
heating in the forward cargo compartment in flight (pressurised).
The equipment cooling system uses these two systems to remove heat
from equipment:
- Supply system (pushes air)
- Exhaust system (pulls air)
The supply system and the exhaust system use fans to move air. Each
system has a primary fan and an alternate fan.
The supply and exhaust fans move air through ducts and manifolds. The
ducts and manifolds connect to shrouds around the electronic and
electrical equipment. Low flow sensors monitor the ducts for cooling flow
conditions.
Supply
The supply fans push filtered air to these components:
- P1, P2, P3 (display units)
- P9 panel (FMC control display units)
- Equipment racks in the EE compartment
Exhaust
The exhaust fans pull air from these components:
- P1, P2, P3 (display units)
- P9 (FMC control display units)
- P6 (circuit breaker panel)
- P5 (control and indication)
- P8 (center aisle stand)
- Equipment racks in the EE compartment
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PRESSURIZATION CONTROL - GENERAL
DESCRIPTION
Purpose
At high altitudes the air is too thin to sustain life. The airplane
pressurization system keeps the cabin air density adequate to sustain life.
General Description
The system controls the position of the outflow valve to control cabin
pressure. The air conditioning packs force air into the airplane/pressure
vessel (cabin).The pressurization system controls the rate at which the air
flows out of the cabin. This maintains a safe cabin pressure.
The pressurization control systems are designed for a nominal operating
pressure of 7.8-8.35 psid with a maximum operating pressure of 8.45 psid.
Safety relief valves protect the fuselage structure from overpressure or
negative pressure. They are set to open and release pressure at 8.65 psid
or -1.0 psid.
Automatic Pressurization Control
In the automatic mode of operation, the system uses a redundant system
of digital pressure controllers to schedule cabin pressurization through all
phases of flight. The active pressure controller keeps cabin altitude at a
safe, comfortable pressure altitude (8,000 ft ISA maximum).
The pressure controllers are line replaceable units and incorporate
standard front face BITE.
Manual Pressurization Control
In the manual mode of operation, the flight crew has direct control of the
outflow valve from the P5 panel.
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COMPONENT LOCATION
General
The control panel is on the right side of the P5-6 panel.
The No. 1 Cabin Pressure Controller (CPC) is on the E2 rack.
The No. 2 CPC is on the E4 rack.
The outflow valve is on the aft right fuselage skin, below the aft service
door.
There are two safety relief valves. One is inboard of the outflow valve. The
other is outboard of the outflow valve.
The negative pressure relief valve is on the aft right fuselage skin, forward
of the outflow valve.
The cabin altitude warning switch is on the ceiling of the forward EE
compartment. Access is through the lower nose access door.
The cabin altitude warning horn is in the aural warning module.
The module is on the right side of the pilots' control stand.
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CABIN PRESSURE CONTROL MODULE AND
CABIN
ALTITUDE PANEL
Purpose
The cabin pressure control module and cabin altitude panel let the crew
monitor and control the pressurization system.
The control panel has these parts:
A three position toggle switch controls the aft outflow valve when in the
manual mode. It has three positions:
- CLOSE
- NEUTRAL
- OPEN
- Cabin pressure control module
- System status lights
- Pressure indication panel
It is spring loaded to the neutral position.
There are four system status lights above the control module:
Location
The cabin pressure control module is on the P5-6 panel. The system
status lights are above the module. The cabin altitude panel (P5-16) is
next to the module.
- AUTO FAIL
- OFF SCHED DESCENT
- ALTN
- MAN
Cabin Pressure Control Module – General
The cabin pressure control module has these controls:
- Mode selector
- Landing altitude selector with display
- Flight altitude selector with display
- Aft outflow valve position indicator
- Manual control toggle switch
The mode selector has three positions. They set these system modes of
operation:
- AUTO for automatic operation
- ALT for alternate automatic operation
- MAN for manual control
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AIR CONDITIONING - GENERAL DESCRIPTION 600/700
Equipment Cooling Panel
General
The supply and exhaust fan switches are on the equipment cooling panel.
The flight compartment panels let you control the air conditioning system.
Air-conditioning Control Panels
Cabin Pressure Selector Panel/Cabin altitude Panel
These flight compartment panels on the P5 forward overhead panel let
you control the air conditioning subsystems:
These controls and indications are on the cabin pressure control panel:
- Landing altitude selector
- Flight altitude selector
- Mode selector
- Outflow valve position indicator
- Outflow valve switch
- Cabin differential pressure indicator
- Cabin rate of climb indicator
- Altitude horn cut-out switch
- Cabin temperature panel
- Air conditioning/bleed air controls panel
- Equipment cooling panel
- Cabin pressure control panel
- Cabin altitude panel
Cabin Temperature Panel
These controls and indications are on the cabin temperature panel:
- Control cabin temperature control
- Passenger cabin temperature control
- Temperature indication and selection
- Duct overheat indication
- Air mix valve position indication
Air Conditioning/Bleed Air Controls Panel
These controls and indications are on the air conditioning panel:
- Ram air inlet door indication
- Recirculation fan switch
- Cooling pack switches
- Pack overheat indication
- Pack reset push button
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COOLING - GENERAL DESCRIPTION
General
Primary Heat Exchanger
The cooling system uses these components and systems to
cool the bleed air:
The primary heat exchanger receives bleed air from the flow control
shutoff valve. As the bleed air goes through the heat exchanger, ram air
removes heat. The cooled bleed air goes to the compressor section of the
air cycle machine.
- Air conditioning/bleed air controls panel
- Flow control shutoff valve
- Heat exchangers (2)
- Air cycle machine
- Ram air system
- Low limit (35F) system
- Water separator
Air cycle machine
The air cycle machine is a three-wheel air bearing air cycle machine.
Cooled bleed air from the primary heat exchanger enters the air cycle
machine and is compressed. The compressed air then goes to a
secondary heat exchanger and back to the air cycle machine. The bleed
air is then rapidly expanded and goes to a condenser.
Air Conditioning/Bleed Air Controls Panel
Secondary Heat Exchanger
The air conditioning/bleed air controls panel gives control and indications
of the cooling system. These are the controls and indications of the
cooling system:
The secondary heat exchanger receives compressed air from the air cycle
machine. As the air goes through the heat exchanger, ram air removes
heat. After the compressed air is cooled, it goes through a water extractor
duct and back to the air cycle machine.
- RAM DOOR FULL OPEN Lights
- L/R PACK switches
- PACK TRIP OFF Lights
- TRIP RESET button
Ram Air System
The ram air system controls the quantity of outside ambient air that flows
through the heat exchangers.
Flow Control Shutoff Valve
Low Limit (35F) System
Bleed air from the pneumatic system supplies bleed air to the flow control
shutoff valve. The valve controls the flow of bleed air into the pack. After
the bleed air goes through the flow control shutoff valve it enters the
primary heat exchanger.
The low limit (35F) system keeps the air temperature into the water
separator at a temperature of 35F.
Water Separator
The water separator collects and removes moisture from the air before it
goes into the distribution system.
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COOLING -­‐ FUNCTIONAL DESCRIPTION Functional Description
The turbine section uses rapid expansion to decrease the temperature of
bleed air.
The cold bleed air then goes into the water separator.
While the cold bleed air goes through the water separator, moisture is
removed.
This moisture goes to the water spray nozzle. The water spray nozzle
sprays the water into the ram air duct.
If the temperature of the cold bleed air in the water separator goes below
35F, the low limit 35F system adds partially cool bleed air to cold bleed air
in the low pressure water separator mix muff. This heats the air and
prevents ice in the water separator.
After the water separator, the cold bleed air goes to the mix chamber. The
mix chamber adds hot bleed air from the hot side of the air mix valve.
The Flow Control Shutoff Valve (FCSOV) gets hot bleed air from the
pneumatic manifold. The flow control shutoff valve controls the flow of hot
bleed air to the primary heat exchanger and the hot side of the air mix
valve. A hot air connection downstream of the FCSOV supplies hot bleed
air to the turbine case. This prevents ice in the turbine case.
The ram air system controls the flow of ram air to the primary and
secondary heat exchangers.
These are the ram air system components:
- Ram air control temperature sensor
- Ram air inlet controller
- Ram air inlet actuator
- Ram air inlet deflector door
- Ram air inlet modulation panels
- Impeller fan
- Fan bypass check valve
When bleed air goes through the primary heat exchanger, ram air
removes some of the heat. This partially cool bleed air goes to the cool
side of the air mix valve.
From the air mix valve, partially cool bleed air goes to the compressor
section of the air cycle machine. The compressor section increases the
pressure and temperature of the partially cool bleed air. This compressed
air goes to the secondary heat exchanger.
When the compressed air goes through the secondary heat exchanger,
ram air removes some of the heat. This bleed air goes to the turbine
section of the air cycle machine.
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TEMPERATURE CONTROL – OPERATION
General
Cabin Temperature Controller
The controls and indications for the temperature control system are on the
temperature control panel. The Cabin Temperature Controller (CPC) is
located in the E/E compartment
The Cabin Temperature Controller (CTC) controls the temperature of
conditioned air for the cabin areas.
Controls
Location
The selector for the flight compartment is on the left side (CONT CABIN).
The passenger compartment temperature selector is on the right side
(PASS CABIN). The passenger compartment has an AIR TEMP selector
in the centre.
The CTC is in the EE compartment on the E4-1 rack.
Physical Description It has BITE controls and instructions on the front
face.
The temperature selectors are spring-loaded to the OFF position. The
selector has a MANUAL COOL and MANUAL WARM position. These
positions are momentary positions. You must hold the selector in these
positions for manual operation.
Air temperature is measured by the temperature bulbs in the passenger
cabin and the passenger supply duct. The air temperature (AIR TEMP)
selector lets you select which bulbs to monitor.
Indications
The left and right air conditioning packs have an air mix valve position
indicator.
This shows the proportion of the hot and cold air in the air-streams.
The temperature (TEMP) indicator shows the passenger compartment air
temperature or the supply duct air temperature.
The DUCT OVERHEAT light gives indication when the duct temperature is
too high. There is a DUCT OVERHEAT light for the flight and passenger
compartment supply ducts.
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TEMPERATURE CONTROL - CABIN TEMP
SENSOR Purpose
The cabin temperature sensor assembly provides a flow of filtered air over
a cabin temperature sensor and bulb. The cabin temperature sensor
provides compartment temperature data to the cabin temperature
controller.
Location
The flight compartment cabin temperature sensor assembly is in the
ceiling of the flight compartment.
Physical Description
These components are part of the cabin temperature sensor assembly:
- Temperature sensor
- Inlet grille
- Air filter
- Temperature sensor fan
Functional Description
The fan pulls in cabin air through the inlet grille and air filter. The
temperature sensor sends the air temperature to the Cabin Temperature
Controller (CTC).
The CTC uses this data to compare with the selected temperature.
The flight compartment temperature sensor fan comes on when 115vac is
available and the left pack switch is in AUTO or HIGH.
The passenger compartment temperature sensor fan comes on when
115vac is available.
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Ventilation
DISTRIBUTION - GENERAL DESCRIPTION –
COMPONENET
General Description
The ventilation system uses differential pressure to pull air out of the
airplane. The air moves through overboard vents from the cabin, galley
and the lavatory areas.
The distribution system has the following sub-systems.
Equipment Cooling System
Main Air Distribution
The equipment cooling system removes heat from the equipment in the
main equipment centre and the flight compartment.
The main air distribution system gets air from these sources:
Distribution Component Location
- Air conditioning packs
- Ground conditioned air
- Recirculation system
The distribution system has these components in the distribution
compartment (aft of the forward cargo compartment):
- Main distribution manifold
- Recirculation fan
- Ground conditioned air connection
The main distribution manifold collects and mixes air from any combination
of the sources.
Flight Compartment Conditioned Air Distribution
The equipment cooling system has components in these areas:
The flight compartment gets conditioned air from the let pack and the mix
manifold. The air goes through a duct on the left side of the airplane. The
flight compartment has supply ducts and outlets to control the air flow at
each station.
- EE compartment
- Forward equipment compartment
- Flight compartment
Passenger Compartment Conditioned Air Distribution
Cooling System Component Location
The Passenger conditioned air distribution gets air from the mix manifold.
The air goes through riser ducts and up side walls to an overhead
distribution duct.
The two air conditioning packs are in the air conditioning compartments.
The air conditioning compartments are on the left and right sides of the
keel beam in the wing-to-body area. Access is from the bottom of the
fuselage.
Recirculation System
The recirculation system uses a fan to move air from the passenger
compartment to the main distribution manifold. This system reduces the
amount of air necessary for the packs to supply.
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RECIRCULATION SYSTEM – INTRODUCTION
Purpose
The recirculation system supplies air for ventilation. The use of cabin air
for ventilation decreases the use of air from the engine bleed system.
General Description
The recirculation system collects cabin air to use with pack air in the
distribution system. The distribution system supplies air to the passenger
compartment area.
The passenger cabin air moves through these recirculation components:
- Collector shroud
- Air filter
- Fan
- Check valve
Location
The recirculation components are in the distribution compartment.
Operation
The recirculation fan is enabled when you move the RECIRC FAN switch
to the AUTO position. Recirculation fan operation depends on air
conditioning pack operation.
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AIR CONDITIONING - FUNCTIONAL
DESCRIPTION
General
The usual control for the left pack makes sure that it supplies air at a
temperature that gives the necessary cooling for the flight compartment.
These are the primary parts of the Air Conditioning (A/C) system that have
an effect on the supply of fresh air or the recirculation of conditioned air:
The control for the right pack makes sure that it supplies air at a
temperature that gives the necessary cooling for the passenger
compartment.
- Pack flow control
- Pack cooling system
- Zone temperature control
- Recirculation
- Air distribution
Zone Temperature Control
This part of the A/C system controls the temperature in the two zones, the
flight compartment and the passenger cabin. The temperature changes
are made by the mix valve with signals from the temperature regulator.
The primary parts of the A/C system have these functions:
- Control fresh air flow for airplane pressurization and ventilation
- Control the flight compartment and passenger cabin temperature
- Recirculate cabin air for ventilation
Recirculation
This part of the A/C system recycles 50 percent of the cabin air for
ventilation purposes. This reduces the quantity of fresh air necessary from
the pneumatic system for ventilation. The recirculation fan and filter are
the primary components.
Pack Flow Control
This part of the A/C system controls the quantity of fresh air that goes into
the airplane. The control is by a flow control and shutoff valve.
The quantity of fresh air necessary for ventilation is more than for
pressurization. The ventilation quantity is based on a fixed value for the
crew and allowable leakage, and on the number of passenger seats.
Usually, the left and right flow control systems provide the same quantity
of fresh air. Fresh air flow changes when airplane conditions change.
See the pack flow control section for more information about the pack flow
control systems.
Pack Cooling System
This part of the A/C system removes water as necessary and controls the
temperature of the fresh air before it goes into the air distribution part of
the air conditioning system. The primary components are the left and right
packs.
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ATA 23-00-00
COMMUNICATIONS
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CONTENTS
ATA 23 – COMMUNICATIONS
FLIGHT INTERPHONE SYSTEM ...................................................................................................................................................................................................................... 4
GENERAL ............................................................................................................................................................................................................................................................... 4
FLIGHT CREW INTERFACES .................................................................................................................................................................................................................................... 4
OTHER COMPONENT AND SYSTEM INTERFACES .................................................................................................................................................................................................... 4
AUDIO CONTROL PANEL .................................................................................................................................................................................................................................. 6
PURPOSE ................................................................................................................................................................................................................................................................ 6
CONTROLS ............................................................................................................................................................................................................................................................. 6
MICROPHONE SELECTOR SWITCHES ...................................................................................................................................................................................................................... 6
RECEIVER SWITCHES ............................................................................................................................................................................................................................................. 6
FILTER SWITCH ...................................................................................................................................................................................................................................................... 6
FLIGHT CREW CALL SYSTEM / CABIN INTERPHONE - .......................................................................................................................................................................... 8
GENERAL DESCRIPTION ................................................................................................................................................................................................................................. 8
LOCATION .............................................................................................................................................................................................................................................................. 8
SERVICE INTERPHONE SYSTEM .................................................................................................................................................................................................................. 10
GENERAL DESCRIPTION ................................................................................................................................................................................................................................ 10
JACK LOCATIONS ................................................................................................................................................................................................................................................. 10
PASSENGER ADDRESS SYSTEM .................................................................................................................................................................................................................... 12
GENERAL DESCRIPTION ................................................................................................................................................................................................................................ 12
RADIO COMMUNICATION PANEL ............................................................................................................................................................................................................... 14
GENERAL ............................................................................................................................................................................................................................................................. 14
CONTROLS AND INDICATIONS .............................................................................................................................................................................................................................. 14
VOICE RECORDER SYSTEM ........................................................................................................................................................................................................................... 16
GENERAL DESCRIPTION ............................................................................................................................................................................................................................... 16
COMPONENTS ...................................................................................................................................................................................................................................................... 16
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FLIGHT INTERPHONE SYSTEM
General
The remote electronic unit (REU) sends audio signals to the headsets and
to the flight interphone speakers.
The Remote Electronics Unit (REU) and the Audio Control Panel (ACP)
control the audio signals to and from the flight crew. The REU also
controls the communication with the service interphone and related
electronics equipment.
Other Component and System Interfaces
The REU connects to these other components:
During a system failure, emergency operation bypasses all active system
circuitry and maintains airplane to ground station communication.
- Communications radios; the REU sends Push-To-Talk (PTT) and
microphone audio to the transceivers and receives audio back from them
- Navigation receivers; the REU receives voice and Morse code
identification tones.
Flight Crew Interfaces
This system description shows the captain's system. Interfaces and
components for other flight crew stations are similar.
The flight crew uses microphone (mic) switches on these components to
send audio to the REU:
The flight interphone system also has an interface with these other
systems:
- Passenger addresses system; lets the flight crew make announcements
to passengers
- Service interphone system; lets the flight crew speak with attendants and
service personnel
- Voice recorder; records the flight crew microphone and receive audio
- Ground Proximity Warning Computer (GPWC); lets flight crew monitor
warning signals
- Traffic Alert and Collision Avoidance system (TCAS); lets the flight crew
monitor TCAS signals
- Flight Control Computer (FCC); gives discrete signals to the REU.
This signal activates an altitude alert tone generator
- Control wheel
- ACP
- Hand microphone
A microphone on these components lets the flight crew speak on the flight
interphone system:
- Oxygen mask
- Headset
- Hand mic
The flight crew uses the audio control panels for these functions:
- Listen to the communication and navigation receivers
- Adjust the volume of the received audio
- Select a transmitter and microphone
- Key the microphone
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The transmitter selectors (except PA) have call lights in the switch.
The call lights come on when the flight crew get any one of these calls:
AUDIO CONTROL PANEL
Purpose
- SELCAL on a VHF or HF radio
- ACARS call from the ACARS MU
- Ground crew call (FLT light)
- Flight crew call (CABIN light)
The flight crew uses the Audio Control Panels (ACPs) to control audio for
the communication and navigation systems. Each ACP controls one
station.
Controls
To turn off the call light, the flight crew selects the system and sends a
PTT to that system.
When you push a PTT switch, the microphone audio and PTT signals go
to the system set by the selector switches.
When the ACP initially gets power, the flight interphone system is active.
These are the controls on the ACP:
- Transmitter selectors
- Receiver switches
- Radio-Intercom PTT switch
- Filter switch
- ALT-NORM switch
Receiver Switches
Push the receiver switch (push-on, push-off) to listen to communication or
navigation system audio. Turn it to adjust the volume. You can monitor
any combination of systems at any time.
Microphone Selector Switches
The flight interphone system gets audio from these microphones:
CAUTION: RECEIVER SWITCHES ARE PUSH-ON/PUSH OFF TYPE.
THE KNOB IS IN WHEN THE CONTROL IS ON, AND OUT WHEN OFF.
DO NOT PULL THESE KNOBS, OR YOU WILL DAMAGE THEM.
- Boom
- Oxygen mask
- Hand-held
Radio-Intercom PTT Switch
You push a transmitter selector to select a communication transmitter or
system. You can select only one system at a time.
When you push a transmitter selector, this happens:
The radio-intercom PTT switch is a three position switch with momentary
contacts in the R/T and I/C position. In the R/T position, the microphone
audio and PTT signals go to the communication system set by the
transmitter selectors. In the I/C position, the boom or mask microphone
jacks connect to the flight interphone system. The radio-intercom PTT
switch is in parallel with the PTT switch on the control wheel.
- The selector switch light comes on
- The received audio comes on at the volume set by the receiver volume
control
- The microphone audio and PTT signals are enabled for that system
Filter Switch
The filter switch controls the filter that processes the navigation audio you
Receive.
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Figure 2
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FLIGHT CREW CALL SYSTEM / CABIN
INTERPHONE -
Aural and visual indications from the system tell the flight and cabin crew
to use the cabin interphone.
GENERAL DESCRIPTION
Flight Compartment to Attendant Stations
Handsets
You push the ATTEND switch on the passenger signs panel to call the
attendant stations from the flight compartment. When you make this call,
these are the indications in the passenger cabin:
The attendants use handsets to speak with each other. They also use
them to make announcements on the Passenger Address (PA) system.
- The pink light on the forward and the aft exit locator signs comes on
- The passenger address system sends a HI/LO chime to the cabin
speakers
Physical Description
The interphone handset is like a telephone handset. It has these features:
Attendant Station to Flight Compartment
- Earpiece speaker
- Microphone
- Push-button switches
You use the handset to call the flight compartment from an attendant
station.
When you make this call, these are the indications in the flight
compartment:
Location
There is a handset at the forward attendant's panel and at the aft
attendant's panel in the passenger compartment.
- The CALL light on the passenger signs panel comes on
- The aural warning module makes a HI chime
General
Attendant Station to Attendant Station
The flight crew call system lets the flight crew and attendants call each
other.
These are the calls that can be made:
You use the handset to call one attendant station from another attendant
station. When you make this call, these are the indications in the
passenger cabin:
- The pink light on the exit locator sign comes on at the other attendant
station
- The passenger address system sends a HI/LO chime to the cabin
speaker
- Flight compartment to attendant stations
- Attendant station to flight compartment
- Attendant station to attendant station
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Figure 3
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SERVICE INTERPHONE SYSTEM
Jack Locations
GENERAL DESCRIPTION
The service interphone system is for the:
These locations have service interphone jacks:
- P19 external power panel
- Electronic equipment compartment
- Fuelling station, behind the access door on the right wing
- Right wheel well, on the forward wheel well fairing exterior
- Left wheel well, on the forward wheel well fairing exterior
- Aft cabin, on the ceiling above the attendant station
- APU service area, adjacent to the 48 section access door
- Flight crew
- Attendants
- Ground crew
The flight crew selects the service interphone function from the Audio
Control
Panel (ACP). Flight interphone microphones send audio to the Remote
Electronics Unit (REU). Flight interphone headsets and speakers get audio
from the REU.
The flight crew can also use a handset to talk on the service interphone
system.
The handset jack connects to the system without ACP control.
The attendants operate a handset to connect into the system. An
attendant panel connects the handset to the REU.
The ground crew microphones connect into the system through the
service interphone switch. You must turn on the service interphone switch
to operate the system from the service station jacks. The headset gets
audio from the REU.
The REU does these functions:
- Combines audio from the microphones
- Amplifies the audio signal
- Sends audio to handsets, headsets, and speakers
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Figure 4
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PASSENGER ADDRESS SYSTEM
GENERAL DESCRIPTION
The Passenger Address (PA) amplifier puts a priority on the audio inputs
from these places:
- Pilots
- Attendants
- Pre-Recorded Announcement and boarding Music reproducer (PRAM)
The PA amplifier amplifies the audio input with the highest priority and
sends the signal to these places:
- Passenger cabin and lavatory speakers
- Passenger entertainment system
- Remote Electronics Unit (REU)
The amplified audio to the REU goes through muting circuits for the
forward and aft attendant speakers. When an attendant makes an
announcement, the muting circuits stop the audio for that attendants
speaker.
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Figure 5
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RADIO COMMUNICATION PANEL
General
The radio communication panel provides these:
- Active/Standby frequency selection
- HF sensitivity control
- Mode selection to the HF transceiver
- Test initiation to the VHF transceivers
Controls and Indications
At power up, RCP -1 controls VHF-1. RCP 2 controls VHF 2. RCP 3
controls VHF 3.
Any radio communication panel can control any transceiver. Push the
radio tuning switch to select the transceiver for that RCP. The light above
the switch comes on. Each radio communication panel can tune only one
transceiver at a time.
When you select an off-side radio, two off-side tuning lights come on. One
light is on the radio communication panel that you use to make the
selection. The other light is on the on-side radio communication panel of
the radio you select. Set the frequency in the standby frequency indicator.
Turn the frequency selectors to set the frequency. The first digit is always
1. The outer knob sets the second two digits (10 MHz and 1 MHz) in 1
MHz increments. The inner 25KHz increments.
Push the frequency transfer switch to change the active and standby
frequencies.
Push the OFF switch to stop the operation of the radio communication
panel.
The switch shows white when it is off.
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Figure 6
RADIO COMMUNICATION PANEL
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VOICE RECORDER SYSTEM
GENERAL DESCRIPTION
The voice recorder unit makes a continuous record of flight crew
communication and flight compartment sounds. It erases the
communication data automatically so that the memory stores only recent
audio.
The voice recorder unit keeps the last 120 minutes of communication data
in memory.
The voice recorder unit receives audio from the remote electronics unit
and the area microphone. The area microphone is in the cockpit voice
recorder panel.
Components
The voice recorder system has these components:
- Cockpit voice recorder panel
- Voice recorder unit-located on E6 rack in aft cargo compartment
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VOICE RECORDER SYSTEM - GENERAL DESCRIPTION
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Training Manual
B 737-600/700/800
ATA 38
Water and Waste
Level 2
Lufthansa
Technical Training GmbH
Lufthansa Base
REFRESHER COURSE
FOR TRAINING PURPOSES ONLY
Issue: July 1999
For Training Purposes Only
 Lufthansa 1995
AMET Ltd.
For training purposes and internal use only.
Copyright by Lufthansa Technical Training GmbH.
All rights reserved. No parts of this training
manual may be sold or reproduced in any form
without permission of:
Lufthansa Technical Training GmbH
Lufthansa Base Frankfurt
D-60546 Frankfurt/Main
Tel. +49 69 / 696 41 78
Fax +49 69 / 696 63 84
Lufthansa Base Hamburg
Weg beim Jäger 193
D-22335 Hamburg
Tel. +49 40 / 5070 24 13
Fax +49 40 / 5070 47 46
REFRESHER COURSE
FOR TRAINING PURPOSES ONLY
AMET Ltd.
TABLE OF CONTENTS
ATA 38 WATER AND WASTE . . . . . . . . . . . . . . . . .
1
38-00
WATER AND WASTE - INTRODUCTION . . . . . . . . . . . . . . .
GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . .
FUNCTIONAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . .
2
4
6
38-10
POTABLE WATER - INTRODUCTION . . . . . . . . . . . . . . . . .
8
38-10
POTABLE WATER - INTRODUCTION . . . . . . . . . . . . . . . . . .
FUNCTIONAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . .
10
12
38-1 1
POTABLE WATER SERVICE PANEL . . . . . . . . . . . . . . . . . .
FILL/OVERFLOW VALVE AND CONTROL CABLE . . . . .
WATER TANK DRAIN VALVE AND CONTROL CABLE .
WATER TANK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
LAVATORY WATER SUPPLY SHUTOFF VALVE . . . . . . .
FORWARD LAVATORY DRAIN VALVE . . . . . . . . . . . . . . .
LAVATORY FAUCET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
14
16
18
20
22
24
26
38-13
WATER HEATER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WATER HEATER - FUNCTIONAL DESCRIPTION . . . . .
28
30
38-14
WATER QUANTITY INDICATION SYSTEM - INTRO . . . . .
WATER QUANTITY TRANSMITTER . . . . . . . . . . . . . . . . .
WATER QUANTITY INDICATOR . . . . . . . . . . . . . . . . . . . .
FUNCTIONAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . .
32
34
36
38
38-42
WATER TANK PRESSURIZATION SYSTEM - INTRO . . . .
COMPONENT LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . .
AIR COMPRESSOR / INLET AIR FILTER . . . . . . . . . . . . .
PRESSURE LIMIT SWITCH . . . . . . . . . . . . . . . . . . . . . . . .
AIR COMPRESSOR FUNCTIONAL DESCRIPTION . . . .
PRESSURE REGULATOR . . . . . . . . . . . . . . . . . . . . . . . . . .
CHECK VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
IN-LINE AIR FILTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PRESSURE RELIEF VALVE . . . . . . . . . . . . . . . . . . . . . . . .
40
42
44
46
48
50
52
54
56
38-30
WASTE DISPOSAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
58
38-31
GRAY WATER SYSTEM - DRAIN MAST . . . . . . . . . . . . . . .
60
REFRESHER COURSE
38-32
VACUUM WASTE SYSTEM - INTRODUCTION . . . . . . . . . .
COMPONENTLOCATION - LAVATORY . . . . . . . . . . . . . .
COMPONENT LOCATION - AFT CARGO COMPRTMNT
WASTE SERVICE PANEL - COMPONENTS . . . . . . . . . .
FLUSH SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
VACUUM TOILET ASSEMBLY . . . . . . . . . . . . . . . . . . . . . .
FLUSH CYCLE - OPERATION . . . . . . . . . . . . . . . . . . . . . .
VACUUM BLOWER AND FILTER . . . . . . . . . . . . . . . . . . . .
VACUUM CHECK VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . .
VACUUM BLOWER BAROMETRIC SWITCH . . . . . . . . .
VACUUM BLOWER - FUNCTIONAL DESCRIPTION . . .
LIQUID SEPARATOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WASTE TANK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WASTE DRAIN BALL VALVE AND PULL ROD . . . . . . . .
WASTE DRAIN VALVE ASSEMBLY . . . . . . . . . . . . . . . . . .
WASTE TANK RINSE FITTING ASSEMBLY . . . . . . . . . .
WASTE TANK RINSE FILTER . . . . . . . . . . . . . . . . . . . . . . .
WASTE TANK RINSE NOZZLE . . . . . . . . . . . . . . . . . . . . . .
DRAIN LINE BLOCKAGE REMOVAL VALVE . . . . . . . . . .
FUNCTIONAL DESCRIPTION - MECHANICAL . . . . . . . .
62
64
66
68
70
72
74
76
78
80
82
84
86
88
90
92
94
96
98
100
38-33
WASTE TANK QUANTITY INDICATION . . . . . . . . . . . . . . . .
WASTE TANK POINT LEVEL SENSOR . . . . . . . . . . . . . .
WASTE TANK CONTINUOUS LEVEL SENSOR . . . . . . .
LOGIC CONTROL MODULE . . . . . . . . . . . . . . . . . . . . . . . .
ATTENDANT PANEL WASTE QUANTITY INDICATOR .
FUNCTIONAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . .
LOGIC CONTROL MODULE . . . . . . . . . . . . . . . . . . . . . . . .
102
104
106
108
110
112
114
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Page: i
AMET Ltd.
TABLE OF FIGURES
Figure 1
Figure 2
Figure 3
Figure 4
Figure 5
Figure 6
Figure 7
Figure 8
Figure 9
Figure 10
Figure 11
Figure 12
Figure 13
Figure 14
Figure 15
Figure 16
Figure 17
Figure 18
Figure 19
Figure 20
Figure 21
Figure 22
Figure 23
Figure 24
Figure 25
Figure 26
Figure 27
Figure 28
Figure 29
Figure 30
Figure 31
Figure 32
Figure 33
Figure 34
Figure 35
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
General Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Functional Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Functional Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Potable Water Service Panel . . . . . . . . . . . . . . . . . . . . . . . .
Water Tank Drain Valve and Control Cable . . . . . . . . . . . .
Water Tank . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Lavatory Water Supply Shutoff Valve . . . . . . . . . . . . . . .
Lavatory Drain Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Lavatory Faucet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Water Heater . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Water Heater - Functional Description . . . . . . . . . . . . . .
Water Quantity Indication System - Introduction . . . . . .
Water Quantity Transmitter and Adapter Cable . . . . . . .
Water Quantity Indicator . . . . . . . . . . . . . . . . . . . . . . . . . .
Water Quantity Indication - Functional Description . . .
Water Tank Pressurization - Introduction . . . . . . . . . . . .
Water Tank Pressurization - Component Location . . . . .
Air Compressor and Inlet Air Filter . . . . . . . . . . . . . . . . . .
Pressure Limit Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Air Compressor Functional Description . . . . . . . . . . . . . .
Pressure Regulator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Check Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
In-Line Air Filter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Pressure Relief Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Gray Water System - Drain Mast . . . . . . . . . . . . . . . . . . .
Vacuum Waste System - Introduction . . . . . . . . . . . . . . .
Vacuum Waste - Component Locations - Lavatory . . . .
Component Locations - Aft Cargo Compartment . . . . . .
Vacuum Waste - Waste Service Panel Components . .
Vacuum Waste - Flush Switch . . . . . . . . . . . . . . . . . . . . .
Vacuum Waste - Vacuum Toilet Assembly . . . . . . . . . . .
REFRESHER COURSE
3
5
7
9
11
13
15
19
21
23
25
27
29
31
33
35
37
39
41
43
45
47
49
51
53
55
57
59
61
63
65
67
69
71
73
Figure 36
Figure 37
Figure 38
Figure 39
Figure 40
Figure 41
Figure 42
Figure 43
Figure 44
Figure 45
Figure 46
Figure 47
Figure 48
Figure 49
Figure 50
Figure 51
Figure 52
Figure 53
Figure 54
Figure 55
Figure 56
Vacuum Waste - Flush Cycle - Operation . . . . . . . . . . . .
Vacuum Waste - Vacuum Blower and Filter . . . . . . . . . .
Vacuum Waste - Vacuum Check Valve . . . . . . . . . . . . . .
Vacuum Waste - Vacuum Blower Barometric Switch . .
Vacuum Waste - Vacuum Blower - Funktional Description
Vacuum Waste - Liquid Separator . . . . . . . . . . . . . . . . . .
Vacuum Waste - Waste Tank . . . . . . . . . . . . . . . . . . . . . .
Vacuum Waste - Waste Drain Ball Valve and Pull Rod .
Vacuum Waste - Waste Drain Valve Assembly . . . . . . .
Vacuum Waste - Waste Tank Rinse Fitting Assembly . .
Vacuum Waste - Waste Tank Rinse Filter . . . . . . . . . . . .
Vacuum Waste - Waste Tank Rinse Nozzle . . . . . . . . . .
Waste Tank Drain Line Blockage Removal Valve . . . . .
Vacuum Waste - Functional Description - Mechanical .
Waste Tank Quantity Indication - Introduction . . . . . . . .
Waste Tank Point Level Sensor . . . . . . . . . . . . . . . . . . . .
Waste Tank Continuous Level Sensor . . . . . . . . . . . . . . .
Waste Tank Quantity Indication - Logic Control Module
Attendent’s Panel Waste Quantity Indicator . . . . . . . . . .
Waste Tank Quantity Indication - Functional Description
Logic Control Module - Training Information Point . . . . .
FOR TRAINING PURPOSES ONLY
75
77
79
81
83
85
87
89
91
93
95
97
99
101
103
105
107
109
111
113
115
Page: ii
AMET Ltd.
B737-600/700/800
w
38-00
ATA 38
WATER AND WASTE
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
INTRODUCTION
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 1
AMET Ltd.
B737-600/700/800
38-00
38-00
WATER AND WASTE - INTRODUCTION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
INTRODUCTION
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 2
AMET Ltd.
B737-600/700/800
38-00
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
INTRODUCTION
Figure 1
25 Jun 99
REFRESHER COURSE
FRA US/E br
Introduction
FOR TRAINING PURPOSES ONLY
Page: 3
AMET Ltd.
B737-600/700/800
38-00
GENERAL DESCRIPTION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
GENERAL DESCRIPTION
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 4
AMET Ltd.
B737-600/700/800
38-00
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
GENERAL DESCRIPTION
Figure 2
25 Jun 99
REFRESHER COURSE
FRA US/E br
General Description
FOR TRAINING PURPOSES ONLY
Page: 5
AMET Ltd.
B737-600/700/800
38-00
FUNCTIONAL DESCRIPTION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
GENERAL DESCRIPTION
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 6
AMET Ltd.
B737-600/700/800
38-00
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
GENERAL DESCRIPTION
Figure 3
25 Jun 99
REFRESHER COURSE
FRA US/E br
Functional Description
FOR TRAINING PURPOSES ONLY
Page: 7
AMET Ltd.
B737-600/700/800
38-10
38-10
POTABLE WATER - INTRODUCTION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 8
AMET Ltd.
B737-600/700/800
38-10
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 4
25 Jun 99
REFRESHER COURSE
FRA US/E br
Introduction
FOR TRAINING PURPOSES ONLY
Page: 9
AMET Ltd.
B737-600/700/800
38-10
38-10
POTABLE WATER - INTRODUCTION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 10
AMET Ltd.
B737-600/700/800
38-10
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 5
25 Jun 99
REFRESHER COURSE
FRA US/E br
Introduction
FOR TRAINING PURPOSES ONLY
Page: 11
AMET Ltd.
B737-600/700/800
38-10
FUNCTIONAL DESCRIPTION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 12
AMET Ltd.
B737-600/700/800
38-10
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 6
25 Jun 99
REFRESHER COURSE
FRA US/E br
Functional Description
FOR TRAINING PURPOSES ONLY
Page: 13
AMET Ltd.
B737-600/700/800
38-1 1
38-1 1
POTABLE WATER SERVICE PANEL
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 14
AMET Ltd.
B737-600/700/800
38-1 1
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 7
25 Jun 99
REFRESHER COURSE
FRA US/E br
Potable Water Service Panel
FOR TRAINING PURPOSES ONLY
Page: 15
AMET Ltd.
B737-600/700/800
38-1 1
FILL/OVERFLOW VALVE AND CONTROL CABLE
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 16
AMET Ltd.
B737-600/700/800
38-1 1
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 17
AMET Ltd.
B737-600/700/800
38-1 1
WATER TANK DRAIN VALVE AND CONTROL CABLE
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 18
AMET Ltd.
B737-600/700/800
38-1 1
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 8
25 Jun 99
REFRESHER COURSE
FRA US/E br
Water Tank Drain Valve and Control Cable
FOR TRAINING PURPOSES ONLY
Page: 19
AMET Ltd.
B737-600/700/800
38-1 1
WATER TANK
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 20
AMET Ltd.
B737-600/700/800
38-1 1
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 9
25 Jun 99
REFRESHER COURSE
FRA US/E br
Water Tank
FOR TRAINING PURPOSES ONLY
Page: 21
AMET Ltd.
B737-600/700/800
38-1 1
LAVATORY WATER SUPPLY SHUTOFF VALVE
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 22
AMET Ltd.
B737-600/700/800
38-1 1
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 10
25 Jun 99
REFRESHER COURSE
FRA US/E br
Lavatory Water Supply Shutoff Valve
FOR TRAINING PURPOSES ONLY
Page: 23
AMET Ltd.
B737-600/700/800
38-1 1
FORWARD LAVATORY DRAIN VALVE
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 24
AMET Ltd.
B737-600/700/800
38-1 1
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 11
25 Jun 99
REFRESHER COURSE
FRA US/E br
Lavatory Drain Valve
FOR TRAINING PURPOSES ONLY
Page: 25
AMET Ltd.
B737-600/700/800
38-1 1
LAVATORY FAUCET
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 26
AMET Ltd.
B737-600/700/800
38-1 1
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 12
25 Jun 99
REFRESHER COURSE
FRA US/E br
Lavatory Faucet
FOR TRAINING PURPOSES ONLY
Page: 27
AMET Ltd.
B737-600/700/800
38-13
38-13
WATER HEATER
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 28
AMET Ltd.
B737-600/700/800
38-13
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 13
25 Jun 99
REFRESHER COURSE
FRA US/E br
Water Heater
FOR TRAINING PURPOSES ONLY
Page: 29
AMET Ltd.
B737-600/700/800
38-13
WATER HEATER - FUNCTIONAL DESCRIPTION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 30
AMET Ltd.
B737-600/700/800
38-13
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 14
25 Jun 99
REFRESHER COURSE
FRA US/E br
Water Heater - Functional Description
FOR TRAINING PURPOSES ONLY
Page: 31
AMET Ltd.
B737-600/700/800
38-14
38-14
WATER QUANTITY INDICATION SYSTEM - INTRODUCTION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 32
AMET Ltd.
B737-600/700/800
38-14
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 15
25 Jun 99
REFRESHER COURSE
FRA US/E br
Water Quantity Indication System - Introduction
FOR TRAINING PURPOSES ONLY
Page: 33
AMET Ltd.
B737-600/700/800
38-14
WATER QUANTITY TRANSMITTER
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 34
AMET Ltd.
B737-600/700/800
38-14
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 16
25 Jun 99
REFRESHER COURSE
FRA US/E br
Water Quantity Transmitter and Adapter Cable
FOR TRAINING PURPOSES ONLY
Page: 35
AMET Ltd.
B737-600/700/800
38-14
WATER QUANTITY INDICATOR
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 36
AMET Ltd.
B737-600/700/800
38-14
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 17
25 Jun 99
REFRESHER COURSE
FRA US/E br
Water Quantity Indicator
FOR TRAINING PURPOSES ONLY
Page: 37
AMET Ltd.
B737-600/700/800
38-10
FUNCTIONAL DESCRIPTION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
25 Jun 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 38
AMET Ltd.
B737-600/700/800
38-10
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 18
25 Jun 99
REFRESHER COURSE
FRA US/E br
Water Quantity Indication - Functional Description
FOR TRAINING PURPOSES ONLY
Page: 39
AMET Ltd.
B737-600/700/800
38-42
38-42
WATER TANK PRESSURIZATION SYSTEM - INTRODUCTION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 40
AMET Ltd.
B737-600/700/800
38-42
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 19
19 Jul 99
REFRESHER COURSE
FRA US/E br
Water Tank Pressurization - Introduction
FOR TRAINING PURPOSES ONLY
Page: 41
AMET Ltd.
B737-600/700/800
38-42
COMPONENT LOCATION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 42
AMET Ltd.
B737-600/700/800
38-42
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 20
19 Jul 99
REFRESHER COURSE
FRA US/E br
Water Tank Pressurization - Component Location
FOR TRAINING PURPOSES ONLY
Page: 43
AMET Ltd.
B737-600/700/800
38-42
AIR COMPRESSOR / INLET AIR FILTER
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 44
AMET Ltd.
B737-600/700/800
38-42
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 21
19 Jul 99
REFRESHER COURSE
FRA US/E br
Air Compressor and Inlet Air Filter
FOR TRAINING PURPOSES ONLY
Page: 45
AMET Ltd.
B737-600/700/800
38-42
PRESSURE LIMIT SWITCH
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 46
AMET Ltd.
B737-600/700/800
38-42
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 22
19 Jul 99
REFRESHER COURSE
FRA US/E br
Pressure Limit Switch
FOR TRAINING PURPOSES ONLY
Page: 47
AMET Ltd.
B737-600/700/800
38-42
AIR COMPRESSOR FUNCTIONAL DESCRIPTION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 48
AMET Ltd.
B737-600/700/800
38-42
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 23
19 Jul 99
REFRESHER COURSE
FRA US/E br
Air Compressor Functional Description
FOR TRAINING PURPOSES ONLY
Page: 49
AMET Ltd.
B737-600/700/800
38-42
PRESSURE REGULATOR
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 50
AMET Ltd.
B737-600/700/800
38-42
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 24
19 Jul 99
REFRESHER COURSE
FRA US/E br
Pressure Regulator
FOR TRAINING PURPOSES ONLY
Page: 51
AMET Ltd.
B737-600/700/800
38-42
CHECK VALVE
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 52
AMET Ltd.
B737-600/700/800
38-42
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 25
19 Jul 99
REFRESHER COURSE
FRA US/E br
Check Valve
FOR TRAINING PURPOSES ONLY
Page: 53
AMET Ltd.
B737-600/700/800
38-42
IN-LINE AIR FILTER
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 54
AMET Ltd.
B737-600/700/800
38-42
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 26
19 Jul 99
REFRESHER COURSE
FRA US/E br
In-Line Air Filter
FOR TRAINING PURPOSES ONLY
Page: 55
AMET Ltd.
B737-600/700/800
38-42
PRESSURE RELIEF VALVE
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 56
AMET Ltd.
B737-600/700/800
38-42
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
POTABLE WATER
Figure 27
19 Jul 99
REFRESHER COURSE
FRA US/E br
Pressure Relief Valve
FOR TRAINING PURPOSES ONLY
Page: 57
AMET Ltd.
B737-600/700/800
38-30
38-30
WASTE DISPOSAL
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 58
AMET Ltd.
B737-600/700/800
38-30
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 28
19 Jul 99
REFRESHER COURSE
FRA US/E br
Introduction
FOR TRAINING PURPOSES ONLY
Page: 59
AMET Ltd.
B737-600/700/800
38-31
38-31
GRAY WATER SYSTEM - DRAIN MAST
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 60
AMET Ltd.
B737-600/700/800
38-31
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 29
19 Jul 99
REFRESHER COURSE
FRA US/E br
Gray Water System - Drain Mast
FOR TRAINING PURPOSES ONLY
Page: 61
AMET Ltd.
B737-600/700/800
38-32
38-32
VACUUM WASTE SYSTEM - INTRODUCTION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 62
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 30
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste System - Introduction
FOR TRAINING PURPOSES ONLY
Page: 63
AMET Ltd.
B737-600/700/800
38-32
COMPONENTLOCATION - LAVATORY
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 64
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 31
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Component Locations - Lavatory
FOR TRAINING PURPOSES ONLY
Page: 65
AMET Ltd.
B737-600/700/800
38-32
COMPONENT LOCATION - AFT CARGO COMPARTMENT
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 66
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 32
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Component Locations - Aft Cargo Compartment
FOR TRAINING PURPOSES ONLY
Page: 67
AMET Ltd.
B737-600/700/800
38-32
WASTE SERVICE PANEL - COMPONENTS
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 68
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 33
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Waste Service Panel Components
FOR TRAINING PURPOSES ONLY
Page: 69
AMET Ltd.
B737-600/700/800
38-32
FLUSH SWITCH
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 70
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 34
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Flush Switch
FOR TRAINING PURPOSES ONLY
Page: 71
AMET Ltd.
B737-600/700/800
38-32
VACUUM TOILET ASSEMBLY
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 72
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 35
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Vacuum Toilet Assembly
FOR TRAINING PURPOSES ONLY
Page: 73
AMET Ltd.
B737-600/700/800
38-32
FLUSH CYCLE - OPERATION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 74
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 36
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Flush Cycle - Operation
FOR TRAINING PURPOSES ONLY
Page: 75
AMET Ltd.
B737-600/700/800
38-32
VACUUM BLOWER AND FILTER
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 76
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 37
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Vacuum Blower and Filter
FOR TRAINING PURPOSES ONLY
Page: 77
AMET Ltd.
B737-600/700/800
38-32
VACUUM CHECK VALVE
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 78
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 38
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Vacuum Check Valve
FOR TRAINING PURPOSES ONLY
Page: 79
AMET Ltd.
B737-600/700/800
38-32
VACUUM BLOWER BAROMETRIC SWITCH
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 80
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 39
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Vacuum Blower Barometric Switch
FOR TRAINING PURPOSES ONLY
Page: 81
AMET Ltd.
B737-600/700/800
38-32
VACUUM BLOWER - FUNCTIONAL DESCRIPTION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 82
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 40
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Vacuum Blower - Funktional Description
FOR TRAINING PURPOSES ONLY
Page: 83
AMET Ltd.
B737-600/700/800
38-32
LIQUID SEPARATOR
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 84
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 41
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Liquid Separator
FOR TRAINING PURPOSES ONLY
Page: 85
AMET Ltd.
B737-600/700/800
38-32
WASTE TANK
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 86
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 42
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Waste Tank
FOR TRAINING PURPOSES ONLY
Page: 87
AMET Ltd.
B737-600/700/800
38-32
WASTE DRAIN BALL VALVE AND PULL ROD
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 88
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 43
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Waste Drain Ball Valve and Pull Rod
FOR TRAINING PURPOSES ONLY
Page: 89
AMET Ltd.
B737-600/700/800
38-32
WASTE DRAIN VALVE ASSEMBLY
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 90
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 44
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Waste Drain Valve Assembly
FOR TRAINING PURPOSES ONLY
Page: 91
AMET Ltd.
B737-600/700/800
38-32
WASTE TANK RINSE FITTING ASSEMBLY
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 92
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 45
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Waste Tank Rinse Fitting Assembly
FOR TRAINING PURPOSES ONLY
Page: 93
AMET Ltd.
B737-600/700/800
38-32
WASTE TANK RINSE FILTER
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 94
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 46
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Waste Tank Rinse Filter
FOR TRAINING PURPOSES ONLY
Page: 95
AMET Ltd.
B737-600/700/800
38-32
WASTE TANK RINSE NOZZLE
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 96
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 47
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Waste Tank Rinse Nozzle
FOR TRAINING PURPOSES ONLY
Page: 97
AMET Ltd.
B737-600/700/800
38-32
WASTE TANK DRAIN LINE BLOCKAGE REMOVAL VALVE
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 98
AMET Ltd.
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 48
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Waste Tank Drain Line Blockage Removal Valve
FOR TRAINING PURPOSES ONLY
Page: 99
AMET Ltd.
B737-600/700/800
38-32
FUNCTIONAL DESCRIPTION - MECHANICAL
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 100
B737-600/700/800
38-32
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 49
19 Jul 99
REFRESHER COURSE
FRA US/E br
Vacuum Waste - Functional Description - Mechanical
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 101
B737-600/700/800
38-33
38-33
WASTE TANK QUANTITY INDICATION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 102
B737-600/700/800
38-33
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 50
19 Jul 99
REFRESHER COURSE
FRA US/E br
Waste Tank Quantity Indication - Introduction
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 103
B737-600/700/800
38-33
WASTE TANK POINT LEVEL SENSOR
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 104
B737-600/700/800
38-33
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 51
19 Jul 99
REFRESHER COURSE
FRA US/E br
Waste Tank Quantity Indication - Waste Tank Point Level Sensor
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 105
B737-600/700/800
38-33
WASTE TANK CONTINUOUS LEVEL SENSOR
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 106
B737-600/700/800
38-33
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 52
19 Jul 99
REFRESHER COURSE
FRA US/E br
Waste Tank Quantity Indication - Waste Tank Continuous Level Sensor
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 107
B737-600/700/800
38-33
LOGIC CONTROL MODULE
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 108
B737-600/700/800
38-33
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 53
19 Jul 99
REFRESHER COURSE
FRA US/E br
Waste Tank Quantity Indication - Logic Control Module
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 109
B737-600/700/800
38-33
ATTENDANT PANEL WASTE QUANTITY INDICATOR
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 110
AMET Ltd.
B737-600/700/800
38-33
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 54
19 Jul 99
REFRESHER COURSE
FRA US/E br
Waste Tank Quantity Indication - Attendent’s Panel Waste Quantity Indicator
FOR TRAINING PURPOSES ONLY
Page: 111
AMET Ltd.
B737-600/700/800
38-33
FUNCTIONAL DESCRIPTION
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 112
AMET Ltd.
B737-600/700/800
38-33
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 55
19 Jul 99
REFRESHER COURSE
FRA US/E br
Waste Tank Quantity Indication - Functional Description
FOR TRAINING PURPOSES ONLY
Page: 113
AMET Ltd.
B737-600/700/800
38-33
LOGIC CONTROL MODULE
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
19 Jul 99
REFRESHER COURSE
FRA US/E br
FOR TRAINING PURPOSES ONLY
Page: 114
AMET Ltd.
B737-600/700/800
38-33
For Training Purposes Only
Lufthansa Technical Training
WATER AND WASTE
WASTE DISPOSAL
Figure 56
19 Jul 99
REFRESHER COURSE
FRA US/E br
Waste Tank Quantity Indication - Logic Control Module - Training Information Point
FOR TRAINING PURPOSES ONLY
Page: 115
AMET Ltd.
Training Manual
B 737-600/700/800/9000
ATA 34-60 FMC,
ATA 22-23 SMYD
ATA 27-24 WTRIS
CONFIG. C2
22-23 Yaw Damper System
27-24 WTRIS (Wheel to Rudder
Interconnect System)
ATA 104 Level 2
Book No:
Lufthansa
Technical Training GmbH
Lufthansa Base
B737-6 34-60 C2 L2 E
REFRESHER COURSE
FOR TRAINING PURPOSES ONLY
Issue: November 2001
For Training Purposes Only
 Lufthansa 1995
AMET Ltd.
For training purposes and internal use only.
Copyright by Lufthansa Technical Training GmbH.
All rights reserved. No parts of this training
manual may be sold or reproduced in any form
without permission of:
Lufthansa Technical Training GmbH
Lufthansa Base Frankfurt
D-60546 Frankfurt/Main
Tel. +49 69 / 696 41 78
Fax +49 69 / 696 63 84
Lufthansa Base Hamburg
Weg beim Jäger 193
D-22335 Hamburg
Tel. +49 40 / 5070 24 13
Fax +49 40 / 5070 47 46
REFRESHER COURSE
FOR TRAINING PURPOSES ONLY
AMET Ltd.
TABLE OF CONTENTS
ATA 34-61 FLIGHT MANAGEMENT COMPUTER
SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
ATA 22-23 YAW DAMPER SYSTEM . . . . . . . . . . . .
1
ATA 27-24 WHEEL TO RUDDER INTERCONNECT
SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
34-61
FMC SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ABBREVIATIONS AND ACRONYMS . . . . . . . . . . . . . . . . . . . . . . . . . . .
FLIGHT MANAGEMENT COMPUTER SYSTEM (FMC) INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMCS - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMCS — FLIGHT MANAGEMENT COMPUTER . . . . . . . . . . . . . . . . .
FMCS — FLIGHT COMPARTMENT COMPONENT LOCATIONS . . .
FMCS — ELECTRONIC EQUIPMENT COMPARTMENT
LOCATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMCS - FMC AND CDU POWER INTERFACE . . . . . . . . . . . . . . . . . . .
FMCS - TRANSFER RELAY POWER INTERFACE . . . . . . . . . . . . . . .
FMCS - DIGITAL INPUT INTERFACE 1 . . . . . . . . . . . . . . . . . . . . . . . . .
FMCS - DIGITAL INPUT INTERFACE 2 . . . . . . . . . . . . . . . . . . . . . . . . .
FMCS - DIGITAL OUTPUT INTERFACE 1 . . . . . . . . . . . . . . . . . . . . . . .
FMCS - DIGITAL OUTPUT INTERFACE 2 . . . . . . . . . . . . . . . . . . . . . . .
FMCS - CDU INTERFACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMCS - FMC DATA LOADER INTERFACE . . . . . . . . . . . . . . . . . . . . . .
FMCS - ACARS INTERFACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMCS - ANALOG DISCRETES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMCS - STATUS ANNUNCIATOR INTERFACE . . . . . . . . . . . . . . . . . .
FMCS - PROGRAM PIN INTERFACE . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMCS - CONTROL DISPLAY UNIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMCS - CONTROL DISPLAY UNIT: CONTROLS AND DISPLAYS . .
FMCS - LCD CDU: CONTROLS AND DISPLAYS . . . . . . . . . . . . . . . . .
REFRESHER COURSE
2
2
6
8
10
12
14
16
18
20
22
24
28
30
32
34
36
38
40
44
46
50
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
- LCD CDU DATA LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
- CDU CONTROLS AND DISPLAYS . . . . . . . . . . . . . . . . . . . . . .
- AIRBORNE DATA LOADER . . . . . . . . . . . . . . . . . . . . . . . . . . . .
- TRANSFER RELAYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
- DISPLAYS: CDU, POWER UP . . . . . . . . . . . . . . . . . . . . . . . . . .
- DISPLAYS: CDU, IDENT PAGE . . . . . . . . . . . . . . . . . . . . . . . . .
- DISPLAYS: CDU, INIT/REF INDEX PAGE . . . . . . . . . . . . . . .
- DISPLAYS: CDU, POSITION PAGES . . . . . . . . . . . . . . . . . . . .
- DISPLAYS: CDU MESSAGES . . . . . . . . . . . . . . . . . . . . . . . . . .
- DISPLAYS: CDS FLIGHT MODE ANNUNCIATIONS . . . . . . .
DISPLAYS - CDS - THRUST MODE . . . . . . . . . . . . . . . . . . . . .
DISPLAYS - CDS - AIRSPEED INDICATION . . . . . . . . . . . . . .
DISPLAYS - CDS - MAP DISPLAY . . . . . . . . . . . . . . . . . . . . . .
DISPLAYS - CDS - PLAN DISPLAY . . . . . . . . . . . . . . . . . . . . . .
DISPLAYS - CDS, NON-NORMAL DISPLAYS . . . . . . . . . . . .
- DATA LOADER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
- DATABASE LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
- CROSSLOAD PAGES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
- DATABASE CROSSLOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
- BITE PAGES: INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . .
- BITE PAGES: BITE ENTRY . . . . . . . . . . . . . . . . . . . . . . . . . . . .
- BITE PAGES: AUTOMATIC BITE ENTRY . . . . . . . . . . . . . . . .
- BITE PAGES: INFLIGHT FAULTS . . . . . . . . . . . . . . . . . . . . . .
- BITE PAGES: CDU TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
- BITE PAGES: SENSORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
- BITE PAGES: DISCRETES . . . . . . . . . . . . . . . . . . . . . . . . . . . .
- BITE PAGES: FMCS FIXED OUTPUTS . . . . . . . . . . . . . . . . .
- BITE PAGES: IRS MONITOR . . . . . . . . . . . . . . . . . . . . . . . . . .
- BITE PAGES: PERFORMANCE FACTORS . . . . . . . . . . . . . .
- BITE PAGES: SOFTWARE OPTIONS . . . . . . . . . . . . . . . . . . .
- BITE PAGES: AIRPL. MODEL, ENGINE CONFIG. . . . . . . . .
- LCD BITE PAGES: INTRODUCTION . . . . . . . . . . . . . . . . . . . .
- LCDU BITE PAGES: FAULTS . . . . . . . . . . . . . . . . . . . . . . . . . .
- LCDU BITE PAGES: KEY TEST . . . . . . . . . . . . . . . . . . . . . . . .
- LCDU BITE PAGES: COLOR TEST . . . . . . . . . . . . . . . . . . . . .
FOR TRAINING PURPOSES ONLY
56
58
62
64
66
70
72
74
76
80
82
84
86
88
90
92
94
96
98
100
102
104
106
108
110
112
114
116
118
120
122
124
126
128
130
Page i
AMET Ltd.
TABLE OF CONTENTS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
FMCS
- LCDU BITE PAGES:
- LCDU BITE PAGES:
- LCDU BITE PAGES:
- LCDU BITE PAGES:
- LCDU BITE PAGES:
- LCDU BITE PAGES:
- LCDU BITE PAGES:
- LCDU BITE PAGES:
DISPLAY TEST . . . . . . . . . . . . . . . . . . . .
CONFIG . . . . . . . . . . . . . . . . . . . . . . . . . .
SW OPTIONS . . . . . . . . . . . . . . . . . . . . .
POWER SUPPLY . . . . . . . . . . . . . . . . . .
TEMP SENSORS . . . . . . . . . . . . . . . . . .
LIGHT SENSORS . . . . . . . . . . . . . . . . . .
LAMP TEST . . . . . . . . . . . . . . . . . . . . . . .
CALIBRATION . . . . . . . . . . . . . . . . . . . . .
132
134
136
138
140
142
144
146
22-23
YAW DAMPER SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ABBREVIATIONS AND ACRONYMS . . . . . . . . . . . . . . . . . . . . . . . . . . .
YAW DAMPER SYSTEM (YDS) - INTRODUCTION . . . . . . . . . . . . . . .
YDS - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
YDS - COCKPIT COMPONENT LOCATIONS . . . . . . . . . . . . . . . . . . . .
YDS - E+E COMPARTMENT COMP. LOCATIONS . . . . . . . . . . . . . . .
YDS - VERTICAL STABILIZER COMP. LOCATIONS . . . . . . . . . . . . . .
SMYD 1 - YDS: INTERFACES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SYMD 2: YD - INTERFACES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
YDS - OPERATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
YDS - OPERATIONS: ENGAGE INTERLOCKS . . . . . . . . . . . . . . . . . .
YDS - SMYD BITE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
YDS - SMYD BITE: EXISTING FAULTS . . . . . . . . . . . . . . . . . . . . . . . . .
YDS - SMYD BITE: FAULT HISTORY . . . . . . . . . . . . . . . . . . . . . . . . . . .
YDS - SMYD BITE: GROUND TESTS . . . . . . . . . . . . . . . . . . . . . . . . . .
YDS - SMYD BITE: SERVO TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
YDS - SMYD BITE: OTHER FUNCTIONS . . . . . . . . . . . . . . . . . . . . . . .
150
150
150
152
154
156
158
160
162
164
166
168
170
172
174
176
178
27-24
WHEEL TO RUDDER INTERCONNECT SYSTEM . . . . . . .
ABBREVIATIONS AND ACRONYMS . . . . . . . . . . . . . . . . . . . . . . . . . . .
WTRIS - INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WTRIS - GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WTRIS - COMPONENT LOCATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . .
SMYD 2 WTRIS - INTERFACES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SYMD 2 - WTRIS: OPERATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SMYD 2 - WTRIS OPERATIONS: ENGAGE INTERLOCKS . . . . . . .
SMYD 2 - WTRIS: FUNCTIONAL DESCRIPTION . . . . . . . . . . . . . . . .
180
180
180
182
184
188
190
192
194
REFRESHER COURSE
SMYD 2 - WTRIS: BITE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WTRIS - SMYD BITE: GROUND TESTS . . . . . . . . . . . . . . . . . . . . . . . .
WTRIS - SMYD BITE: SERVO TEST . . . . . . . . . . . . . . . . . . . . . . . . . . .
FOR TRAINING PURPOSES ONLY
196
198
200
Page ii
AMET Ltd.
TABLE OF FIGURES
Figure 1
Figure 2
Figure 3
Figure 4
Figure 5
Figure 6
Figure 7
Figure 8
Figure 9
Figure 10
Figure 11
Figure 12
Figure 13
Figure 14
Figure 15
Figure 16
Figure 17
Figure 18
Figure 19
Figure 20
Figure 21
Figure 22
Figure 23
Figure 24
Figure 25
Figure 26
Figure 27
Figure 28
Figure 29
Figure 30
Figure 31
Figure 32
Figure 33
Figure 34
Figure 35
FMCS INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMCS GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . .
FMCS COMPONENT: COMPUTER . . . . . . . . . . . . . . . . .
FMCS COMPONENT LOCATIONS . . . . . . . . . . . . . . . . . .
FMCS COMPONENT LOCATIONS . . . . . . . . . . . . . . . . . .
FMC and CDU POWER INTERFACE . . . . . . . . . . . . . . . .
FMC TRANSFER RELAY POWER INTERFACE . . . . . .
FMC DIGITAL INPUT INTERFACE - 1 . . . . . . . . . . . . . . .
FMC DIGITAL INPUT INTERFACE - 2 . . . . . . . . . . . . . . .
FMC DIGITAL OUTPUTS INTERFACE - 1 . . . . . . . . . .
FMC DIGITAL OUTPUTS INTERFACE - 1 . . . . . . . . . .
FMC DIGITAL OUTPUTS INTERFACE - 2 . . . . . . . . . .
FMC CDU INTERFACE . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMC DATA LOADER INTERFACE . . . . . . . . . . . . . . . . .
FMC ACARS INTERFACE . . . . . . . . . . . . . . . . . . . . . . . .
FMC ANALOG DISCRETES . . . . . . . . . . . . . . . . . . . . . . .
FMC STATUS ANN. INTERFACE . . . . . . . . . . . . . . . . . .
FMC PROGRAM PINS INTERFACE . . . . . . . . . . . . . . .
FMCS - SYSTEM SUMMARY . . . . . . . . . . . . . . . . . . . . .
FMCS - CONTROL DISPLAY UNIT . . . . . . . . . . . . . . . .
FMCS - CONTROL DISPLAY UNIT . . . . . . . . . . . . . . . .
FMCS - CONTROL DISPLAY UNIT . . . . . . . . . . . . . . . .
FMCS - CONTROL DISPLAY UNIT . . . . . . . . . . . . . . . .
FMCS - CONTROL DISPLAY UNIT . . . . . . . . . . . . . . . .
FMS LCD CDU-DATA LOAD . . . . . . . . . . . . . . . . . . . . . .
FMC CDU CONTROLS AND DISPLAYS . . . . . . . . . . . .
FMC CDU CONTROLS AND DISPLAYS . . . . . . . . . . . .
FMC AIRBORNE DATA LOADER . . . . . . . . . . . . . . . . . .
FMC XFR RELAYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMS POWER UP, NORMAL DISLPLAY . . . . . . . . . . . . .
FMS POWER UP, NON-NORMAL DISPLAY . . . . . . . .
FMC IDENT PAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMC INIT/REF PAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMC POSITION PAGES . . . . . . . . . . . . . . . . . . . . . . . . . .
FMC CDU MESSAGES . . . . . . . . . . . . . . . . . . . . . . . . . . .
REFRESHER COURSE
7
9
11
13
15
17
19
21
23
25
27
29
31
33
35
37
39
41
43
45
49
51
53
55
57
59
61
63
65
67
69
71
73
75
79
Figure 36
Figure 37
Figure 38
Figure 39
Figure 40
Figure 41
Figure 42
Figure 43
Figure 44
Figure 45
Figure 46
Figure 47
Figure 48
Figure 49
Figure 50
Figure 51
Figure 52
Figure 53
Figure 54
Figure 55
Figure 56
Figure 57
Figure 58
Figure 59
Figure 60
Figure 61
Figure 62
Figure 63
Figure 64
Figure 65
Figure 66
Figure 67
Figure 68
Figure 69
Figure 70
FMC FLIGHT MODE ANN. . . . . . . . . . . . . . . . . . . . . . . . .
FMC THRUST MODE ANN. . . . . . . . . . . . . . . . . . . . . . . .
FMC MACH AIRSPEED INDICATION . . . . . . . . . . . . . .
FMC MAP DISPLAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMC PLAN DISPLAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMC NON-NORMAL DISPLAYS . . . . . . . . . . . . . . . . . . .
FMS DATA LOADER . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMS DATA BASE LOADING . . . . . . . . . . . . . . . . . . . . . .
FMS CROSSLOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMS CROSS LOADING . . . . . . . . . . . . . . . . . . . . . . . . . .
FMS BITE INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . .
FMS BITE ENTRY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FMS BITE ENTRY AUTOMATIC . . . . . . . . . . . . . . . . . . .
FMS INFLIGHT FAULTS . . . . . . . . . . . . . . . . . . . . . . . . . .
FMS BITE PAGES CDU TEST . . . . . . . . . . . . . . . . . . . . .
FMS BITE PAGES, SENSORS . . . . . . . . . . . . . . . . . . . .
FMS BITE PAGES, DISCRETES . . . . . . . . . . . . . . . . . . .
FMS BITE PAGES, FIXED OUTPUTS . . . . . . . . . . . . . .
FMS BITE PAGES, IRS MONITOR . . . . . . . . . . . . . . . . .
FMS BITE PAGES, PERFORMANCE FACTORS . . . .
FMS BITE PAGES, SOFTWARE OPTIONS . . . . . . . . .
FMS BITE PAGES, AC-CONFIG. . . . . . . . . . . . . . . . . . .
FMCS BITE PAGES - LCD CDU . . . . . . . . . . . . . . . . . . .
FMCS BITE PAGES - LCD CDU FAULTS . . . . . . . . . . .
FMCS BITE PAGES - LCD CDU KEY TEST . . . . . . . . .
FMCS BITE PAGES - LCD CDU COLOR TEST . . . . . .
FMCS BITE PAGES - LCD CDU DISPLAY TEST . . . . .
FMCS BITE PAGES - LCD CDU CONFIG . . . . . . . . . . .
FMCS BITE PAGES - LCD CDU SW OPTIONS . . . . . .
FMCS BITE PAGES - LCD CDU PWR SUPPLY . . . . . .
FMCS BITE PAGES - LCD CDU TEMP SENSORS . . .
FMCS BITE PAGES - LCD CDU LIGHT SENSORS . .
FMCS BITE PAGES - LCD CDU LAMP TEST . . . . . . .
FMCS BITE PAGES - LCD CDU CALIBRATION . . . . .
FMCS - SYSTEM SUMMARY . . . . . . . . . . . . . . . . . . . . .
FOR TRAINING PURPOSES ONLY
81
83
85
87
89
91
93
95
97
99
101
103
105
107
109
111
113
115
117
119
121
123
125
127
129
131
133
135
137
139
141
143
145
147
149
Page iii
AMET Ltd.
TABLE OF FIGURES
Figure 71
Figure 72
Figure 73
Figure 74
Figure 75
Figure 76
Figure 77
Figure 78
Figure 79
Figure 80
Figure 81
Figure 82
Figure 83
Figure 84
Figure 85
Figure 86
Figure 87
Figure 88
Figure 89
Figure 90
Figure 91
Figure 92
Figure 93
Figure 94
Figure 95
Figure 96
YAW DAMPER (YD) INTRODUCTION . . . . . . . . . . . . . .
YD GENERAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . .
YD COMPONENT LOCATION . . . . . . . . . . . . . . . . . . . . .
YD COMPONENT LOCATION . . . . . . . . . . . . . . . . . . . . .
YD COMPONENT LOCATION . . . . . . . . . . . . . . . . . . . . .
YD INTERFACES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SMYD 2 - YD INTERFACES . . . . . . . . . . . . . . . . . . . . . . .
YD OPERATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
YD ENGAGE INTERLOCK . . . . . . . . . . . . . . . . . . . . . . . .
SMYD - BITE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
YDS BITE, EXISTING FAULTS . . . . . . . . . . . . . . . . . . . .
YDS BITE, FAULT HISTORY . . . . . . . . . . . . . . . . . . . . . .
YDS BITE, GROUND TESTS . . . . . . . . . . . . . . . . . . . . . .
YDS BITE, SERVO TEST . . . . . . . . . . . . . . . . . . . . . . . . .
YDS BITE, OTHER FUNCTIONS . . . . . . . . . . . . . . . . . .
WTRIS INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . .
WTRIS - GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WTRIS - COMPONENT LOCATION . . . . . . . . . . . . . . .
WTRIS COMPONENT LOCATION . . . . . . . . . . . . . . . . .
SMYD 2 - WTRIS INTERFACES . . . . . . . . . . . . . . . . . . .
SMYD 2 - YD/WTRIS OPS . . . . . . . . . . . . . . . . . . . . . . . .
SMYD 2 - WTRIS ENGAGE . . . . . . . . . . . . . . . . . . . . . . .
SMYD 2 - FUNCTIONAL DESCR. . . . . . . . . . . . . . . . . . .
SMYD - BITE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SMYD WTRIS BITE GROUND TESTS . . . . . . . . . . . . .
SMYD WTRIS SERVO TEST . . . . . . . . . . . . . . . . . . . . . .
REFRESHER COURSE
151
153
155
157
159
161
163
165
167
169
171
173
175
177
179
181
183
185
187
189
191
193
195
197
199
201
FOR TRAINING PURPOSES ONLY
Page iv
AMET Ltd.
B737-600/700/800
ATA 34-61 FLIGHT MANAGEMENT COMPUTER SYSTEM
ATA 22-23 YAW DAMPER SYSTEM
ATA 27-24 WHEEL TO RUDDER INTERCONNECT SYSTEM
For Training Purposes Only
Lufthansa Technical Training
NAVIGATION
AUTOFLIGHT
Aug 1999
REFRESHER COURSE
FRA USE NM
FOR TRAINING PURPOSES ONLY
Page: 1
AMET Ltd.
Lufthansa Technical Training
For Training Purposes Only
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMCS)
34-61
B737-600/700/800
34-61
FMC SYSTEM
ABBREVIATIONS AND ACRONYMS
act
AC
ADIRU
ADIRS
ADL
alt
appr
APU
ARINC
arr
A/T
ATA
BITE
brg
C
calc
CAS
CAPT
CDS
CDU
clb
clr
CO
CON
cmd
chng
comp
crs
crz
— active
— alternating current
— air data inertial reference unit
— air data inertial reference system
— airborne data loader
— altitude
— approach
— auxiliary power unit
— aeronautical radio incorporated
— arrival
— autothrottle
— actual time of arrival
— built in test equipment
— bearing
— celsius
— calculate
— computed airspeed
— captain
— common display system
— control display unit
— climb
— clear
— company
— continuous
— command
— change
— complete
— course
— cruise
Aug 99
REFRESHER COURSE
FRA US/E NM
ctr
DC
del
dep
des
dest
DEU
dev
DFCS
DIR
dist
dspl
DTG
DME
E
E/O
econ
ECU
E/D
EEC
ELEX
eng
EPR
ETA
EXEC
F
FF
FL
FDAU
— center
— direct current
— delete
— departure
— descent
— destination
— display electronic unit
— deviation
— digital flight control system
— direct
— distance
— display
— distance to go
— distance measuring equipment
— east
— engine out
— economy
— engine control unit
— end of descent
— electronic engine control
— electronics
— engine
— engine pressure ratio
— estimated time of arrival
— execute
— fahrenheit
— fuel flow
— flight level
— flight data acquisition unit
FOR TRAINING PURPOSES ONLY
Page: 2
AMET Ltd.
Lufthansa Technical Training
For Training Purposes Only
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMCS)
lim
LNAV
long
FMC
FMCS
F/O
flt
FMA
FMCS
FPA
FQIS
FQPU
fwd
G
G/A
GMT
GPWC
GRWT
GS
HF
hdg
hrdw
ident
IFSAU
ILS
inbd
info
INIT/REF
INTC
ISA
KTS
L
34-61
— limit
— lateral navigation
— longitude
— flight management computer
— flight management computer system
— first officer
— flight
— flight mode annunciation
— flight management computer system
— flight path angle
— fuel quantity indicating system
— fuel quantity processor unit
— forward
— ground
— go around
— greenwich mean time
— ground proximity warning computer
— gross weight
— ground speed
— high frequency
— heading
— hardware
— identification
— integrated flight system accessory unit
— instrument landing system
— inboard
— information
— initialization/reference
— intercept
— international standard atmosphere
— nautical miles per hour (knots)
— left
Aug 99
REFRESHER COURSE
FRA US/E NM
B737-600/700/800
lat
LED
LVL CHG
MASI
max
MCDU
MCP
MMR
mod
msg
M
N
nav
NAV RAD
NDB
NM
OAT
OFP
OFST
OP
PDB
PDL
perf
pln
pos
PPOS
pred
preflt
proc
prof
PROG
PSEU
— latitude
— light emitting diode
— level change
— mach airspeed indicator
— maximum
— multi—purpose control display unit
— mode control panel
— multi mode receiver
— modification
— message
— meters
— north
— navigation
— navigation radio
— navigation database
—nautical miles
—outside air temperature
—operational flight program
— offset
— operational program
— performance data base
— portable data loader
— performance
— plan
— position
— present position
— predicted
— preflight
— procedure
— profile
— progress
— proximity switch electronics unit
FOR TRAINING PURPOSES ONLY
Page: 3
AMET Ltd.
Lufthansa Technical Training
For Training Purposes Only
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMCS)
PTH
QFE
QNH
QUAD
qty
R
rad
RDY
REC
ref
RTA
rte
R/W
rwy
s
S/C
SAT
sel
SID
SMYD
SPD
STAR
Sw
TACAN
TAS
TAT
T/C
T/D
tgt
thr
thr ref
TO/GA
34-61
— path
— altimeter setting to indicate altitude above reference airfield
— altimeter setting to indicate altitude above mean sea level
— quadrant
— quantity
— right
— radio
— ready
— recorder
— reference
— required time of arrival
— route
— read/write
— runway
— south
—step climb
— static air temperature
— selector
— standard instrument departure
— stall management yaw damper
— speed
— standard terminal arrival route
— software
— tactical air navigation
— true airspeed
— total air temperature
— top of climb
— top of descent
— target
— thrust
— thrust reference
— takeoff/go—around
Aug 99
REFRESHER COURSE
FRA US/E NM
B737-600/700/800
trans
trk
UTC
V1
V2
v
V
VNAV
VR
VREF
V/S
VTK
w
wpt
wt
XFR
XTK
z
ZFW
— transition
— track
— universal time (coordinated)
— takeoff decision speed
— climbout speed
— volt
— volt
— vertical navigation
— rotation speed
— reference speed
— vertical speed
— vertical track
— west
— waypoint
— weight
— transfer
— cross track
— zulu
— zero fuel weight
FOR TRAINING PURPOSES ONLY
Page: 4
AMET Ltd.
B737-600/700/800
34-61
THIS PAGE INTENTIONALLY LEFT BLANK
For Training Purposes Only
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMCS)
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
Page: 5
AMET Ltd.
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMCS)
B737-600/700/800
34-61
FLIGHT MANAGEMENT COMPUTER SYSTEM (FMC) - INTRODUCTION
General
The flight crew uses the flight management computer system (FMCS) to enter
route and vertical performance flight plan data for a flight.
With the flight plan and inputs from the airplane sensors, the FMCS does these
functions:
S Navigation
S Performance
S Guidance.
For Training Purposes Only
Navigation
A navigation data base is in the FMC memory. It includes the navigation data
for the area of operation.
The pilot can use the navigation data base to set the entire flight plan before a
flight.
The FMC calculates the airplane position during the flight. To do the calculation, it uses the inertial reference function and the radio navigation aids, if available.
The FMC compares the calculated position with the set position. If there is a
difference, it shows on the common display system.
Guidance
The FMC sends commands to the digital flight control system (DFCS) and the
autothrottle (A/T).
The DFCS and the A/T use these signals to control the airplane in the lateral
(LNAV) and vertical (VNAV) modes of flight.
Built In Test equipment
You use the FMCS CDU to select and control BITE for these systems:
S FMCS
S Fuel quantity indication system (FQIS)
S Digital flight control system (DFCS)
S Autothrottle (A/T)
S Common display system (CDS)
S APU engine control unit (ECU)
S Electronic engine controller (EEC)
S Air data inertial reference unit (ADIRU).
Performance
A performance data base in the FMC contains data to model the airplane and
the engines.
The flight crew puts this data in the FMC:
S Airplane gross weight
S Cruise altitude
S Cost index.
The FMC uses the data to calculate these functions:
S Economy speeds
S Best flight altitude
S Top of descent point
The common display system (CDS) shows target speeds and altitudes.
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
Page: 6
AMET Ltd.
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMCS)
For Training Purposes Only
CONTROL DISPLAY
UNIT
B737-600/700/800
34-61
FLIGHT MANAGEMENT
COMPUTER
NAVIGATION DISPLAY
Figure 1
Aug 99
REFRESHER COURSE
FRA US/E NM
FMCS INTRODUCTION
FOR TRAINING PURPOSES ONLY
Page: 7
AMET Ltd.
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMCS)
B737-600/700/800
34-61
FMCS - GENERAL DESCRIPTION
General
The main component of the flight management computer system (FMCS) is the
FMC.
The FMC receives the data and does the navigation and performance calculations.
The flight crew uses the CDUs (also called MCDUs) to put data into the FMC.
The FMC input and output data format is ARINC 429 digital data and analog
discretes.
Some FMC data goes directly to the user systems. Other output data goes to
the user systems through the transfer relays.
For Training Purposes Only
NOTE:
Some Airlines have only one FMC installed: But normally all provisions for a
second set of Flight Management Computer System are installed.
This includes also the FMCS transfer relay.
The FMC transfer switch is not installed.
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
Page: 8
AMET Ltd.
Lufthansa Technical Training
For Training Purposes Only
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMCS)
B737-600/700/800
34-61
– GPS
– DME
– ILS
– VOR
RADIO NAVIGATION SYSTEMS
Figure 2
Aug 99
REFRESHER COURSE
FRA US/E NM
FMCS GENERAL DESCRIPTION
FOR TRAINING PURPOSES ONLY
Page: 9
AMET Ltd.
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMCS)
B737-600/700/800
34-61
FMCS — FLIGHT MANAGEMENT COMPUTER
Purpose
The FMC uses data from sensors and data stored in the FMC to do the calculations for the FMCS.
Physical Description
The FMC is a rack—mounted chassis assembly in an ARINC 600, 4 MCU box.
It weighs less than 22 pounds (10 kilograms).
The FMCs are cooled with air from the equipment cooling supply and exhaust
systems. Cooling air for FMC 1 is blow—thru. Cooling air for FMC 2 is draw—
thru.
Two light emitting diodes (LED) show through openings in the front of the unit.
The PWR ON LED comes on when the FMC has power. The FMC VALID LED
comes on after power is on and the unit passes internal tests.
FAILURE TO OBSERVE ELECTROSTATIC DISCHARGE
PRECAUTIONARY PROCEDURES WHEN TOUCHING, REMOVING, OR INSERTING PARTS OF ASSEMBLIES, MAY
RESULT IN DEGRADATION OR FAILURE OF THE FMC.
For Training Purposes Only
CAUTION:
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
Page: 10
AMET Ltd.
Lufthansa Technical Training
For Training Purposes Only
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMCS)
B737-600/700/800
34-61
FMC
Figure 3
Aug 99
REFRESHER COURSE
FRA US/E NM
FMCS COMPONENT: COMPUTER
FOR TRAINING PURPOSES ONLY
Page: 11
AMET Ltd.
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMCS)
B737-600/700/800
34-61
FMCS — FLIGHT COMPARTMENT COMPONENT LOCATIONS
FMCS Component Locations — P9 Forward Electronics Panel
These are the FMCS components on the P9 forward electronics panel:
S CDU 1
S CDU 2.
FMCS Component Location — P5 FWD Overhead Panel
The FMC source select switch is on the P5—28 forward overhead panel.
For Training Purposes Only
FMCS Component Locations — P61 Panel
These are the FMCS components on the P61 panel:
S Airborne data loader
S Data loader control panel.
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
Page: 12
AMET Ltd.
B737-600/700/800
34-61
For Training Purposes Only
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMCS)
Figure 4
Aug 99
REFRESHER COURSE
FRA US/E NM
FMCS COMPONENT LOCATIONS
FOR TRAINING PURPOSES ONLY
Page: 13
AMET Ltd.
B737-600/700/800
34-61
FMCS — ELECTRONIC EQUIPMENT COMPARTMENT LOCATIONS
FMCS— Component Location — Electronic Equipment Shelf
The FMCS components on the electronic equipment shelf E5—2 are:
S FMC 1
S FMC 2
S FMCS transfer relay 1
S FMCS transfer relay 2.
For Training Purposes Only
Lufthansa Technical Training
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Figure 5
Aug 99
REFRESHER COURSE
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FMCS COMPONENT LOCATIONS
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FMCS - FMC AND CDU POWER INTERFACE
General
The FMC and CDU primary power is 115v ac from electronics buses 1 and 2.
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Figure 6
Nov. 2001
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FMC and CDU POWER INTERFACE
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FMCS - TRANSFER RELAY POWER INTERFACE
General
The transfer relays are Ledex type relays. They mechanically latch to the position you select.
The FMCS source select switch controls the FMCS transfer relays.
These are the switch positions:
S NORMAL
S BOTH ON L (both on left FMC)
S BOTH ON R (both on right FMC).
Operation
The transfer relay power is 28v dc from electronics bus 2.
The FMC source select switch controls the dc power to the transfer relays.
With the FMC source select switch in the NORMAL position, both transfer relays go to the normal position and mechanically latch in that position.
With the FMC source select switch set to the BOTH ON R position, 28v dc
goes from a contact on transfer relay 2 to the relay 1 coil winding.
Relay 1 transfers to the both on right position and mechanically latches to that
position.
With the FMC source select switch set to the BOTH ON L position, 28v dc
goes from a contact on transfer relay 1 to the relay 2 coil winding.
Relay 2 transfers to the both on left position and mechanically latches to that
position.
Contacts on the transfer relays tell these LRUs the position of the transfer relays:
S DEU (1&2)
S FDAU
S FMC (1&2).
Training Information Point
You use the FMCS BITE on the ANALOG DISCRETES page 3/4 to do a check
of the FMC source selection.
Nov. 2001
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Figure 7
Nov. 2001
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FMC TRANSFER RELAY POWER INTERFACE
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FMCS - DIGITAL INPUT INTERFACE 1
General
These LRUs supply data to the FMCS:
S VOR/MB
S DME
S MMR
S Electronic clock.
VOR/MB
The left and right VOR receivers supply the bearing and the frequency of the
VOR stations that are manual tuned.
ILS/MMR
The localizer deviation and the station frequency come from multi—mode receivers 1 and 2.
DME
The Slant range distance and the station frequency come from the left and right
DME transceivers.
For Training Purposes Only
Electronic Clock
The captain’s electronic clock supplies GMT to FMC 1. The first officers electronic clock supplies GMT to FMC 2.
Nov. 2001
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Figure 8
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FMC DIGITAL INPUT INTERFACE - 1
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FMCS - DIGITAL INPUT INTERFACE 2
General
These components send data to the FMCS:
S ADIRU
S DEU
S APU engine control unit (ECU)
S Engine electronic control (EEC)
S A/T
S DFCS MCP
S FQPU.
ADIRU
The ADIRUs send this data to the FMCS:
S Present position
S Heading
S Attitude
S Ground speed
S Vertical speed
S Airspeed
S Altitude
S Mach
S Temperature
S ADIRU BITE words.
DFCS
The DFCS sends data to the mode control panel (MCP)
The MCP sends it to the FMCS.
The MCP sends this data:
S LNAV and VNAV mode status
S Trailing edge flap position
S DFCS BITE words.
A/T
The autothrottle computer sends A/T BITE words.
For Training Purposes Only
FQPU
The fuel quantity processor unit (FQPU) calculates total fuel weight and sends
it to the FMCS. Fuel quantity BITE words also come from the FQPU.
ADIRU Selection
The FMC sees the inertial data and the air data as two different sensors.
In normal operation, the FMCs receive inertial data from their on—side ADIRU
(ADIRU L — FMC 1/ADIRU R — FMC 2).
If the on—side ADIRU malfunctions or it is in the FMCS — DIGITAL INPUT
INTERFACE — 2
ATT or ALIGN mode, the FMC automatically switches to its off—side ADIRU.
The FMCs use the same air data source as the DFCS.
CDS/APU/EEC
The display electronic units (DEU) send EFIS control panel discretes and CDS
BITE data to the FMCS.
The DEUs, also send APU, ECU and engine EEC BITE data on the same bus.
There is no direct BITE interface between the FMCS and the APU and EEC.
The DEUs are a buffer between the APU, EEC and the FMCS.
Nov. 2001
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Figure 9
Nov. 2001
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FMC DIGITAL INPUT INTERFACE - 2
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FMCS - DIGITAL OUTPUT INTERFACE 1
General
The FMC data on bus 01 and 02, goes directly to the ADIRUs. The other user
systems get this FMC data through the transfer relays.
ADIRU
The FMCs send CDU latitude and longitude data to the ADIRUs to start alignment. The FMcs also send the CDU magnetic heading and a BITE test word.
The ADIRUs use the magnetic heading when in the attitude mode.
For Training Purposes Only
A/T
The FMC you select sends this data to the autothrottle:
S N1 thrust limits
S N1 targets
S FMCS gross weight
S Temperature
S BITE test word.
FCC
The FMC sends this data to the FCCs:
S Target airspeed
S MACH
S Target altitude
S Target vertical speed
S Roll command
S FMC discretes (FMC mode logic)
S BITE test word.
DEU
The FMC you select sends this data to the DEUs:
S Thrust mode annunciation
S Ground speed
S N1 reference display
S BITE test words
S Flight mode annunciation
S Gross weight (CDS calculates flap manuevering speeds that show on the
MASI).
The BITE test words are for the DEUs and these systems:
S Engines (EEC)
S APU (ECU).
There is no direct BITE interface between the FMC 1 and the EEC and ECU.
The DEUs are a buffer between the EECand ECU and the FMC.
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FMC 2
Figure 10
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FMC DIGITAL OUTPUTS INTERFACE - 1
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FMCS - DIGITAL OUTPUT INTERFACE 1 (cont‘d)
You select the source of FMC data with the FMC source select switch.
FMC SOURCE SELECT SWITCH POSITION
FCC A
FCC B
NORMAL
FMC 1
FMC 2
BOTH ON LEFT
FMC 1
FMC 1
BOTH ON RIGHT
FMC 2
FMC 2
Fuel Quantity Processor Unit
The selected FMC sends a BITE test word to the processor unit.
FDAU
The FMCS sends navigation data to the FDAU.
SMYD
The FMCS sends gross weight data to the stall management function in the
SMYDs.
You select the source of FMC data with the FMC source select switch.
FMC SOURCE SELECT SWITCH POSITION
SMYD 1
SMYD 2
NORMAL
FMC 1
FMC 2
BOTH ON LEFT
FMC 1
FMC 1
BOTH ON RIGHT
FMC 2
FMC 2
For Training Purposes Only
DME
The FMCs send autotuned navigation frequencies to the NAV control panels
and DMEs.
In normal operation, the FMCs autotune the DME interrogators through the
NAV control panels. If a NAV control panel fails, its on—side DME interrogator
is autotuned directly from the FMC you select.
You select the source of FMC data with the FMC source select switch.
FMC SOURCE SELECT SWITCH POSITION
DME LEFT
DME RIGHT
AND CAPT
AND F/O
NAV/DME CP NAV/DME CP
NORMAL
FMC 1
FMC 2
BOTH ON LEFT
FMC 1
FMC 1
BOTH ON RIGHT
FMC 2
FMC 2
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FMC 2
Figure 11
Nov. 2001
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FMC DIGITAL OUTPUTS INTERFACE - 1
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FMCS - DIGITAL OUTPUT INTERFACE 2
General
The FMC data on bus 08 and 09, goes directly to the DEUs. The other user
systems get this FMC data through the transfer relays.
The DEUs get EFIS display data directly from both FMCs.
The DEUs use contacts on the FMCS transfer relays to know the position of
the transfer relays.
The DEUs use the position information to know which FMC to use for data.
See FMCS Transfer Relay Power Interface in this section, for more information.
You select the source of FMC data with the FMC source select switch.
FMC SOURCE SELECT SWITCH POSITION
DEU 1
DEU 2
NORMAL
FMC 1
FMC 2
BOTH ON LEFT
FMC 1
FMC 1
BOTH ON RIGHT
FMC 2
FMC 2
GPWC
The selected FMC sends track and path angle plus wind direction.
For Training Purposes Only
FDAU
The selected FMC sends present position (latitude and longitude) plus wind
speed and direction.
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Figure 12
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FMC DIGITAL OUTPUTS INTERFACE - 2
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FMCS - CDU INTERFACE
FMC Digital Output
With the FMC source select switch set to the BOTH ON L or the NORMAL
position, CDU 1 and CDU 2 get data from FMC 1.
With the source select switch set to the BOTH ON R position, both CDUs get
data from FMC 2.
For Training Purposes Only
FMC Digital Input
CDU 1 and CDU 2 send data directly to both FMCs.
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Figure 13
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FMC CDU INTERFACE
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FMCS - FMC DATA LOADER INTERFACE
General
The airborne data loader (ADL) connects to the FMCs through the data loader
control panel.
The data loader gets 115v ac power from the P18 circuit breaker panel. It goes
through the data loader control panel.
The data loader digital input and output connects to FMC 1 and FMC 2 through
the data loader control panel.
The control panel must be set to the FMC position to transfer data to the
FMCs.
With the FMC source select switch set to the BOTH ON L or NORMAL position, the data comes from FMC 1.
With the source select switch set to the BOTH ON R position, the data comes
from FMC 2.
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Figure 14
Nov. 2001
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FMC DATA LOADER INTERFACE
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FMCS - ACARS INTERFACE
General
ACARS data for FMC 1 and FMC 2 goes through FMCS Transfer Relay 1.
ACARS data for the CDUs is direct.
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Figure 15
Nov. 2001
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FMC ACARS INTERFACE
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FMCS - ANALOG DISCRETES
General
Inputs from switches and valves give engine bleed air data to the FMCS. The
FMCS uses these signals to calculate the performance values.
The program pin selectable options customize the FMCS to your airline’ s configuration.
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Figure 16
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FMC ANALOG DISCRETES
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FMCS - STATUS ANNUNCIATOR INTERFACE
General
The autoflight status annunciators (ASA), have three warning lights.
The warning lights are push to reset.
The ASA also has a test switch.
The ASAs show a change of condition for these systems:
S Autopilot
S Autothrottte
S Flight management computer system (FMCS).
For Training Purposes Only
FMCS
The FMC warning light is amber when an FMC has an alert message or when
an FMC fails. The light comes also on when you put the TEST switch in position 1 or 2.
You push the FMC warning light to reset the latch and turn the light off.
Nov. 2001
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Figure 17
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FMC STATUS ANN. INTERFACE
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FMCS - PROGRAM PIN INTERFACE
General
These program pins customize the FMCS to your airline’s configuration.
There are several FMCS options available. A dip switch assembly sets the options.
These are your airplane options:
S Airplane model 737-700
S Thrust rating 22,000
S Performance code 1
S ACARS installed
S Selected course radial inhibit on EFIS
S Degrees C default
S Flight number entry
S Runway position update on TO/GA
S Weight in kilograms
S JAA flight rules
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Figure 18
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FMC PROGRAM PINS INTERFACE
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THE FOLLOWING PAGE IS FOR REFERENCE ONLY!
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115V AC
BUS 1
BUS 2
BUS 4
BUS 5
BUS 6
BUS 7
BUS 8
115V AC
VOR 2
DME 1
VOR/MB
ILS 2
DME
1
2
4
5
6
7
8
BUS 1
28V DC
UPLINK
XFER RLY
DISCRETE
CLOCK 1
BUS 4
C
BUS 7
BUS 8
B
DEU 2
FCC A
BUS 6
BUS 2
BUS 5
BUS 6
GPS 1/2
MMR
A/T COMP
BUS 2
GPWC
DEU 1
FDAU
A
ADR 4
XFR RLY 1
CLOCK
SMYD 1
FMC 1/2
IR 3
ADIRU
HGS (OPTION)
FAIL WARN
DME 1
115V AC
DEU-FMC
CDU 1
FAIL WARN
A/T COMP
ELT (OPTION)
115V AC
A/T 1
DEU
CAP NAV C/P
B
MCP 3
FQPU
CDU 1
DFCS MCP
ACARS MU
FQPU 5
FQPU
DIU (OPTION)
BUS 1
CDU 2
DLDR 1
XFER RLY
DISCRETE
LOAD ENABLE
C
DATA LOADER
CONTROL PANEL
For Training Purposes Only
ENG 2 BLEED
AIR SWITCH
ENGINE 2
ANTICE SW
RIGHT PACK
VALVE
RIGHT PACK
A/C RELAY
FCC B
FDAU
BUS 2
1
BUS 1
2
BUS 2
ENG 1 BLEED
AIR SWITCH
ON/OFF
ENGINE 1
ANTICE SW
ON/OFF
LEFT PACK
VALVE
OPEN/CLOSE
LEFT PACK
A/C RELAY
WING ANTICE
A/C ISOL
VALVE
ON/OFF
SMYD 2
28V DC
ON/OFF
DME 2
OPEN/CLOSE
OFF/HIGH/
CDU 1 OR
AUTO
PORTABLE
OFF/HIGH/
AUTO
BUS 9
ON/OFF FMC MESSAGE
FMC FAIL
OPEN/CLOSE
IFSAU
INTERSYSTEM
BUS
XFR RLY 2
PROG SW MOD
PROG SW MOD
FMC 2
FMC 1
Figure 19
Nov. 2001
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RESET
F/O NAV C/P
DEU 2
FMC MESSAGE
FMC FAIL
FMC FAIL
FMC MESSAGE
FMC CONFIG
OPTIONS
A
PORTABLE CDU
DEU 1
28V DC
OPTIONS
BITE PRINTER
RECEPTACLE
FMC WARN RESET
CAPT ASA
28V DC
FMC WARN RESET
F/O ASA
FMCS - SYSTEM SUMMARY
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FMCS - CONTROL DISPLAY UNIT
Purpose
The flight crew uses the control display unit (CDU, also called the MCDU) to
put in flight data and to select displays and modes of operation.
They also use the CDU to start ADIRU alignment.
You use the CDU to test the FMCS and other systems.
There are two CDUs in the airplane. They are functionally and physically interchangeable.
Physical Description
There are holes in the chassis for cooling air.
The equipment cooling supply and exhaust systems supply the cooling air to
the CDUs. Keep dust and dirt build—up from the CDU vent and surfaces.
The procedures to clean the CDU are in the maintenance practices section for
the CDU.
The CDU has these annunciators:
S Fail
S CALL
S MSG (Message)
S OFST (Offset)
S EXEC (Execute).
The annunciators each use a two lamp circuit board assembly. Each board assembly is line replaceable.
The EXEC light is on the right of the CDU.
The EXEC light is a lamp assembly with two lamps. The lamp assembly is line
replaceable.
The lighted switch panel is line replaceable. Six screws hold the panel in place.
The remove and replace procedures for the annunciators and the lighted switch
panel are in part two of the maintenance manual.
CAUTION:
Training Information Point
If you remove CDU number 2, install the ground lock assemblies on the landing
gear. Put the control lever for the landing gear in the OFF position.
CAUTION:
MAKE SURE THAT YOU INSTALL THE GROUND LOCK ASSEMBLIES ON THE LANDING GEAR BEFORE YOU MOVE
THE CONTROL LEVER FOR THE LANDING GEAR. YOU
WILL DAMAGE THE AIRPLANE IF YOU RETRACT THE
LANDING GEAR WHILE THE AIRPLANE IS ON THE
GROUND.
FAILURE TO OBSERVE ELECTROSTATIC DISCHARGE
PRECAUTIONARY PROCEDURES WHEN TOUCHING, REMOVING, OR INSERTING PARTS OR ASSEMBLIES MAY
RESULT IN DEGRADATION OR FAILURE OF THE CONTROL DISPLAY UNIT.
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Figure 20
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FMCS - CONTROL DISPLAY UNIT
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FMCS - CONTROL DISPLAY UNIT: CONTROLS AND DISPLAYS
Data shows in these colors:
Black - background
White - default color for text
Magenta - active waypoint, active speed target and active altitude target in
Flight plan
Green - actively tuned VOR, ILS and DME data (frequency, station ID and
course). Also, green will be used for data fields that can be toggled on and off
in which case the active state is green
Amber - FMC mismatch indications on maintenance BITE pages
Cyan - Inactive route page titles
Shaded white - data that modifies the flight plan until the EXEC key is
pushed.
Display Layout
The first line shows these data blocks:
Status
Title
Page number.
Status shows that the information on the display is the active executed plan
(ACT) or a modified plan (MOD). When the data on the display is not active or
not a part of the flight plan, the status block is blank.
The next block is the title for the display. An example of a title is POS INIT.
The last character spaces in the first line show the page number for each display. This tells the operator the active page and the total number of pages.
Data on lines two through thirteen (data field) applies to operation of the airplane.
Line fourteen is a scratch pad to enter data from the keyboard.
Also, this line shows this data:
Failure messages
Alerts during operation
Advisory prompts.
Alphanumeric Key Board
You use the key board to enter data into the FMCS and to make changes to a
flight plan.
Each time you push an alphanumeric key, the entry shows in the scratch pad
(line 14). In the scratch pad, you can edit the entry or clear it.
The MCDU shows this data in white:
Text
Scratchpad messages
Header line titles
Box prompts
Dashes, except when the dash is an integral part of the data field (i.e. negative
temperature) in which case it will be the same color as the data
Slashes, except when the slash has data on both sides in which case it will be
the same color as the data.
Function and Mode Keys
These are the function and mode keys:
S INIT REF
S RTE
S CLB
S CRZ
S DES
S MENU
S LEGS
Display Format
The multi-purpose control display unit (MCDU) data shows on the five-inch
liquid crystal display (LCD). The basic display is a set of fourteen lines. Each
line can show 24 characters. Each line can show alphanumeric characters and
symbols.
For Training Purposes Only
Color
The MCDU contains a liquid crystal display (LCD).
It shows white text on a black background.
The FANS MCDU contains a liquid crystal display (LCD).
It shows white text on a black background.
The LCD uses different colors to show flight activity and modes.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
Page: 46
AMET Ltd.
Lufthansa Technical Training
For Training Purposes Only
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMC)
S
S
S
S
S
S
B737-600/700/800
34-61
DEP ARR
HOLD
PROG
N1 LIMIT
FIX
EXEC.
These are the function and mode keys:
- INIT REF
- RTE
- DEP ARR
- ATC
- VNAV
- FIX
- LEGS
- HOLD
- FMC COMM
- PROG
- MENU
- N1 LIMIT
- EXEC.
The INIT REF key supplies access to a selection of data pages necessary to
start the FMCS and ADIRU. Also, the operator can access navigation data and
maintenance pages.
The RTE key selects the page you use to enter route data. This includes the
flight origin and destination plus the takeoff runway number.
The CLB key shows the climb modes. Top-of-climb (T/C) altitude and speed/
altitude restrictions show here. Information about time and distance to the next
waypoint is also shown here.
The CRZ key shows the cruise modes. Information about optimum altitude,
maximum altitude, step climb savings and turbulence N1 targets also show.
The DES key shows the descent modes. The end-of-descent altitude and
speed/altitude restrictions show here. Information about flight path angle, airplane vertical speed and vertical bearing also show.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
The MENU key gives access to other airplane data communication systems.
The LEGS key shows and accepts input of data about each leg of the flight
plan. Information about heading between the waypoints, speed and altitude is
also shown.
The DEP/ARR key supplies access to a selection of departure and arrival runways and procedures for the origin and destination airports.
The HOLD key lets you plan or start a hold at a waypoint or present position.
The PROG key shows this current flight status information.
The N1 LIMIT key shows the FMC calculated N1 thrust limits for specific flight
phases.
This page also shows the reduced climb thrust limits CLB-1 (Climb 1)and
CLB-2 (Climb 2). The flight crew can set N1 limit data from this page.
The FIX key shows range and bearing data from the present position to a selected reference position (SRP).
The ATC key is not active at this time and selecting this key will result in the
display of the KEY/FUNCTION INOP message in the scratchpad.
The VNAV key shows the climb, cruise, and descent performance pages.
When the VNAV key is pushed in flight, the page shown will be the active flight
phase. On the ground, the CLB page shows. The other flight phase pages may
be shown with the PREV PAGE and NEXT PAGE keys.
The FMC COMM key shows FMC communications page. This page has the
airline operational communications (AOC) datalink functions.
The EXEC key is used to make active or to modify a page with data entry
when the EXEC light comes on.
Page Select Keys
You push the NEXT PAGE key to advance the display to the next higher number page. You push the PREV PAGE key to back-up the display to the next
lower number page.
The page strings are continuous. If the first page of a string is shown (1/9) and
you push the PREV PAGE key, the display shows the last page in the string
(9/9). If you go past the last page in a string (past 9/9 for example), this takes
the display back to the first page in the string (1/9).
Line Select Keys
You use the line select keys for these operations:
Move data from the scratch pad to a data field
FOR TRAINING PURPOSES ONLY
Page: 47
AMET Ltd.
Lufthansa Technical Training
For Training Purposes Only
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMC)
B737-600/700/800
34-61
Copy data from a data field to the scratch pad
Remove data from a data field
Select a BITE operation from the maintenance bite index.
Lighted Annunciators
These are the active annunciators:
- CALL
- MSG (Message)
- OFST (Offset).
The CALL light is on when there is a call from another system other than the
FMCS.
The MSG light is on to show there is an alert or advisory message. The MSG
light stays on until you clear the message.
The OFST light is on when a parallel offset is active.
Special Keys
The keyboard has special keys in addition to the alpha-numeric keys.
These are the special keys:
S Change sign (+/-)
S Space (SP)
S Delete (DEL).
S Slash (/)
S Clear (CLR).
The change sign (+/-) and slash (/) keys are standard keys on a keyboard.
The space key (SP) puts a space into the scratchpad. This will allow the flight
crew to write messages into the scratchpad.
A push of the DEL key puts the word DELETE in the CDU scratch pad. This
lets the operator delete a data field with the line select key next to the data
field. The DEL key does not work when the scratchpad contains data. Some
data fields do not permit the DEL key function. In this case, the INVALID DELETE message shows in the CDU scratchpad.
Push the CLR key once to remove one alphanumeric character in the scratch
pad or an alert or advisory message from the scratch pad. Hold the CLR key
down for one second to remove all scratch pad data.
BITE
The FMCS BITE function does a check of all key functions.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
Page: 48
AMET Ltd.
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMC)
B737-600/700/800
34-61
TITLE
BLOCK
AMBIENT LIGHT SENSORS
FOR AUTOMATIC CONTRAST
ADJUSTMENT (2)
PAGE NUMBER
BLOCK
5-INCH DISPLAY,
14 24-CHARACTER
LINES
DATA STATUS BLOCK
DATA BLOCK
LINE SELECT KEYS
LINE SELECT KEYS
BRIGHTNESS
ADJUSTMENT
SCRATCH PAD/
MESSAGE BLOCK
INIT
REF
FUNCTION AND
MODE KEYS
FIX
RTE
LEGS HOLD
N1
MENU LIMIT
PREV
For Training Purposes Only
ANNUNCIATORS
CHANGE SIGN KEY
FMCS - CONTROL DISPLAY UNIT - CONTROLS AND DISPLAYS
Figure 21
Nov. 2001
REFRESHER COURSE
FRA US/E NM
NEXT
C PAGE PAGE
A
L
LW 1
2
3
F
A
I
5
6
LA 4
DECIMAL POINT KEY
DEP
ARR
ATC
VNAV
BRT
EXECUTE KEY
FMC
COMM PROG
EXEC
A
B
C
D
E
F
G
H
I
J
K
L
M
N
O
P
Q
R
S
T
Y
7
8
9
U
V
W
X
.
0
+/ -
Z
SP
DEL
/
EXECUTE LIGHT
M
S
G
W
O
F
S
TW
ANNUNCIATORS
DELETE KEY
SLASH KEY
CLEAR KEY
NUMERIC
CHARACTER
KEYS
CLR
ALPHABETIC
CHARACTER
KEYS
FMCS - CONTROL DISPLAY UNIT
FOR TRAINING PURPOSES ONLY
Page: 49
AMET Ltd.
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMC)
B737-600/700/800
34-61
FMCS - LCD CDU: CONTROLS AND DISPLAYS
Display Format
The multi-purpose control display unit (MCDU) data shows on the five-inch
liquid crystal display (LCD).
The basic display is a set of fourteen lines. Each line can show 24 characters.
Each line can show alphanumeric characters and symbols.
For Training Purposes Only
Color
The MCDU contains a liquid crystal display (LCD).
It shows white text on a black background.
The FANS MCDU contains a liquid crystal display (LCD).
It shows white text on a black background.
The LCD uses different colors to show flight activity and modes.
Data shows in these colors:
Black - background
White - default color for text
Magenta - active waypoint, active speed target and active altitude target in
Flight plan
Green - actively tuned VOR, ILS and DME data (frequency, station ID and
course).
Also, green will be used for data fields that can be toggled on and off in which
case the active state is green
Amber - FMC mismatch indications on maintenance BITE pages
Cyan - Inactive route page titles
Shaded white - data that modifies the flight plan until the EXEC key is
pushed.
The MCDU shows this data in white:
- Text
- Scratchpad messages
- Header line titles
- Box prompts
Dashes, except when the dash is an integral part of the data field (i.e. negative
temperature) in which case it will be the same color as the data
Nov. 2001
REFRESHER COURSE
FRA US/E NM
Slashes, except when the slash has data on both sides in which case it will be
the same color as the data.
Display Layout
The first line shows these data blocks:
- Status
- Title
- Page number.
Status shows that the information on the display is the active executed plan
(ACT) or a modified plan (MOD).
When the data on the display is not active or not a part of the flight plan, the
status block is blank.
The next block is the title for the display. An example of a title is POS INIT.
The last character spaces in the first line show the page number for each display. This tells the operator the active page and the total number of pages.
Data on lines two through thirteen (data field) applies to operation of the airplane.
Line fourteen is a scratch pad to enter data from the keyboard.
Also, this line shows this data:
S Failure messages
S Alerts during operation
S Advisory prompts.
S Alphanumeric Key Board
You use the key board to enter data into the FMCS and to make changes to a
flight plan.
Each time you push an alphanumeric key, the entry shows in the scratch pad
(line 14).
In the scratch pad, you can edit the entry or clear it.
FOR TRAINING PURPOSES ONLY
Page: 50
AMET Ltd.
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMC)
B737-600/700/800
34-61
TITLE
BLOCK
AMBIENT LIGHT SENSORS
FOR AUTOMATIC CONTRAST
ADJUSTMENT (2)
PAGE NUMBER
BLOCK
5-INCH DISPLAY,
14 24-CHARACTER
LINES
DATA STATUS BLOCK
DATA BLOCK
LINE SELECT KEYS
LINE SELECT KEYS
BRIGHTNESS
ADJUSTMENT
SCRATCH PAD/
MESSAGE BLOCK
INIT
REF
FUNCTION AND
MODE KEYS
FIX
RTE
LEGS HOLD
N1
For Training Purposes Only
ANNUNCIATORS
CHANGE SIGN KEY
C
A
L
L
F
A
I
L
DECIMAL POINT KEY
FMCS - CONTROL DISPLAY UNIT - CONTROLS AND DISPLAYS
Figure 22
Nov. 2001
REFRESHER COURSE
FRA US/E NM
DEP
ARR
ATC
VNAV
BRT
EXECUTE KEY
FMC
COMM PROG
EXEC
MENU LIMIT
A
B
C
D
E
PREV
PAGE
F
G
H
I
J
K
L
M
N
O
1
NEXT
PAGE
2
3
4
5
6
P
Q
R
S
T
7
8
9
U
V
W
X
Y
.
0
+/ -
Z
SP
DEL
/
EXECUTE LIGHT
M
S
G
O
F
S
T
ANNUNCIATORS
DELETE KEY
SLASH KEY
CLEAR KEY
NUMERIC
CHARACTER
KEYS
CLR
ALPHABETIC
CHARACTER
KEYS
FMCS - CONTROL DISPLAY UNIT
FOR TRAINING PURPOSES ONLY
Page: 51
AMET Ltd.
Lufthansa Technical Training
For Training Purposes Only
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMC)
B737-600/700/800
34-61
Function and Mode Keys
These are the function and mode keys:
S INIT REF
S RTE
S CLB
S CRZ
S DES
S MENU
S LEGS
S DEP ARR
S HOLD
S PROG
S N1 LIMIT
S FIX
S EXEC.
These are the function and mode keys:
- INIT REF
- RTE
- DEP ARR
- ATC
- VNAV
- FIX
- LEGS
- HOLD
- FMC COMM
- PROG
- MENU
- N1 LIMIT
- EXEC.
The INIT REF key supplies access to a selection of data pages necessary to
start the FMCS and ADIRU. Also, the operator can access navigation data and
maintenance pages.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
The RTE key selects the page you use to enter route data. This includes the
flight origin and destination plus the takeoff runway number.
The CLB key shows the climb modes. Top-of-climb (T/C) altitude and speed/
altitude restrictions show here. Information about time and distance to the next
waypoint is also shown here.
The CRZ key shows the cruise modes. Information about optimum altitude,
maximum altitude, step climb savings and turbulence N1 targets also show.
The DES key shows the descent modes. The end-of-descent altitude and
speed/altitude restrictions show here. Information about flight path angle, airplane vertical speed and vertical bearing also show.
The MENU key gives access to other airplane data communication systems.
The LEGS key shows and accepts input of data about each leg of the flight
plan. Information about heading between the waypoints, speed and altitude is
also shown.
The DEP/ARR key supplies access to a selection of departure and arrival runways and procedures for the origin and destination airports.
The HOLD key lets you plan or start a hold at a waypoint or present position.
The PROG key shows this current flight status information.
The N1 LIMIT key shows the FMC calculated N1 thrust limits for specific flight
phases.
This page also shows the reduced climb thrust limits CLB-1 (Climb 1)and
CLB-2 (Climb 2). The flight crew can set N1 limit data from this page.
The FIX key shows range and bearing data from the present position to a selected reference position (SRP).
The ATC key is not active at this time and selecting this key will result in the
display of the KEY/FUNCTION INOP message in the scratchpad.
The VNAV key shows the climb, cruise, and descent performance pages.
When the VNAV key is pushed in flight, the page shown will be the active flight
phase.
On the ground, the CLB page shows.
The other flight phase pages may be shown with the PREV PAGE and NEXT
PAGE keys.
The FMC COMM key shows FMC communications page. This page has the
airline operational communications (AOC) datalink functions.
FOR TRAINING PURPOSES ONLY
Page: 52
AMET Ltd.
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMC)
B737-600/700/800
34-61
TITLE
BLOCK
AMBIENT LIGHT SENSORS
FOR AUTOMATIC CONTRAST
ADJUSTMENT (2)
PAGE NUMBER
BLOCK
5-INCH DISPLAY,
14 24-CHARACTER
LINES
DATA STATUS BLOCK
DATA BLOCK
LINE SELECT KEYS
LINE SELECT KEYS
BRIGHTNESS
ADJUSTMENT
SCRATCH PAD/
MESSAGE BLOCK
INIT
REF
FUNCTION AND
MODE KEYS
FIX
RTE
LEGS HOLD
N1
For Training Purposes Only
ANNUNCIATORS
CHANGE SIGN KEY
C
A
L
L
F
A
I
L
DECIMAL POINT KEY
FMCS - CONTROL DISPLAY UNIT - CONTROLS AND DISPLAYS
Figure 23
Nov. 2001
REFRESHER COURSE
FRA US/E NM
DEP
ARR
ATC
VNAV
BRT
EXECUTE KEY
FMC
COMM PROG
EXEC
MENU LIMIT
A
B
C
D
E
PREV
PAGE
F
G
H
I
J
K
L
M
N
O
1
NEXT
PAGE
2
3
4
5
6
P
Q
R
S
T
7
8
9
U
V
W
X
Y
.
0
+/ -
Z
SP
DEL
/
EXECUTE LIGHT
M
S
G
O
F
S
T
ANNUNCIATORS
DELETE KEY
SLASH KEY
CLEAR KEY
NUMERIC
CHARACTER
KEYS
CLR
ALPHABETIC
CHARACTER
KEYS
FMCS - CONTROL DISPLAY UNIT
FOR TRAINING PURPOSES ONLY
Page: 53
AMET Ltd.
Lufthansa Technical Training
For Training Purposes Only
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMC)
B737-600/700/800
34-61
The EXEC key is used to make active or to modify a page with data entry
when the EXEC light comes on.
Page Select Keys
You push the NEXT PAGE key to advance the display to the next higher number page. You push the PREV PAGE key to back-up the display to the next
lower number page.
The page strings are continuous. If the first page of a string is shown (1/9) and
you push the PREV PAGE key, the display shows the last page in the string
(9/9).
If you go past the last page in a string (past 9/9 for example), this takes the
display back to the first page in the string (1/9).
Line Select Keys
S You use the line select keys for these operations:
S Move data from the scratch pad to a data field
S Copy data from a data field to the scratch pad
S Remove data from a data field
S Select a BITE operation from the maintenance bite index.
Lighted Annunciators
These are the active annunciators:
- CALL
- MSG (Message)
- OFST (Offset).
The CALL light is on when there is a call from another system other than the
FMCS.
The MSG light is on to show there is an alert or advisory message.
The MSG light stays on until you clear the message.
The OFST light is on when a parallel offset is active.
Special Keys
Nov. 2001
REFRESHER COURSE
FRA US/E NM
The keyboard has special keys in addition to the alpha-numeric keys.
These are the special keys:
S Change sign (+/-)
S Space (SP)
S Delete (DEL).
S Slash (/)
S Clear (CLR).
The change sign (+/-) and slash (/) keys are standard keys on a keyboard.
The space key (SP) puts a space into the scratchpad. This will allow the flight
crew to write messages into the scratchpad.
A push of the DEL key puts the word DELETE in the CDU scratch pad.
This lets the operator delete a data field with the line select key next to the data
field.
The DEL key does not work when the scratchpad contains data. Some data
fields do not permit the DEL key function.
In this case, the INVALID DELETE message shows in the CDU scratchpad.
Push the CLR key once to remove one alphanumeric character in the scratch
pad or an alert or advisory message from the scratch pad.
Hold the CLR key down for one second to remove all scratch pad data.
BITE
The FMCS BITE function does a check of all key functions.
FOR TRAINING PURPOSES ONLY
Page: 54
AMET Ltd.
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMC)
B737-600/700/800
34-61
TITLE
BLOCK
AMBIENT LIGHT SENSORS
FOR AUTOMATIC CONTRAST
ADJUSTMENT (2)
PAGE NUMBER
BLOCK
5-INCH DISPLAY,
14 24-CHARACTER
LINES
DATA STATUS BLOCK
DATA BLOCK
LINE SELECT KEYS
LINE SELECT KEYS
BRIGHTNESS
ADJUSTMENT
SCRATCH PAD/
MESSAGE BLOCK
INIT
REF
FUNCTION AND
MODE KEYS
FIX
RTE
LEGS HOLD
N1
For Training Purposes Only
ANNUNCIATORS
CHANGE SIGN KEY
C
A
L
L
F
A
I
L
DECIMAL POINT KEY
FMCS - CONTROL DISPLAY UNIT - CONTROLS AND DISPLAYS
Figure 24
Nov. 2001
REFRESHER COURSE
FRA US/E NM
DEP
ARR
ATC
VNAV
BRT
EXECUTE KEY
FMC
COMM PROG
EXEC
MENU LIMIT
A
B
C
D
E
PREV
PAGE
F
G
H
I
J
K
L
M
N
O
1
NEXT
PAGE
2
3
4
5
6
P
Q
R
S
T
7
8
9
U
V
W
X
Y
.
0
+/ -
Z
SP
DEL
/
EXECUTE LIGHT
M
S
G
O
F
S
T
ANNUNCIATORS
DELETE KEY
SLASH KEY
CLEAR KEY
NUMERIC
CHARACTER
KEYS
CLR
ALPHABETIC
CHARACTER
KEYS
FMCS - CONTROL DISPLAY UNIT
FOR TRAINING PURPOSES ONLY
Page: 55
AMET Ltd.
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMCS)
B737-600/700/800
34-61
FMCS - LCD CDU DATA LOAD
General
You use the airborne data loader (ADL) to load the operational program software (OPS) into the CDUs.
To load the OPS into the CDUs, set the data loader selector to the CDU position and the data loader 3-position switch to the L or R position depending on
which CDU is to be loaded.
This connects the loader to the CDU being loaded.
Preparation
This is a summary of the steps to load the OPS with an ADL:
S Airplane must be on the ground
S Apply electrical power to the airplane
S Set the data loader selector to the CDU position
S Set the data loader 3-position switch to the CDU you will load (the L position loads CDU 1 and the R position loads CDU 2)
S Open the data loader access door
S Put the CDU OPS software diskette into the ADL.
For Training Purposes Only
The CDUs show the DATA LOADER page when the CDU receives valid data
from the loader.
The data load process is automatic.
When the CDU shows the message LOAD COMPLETE, remove the diskette
from the ADL and perform the applicable software verification procedure.
Return the data loader selector to the NORM position after the transfer is complete.
NOTE:
Do not interrupt electrical power to the system during software loading.
If power is interrupted, you will need to do the software load procedure again.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
Page: 56
AMET Ltd.
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMCS)
B737-600/700/800
34-61
DATA LOAD SELECTOR
C
SINGLE SYS R
L
CAPT
F/O
LWR
UPR
SYSTEM SELECT
NORMAL FMC
CDU
DATA LOADER
DATA LOADER
DATA LOADER
CONTROL PANEL
For Training Purposes Only
P18-2 CIRCUIT
BREAKER PANEL
Figure 25
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FMS LCD CDU-DATA LOAD
FOR TRAINING PURPOSES ONLY
Page: 57
AMET Ltd.
Lufthansa Technical Training
For Training Purposes Only
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMC)
B737-600/700/800
34-61
FMCS - CDU CONTROLS AND DISPLAYS
Display Format
The CDU (also called the MCDU) data displays show on the five—inch CRT.
The basic display is a set of fourteen lines. Each line can show 34 characters.
Each line can show alphanumeric characters and symbols.
The first line shows these data blocks:
S Status
S Title
S Page number.
Status shows that the information on display is the active executed plan (ACT)
or a modified plan (MOD).
When the data on the display is not active or not a part of the flight plan, the
status block is blank.
The next block identifies the title for the display. An example of a title is POS
INIT.
The last character spaces in the first line show the page number for each display. This tells the operator the active page and the total number of pages.
Data on lines two through thirteen (data field) applies to operation of the airplane.
Line fourteen is a scratch pad to enter data from the keyboard.
Also, this line shows this data:
S Failure messages
S Alerts during operation
S Advisory prompts.
Alphanumeric Key Board
You use the key board to enter data into the FMCS and to make changes to a
flight plan.
Each time you push an alphanumeric key, the entry shows in the scratch pad
(line 14).
In the scratch pad, you can edit the entry or clear it.
The space key (SP) puts a space into the scratchpad.
Aug 99
REFRESHER COURSE
FRA US/E NM
Flight Phase Keys
These are the flight phase keys:
S Climb (CLB)
S Cruise (CRZ)
S Descent (DES).
The CLB key shows the climb modes. Top—of—climb (T/C), altitude, and
speed/altitude limits show here.
The CRZ key shows the cruise modes. Information about optimum altitude and
turbulence N1 targets also show.
The DES key shows the descent modes. The end—of—descent altitude and
airport speed/altitude restrictions also show here.
Function Keys
These are the function keys:
S INIT REF (Initialization/Reference)
S RTE (ROUTE)
S MENU
S LEGS
S N1 LIMIT
S FIX (Fix Information)
S DEP ARR (Departure Arrivals)
S HOLD
S PROG (Flight Progress)
S EXEC (Execute).
The INIT REF key supplies access to a selection of data pages necessary to
start the FMCS and ADIRU. Also, the operator can access navigation data and
maintenance pages.
The RTE key selects the page you use to enter route data. This includes the
flight origin and destination plus the takeoff runway number.
The MENU key gives access to subsystems.
The LEGS key shows and accepts input of data about each leg of the flight
plan for both the lateral and vertical paths.
FOR TRAINING PURPOSES ONLY
Page: 58
AMET Ltd.
B737-600/700/800
34-61
For Training Purposes Only
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMC)
Figure 26
Aug 99
REFRESHER COURSE
FRA US/E NM
FMC CDU CONTROLS AND DISPLAYS
FOR TRAINING PURPOSES ONLY
Page: 59
AMET Ltd.
Lufthansa Technical Training
For Training Purposes Only
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMC)
B737-600/700/800
34-61
FMCS - CDU CONTROLS AND DISPLAYS (cont.)
The N1 LIMIT key shows the calculated N1 limits for these functions:
S G/A (Go—around)
S CON (Maximum continuous thrust)
S CLB (Climb)
S CRZ (Cruise).
This page also shows the reduced climb thrust limits CLB—1 (Climb 1) and
CLB—2 (Climb 2). You can set both limits from this page.
The FIX key shows range and bearing data from the present position to a different position.
The DEP/ARR key supplies access to a selection of departure and arrival data
for the origin and destination airports.
The HOLD key lets you plan or start a hold at a waypoint or present position.
The PROG key shows this current flight status information:
S Fuel remaining at waypoint
S Navigation radio status
S Wind
S Path error
S ETA.
Push the EXEC key to make active or to modify a page with data entry when
the EXEC light comes on.
Page Select Keys
You push the NEXT PAGE key to advance the display to the next higher number page. You push the PREV PAGE key to back—up the display to the next
lower number page.
The page strings are continuous. If the first page of a string is shown (1/9) and
you push the PREV PAGE key, the display shows the last page in the string
(9/9). If you go past the last page in a string (past 9/9 for example), this takes
the display back to the first page in the string (1/9).
Line Select Keys
You use the line select keys for these operations:
S Move data from the scratch pad to a data field
S Copy data from a data field to the scratch pad
Aug 99
REFRESHER COURSE
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S Remove data from a data field
S Select a BITE operation from the maintenance bite index.
Lighted Annunciators
These are the active annunciators:
S FAIL
S MSG (Message)
S CALL
S OFST (Offset).
The FAIL light is on if there is a system failure found by BITE.
The MSG light is on to show there is an alert or advisory message. The MSG
light stays on until you clear the message.
The CALL light is on when there is a call from another subsystem.
The OFST light is on when a parallel offset is active.
Special Keys
The keyboard has special keys in addition to the alpha— numeric keys.
These are the special keys:
S Change sign (+/-)
S Slash (/)
S Clear (CLR)
S Delete (DEL).
The change sign (+/-) and slash (/) keys are standard keys on a keyboard.
Push the CLR key once to remove one alpha—numeric character in the
scratch pad or an alert or advisory message from the scratch pad.
Hold the CLR key down for one second to remove all scratch pad data.
A push of the DEL key puts the word DELETE in the CDU scratch pad. This
lets the operator delete a data field with the line select key next to the data
field. The DEL key does not work when the scratchpad contains data.
Some data fields do not permit the DEL key function.
In this case, the INVALID DELETE message shows in the CDU scratchpad.
BITE
The FMCS BITE function does a check of all key functions.
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FMC CDU CONTROLS AND DISPLAYS
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FMCS - AIRBORNE DATA LOADER
Purpose
You use the airborne data loader (ADL) to load data into selected LRUs and to
record data from selected LRUs.
You use the data loader control panel to select the LRU.
Physical Description/Features
The airborne data loader (ADL) is an ARINC—615 high speed loader.
These are the ADL features:
S Access door
S Disk drive
S Disk drive light
S Disk drive eject button
S Status indicator panel.
These messages show on the ADL status indicator panel:
S PROG (Data transfer in progress)
S CHNG (Diskette change required)
S COMP (Data transfer complete)
S RDY (The loader is ready for operation.
If RDY flashes, the LRU has stopped the data transfer to check the data.
The transfer will continue automatically)
S XFER (Data transfer failure)
S R/W (Unable to access diskette data)
S HRDW (Internal loader failure. If HRDW flashes, there is no communication
between the loader and the LRU).
The data loader does an internal self test at power up.
During the self test, all the front panel status indicators flash. At the end of the
self test, the indicators go off.
If there is a failure at power up, the HRDW status indicator is on.
If the self test is satisfactory, the RDY message shows.
The other indicators come on as the data loader moves through the load or
transfer.
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Figure 28
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FMC AIRBORNE DATA LOADER
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FMCS - TRANSFER RELAYS
Purpose
There are two FMCS transfer relays. The relays select the FMC to send data
to the systems that interface with the FMCS.
The FMC SOURCE SELECT SWITCH controls the relays.
The source select switch is in the flight deck.
Location
The relays are on the E5—2 shelf in the electronic equipment compartment.
For Training Purposes Only
Physical Description
The relays mechanically latch (latch-type relays) and are hermetically sealed.
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FMC XFR RELAYS
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FMCS - DISPLAYS: CDU, POWER UP
General
The CDU and FMCs do tests at power up. If the tests pass, the CDUs show
the IDENT page for a normal power up.
For Training Purposes Only
Menu Key
Push the MENU key on a CDU to see the full menu page on both CDUs.
The MENU page shows all the subsystems that connect to the CDUs.
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PUSH LSK
< FMC
NORMAL POWER UP
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FMS POWER UP, NORMAL DISLPLAY
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FMC
At power up, each FMC does a check of the status of the other FMC.
If the primary FMC fails at power up, the FMC menu prompt does not show.
The FMC warning light on the autoflight status annunciators also comes on.
If the secondary FMC fails, the primary FMC shows the SINGLE FMC OPERATION message in the scratch pads.
If the transfer switch is in normal, the FMC warning light comes on.
CDU
A CDU display is blank if the CDU fails at power up.
For Training Purposes Only
Other Tests
The FMCs also check these functions at power up:
S Airplane and engine configuration program pins for parity
S Cross compare FMC 1 and FMC 2 data bases and operational flight programs.
For example, the message OP PROGRAM INVALID shows if the operational
flight program (OFP) of the primary FMC is invalid at power up.
If the secondary FMC has a valid OFP, the message tells the operator to switch
to the both on right position.
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FMS POWER UP, NON-NORMAL DISPLAY
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FMCS - DISPLAYS: CDU, IDENT PAGE
Purpose
The IDENT page shows the FMCS data base and program configuration data.
Also, you can select the POS INIT and INDEX pages from the IDENT page.
Page Access
The IDENT page shows after power up if the self—tests are normal (see the
graphic for the other inputs).
Page 1/2 Information
Page 2/2 Information
Line select key 1L shows the performance default data base number.
Line select key 2L shows the identification number of the software options
data base.
Line select key 5L shows the identification number of the performance data
base.
This line is blank if the data base is not loaded.
You can select the INIT/REF INDEX page with line select key 6L.
For Training Purposes Only
Line select key 1L shows the airplane model.
The airframe/engine program pin configuration sets this information. This line is
blank if the FMC finds a parity error for the airframe/engine program pins or a
valid performance data base is not loaded into the FMC.
Line select key 2L shows the navigation data base number loaded in the
FMC. This line is blank if a navigation data base is not loaded.
Line select key 4L shows the operational program software part number.
Line select key 5L can show the Smiths Industries operational program part
number.
To show the number, put the word SIPART into the scratch pad and select key
5L. This line is blank when the part number is not shown.
You can select the INIT/REF INDEX page with key 6L.
Line select key 1R shows the engine thrust rating.
This information is set by the airframe/engine program pin configuration.
This line is blank if the FMC finds a parity error for the airframe/engine program
pins or a valid performance data base is not loaded into the FMC.
Line select key 2R shows the active data base.
Key 3R shows the data base that is not active.
You can interchange the data on these two lines to activate a new data base or
recall the old one. The interchange can only be done when the airplane is on
the ground.
Line select key 5R shows there is supplemental data and gives the effective
date of the data. The line is blank if an effective date is not set or there is no
supplemental data.
Line select key 6R selects the POS INIT page.
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FMC IDENT PAGE
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FMCS - DISPLAYS: CDU, INIT/REF INDEX PAGE
Purpose
The INIT/REF INDEX page shows a menu of pages you can use to initialize
the FMCS, the ADIRU and other reference data.
Also, you can use this page to access the FMCS MAINT BITE INDEX page.
Page Access
To select this page, push line select key 6L on pages that show the index
prompt and are not BITE pages.
The INDEX prompt on BITE pages moves the display back to the last menu.
For Training Purposes Only
Information
Select line select key 1L through line 5L to show the first page of the selected
prompt.
Select line select key 6L to show the lateral offset page.
Select line select key 1R to show the navigation data reference page.
Select line select key 5R to show configuration data for loadable software.
Select tine select key 6R to show the maintenance bite index page.
The bite page only shows with the airplane on the ground and the
ground speed is below 20 knots.
With the airplane in the air, the NAV STATUS prompt shows in place of the
MAINT prompt.
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FMC INIT/REF PAGE
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FMCS - DISPLAYS: CDU, POSITION PAGES
Purpose
There are three position pages.
They show this information:
S Present position and groundspeed calculated by the FMCS and each
ADIRU
S Box prompts to initialize the ADIRUs.
The box prompts show that data must be set to complete the preflight. The
dash prompts show the data is optional.
For Training Purposes Only
Page Access
You use the INIT REF function key or these CDU pages, to go to the first position page:
S INIT/REF INDEX
S IDENT
S TAKEOFF REF.
Page 1/3 Information
Line select key 2L shows dash prompts for an airport identifier. KBFI (Boeing
Field International) is an example of a valid identifier.
The identifiers you put here must also be in the navigation data base.
If the identifier you put in is valid and is in the data base, the latitude/longitude
(LAT/LON) for the airport identifier shows at line 2R.
Line select key 3L shows dash prompts for airport gate identifiers.
If the identifier you put in is valid and is in the data base, the LAT/LON for the
gate shows at LSK 3R.
You must put the airport identifier in first.
Line select key 5L shows airplane clock input.
The clock input (time and date) to both FMCs is from the captain’s clock.
If the captain’s clock does not operate, both FMCs use the F/O’s clock.
If a valid clock is not available, you can set time with the CDU.
You can select the index page at key 6L
Aug 99
REFRESHER COURSE
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Line select key 1R shows the last calculated FMCS present position. This data
is kept at power down.
Line select key 2R and 3R show the LAT/LON position for the reference airport
and gate identifiers set at Line select key 2L and 3L.
Box prompts at Line select key 4R show the ADIRUs are ready for alignment
and the airplane is on the ground.
See the air data inertial reference unit section for more information on aligning
the ADIRU.(AMM PART 1, 34— 21)
A heading update can be set in Line select key 5R for an ADIRU in the attitude
(ATT) mode.
Line select key 5R is blank if there is no ADIRU in the ATT mode.
2/3 Information
Information on page 2 shows the current position and ground speed calculated
by the different systems.
The information can be line selected to the scratch pad to initialize the ADIRUs.
The radio position data does not show on the ground or in the air and radio
position data is not valid.
Page 3/3 Information
This page shows the bearing and distance between the FMCS calculated position shown on page 2/3 (Line select key 1L), and the position of the systems
shown on page 3/3.
Page 3/3 also provides the capability to update the FMCS calculated position to
one of the positions shown by line selection and execute (EXEC).
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GPS L
N40_38.1
W73_46.0
Figure 34
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FMC POSITION PAGES
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FMCS - DISPLAYS: CDU MESSAGES
General
The FMCS shows alert or advisory messages when there is a condition that
degrades the system.
The messages show one at a time, by priority, on the CDU scratch pad.
All advisory and alert messages turn on the CDU MSG annunciator.
Only an alert message turns on the FMC warning lights on the autoflight status
annunciators.
If the scratch pad is empty, any message shows immediately.
Some messages replace other messages and show immediately.
Other messages do not show until the scratch pad field is clear but the CDU
MSG light still comes on.
To clear a message, push the CLR key or remove the conditions that cause the
message.
Other messages clear when you change the page.
The CDUs show these message types in this priority:
S Alert
S Entry error advisory
S Advisory.
Below are examples of messages that are maintenance related.
The operations manual has a complete list of the CDU messages.
Alert Messages
Alert messages tell about conditions which you should know and correct before
you use the FMCS.
The messages show on both CDUs.
ALERT MESSAGE
CONDITION
DATA BASE INVALID
THE TEST OF THE NAV DATA
BASE HAS FAILED
NAV DATA OUT OF DATE
THE NAVIGATION DATA BASE EFFECTIVITY IS OUT OF DATE
ENTER IRS POSITION
AN IRS IS IN THE ALIGN MODE
AND NEEDS A POSITION SET
CYCLE IRS OFF-NAV
IRS IS NOT ABLE TO COMPLETE
ALIGNMENT UNDER CURRENT
CONDITIONS
IRS MOTION
THE IRS HAS AUTOMATICALLY
RESTARTED THE ALIGNMENT
DUE TO DETECTION OF EXCESSIVE MOTION
MODEL ENGINE DATA INVALID
A VALID PERFORMANCE DATA
BASE IS NOT AVAILABLE OR HAS
FAILED
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FMCS - DISPLAYS: CDU MESSAGES (cont‘d.)
Entry Error Advisory Messages
These messages show that data set in the scratch pad is not correct.
Clear the message and enter the data again.
These messages show only on the CDU where the entry error is made.
ENTRY ERROR MESSAGE
CONDITION
INVALID ENTRY
THE DATA HAS AN INCORRECT
FORMAT OR RANGE
NOT IN DATA BASE
A SEARCH OF THE NAV DATA
BASE DID NOT FIND THE REQUIRED DATA
For Training Purposes Only
Advisory Messages
Advisory messages show the FMC/CDU system status.
If the MSG annunciators are on but no message shows, you must first CLR the
scratch pad of any messages.
These messages show on both CDUs.
ADVISORY MESSAGE
CONDITION
PROGRAM PIN ERROR
THE AIRFRAME/ENGINE PROGRAM PIN CONFIGURATION IS
NOT VALID
CHECK FMC FUEL QUANTITY
THE FMCS DETECTED AN UNEXPECTED DROP IN THE FUEL
QUANTITY
MODEL/ENG CFG INVALID
THE AIRFRAME/ENGINE PROGRAM PINS DO NOT AGREE WITH
DATA STORED IN THE PERFORMANCE DATA BASE.
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Figure 35
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FMC CDU MESSAGES
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FMCS - DISPLAYS: CDS FLIGHT MODE ANNUNCIATIONS
FMCS Flight Mode Annunciation
These are the active FMCS flight mode annunciations (FMA) that can show
during FMCS operation:
S Autothrottle (A/T) mode annunciation
S Pitch mode annunciation
S Roll mode annunciation.
See the digital flight control system section for more information about mode
annunciation. (AMM PART 1, ATA 22—11)
Autothrottle Mode Annunciation
The A/T mode annunciation shows in column one of the FMA.
These are the autothrottle modes that can show during FMCS operation:
S FMC SPD
S N1
S RETARD
S ARM.
Pitch Mode Annunciations
The pitch mode annunciation shows in column two of the FMA.
These are the pitch modes that can show during FMCS operation:
S VNAV PTH
S VNAV SPD.
For Training Purposes Only
Roll Mode Annunciation
The roll mode annunciation LNAV, shows in column three of the FMA.
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FMC FLIGHT MODE ANN.
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FMCS DISPLAYS - CDS - THRUST MODE
General
The thrust mode annunciation display shows the active N1 limit mode calculated by the FMCS.
The reference N1 bugs (2) show the N1 limit for the active mode.
The N1 limit mode controls the N1 limit for autothrottle operation.
The reference N1 readouts may be set manually. They are set with the N1 SET
CONTROL inner knob.
When the reference N1 readout is set manually, the N1 bugs show the N1 reference readout value.
These manually set limits have no effect on autothrottle operation.
Thrust Mode Display
These thrust modes show on the engine display:
S TO (Takeoff)
S R-T O (Reduced takeoff)
S CLB (Climb)
S R-CLB (Reduced climb)
S CRZ (Cruise)
S CON (Continuous)
S GA (Go-around)
S - - - (no computed data from the FMCS).
Display Control
When the N1 SET CONTROL outer knob is set to the AUTO position, the
thrust mode display and N1 bug position are set by the FMCS as a function of
DFCS mode logic.
To override automatic control, you can line select another mode from the N1
limit page.
The displays go back to automatic control when the DFCS pitch mode
changes.
When the outer knob is set to the BOTH, 1 or 2 position, you can manually set
the reference N1 bugs and the N1 reference readouts will be displayed above
the digital N1 displays.
With the outer knob in the AUTO position, the readout is blank.
Non-Normal Operation
In automatic operation, the thrust mode display and reference N1 bug readout
are calculated by the FMCS.
If the FMCS calculations are not valid, the autothrottle limit message A/T LIM
shows.
The autothrottle computer then calculates a single N1 limit for both engines.
For Training Purposes Only
Only one thrust mode can show and be active.
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N1 L I M I T
N1 SET
AUT O
AUTO
1
BOTH
For Training Purposes Only
REF N1 BUG
THRUST MODE
DISPLAY
- TO
- R-TO
- CLB
- R-CLB
- CRZ
- GA
- CON
- - - - A/T LIM
R-CLB
89.8
TAI
87.1
0
2
10
8
6
4
89.8
TAI
87.1
0
2
10
8
6
N1
CON
99. 8/
99. 8%
CL B
89. 8/
89. 8%
83. 8/ 83 . 8%
CRZ
- - - - - - REDU CE D CL B - - - - - - CL B - 2
CL B- 1 < SEL >
ENGINE DISPLAY CONTROL PANEL
ACTUAL N1
101. 6/ 101 . 6%
GA
2
ENGINE DISPLAY
1/ 1
REF N1 READOUT
N1 LIMIT PAGE
A CT E CON CL B
CRZ A L T
FL 3 3 0
T GT S P D
2004.
280/ . 720
S P D RE S T
E RR
250/ 100 00
- - - - - - - - - - - 87.
- - - < MA X RAT E
1/ 1
A T C R1 0 2
2 50 0A
T O C R1 0 2
3 Z/ 1 9 NM
A T C R1 0 2
3 10 LO
CL B 1 - N1
1/ 8 7. 1%
- - - - - - - E NG OU T >
< MA X A NGL E
RT A >
4
CLIMB PAGE
FMCS - DISPLAYS - CDS - THRUST MODE
Figure 37
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FMC THRUST MODE ANN.
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FMCS DISPLAYS - CDS - AIRSPEED INDICATION
General
The takeoff and landing airspeed bugs show on the PFD speed tape indication.
The bugs are set automatically by the FMC or, they can be set manually by the
flight crew using the speed reference selector on the engine control panel.
When set manually, the airspeeds show on the PFD speed tape indication and
a digital display of the set value shows.
You also use the speed reference selector to manually set the airplane takeoff
or landing gross weight.
CDS will use this weight value to calculate and display the flap maneuvering
speeds.
Speed Reference Selector
The outer control has these functions:
- AUTO (the FMCS supplies the reference airspeeds and gross weight
automatically)
- V1 (shows the takeoff decision speed on the ground and shows INVALID
ENTRY in-flight)
- VR (shows takeoff rotation speed on the ground and shows INVALID
ENTRY in-flight)
- WT (the pilot can set the gross weight manually)
- VREF (shows the landing reference speed (REF) in the air and shows
INVALID ENTRY on the ground)
- Triangle symbol (shows an airspeed bug the pilot can set)
SET (the FMC and the inner control cannot move the airspeed bugs).
The inner control sets the selected bug to the desired airspeed or sets gross
weight.
The control is spring loaded to center.
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Takeoff
This data shows on the PFD speed tape indication:
Digital display (the display shows if the airspeed bug(s) or weight is set with the
speed reference selector)
S V1 (decision speed)
S VR (rotation speed)
Selected speed (indicates the airspeed manually set in the IAS/MACH display
on the DFCS mode control panel (MCP) or the FMC computed airspeed when
the IAS/MACH window is blank)
S V2 (single engine climb speed)
S V2+15 (single engine climb speed plus 15 knots)
S Flap maneuver speed (maneuver speed for flap position shown. It does
not show for 30 or 40 units of flap.)
S Flaps up speed (shows after zero fuel weight is set in the CDU and takeoff
gross weight is calculated, or after takeoff gross weight is set with the speed
reference selector)
Approach/Landing
This data can show on the PFD speed tape during approach:
S REF (landing reference speed VREF is set on the CDU APPROACH
REF page or set with the speed reference selector)
S VREF+15 (this shows after VREF is set)
S Flap maneuver speed (maneuver speed for flap position shown).
FOR TRAINING PURPOSES ONLY
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34-61
SELECTED SPEED
FLAP MANEUVERING SPEED
149
180 1
SPEED
TREND
VECTOR
160
140
122
VR
V1
135
154
220
V2+15
200
SELECTED SPEED
(V2 SPEED SHOWS
AT TAKEOFF)
TAKEOFF REFERENCE
SPEEDS
162
140 REF
132
120
80
WT LB
104000
For Training Purposes Only
LANDING
REFERENCE SPEED
(VREF)
DIGITAL DISPLAY
SPD REF
AUTO
OUTER CONTROL
TAKEOFF
(TYPICAL)
15
VREF + 15
CURRENT AIRSPEED
100
FLAP MANEUVER
SPEED
180
V1
INNER CONTROL
APPROACH/LANDING
(TYPICAL)
SET
VR
WT
FMCS - DISPLAYS - CDS - AIRSPEED INDICATION
VREF
SPEED REFERENCE SELECTOR
Figure 38
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FMC MACH AIRSPEED INDICATION
FOR TRAINING PURPOSES ONLY
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34-61
FMCS DISPLAYS - CDS - MAP DISPLAY
General
The FMCS provides the navigation data for the MAP mode displays on the
common display system (CDS).
There are two types of navigation data, dynamic data and background data.
Dynamic data changes as a function of time while background data is stationary data that does not move as a function of time.
The FMCS formats and transmits the data (FMC bus 08 and FMC bus 09) to
show the airplane position with respect to the flight plan and vertical profile.
The CDS controls symbol color, size, and brightness.
For Training Purposes Only
Map Mode
The map mode shows the progress of the flight and is the normal display the
crew uses for navigation in flight.
This display may show in either the expanded mode or the centered mode.
The display is dynamic and moves as the airplane moves.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
Symbol Definitions
This data is shown:
S Active waypoint distance (distance to go to the active waypoint. White)
S Active waypoint ETA (estimated time of arrival for the active waypoint.
White)
S T/C altitude profile point (top of climb position in the active route. Green)
S T/D altitude profile point (top of descent position in the active route. Green)
S E/D altitude profile point (end of descent position in the active route. Green)
S S/C altitude profile point (step climb position in the active route. Green)
S Speed profile point (deceleration point in the active route. Green)
S Active waypoint (next waypoint in the active route. Magenta)
S Range to altitude arc (range at which the airplane will reach the MCP altitude. Green)
S Trend vector (predicted position of airplane at the end of 30, 60 or 90 second intervals. White)
S Inactive waypoint (waypoint other than the active waypoint in the active
route. White)
S Vertical deviation scale (vertical deviation from the calculated descent profile. Scale is white and pointer is magenta)
S Map options (options selected on the EFIS control panel. Cyan)
S Wind data (wind speed and direction. White)
S Map source (source of dynamic and background data. Green)
S Navaids (navigation stations within the selected map area. Cyan)
S Off route waypoints (waypoints within the selected map area but not in the
active route. Cyan)
S Airports (airports within the selected map area. Cyan)
S Route data (altitude constraints and ETAs for the waypoint in the active
route. Magenta or white)
S Track angle (airplane track. White).
FOR TRAINING PURPOSES ONLY
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GROUND SPEED
B737-600/700/800
34-61
GS 351 TAS 338
336_/15
140
TRK
CHN
0838.4Z
32.5 NM
MAG
WIND DATA
INACTIVE
WAYPOINT
DECE
L
TAU
OFF ROUTE
WAYPOINT
RID
TRACK ANGLE
MAP OPTIONS
40
MUC
ALTITUDE PROFILE
POINT
T/D
ARPT
WPT
STA
DINKU
EDDF
2100
ACTIVE
WAYPOINT
VERTICAL
DEVIATION
SCALE
AIRPORT
FRA
TREND VECTOR
For Training Purposes Only
ACTIVE WAYPOINT
DISTANCE
SPEED PROFILE
POINT
MARK
RANGE TO
ALTITUDE ARC
ACTIVE
WAYPOINT ETA
NAVAID
MAP SOURCE
FMC L
EXPANDED MAP MODE
Figure 39
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FMC MAP DISPLAY
FOR TRAINING PURPOSES ONLY
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FMCS DISPLAYS - CDS - PLAN DISPLAY
General
The FMCS provides the navigation data for the PLAN mode displays on the
common display system (CDS).
There are two types of navigation data, dynamic data and background data.
Dynamic data changes as a function of time while background data is stationary data that does not move as a function of time.
The FMCS formats and transmits the data (FMC bus 08 and FMC bus 09) to
accurately show the airplane position with respect to the flight plan and vertical
profile.
The CDS controls symbol color, size, and brightness.
Symbol Definitions
This data shows:
- Distance to go to the active waypoint (white)
- Estimated time of arrival for the active waypoint (white)
- Active waypoint (next waypoint in active route) (magenta)
- Waypoints other than the active waypoint in the active route (white)
- Options selected on the EFIS control panel (cyan)
- Source of the dynamic and background data (green).
For Training Purposes Only
Plan Mode
The plan mode shows NORTH UP. The crew uses the plan mode with the
FMC/CDU LEGS page and the STEP line select key to review the route.
The plan mode display is a static display.
Range information shows as circles around the reference point that is in the
middle of the display.
The airplane symbol shows the current position and track if the airplane is in
the range of the flight plan shown.
Display Data
Ground speed, wind data, and true airspeed show the same as for the APP,
VOR, and MAP modes except that the wind direction arrow does not show.
This data shows in the upper right corner:
S Active waypoint identifier
S Estimated time of arrival at the active waypoint
S Distance to the waypoint.
Only TCAS traffic data messages show in the plan mode. TCAS mode/status
information shows in the lower left corner.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
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GROUND
SPEED
WIND DATA
B737-600/700/800
34-61
GS351 TAS 338
336_/15
CHN
0838.4Z
5.8NM
N
80
ACTIVE
WAYPOINT ETA
ACTIVE
WAYPOINT
DISTANCE
INACTIVE
WAYPOINTS
TAU
40
ACTIVE
WAYPOINT
MAP
OPTIONS
W
RID
E
AIRPLANE
SYMBOL
ARPT
WPT
STA
40
For Training Purposes Only
DINKU
TCAS MODE/STATUS
INFORMATION
TA ONLY
MAP SOURCE
80
FMC L
E
PLAN MODE
Figure 40
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FMC PLAN DISPLAY
FOR TRAINING PURPOSES ONLY
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FMCS DISPLAYS - CDS, NON-NORMAL DISPLAYS
General
These non-normal messages can show:
S UNABLE REQD NAV PERF - RNP
S MAP RANGE DISAGREE.
These non-normal flags can show:
- MAP flag
- Vertical track (VTK).
The UNABLE REQD NAV PERF - RNP message shows when the actual navigation performance (ANP) exceeds the required navigation performance (RNP)
for the current flight environment.
The map data is not blanked in this condition.
The MAP RANGE DISAGREE message shows when a new range has been
selected on the EFIS control panel and new map data is not received from the
FMC.
All map data is blanked in this condition.
For Training Purposes Only
The MAP flag shows if the map data from the FMC is invalid or NCD. All map
data is blanked in this condition.
The VTK (vertical track) flag shows when the vertical deviation data from the
FMC is invalid or NCD.
Only the vertical deviation scale is blanked in this condition.
All these non-normal messages and flags can show in the map and plan
modes.
They are amber.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
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GS 351 TAS 338
336_/15
TRK
140
MARK
IAN
B737-600/700/800
34-61
CHN
0838.4Z
32.5 NM
MAG
GS 351 TAS 338
336_/15
140
MAG
DECEL
DOT
UNABLE REQD NAV PERF-RNP
40
TRK
MAP RANGE DISAGREE
AMY26
T/D
MAP
ARPT
WPT
STA
WRB
2100
KJAN
V
T
K
FRA
For Training Purposes Only
FMC L
FMC L
EXPANDED MAP MODE
EXPANDED MAP MODE
Figure 41
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FMC NON-NORMAL DISPLAYS
FOR TRAINING PURPOSES ONLY
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34-61
FMCS - DATA LOADER
General
You use the airborne data loader (ADL) to load data into the FMCS and other
airplane systems.
The steps to load data into the FMCS and the other systems are similar.
To load data into the FMCS, you set the data loader control panel selector to
the FMC position. This connects the loader to the primary FMC.
You can load the operational flight program (OFP) and these data bases into
the FMCS:
S Navigation
S Model/engine data
S Software options
S Performance.
You then do a crossload and load the data into FMC 2 through the FMCS cross
channel bus.
Return the data loader selector to the NORM position after the transfer is complete.
Prepare
The information below shows the steps to load a navigation data base.
The procedure to load the other systems data or the other FMCS data is similar.
This is a summary of the steps to load data:
S The airplane must be on the ground
S Apply electrical power to the airplane
S Set the FMC source select switch to the FMC you will load (the BOTH ON L
and the NORMAL positions load the left FMC and the BOTH ON R position
loads the right FMC)
S Set the data load selector to the FMC position
S Open the data loader access door
S Put the required diskette into the ADL.
The CDUs automatically go to the FMCS DATA LOADER page when the FMC
receives valid data from the loader.
The data loading process is now automatic.
With the FMCS source select switch in the normal position, the data loads into
FMC 1.
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
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FLIGHT MANAGEMENT COMPUTER
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Figure 42
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS DATA LOADER
FOR TRAINING PURPOSES ONLY
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FMCS - DATABASE LOAD
Load
After you put the diskette into the Loader, the Load process is automatic.
Except to change diskettes, no further operation is required.
The load is complete when LOAD COMPLETE shows on the CDU.
Press the eject button on the Loader to remove the diskette.
For Training Purposes Only
Load Failure Indications
If the loader finds a problem, a message shows on the data loader display.
If the FMC finds a problem with the data from the Loader, the CDU can show
one of these messages:
S CHECK MEDIA (part of the data on the disk cannot be read by the Loader)
S RESET COUNT EXCEEDED (five Load attempts have failed)
S DB EXCEEDS FMC (the data on the disk is too large for FMC memory)
S DB—OFP INCOMPATIBLE (the data on the disk does not compare with the
FMC operational program)
S INCORRECT DISK INSERTED (the diskette does not compare with the diskette you used before)
S CHECK DBL OR INTERFACE (there is a problem that the FMCS cannot
isolate to the FMC or the Loader).
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
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For Training Purposes Only
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Figure 43
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS DATA BASE LOADING
FOR TRAINING PURPOSES ONLY
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34-61
FMCS - CROSSLOAD PAGES
General
These are the two crossload pages that can show on the CDU:
- DATABASE CROSSLOAD
- OP PROGRAM CROSSLOAD.
The OP PROGRAM CROSSLOAD page shows automatically for any of these
conditions:
S You apply power on the ground and the primary FMC, finds the OFPs in the
two FMCS do not match (anytime the OFP in the primary FMC is not valid,
the CDU shows a message to set the source select switch to the BOTH ON
R position)
S You load a new OFP in one FMC
S The OFP does not compare between the primary and secondary FMCs and
you enter FMCS BITE and select the Crossload line select key.
For Training Purposes Only
The DATABASE CROSSLOAD page shows automatically for any of these
conditions:
- You apply power on the ground and a database in the primary FMC and
the secondary FMC do not match
- You load a new database in one FMC
- A database does not match between the primary and secondary FMCs
when you enter FMCS BITE and select the Crossload line select key.
The database pages show only the databases that do not match between
FMCs. The example in the graphic shows the condition where all the databases do not match.
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
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For Training Purposes Only
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Figure 44
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS CROSSLOAD
FOR TRAINING PURPOSES ONLY
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FMCS - DATABASE CROSSLOAD
Operation
The example in the graphic shows the steps to crossload a navigation database from the primary FMC to the secondary FMC.
In this example, FMC 1 is the primary FMC.
After you load a new navigation database and you remove the diskette from
the loader, FMC 1 does a power—up test.
Since the database in FMC 1 and FMC 2 do not compare, the DATABASE
CROSSLOAD page shows automatically.
To start the crossload, select COPY FROM LEFT on the CDU and push the
EXEC key.
The message CROSSLOAD COMPLETE shows at the end of the crossload.
If, in this example, you select COPY FROM RIGHT in error, you will receive
instructions on the CDU to set FMC 2 as the primary FMC.
If you continue, you will load the old database from FMC 2, to FMC 1.
For Training Purposes Only
Crossload Failure
These are the messages that show if the data base did not crossload:
S CROSSLOAD FAIL (the database in the source FMC did not crossload to
the other FMC)
S DB EXCEEDS FMC MEMORY — (the size of the database in the source
FMC is too large for the memory of the other FMC)
S CROSSLOAD UNAVAILABLE (the source FMC cannot interface with the
other FMC).
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
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Figure 45
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS CROSS LOADING
FOR TRAINING PURPOSES ONLY
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34-61
FMCS - BITE PAGES: INTRODUCTION
General
The FMCS has BITE functions for maintenance and test of the system. The
BITE is in the FMC.
You operate the BITE with the CDUs.
The BITE functions continuously monitor the status of the FMC and CDU.
The functions also continuously monitor the status of airplane sensor systems
which interface with the FMCS.
The monitors operate at all times. This includes power—up.
These are the BITE functions:
S INFLT FAULTS
S CDU TEST
S SENSORS
S DISCRETES
S FMCS — FIXED OUTPUTS
S IRS MONITOR
S PERF FACTR
S SW OPTIONS
S MODEL/ENG.
INFLT FAULTS
The FMCs record their in—flight faults and in—flight faults for the CDUs and
the LRUs they interface with.
They have storage capacity for nine flights.
In addition, the FMCs record their ground faults and ground faults for the
CDUs.
Aug 99
REFRESHER COURSE
FRA US/E NM
CDU TEST
These are tests of the CDU display and keyboard.
SENSORS/DISCRETES
The status of the interface LRUs and analog discrete signals show on this
page.
FMCS — FIXED OUTPUTS
Shows the values of outputs that are sent to the components selected on the
CDU display.
IRS MONITOR
This page shows the ADIRU position error rate calculated by the FMC.
PERF FACTR
This page shows performance codes and performance factors.
SW OPTIONS
The status of the software option database show here.
MODEL/ENG
This page shows the status of the airplane model/engine configuration program
pins.
FOR TRAINING PURPOSES ONLY
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Figure 46
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS BITE INTRODUCTION
FOR TRAINING PURPOSES ONLY
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FMCS - BITE PAGES: BITE ENTRY
General
You use the INIT/REF INDEX page, line select key (LSK) 6R to show the
MAINT BITE INDEX PAGE.
Select LSK 1L on the MAINT BITE INDEX PAGE to enter FMCS BITE.
On the FMCS BITE page, you select FMC L (FMC 1) or FMC R (FMC 2) as
the BITE source.
It is possible to select FMC 1 as the BITE source on the left CDU and FMC 2
as the BITE source on the right CDU. In this configuration you can show and
compare sensor status for both FMCs.
Primary/Secondary FMC Select
Data from the BITE source comes through the primary FMC.
The arrow direction on the CDUs show which FMC is primary.
The example on the graphic shows a left arrow (FMC 1 is the primary FMC).
A right arrow shows FMC 2 is the primary FMC. You use the FMCS transfer
switch to select the primary FMC.
In the NORMAL or BOTH—ON—LEFT position, FMC 1 is the primary FMC.
In the BOTH-ON—RIGHT position, FMC 2 is the primary FMC.
For Training Purposes Only
FMC Download
You can use your data loader to copy the file system from a FMC to a diskette.
You start the procedure with line select key 6R (FMC DOWNLOAD).
See the AMM, FMCS troubleshooting section 34—61, for more information
about the data transfer.
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
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Figure 47
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS BITE ENTRY
FOR TRAINING PURPOSES ONLY
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FMCS - BITE PAGES: AUTOMATIC BITE ENTRY
General
At start—up on the ground, the primary and secondary FMC compare this information:
S Operational Flight Programs (OP)
S Data bases
S Analog discretes/program pins
S Performance factor.
If the information does not agree, the correct BITE page shows automatically.
For in flight restarts, the two FMCs also compare their information.
If the information does not agree, the secondary FMC stops operation and the
message SINGLE FMC OPERATION shows on the CDUs.
For Training Purposes Only
Ground Start—up
If the two OPs do not agree, the primary FMC shows the OP PROGRAM
CROSSLOAD page.
You use this page to crossload the correct OP.
If a database does not agree between the two FMCs, a crossload page for that
database shows on the CDU.
If an analog discrete/program pin or a performance factor does not agree between the two FMCs, the analog discrete or the performance factor page
shows.
A highlight shows around the item that does not agree.
If you exit BITE before you take corrective action, the secondary FMC stops
operation and the message SINGLE FMC OPERATION shows on the CDUs.
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
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Figure 48
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS BITE ENTRY AUTOMATIC
FOR TRAINING PURPOSES ONLY
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34-61
FMCS - BITE PAGES: INFLIGHT FAULTS
General
To look at in—flight faults, select INFLT FAULT on line select key (LSK) 1L,
from the FMCS BITE page.
The FMC stores in—flight faults for 9 flight legs and faults that occur on the
ground.
The FMC can store up to 20 faults for each flight leg.
A new flight leg starts when the airplane goes above 20 knots ground speed
and goes in the air.
The new leg stops when the airplane is on the ground and ground speed goes
below 20 knots.
Faults that occur on the ground are stored as ground faults.
IN FLT FAULTS Page
This page shows this information:
S Name of the possible LRU
S Fault occurred, in flight or on the ground
S Flight leg the fault occurred
S Fault was recorded by one or both FMCs
S Access code for engineering data you set in the scratch pad.
All of the LRUs that interface with the FMCS show on the IN FLT FAULTS
pages.
The LRUs with a possible failure show a letter L (FMC 1), R (FMC 2) or B
(FMC 1 and FMC 2) to show the FMC or FMCs that record the fault.
If the FMCs did not record a fault for that LRU, no letter shows to the right of
the LRU name.
The alpha numeric characters at the top of the page show the flight legs.
The letter G shows the FMCS recorded the fault on the ground after the last
flight leg.
The number 1 is the last flight leg. The number 9 is 9 flights ago.
To see more details about the possible LRU failures, you can set the access
code 300 into the scratch pad and push LSK 6R.
The flight select page now shows.
Aug 99
REFRESHER COURSE
FRA US/E NM
FLIGHT SELECT Page
This page shows a menu of the flight legs. Flight G shows faults that occur on
the ground.
FLIGHT Page
Flight leg faults and ground faults show on these pages.
This information shows for each fault:
S Possible LRU
S Fault description
S Fault is steady (S) or intermittent (I)
S Time the fault occurred.
The ground faults clear from storage after the airplane goes above 20 knots
ground speed and goes in the air.
FOR TRAINING PURPOSES ONLY
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Figure 49
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS INFLIGHT FAULTS
FOR TRAINING PURPOSES ONLY
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FMCS - BITE PAGES: CDU TEST
General
To test the CDUs, select CDU TEST on line select key (LSK) 2L, from the
FMCS BITE page.
The CDU TEST is an interactive self test that shows the CDU characters. It
also tests the CDU push buttons and annunciators.
FMCS CDU TEST Page
On this page you can select the CDU DSPLY TEST (LSK 5R) or the CDU KEY
TEST (LSK 5L).
FMCS—DSPLY—TEST Page
This test shows the complete CDU character set. Push LSK 6L to go back to
the FMCS CDU TEST page.
For Training Purposes Only
FMCS KEY TEST
This test displays the CDU faceplate keys on the CDU screens.
As you push each key on a keyboard, the CDUs highlight the key on the
screen while the scratchpad shows the name of the key you pushed.
When you push LSK 6L the second time, the CDU goes back to the FMCS
CDU TEST page.
When you push the INIT/REF key the second time, the CDU goes back to the
INIT/REF page.
Aug 99
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Figure 50
Aug 99
REFRESHER COURSE
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FMS BITE PAGES CDU TEST
FOR TRAINING PURPOSES ONLY
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34-61
FMCS - BITE PAGES: SENSORS
General
To check FMCS sensor status, select SENS0RS on line select key (LSK) 3L,
from the FMCS BITE page.
Sensor Status Pages
The sensor status pages show the current status of the sensors that send data
to the FMC selected as the BITE source.
If the two FMCs do not agree on the status of an LRU, a highlight shows
around the status field for that lRU.
In the example shown on the graphic, FMC L and FMC R do not agree on the
status of the right VOR.
Dashed lines in the status field show the LRU does not exist or the FMC selected as the BITE source does not interface with the LRU.
In the example shown on the graphic, the DFCS FCC A is the master FCC and
it is the FCC that reports DFCS status to FMC 1 and FMC 2.
For Training Purposes Only
Sensor Data Pages
This page shows engineering data for sensors which have a FAIL status on a
SENSOR STATUS page. The faults show in chronological order.
To clear the screen, push LSK 6R. After you push the key, only engineering
data for faults that occur from the time you push the key will show.
The clear key only clears the engineering data for the FMC selected as the
BITE source. It does not clear the data for both FMCs.
Aug 99
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Figure 51
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS BITE PAGES, SENSORS
FOR TRAINING PURPOSES ONLY
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FMCS - BITE PAGES: DISCRETES
General
To check FMCS discretes status, select DISCRETES on line select key (LSK)
4L, from the FMCS BITE page.
Discretes Pages
These pages shows the current status of the analog discretes that send data to
the FMC selected as the BITE source.
If the two FMCs do not agree on the status of a discrete, a highlight shows
around the status field for that discrete. In the example shown on the graphic,
FMC 1 does not see the right ECS PACK on.
MAKE SURE THAT PERSONS AND EQUIPMENT ARE
CLEAR OF THE SLATS BEFORE YOU REMOVE ELECTRICAL POWER FROM THE AIR/GROUND RELAYS.
THE SLATS CAN MOVE AUTOMATICALLY WHEN FLAPS
ARE IN POSITION 1, 2, OR 5, AND THE NOSE OR MAIN
LANDING GEAR AIR/GROUND RELAYS INDICATE AN AIRBORNE CONDITION.
THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
For Training Purposes Only
WARNING:
Aug 99
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Figure 52
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS BITE PAGES, DISCRETES
FOR TRAINING PURPOSES ONLY
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FMCS - BITE PAGES: FMCS FIXED OUTPUTS
General
To check FMCS fixed output status, select FMCS—FIXED OUTS on line select
key (LSK) 5L, from the FMCS BITE page.
The navigation control panels must be set to the MAP mode.
FMCS FIXED OUTPUTS Page 1/2
This page shows FMCS data that goes to the thrust mode annunciation (TMA)
on the engine display.
The thrust modes show in sequence on the TMA. The word ON shows on the
CDUs as each mode comes into view on the FMA.
For Training Purposes Only
FMCS FIXED OUTPUTS Page 2/2
When you select this page, these annunciators on the CDUs come on until you
exit the page:
S MSG
S FAIL
S CALL
S OFST.
Aug 99
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Figure 53
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS BITE PAGES, FIXED OUTPUTS
FOR TRAINING PURPOSES ONLY
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FMCS - BITE PAGES: IRS MONITOR
General
To check the IRS position error rate, select IRS MONITOR on line select key
(LSK) 5R, from the FMCS BITE page.
IRS MONITOR Page
The position error rate (nautical miles per hour) for each IRS shows on this
page.
The FMCS calculates the position error rate for each flight.
It divides the difference between the FMCS position and IRS position by the
total flight time.
The FMCS calculates the error rate at the end of each flight.
The error rate does not show in—flight.
The error rate does not show for an IRS that is not aligned in the NAV
mode or is in the attitude mode.
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The error rate does not show for an
IRS that is not aligned in the NAV
mode or is in the attitude mode.
Figure 54
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS BITE PAGES, IRS MONITOR
FOR TRAINING PURPOSES ONLY
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FMCS - BITE PAGES: PERFORMANCE FACTORS
General
To check FMCS performance factors, select PERF FACTR on line select key
(LSK) 4R, from the FMCS BITE page.
PERFormance FACTORS Page
The aerodynamic and engine models in the performance data base are from
airplane design and flight test data.
Since each production airplane may be different, the FMCS PERF FACTORS
page lets the operator make adjustments for these factors.
Some factors cannot be set on this page. They are set with the performance
database.
To set a new factor, put the word ARM in the scratch pad and LSK 6R. Put the
new factor in the scratch pad and Line select the applicable key.
If the two FMCs do not agree on the value for a performance factor, the factor
is highlighted.
In the example shown on the graphic, FMC 2 does not agree with the value for
the engine out minimum rate of climb.
These are the performance factors:
S DRAG FACTOR (range is +/- 9.9 percent)
S F — F (fuel flow factor) (range is +/- 9.9 percent)
S MNVR MARGIN (maneuver margin) (range is set in the performance data
base)
S MIN CRZ TIME (minimum cruise time) (range is 1 to 20 minutes)
S MIN R/C (minimum rate—of—climb for climb, cruise and engine out conditions) (range is 0—999 for climb and cruise and 0—500 for engine out).
Aug 99
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Figure 55
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS BITE PAGES, PERFORMANCE FACTORS
FOR TRAINING PURPOSES ONLY
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FMCS - BITE PAGES: SOFTWARE OPTIONS
General
To show the FMCS software options, select SW OPTIONS on Line select key
(LSK) 3R, from the FMCS BITE page.
Software OPTION Pages
The software option pages show the status of the options that are in the software options database.
The graphics show pages with example options.
The navigation data base (NDB) size is 1 meg words.
These are the software options your airline selected (if no software options
show here, your airline did not select any options):
To find your option code add each column in the software code (start with the
left column).
For example, if you have these options:
S High idle descent—(00000001)
S GPS with integrity—(00000000)
S GPSSU installation—(00000100)
S Manual RNP entry—(00000200).
Your code is 000003C1. If your airline did not select any software options, your
code is 00000000.
The software option code is a 12 digit hex code. The first four zeros are not
shown here.
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Figure 56
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS BITE PAGES, SOFTWARE OPTIONS
FOR TRAINING PURPOSES ONLY
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FMCS - BITE PAGES: AIRPL. MODEL, ENGINE CONFIG.
General
The model/engine configuration page shows the airplane and engine configuration.
To access this page, select MODEL/ENG (line select key 1R), from the FMCS
BITE page.
For Training Purposes Only
FMC MODEL/ENG Pages
A normal display shows when the program pin connections match the data in
the performance database.
If there is a non normal condition, one of these messages show on the CDUs:
S PARITY ERROR
S INVALID
S PROGRAM PIN NOT IN MODEL/ENGINE DATA BASE.
The message PARITY ERROR shows if the program pins are not set to odd
parity.
INVALID shows if a performance database is not installed and there is not a
parity error.
PROGRAM PIN NOT IN MODEL/ENGINE DATA BASE shows if the program
pins do not match the data in the performance database and there is not a parity error.
Aug 99
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Figure 57
Aug 99
REFRESHER COURSE
FRA US/E NM
FMS BITE PAGES, AC-CONFIG.
FOR TRAINING PURPOSES ONLY
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FMCS - LCD BITE PAGES: INTRODUCTION
GENERAL
To see the CDU MAINT BITE INDEX page, use the LCD CDU prompt (LSK
5R) on the FMCS BITE INDEX page.
The CDU MAINT BITE INDEX page has these CDU maintenance categories:
S FAULTS
S KEY TEST
S COLOR TEST
S DISPLAY TEST
S CONFIG
S SOFTWARE OPTIONS
S POWER SUPPLY (P/S)
S TEMPERATURE
S LIGHT
S LAMP TEST
S CALIBRATION.
For Training Purposes Only
NOTE:
Power supply, temperature, light, lamp test, and calibration are used primarily
for bench test of the CDU.
The EXIT prompt (LSK 6L) selects the FMCS BITE INDEX page.
Nov. 2001
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LT
< I NF L T
< CDU
F MC S
B737-600/700/800
34-61
BI TE
MO D E L / E N G >
F AUL T
T E S T
S W
OP TI ONS >
< S E NS OR S
P E RF
< DI S CRE TE S
I RS
< F I XE D
1 / 1
OUT P UT S
F ACT R>
MO N I T R >
L CD
CDU>
< I NDE X
C DU
MA I N T
BI TE
S W
< F AUL T S
< KE Y
For Training Purposes Only
< C ONF I G
Nov. 2001
REFRESHER COURSE
FRA US/E NM
P / S >
T E MP >
T E S T
< DI S P L AY
Figure 58
OPT I ONS >
T E S T
< C OLO R
< E XI T
I NDEX
L I GHT >
T E S T
L AMP
T E S T >
C AL I B RAT I ON>
FMCS BITE PAGES - LCD CDU
FOR TRAINING PURPOSES ONLY
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FMCS - LCDU BITE PAGES: FAULTS
General
To see the CDU faults page, first select FAULTS on line select key (LSK) 1L
from the CDU MAINT BITE INDEX page.
This selects the CDU BITE DISPLY INDEX page.
For Training Purposes Only
CDU BITE DISPLAY INDEX Page
This page shows the fault history for the last ten full power-up cycles.
When no faults are recorded during a cycle, the data field is blank.
To see the fault data for a specific cycle, select that line select key.
This selects the CDU BITE DISPLAY page for that power up cycle.
Line select key 6L shows the INDEX prompt.
This selects the CDU MAINT BITE INDEX page.
CDU BITE DISPLAY Page
This page shows the fault data for a specific cycle.
Up to a maximum of five faults are recorded per cycle. The header shows the
cycle number.
This data shows for each fault:
S Failed unit
S Failure description
S Fault state
S Failure frequency
S Failure time
S Extended fault code.
The failed unit can show FMC, CDU, or USER 1-5 where USER is an airplane
sub-system.
These are the failure descriptions that can show:
S PROCESSOR
S WATCHDOG TIMER
S 429 FAULT
S ANNUN FAULT
S LCD
S KEYBOARD
S MEMORY
S R/C TIMER (resistor/capacitor)
S POWER SUPPLY
S LIGHT SENSOR
S ADC (analog to digital converter)
S TEMP SENSOR
S FMC FAULT
S SUB-SYSTEM FAULT
S EDC (error detection and correction logic)
S SOFTWARE FAULT
S FONTROM (read only memory).
The fault state shows if the fault is steady (S) or intermittent (I).
All faults are initially recorded as a steady fault.
If the fault later goes away, the indication changes to intermittent.
The failure frequency shows the number of times the fault occurs.
The failure time shows the CDU elapsed time indication when the fault first occurred.
The extended fault code is used by shop personnel only.
Line select key 6L shows the INDEX prompt. This selects the CDU MAINT
BITE INDEX page.
Nov. 2001
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C DU
MA I N T
34-61
BI T E
SW
< F A UL T S
< KEY
B737-600/700/800
I NDE X
< EXI T
I NDE X
0 1
CY CL E
0 6 >
P/ S>
< CYCL E
0 2
CY CL E
0 7 >
T E MP >
< CYCL E
0 3
CY CL E
0 8 >
L I GH T >
< CYCL E
0 4
CY CL E
0 9 >
CY CL E
1 0 >
TEST
< CONF I G
DS PL Y
< CYCL E
TEST
< DI SP L A Y
BI T
OP T I ON S >
T EST
< COL O R
CDU
L A MP
TEST>
< I NDEX
CA L I BRA T I ON>
EXTENDED
FAULT CODE
CDU
FAILED UNIT
BI T
CY CL E
For Training Purposes Only
FAILURE DESCRIPTION
CDU
L I GH T
0 9
S E NS OR
DI S P L A Y
F AUL T S
S 1
5 7
0 2 1 6 . 0
FAULT STATE
FAILURE FREQUENCY
FAILURE TIME
< I N D EX
Figure 59
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FMCS BITE PAGES - LCD CDU FAULTS
FOR TRAINING PURPOSES ONLY
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FMCS - LCDU BITE PAGES: KEY TEST
General
To see the CDU KEY TEST page, select KEY TEST on LSK 2L from the CDU
MAINT BITE INDEX page.
Key Test Page
This page shows the test displays for the MCDU faceplate keys on the MCDU
screens.
As you push each key on the keyboard, the corresponding character set will be
highlighted (shaded white) on the CDU screen.
Push the same key again to return the character set to normal.
For Training Purposes Only
Line select key 6L shows the INDEX prompt. This selects the CDU MAINT
BITE INDEX page.
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CD U
MA I N T
B737-600/700/800
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BI T E
SW
< FAU L T S
< KE Y
I NDE X
OP T I ON S >
TEST
< CO L O R
TEST
< DI S P L A Y
< CO N F I G
< EX I T
P/ S>
T E MP >
L I GH T >
T EST
L A MP
TEST >
CA L I B RA T I ON>
C DU
For Training Purposes Only
1
2
3
4
5
6
Figure 60
Nov. 2001
REFRESHER COURSE
FRA US/E NM
I NI
R
ME N
L
N1
F
PRV
N
L
L 1 2 3
L 4 5 6
L 7 8 9
L . 0 +
L
- - - PUS
< I NDE X
TE
EG
I X
EX
H
KE Y
T ES T
CL B
DEP
C RZ
H OL
A B CD
F GHI
K L MN
P QRS
U V WX
Z D/
1 / 1
DES
P RO
E
J
O
T
Y
C
EXE
1
2
3
4
5
6
KEYS T O TEST- - - ( P U S H T WI C E )
R
R
R
R
R
R
FMCS BITE PAGES - LCD CDU KEY TEST
FOR TRAINING PURPOSES ONLY
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FMCS - LCDU BITE PAGES: COLOR TEST
General
To see the CDU color test page, select COLOR TEST on LSK 3L from the
CDU MAINT BITE INDEX page.
Color Test Page
Line 1L shows the RED prompt. This selects a full screen display of the color
red.
Line 2L shows the GREEN prompt. This selects a full screen display of the
color green.
Line 3L shows the BLUE prompt. This selects a full screen display of the color
blue.
Line 4L shows the AMBER prompt. This selects a full screen display of the
color amber.
Line 5L shows the MAGENTA prompt. This selects a full screen display of the
color magenta.
Line 6L shows the INDEX prompt. This selects the CDU MAINT BITE INDEX
page.
Line 1R shows the CYAN prompt. This selects a full screen display of the color
cyan.
Line 2R shows the WHITE prompt. This selects a full screen display of the
color white.
Line 3R shows the GRAY SCALE prompt. This selects a display of the eight
brightness levels for the gray scale.
Line 4R shows the CHECKERBOARD prompt. This selects a full screen display of a black and white checkerboard pattern.
Push the LSK a second time to return the MCDU screen to normal.
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CD U
MAI N T
B737-600/700/800
34-61
BI TE
SW
< FAUL TS
< KEY
I NDE X
OPT I ONS >
P/ S>
TE ST
< C OL O R
TEST
< DI S P L A Y
< C ON F I G
< EXI T
T E MP >
L I GHT >
T E ST
L A MP
T EST >
CA L I B RA T I ON>
CDU
C O L OR
T EST
< RED
CYAN>
For Training Purposes Only
< GRE E N
< BL UE
< A MB E R
1 / 1
WH I T E >
GRA Y
SCAL E>
CH E CK E R B OA RD >
< MA G E N T A
< I NDE X
Figure 61
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FMCS BITE PAGES - LCD CDU COLOR TEST
FOR TRAINING PURPOSES ONLY
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FMCS - LCDU BITE PAGES: DISPLAY TEST
General
To see the CDU display test page, select the DISPLAY TEST prompt on LSK
4L from the MAINT BITE INDEX page.
Display Test Page
This page shows the complete MCDU character set.
Selection of the PREV PAGE or NEXT PAGE pushbuttons steps the display
through the next seven pages.
Each page shows one of the seven colors.
For Training Purposes Only
Line 6L shows the INDEX prompt. This selects the CDU MAINT BITE INDEX
page.
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B I T E I NDE X
S W OP T I ON S >
< FAUL TS
< KEY
< C OL O R
TEST
< DI S P L A Y
< C ON F I G
< EXI T
P/ S>
TEST
T E MP >
L I GH T >
TE ST
L A MP
TEST>
C A L I B RA T I ON>
- - - - CD U - D S P L Y - T E S T - - 1 / X
>
>
For Training Purposes Only
#&
0123456 789 ! ” F %
\
’ ( ) * +, - . / 0 1 2 3 4 5 6 7 8 9 : ; <= >
? A B C D E F G H I J K L MN O P Q R S T U V
A B C D E F G H I J K L MN O P
WX Y Z [
]
Q R S T U V WX Y Z # &
! F
” \
]
% C’ ( ) * + , - . / : ; < = > ? [
< I ND E X - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -
FMCS - TRAINING INFORMATION POINT - CDU BITE PAGES - DISPLAY TEST
Figure 62
Nov. 2001
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FMCS BITE PAGES - LCD CDU DISPLAY TEST
FOR TRAINING PURPOSES ONLY
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FMCS - LCDU BITE PAGES: CONFIG
General
To see the CDU CONFIGURATION page, select CONFIG on LSK 5L from the
CDU MAINT BITE INDEX page.
Configuration Page
The CDU CONFIGURATION page shows this information:
S Software part number
S Operating mode (CDU, MCDU, or FANS MCDU)
S Location (left or right)
S Elapsed time indicator
S CDU serial number.
For Training Purposes Only
Line 6L shows the INDEX prompt. This selects the CDU MAINT BITE INDEX
page.
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MA I N T
C DU
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BI T E
SW
< F A UL T S
< KEY
OP T I ON S >
P/ S>
T EST
< C OL O R
TEST
< DI SP L A Y
< C ONF I G
< EXI T
I NDE X
T E MP >
L I GH T >
TEST
L A MP
TEST>
CA L I BRA T I ON>
CD U
For Training Purposes Only
S OF T
3 46 3 CDU
MC D U
CDU
RI GHT
ETI
1 2 9
SERI
0 91 7
C ON F I G U R A T I O N
WA R E P / N
S MI - 0 0 1 - 0 2
MODE
L OCA T I ON
HRS
. 6
A L NO
< I NDE X
Figure 63
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FMCS BITE PAGES - LCD CDU CONFIG
FOR TRAINING PURPOSES ONLY
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FMCS - LCDU BITE PAGES: SW OPTIONS
General
To see the software options page, select SW OPTIONS on LSK 1R from the
CDU MAINT BITE INDEX page.
Software Options Page
The software option page shows the status of the options that are in the CDU
software options database.
The software option code is an eight-digit hexadecimal number.
These option codes are available:
S No option code - 00000000
S Switching mode - 00000001
S ARINC 739 color usage - 00000002
S Switching mode & ARINC 739 color usage - 00000003.
The enabled options show at line 3L.
If there are no option codes enabled, NONE shows.
For Training Purposes Only
Line 6L shows the INDEX prompt.
This selects the CDU MAINT BITE INDEX page.
Line 6R allows the entry of the word ARM.
This is a necessary entry to enable software option entry on this page.
After you enter ARM and push LSK 6R, you may enter the new software option
into the scratch pad and line select it to the option code (LSK 1R).
NOTE:
When you enter an option code, all eight digits must be entered.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
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FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMS)
B737-600/700/800
34-61
CDU SW OPT I ONS
1/ 1
OP T I ON CODE
00 0 00 00 0
CDU MAI NT BI TE I NDEX
SW OPT I ONS >
< FAUL TS
< KEY TE ST
ENA B L E D OP T I ONS
P/ S >
< COL OR T EST
NONE
T EMP >
< DI S P L A Y T E ST
L I GHT >
L A MP T EST >
< CONF I G
< EXI T
< I NDEX
CAL I BRAT I ON>
-- -
OR
CDU SW OPT I ONS
CDU SW OPT I ONS
CDU SW OPT I ONS
E NA B L ED OP T I ONS
E NA B L ED OP T I ONS
E NA B L E D OPT I ONS
For Training Purposes Only
S WI T CHI NG MODE
< I NDE X
- --
Figure 64
Nov. 2001
REFRESHER COURSE
FRA US/E NM
1/ 1
OPT I ON CODE
0 000 0 0 03
1/ 1
OP T I ON CODE
0 0 00 00 0 2
1/ 1
OP T I ON CODE
00000001
A RI NC 7 3 9 CO L OR U S AGE
S WI T CHI NG MOD E
A RI NC 7 3 9 COL OR US AGE
< I NDE X
< I N DE X
- - -
- --
FMCS BITE PAGES - LCD CDU SW OPTIONS
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 137
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMS)
B737-600/700/800
34-61
FMCS - LCDU BITE PAGES: POWER SUPPLY
General
To see the CDU power supply page, select P/S on LSK 2R from the CDU
MAINT BITE INDEX page.
Power Supply Page
This page shows the voltage levels from the MCDU power supply.
These voltages come the power supply:
S +5v dc
S +12v dc
S -12v dc
S +26v dc
S +28v dc
S Switched +28v dc
S Annunciator +5v dc.
NOTE:
The switched 28v dc power supply is only active when the CDU heater is on
and the voltage will be displayed.
If the heater is off, the data field will be blank.
For Training Purposes Only
Line 6L shows the INDEX prompt. This selects the CDU MAINT BITE INDEX
page.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 138
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMS)
CD U
MA I N T
34-61
BI T E
I NDE X
SW
OP T I ON S >
< FAUL TS
< KEY
B737-600/700/800
P/ S>
TEST
< C OL O R
TEST
< DI S P L A Y
T E MP >
L I GHT >
T E ST
< C ON F I G
< EXI T
L A MP
T EST >
CA L I B RA T I ON>
P/ S
S E N S O RS
S E N S OR
For Training Purposes Only
+
+
+
+
S
A
5
1 2
1 2
2 6
2 8
W_ 2 8
NNUN
VA L UE
XX
XX
XX
XX
XX
XX
XX
.
.
.
.
.
.
.
X
X
X
X
X
X
X
X
X
X
X
X
X
X
V
V
V
V
V
V
V
< I NDEX
Figure 65
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FMCS BITE PAGES - LCD CDU PWR SUPPLY
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 139
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMS)
B737-600/700/800
34-61
FMCS - LCDU BITE PAGES: TEMP SENSORS
General
To see the CDU TEMP SENSORS page, select TEMP on LSK 3R from the
CDU MAINT BITE INDEX page.
Temperature Sensors Page
This page shows the temperature values from the sensors in the LCD module
and the backlight assembly.
It also shows the operational status of the thermal electric coolers (TEC) and
the heater.
For Training Purposes Only
Line 6L shows the INDEX prompt. This selects the CDU MAINT BITE INDEX
page.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 140
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NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMS)
CDU
MA I N T
BI T E
SW
< F AUL T S
< KEY
B737-600/700/800
34-61
I NDEX
OP T I ON S >
P/ S>
TEST
< COL O R
T EST
< DI S P L A Y
T E MP >
L I GH T >
T E ST
< CON F I G
< EXI T
L A MP
T EST >
CA L I B RA T I ON>
For Training Purposes Only
T E MP
S EN S OR S
S E NS OR
L C D _ T E MP _ R
L C D _ T E MP _ C
VAL UE
O
| XX . XX C
O
| XX . XX C
BK
BK
O
| XX . XX C
O
| XX . XX C
L I GHT
L I GHT
R
H
T E C MO D E
T E C C MD
HEAT ER
< I NDE X
Figure 66
Nov. 2001
REFRESHER COURSE
FRA US/E NM
COOL
XXX
OF F
FMCS BITE PAGES - LCD CDU TEMP SENSORS
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 141
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMS)
B737-600/700/800
34-61
FMCS - LCDU BITE PAGES: LIGHT SENSORS
General
To see the CDU LIGHT SENSORS page, select LIGHT on LSK 4R from the
CDU MAINT BITE INDEX page.
Light Sensors Page
This page shows the voltage levels from the MCDU light sensors.
For Training Purposes Only
Line 6L shows the INDEX prompt.
This selects the CDU MAINT BITE INDEX page.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 142
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMS)
CD U
MA I N T
34-61
BI T E
INDEX
SW
OP T I ON S >
< F AUL T S
< KEY
B737-600/700/800
T EST
< C OL O R
P/ S>
T EST
< DI S P L AY
T E MP >
L I GHT >
T E ST
< C ON F I G
< EXI T
L A MP
T EST >
CA L I BRA T I ON>
L I GHT
S E N S OR S
S E NS OR
V AL UE
XXXX . XF C
XXX . X%
For Training Purposes Only
A MB I E N T L T
D I MME R P OT
D
S
A
A
E
P
R
R
S L UM
OT BRT
C HI GH
C L OW
X
X
X
X
X
X
X
X
.
X
X
X
X
X
X
X
(
(
(
(
F
F
H
H
T
T
E
E
X
X
L )
L )
)
)
< INDE X
Figure 67
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FMCS BITE PAGES - LCD CDU LIGHT SENSORS
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 143
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMS)
B737-600/700/800
34-61
FMCS - LCDU BITE PAGES: LAMP TEST
General
To see the CDU lamp test page, select LAMP TEST on LSK 5R from the CDU
MAINT BITE INDEX page.
Lamp Test Page
This page does a test of the MCDU annunciators.
The message ANNUNCIATORS ALL LT shows on the CDU and these annunciators come on:
S CALL
S FAIL
S MSG
S OFST
S EXEC.
For Training Purposes Only
Line 6L shows the INDEX prompt. This selects the CDU MAINT BITE INDEX
page and the annunciators go out.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
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Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMS)
MA I N T
CDU
BI T E
SW
< F AUL T S
< KEY
B737-600/700/800
34-61
I N DE X
OP T I ON S >
T EST
< COL O R
P/ S>
T ES T
< DI SP L AY
T E MP >
L I GHT >
T E ST
< CONF I G
< EXI T
L A MP
T E S T >
CAL I BRA T I ON>
For Training Purposes Only
CDU
L A MP T ES T
A NN U NC I A T O RS
AL L
L I T
< I N DE X
Figure 68
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FMCS BITE PAGES - LCD CDU LAMP TEST
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 145
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMS)
B737-600/700/800
34-61
FMCS - LCDU BITE PAGES: CALIBRATION
General
To see the CDU calibration page, select CALIBRATION on line select key
(LSK) 6R from the CDU MAINT BITE INDEX page.
Calibration Page
This page shows the current deflection voltages and calibration factors for the
LCD module.
It also shows the light sensor bias level and the scale factor used.
The scratchpad shows the source of the currently used data.
If the software uses calibrated data, then CALIBRATED will be shown.
If it uses hardcoded defaults, then DEFAULTS will be shown.
For Training Purposes Only
Line select key 6L shows the INDEX prompt. This selects the CDU MAINT
BITE INDEX page.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 146
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NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMS)
C DU
MA I N T
BI T E
SW
< F A UL T S
< KEY
B737-600/700/800
34-61
I NDEX
OP T I ON S >
T E ST
< COL O R
P/ S>
T ES T
< DI SP L A Y
T E MP >
L I GH T >
T E ST
< C ONF I G
< EXI T
L A MP
T ES T >
CAL I BRA T I ON>
For Training Purposes Only
CDU
C A L I B RAT I O N
GS
DE F L
T RI M
OO
1 6
3 2
4 8
6 3
VC
V E
X.
X.
X.
X.
X.
X.
X.
X.
X.
X.
X.
X.
X.
X.
X
X
X
X
X
X
X
V
V
V
V
V
V
V
X
X
X
X
X
X
X
V
V
V
V
V
V
V
L T SE NS B I A S
X X X X MV
SCA L E
FA CT OR X . X X X
< I NDE X
C A L I B R A T ED
Figure 69
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FMCS BITE PAGES - LCD CDU CALIBRATION
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 147
B737-600/700/800
34-61
THE FOLLOWING PAGE IS FOR REFERENCE ONLY!
For Training Purposes Only
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMS)
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 148
Lufthansa Technical Training
NAVIGATION
FLIGHT MANAGEMENT COMPUTER
SYSTEM (FMS)
B737-600/700/800
34-61
115V AC
BUS 1
BUS 2
BUS 4
BUS 5
BUS 6
BUS 7
BUS 8
115V AC
VOR 2
DME 1
VOR/MB
ILS 2
DME
1
2
4
5
6
7
8
BUS 1
28V DC
UPLINK
XFER RLY
DISCRETE
CLOCK 1
C
BUS 7
BUS 8
B
DEU 2
FCC A
GPWC
DEU 1
FDAU
A
ADR 4
CLOCK
BUS 4
BUS 6
BUS 2
BUS 5
BUS 6
GPS 1/2
MMR
A/T COMP
BUS 2
XFR RLY 1
SMYD 1
FMC 1/2
IR 3
ADIRU
HGS (OPTION)
FAIL WARN
DME 1
115V AC
DEU-FMC
CDU 1
FAIL WARN
A/T COMP
ELT (OPTION)
115V AC
A/T 1
DEU
CAP NAV C/P
B
MCP 3
FQPU
CDU 1
DFCS MCP
ACARS MU
FQPU 5
FQPU
DIU (OPTION)
BUS 1
CDU 2
DLDR 1
XFER RLY
DISCRETE
LOAD ENABLE
C
DATA LOADER
CONTROL PANEL
For Training Purposes Only
ENG 2 BLEED
AIR SWITCH
ENGINE 2
ANTICE SW
RIGHT PACK
VALVE
RIGHT PACK
A/C RELAY
FCC B
FDAU
BUS 2
1
BUS 1
2
BUS 2
ENG 1 BLEED
AIR SWITCH
ON/OFF
ENGINE 1
ANTICE SW
ON/OFF
LEFT PACK
VALVE
OPEN/CLOSE
LEFT PACK
A/C RELAY
WING ANTICE
A/C ISOL
VALVE
ON/OFF
SMYD 2
28V DC
ON/OFF
DME 2
OPEN/CLOSE
OFF/HIGH/
CDU 1 OR
AUTO
PORTABLE
OFF/HIGH/
AUTO
BUS 9
ON/OFF FMC MESSAGE
FMC FAIL
OPEN/CLOSE
PROG SW MOD
PROG SW MOD
FMC 2
FMC 1
Figure 70
Nov. 2001
REFRESHER COURSE
FRA US/E NM
XFR RLY 2
F/O NAV C/P
DEU 2
FMC MESSAGE
FMC FAIL
FMC FAIL
FMC MESSAGE
RESET
A
PORTABLE CDU
DEU 1
FMC CONFIG
OPTIONS
IFSAU
INTERSYSTEM
BUS
28V DC
OPTIONS
BITE PRINTER
RECEPTACLE
FMC WARN RESET
CAPT ASA
28V DC
FMC WARN RESET
F/O ASA
FMCS - SYSTEM SUMMARY
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 149
Lufthansa Technical Training
For Training Purposes Only
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
22-23
YAW DAMPER SYSTEM
ABBREVIATIONS AND ACRONYMS
AC
ADR
ADIRU
AOA
ARINC
BITE
CAA
CDS
CPU
DC
DEU
DFCS
EHSV
FAA
FMC
IR
I/O
LRU
LVDT
MCP
N1
NN
PCU
SMYD
V
WTRIS
YDS
— alternating current
— air data reference
— air data inertial reference unit
— angle of attack
— Aeronautical Radio Incorporated
— built in test equipment
— Civil Aviation Authority
— common display system
— central processing unit
— direct current
— display electronic unit
— digital flight control system
— electrohydraulic servo valve
— Federal Aviation Administration
— flight management computer
— inertial reference
— input/output
— line replaceable unit
— linear variable differential transformer
— mode control panel
— Low pressure rotor speed
— a number from 01 to 99
— power control unit
— stall management yaw damper
— volts
— wheel to rudder interconnect system
— yaw damper system
Aug 99
REFRESHER COURSE
FRA US/E NM
YAW DAMPER SYSTEM (YDS) - INTRODUCTION
Purpose
The yaw damper system keeps the airplane stable around the yaw axis.
When in flight, the yaw damper commands rudder movement in proportion to,
and opposite to, the yawing moment.
This keeps dutch roll to a minimum and makes the flight smoother.
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 150
B737-600/700/800
22-23
For Training Purposes Only
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
Figure 71
Aug 99
REFRESHER COURSE
FRA US/E NM
YAW DAMPER (YD) INTRODUCTION
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 151
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AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
YDS - GENERAL DESCRIPTION
General
The yaw damper system moves the rudder to oppose dutch roll.
The system is available for the full flight.
The yaw damper system consists of these components:
S Yaw damper engage switch
S Yaw damper disengage light
S Stall management yaw dampers (SMYD 1 + 2)
S Yaw damper indicator
S Solenoid valve (main rudder PCU)
S Electrohydraulic servo valve (main rudder PCU)
S LVDT (main rudder PCU).
ADIRU
The air data inertial reference units send airspeed and inertial reference data to
the SMYD.
Yaw Damper Engage Switch and Disengage Light
You engage the yaw damper system with a switch on the flight control panel.
When you engage the yaw damper, the B-Hydraulic system should be ON.
This is not a precondition for holding the Yaw Damper switch in the ON position.
The disengage warning light is above the switch.
The light shows if the yaw damper is not engaged while power is on the airplane.
For Training Purposes Only
Stall Management Yaw Damper
The SMYD 1 controls the primary yaw damping function and the stall management function. SMYD 1 receives data from both ADIRUs and sends commands
to the main rudder PCU.
Yaw Damper Indicator
The yaw damper indicator, on the P2 panel, shows rudder movement due to
the yaw damper
Main Rudder PCU
The main rudder power control unit (PCU) is a hydraulic component that moves
the rudder.
It receives commands from the SMYD 1 to decrease unwanted yaw motion.
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 152
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
HYDRAULIK
SYSTEM A
For Training Purposes Only
HYDRAULIK
SYSTEM B
Figure 72
Aug 99
REFRESHER COURSE
FRA US/E NM
YD GENERAL DESCRIPTION
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 153
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
YDS - COCKPIT COMPONENT LOCATIONS
Engage Switch and Disengage Light
The yaw damper engage switch and the disengage light are on the flight control panel (P5 forward overhead panel)
For Training Purposes Only
Yaw Damper Indicator
The yaw damper indicator is on the P2 panel
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 154
B737-600/700/800
22-23
For Training Purposes Only
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
Figure 73
Aug 99
REFRESHER COURSE
FRA US/E NM
YD COMPONENT LOCATION
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 155
B737-600/700/800
22-23
YDS - E+E COMPARTMENT COMP. LOCATIONS
Stall Management Yaw Damper
The SMYD 1 is on the E3—2 shelf in the electronic equipment compartment.
For Training Purposes Only
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 156
B737-600/700/800
22-23
For Training Purposes Only
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
Figure 74
Aug 99
REFRESHER COURSE
FRA US/E NM
YD COMPONENT LOCATION
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 157
B737-600/700/800
22-23
YDS - VERTICAL STABILIZER COMP. LOCATIONS
Solenoid and Electrohydraulic Servo Valve
The YPS has two LRUs in the vertical stabilizer.
The yaw damper solenoid valve and the electrohydraulic servo valve (EHSV)
are mounted on the main rudder PCU.
In addition to the LRUs, there is a linear variable differential transformer (LVDT)
that is mounted on the main PCU. The LVDT is not an LRU.
You access these components from the right side of the vertical stabilizer
For Training Purposes Only
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 158
B737-600/700/800
22-23
For Training Purposes Only
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
Figure 75
Aug 99
REFRESHER COURSE
FRA US/E NM
YD COMPONENT LOCATION
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 159
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
SMYD 1 - YDS: INTERFACES
Power
The SMYD 1 gets 28v dc from electrical bus 1 and 28v ac from transfer bus 1.
28v dc power goes from SMYD 1 to the engage switch.
The yaw damper indicator gets 115v ac from transfer bus 1.
The LVDT gets 28v ac from the same circuit as the SMYD 1.
For Training Purposes Only
Digital Data
The SMYD 1 gets this data from the ADIRUs:
S Airspeed (ADIRU 1 only)
S Impact pressure (ADIRU 1 only)
S Lateral acceleration
S Roll angle
S Roll rate
S Yaw rate.
Analog Signals
The SMYD 1 sends yaw damper commands to the main rudder PCU.
The LVDT on the main rudder PCU sends rudder position feedback, due to yaw
damping, to the yaw damper indicator and the SMYD 1.
The trailing edge flap limit switch sends flap position data to the SMYD 1.
The AOA sensor sends angle of attack information to the SMYD 1.
When you close the yaw damper engage switch, it sends an engage signal
through SMYD 1 to the actuator solenoid on the main rudder PCU.
Power goes from the DC power and dim control to the yaw damper disengage
light.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 160
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
115V AC
XFER BUS 1
YAW DAMPER
28V AC
XFER BUS 1
LVDT-Y AW DAMPER
YAW DAMPER
28V DC
ELEX BUS 1
RUDDER POSITION
RUDDER
FEEDBACK
ELECTROHYDRAULIC
SERVO VALVE
YAW DAMPER
COMMAND
SIGNAL
P18 CIRCUIT BREAKER
PANEL
AIRSPEED
IMPACT PRESSURE
LATERAL ACC
ROLL ANGLE
ROLL RATE
YAW RATE
LATERAL ACC
ROLL ANGLE
ROLL RATE
YAW RATE
28 V DC POWER
ENGAGE COMMAND
SOLENOID VALVE
YAW DAMPER
INDICATOR
MAIN RUDDER PCU
ADIRU 1
ENGAGE
ENABLE
ENGAGE SWITCH
SOLENOID POWER
ENGAGE
SIGNAL
ENGAGE REQUEST
- - - - - - - - - - YD DISENGAGE LIGHT
POWER
GROSS WEIGHT
FLIGHT CONTROL PANEL
DC POWER AND
DIM CONTROL
ADIRU 2
FMC
For Training Purposes Only
ANGLE OF AIRFLOW
SMYD CROSSCHANNEL BUS
LEFT AOA SENSOR
FLAPS UP
SMYD 2
SMYD 1
NOTE:
THE SHADOWED
AREAS ARE NOT
FOR YAW DAMPING !
TRAILING EDGE
FLAPS UP
LIMIT SWITCH
NOTE:
THIS DIAGRAM ONLY
SHOWS INTERFACES FOR
PRIMARY YAW DAMPING
Figure 76
Nov. 2001
REFRESHER COURSE
FRA US/E NM
YD INTERFACES
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 161
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
SYMD 2: YD - INTERFACES
Power
SMYD 2 gets 28v dc from DC bus 1 and 28v ac from transfer bus 1. 28v dc
power goes from SMYD 2 to the yaw damper engage switch.
The linear variable differential transformer (LVDT) on the standby rudder PCU
gets 28v ac from the same circuit as SMYD 2.
For Training Purposes Only
Digital Data
SMYD 2 receives airplane gross weight from the FMC.
SMYD 2 receives these air data from the right ADIRU:
S Airspeed
S Impact pressure.
SMYD 2 receives these inertial data from the left and right ADIRUs:
- Lateral acceleration
- Roll angle
- Roll rate
- Yaw rate.
Analog Signals
SMYD 2 sends commands to the standby rudder PCU to assist turns during
flight control manual reversion, and for standby yaw damping/turn coordination.
The LVDT on the standby rudder PCU sends rudder position data to SMYD 2
about rudder movement.
The trailing edge flaps up limit switches send flaps up/not up data to SMYD 2
to limit rudder movement when the flaps are up.
Power goes from the DC power and dim control to the yaw damper disengage
light.
During standby hydraulic operations, when you turn ON the yaw damper engage switch, an engage signal goes through SMYD 2 to the yaw damper solenoid valve on the standby rudder PCU to engage the yaw damper.
SMYD 2 commands rudder movement using the standby EHSV.
The flight control panel switches for system A and B must be in the OFF or
STBY RUD position to enable SMYD 2 for WTRIS and standby yaw damping.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 162
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
28V AC
XFR BUS 1
YAW DAMPER
CONTROL WHEEL
POSITION
28V DC
BUS 1
YAW DAMPER
CAPT CONTROL WHEEL
POSITION SENSOR
P6-1 CB PANEL
AIRSPEED
IMPACT PRESSURE
RUDDER
FEEDBACK
LATERAL ACC
ROLL ANGLE
ROLL RATE
YAW RATE
COMMAND
SIGNALS
LATERAL ACC
ROLL ANGLE
ROLL RATE
YAW RATE
RIGHT ADIRU
28V DC POWER
ENGAGE COMMAND
LVDT YAW DAMPER
RUDDER POSITION
EHSV
SOLENOID VALVE
STANDBY RUDDER PCU
LEFT ADIRU
ENGAGE
ENABLE
ENGAGE
SIGNAL
GROSS WEIGHT
For Training Purposes Only
FMC
FLAP POSITION
LEFT FLAP POSITION XMTR
POWER
FLAPS UP
SMYD 2
NOTE:
THE SHADOWED INPUTS
ARE NOT FOR
YAW DAMPING
TRAILING EDGE FLAPS UP
LIMIT SWITCHES
Figure 77
Nov. 2001
REFRESHER COURSE
FRA US/E NM
YD ENGAGE REQUEST
- - - - - - - - - YD DISENGAGE LIGHT
FLIGHT CONTROL PANEL
ANGLE-OF-AIRFLOW
RIGHT AOA SENSOR
SWITCH SOLENOID
POWER
NOTE:
THIS DIAGRAM ONLY
SHOWS INTERFACES FOR
PRIMARY YAW DAMPING
DC POWER AND
DIM CONTROL
SMYD 2 - YD INTERFACES
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 163
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AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
YDS - OPERATIONS
General
There is only one control for the dual yaw damper system.
This is the ON/OFF switch on the flight control panel in the flight compartment.
There are two displays for the yaw damper system:
- the yaw damper warning light and
- the yaw damper indicator.
The yaw damper warning light is on the flight control panel above the yaw
damper ON/OFF switch.
The yaw damper indicator shows yaw damper movement.
For Training Purposes Only
Engage Switch and Warning Light
With the B hydraulic system ON, you engage the yaw damper system No.1
with the ON / OFF switch on the flight control panel.
To engage the YDS, put the switch in the ON position.
If there are no faults, two seconds later the yaw damper warning light will go
out.
The switch is held in the ON position electronically.
Put the switch in the OFF position to disengage the YDS.
The yaw damper warning light will come on.
The warning light comes on anytime the system disengages.
Yaw Damper Indicator
The yaw damper indicator shows yaw damper movement
The yaw damper moves the rudder a maximum of 2 degrees with flaps up, and
2 1/2 degrees with flaps down, in each direction to reduce dutch roll.
The yaw damper indicator shows this rudder motion, but the rudder pedals do not move.
Moving the rudder by pressing the rudder pedals does not move the indicator.
To test the indicator and the yaw damper system, do the servo test described
on the SMYD BITE — GROUND TEST pageset at the end of this section.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 164
B737-600/700/800
22-23
For Training Purposes Only
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
Figure 78
Nov. 2001
REFRESHER COURSE
FRA US/E NM
YD OPERATIONS
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 165
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
YDS - OPERATIONS: ENGAGE INTERLOCKS
General
There are two SMYDs on the airplane.
SMYD 1 controls primary yaw damping and turn coordination during normal
operation.
SMYD 2 operates WTRIS and standby yaw damping, and is discussed in the
WTRIS section.(AMM PART 1, 27-24)
These functions in SMYD 2 are activated by pin programming at the E/E shelf.
SMYDs
The two SMYDs are the same.
They both do stall management and yaw damper functions.
For stall management functions, both SMYDs operate together.
If one function fails, the other SMYD will continue to do stall management functions.
For Training Purposes Only
Only one SMYD does yaw damping at a time.
SMYD 1 does only primary yaw damping during normal operations.
SMYD 2 does standby yaw damping during standby operations.
This is controlled by the FLT CONTROL A and B switches on the flight control
panel.
SMYD 1 uses the main rudder PCU to move the rudder for the primary yaw
damper function. For primary yaw damping,
SMYD 1 compares its yaw damping calculations with SMYD 2 before it sends a
command to the main rudder PCU.
If the SMYD 2 calculations disagree or if SMYD 2 fails, the yaw damper function in SMYD 1 disengages even though SMYD 2 is not used for primary yaw
damping.
When the SMYD is in the number 2 position it uses the standby rudder PCU for
standby yaw damper functions.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
SMYD 1:
YD Engage Switch and Warning Light
You engage the primary yaw damper system (YDS) with the yaw damper engage switch on the flight control panel and with the FLT CONTROL B switch in
the ON position.
The SMYD does a self check and two seconds later the yaw damper warning
light goes out to show that you have yaw damper operation.
The switch is held in the ON position electronically with power from the SMYD.
Put the switch in the OFF position to disengage the YDS.
After you put the switch to the OFF position, the yaw damper warning light
comes on.
The warning light comes on anytime the system disengages.
SMYD 2:
YD Engage Switch and Warning Light
You engage the standby yaw damper system (YDS) with the
- yaw damper engage switch on the flight control panel in the ON position
and
- with both FLT CONTROL switches not in ON position and at least one in
the STANDBY position.
The SMYD does a self check and two seconds later the yaw damper warning
light goes out to show that you have yaw damper operation.
The switch is held in the ON position electronically with power from the SMYD.
Put the switch in the OFF position to disengage the YDS.
After you put the switch to the OFF position, the yaw damper warning light
comes on.
The warning light comes on anytime the system disengages.
Training Information Point
The electrical ground for the disengage light is connected in series through
both SMYDs. For normal operation, it is necessary to have both SMYDs
installed on the airplane.
The light test can be done with the master dim and test system.
The WTRIS and standby yaw damping functions of SMYD 2 can only be engaged when standby hydraulics is ON and both systems A and B are OFF.
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 166
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
DC POWER
28V DC
BUS 1
POWER SUPPLY
YAW DAMPER 1
A A
2 SEC
YAW DAMPER 2
MASTER
WARNING
SYSTEM
DISENGAGE LIGHT
P18 CIRCUIT BREAKER PANEL
2 SEC
FLIGHT CONTROL
MODULE
YD CHANNEL OK
YAW
DAMPER
SWITCH
NC
PROGRAM
PINS
2 SEC
YAW DAMPER
ACTUATOR
SOLENOID
SMYD 1
OFF/STANDBY
MAIN RUDDER PCU
POWER SUPPLY
2 SEC
ON
For Training Purposes Only
FLT CONT B
2 SEC
OFF/STANDBY
ON
FLT CONT A
FLIGHT CONTROL
PANEL
YAW DAMPER
ACTUATOR
SOLENOID
YD CHANNEL OK
NC
PROGRAM
PINS
2 SEC
STANDBY RUDDER PCU
SMYD 2
Figure 79
Nov. 2001
REFRESHER COURSE
FRA US/E NM
YD ENGAGE INTERLOCK
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 167
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
YDS - SMYD BITE
General
The SMYD has these BITE functions:
S Continuous monitors
S BITE tests.
The BITE tests on the front of the SMYD test those items that the continuous
monitor cannot test.
Continuous Monitor
Continuous monitors test the SMYD for proper operation.
When the SMYD has a failure, a fault is put in fault history.
Some faults cause no SMYD outputs.
BITE Tests
BITE tests have these functions:
S A quick system test
S Check SMYD operation after replacement
S A series of tests to show all functions are within specifications
S Support fault isolation.
Six push—button switches and a two row 8 character display are on the front of
the SMYD for BITE tests.
BITE
-
Operation
Push the ON/OFF switch to start BITE tests.
Push the up arrow to see the previous menu item.
Push the down arrow or NO key to see the next menu item.
Push the YES key to move down into the menu on the display.
Push the MENU key to move back up one level. In some lists, TOP OF
LIST and END OF LIST show for one second when you move to the top
or bottom of the list.
To operate BITE, the airplane must have the flaps up and VCAS < 60 knots or
engine not running to start the test.
Engines not running means that the on—side engine N1 < 15% and the off—
side engine N1 < 50%.
Main Menu
These are the BITE main menu selections:
S EXISTING FAULTS
S FAULTS HISTORY
S GROUND TESTS
S OTHER FUNCTIONS.
For Training Purposes Only
You push the YES key to enter any of these menu selections.
Aug 99
REFRESHER COURSE
FRA USE NM
FOR TRAINING PURPOSES ONLY
AMET Page:
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AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
ON
STATIC
SENSITIVE
”BITE INSTRUCTIONS”
ON/OFF:START OR STOP BITE
MENU : TO DISPLAY MENU
YES/NO: IN RESPONSE TO
QUESTION (?)
:TO SCROLL THROUGH
OR
MENU OR RESULTS
OFF
1
INTO
EXISTING
FAULTS
YES
EXISTING
FAULTS?
NO
MENU
For Training Purposes Only
YES
ON
OFF
XXXXXXXXXXX
YES
ON-SIDE ENG N1 < 15%
FAULTS
HISTORY?
OFF-SIDE ENG N2 < 50%
FLAPS UP
AIRSPEED < 60 KNOTS
INTO
GROUND
TESTS
YES
GROUND
TESTS?
NO
MOD
INTO
OTHER
FUNCTIONS
YES
OTHER
FUNCTNS?
NO
2
Figure 80
Aug 99
REFRESHER COURSE
FRA USE NM
BITE
ENABLE
NO
NO
STALL MANAGEMENT
YAW DAMPER
P/N 65-52822-XX
S/N XXXXXXXXXXXX
XXXXXXXXXXXX
INTO
FAULTS
HISTORY
1
SHOWS TOP OF LIST FOR 1 SECOND
2
SHOWS END OF LIST FOR 1 SECOND
SMYD - BITE
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 169
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
YDS - SMYD BITE: EXISTING FAULTS
Existing Faults
The existing faults test does a check of the interfaces to the SMYD.
To do the existing faults test, do these steps:
S Go to the main menu
S Use the up or down arrow switches until you see EXISTING FAULTS? in
the BITE display
S Push the YES switch.
If the test passes, then the display shows NO FAULTS.
If the test fails, then the display shows a fault message.
You can use the switches on the BITE panel to see more information about the
fault message.
You can also see if there are other fault messages.
For Training Purposes Only
More Details
MORE DETAILS? shows:
S The message number
S Flight deck effect for the SWS, YD, and autoslat
S The most likely LRU causing the fault
S Whether the fault is latched or not.
Reset Latches
Note:
There are faults in the memory which disable the SMYD-Test.
They are not automatically reset after replacing the faulty component(s).
You have to do the RESET LATCHES procedure on the SMYDs front.
To reset the latched faults, push the YES switch.
The RESET IN PROGRESS display with show while the latched faults are being reset.
Aug 99
REFRESHER COURSE
FRA USE NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 170
B737-600/700/800
22-23
NOTE:
IF YOU ENTER THE MSG NO. IN
THE PMAs „MAINTENANCE MSG“
FIELD, THE PMA WILL SHOW THE
FIM TASK FOR REPAIR !!
For Training Purposes Only
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
Figure 81
Aug 99
REFRESHER COURSE
FRA USE NM
YDS BITE, EXISTING FAULTS
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 171
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
YDS - SMYD BITE: FAULT HISTORY
Fault History
The fault history selection shows fault information that is in the non—volatile
memory (NVM) in the SMYD.
Monitors in the SMYD put data in the NVM during these conditions:
S System tests using the SMYD BITE
S Continuous monitoring
S Power up tests.
The NVM keeps data for the last 64 flight legs and a maximum of 256 failures.
Only flight legs that have faults are displayed in fault history.
The flight leg changes when the airplane goes from the ground to the air, except during touch and go operations.
Flight leg 0 is the most recent flight.
To find fault information, do these steps:
S Go to the main menu
S Use the up or down arrow switches until you see FAULT HISTORY? in the
BITE display
S Push the YES switch
S Use the up or down arrow switches until you see the flight leg that you want
S Push the YES switch.
For Training Purposes Only
The information for MORE DETAILS? is the same as for the existing faults test.
Aug 99
REFRESHER COURSE
FRA USE NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 172
B737-600/700/800
22-23
NOTE:
IF YOU ENTER THE MSG NO. IN
THE PMAs „MAINTENANCE MSG“
FIELD, THE PMA WILL SHOW THE
FIM TASK FOR REPAIR !!
For Training Purposes Only
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
Figure 82
Aug 99
REFRESHER COURSE
FRA USE NM
YDS BITE, FAULT HISTORY
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 173
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
YDS - SMYD BITE: GROUND TESTS
Ground Test
GROUND TEST has these menus:
S SELF TESTS?
S DISCRETE INPUTS?
S ARINC 429 INPUTS?
S ANALOG INPUTS?
S SERVO TEST?
S DISPLAY TEST?.
To start one of these tests, do these steps:
S Go to the main menu
S Use the up or down arrow switches until you see GROUND TESTS? in the
BITE display
S Push the YES switch
S Use the up or down arrow switches until you see the test that you want
S Push the YES switch.
If the test passes, then the display shows TEST PASSED. If the test fails, then
the display shows a fault message. The information for MORE DETAILS? is
the same as for the existing faults test.
For Training Purposes Only
Self Test
The self test checks the SMYD for faults. When you push YES, the display
shows TEST IN PROGRESS until the test is finished. If the SMYD passes the
test, the display shows SMYD LRU OK. If the SMYD does not pass the test,
the display shows SMYD LRU FAIL for 2 seconds, then shows the first fault.
Discrete Inputs
You check the status of the discrete inputs from the DISCRETE INPUTS?
menu. Push the YES switch to see the list of discrete inputs. Use the up (previous), and down (next) arrows to move through the list.
ARINC 429 Test
You can check the ARINC 429 buses from the ARINC 429 INPUT?
You can check the activity status of these buses:
S On side IR bus
Aug 99
REFRESHER COURSE
FRA USE NM
S Off side IR bus
S On side ADR bus
S CDS DEU bus
S FMC bus
S DFCS MCP bus
S Cross channel bus.
Push the YES switch to see if the bus is active or inactive. Use the up and
down arrows to move through the list.
Analog Inputs
You check the status of these sensors from the ANALOG INPUTS? menu.
Push the YES switch to select a sensor. Use the up (previous) and down (next)
arrows to move through the list. These sensors can be checked:
S AOA sensor
S Flap sensor
S Wheel sensor
S YD LVDT.
Push the YES switch to select a sensor. Use the up (previous), and down
(next) arrows to move through the list.
Servo Test
You test the yaw damper components on the rudder PCU, as well as the interface between the SMYD and the PCU, with the SERVO TEST. You can test
these components
S Yaw damper EHSV
S Yaw damper engage solenoid.
S Yaw damper LVDT.
Display Test
You test the display on the SMYD by pushing the YES switch when the DISPLAY TEST? prompt shows.
The test takes about 10 seconds. All the LEDs on the left half of the top line will
come on first. Then all the LEDs on the right half will come on. Next all the
LEDs on the left half of the bottom line will come on, and finally all the LEDs on
the right half will come on. When the test is complete, DISPLAY TEST? will
show on the display.
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 174
B737-600/700/800
22-23
For Training Purposes Only
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
Figure 83
Aug 99
REFRESHER COURSE
FRA USE NM
YDS BITE, GROUND TESTS
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 175
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
YDS - SMYD BITE: SERVO TEST
General
The servo test consists of these two tests:
S ZERO COMMAND
S SWEEP TEST.
Zero Command
The main rudder PCU is commanded to the zero position. The signal from the
LVDT is compared to the servo command.
For Training Purposes Only
Sweep Test
The main rudder PCU is commanded to the left, right and center position.
The signal from the LVDT is compared to the servo command to pass or fail
the test.
If the test passes, the ZERO COMMAND menu shows after the TEST EXISTING? display.
If the test fails, the faults are listed the same as for the existing faults test.
Aug 99
REFRESHER COURSE
FRA USE NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 176
B737-600/700/800
22-23
For Training Purposes Only
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
Figure 84
Aug 99
REFRESHER COURSE
FRA USE NM
YDS BITE, SERVO TEST
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 177
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
YDS - SMYD BITE: OTHER FUNCTIONS
General
OTHER FUNCTIONS has these menus:
S SYSTEM CONFIG?
S I/O MONITOR.
To enter these sections you must push the YES key.
System Configuration
In the system configuration section you verify these attributes:
S Part number
S Software Level Position (1 or 2)
S Airplane type
S FAA or CAA/FAA.
For Training Purposes Only
I/O Monitor
In the I/O Monitor section you verify these inputs and outputs:
S ARINC 429 inputs
S ARINC 429 low speed outputs
S ARINC 429 high speed outputs
Aug 99
REFRESHER COURSE
FRA USE NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 178
B737-600/700/800
22-23
For Training Purposes Only
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
Figure 85
Aug 99
REFRESHER COURSE
FRA USE NM
YDS BITE, OTHER FUNCTIONS
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 179
Lufthansa Technical Training
For Training Purposes Only
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
27-24
B737-600/700/800
27-24
WHEEL TO RUDDER INTERCONNECT SYSTEM
ABBREVIATIONS AND ACRONYMS
AC
ADR
ADIRU
AOA
ARINC
ATR
BITE
CAA
CDS
CPU
DC
DEU
DFCS
EHSV
FAA
FMC
IR
I/O
LRU
LVDT
MCP
N1
NN
PCU
SMYD
V
WTRIS
YDS
WTRIS - INTRODUCTION
— alternating current
— air data reference
— air data inertial reference unit
— angle of attack
— Aeronautical Radio Incorporated
— Austin Trumbull Radio
— built in test equipment
— Civil Aviation Authority
— common display system
— central processing unit
— direct current
— display electronic unit
— digital flight control system
— electrohydraulic servo valve
— Federal Aviation Administration
— flight management computer
— inertial reference
— input/output
— line replaceable unit
— Linear variable differential transformer
— mode control panel
— Low pressure rotor speed
— a number from 01 to 99
— power control unit
— stall management yaw damper
— volts
— wheel to rudder interconnect system
— yaw damper system
Nov. 2001
REFRESHER COURSE
FRA US/E NM
Purpose
The wheel to rudder interconnect system (WTRIS) assists manual reversion
turns when both hydraulic systems A and B are OFF, and the standby system
is ON.
The WTRIS commands a small amount of rudder movement as a function of
the capt’s control wheel aileron input.
FOR TRAINING PURPOSES ONLY
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FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
B737-600/700/800
27-24
For Training Purposes Only
YAW DAMPER COMPONENTS
ON STANDBY RUDDER PCU
SMYD 2
(E/E BAY)
CONTROL WHEEL
POSITION SENSOR
(CAPT SIDE)
Figure 86
Nov. 2001
REFRESHER COURSE
FRA US/E NM
WTRIS INTRODUCTION
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 181
Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
B737-600/700/800
27-24
WTRIS - GENERAL DESCRIPTION
General
The wheel-to-rudder interconnect system (WTRIS) moves the rudder to help
turns during flight control manual reversion when on standby hydraulics.
For the WTRIS function, SMYD 2 has interfaces with these components:
- Control wheel position sensor (captain)
- Yaw damper engage switch
- Yaw damper disengage light
- Flight control panel switches
- Standby yaw damper solenoid valve
- Standby EHSV
- Standby LVDT
- FMC
- Trailing edge flaps up limit switches
- Left flap position transmitter.
- Stall Management Yaw Damper
For Training Purposes Only
SMYD 2 commands rudder movement for WTRIS and standby yaw damping
and turn coordination during flight control manual reversion when on standby
hydraulics.
SMYD 2 receives data from airplane sensors, switches and components, and
uses the data to calculate and send commands to the standby rudder PCU to
move the rudder.
Standby Rudder PCU
The standby rudder PCU is a hydraulic actuator that moves the rudder in
response to pilot rudder inputs when on standby hydraulic pressure.
During standby operation, SMYD 2 sends commands to the yaw damper
components on the standby rudder PCU.
ADIRU
The air data inertial reference units (ADIRUs) send data to the SMYDs.
The data includes airspeed, attitude, and yaw and roll rates and accelerations.
FMC
The FMC provides airplane gross weight to the SMYDs.
Trailing Edge Flaps Up Limit Switches
The trailing edge flaps up limit switches send data to the SMYD to limit rudder
travel when flaps are up.
Left Flap Position Transmitter
The left flap position transmitter sends data to SMYD 2.
Control Wheel Position Sensor
The captain control wheel (CW) position sensor senses pilot aileron input and
sends an analog signal to the SMYD 2 to calculate a command for left/right
rudder movement for WTRIS.
Yaw Damper Engage Switch and Disengage Light
You engage WTRIS and standby yaw damping with the yaw damper switch on
the flight control panel.
The disengage warning light is above the switch.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
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Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
STBY
RUD
OFF
A ON
B737-600/700/800
27-24
FLT CONTROL
A
B
STBY
RUD
OFF
B ON
CONTROL WHEEL
POSITION SENSOR
(CAPT SIDE)
FWD
YAW DAMPER
OTHER SENSORS
FMC
RIGHT AOA SENSOR
TE FLAPS UP LIMIT SWITCHES
LEFT FLAP POSITION TRANSMITTER
YAW
DAMPER
OFF
ON
For Training Purposes Only
FLIGHT CONTROL PANEL
SMYD 2
STANDBY RUDDER PCU
RUDDER
ADIRU (2)
Figure 87
Nov. 2001
REFRESHER COURSE
FRA US/E NM
WTRIS - GENERAL
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 183
Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
B737-600/700/800
27-24
WTRIS - COMPONENT LOCATIONS
Flight Compartment
The yaw damper engage switch and the disengage light are on the flight control panel.
For Training Purposes Only
Forward Nose Compartment
The control wheel position sensor is at the bottom of the captain’s control column, below the floor.
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 184
B737-600/700/800
27-24
For Training Purposes Only
Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
Figure 88
Aug 99
REFRESHER COURSE
FRA US/E NM
WTRIS - COMPONENT LOCATION
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 185
B737-600/700/800
27-24
Stall Management Yaw Damper
The SMYD 2 is on the E3—2 shelf in the electronic equipment bay.
For Training Purposes Only
Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
Aug 99
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 186
B737-600/700/800
27-24
For Training Purposes Only
Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
Figure 89
Aug 99
REFRESHER COURSE
FRA US/E NM
WTRIS COMPONENT LOCATION
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 187
Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
B737-600/700/800
27-24
SMYD 2 WTRIS - INTERFACES
Power
The SMYD 2 gets 28v dc from electrical bus 1 and 28v ac from transfer bus 1.
28v dc power goes from SMYD 2 to the engage switch.
The linear variable differential transformer (LVDT) gets 28v ac from the same
circuit as the SMYD 2.
Digital Data:
SMYD 2 receives airplane gross weight from the FMC.
SMYD 2 receives these air data from the right ADIRU:
S Airspeed
S Impact pressure.
Operation
During standby hydraulic operations, when you turn ON the yaw damper engage switch, an engage signal goes through SMYD 2 to the yaw damper solenoid valve on the standby rudder PCU to engage the yaw damper.
SMYD 2 commands rudder movement using the standby EHSV.
The flight control panel switches for system A and B must be in the OFF or
STBY RUD position to enable SMYD 2 for WTRIS and standby yaw damping.
For Training Purposes Only
SMYD 2 receives these inertial data from the left and right ADIRUs:
- Lateral acceleration
- Roll angle
- Roll rate
- Yaw rate.
Analog Signals:
SMYD 2 sends commands to the standby rudder PCU to assist turns during
flight control manual reversion, and for standby yaw damping/turn coordination.
The LVDT on the standby rudder PCU sends rudder position data to SMYD 2
about rudder movement.
The trailing edge flaps up limit switches send flaps up/not up data to SMYD
2 to limit rudder movement when the flaps are up.
The left flap position transmitter sends flap position data to SMYD 2 to use
in stall warning, WTRIS and yaw damping command calculation.
Power goes from the DC power and dim control to the yaw damper disengage
light.
The captain control wheel (CW) position sensor sends control wheel aileron input information to SMYD 2 for the WTRIS function.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 188
Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
B737-600/700/800
27-24
28V AC
XFR BUS 1
YAW DAMPER
CONTROL WHEEL
POSITION
28V DC
BUS 1
YAW DAMPER
CAPT CONTROL WHEEL
POSITION SENSOR
P6-1 CB PANEL
AIRSPEED
IMPACT PRESSURE
LVDT YAW DAMPER
RUDDER POSITION
RUDDER
FEEDBACK
LATERAL ACC
ROLL ANGLE
ROLL RATE
YAW RATE
COMMAND
SIGNALS
LATERAL ACC
ROLL ANGLE
ROLL RATE
YAW RATE
RIGHT ADIRU
EHSV
28V DC POWER
ENGAGE COMMAND
SOLENOID VALVE
STANDBY RUDDER PCU
LEFT ADIRU
For Training Purposes Only
FMC
FLAP POSITION
LEFT FLAP POSITION XMTR
POWER
FLAPS UP
DC POWER AND
DIM CONTROL
SMYD 2
NOTE:
THE SHADOWED INPUTS
ARE NOT FOR WTRIS !!
TRAILING EDGE FLAPS UP
LIMIT SWITCHES
Figure 90
Nov. 2001
REFRESHER COURSE
FRA US/E NM
YD ENGAGE REQUEST
- - - - - - - - - YD DISENGAGE LIGHT
FLIGHT CONTROL PANEL
ANGLE-OF-AIRFLOW
RIGHT AOA SENSOR
SWITCH SOLENOID
POWER
ENGAGE
ENABLE
ENGAGE
SIGNAL
GROSS WEIGHT
NOTE:
THIS DIAGRAM ONLY
SHOWS INTERFACES FORWTRIS
SMYD 2 - WTRIS INTERFACES
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 189
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
SYMD 2 - WTRIS: OPERATIONS
General
The yaw damper engage switch on the flight control panel is used to turn ON
the WTRIS and standby yaw damper.
The yaw damper disengage warning light is above the engage switch.
For Training Purposes Only
Engage Switch and Warning Light
To turn on the WTRIS and standby yaw damper (SMYD 2 ), do these steps on
the flight control panel:
- Place both FLT CONT A and B switches to OFF
- Place at least one of these switches to STBY RUD
- Engage the yaw damper switch to ON.
The flight control A and B switches to OFF sends a signal to enable SMYD 2
for WTRIS and standby yaw damping.
One or both of these switches to the STBY RUD position provides standby hydraulic pressure to the standby rudder PCU to move the rudder.
After you turn on the WTRIS and the standby yaw damper, and after a twosecond delay, the yaw damper engage light will go off to show these systems
are operating.
If there is a system fault, SMYD 2 will remove power from the engage solenoid
valve on the standby rudder PCU to shut off hydraulic fluid to the EHSV.
SMYD 2 also removes power from the yaw damper engage switch on the flight
control panel.
After a two-second delay, the engage switch moves to OFF and the yaw
damper disengage light comes ON to show the system has disengaged.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
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Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
FLT CONTROL
FLT CONTROL
A AND B SWITCHES
A
STANDBY
HYD
B
STBY
RUD
STBY
RUD
OFF
OFF
A ON
B ON
LOW
QUANTITY
LOW
PRESSURE
ALTERNATE FLAPS
OFF
UP
LOW
LOW
PRESSURE PRESSURE
OFF
SPOILER
A
B
For Training Purposes Only
DISENGAGE
WARNING LIGHT
ARM
OFF
OFF
ON
ON
YAW DAMPER
YAW
DAMPER
YAW DAMPER
ENGAGE SWITCH
DOWN
SPEED TRIM
FAIL
FEEL DIFF
FAIL
MACH TRIM
FAIL
AUTO SLAT
FAIL
OFF
ON
FLIGHT CONTROL PANEL
Figure 91
Nov. 2001
REFRESHER COURSE
FRA US/E NM
SMYD 2 - YD/WTRIS OPS
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 191
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
SMYD 2 - WTRIS OPERATIONS: ENGAGE INTERLOCKS
General
SMYD 2 operates the wheel to rudder interconnect system (WTRIS) and
standby yaw damping during standby operations.
For WTRIS and standby yaw damping, SMYD 2 requires that both flight control
A and B hydraulic switches be OFF, with at least one switch in STBY RUD to
provide standby hydraulic pressure to the standby rudder PCU.
Engage Switch and Warning Light
To engage the WTRIS and standby yaw damping, you put the yaw damper
engage switch on the flight control panel to the ON position.
Two seconds later, the yaw damper warning light goes out to show these
systems are operating.
The switch is held in the ON position with power from SMYD 2.
For Training Purposes Only
Put the switch in the OFF position to disengage the WTRIS and standby yaw
damping.
The yaw damper warning light comes on.
The warning light comes on anytime the system is disengaged.
During a system fault and after disengagement, the SMYD 2 removes power
from the engage switch solenoid so that the switch moves to the OFF position.
Training Information Point
The electrical ground for the disengage light is connected in series through
both SMYDs.
For normal operation, both SMYDs are necessary on the airplane.
You can do a test of the light with the master dim and test system.
SMYD
When a SMYD computer is in the number 2 position, it operates the WTRIS
and standby yaw damping.
This is when flight control hydraulic system A and B are OFF and the standby
system is ON.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 192
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
DC POWER
A A
28V DC
BUS 1
POWER SUPPLY
YAW DAMPER 1
2 SEC
YAW DAMPER 2
MASTER
WARNING
SYSTEM
DISENGAGE LIGHT
P18 CIRCUIT BREAKER PANEL
FLIGHT CONTROL
PANEL
2 SEC
YD CHANNEL OK
YAW
DAMPER
SWITCH
NC
OFF/
STANDBY
PROGRAM
PINS
YAW DAMPER
ACTUATOR
SOLENOID
2 SEC
MAIN RUDDER PCU
SMYD 1
NOTE:
THE SHADOWED
COMPONENTS
ARE NOT FOR
WTRIS !!
POWER SUPPLY
For Training Purposes Only
ON
FLT CONT B
2 SEC
2 SEC
OFF/
STANDBY
ON
FLT CONT A
FLIGHT CONTROL
PANEL
YD CHANNEL OK
NC
PROGRAM
PINS
YAW DAMPER
ACTUATOR
SOLENOID
2 SEC
STANDBY RUDDER PCU
SMYD 2
WTRIS - OPERATIONS - ENGAGE INTERLOCKS
Figure 92
Nov. 2001
REFRESHER COURSE
FRA US/E NM
SMYD 2 - WTRIS ENGAGE
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 193
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
SMYD 2 - WTRIS: FUNCTIONAL DESCRIPTION
General
SMYD 2 uses analog and digital data inputs to calculate rudder commands for
WTRIS and standby yaw damping/turn coordination.
For Training Purposes Only
Engage Interlock
SMYD 2 supplies 28v dc to the yaw damper solenoid valve on the standby rudder PCU.
When this solenoid valve is energized it supplies hydraulic fluid to the EHSV to
operate the yaw damper actuator on the standby rudder PCU to move the rudder for WTRIS and standby yaw damping.
WTRIS
The WTRIS function of SMYD 2 uses control wheel aileron inputs from the
captain control wheel position sensor to command small amounts of rudder
movement.
This helps turn the airplane during flight control manual reversion when operating on standby hydraulics.
The SMYD central processing unit (CPU) operates the control law software.
For SMYD 2, the software calculations are based on inputs from these components:
- Captain control wheel position sensor
- ADIRUs (inertial and air data)
- Right AOA sensor
- FMC
- Standby rudder PCU LVDT
- Trailing edge flap up limit switches.
The standby LVDT sends yaw damper actuator position data about rudder
movement to SMYD 2.
WTRIS only operates at Mach < 0.4.
The gain schedule changes from 1 (full gain) at Mach < 0.3 to zero gain at
Mach > 0.4.
For WTRIS and standby yaw damping, these are the limits for rudder commands:
S 2 degrees with flaps up
S 2.5 degrees with flaps not up.
BITE
The SMYD has BITE test and continuous BITE. It stores failures in fault history.
The keypad is for operator interface. The display shows test results and
prompts for input.
SMYD 2 receives inertial data from the ADIRU to calculate commands for
standby yaw damping and turn coordination.
These commands go to the yaw damper EHSV on the standby rudder PCU to
move the rudder.
The EHSV applies hydraulic pressure to the yaw damper actuator and the actuator makes a mechanical summing input to the rudder PCU to move the rudder to assist turns and to reduce unwanted yaw.
Nov. 2001
REFRESHER COURSE
FRA US/E NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 194
Lufthansa Technical Training
AUTO FLIGHT
YAW DAMPER SYSTEM
B737-600/700/800
22-23
28V AC
28V DC
POWER
28V DC
YAW DAMPER
ENGAGE SWITCH
R AOA SENSOR
L FLAP POS
TRANSMITTER
ANALOG
INPUTS
TE FLAP UP
LIMIT SWITCH
ANALOG
OUTPUT
CW SENSOR
STBY RUDDER
PCU EHSV
LVDT ON STBY
RUDDER PCU
SOFTWARE
CALCULATIONS
R ADIRU IR
CPU
R ADIRU ADR
WTRIS
YAW DAMPING
ARINC
429
INPUT
L ADIRU IR
FMC GW
ARINC
429
OUTPUT
For Training Purposes Only
SMYD 1
FAULT
HISTORY
KEYPAD
BITE
DISPLAY
SMYD 2
Nov. 2001
REFRESHER COURSE
STALL MGT
YAW DAMPER 1
CROSS CHANNEL
BUS
NOTE: ONLY INTERFACES FOR WTRIS AND STBY YAW
DAMPING ARE SHOWN ON THIS DIAGRAM.
Figure 93
FRA US/E NM
STBY RUDDER
PCU SOLENOID
VALVE
SMYD 2 - FUNCTIONAL DESCR.
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 195
Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
B737-600/700/800
27-24
SMYD 2 - WTRIS: BITE
General
The SMYD has these BITE functions:
S Continuous monitors
S BITE tests.
BITE tests on the front of the SMYD test items that the continuous monitor
cannot.
Continuous Monitor
Continuous monitors test the SMYD for proper operation.
When the SMYD has a failure a fault is put in fault history.
Some faults cause no SMYD outputs.
For Training Purposes Only
Display
The SMYD has two amber eight character alphanumeric displays.
These displays show messages and instructions while operating BITE.
Keypad
The keypad has these keys:
S MENU
S YES
S Up arrow (PREVIOUS)
S Down arrow (NEXT)
S ON/OFF
S NO.
You use these keys to interact with the SMYD while operating BITE.
Nov. 2001
REFRESHER COURSE
FRA USE NM
BITE Tests
BITE tests have these functions:
S A quick system test
S SMYD self test
S Component tests
S A series of tests to show all functions are within specifications
S Support fault isolation.
Six push—button switches and a two row 8 character display are on the front of
the SMYD for BITE tests.
BITE Operation
Push the ON/OFF switch to start BITE tests. Push the up arrow to see the previous menu item.
Push the Down arrow or NO key to see the next menu item.
Push the YES key to move down into the menu on the display.
Push the MENU key to move back up one level. In some lists, TOP OF LIST
and END OF LIST show for a second when you move to the top or bottom of
the list.
To operate BITE the airplane must have the flaps up and airspeed < 60 knots
or engine not running.
Engines not running means that the on—side engine N1 is less than 15% and
the off—side engine N1 is less than 50%.
Main Menu
These are the BITE main menu selections:
S EXISTING FAULTS
S FAULTS HISTORY
S GROUND TESTS
S OTHER FUNCTIONS.
You press the YES key to enter any of these menu selections.
See the yaw damper system section 22—23 for more information about the
SMYD BITE operation. (AMM PART 1, 22—23)
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 196
Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
B737-600/700/800
27-24
ON
STATIC
SENSITIVE
”BITE INSTRUCTIONS”
ON/OFF:START OR STOP BITE
MENU : TO DISPLAY MENU
YES/NO: IN RESPONSE TO
QUESTION (?)
:TO SCROLL THROUGH
OR
MENU OR RESULTS
OFF
1
INTO
EXISTING
FAULTS
YES
EXISTING
FAULTS?
NO
ON-SIDE ENG N1 < 15%
OFF-SIDE ENG N2 < 50%
MENU
YES
ON
INTO
FAULTS
HISTORY
OFF
XXXXXXXXXXXX
AIRSPEED < 60 KNOTS
YES
MOD
GROUND
TESTS?
SEE NEXT PAGES !!
NO
INTO
OTHER
FUNCTIONS
YES
OTHER
FUNCTNS?
NO
2
Figure 94
Nov. 2001
REFRESHER COURSE
FRA USE NM
FLAPS UP
NO
STALL MANAGEMENT
YAW DAMPER
P/N 65-52822-XX
S/N XXXXXXXXXXXX
XXXXXXXXXXX
BITE
ENABLE
FAULTS
HISTORY?
NO
INTO
GROUND
TESTS
For Training Purposes Only
YES
1
SHOWS TOP OF LIST FOR 1 SECOND
2
SHOWS END OF LIST FOR 1 SECOND
SMYD - BITE
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 197
Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
B737-600/700/800
27-24
WTRIS - SMYD BITE: GROUND TESTS
NOTE:
For WTRIS troubleshooting, the maintenance manual only suggests the
GROUND TEST and the SERVO TESTS of the SMYD 2.
THIS FOR TRAINING PURPOSES ONLY !!
REFER TO YOUR MM-PMA FOR TROUBLESHOOTING DETAILS !!
For Training Purposes Only
Ground Test
GROUND TEST has these menus:
S SELF TESTS?
S DISCRETE INPUTS?
S ARINC 429 INPUTS?
S ANALOG INPUTS?
S SERVO TEST?
S DISPLAY TEST?
To start one of these tests, do these steps:
S Go to the main menu
S Use the up or down arrow switches until you see GROUND TESTS? in the
BITE display
S Push the YES switch
S Use the up or down arrow switches until you see the test that you want
S Push the YES switch.
If the test passes, then the display shows TEST PASSED.
If the test fails, then the display shows a fault message.
The information for MORE DETAILS? is the same as for the existing faults test.
Servo Test
You use the SERVO TEST to test the yaw damper components on the rudder
PC, and to test the interface between the SMYD and the PCU.
You can test these components:
S Yaw damper EHSV
S Yaw damper engage solenoid
S Yaw damper LVDT
Nov. 2001
REFRESHER COURSE
FRA USE NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 198
B737-600/700/800
27-24
For Training Purposes Only
Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
Figure 95
Nov. 2001
REFRESHER COURSE
FRA USE NM
SMYD WTRIS BITE GROUND TESTS
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 199
Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
B737-600/700/800
27-24
WTRIS - SMYD BITE: SERVO TEST
General
The servo test consists of these two tests:
S ZERO COMMAND
S SWEEP TEST.
Zero Command
The standby rudder PCU is commanded to the zero position.
The signal from the LVDT is compared to the servo command.
For Training Purposes Only
Sweep Test
The standby rudder PCU is commanded to the left, right and center position.
The signal from the LVDT is compared to the servo command to pass or fail
the test.
If the test passes, the ZERO COMMAND menu shows after the TEST EXITING? display.
If the test fails, the faults are listed the same as for the existing faults test.
Nov. 2001
REFRESHER COURSE
FRA USE NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 200
B737-600/700/800
27-24
For Training Purposes Only
Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
Figure 96
Nov. 2001
REFRESHER COURSE
FRA USE NM
SMYD WTRIS SERVO TEST
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 201
B737-600/700/800
27-24
THIS PAGE INTENTIONALLY LEFT BLANK
For Training Purposes Only
Lufthansa Technical Training
FLIGHT CONTROLS
WHEEL TO RUDDER INTERCONNECT SYSTEM (WTRIS)
Nov. 2001
REFRESHER COURSE
FRA USE NM
FOR TRAINING PURPOSES ONLY
AMET Page:
Ltd. 202
Training Manual
B 737-600/700/800
ATA 35
Oxygen
Level 2
Lufthansa
Technical Training GmbH
Lufthansa Base
REFRESHER COURSE
FOR TRAINING PURPOSES ONLY
Issue: June 1999
For Training Purposes Only
 Lufthansa 1995
AMET Ltd.
For training purposes and internal use only.
Copyright by Lufthansa Technical Training GmbH.
All rights reserved. No parts of this training
manual may be sold or reproduced in any form
without permission of:
Lufthansa Technical Training GmbH
Lufthansa Base Frankfurt
D-60546 Frankfurt/Main
Tel. +49 69 / 696 41 78
Fax +49 69 / 696 63 84
Lufthansa Base Hamburg
Weg beim Jäger 193
D-22335 Hamburg
Tel. +49 40 / 5070 24 13
Fax +49 40 / 5070 47 46
REFRESHER COURSE
FOR TRAINING PURPOSES ONLY
AMET Ltd.
Inhaltsverzeichnis
ATA OXYGEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
35-00
OXYGEN SYSTEMS — INTRODUCTION . . . . . . . . . . . . . . .
2
35-10
FLIGHT CREW OXYGEN — GENERAL DESCRIPTION . .
INTERFACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
OXYGEN CYLINDER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
OXYGEN CYLINDER - FUNCTIONAL DESRIPTION . . .
DISCHARGE INDICATION DISK . . . . . . . . . . . . . . . . . . . .
THERMAL COMPENSATOR . . . . . . . . . . . . . . . . . . . . . . . .
PRESSURE TRANSDUCER . . . . . . . . . . . . . . . . . . . . . . . .
PRESSURE REDUCING REGULATOR . . . . . . . . . . . . . . .
SYSTEM SHUTOFF VALVE . . . . . . . . . . . . . . . . . . . . . . . . .
MASK WITH GOGGLES — GENERAL DESCRIPTION .
MASK WITH GOGGLES — FUNCTIONAL
DESCRIPTION AND OPERATION . . . . . . . . . . . . . . . . . . .
4
6
8
10
12
14
16
18
20
22
35-20
PASSENGER OXYGEN — INTRODUCTION . . . . . . . . . . . .
OXYGEN GENERATOR . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PASSENGER OXYGEN MASK . . . . . . . . . . . . . . . . . . . . . .
DOOR LATCH ACTUATOR . . . . . . . . . . . . . . . . . . . . . . . . .
DOOR LATCH ACTUATOR CIRCUIT . . . . . . . . . . . . . . . . .
DOOR TEST / RESET . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
26
28
30
32
34
38
35-30
PORTABLE OXYGEN EQUIPMENT — INTRODUCTION .
40
REFRESHER COURSE
24
FOR TRAINING PURPOSES ONLY
Seite: i
AMET Ltd.
Bildverzeichnis
Figure 1
Figure 2
Figure 3
Figure 4
Figure 5
Figure 6
Figure 7
Figure 8
Figure 9
Figure 10
Figure 11
Figure 12
Figure 13
Figure 14
Figure 15
Figure 16
Figure 17
Figure 18
Figure 19
Figure 20
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
General Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Interface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Crew Oxygen Cylinder - Location . . . . . . . . . . . . . . . . . . . . . . . . .
Oxygen Cylinder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Discharge Indication Disk . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Thermal Compensator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Pressure Transducer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Pressure Reducing Regulator . . . . . . . . . . . . . . . . . . . . . . . . . . . .
System Shutoff Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Mask with Goggles - General Description . . . . . . . . . . . . . . . . .
Mask with Goggles - Functional Description and Operation .
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Oxygen Generator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Passenger Oxygen Mask . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Door Latch Actuator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Door Latch Actuator Circuit . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Pressure Switch and Relays . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Door Test / Reset . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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AMET Ltd.
B737-600/700/800
35-00
ATA OXYGEN
For Training Purposes Only
Lufthansa Technical Training
OXYGEN SYSTEMS
INTRODUCTION
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AMET Ltd.
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OXYGEN SYSTEMS
INTRODUCTION
B737-600/700/800
35-00
35-00
OXYGEN SYSTEMS — INTRODUCTION
Purpose
The oxygen systems supply oxygen to the flight crew, cabin attendants, and
passengers. Oxygen can be used for these reasons:
- As life sustaining oxygen if the plane depressuri zes
- For emergencies
- For first aid.
For Training Purposes Only
General Description
The flight crew oxygen system is independent of the other systems. It is a high
pressure gaseous system. High pressure gaseous oxygen is stored in a cylinder in the EE compartment. A cylinder regulator reduces the cylinder pressure
before the oxygen enters the supply line. An oxygen supply line connects the
regulator to a shutoff valve on the P6 panel. The shutoff valve outputs to a supply manifold in the flight deck. The manifold supplies oxygen to the flight crew
oxygen masks.
The passenger oxygen system uses chemical oxygen generators. The generators are mounted in the passenger service units (PSUs). Each chemical generator is separate, and supplies only its masks. The passenger masks are connected to the chemical generators by flexible tubes.
There are two portable oxygen systems:
- Portable oxygen cylinders with masks
- Protective breathing equipment (PBE) (when installed).
Location
The flight crew oxygen system components are located in flight compartment
and the EE compartment.
The passenger system components are located in the passenger service units
(PSUs), the attendant service panels, and the lavatory service panels.
Portable system components are located in the flight compartment and passenger cabin.
Abbreviations and Acronyms
EE
— electronic equipment
PBE
— protective breathing equipment
PSU
—passenger service unit
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AMET Ltd.
B737-600/700/800
35-00
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OXYGEN SYSTEMS
INTRODUCTION
Figure 1
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Introduction
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Page: 3
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
B737-600/700/800
35-10
35-10
FLIGHT CREW OXYGEN — GENERAL DESCRIPTION
Purpose
The flight crew oxygen system supplies the flight crew with low pressure gaseous oxygen.
For Training Purposes Only
General Description
High pressure gaseous oxygen is stored in a cylinder. A gauge on the cylinder
shows cylinder pressure.
Overpressure devices protect the cylinder. A green plastic discharge indication
disk on the fuselage skin shows cylinder discharge from overpressure (when
disk is missing).
A temperature compensating coupling connects the cylinder to the aircraft’s
distribution system.
A pressure transducer on the cylinder coupling sends a signal to a gage on the
P5 panel for cylinder pressure indication.
A pressure regulator on the coupling reduces the oxygen pressure. This keeps
oxygen in the distribution system to a lower pressure.
Low pressure supply lines supply oxygen to a shutoff valve in the flight deck.
The shutoff valve controls the flow of oxygen to the mask assemblies in the
flight deck. The oxygen supply lines are made of seamless stainless steel tubing and use flareless fittings.
The flight crew masks supply the oxygen to the crew.
The masks have diluter—demand regulators and controls.
The masks are modular, independently adjustable, and easy to put on.
When cylinder pressure is too low for operational requirements, you replace it.
These components are in the flight compartment:
- P6 panel oxygen shutoff valve
- Crew mask modules
- P5 crew oxygen cylinder pressure gage.
The green cylinder overpressure discharge disk is on the fuselage skin aft of
the electronic equipment compartment external access door.
Training Information Point
Oxygen system maintenance requires special care and clean liness. Oxygen
system maintenance personnel should know the special materials and procedures used in system servicing. Refer to chapter 12 of the maintenance manual for these materials and procedures.
Keep oxygen systems clean and dry. Use approved cleaning materials.
NOTE:
Use only aviation grade oxygen in the flight crew oxygen system.
Welding oxygen and hospital oxygen can be pure enough to
breathe but contain water. The water can freeze and plug the lines,
regulators, and valves of the system.
NOTE:
Oil, grease, flammable solvents, dust, lint, fine metal filings, or
other combustible materials may ignite and result in an explosion.
Contamination inside the system can cause noxious or toxic reactions. This can render the system inoperative for its intended use.
NOTE:
Do not tighten fittings on a pressurized oxygen system. An explosion may result.
Location
These system components are in the EE compartment:
- A high pressure oxygen cylinder
- A temperature compensator cylinder coupling
- A pressure reducing regulator
- A pressure transmitter
- Overpressure discharge tubing.
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AMET Ltd.
B737-600/700/800
35-10
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
Figure 2
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General Description
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
B737-600/700/800
35-10
INTERFACE
Purpose
The schematic below shows the interfaces of the flight crew oxygen system.
The flight crew oxygen system has these interfaces:
- System supply tubing
- Shutoff valves
- Pressure indication
- Overpressure discharge and indication
- Flight crew communications systems.
sed. If the cylinder shutoff valve is open, oxygen from the cylinder and the system supply tubing flows overboard.
Flight Crew Communications Systems
The flight crew oxygen masks have internal microphones. These microphones
are part of the communications system. Refer to chapter 23 of the AMM for
microphone information.
System Plumbing
The system plumbing has these components:
- Corrosion resistant, seamless stainless steel tubing
- Flareless fittings
- Bayonet type quick disconnect connectors
- Flexible silicon rubber hoses with braided sheathing.
For Training Purposes Only
Shutoff Valves
A shutoff valve on the cylinder head opens or closes the cylinder to the supply
system.
A system shutoff valve on the P6 panel controls the flow of low pressure oxygen to the crew masks.
Pressure Indication
A mechanical pressure gage on the oxygen cylinder indicates the cylinder pressure. The gage shows pressure regardless of the cylinder shutoff valve position.
An electrically powered gage on the P5 panel shows the pressure at the cylinder outlet coupling. A pressure transducer on the cylinder coupling supplies a
signal to the gage. The system uses 28 V D.C. from the battery bus.
Overpressure Discharge and Indication
A frangible (breakable) disk on the oxygen cylinder protects the cylinder from
overpressure. If an overpressure condition breaks this disk, the oxygen will flow
overboard. This flow will blow out a green indication disk on the airplane fuselage. The cylinder discharge works with the cylinder shutoff valve open or clo24 Jun 99
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AMET Ltd.
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35-10
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
Figure 3
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Interface
FOR TRAINING PURPOSES ONLY
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AMET Ltd.
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
B737-600/700/800
35-10
OXYGEN CYLINDER
Purpose
The oxygen cylinder stores the oxygen for the flight crew system.
Physical Description
The oxygen cylinder is made of steel and is painted green.
The cylinder assembly has these features:
- A slow opening shutoff valve
- A cylinder pressure gage
- An overpressure safety relief device.
For Training Purposes Only
Location
The crew oxygen cylinder is located in the EE compartment, in the lower right
area of the transverse rack.
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AMET Ltd.
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35-10
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
Figure 4
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Crew Oxygen Cylinder - Location
FOR TRAINING PURPOSES ONLY
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AMET Ltd.
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
B737-600/700/800
35-10
OXYGEN CYLINDER - FUNCTIONAL DESRIPTION
Functional Description
The crew oxygen cylinder is a pressure vessel. It is made of shatterproof mild
steel. A frangible disk in the cylinder assembly protects the bottle from overpressure.
A mechanical pressure gage on the bottle shows bottle pressure. The bottle is
filled to 1850 psig at a temperature of 70F.
The cylinder has a slow opening shutoff valve. The valve is designed to prevent
high temperatures when the valve is operated.
The cylinder is installed on a roller rack. Two collars hold the cylinder to the
rack.
Flareless pressure fittings connect the cylinder to these components:
- The cylinder thermal compensator coupling
- The overpressure discharge tubing.
For Training Purposes Only
Training Information Point
Servicing the oxygen cylinder is by cylinder replacement. Access to the cylinder
is from the forward cargo compartment. Refer to Chapter 12 of the AMM for
complete servicing instructions. Clinder sizes vary. Make sure you use the
same size cylinder for replacement. The cylinder must fit its support rack.
Keep oxygen cylinder and components clean and free from any grease, oil, or
other contamination. Use only approved cleaning, installation, and test materials.
Bleed pressure out of the supply lines at the crew masks before uncoupling
bottle connections. Do not torque line fittings when they are pressurized.
Do not overtorque the cylinder shutoff valve or cylinder coupling fittings.
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AMET Ltd.
B737-600/700/800
35-10
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
Figure 5
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Oxygen Cylinder
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AMET Ltd.
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
B737-600/700/800
35-10
DISCHARGE INDICATION DISK
Purpose
The discharge indication disk, when missing, shows the oxygen cylinder has
discharged due to over pressure.
Physical Description
The discharge indication disk is a green plastic disk. It is backed—up by an
o—ring, and held in place by a snap—ring.
Location
The discharge indication disk is flush—mounted to the fuselage skin, just aft of
the electronic equipment compartment external access door.
Functional Description
A frangible disk in the crew oxygen cylinder protects the cylinder from overpressure. If cylinder pressure reaches 2600 psig the frangible disk breaks. This
vents the bottle contents overboard through a high pressure line. The line outlet
is covered by the discharge indication disk. The escaping oxygen blows the
disk out of its seat.
A missing disk indicates bottle overpressure discharge.
For Training Purposes Only
Operation Displays
Preflight visual checks will confirm the green flight crew oxygen discharge indication disk is in place.
Training Information Point
The o—ring behind the discharge indication disk makes a seal for the discharge tubing. The seal prevents contamination or moisture accumulation in
the discharge line.
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AMET Ltd.
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35-10
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
Figure 6
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Discharge Indication Disk
FOR TRAINING PURPOSES ONLY
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AMET Ltd.
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
B737-600/700/800
35-10
THERMAL COMPENSATOR
Purpose
The thermal compensator prevents excessive temperature buildup in the cylinder coupling.
Physical Description
The thermal compensator is a brush—like device, about three inches long.
Location
The thermal compensator is a permanent part of the oxygen cylinder coupling
fitting.
For Training Purposes Only
Functional Description
The thermal compensator is a heat sink and heat dissipater. High pressure
oxygen flow in the cylinder coupling creates heat. The compensator absorbs
and removes this heat.
Training Information Point
The thermal compensator is an integral part of the coupling fitting. It should not
be removed from the fitting. Do not twist, pull, or push the thermal compensator
while you fill the oxygen cylinder. Bristles broken off of the compensator can
cause downstream components to clog.
Bleed the pressure from the temperature compensator coupling before you torque the fittings.
Do not use the temperature compensator coupling as a lever when you torque
the coupling fittings. Use the wrenching flats on the coupling so that it cannot
turn.
Replace the coupling fitting and the thermal compensator as a single unit.
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AMET Ltd.
B737-600/700/800
35-10
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
Figure 7
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REFRESHER COURSE
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Thermal Compensator
FOR TRAINING PURPOSES ONLY
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AMET Ltd.
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
B737-600/700/800
35-10
PRESSURE TRANSDUCER
Purpose
The pressure transducer supplies a bottle pressure signal to the flight crew
oxygen pressure indicator.
Physical Description
The pressure transducer is a small cylindrical device. It has a threaded fitting
and an electrical connector for its output signal.
Location
The pressure transducer attaches to the temperature compensating coupling
by a threaded fitting.
Functional Description
The pressure transducer is a solid state electronic device. It uses a piezoelectric crystal to convert the force of the gas pressure to an electrical signal. This
output signal goes to the flight crew oxygen pressure indicator.
For Training Purposes Only
Operational Displays
The output voltage of the pressure transducer goes to the flight crew oxygen
pressure indicator.
The indicator has internal lights and gets power from 28v dc from the battery
bus. The indicator reads from 0-2000 psi.
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AMET Ltd.
B737-600/700/800
35-10
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
Figure 8
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REFRESHER COURSE
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Pressure Transducer
FOR TRAINING PURPOSES ONLY
Page: 17
AMET Ltd.
Lufthansa Technical Training
FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
B737-600/700/800
35-10
PRESSURE REDUCING REGULATOR
Purpose
The pressure reducing regulator reduces the oxygen pressure before it goes
into the low pressure supply line. It protects the downstream components from
high pressure.
Location
The pressure reducing regulator attaches to the thermal compensator coupling
on the oxygen cylinder.
For Training Purposes Only
Functional Description
These components supply force on a diaphragm in the pressure reducing regulator:
- Spring pressure
- Ambient pressure
- Oxygen cylinder pressure.
The diaphragm controls a metering valve that reduces the oxygen pressure
from bottle pressure to 60 — 85 psig.
The regulator has a fail safe relief valve. This relief valve opens when downstream line pressure is more than 100 psig. The relief valve bleeds into the EE
compartment.
The inlet of the pressure reducing regulator has a filter. The filter does not require servicing.
Training Information Point
There are no line adjustments for the pressure reducing regulator. Remove the
valve and send it to overhaul for adjustment.
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AMET Ltd.
B737-600/700/800
35-10
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
Figure 9
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REFRESHER COURSE
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Pressure Reducing Regulator
FOR TRAINING PURPOSES ONLY
Page: 19
AMET Ltd.
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
B737-600/700/800
35-10
SYSTEM SHUTOFF VALVE
Purpose
The crew oxygen system shutoff valve controls the flow of oxygen to the masks
in the flight deck. The valve is open during flight operations. It can be closed for
maintenance operations.
Physical Description
The system shutoff valve is installed on the P6 panel. A round, knurled knob
controls the valve.
The valve has two threaded fittings to attach it to the oxygen supply line. An
arrow cast into the valve body shows the direction of flow. The valve has a
flange with holes for four mounting screws.
Location
The system shutoff valve is on the outboard middle area of the P6 panel.
Functional Description
The system shutoff valve is a needle valve. It shuts off oxygen flow in the closed position. It allows partial flow in the partially open position. The valve allows full flow when fully opened. The valve should be positioned either fully
open or fully closed.
For Training Purposes Only
Operational Controls
Turn the valve knob clockwise (facing the valve) to close the valve.
Turn the valve knob counterclockwise (facing the valve) to open the valve.
Training Information Point
Do not overtorque the crew oxygen system shutoff valve. Torque to finger tight
only (25 pound—inches maximum).
Do not use oil on any part of the valve. Oil is combustible. Even small quantities of oil, in contact with oxygen can cause a fire or explosion.
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AMET Ltd.
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35-10
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
Figure 10
24 Jun 99
REFRESHER COURSE
FRA US/E br
System Shutoff Valve
FOR TRAINING PURPOSES ONLY
Page: 21
AMET Ltd.
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
B737-600/700/800
35-00
MASK WITH GOGGLES — GENERAL DESCRIPTION
Purpose
The flight crew oxygen masks supply each crew member with an independently
adjustable source of oxygen.
Physical Description
The flight crew oxygen masks are identical modular units. The masks have
these components:
- A hard—shell oronasal (mouth and nose) cup
- Goggles
- An inflatable harness
- An armored flexible oxygen supply hose with a bayonet connection
- A microphone lead with a radio jack connection.
The pilot oxygen masks are in stowage boxes. The boxes have these features:
- An automatic shutoff valve
- An oxygen flow indicator (yellow cross)
- A RESET/TEST selector.
The observer oxygen masks are in stowage cups. The stowage cups do not
have the features of the stowage boxes.
Operational Displays
Flow indicators on the stowage boxes show oxygen flow to the masks. A yellow
cross shows oxygen flow.
A white OXY ON flag on the box door shows when the stowage box shutoff
valve is open.
For Training Purposes Only
Location
The flight crew oxygen masks are outboard of the crew member seats.
Operational Controls
The flight crew oxygen masks have these control features:
- Dilution or 100% oxygen
- Demand or constant flow oxygen
- Goggle vents for smoke clearance
- Mask harness inflation.
The mask stowage boxes have these control features:
- Box shutoff valve tests
- Box resets for mask stowage.
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AMET Ltd.
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
Figure 11
24 Jun 99
REFRESHER COURSE
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Mask with Goggles - General Description
FOR TRAINING PURPOSES ONLY
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AMET Ltd.
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
B737-600/700/800
35-10
MASK WITH GOGGLES — FUNCTIONAL DESCRIPTION AND OPERATION
Functional Description and Operation
To remove the masks from their stowage modules, grasp and pull on the red
donning/inflation plates (ears). The elastic mask harness inflates when you
push the left plate in. You can put on the mask with one hand. The harness
deflates when the plates are released. The deflated harness holds the mask
securely on the user’s face.
As you pull the mask from the stowage box, the box shutoff valve opens, and
the white OXY ON flag comes into view. The flight crew oxygen mask now supplies oxygen to the user.
The crew oxygen masks are diluter/demand masks. Controls on each mask
determine the mode of oxygen de livery.
In the demand mode, a mask regulator supplies oxygen to the crew member
only when the crew member inhales. To select continuous flow mode, move the
EMERGENCY/TEST selector to EMERGENCY.
In the diluter mode, ambient cabin air mixes with oxygen. An aneroid metering
valve in the mask controls this function. The mix of air and oxygen is proportional to the cabin pressure altitude. To select pure oxygen, push the red normal/100% selector to the 100% position.
The mask goggles have vent valves for smoke clearance. The vent valves
clear smoke from the goggles when the user exhales.
The pilot masks stow in special panel mounted boxes. The boxes have these
features:
- A shutoff valve
- A RESET/TEST selector (red)
- An OXY—ON flag (white)
- An oxygen flow indicator (yellow cross).
The box shutoff valve is closed when the mask is stowed. It opens when you
remove the mask.
The OXY—ON flag is in view when the shutoff valve is open.
The flow indicator is a visual indication of oxygen flow to the mask.
You use the RESET/TEST selector to do a test of the system and reset the
shutoff valve when the mask is stowed.
The observer mask stowage cups do not have the box features.
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AMET Ltd.
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FLIGHT CREW OXYGEN
GENERAL DESCRIPTION
Figure 12
24 Jun 99
REFRESHER COURSE
FRA US/E br
Mask with Goggles - Functional Description and Operation
FOR TRAINING PURPOSES ONLY
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AMET Ltd.
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PASSENGER OXYGEN
GENERAL DESCRIPTION
B737-600/700/800
35-20
35-20
PASSENGER OXYGEN — INTRODUCTION
Purpose
The passenger oxygen system supplies emergency oxygen to the passengers
and cabin attendants.
For Training Purposes Only
General Description
The passenger oxygen system uses chemical generators to make oxygen.
Oxygen from the generators flows through flexible supply hoses to the passenger oxygen masks.
Passenger oxygen masks are deployed electrically one of two ways:
- Manually by the crew using a guarded toggle switch on the aft P5 panel
- Automatically by activation of an aneroid switch (cabin altitude 14000 ft.).
Passenger oxygen generation is initiated mechanically when the oxygen mask
is pulled to the user s face. Pulling the mask releases a spring loaded firing pin
on the generator. The firing pin strikes a percussion cap, which starts the reaction. Once started, the reaction goes to completion, and cannot be stopped.
Operational Displays
The PASS OXY ON light on the P5 panel comes on when the passenger oxygen masks are deployed.
The chemical oxygen generators have a band of heat sensitive tape around
them. The tape turns black when heated. A chemical oxygen generator with
black tape is expended and must be replaced.
WARNING: THE OXYGEN GENERATOR IS A PYROTECHNIC— ACTIVATED
DEVICE. MAKE SURE THE RELEASE PIN OR A SAFETY PIN IS
SECURED BEFORE HANDLING AN UNFIRED GENERATOR. IF
THE GENERATOR FIRES, THE SURFACE TEMPERATURE CAN
BE MORE THAN 450F (232C) AND CAUSE INJURY TO PERSONS.
Location
Passenger oxygen generators, masks, firing pin mechanisms, and deployment
door latch actuators are located in:
- The passenger service units (PSUs)
- The lavatory service units
- The attendant service units.
A guarded toggle switch for manual deployment of the passenger oxygen
masks is located on the aft P5 panel.
An aneroid switch for automatic deployment, and system electrical relays are
located in the EE compartment in the J23 junction box.
A PASS OXY ON light on the P5 panel indicates deployment of the passenger
oxygen masks.
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PASSENGER OXYGEN
GENERAL DESCRIPTION
Figure 13
24 Jun 99
REFRESHER COURSE
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Introduction
FOR TRAINING PURPOSES ONLY
Page: 27
AMET Ltd.
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PASSENGER OXYGEN
INTRODUCTION
B737-600/700/800
35-20
OXYGEN GENERATOR
Purpose
The oxygen generators supply emergency oxygen to the passengers and flight
attendants.
Physical Description
The oxygen generators are metal cased cylindrical devices. At one end of the
generator is a spring loaded firing mechanism. At the other end is an output
manifold and a relief valve. The oxygen generator output manifolds have 4,3, or
2 ports. The size of the generator determines the number of output manifold
ports.
For Training Purposes Only
Location
The oxygen generators are located in:
- The passenger service units (PSUs)
- The lavatory service units
- The attendant service units.
Operational Displays
A heat sensitive indicator on the generator shows the generator condition. The
indicator is a piece of tape, a painted stripe, or a band of dots around the generator. The indicator is normally orange. The heat generated during activation
changes the indicator to black.
A used generator cannot be recharged. Replace generators if their indicator is
black.
Training Information Point
Safety pin the oxygen generators to prevent accidental firing during maintenance activities. The firing pins are cross—drilled to accept a safety pin. Special safety pin pliers can be used to pull the firing pin back to expose the safety
pin hole. The safety pin should have a ribbon to prevent a safety pinned generator from being put into service.
Functional Description
The oxygen generators make oxygen by a chemical reaction. In the reaction,
sodium chlorate and iron react to generate salt and gaseous oxygen. Once the
reaction starts, it cannot be stopped. The reaction continues until all the sodium
chlorate is used. The reaction produces heat and generator surface temperatures can reach 450F.
The gaseous oxygen passes through a filtering medium and then flows out of
the output manifold. The output manifold ports are connected to the passenger
oxygen masks by flexible tubing.
A pressure relief valve prevents over pressurization of the generator.
Operational Controls
The oxygen generator is activated mechanically. When a passenger pulls on an
oxygen mask, a mask lanyard pulls on the firing pin release cable. The release
cable pulls the release pin from the spring loaded firing pin. The firing pin then
strikes the percussion cap.
The percussion cap supplies the energy required to activate the generator.
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PASSENGER OXYGEN
INTRODUCTION
Figure 14
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Oxygen Generator
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PASSENGER OXYGEN
INTRODUCTION
B737-600/700/800
35-20
PASSENGER OXYGEN MASK
Purpose
The passenger oxygen masks supply breathing oxygen to aircraft passengers
and flight attendants during emergency decompression of the aircraft.
Physical Description
The passenger oxygen masks have the following parts:
- A bright yellow silicon rubber facepiece with breathing valves, elastic
headstrap, and generator release lanyard
- Flexible supply tubing and reservoir bag.
For Training Purposes Only
Location
The passenger oxygen masks are located in the passenger service units
(PSUs), the flight attendant service units, and the lavatory service units. An
extra mask is in each station for an infant.
Operational Displays
Instructions for mask use are diagrammed on the reservoir bag.
In some models the reservoir bag has a built—in flow indicator which inflates
when oxygen flows into the bag. The indicator area is shaded green for easy
recognition. Other configurations include an in—line flow indicator which changes color to green in the presence of oxygen.
Training Information Point
The length of the oxygen tube differs between the various bag and tube assemblies. Be sure to use the right length.
When repitching PSUs for class configuration changes, make sure the gasper
hose brackets near the PSUs do not interfere with the passenger oxygen supply tubing. If improperly spaced, the brackets can pinch or cut the supply tubing
when the PSU is closed.
Functional Description
When stowed, the masks are packed in the service unit.
When deployed, the masks hang by a mask lanyard. When the mask is pulled
to the user’s face, the mask lanyard pulls on the oxygen generator firing pin
release cable. This starts the oxygen generator.
Oxygen from the generator manifold flows through the mask tubing to the reservoir bag. The reservoir bag stores oxygen from the constant outflow of the
generator when the user is not inhaling.
During inhalation, the oxygen flows through the reservoir bag and the mask
inhalation valve. When the oxygen in the bag is used, the mask ambient air
valve opens to allow ambient air to enter the facepiece.
When the user exhales, the inhalation and ambient air valves close, and the
exhalation valve opens. The exhalation valve lets the used air flow out of the
mask.
Operational Controls
The user places the yellow facepiece over the mouth and nose. The soft silicon
rubber of the mask contours to the facial features to give a good seal. The
mask can be held in place by hand or by pulling the mask’s elastic headstrap
over the user1s head. The headstrap can be adjusted by pulling on either of its
ends.
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B737-600/700/800
35-20
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PASSENGER OXYGEN
INTRODUCTION
Figure 15
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Passenger Oxygen Mask
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PASSENGER OXYGEN
INTRODUCTION
B737-600/700/800
35-20
DOOR LATCH ACTUATOR
Purpose
The door latch actuators open the oxygen mask door panels in the passenger
service units (PSUs), attendant service units, and lavatory service units. When
the oxygen door panel is open, the masks fall out of their stowed position and
hang in front of the user.
Physical Description
The door latch actuators have:
- A solenoid
- A spring loaded latch actuator
- A latch actuator lever
- A spring loaded door latch.
For Training Purposes Only
Location
The door latch actuators are part of the upper assemblies in:
- The PSUs
- The attendant service units
- The lavatory service units.
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35-20
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PASSENGER OXYGEN
INTRODUCTION
Figure 16
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Door Latch Actuator
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PASSENGER OXYGEN
INTRODUCTION
B737-600/700/800
35-20
DOOR LATCH ACTUATOR CIRCUIT
Location
These components are in the J23 junction box in the EE compartment:
- R323 passenger oxygen manual deployment relay
- R322 passenger oxygen auto deployment relay
- R324 passenger oxygen indicator relay
- S813 14,000 ft. altitude pressure switch.
The PASS OXYGEN switch and PASS OXY ON light are on the aft P5 panel.
The passenger oxygen door latch actuators are located in:
- The passenger service units (PSUs)
- The lavatory service units
- The flight attendant service units.
Operational Displays
The oxygen indicator relay is energized through the energized contacts of either of the two oxygen deployment relays. The energized contacts of the oxygen indicator relay cause:
- The P5 PASS OXY ON light to come on
- A relay holding circuit to be made.
The holding circuit keeps the indication relay energized until power is removed
from the 28 volts D.C. battery bus.
For Training Purposes Only
Functional Description
The oxygen mask door panels are held closed by a spring loaded door latch.
The passenger oxygen masks are deployed electrically. The signal is 28 volts
D.C. The voltage energizes the door latch actuator solenoid. The energized
solenoid releases a spring loaded latch actuator. The actuator pushes the oxygen mask door open.
Operational Controls
The door latch actuators receive power through the energized contacts of either of two oxygen deployment re lays:
- R323 manual oxygen deploy relay
- R322 auto oxygen deploy relay.
The deployment relays are energized by either:
- Placing the P5 PASS OXYGEN switch to ON
- Actuation of the 14,000 ft. altitude pressure switch.
The deployment relays have timers and remain energized for only 5 seconds.
This is enough time to ensure mask deployment and conserves the airplane1s
battery power.
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PASSENGER OXYGEN
INTRODUCTION
Figure 17
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Door Latch Actuator Circuit
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PASSENGER OXYGEN
INTRODUCTION
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PASSENGER OXYGEN
INTRODUCTION
B737-600/700/800
35-20
PASSENGER OXYGEN
SYSTEM RELAYS
For Training Purposes Only
EE COMPT
ACCESS DOOR
ALTITUDE
PRESSURE
SWITCH
J23 BOX
EE COMPARTMENT
(LOOKING AFT)
FWD
Figure 18
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EE COMPT
ACCESS DOOR
Pressure Switch and Relays
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PASSENGER OXYGEN
INTRODUCTION
B737-600/700/800
35-20
DOOR TEST / RESET
Purpose
The passenger oxygen mask deployment doors have test/reset buttons. These
buttons are used:
- To make door deployment tests easier
- To reset the door latch actuator.
Physical Description
The test/reset button is a rectangular piece on the passenger oxygen mask
door.
For Training Purposes Only
Functional Description
In the normal position, the stop is faired with the door panel. In the normal position, the stop will allow the door to fully open when the latch actuator is energi
zed.
In the test position, the stop is pulled out of and turned crosswise to its recess
in the door panel. In this position it will block the doors from opening far enough
to drop the masks. This position is used when testing the mask deployment
system.
To reset the door latch actuator:
- Hold the oxygen mask door panel closed
- Align the test/reset button to the normal position
- Push on the test stop and reset button.
An audible click is heard when the spring loaded latch actuator resets.
Training Information Point
The PSU oxygen door panels can be opened manually. This is done by inserting a 0.125 in (3.0 mm) pin punch into the door panel release hole. Then press
upward against the latch release to open the door.
The attendant service oxygen panel doors and lavatory service oxygen panel
doors can be opened manually. This is done by inserting a flat tool (6.0 in. pokket scale) in the door edge gap. Then press upward against the latch release to
open the door.
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PASSENGER OXYGEN
INTRODUCTION
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Door Test / Reset
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PASSENGER OXYGEN
INTRODUCTION
B737-600/700/800
35-30
35-30
PORTABLE OXYGEN EQUIPMENT — INTRODUCTION
Purpose
Portable oxygen cylinders are used for walk around First Aid and sustaining
purposes.
Protective breathing equipment (PBE) supplies a crew member with a smoke
hood and an air system for protection against smoke or toxic fumes. The PBEs
protect the user during fire fighting operations.
General Description
Each portable oxygen cylinder is a separate system. The cylinder stores a supply of oxygen under high pressure (1800 psig at 70F). A gage on the cylinder
shows cylinder pressure (and thereby the quantity of oxygen available). A shutoff valve on the cylinder head controls the flow of the high pressure oxygen to
the cylinder head assembly. Cylinder head components regulate oxygen pressure and flow to the attached mask(s).
The portable oxygen cylinders have these features:
- Identifying and instructional placards
- A high pressure cylinder
- A cylinder pressure gage
- A shutoff valve
- A cylinder head assembly
- A mask
- A carrying strap.
Each PBE is a separate system. The PBEs have these features:
- A vacuum sealed storage container with identifying and instructional placards
- A loose fitting universal sized smoke hood with oronasal mask and breathing air system.
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Location
The portable oxygen equipment is installed at easily reached locations throughout the airplane:
- On the exterior walls of windscreens, lavatories, and galleys
- In placarded overhead stowage bins
- In placarded storage units.
Interface
The portable oxygen equipment is independent (separate) of the other aircraft
systems.
Standard outlet fittings (bayonet type) are used on the portable oxygen cylinders.
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PASSENGER OXYGEN
INTRODUCTION
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ATA 24-00-00
ELECTRICAL POWER
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CONTENTS
ATA 24 – ELECTRICAL POWER
ELECTRICAL POWER - POWER AND CONTROL - ..................................................................................................................................................................................... 6
GENERAL DESCRIPTION ................................................................................................................................................................................................................................. 6
PURPOSE ................................................................................................................................................................................................................................................................ 6
AC POWER ............................................................................................................................................................................................................................................................. 6
STANDBY POWER ................................................................................................................................................................................................................................................... 6
PROTECTION AND CONTROL .................................................................................................................................................................................................................................. 6
ELECTRICAL POWER - OPERATION ............................................................................................................................................................................................................. 8
GENERAL DESCRIPTION ................................................................................................................................................................................................................................. 8
AC SYSTEMS, GENERATOR AND APU MODULE (P5-4) ...................................................................................................................................................................................... 10
FORWARD FLIGHT ATTENDANT’S PANEL ............................................................................................................................................................................................................ 10
EXTERNAL POWER - GENERAL DESCRIPTION ....................................................................................................................................................................................... 12
PURPOSE .............................................................................................................................................................................................................................................................. 12
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 12
BUS POWER CONTROL UNIT (BPCU) .................................................................................................................................................................................................................. 12
MANUAL CONTROL ............................................................................................................................................................................................................................................. 12
AUTOMATIC CONTROL (SYSTEM PROTECTION) ................................................................................................................................................................................................... 12
INDICATION.......................................................................................................................................................................................................................................................... 12
INDICATION.......................................................................................................................................................................................................................................................... 14
INTERFACES ......................................................................................................................................................................................................................................................... 14
GENERATOR DRIVE - COMPONENT LOCATION ..................................................................................................................................................................................... 16
GENERAL ............................................................................................................................................................................................................................................................. 16
INTEGRATED DRIVE GENERATOR (IDG) .............................................................................................................................................................................................................. 16
IDG AIR/OIL COOLER ......................................................................................................................................................................................................................................... 16
GENERATOR DRIVE AND STANDBY POWER MODULE ......................................................................................................................................................................................... 16
GENERATOR DRIVE - INTEGRATED DRIVE GENERATOR .................................................................................................................................................................. 18
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PURPOSE .............................................................................................................................................................................................................................................................. 18
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 18
PUSH-TO-VENT VALVE ....................................................................................................................................................................................................................................... 18
CASE PRESSURE RELIEF VALVE .......................................................................................................................................................................................................................... 18
DISCONNECT RESET RING.................................................................................................................................................................................................................................... 18
CHARGE OIL FILTER ............................................................................................................................................................................................................................................ 18
SCAVENGE OIL FILTER ........................................................................................................................................................................................................................................ 18
DIFFERENTIAL PRESSURE INDICATOR .................................................................................................................................................................................................................. 18
OIL LEVEL SIGHTGLASS....................................................................................................................................................................................................................................... 18
DRAIN PLUG ........................................................................................................................................................................................................................................................ 18
PRESSURE FILL ADAPTER .................................................................................................................................................................................................................................... 18
GENERATOR DRIVE – SERVICING ............................................................................................................................................................................................................... 20
CHARGE AND SCAVENGE OIL FILTERS ................................................................................................................................................................................................................ 20
OIL SERVICING .................................................................................................................................................................................................................................................... 20
OIL QUANTITY CHECK ......................................................................................................................................................................................................................................... 20
DRAIN PLUG ........................................................................................................................................................................................................................................................ 20
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 20
AC GENERATION - APU STARTER GENERATOR ..................................................................................................................................................................................... 22
PURPOSE .............................................................................................................................................................................................................................................................. 22
LOCATION ............................................................................................................................................................................................................................................................ 22
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 22
AC GENERATION - START CONVERTER UNIT (SCU) ............................................................................................................................................................................. 24
PURPOSE .............................................................................................................................................................................................................................................................. 24
LOCATION ............................................................................................................................................................................................................................................................ 24
GENERAL ............................................................................................................................................................................................................................................................. 24
AC GENERATION - POWER DISTRIBUTION PANELS ............................................................................................................................................................................. 26
GENERAL ............................................................................................................................................................................................................................................................. 26
LOCATION ............................................................................................................................................................................................................................................................ 26
POWER DISTRIBUTION PANEL 1 ........................................................................................................................................................................................................................... 26
POWER DISTRIBUTION PANEL 2 ........................................................................................................................................................................................................................... 26
DC GENERATION ............................................................................................................................................................................................................................................... 28
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DISTRIBUTION AND CONTROL ..................................................................................................................................................................................................................... 28
DC GENERATION SYSTEM - MAIN BATTERY AND AUXILIARY BATTERY ..................................................................................................................................... 30
PURPOSE .............................................................................................................................................................................................................................................................. 30
LOCATION ............................................................................................................................................................................................................................................................ 30
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 30
STANDBY POWER SYSTEM - STANDBY POWER CONTROL UNIT (SPCU) ....................................................................................................................................... 32
PURPOSE .............................................................................................................................................................................................................................................................. 32
LOCATION ............................................................................................................................................................................................................................................................ 32
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 32
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ELECTRICAL POWER - POWER AND CONTROL -
Standby Power
GENERAL DESCRIPTION
With the loss of normal power, the standby power system supplies a
minimum of 60 minutes of AC and DC power to systems necessary to
maintain safe flight.
The batteries supply DC power. The static inverter uses battery power to
make AC power. The SPCU controls the distribution of AC and DC
standby power.
Purpose
The electrical power system makes and supplies AC and DC power to the
airplane. The system has automatic and manual controls and protection. A
standby AC and DC system gives normal and emergency power.
AC Power
Protection and Control
The electrical power system has four main AC power sources and one
standby power source.
These are the main AC power sources and their supply capacity:
The electrical power system uses automatic control to protect the system
from source failure or load failure.
These Line Replaceable Units (LRUs) supply the system with protection
and control logic:
- Left Integrated Drive Generator (IDG 1) (90 KVA)
- Right Integrated Drive Generator (IDG 2) (90 KVA)
- APU starter-generator (90 KVA below 32,000 feet/9,753 meters, and
goes down to 66 KVA at 41,000 feet/12,496 meters)
- External power (90 KVA)
- Left Generator Control Unit (GCU 1)
- Right Generator Control Unit (GCU 2)
- APU Generator Control Unit (AGCU)
- Bus Power Control Unit (BPCU)
- Standby Power Control Unit (SPCU)
- Start Converter Unit (SCU)
The IDGs and APU starter-generator supply a 3 phase, 115 volts
(nominal) at 400 Hz. The AC power system design prevents two sources
to the same load at the same time.
The static inverter supplies a one phase, 115vac output to the AC standby
bus. DC Power
Three Transformer Rectifier Units (TRUs) change 115vac to 28vdc.
The airplane also has these DC power sources:
The GCUs monitor the system to control and protect the IDGs. The APU
GCU and the Starter Converter Unit (SCU) work together to control and
protect the APU starter-generator. The Bus Power Control Unit (BPCU)
controls and monitors the use of external power. The BPCU protects the
airplane from external power whose quality is out of limits.
The modules on the P5 panel give manual control and also let you monitor
the status of the electrical power system.
These breakers allow power to the buses:
- Main battery
- Main battery charger
- Auxiliary battery
- Auxiliary battery charger
- External Power Contactor (EPC)
- APU Power Breaker (APB)
- Generator Control Breaker (GCB)
- Bus Tie Breakers (BTBs)
The batteries are the backup DC source if other sources do not operate.
The Standby Power Control Unit (SPCU) controls the distribution of DC
power.
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ELECTRICAL POWER - OPERATION
GENERAL DESCRIPTION
These are the effects of the standby power switch in the other two
positions:
You use switches on the forward P5 overhead panel or the forward flight
attendant's panel to operate the electrical system.
Electrical Meters, Battery and Galley Power Module (P5-13)
You put the BAT switch to the ON position to energize these buses and
components with battery power:
- De-energize the AC standby bus and the DC standby bus (OFF position),
- Energize the AC standby bus with battery power through the static
inverter
- Energize the DC standby bus with battery power (BAT position)
- Switched hot battery bus
- Battery bus
- Static inverter
- AC standby bus
- DC standby bus
- P5-13 alphanumeric display
You use the GALLEY switch to control power to all galleys.
You use the DC and AC selectors and the alphanumeric display to monitor
the electrical power system power sources.
Generator Drive And Standby Power Module (P5-5)
The generator drive disconnect switch operates the disconnect
mechanism for its Integrated Drive Generator (IDG). This removes engine
accessory gearbox power from the IDG. The engine start lever must be in
the idle position for the disconnect function to operate.
The standby power switch gives you manual control of the AC and DC
standby power bus sources. In the auto position, the AC standby bus
receives power from AC transfer bus 1 and the DC standby bus receives
power from DC bus 1 when these sources are available. If the sources are
not available, the AC standby bus receives power from the static inverter
and the DC standby bus receives power from the battery.
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ELECTRICAL POWER - OPERATION GENERAL DESCRIPTION pt 2
AC Systems, Generator and APU Module (P5-4)
If the AC transfer buses do have power initially, then only the AC transfer
bus on the same side as the APU GEN switch you operate will energize
with APU power.
The blue APU GEN OFF BUS light comes on when the APU is ready to
supply electrical power.
You use the ground power switch to control external power to the AC
transfer buses.
The blue GRD POWER AVAILABLE light above the switch shows if the
ground source is connected and quality is good. Both AC transfer buses
receive power when you put the ground power switch to the ON position.
Forward Flight Attendant’s Panel
Any initial power sources are removed before the transfer buses receive
external power.
You use the ground service switch to supply external power to ground
service bus 1 and 2 with external power connected. This makes it possible
to supply electrical power for cabin servicing without going into the flight
compartment.
The bus transfer switch gives you manual control of the BTBs and the DC
bus tie relay. In the AUTO position, the BTBs and the DC bus tie relay
operate automatically as necessary.
In the OFF position, the BTBs open and isolate the AC transfer buses from
each other. The DC bus tie relay will also open. This isolates DC bus 1
and DC bus 2 from each other. The position also resets the BTB trip
circuits.
You use the GEN 1 and GEN 2 switches to supply IDG power to an AC
transfer bus. The AC transfer bus on that side goes to IDG power when
you temporarily put the switch to the ON position. Any initial power
sources are removed.
You use the APU GEN switches to supply power to the AC transfer buses.
There are two switches because there are two Bus Tie Breakers (BTBs)
that supply power to the AC transfer buses. Both AC transfer buses will
receive APU power with operation of just one APU GEN switch if both AC
transfer buses do not have power initially.
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EXTERNAL POWER - GENERAL DESCRIPTION
Purpose
Manual Control
External power is the normal source of AC power for the airplane electrical
system when the airplane is on the ground. It lets you have the engines
and APU power sources off. It also gives power to the battery charger to
charge the battery.
The ground power switch is on the AC system, generator, and APU
module.
You use this switch to make the AC transfer buses receive external power
through the EPC and the BTBs. The BPCU closes the EPC directly. Each
BTB closes after it receives a signal from the BPCU through a GCU.
General Description
A switch on the forward attendant's panel lets you power the AC and DC
ground service buses directly from the external power source. AC power
goes through the two ground service transfer relays. DC power goes
through the ground service bus relay. The BPCU uses input from the
forward attendant's panel to control the relays.
The Bus Power Control Unit (BPCU) uses inputs and internal logic to
control distribution of external power on the airplane. The BPCU has BuiltIn Test Equipment (BITE) to help you do troubleshooting of the external
power system.
Switches on the AC system, generator, and APU module and the forward
attendant's panel give you manual control of external power.
The external power panel and the AC system, generator, and APU module
have external power indication.
The external power panel has a receptacle for AC external power
connection.
Automatic Control (System Protection)
The BPCU uses inputs from the external power Line Current Transformer
(LCT) and feeder lines to monitor external power quality. The BPCU
controls the EPC position to protect airplane systems.
The BPCU also removes power to some buses (load shed) to protect the
system.
Bus Power Control Unit (BPCU)
The BPCU controls the use of external power through these components:
Indication
- External Power Contactor (EPC) position
- Bus Tie Breaker (BTB) positions through the Generator Control Units
(GCUs)
- Ground service transfer relays (power to AC ground service buses)
- Ground service bus relay (power to ground service DC bus)
- Indication on the AC system, generator, and APU module and the
external power panel
The BPCU controls external power indication at the AC systems,
generator, and APU module and at the external power panel.
The BPCU also interfaces with other systems.
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EXTERNAL POWER - BPCU - EXTERNAL POWER
CONTACTOR CONTROL, PROTECTION, AND
INDICATION
(CONT.)
Indication
Interfaces
The blue GRD POWER AVAILABLE light comes on to show the external
power is connected and power quality is in limits. The BPCU supplies
power for the light.
The external power sensing relay (R47) energizes to supply entry way
lighting to the passenger entry door areas. This relay receives power from
the BPCU.
The refuelling power control relay (R11) energizes to supply power to the
fuelling station. This relay receives power from the BPCU.
The light comes on when these conditions are true:
- There is continuity through pins E and F at the external power connection
- Connected external power quality is in limits
The amber CONN light comes on to show that external power is
connected.
This light is not an indication that power quality is good. The light is neon
and receives AC power directly from the external power feeder lines in
PDP 2 (P92).
The white NOT IS USE light comes on to show that the ground service
buses and transfer buses are not receiving power from the external power
source.
The light comes on when these conditions are true:
- There is continuity through pins E and F (external power plug connected)
- The ground service relays are de-energized
- The EPC is open
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GENERATOR DRIVE - COMPONENT LOCATION
General
The components of the generator drive are on the engine and in the flight
compartment.
Integrated Drive Generator (IDG)
The IDG is on the front face of the engine accessory gearbox at the 7:00
position. The IDG is immediately below the engine starter.
You open the left engine fan cowl to gain access to the IDG installation.
When servicing, you can gain access to the IDG through the IDG servicing
door in the left fan cowl.
IDG Air/Oil Cooler
The air/oil cooler is on the inside, aft portion, of the fan case at the 6:30
position.
You open the engine left fan cowl to get access to the air/oil cooler.
Generator Drive and Standby Power Module
The generator drive and standby power module is on the P5 forward
overhead panel in the flight compartment.
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Figure 6
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GENERATOR DRIVE - INTEGRATED DRIVE
GENERATOR
Charge Oil Filter
(IDG)
The charge oil filter is downstream of the IDG charge pump. Oil bypasses
this filter if it becomes clogged. There is no visual indication on the IDG
that this filter is in the bypass condition. You replace the charge oil filter on
regular intervals.
Purpose
The Integrated Drive Generators (IDG) are the normal source of AC power
generation in flight. There are two IDGs on the airplane. Each supplies
115vac, 400 Hz power. The IDG can supply up to 90 KVA.
Scavenge Oil Filter
Physical Description
The scavenge oil filter is downstream of the IDG scavenge pump. Oil
bypasses this filter if it becomes clogged. You replace the scavenge oil
filter on regular intervals.
The IDG has a constant speed drive section and a generator. The IDG
weighs approximately 117 pounds (53 kgs).
Differential Pressure Indicator
Push-To-Vent Valve
The differential pressure indicator supplies a visual indication of a clogged
scavenge filter. A temperature lockout feature prevents a false differential
pressure indication during engine start with cold oil.
The vent valve is a spring-actuated valve that keeps constant internal
pressure in the IDG case. You also push the button to release the air
pressure before you service the IDG with oil or drain the oil.
Oil Level Sightglass
Case Pressure Relief Valve
The oil level sightglass shows the relative amount of oil in the IDG. You
use the sightglass to do a check of the oil quantity.
The case pressure relief valve prevents the IDG case from rupture if the
fuel/oil cooler leaks fuel into the oil system. The oil vents into the area
between the engine accessory gearbox and the IDG. Fluid in this area
drains overboard through the engine drain system.
Drain Plug
You remove the drain plug to drain the IDG oil.
Disconnect Reset Ring
Pressure Fill Adapter
You use the disconnect reset ring to reconnect the IDG after a manual
disconnect. The engine must not be turning when you do a reset of the
IDG.
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You use the pressure fill adapter when servicing the IDG oil level.
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GENERATOR DRIVE – SERVICING
Charge and Scavenge Oil Filters
Oil Quantity Check
There are two remove-and-replace oil filters on the IDG. You check and
replace both filters at scheduled intervals. You should always replace old
filters with new filters.
The charge oil filter is downstream of the charge pump. If this filter clogs, a
differential pressure valve opens and lets oil bypass the filter. There is no
indication if this filter clogs.
The scavenge filter is downstream of the scavenge pump. The differential
pressure indicator shows if the filter clogs.
The oil level sight glass shows the relative amount of oil in the IDG. The oil
level sight glass cover is black with a silver band. When the oil level is
below the silver band, the IDG oil level is low and it is necessary to add oil.
When the oil level is in the silver band, the IDG oil level is normal. When
the oil level is above the silver band, the IDG oil level is high and you must
drain oil. The same IDG is used on either the left or right engine. With wing
dihedral, the oil level in the sight glass changes. You must service to the
correct left or right engine marks on the sight glass. You should always
vent the IDG before you do an oil quantity check.
Oil Servicing
Oil servicing of the IDG occurs at the pressure fill port. You should push
the push-to-vent-valve to release IDG case air pressure before you add
oil. The oil that you pump into the IDG flows through the scavenge filter
and then through the heat exchangers and into the IDG case. Air in the
circuit moves ahead of the oil to the IDG sump.
Because it takes time for the oil to flow through external components, you
should add oil slowly. This prevents over servicing. You pump oil into the
IDG until the correct oil level shows on the oil sight glass.
CAUTION: DO NOT CHECK THE OIL LEVEL OF A DISCONNECTED
IDG. A DISCONNECT CAN CAUSE AN INCORRECT OIL QUANTITY
INDICATION IN THE IDG. TOO MUCH OR NOT ENOUGH OIL CAN
CAUSE DAMAGE TO THE IDG DURING CONTINUED OPERATION
WARNING: SERVICE TO THE PROPER LEVEL. OPERATION OF THE
IDG WITH TOO MUCH OIL OR WITHOUT ENOUGH OIL CAUSES
DAMAGE TO THE IDG.
Training Information Point
Drain Plug
There is a drain plug at the bottom of the IDG. You use it to drain the oil
from the IDG.
The IDG has two servicing placards.
The small placard below the sightglass reminds you to vent the IDG before
you do an oil quantity check. Your check may not be accurate if you do not
vent the IDG.
WARNING: FAILURE TO PUSH THE CAP OF THE VENT VALVE TO
RELIEVE THE INTERNAL IDG PRESSURE COULD CAUSE HOT OIL
TO SPRAY OUT.
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The large placard has a warning and the IDG servicing instructions. You
should always vent the IDG before and after you service it.
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AC GENERATION - APU STARTER GENERATOR
Purpose
The APU starter-generator has two functions.
First, the starter-generator makes AC power for ground operations. The
starter generator can supply electrical power during flight as backup to the
IDGs.
The starter-generator also starts the APU. It uses AC power from the Start
Converter Unit (SCU) to turn the APU during the start sequence.
Location
The starter-generator is on the right side of the APU gear box. It attaches
to the gearbox with 8 nuts. You replace the starter-generator without
removal of the APU.
General Description
The APU starter-generator is an oil cooled, three phase, brushless,
rotating rectifier machine. It operates at 12,000 rpm.
The generator includes these components:
- An exciter
- A main generator
- A Permanent Magnet Generator (PMG)
The PMG supplies power for start-up, and voltage control of the APU
channel.
The starter-generator supplies 3 phase, 115 volts (nominal) power at
400Hz.
The starter-generator supplies up to 90 KVA below 32,000 feet (9753
meters).
The starter-generator can supply 66 KVA at 41,000 feet (12,496 meters).
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AC GENERATION - START CONVERTER UNIT
(SCU)
Purpose
The start converter unit (SCU) has two functions:
- Regulate the APU starter-generator electrical power output
- Turn the APU during an APU start
Location
The SCU is on the E2 rack in the EE compartment.
General
The SCU operates with the APU Generator Control Unit (AGCU) to control
and regulate APU starter-generator power. The APU Generator Control
Relay (AGCR) and the starter-generator voltage regulator are inside the
SCU.
The SCU also makes the starter-generator function like a motor to turn the
APU during starting.
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AC GENERATION - POWER DISTRIBUTION
PANELS
Power Distribution Panel 2
General
The Power Distribution Panel 2 (PDP 2 or P92), have these components:
The Power Distribution Panels (PDPs) contain the breakers and many of
the electrical buses.
Each PDP has a door on the front of it that is usually closed. The front of
each door has circuit breakers.
- AC transfer bus 2
- Ground service bus 2
- DC bus 2
- GCB 2
- External Power Contactor (EPC)
- BTB 2
Location
PDP 1 (P91) is on the left side of the E/E compartment. PDP 2 (P92) is on
the right side of the E/E compartment.
There are four red lights on the forward and aft face of the Power
Distribution Panel. You can see the lights on the aft face when you are in
the forward cargo compartment. These lights come on to warn you that
electrical power is active inside the panel.
Power Distribution Panel 1
The Power Distribution Panel 1 (PDP 1 or P91), have these components:
The lights have these names and come on with these conditions:
- AC transfer bus 1
- Ground service bus 1
- DC bus 1
- Generator Control Breaker 1 (GCB 1)
- Auxiliary Power Breaker (APB)
- Bus Tie Breaker 1 (BTB 1)
- GEN 2 (on when IDG 2 supplies power)
- TIE BUS (on where there is power at the bus tie breakers)
- XFR BUS (on when AC transfer bus 2 has power)
- EXT PWR (on when external power supplies power)
There are four red lights on the forward and aft face of the Power
Distribution Panel. These lights come on to warn you that electrical power
is active inside the panel. You can see the lights on the aft face when you
are in the forward cargo compartment.
The lights have these names and come on with these conditions:
- GEN 1 (on when IDG 1 supplies power)
- TIE BUS (on where there is power at the bus tie breakers)
- APU PWR (on when the starter-generator supplies power)
- EXT PWR (on when external power supplies power)
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DC GENERATION
DISTRIBUTION AND CONTROL
The auxiliary battery charger receives power from ground service bus 1.
Control
These switches and components control the relays in the DC distribution:
- Standby Power Control Unit (SPCU)
- Bus Power Control Unit (BPCU)
- Battery switch
- Standby power switch
The DC power system is a two wire system that operates at 28 volts
(nominal).
The DC system has these power sources:
- Three Transformer Rectifiers Units (TRUs)
- Battery charger
- Battery
The TRUs are the normal power source for the DC power system. The
TRUs change 115vac, 3 phase power to unregulated 28vdc. Each TRU
can supply up to 75 amps when airplane cooling air is available. The
TRUs are connected in parallel to provide back-up to each other.
TRU 1 receives power from the AC transfer bus 1. TRU 1 output connects
directly to DC bus 1.
TRU 2 receives power from the AC transfer bus 2. TRU 2 output connects
directly to DC bus 2.
TRU 3 usually receives power from AC transfer bus 2. AC transfer bus 1
supplies back up power through R662 if normal power is lost. The primary
use of TRU 3 is as a power source for the battery bus.
The main battery charger receives power from the AC ground service bus
2. Ground service bus 2 gets power from AC transfer bus 2. The main
battery charger is the primary power supply for the hot and switched hot
battery bus.
The auxiliary battery and its charger connect in parallel when the dual
battery Remote Control Circuit Breaker (RCCB) is closed. This happens
only during conditions when the main battery must supply standby AC and
DC power.
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Figure 12
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DC GENERATION SYSTEM - MAIN BATTERY
AND AUXILIARY BATTERY
Purpose
The main battery has these functions:
- Supply power to critical airplane systems (AC and DC standby buses) if
the normal power sources are not available
- Backup power supply for the AC system control and protection
- Power supply for APU start
The auxiliary battery helps the main battery supply power to the critical
airplane systems (AC and DC standby buses).
Location
The batteries are in the E/E compartment, under the E3 rack. The auxiliary
battery is forward of the main battery. You remove an access panel in the
forward cargo compartment to gain access to the batteries. You must
remove the main battery before you can remove the auxiliary battery.
General Description
Each battery is a 20 cell nickel-cadmium battery with a 48 amp-hour
capacity.
With full charge, the batteries supply a minimum of 60 minutes of standby
AC and DC power.
Each battery has an internal thermal sensor. The battery's charger uses
this sensor to measure internal battery temperature.
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Figure 13
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STANDBY POWER SYSTEM - STANDBY POWER
CONTROL UNIT (SPCU)
Purpose
The Standby Power Control Unit (SPCU) gives manual and automatic
power source selection control of the battery and standby buses.
The SPCU supplies DC system failure data to the electrical meters,
battery and galley power module (P5-13).
The SPCU also controls some power distribution relays in the electrical
system.
Location
The SPCU is in the P6 panel. The P6 panel is in the flight compartment,
behind the first officer's seat.
General Description
The SPCU monitors the position of the battery and standby power
switches. It also monitors AC, DC and battery buses to control the
connection of the battery bus, switched hot battery bus, AC and DC
standby buses to the correct power source.
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ATA 26-00-00
FIRE PROTECTION
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CONTENTS
ATA 26 – FIRE PROTECTION
FIRE PROTECTION – INTRODUCTION .......................................................................................................................................................................................................... 4
PURPOSE ................................................................................................................................................................................................................................................................ 4
FIRE/OVERHEAT DETECTION ................................................................................................................................................................................................................................. 4
EXTINGUISHING ..................................................................................................................................................................................................................................................... 4
ENGINE FIRE DETECTION - GENERAL DESCRIPTION ............................................................................................................................................................................ 6
PHYSICAL DESCRIPTION ........................................................................................................................................................................................................................................ 6
GENERAL DESCRIPTION.......................................................................................................................................................................................................................................... 6
ENGINE FIRE EXTINGUISHING - OVERHEAT/FIRE .................................................................................................................................................................................. 8
PROTECTION PANEL ........................................................................................................................................................................................................................................ 8
PURPOSE ................................................................................................................................................................................................................................................................ 8
LOCATION .............................................................................................................................................................................................................................................................. 8
ENGINE FIRE DETECTION - ENGINE AND APU FIRE ............................................................................................................................................................................. 10
DETECTION CONTROL MODULE ................................................................................................................................................................................................................. 10
PURPOSE .............................................................................................................................................................................................................................................................. 10
LOCATION ............................................................................................................................................................................................................................................................ 10
ENGINE FIRE EXTINGUISHING - EXTINGUISHER BOTTLE ................................................................................................................................................................. 12
PURPOSE .............................................................................................................................................................................................................................................................. 12
LOCATION ............................................................................................................................................................................................................................................................ 12
APU FIRE EXTINGUISHING - APU GROUND CONTROL PANEL .......................................................................................................................................................... 14
PURPOSE .............................................................................................................................................................................................................................................................. 14
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 14
OPERATION .......................................................................................................................................................................................................................................................... 14
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WING AND BODY OVERHEAT DETECTION – INTRODUCTION .......................................................................................................................................................... 16
PURPOSE .............................................................................................................................................................................................................................................................. 16
LAVATORY SMOKE DETECTION - GENERAL DESCRIPTION ............................................................................................................................................................. 18
PURPOSE .............................................................................................................................................................................................................................................................. 18
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 18
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FIRE PROTECTION – INTRODUCTION
Purpose
The fire protection systems monitor the airplane for these conditions:
- Fire
- Smoke
- Overheat
- Pneumatic duct leaks
Fire/Overheat Detection
The airplane has these fire/overheat detection systems:
- Lavatory smoke detection
- Engine fire detection
- APU fire detection
- Wheel well fire detection
- Wing/Body overheat detection
Extinguishing
The airplane has these fire extinguishing systems:
- Lavatory fire extinguishing bottles
- Engine fire extinguishing bottles
- APU fire extinguishing bottle
- Portable fire extinguishers
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ENGINE FIRE DETECTION - GENERAL
DESCRIPTION
Physical Description
These are the major components of the engine fire detection system:
- Engine overheat/fire detectors
- Engine and APU fire detection control module (M279)
- Overheat/fire protection panel
General description
The engine fire detection system uses dual overheat/fire detector loops.
The loops are identified as loop A and loop B.
The detector loops on the engine supply overheat and fire signals to the
engine and APU fire detection control module. This module uses the
signals to set the related alarm indications in the flight compartment.
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ENGINE FIRE EXTINGUISHING - OVERHEAT/FIRE
PROTECTION PANEL
Purpose
The overheat/fire protection panel monitors the fire protection system for
these conditions:
- Engine overheat
- Engine fire
- APU fire
- Wheel well fire
- L bottle discharge
- R bottle discharge
- APU bottle discharge
- Engine fire protection fault conditions
- APU fire protection fault conditions
The overheat/fire protection panel lets you do these functions:
- Set the mode of operation (single or dual loop operation)
- Discharge the fire extinguisher bottles
- Do a test of the fire extinguisher bottle squibs
- Do a test of the fire protection system
- Do a test of the fault detection circuits
- Stop the fire alarm bell
Location
The overheat/fire protection panel is on the P8 panel.
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ENGINE FIRE DETECTION - ENGINE AND APU
FIRE
DETECTION CONTROL MODULE
Purpose
The engine and APU fire detection control module monitors detector
elements for overheat and fire conditions in the engine and APU areas.
Location
The engine and APU fire detection control module is in the electronic
equipment compartment rack E2-2.
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ENGINE FIRE EXTINGUISHING - EXTINGUISHER BOTTLE
Purpose
The engine fire extinguisher bottles contain the halon gas that extinguishes an
engine fire.
Location
The two engine fire extinguisher bottles are in the upper aft left corner of the left
main wheel well.
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APU FIRE EXTINGUISHING - APU GROUND
CONTROL PANEL
Purpose
On the ground, the APU ground control panel gives you visual and aural
indications of an APU fire. The control panel also lets you extinguish an
APU fire.
Physical Description
The APU ground control panel has these components:
- Red fire warning light
- Fire horn
- Horn cut-out switch
- APU fire control handle
- Bottle discharge switch
Operation
When there is a fire in the APU, the horn and light operates alternately and
the APU stops.
When you push the horn cut-out button the horn sound stops and the red
light stays on continuously.
When you pull the APU fire control handle, the APU system stops and
isolates the APU from other systems.
When you pull down the APU fire control handle, you also arm the bottle
discharge toggle switch. You push the toggle switch to cause the APU
bottle squib explosion.
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WING AND BODY OVERHEAT DETECTION –
INTRODUCTION
Purpose
The wing and body overheat detection system monitors for overheat
conditions caused by pneumatic duct leaks.
When its detectors sense this condition, they are shown in the flight
compartment on the P5 and P7 panels.
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LAVATORY SMOKE DETECTION - GENERAL DESCRIPTION
Purpose
The lavatory smoke detection system monitors for smoke in the lavatories.
General Description
When there is smoke in a lavatory, the detector gives these alarm indications:
- Detector alarm indicator light comes on
- Detector gives a horn sound
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ATA 27-00-00
FLYING CONTROLS
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GEN FAM FLYING CONTROLS
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CONTENTS
ATA 27 – FLYING CONTROLS
FLIGHT CONTROLS – INTRODUCTION ........................................................................................................................................................................................................ 6
GENERAL ............................................................................................................................................................................................................................................................... 6
PRIMARY FLIGHT CONTROL SYSTEM ..................................................................................................................................................................................................................... 6
SECONDARY FLIGHT CONTROLS ............................................................................................................................................................................................................................ 6
FLIGHT CONTROLS - FLIGHT COMPARTMENT CONTROLS AND INDICATIONS .......................................................................................................................... 8
GENERAL ............................................................................................................................................................................................................................................................... 8
AILERON ................................................................................................................................................................................................................................................................ 8
ELEVATOR ............................................................................................................................................................................................................................................................. 8
RUDDER ................................................................................................................................................................................................................................................................. 8
FLAPS AND SLATS .................................................................................................................................................................................................................................................. 8
SPOILERS AND SPEEDBRAKES ................................................................................................................................................................................................................................ 8
HORIZONTAL STABILIZER ...................................................................................................................................................................................................................................... 8
STALL WARNING ................................................................................................................................................................................................................................................... 8
FLIGHT CONTROLS - FLIGHT COMPARTMENT CONTROLS AND INDICATIONS PT 2 ............................................................................................................... 10
GENERAL ............................................................................................................................................................................................................................................................. 10
AILERON .............................................................................................................................................................................................................................................................. 10
RUDDER ............................................................................................................................................................................................................................................................... 10
FLAPS AND SLATS ................................................................................................................................................................................................................................................ 10
SPOILERS AND SPEEDBRAKES .............................................................................................................................................................................................................................. 10
HORIZONTAL STABILIZER .................................................................................................................................................................................................................................... 10
AILERON AND AILERON TRIM CONTROL SYSTEM - CABLE ............................................................................................................................................................. 12
GENERAL ............................................................................................................................................................................................................................................................. 12
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 12
FUNCTIONAL DESCRIPTION – NORMAL................................................................................................................................................................................................................ 12
FUNCTIONAL DESCRIPTION – MANUAL ............................................................................................................................................................................................................... 12
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AILERON AND AILERON TRIM CONTROL SYSTEM - AILERON ........................................................................................................................................................ 14
PCU LINKAGE ..................................................................................................................................................................................................................................................... 14
PURPOSE .............................................................................................................................................................................................................................................................. 14
LOCATION ............................................................................................................................................................................................................................................................ 14
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 14
FUNCTIONAL DESCRIPTION.................................................................................................................................................................................................................................. 14
AILERON AND AILERON TRIM CONTROL SYSTEM - ............................................................................................................................................................................ 16
BALANCE PANEL AND TAB ............................................................................................................................................................................................................................ 16
PURPOSE .............................................................................................................................................................................................................................................................. 16
LOCATION ............................................................................................................................................................................................................................................................ 16
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 16
FUNCTIONAL DESCRIPTION.................................................................................................................................................................................................................................. 16
FLIGHT SPOILER CONTROL SYSTEM – INTRODUCTION .................................................................................................................................................................... 18
GENERAL ............................................................................................................................................................................................................................................................. 18
ROLL CONTROL ................................................................................................................................................................................................................................................... 18
SPEEDBRAKE CONTROL ....................................................................................................................................................................................................................................... 18
AUTO SPEEDBRAKE CONTROL ............................................................................................................................................................................................................................. 18
FLIGHT SPOILER CONTROL SYSTEM – FUNCTIONAL DESCRIPTION ............................................................................................................................................. 20
GENERAL ............................................................................................................................................................................................................................................................. 20
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 20
FUNCTIONAL DESCRIPTION - ROLL CONTROL ..................................................................................................................................................................................................... 20
FUNCTIONAL DESCRIPTION - SPEEDBRAKE CONTROL ......................................................................................................................................................................................... 20
RUDDER AND RUDDER TRIM CONTROL SYSTEM – GENERAL DESCRIPTION ............................................................................................................................. 22
GENERAL ............................................................................................................................................................................................................................................................. 22
MANUAL OPERATION - RUDDER PEDALS ............................................................................................................................................................................................................ 22
MANUAL OPERATION - RUDDER TRIM ................................................................................................................................................................................................................ 22
YAW DAMPER ...................................................................................................................................................................................................................................................... 22
WHEEL-TO-RUDDER INTERCONNECT SYSTEM (WTRIS) .................................................................................................................................................................................... 22
AUTHORITY LIMITER ........................................................................................................................................................................................................................................... 22
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ELEVATOR AND TAB CONTROL SYSTEM – GENERAL DESCRIPTION ............................................................................................................................................ 24
GENERAL ............................................................................................................................................................................................................................................................. 24
CONTROL COLUMNS ............................................................................................................................................................................................................................................ 24
ELEVATOR FORWARD CONTROL QUADRANTS .................................................................................................................................................................................................... 24
ELEVATOR CONTROL CABLES ............................................................................................................................................................................................................................. 24
ELEVATORS ......................................................................................................................................................................................................................................................... 24
ELEVATOR FEEL AND CENTRING UNIT ................................................................................................................................................................................................................ 24
ELEVATOR NEUTRAL SHIFT - STABILIZER INPUT ................................................................................................................................................................................................. 24
HORIZONTAL STABILIZER TRIM CONTROL SYSTEM ......................................................................................................................................................................... 26
GENERAL DESCRIPTION ............................................................................................................................................................................................................................... 26
MANUAL OPERATION - STABILIZER TRIM SWITCHES .......................................................................................................................................................................................... 26
MANUAL OPERATION - STABILIZER TRIM WHEELS ............................................................................................................................................................................................. 26
DFCS OPERATION ............................................................................................................................................................................................................................................... 26
COLUMN CUT-OUT SWITCHES ............................................................................................................................................................................................................................. 26
STABILIZER TRIM OVERRIDE SWITCH.................................................................................................................................................................................................................. 26
STABILIZER TRIM CUT-OUT SWITCHES ................................................................................................................................................................................................................ 26
FLAPS UP SWITCH ................................................................................................................................................................................................................................................ 26
STABILIZER TRIM LIMIT SWITCHES ..................................................................................................................................................................................................................... 26
TE FLAP SYSTEM - GENERAL DESCRIPTION ........................................................................................................................................................................................... 28
GENERAL ............................................................................................................................................................................................................................................................. 28
NORMAL OPERATION ........................................................................................................................................................................................................................................... 28
ALTERNATE OPERATION ...................................................................................................................................................................................................................................... 28
TE FLAP SYSTEM - FLAP POWER DRIVE UNIT ........................................................................................................................................................................................ 30
PURPOSE .............................................................................................................................................................................................................................................................. 30
LOCATION ............................................................................................................................................................................................................................................................ 30
LE FLAP AND SLAT CONTROL SYSTEM .................................................................................................................................................................................................... 32
GENERAL DESCRIPTION ............................................................................................................................................................................................................................... 32
NORMAL OPERATION ........................................................................................................................................................................................................................................... 32
ALTERNATE OPERATION ...................................................................................................................................................................................................................................... 32
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FLIGHT CONTROLS – INTRODUCTION
General
The flight controls keep the airplane at the necessary attitude during flight.
They have movable surfaces on the wing and the empennage.
These are the two types of flight control systems:
- Primary
- Secondary
Primary Flight Control System
The primary flight control system moves the airplane about three axes: lateral,
longitudinal, and vertical.
The primary flight control system has these components:
- Aileron (2)
- Elevator (2)
- Rudder
Secondary Flight Controls
The secondary flight controls improve the lift and handling properties of the
airplane.
The secondary flight control system has these components:
- Leading edge devices (12)
- Trailing edge flaps (4)
- Spoilers and speedbrakes (12)
- Horizontal stabilizer
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FLIGHT CONTROLS - FLIGHT COMPARTMENT
CONTROLS AND INDICATIONS
Spoilers and Speedbrakes
General
A green SPEED BRAKE ARM light and amber SPEED BRAKE DO NOT
ARM light are on the P1 panel. The SPEEDBRAKES EXTENDED light is
on the P3 panel.
The flight control indication and control components are in the flight
compartment.
Aileron
Horizontal Stabilizer
The aileron control wheel is on the top of the elevator control column. The
aileron trim indication is on the top of the control wheel.
The electric trim switches are on the outboard side of each control wheel.
Stall Warning
Elevator
The stall warning test switches are on the P5 aft overhead panel.
The elevator control columns are forward of the pilot seats.
Rudder
The rudder pedals are forward of the pilot seats.
Flaps and Slats
The alternate flap switches are on the flight control panel on the P5
forward overhead panel. The indication for the leading edge devices is on
the P5 aft overhead panel. The trailing edge flaps indication is on the P2
centre instrument panel.
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FLIGHT CONTROLS - FLIGHT COMPARTMENT
CONTROLS AND INDICATIONS Pt 2
Horizontal Stabilizer
General
Some of the flight control indication and control components in the flight
compartment are on the control stand.
These controls and indications for the horizontal stabilizer are on the
P10control stand:
Aileron
- Captain and first officer stabilizer trim wheels
- Stabilizer trim indicator
- Stabilizer trim cut-out switches
The aileron trim switches are on the aileron/rudder trim panel on the P8 aft
electronic panel.
A stabilizer override switch is on the P8 aft electronic panel.
Rudder
The rudder trim control and the rudder trim indicator are on the
aileron/rudder trim panel on the P8 aft electronic panel.
Flaps and Slats
The flap lever is on the P10 control stand.
Spoilers and Speedbrakes
The speedbrake lever is on the P10 control stand.
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AILERON AND AILERON TRIM CONTROL
SYSTEM - CABLE
General
The aileron control system and the flight spoilers use cable force input
from the control wheels.
Physical Description
The aileron control system has these cables:
- Bus drum cables
- Left and right body cables
- Left and right wing cables
Two spring mechanisms isolate the aileron system from the flight spoilers.
They are the transfer mechanism and the aileron spring cartridge.
Functional Description – Normal
When the control wheels move, the left body cables move and control the
PCUs. The PCU housing moves and controls the aileron wing cables.
When the PCU housing moves, it also controls the right body cables and
completes the loop to the right control column. It also controls the spoiler
wing cables through the spoiler mixer. This controls the flight spoiler
actuators to move after some control wheel movement.
Functional Description – Manual
Manual operation is almost the same as normal operation with one
difference.
There is three degrees of control wheel movement at the aileron PCUs
before the input crank meets the mechanical stops. Then the PCU housing
moves, but the pilot supplies the force.
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AILERON AND AILERON TRIM CONTROL SYSTEM - AILERON
PCU LINKAGE
Purpose
The aileron PCU linkage sends the aileron inputs to the aileron PCUs.
Location
The aileron PCU linkage is on the left forward bulkhead of the main landing gear
wheel well.
Physical Description
The aileron PCU linkage includes these components:
- Control quadrant
- Autopilot input rod
- Aileron trim actuator
- Aileron feel and centring unit · Input shaft
- Input pogo cranks (4)
- Input pogo (4)
Functional Description
The aileron input shaft receives inputs from the:
- Pilot through the aileron control quadrant
- Autopilot through the aileron autopilot input rod
- Trim switches through the aileron trim actuator
When the shaft moves, it moves the input pogo cranks. This moves the input
pogos which control the aileron PCUs
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AILERON AND AILERON TRIM CONTROL
SYSTEM BALANCE PANEL AND TAB
Purpose
The aileron balance panels and tab decrease the force necessary to move
the aileron in flight.
Location
The balance panels are in the number one through four aileron bays.
Physical Description
The forward edge of the balance panel attaches to the wing structure
through an idler hinge. The aft edge attaches to the aileron.
Seals connect the hinge assemblies along the two sides of the balance
panel.
This makes two separate chambers. The upper chamber vents to the
airstream over the wing and the lower to the airstream under the wing.
Functional Description
When there is no lateral input, pressure forces occur across the balance
panel and keep the aileron in the neutral position. When the aileron
moves, it causes a differential pressure. This moves the balance panel in
the opposite direction of the aileron movement.
As the balance tab moves, differential forces occur at the tail of the
aileron.
They help the power source that moves the aileron. These forces are
always applied but they are most useful during manual control.
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FLIGHT SPOILER CONTROL SYSTEM –
INTRODUCTION
General
The spoilers help the ailerons control airplane roll about the longitudinal
axis. They also supply speedbrake control to reduce lift and increase drag
during landing and refused takeoff.
There are six spoilers on each wing. There is one spoiler inboard of each
engine strut, and five spoilers outboard of each engine strut. Each spoiler
has a number, 1 through 12 (from left to right). The ground spoilers are the
most outboard and the most inboard spoiler on each wing. All the other
spoilers are flight spoilers.
The flight crew uses the control wheels and speedbrake lever to manually
move the flight spoilers. The autopilot controls them during autoland.
Roll Control
During roll control, the flight spoilers on one wing move up and all the
other spoilers stay down.
The pilots manually control roll with the control wheels. When the autopilot
is in autoland, the autopilot commands the flight spoilers.
Speedbrake Control
During speedbrake control, the spoilers on both wings move
symmetrically. The pilots manually command speedbrake control with a
speedbrake lever on the aisle stand. The autopilot does not control the
speedbrake function.
Auto Speedbrake Control
The auto speedbrake function supplies automatic extension or retraction
of all the spoilers during landing and refused takeoff.
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FLIGHT SPOILER CONTROL SYSTEM –
FUNCTIONAL DESCRIPTION
Functional Description - Speedbrake Control
General
When the pilot moves the speedbrake lever, the speedbrake lever cables
move a quadrant in the spoiler ratio changer. The spoiler ratio changer
moves the spoiler wing cables. The flight spoilers start to move up after 5
degrees of speedbrake lever movement. The flight spoilers on each wing
move symmetrically.
The pilot uses the control wheels and speedbrake lever to manually move
the flight spoilers. The autopilot automatically controls them.
Physical Description
When the speedbrake lever moves more, the flight spoilers on both wings
moves more.
The lateral control system has these spoiler cables:
- Right body cables
- Spoiler wing cables
- Speedbrake lever cables
Two spring mechanisms isolate the aileron system from the flight spoilers.
They are the transfer mechanism and the aileron spring cartridge.
Functional Description - Roll Control
When the control wheels move, the left body cables move and control the
aileron PCUs. The PCU moves the body quadrant, which moves the left
and right aileron wing cables.
The aileron spring cartridge connects the body quadrant to the spoiler
control quadrant. The spoiler control quadrant supplies the control wheel
inputs to the spoiler ratio changer and mixer. The spoiler ratio changer
moves the spoiler wing cables. The flight spoilers start to move up after 11
degrees of control wheel movement.
When the pilot turns the control wheel 11 degrees clockwise, the flight
spoilers on the right wing start to move up. When the control wheel turns
more, the flight spoilers on the right wing move more.
There is no manual reversion for the spoilers.
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RUDDER AND RUDDER TRIM CONTROL
SYSTEM – GENERAL DESCRIPTION
Wheel-To-Rudder Interconnect System (WTRIS)
General
The WTRIS system assists lateral control during manual reversion turns.
The WTRIS system provides a small amount of rudder movement in
response to control wheel inputs. When engaged, the WTRIS system
gives input to the standby PCU.
The pilot uses the rudder pedals or the rudder trim control knob to control
the rudder. The Yaw Damper and Wheel To Rudder Interconnect System
(WTRIS) automatically control the rudder.
Manual Operation - Rudder Pedals
Authority Limiter
The flight crew uses the rudder pedals to control the rudder through the
cables and the hydraulic PCUs.
The authority limiter reduces the maximum rudder movement. At specified
air speeds, the FSEU opens the main rudder PCU authority limiter
solenoid valve. This limits hydraulic system A pressure to the PCU, which
limits the rudder authority.
Manual Operation - Rudder Trim
The rudder trim control knob and the trim actuator permit the flight crew to
trim out unwanted rudder pedal forces. When the pilots move the rudder
trim control knob on the aisle stand, the control sends a signal to the
rudder trim actuator.
The rudder trim actuator moves the feel and centring unit. This also back
drives the rudder pedals. This movement creates an input to the rudder
PCU. Rudder PCU movement mechanically moves the rudder.
Yaw Damper
The yaw damper keeps the airplane stable around the vertical axis. When
engaged, the yaw damper system gives input to the main or the standby
PCU.
During normal operation, the Stall Management Yaw Damp (SMYD) 1
controls yaw damping with the main rudder PCU. During manual
reversion, SMYD 2 controls yaw damping with the standby rudder PCU.
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ELEVATOR AND TAB CONTROL SYSTEM –
GENERAL DESCRIPTION
General
Elevator Control Cables
These are the components of the elevator and tab control system:
- Control columns (2)
- Elevator forward control quadrants (2)
- EA and EB; left and right body cables
- Elevator aft control quadrants (2)
- Elevator input torque tube
- Elevator power control units (2)
- Elevator output torque tube
- Elevators (2)
- Elevator feel computer
- Elevator feel and centring unit
- Balance panels (6) and tabs (2)
- Elevator tab control mechanism
- Neutral shift rods (2)
The elevator left and right body control cables move the elevator aft
control quadrant, which provides an input to the elevator input torque tube.
Elevators
The elevators attach to the rear spar of the horizontal stabilizer. They
control the pitch attitude of the airplane by up or down movement.
Elevator Feel and Centring Unit
The control columns move the elevator forward quadrant and the elevator
control cables
Feel force is provided by the feel and centring unit and the dual feel
actuator.
Inputs to the feel and centring unit are provided by the stabilizer, the flight
control computers, and elevator feel computer. The stabilizer inputs go
through the elevator neutral shift rods. The flight control computer inputs
go through the mach trim actuator. The elevator feel computer inputs go
through the dual feel actuator. The dual feel actuator adds a variable feel
force to the spring force in the feel and centring unit.
Elevator Forward Control Quadrants
Elevator Neutral Shift - Stabilizer Input
The elevator forward control quadrants connect to the control columns and
transmit pilot forces through control cables to the elevator input torque
tube.
The stabilizer moves two elevator neutral shift rods. The neutral shift rods
provide an input to the elevators through the mach trim actuator, the feel
and centring unit, and the elevator input torque tube to the PCUs. When
the elevator input torque tube moves, it also back drives the control cables
which move the control columns to their new neutral position.
Control Columns
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HORIZONTAL STABILIZER TRIM CONTROL
SYSTEM
GENERAL DESCRIPTION
Stabilizer Trim Cut-out Switches
The pilots control the horizontal stabilizer manually. The autopilot controls
it automatically.
The pilots use the stabilizer trim cut-out switches to stop the stabilizer trim
actuator.
Manual Operation - Stabilizer Trim Switches
Flaps up Switch
The pilots operate two stabilizer trim switches for main electric pitch trim
control. The switches are on the outboard side of each control wheel. This
gives electric input to the stabilizer trim actuator. The motor operates and
drives the gearbox and stabilizer jackscrew.
The flap up switch controls the speed of the stabilizer trim actuator.
Stabilizer Trim Limit Switches
Manual Operation - Stabilizer Trim Wheels
The stabilizer trim limit switches limit the range of stabilizer motion.
The pilots use the stabilizer trim wheels. The wheels are on each side of
the control stand.
DFCS Operation
The Digital Flight Control System (DFCS) gives electric input to the
stabilizer trim actuator. During autopilot operation, the actuator operates
the same as during manual electric operation.
Column Cut-out Switches
The column cut-out switches stop the stabilizer trim when the pilot moves
the control column in a direction opposite the trim direction.
Stabilizer Trim Override Switch
The pilots use the stabilizer trim override switch to bypass the column cutout switches.
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TE FLAP SYSTEM - GENERAL DESCRIPTION
General
For normal operation of the TE flaps, the flap lever makes the command to
the flaps and hydraulic power moves them. If hydraulic power is not
available, you can manually select alternate operation. During alternate
operation, the alternate flaps switch makes the command to the flaps and
electrical power moves them.
Normal Operation
Hydraulic system B power goes through a priority valve and a flow limiter
to the flap control unit. The priority valve gives priority of hydraulic system
B power to the LE devices over the TE flaps. The flow limiter limits the
speed of movement of the TE flaps.
During normal operation, the flap lever makes the commands to the TE
flaps to move. The flap lever moves a cable system that supplies a
mechanical input to a flap control valve in the flap control unit. The flap
control valve sends system B hydraulic power through the bypass valve to
the flap Power Drive Unit (PDU). The PDU moves the flap drive system to
move the TE flaps. The PDU supplies a mechanical feedback to the flap
control valve as the flap drive system moves. The flap PDU also supplies
a mechanical input to the slat control valve and the flap limit switches in
the flap control unit.
Alternate Operation
During alternate operation, the alternate flaps switch sends a signal to
move the bypass valve to the bypass position. The bypass valve prevents
a hydraulic lock on the PDU. The alternate flaps switch also energizes the
alternate flap relays. These relays supply electrical power to an electric
motor on the flap PDU. The PDU moves the flap drive system to move the
TE flaps.
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TE FLAP SYSTEM - FLAP POWER DRIVE UNIT
Purpose
The TE flap power drive unit (PDU) uses hydraulic or electric power to turn
the TE flap torque tubes and the follow-up cables.
Location
The flap PDU is on the aft bulkhead of the MLG wheel well.
Physical Description
The flap PDU has these components:
- Gearbox
- Hydraulic motor
- Electric motor
The gearbox transfers power from the hydraulic and electric motors to the
flap torque tubes. As the torque tubes turn, the gearbox moves the followup cables that attach to the flap control unit.
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LE FLAP AND SLAT CONTROL SYSTEM
GENERAL DESCRIPTION
The LE flaps and slats use hydraulic power to move. For the normal
operation, hydraulic system B supplies hydraulic power. The commands
for the LE flaps and slats come from the TE flap system. During the
alternate operation, the standby hydraulic system supplies hydraulic
power. The commands come from the alternate flaps switches.
Normal Operation
The TE flap system sends inputs to the LE flap and slat control valve
during normal operation. The LE flap and slat control valve sends
hydraulic power through the autoslat control valve to the LE flap and slat
actuators. These actuators move the LE flaps and slats.
The LE flap and slat proximity sensors send signals to the flap/slat
electronics unit (FSEU). The FSEU sends this data to the LE devices
annunciator panel and the LE flaps lights in the flight deck.
If the airplane gets near a stall condition, the Stall Management Yaw
Damper (SMYD) computers send signals to the autoslat control valve. The
autoslat control valve sends hydraulic power to the LE slat actuators to
fully extend the LE slats.
Alternate Operation
During the alternate operation, the alternate flaps switch sends a signal to
the LE standby shutoff valve and to the standby hydraulic system. The LE
standby shutoff valve sends hydraulic power to the LE flap and slat
actuators to extend the LE flaps and slats. Hydraulic power from the LE
standby shutoff valve has priority over the hydraulic power from the LE
flap and slat control valve.
During the alternate operation, the LE flaps and slats can not retract.
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INTENTIONALLY LEFT BLANK
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ATA 28-00-00
FUEL
B737 NG
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INTENTIONALLY LEFT BLANK
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CONTENTS
ATA 28 – FUEL
FUEL STORAGE .................................................................................................................................................................................................................................................... 4
GENERAL DESCRIPTION .................................................................................................................................................................................................................................. 4
FUEL TANK ARRANGEMENT ................................................................................................................................................................................................................................... 4
COMPONENT LOCATION ......................................................................................................................................................................................................................................... 4
CAPACITY ............................................................................................................................................................................................................................................................... 4
PRESSURE FUELING SYSTEM - GENERAL DESCRIPTION ...................................................................................................................................................................... 6
GENERAL ................................................................................................................................................................................................................................................................ 6
CONTROL................................................................................................................................................................................................................................................................ 6
INDICATION ............................................................................................................................................................................................................................................................ 6
PRESSURE FUELING SYSTEM - FUELING PANEL (P15) ............................................................................................................................................................................ 8
GENERAL ................................................................................................................................................................................................................................................................ 8
FUELING VALVE OPEN LIGHTS .............................................................................................................................................................................................................................. 8
FUELING VALVE CONTROL SWITCH ....................................................................................................................................................................................................................... 8
PRESSURE FUELING SYSTEM – OPERATION ............................................................................................................................................................................................... 8
GENERAL ................................................................................................................................................................................................................................................................ 8
ENGINE FUEL FEED - GENERAL DESCRIPTION ....................................................................................................................................................................................... 10
GENERAL .............................................................................................................................................................................................................................................................. 10
APU FUEL FEED - GENERAL DESCRIPTION ............................................................................................................................................................................................... 10
GENERAL .............................................................................................................................................................................................................................................................. 10
FUEL INDICATING - GENERAL DESCRIPTION ......................................................................................................................................................................................... 12
GENERAL .............................................................................................................................................................................................................................................................. 12
OPERATION .......................................................................................................................................................................................................................................................... 12
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FUEL STORAGE
GENERAL DESCRIPTION
Fuel Tank Arrangement
There are three fuel tanks:
- Main tank No. 1
- Main tank No. 2
- Centre tank
Surge tanks collect fuel overflow only. The fuel overflow in the left wing
surge tank drains to main tank number one. The fuel overflow in the right
wing surge tank drains to main tank number two. If the fuel level is high
enough in the surge tank fuel drains out the vent scoop.
Component Location
Main tank number one is in the wing box of the left wing. Main tank
number two is in the wing box of the right wing. The centre tank is in the
fuselage and the left and right wing root.
Capacity
The nominal capacity of main tank number one is 3,867 kgs.
The nominal capacity of main tank number two is 3,867 kgs.
The nominal capacity of the centre tank is 12,802 kgs).
Fuel tank capacity does not include surge tanks.
B737 NG
GEN FAM FUEL
REFRESHER COURSE
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PRESSURE FUELING SYSTEM - GENERAL
DESCRIPTION
General
The three tanks fill from a fuelling station on the right wing.
The fuelling station has these components
:
- Fuelling panel
- Fuelling manifold
- Fuelling receptacle
The fuelling panel controls the pressure fuelling system. Each tank fills
from the single fuelling receptacle. The fuelling manifold divides fuel from
the fuelling receptacle to the fuelling valves.
A float switch removes power to the fuelling valves when the fuel quantity
in the tank is full.
Control
The fuelling station permits automatic and manual control of fuelling
valves. The fuelling station receives electrical power from the 28vdc hot
battery bus. You use the fuelling indication test switch as an alternative
switch to supply power to the fuelling station. An override switch on each
fuelling valve allows manual operation.
Indication
Three valve position lights show that there is power to the fuelling valves.
Three fuelling indicators show fuel quantity in each tank.
B737 NG
GEN FAM FUEL
REFRESHER COURSE
6
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PRESSURE FUELING SYSTEM - FUELING PANEL
(P15)
General
The fueling panel (P15) has these components:
- Fueling valve open lights
- Fueling indication test switch
- Fueling valve control switch
- Fuel indicators
- Fueling power control switch
Fueling Valve Open Lights
The blue valve position lights come on when the fueling shutoff valve
solenoids
have power.
Fueling Valve Control Switch
The fueling valve control switch is a two position switch. In the OPEN
position, the switch commands the fueling valve to open. In the CLOSED
position, the switch commands the fueling valve to close.
PRESSURE FUELING SYSTEM – OPERATION
General
Fueling placards, with instructions for fueling, are on the fueling station
door.
Use these placards when fueling the aircraft.
The fueling station receives power when the fueling station door opens.
B737 NG
GEN FAM FUEL
REFRESHER COURSE
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FOR TRAINING PURPOSES ONLY
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ENGINE FUEL FEED - GENERAL DESCRIPTION
General
The engine fuel feed system controls and supplies fuel to the engines.
It uses these inputs:
- Fuel system panel (P5-2)
- Engine start switches
- Engine fire switches
The engine fuel feed system uses these components to supply fuel to the
engines:
- Centre tank boost pumps
- Forward boost pumps
- Aft boost pumps
- Bypass valve
- Cross feed valve
- Engine fuel spar valve
APU FUEL FEED - GENERAL DESCRIPTION
General
The APU fuel feed system supplies fuel from any tank to the APU.
APU Fuel Feed
The centre tank boost pumps or the boost pumps in main tank No. 1 and
main tank No. 2 supply fuel to the APU. If the boost pumps are off, the
APU suctions fuel from main tank No. 1.
B737 NG
GEN FAM FUEL
REFRESHER COURSE
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FUEL INDICATING - GENERAL DESCRIPTION
General
The Fuel Quantity Indicating System (FQIS) measures the fuel volume in
the fuel tanks.
The FQIS also calculates the fuel weight in the fuel tanks.
These are the FQIS components:
- Fuel quantity processor unit
- Tank units
- Compensators
- Wiring harnesses
Operation
The fuel quantity processor unit excites and receives signals from the tank
units and compensators. The fuel quantity processor unit uses these
signals to calculate fuel quantity in each tank.
The fuel quantity processer unit sends an individual fuel tank weight signal
to the common display system and the refuel panel. The fuel quantity
processor unit sends a total fuel weight signal to the flight management
computers.
B737 NG
GEN FAM FUEL
REFRESHER COURSE
12
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INTENTIONALLY LEFT BLANK
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ATA 29-00-00
HYDRAULIC POWER
B737 NG
GEN FAM HYDRAULIC POWER
REFRESHER COURSE
1
FOR TRAINING PURPOSES ONLY
29-00-00
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INTENTIONALLY LEFT BLANK
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GEN FAM HYDRAULIC POWER
REFRESHER COURSE
2
FOR TRAINING PURPOSES ONLY
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CONTENTS
ATA 29 – HYDRAULIC POWER
HYDRAULIC POWER - GENERAL DESCRIPTION ...................................................................................................................................................................................... 4
HYDRAULIC SYSTEM A .......................................................................................................................................................................................................................................... 4
HYDRAULIC SYSTEM B .......................................................................................................................................................................................................................................... 4
STANDBY HYDRAULIC SYSTEM ............................................................................................................................................................................................................................. 4
POWER TRANSFER UNIT ........................................................................................................................................................................................................................................ 4
PRESSURIZATION ................................................................................................................................................................................................................................................... 4
MAIN HYDRAULIC SYSTEMS - CONTROLS AND INDICATIONS ........................................................................................................................................................... 6
GENERAL ............................................................................................................................................................................................................................................................... 6
EDP AND EMDP PUMP CONTROLS ....................................................................................................................................................................................................................... 6
ENGINE FIRE SWITCHES ......................................................................................................................................................................................................................................... 6
TRAINING INFORMATION POINT............................................................................................................................................................................................................................. 6
STANDBY HYDRAULIC SYSTEM - CONTROLS AND ................................................................................................................................................................................. 8
INDICATIONS ........................................................................................................................................................................................................................................................ 8
GENERAL ............................................................................................................................................................................................................................................................... 8
CONTROLS ............................................................................................................................................................................................................................................................. 8
INDICATIONS .......................................................................................................................................................................................................................................................... 8
STANDBY HYDRAULIC SYSTEM ................................................................................................................................................................................................................... 10
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 10
LOCATION ............................................................................................................................................................................................................................................................ 10
FUNCTIONAL DESCRIPTION.................................................................................................................................................................................................................................. 10
STANDBY HYDRAULIC SYSTEM PUMP ..................................................................................................................................................................................................... 10
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 10
MAIN HYDRAULIC SYSTEMS - GROUND SERVICING SYSTEM .......................................................................................................................................................... 12
GENERAL ............................................................................................................................................................................................................................................................. 12
LOCATION ............................................................................................................................................................................................................................................................ 12
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 12
OPERATION .......................................................................................................................................................................................................................................................... 12
B737 NG
GEN FAM HYDRAULIC POWER
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HYDRAULIC POWER - GENERAL
DESCRIPTION
Hydraulic System A
Standby Hydraulic System
Hydraulic system A supplies pressure to these airplane systems:
The standby hydraulic system supplies alternative hydraulic pressure to
these airplane systems:
- Standby rudder
- Both thrust reversers
- Leading edge flaps and slats
- Aileron
- Autopilot A
- Elevator
- Rudder
- Elevator feel
- Flight spoilers
- Ground spoilers
- Left thrust reverser
- Alternate brakes
- Nose wheel steering
- Landing gear extension and retraction
- Power transfer unit motor
Power Transfer Unit
The Power Transfer Unit (PTU) is a hydraulic motor-pump that supplies
alternative pressure to leading edge flaps and slats.
Pressurization
Air pressure from the reservoir pressurization system maintains head
pressure on hydraulic system A, system B, and the standby hydraulic
system reservoirs.
The pressurized reservoirs supply a constant flow of fluid to the hydraulic
pumps.
Hydraulic System B
Hydraulic system B supplies pressure to these airplane systems:
- Aileron
- Autopilot B
- Elevator
- Rudder
- Elevator feel
- Flight spoilers
- Right thrust reverser
- Normal brakes
- Alternate nose wheel steering
- Alternate landing gear retraction
- Trailing edge flaps
- Leading edge flaps and slats
B737 NG
GEN FAM HYDRAULIC POWER
REFRESHER COURSE
4
FOR TRAINING PURPOSES ONLY
29-00-00
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B737 NG
GEN FAM HYDRAULIC POWER
REFRESHER COURSE
5
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MAIN HYDRAULIC SYSTEMS - CONTROLS
AND INDICATIONS
General
The controls for the main hydraulic system pumps are on the hydraulic
panel.
This panel is on the P5 forward overhead panel.
The engine fire switches on the P8 aft electronics panel control the fluid
supply to the EDPs.
EDP and EMDP Pump Controls
The EDP and the EMDP each have a switch on the hydraulic panel. The
switches have two positions, ON and OFF. The ENG 1 hydraulic pump
switch controls the EDP for system A. The ELEC 2 hydraulic pump switch
controls the EMDP for system A The ENG 2 switch controls the EDP for
system B. The ELEC 1 switch controls the EMDP for system B.
There is an amber low pressure light for each pump above each pump
switch.
Each EMDP also has an amber overheat light above the switch.
Engine Fire Switches
The engine fire switches isolate the engine if there is an engine fire. When
you operate one of the fire switches, the pump low pressure light is
disarmed and the hydraulic fluid supply to the related EDP stops.
Training Information Point
Because the EDP depressurization solenoid gets electrical power when
the EDP control switch is OFF, you normally keep the switch in the ON
position. While you do maintenance, if the switch is in the OFF position for
a long time, you should open the circuit breaker for the EDP solenoid.
B737 NG
GEN FAM HYDRAULIC POWER
REFRESHER COURSE
6
FOR TRAINING PURPOSES ONLY
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7
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STANDBY HYDRAULIC SYSTEM CONTROLS AND
INDICATIONS
General
The controls and indications for the standby hydraulic system are on the
flight control panel. The flight control panel is on the P5 forward overhead
panel in the flight compartment.
Controls
These switches operate components in the standby hydraulic system:
- FLT CONTROL A and B switches
- ALTERNATE FLAPS arming switch
Move one of the two FLT CONTROL A or B switches to the STBY RUD
position to start the standby hydraulic system EMDP and open the standby
rudder shutoff valve in the standby system module.
Move the ALTERNATE FLAPS arming switch to the ARM position to start
the standby hydraulic system EMDP.
Indications
There are two caution indications on the flight control panel for the standby
hydraulic system:
- Standby hydraulic low quantity light.
- Standby hydraulic low pressure light.
B737 NG
GEN FAM HYDRAULIC POWER
REFRESHER COURSE
8
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STANDBY HYDRAULIC SYSTEM
Physical Description
The standby hydraulic system reservoir supplies hydraulic fluid under
pressure to the standby hydraulic system EMDP.
The EMDP has an electric motor that mechanically connects to a hydraulic
pump. The standby hydraulic system EMDP is in the right aft wing to body
fairing, inboard of the brake accumulator.
Physical Description
The standby hydraulic system reservoir contains 3.6 gallons (13.3 liters) of
hydraulic fluid.
Location
The standby hydraulic system reservoir is on the keel beam in the main
landing gear wheel well.
Functional Description
The fill connection permits fluid servicing from the ground servicing system
to the standby and system B reservoirs.
The fill and balance connection connects the standby reservoir to the
hydraulic system B reservoir. The fill and balance line does these
functions:
- Overfill from the servicing system to the system B reservoir
- Thermal expansion of the standby hydraulic system reservoir
- Supply pressure from the hydraulic system B reservoir
STANDBY HYDRAULIC SYSTEM PUMP
The standby hydraulic system electric motor-driven pump (EMDP)
supplies hydraulic pressure to the standby hydraulic system.
B737 NG
GEN FAM HYDRAULIC POWER
REFRESHER COURSE
10
FOR TRAINING PURPOSES ONLY
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MAIN HYDRAULIC SYSTEMS - GROUND
SERVICING SYSTEM
General
The ground servicing system fills all hydraulic reservoirs from one central
location.
Location
The system components are in the right main gear wheel well on the lower
outboard area of the forward bulkhead.
Physical Description
These are the hydraulic servicing components:
- Fill selector valve
- Fill filter module
- Manual fill pump
- Pressure fill connection
Operation
You set the three position fill selector valve to send hydraulic fluid to the
system A or the system B and standby reservoirs. Move the valve to the
closed position after servicing.
The fill filter module cleans the fluid that goes into the hydraulic systems.
The manual fill pump lets you fill the hydraulic system reservoirs manually.
You use the manual pump suction hose during the manual fill operation.
One end of the hose connects to the manual fill pump. The other end of
the hose goes in the hydraulic fluid container. When not in use, you put
the end of the suction hose in a protective cover.
B737 NG
GEN FAM HYDRAULIC POWER
REFRESHER COURSE
12
FOR TRAINING PURPOSES ONLY
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GEN FAM HYDRAULIC POWER
REFRESHER COURSE
13
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INTENTIONALLY LEFT BLANK
B737 NG
GEN FAM HYDRAULIC POWER
REFRESHER COURSE
14
FOR TRAINING PURPOSES ONLY
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ATA 30-00-00
ICE AND RAIN
B737 NG
GEN FAM ICE AND RAIN
REFRESHER COURSE
1
FOR TRAINING PURPOSES ONLY
30-00-00
Version 1
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INTENTIONALLY LEFT BLANK
B737 NG
GEN FAM ICE AND RAIN
REFRESHER COURSE
2
FOR TRAINING PURPOSES ONLY
30-00-00
Version 1
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CONTENTS
ATA 30 – ICE AND RAIN
ICE AND RAIN PROTECTION - GENERAL DESCRIPTION ....................................................................................................................................................................... 4
CONTROL PANEL ................................................................................................................................................................................................................................................... 4
WING AND ENGINE THERMAL ANTI-ICE SYSTEMS ................................................................................................................................................................................................ 4
PROBE HEAT .......................................................................................................................................................................................................................................................... 4
FLIGHT DECK WINDOWS ....................................................................................................................................................................................................................................... 4
DRAIN AND WATER LINE HEATING........................................................................................................................................................................................................................ 4
WING THERMAL ANTI-ICING SYSTEM – INTRODUCTION .................................................................................................................................................................... 6
PURPOSE ................................................................................................................................................................................................................................................................ 6
GENERAL DESCRIPTION ......................................................................................................................................................................................................................................... 6
PITOT AND STATIC – INTRODUCTION ......................................................................................................................................................................................................... 8
PURPOSE ................................................................................................................................................................................................................................................................ 8
GENERAL ............................................................................................................................................................................................................................................................... 8
CONTROL CABIN WINDOW ANTI-ICING SYSTEM -INTRODUCTION ............................................................................................................................................... 10
PURPOSE .............................................................................................................................................................................................................................................................. 10
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 10
B737 NG
GEN FAM ICE AND RAIN
REFRESHER COURSE
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ICE AND RAIN PROTECTION - GENERAL
DESCRIPTION
Drain and Water line Heating
Control Panel
Electric heaters prevent freezing in the water and waste systems
components.
The controls and indications for the ice and rain protection system are on
the P-5 panel.
Wing and Engine Thermal Anti-ice Systems
The wing thermal anti-ice and the engine inlet cowl thermal anti-ice
systems use hot engine bleed air to prevent ice formation.
Probe Heat
The air data probes use electric heat to prevent ice.
Flight Deck Windows
Flight deck windows use electric heat to do these things:
- Prevent ice formation on the windows
- Prevent fog on the windows
- Improve windshield impact strength
The windshields have these features to improve forward vision in heavy
rain:
- Windshield wipers
- Hydrophobic (rain repellent) coatings
B737 NG
GEN FAM ICE AND RAIN
REFRESHER COURSE
4
FOR TRAINING PURPOSES ONLY
30-00-00
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B737 NG
GEN FAM ICE AND RAIN
REFRESHER COURSE
5
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30-00-00
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WING THERMAL ANTI-ICING SYSTEM –
INTRODUCTION
Purpose
The Wing Thermal Anti-Ice system (WTAI) keeps ice from forming on the
leading edge of the wing.
General Description
The WTAI system uses hot air from the pneumatic system to heat the 3
inboard leading edge slats of the wing.
Switches in the flight deck control the operation of the WTAI system.
The WTAI system may operate in flight or on the ground.
The controls and indicators are on the P-5 panel.
B737 NG
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PITOT AND STATIC – INTRODUCTION
Purpose
The pitot and static anti-icing system keeps ice off the air data probes.
This prevents false air data signals that ice causes.
General
The air data probes use electric power for heat. The probes have integral
heaters.
The pitot and static anti-icing system supplies heat to these probes:
- Alpha vanes (2)
- Total air temperature probe (1)
- Pitot probes (5)
The static system sense ports are not part of the probe heat system.
These ports are flush with the fuselage and heat is not necessary.
You control the air data probe heat from the control module on the P-5
panel.
B737 NG
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CONTROL CABIN WINDOW ANTI-ICING SYSTEM
-INTRODUCTION
Purpose
The control cabin window anti-icing system improves window impact
strength and prevents ice formation on the flight compartment windows.
General Description
The control cabin anti-icing system uses electrical power to heat the flight
compartment windows.
The controls and indications for the control cabin window anti-icing system
are on the P5-9 panel.
Window heat control units (WHCUs) are part of the control cabin window
ant-icing system.
B737 NG
GEN FAM ICE AND RAIN
REFRESHER COURSE
10
FOR TRAINING PURPOSES ONLY
30-00-00
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GEN FAM ICE AND RAIN
REFRESHER COURSE
11
FOR TRAINING PURPOSES ONLY
30-00-00
Version 1
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INTENTIONALLY LEFT BLANK
B737 NG
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12
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ATA 31-00-00
INDICATING & RECORDING
B737 NG
GEN FAM INDICATING & RECORDING
REFRESHER COURSE
1
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31-00-00
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INTENTIONALLY LEFT BLANK
B737 NG
GEN FAM INDICATING & RECORDING
REFRESHER COURSE
2
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CONTENTS
ATA 31 – INDICATING AND RECORDING
CDS - FLIGHT COMPARTMENT COMPONENT LOCATIONS .................................................................................................................................................................. 4
COMPONENT LOCATION ......................................................................................................................................................................................................................................... 4
DISPLAY UNITS ................................................................................................................................................................................................................................................. 4
CDS - ENGINE DISPLAY – INTRODUCTION ................................................................................................................................................................................................. 6
ENGINE DISPLAY ................................................................................................................................................................................................................................................... 6
MASTER CAUTION SYSTEM - COMPONENT LOCATION ........................................................................................................................................................................ 8
GENERAL ............................................................................................................................................................................................................................................................... 8
MASTER CAUTION SYSTEM COMPONENTS ............................................................................................................................................................................................................ 8
INPUT COMPONENTS .............................................................................................................................................................................................................................................. 8
MASTER CAUTION SYSTEM – INTERFACES ............................................................................................................................................................................................. 10
CONTROL OF THE SYSTEM ANNUNCIATOR LIGHTS .............................................................................................................................................................................................. 10
RESETS................................................................................................................................................................................................................................................................. 10
AURAL WARNING SYSTEM - GENERAL DESCRIPTION ........................................................................................................................................................................ 12
GENERAL ............................................................................................................................................................................................................................................................. 12
TAKEOFF AND LANDING WARNINGS – OPERATION ............................................................................................................................................................................ 14
TAKEOFF .............................................................................................................................................................................................................................................................. 14
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CDS - FLIGHT COMPARTMENT COMPONENT LOCATIONS
Component location
These are the CDS components in the flight compartment:
- Left outboard DU
- Left inboard DU
- Right outboard DU
- Right inboard DU
- Upper centre DU
- Lower centre DU
- Captain's EFIS control panel
- First Officer's EFIS control panel
- Captain's display select panel
- First Officer's display select panel
- Engine display control panel
- Left remote light sensor
- Right remote light sensor
- Captain's brightness controls
- First Officer's brightness controls
- Display source selectors
DISPLAY UNITS
The common display system uses six identical flat
panel Liquid Crystal Display (LCD) units.
The Display Units (DU’s) show this type of information:
- Primary flight information
- Navigation information
- Engine information
B737 NG
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CDS - ENGINE DISPLAY – INTRODUCTION
Engine Display
The engine display shows engine data.
These are the major indications that show:
- Autothrottle limit message, thrust mode and TAT
- N1
- EGT
- N2
- Fuel flow/fuel used, and fuel quantity
- Crew alert messages
- Oil pressure, temperature and quantity
- Engine vibration
B737 NG
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6
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MASTER CAUTION SYSTEM - COMPONENT
LOCATION
General
The overheat/fire protection panel is on the P8 aft electronic panel.
The components for the master caution system are in the flight
compartment.
Master Caution System Components
These are the master caution system components on the P7 glareshield
panel:
- Master caution lights
- Left system annunciator lights
- Right system annunciator lights
Input Components
Many systems provide discrete inputs to the master caution system.
These are the components on the P5 aft overhead panel:
- IRS mode select unit
- Engine panel
- Flight recorder/Mach airspeed warning panel
These are the components on the P5 forward overhead panel:
- Flight control panel
- Fuel control panel
- Generator drive and standby power panel
- APU indicator panel
- Window heat panel
- Probe heat panel
- Hydraulic panel
- System annunciators
- Air conditioning/bleed air controls panel
B737 NG
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8
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MASTER CAUTION SYSTEM – INTERFACES
Control of the System Annunciator Lights
The control of the left system annunciator lights come from these
components:
- Flight control panel (FLT CONT)
- IRS master caution unit (IRS)
- Flight control panel (FUEL)
- Generator drive and standby power panel (ELEC)
- APU indicator panel (APU)
- Overheat/fire protection panel (OVHT/DET)
The control of the right system annunciator lights come from these
components:
- Window heat panel (ANTI-ICE)
- Hydraulic panel (HYD)
- System annunciators (DOORS)
- Engine panel (ENG)
- Flight recorder/Mach airspeed warning panel (OVERHEAD)
- Air conditioning/bleed air control panel (AIR COND)
Resets
When you push the master caution light, you remove power to all the
master caution circuits. This causes the circuits to reset the master caution
annunciation. If a fault condition remains, the component warning light
remains on.
When you push the system annunciator lights, the recall signal goes to all
the components which cause the system annunciator lights to come on. All
the lights in the system annunciator come on while you push the lights.
When you release the lights, the system annunciator lights show which
systems have faults.
B737 NG
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MASTER CAUTION INTERFACES B737 NG
GEN FAM INDICATING & RECORDING
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AURAL WARNING SYSTEM - GENERAL DESCRIPTION
General
The aural warning module is the only component in aural warning system.
System monitor circuits detect incorrect system conditions and flight crew alerts.
The monitor circuits supply discrete signals to the aural warning module.
These are the discrete inputs to the aural warning system:
- Unsafe landing warning
- Unsafe takeoff warning
- Cabin pressure warning
- Autopilot disengage
- Overspeed warning
- Fire warning
- SELCAL
- Crew call
The aural warning module gives these sounds in the flight compartment:
- Fire bells
- Chimes
- Overspeed clackers
- Wailer
- Continuous horn
- Intermittent horn
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TAKEOFF AND LANDING WARNINGS –
OPERATION
Functional Description
The takeoff warning function is in the Proximity Switch Electronics Unit
(PSEU).
The aural warning module gives the sound of an intermittent horn for a
takeoff warning.
Takeoff
The airplane must be on the ground and you must move either thrust lever
to takeoff power (thrust resolver angle more than 53 degrees) before the
aural warning system gives the takeoff warning sound. The takeoff
warning occurs if any of these conditions occur:
- The stabilizer is out of the green band
- The TE flaps are not in a takeoff position
- The TE flaps are in a skew or asymmetry condition
- The TE flaps have an Uncommanded Motion (UCM)
- The LE flaps and slats are not extended
- The LE flaps and slats have an Uncommanded Motion (UCM)
- The ground spoilers have pressure
- The speedbrake lever is not down
- The parking brake is set
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ATA 32-00-00
LANDING GEAR
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CONTENTS
ATA 32 – LANDING GEAR
MAIN / NOSE LANDING GEAR AND DOORS – INTRODUCTION ............................................................................................................................................................. 4
PURPOSE (MAIN LANDING GEAR) ......................................................................................................................................................................................................................... 4
MAIN LANDING GEAR ........................................................................................................................................................................................................................................... 4
MAIN LANDING GEAR SHOCK STRUT DOORS ........................................................................................................................................................................................................ 4
TRAINING INFORMATION POINT............................................................................................................................................................................................................................. 4
PURPOSE (NOSE LANDING GEAR) .......................................................................................................................................................................................................................... 4
NOSE LANDING GEAR ............................................................................................................................................................................................................................................ 4
NOSE LANDING GEAR DOORS................................................................................................................................................................................................................................ 4
LANDING GEAR CONTROL SYSTEM - LEVER ASSEMBLY ..................................................................................................................................................................... 6
PURPOSE ................................................................................................................................................................................................................................................................ 6
PHYSICAL DESCRIPTION ........................................................................................................................................................................................................................................ 6
LOCATION .............................................................................................................................................................................................................................................................. 6
FUNCTIONAL DESCRIPTION.................................................................................................................................................................................................................................... 6
HYDRAULIC BRAKE SYSTEM - BRAKE ASSEMBLY ................................................................................................................................................................................. 8
GENERAL ............................................................................................................................................................................................................................................................... 8
PHYSICAL DESCRIPTION ........................................................................................................................................................................................................................................ 8
PARKING BRAKE SYSTEM – LINKAGE ....................................................................................................................................................................................................... 10
PURPOSE .............................................................................................................................................................................................................................................................. 10
LOCATION ............................................................................................................................................................................................................................................................ 10
FUNCTIONAL DESCRIPTION.................................................................................................................................................................................................................................. 10
ANTISKID/AUTOBRAKE SYSTEM - ANTISKID GENERAL DESCRIPTION ........................................................................................................................................ 12
PURPOSE .............................................................................................................................................................................................................................................................. 12
ANTISKID VALVES ............................................................................................................................................................................................................................................... 12
TRANSDUCER ....................................................................................................................................................................................................................................................... 12
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LANDING GEAR - DOWNLOCK PIN - MAIN LANDING GEAR ............................................................................................................................................................... 14
GENERAL ............................................................................................................................................................................................................................................................. 14
LANDING GEAR - DOWNLOCK PIN - NOSE LANDING GEAR ............................................................................................................................................................... 16
GENERAL ............................................................................................................................................................................................................................................................. 16
NOSE WHEEL STEERING SYSTEM - GENERAL DESCRIPTION ........................................................................................................................................................... 18
PURPOSE .............................................................................................................................................................................................................................................................. 18
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 18
NOSE WHEEL STEERING SYSTEM - STEERING METERING VALVE MODULE .............................................................................................................................. 20
GENERAL ............................................................................................................................................................................................................................................................. 20
LOCATION ............................................................................................................................................................................................................................................................ 20
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 20
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MAIN / NOSE LANDING GEAR AND DOORS –
INTRODUCTION
Training Information Point
Purpose (Main Landing Gear)
Be careful when you move around the inner door. The sharp point on the
inner door can cause injury to persons.
The two Main Landing Gear (MLG) absorb landing forces and hold most of
the airplane weight when the airplane makes a landing. The main landing
gear also transmits the braking forces to the airplane structure.
These are the landing gear structural systems:
Purpose (Nose Landing Gear)
- The main landing gear (MLG) and doors
- The nose landing gear (NLG) and doors
The nose landing gear absorbs landing forces and holds the forward part
of the airplane weight when the airplane makes a landing.
The nose landing gear doors open to permit gear operation. They close to
aerodynamically seal the nose landing gear wheel well.
The landing gear extension and retraction systems extend and retract the
landing gear.
Nose Landing Gear
Main Landing Gear
Each main landing gear has two wheels. The side strut holds the main
landing gear in the extended position. The side strut has an upper and a
lower part. A downlock strut moves to an over-centre position to lock the
main landing gear in the down position.
A jack pad is on the bottom of the shock strut. The jack pad permits the
inner cylinder to be moved up for wheel and tire replacement.
The nose landing gear is a conventional two wheel gear. A drag strut
holds the nose gear in the extended or retracted position. The drag strut
has a upper and lower part. A lock link moves to an over-centre position to
lock the drag strut in both up and down positions.
A tow fitting is between the nose landing gear tires.
A jack pad is on the bottom of the shock strut.
You can disconnect the torsion links to permit the nose landing gear to
move more than the normal steering limits (78 degrees).
Main Landing Gear Shock Strut Doors
Nose Landing Gear Doors
The MLG shock strut doors open to let the main landing gear extend and
retract. The doors aerodynamically seal the opening in the lower surface
of the wing and the wing to body fairing.
There are no wheel well doors. The outboard surface of the outboard
wheels operates as aerodynamic covers for the main gear wheel well
when the main landing gear retracts. The wheel well seal system supplies
an aerodynamic seal around the outboard tire.
Two doors aerodynamically seal the nose landing gear wheel well to
decrease drag. The doors attach to the outboard edges of the nose
landing gear wheel well. The doors connect to the shock strut and move
mechanically when the nose landing gear extends or retracts.
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LANDING GEAR CONTROL SYSTEM - LEVER
ASSEMBLY
When the airplane takes off, the solenoid gets electrical power and
releases the lever lock.
Purpose
The landing gear control lever assembly operates the landing gear
selector valve through the landing gear control cables.
Physical Description
The control lever assembly has these components:
- Control lever
- Position switch (4)
- Lock mechanism
- Lever lock solenoid
Location
The landing gear control lever is on the P2 centre forward panel in the
flight compartment.
Functional Description
The landing gear control lever has these three positions with detents:
- UP
- OFF
- DOWN
You must first pull the control lever out before you can move the lever. The
lever operates a push-pull cable which moves the forward quadrant. The
forward quadrant is below the flight compartment floor.
The control lever assembly has a lever lock mechanism operated by a
lever lock solenoid. The lever lock prevents accidental movement of the
landing gear lever to the up position when the airplane is on the ground.
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HYDRAULIC BRAKE SYSTEM - BRAKE
ASSEMBLY
General
A torque takeout slot on the brake assembly aligns with a torque pin on
the bottom of the main landing gear inner cylinder.
The main landing gear wheel brakes use hydraulic pressure to slow or
stop the airplane during landing and taxi.
Each main landing gear wheel brake has these components:
The slot and pin transmit brake torque to the main landing gear strut.
- Stators· Rotors
- Pressure plate
- Piston/adjusters (6)
- Axle bushings
- Wear indicator pins (2)
- Brake hose connection/hydraulic bleed port
Physical Description
The brake assembly is a rotor-stator unit that operates using hydraulic
pressure.
The assembly uses multiple steel discs as rotors and stators.
Piston/adjuster assemblies apply brake system hydraulic pressure to the
pressure plate. The pressure plate forces the stators and rotors together in
the brake housing. This slows or stops the wheel. The pistons
automatically adjust for brake wear.
Two indicator pins on the inboard side of the brake housing show brake
wear.
You must apply the brakes to check the wear indicator pins.
The brake assembly has bushings. These bushings attach to replaceable
sleeves on the landing gear axle.
A retention cable connects both brakes together on each main landing
gear.
The cable keeps the brake on the axle if the wheel falls off the airplane.
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PARKING BRAKE SYSTEM – LINKAGE
Purpose
The parking brake linkage mechanically locks the brake pedals in the applied
position.
These are the parking brake linkage components:
- Parking brake lever
- Parking brake switch
- Latch pawls (2)
- Return spring
Location
The parking brake linkage is in the forward equipment compartment below the
captains brake pedals.
The parking brake switch is on the parking brake linkage.
Functional Description
When you push the brake pedals and pull the parking brake lever up, these
things occur:
- The brake pedals move the vertical control rods down
- The vertical control rods move the pawl stop down
- The parking brake lever moves the linkage and the bellcrank
- The bellcrank turns the latch pawl
- The latch pawl holds the pawl stop down when the brake pedals are released
- The parking brake switch moves to the closed position
- You can then release the parking brake lever
- This keeps the captains and first officers brake pedals in the applied position.
To release the parking brakes, momentarily push on the brake pedals. This
moves the pawl stop down and the return spring turns the latch pawl. When you
release the pedals, the pedals move to the brakes off position.
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ANTISKID/AUTOBRAKE SYSTEM - ANTISKID
GENERAL DESCRIPTION
Purpose
The antiskid system controls the metered brake pressure from the
hydraulic brake system or the autobrake pressure from the autobrake
system to prevent wheel skid. This gives maximum brake force to stop the
airplane with any runway condition.
These are the antiskid components:
- Antiskid valves (6)
- Transducers (4)
- Landing gear lever up switch
- Alternate brake pressure switch
- Antiskid/Autobrake Control Unit (AACU)
- Antiskid inoperative amber light
Antiskid Valves
Four antiskid valves in the normal hydraulic brake system control brake
pressure to each wheel brake. Two antiskid valves in the alternate
hydraulic brake system control brake pressure to the wheel brakes on
each main landing gear.
Transducer
A transducer in each main landing gear wheel axle supplies wheel speed
data to the AACU.
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LANDING GEAR - DOWNLOCK PIN - MAIN
LANDING GEAR
General
You install a downlock pin into the main landing gear to make sure an
outside force does not unlock the main landing gear.
There is one main landing gear downlock pin for each main landing gear.
The downlock pin installs in the MLG downlock strut.
WARNING: YOU MUST CAREFULLY INSTALL THE GROUND LOCKS
IN ALL LANDING GEAR. AN ACCIDENTAL RETRACTION OF THE
LANDING GEAR CAN CAUSE INJURY TO PERSONS AND DAMAGE
TO EQUIPMENT.
B737 NG
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LANDING GEAR - DOWNLOCK PIN - NOSE
LANDING GEAR
General
You install a downlock pin into the nose landing gear to make sure an
outside force does not unlock the nose landing gear.
There is one nose landing gear downlock pin for the nose landing gear.
The nose landing gear downlock pin installs in the NLG downlock pin hole.
WARNING: YOU MUST CAREFULLY INSTALL THE GROUND LOCKS
IN ALL LANDING GEAR. AN ACCIDENTAL RETRACTION OF THE
LANDING GEAR CAN CAUSE INJURY TO PERSONS AND DAMAGE
TO EQUIPMENT.
B737 NG
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NOSE WHEEL STEERING SYSTEM - GENERAL
DESCRIPTION
Purpose
The landing gear transfer valve changes the pressure supply of nose
wheel steering from hydraulic system A to hydraulic system B. You
manually control the landing gear transfer valve with the alternate nose
wheel steering switch in the flight compartment.
The nose wheel steering system supplies the ground directional control of
the airplane.
General Description
These conditions cause the manual operation of the landing gear transfer
valve:
Steering inputs are from the steering wheel or the rudder pedals. When
you move the steering wheel full travel, the nose wheels turn a maximum
of 78 degrees in the left or right direction. When you move the rudder
pedals full travel on the ground, the nose wheels turn a maximum of 7
degrees in the left or right direction. Steering inputs from the steering
wheel or rudder pedals go to the metering valve through a cable loop.
* Alternate nose wheel steering switch to the alternate position
* Normal quantity in system B reservoir
* Nose air/ground system in ground mode.
The steering metering valve supplies right turn or left turn pressure to the
steering actuators.
The rotary actuator disconnects the rudder pedal input in the air.
CAUTION: DO NOT OPERATE THE STEERING WHEEL WITH
THE SHOCK STRUT FULLY EXTENDED AND THE TORSION LINKS
CONNECTED. DAMAGE TO THE CENTERING CAMS OF THE SHOCK
STRUT CAN OCCUR. IF IT IS NECESSARY TO OPERATE THE
STEERING SYSTEM, MAKE SURE THAT YOU COMPRESS THE
SHOCK STRUT TO 2.10 INCHES OR MORE. MAKE SURE THAT THE
DISTANCE BETWEEN THE BOTTOM SURFACE OF THE LOWER
STEERING PLATE AND THE TOP SURFACE OF THE TOWING LUG IS
LESS THAN 21.90 INCHES.
Hydraulic system A usually supplies pressure to extend and retract the
main landing gear. The extend pressure from the landing gear extension
and retraction system supplies pressure for nose wheel steering.
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NOSE WHEEL STEERING SYSTEM - STEERING
METERING VALVE MODULE
General
The steering metering valve module controls the flow of hydraulic pressure
to the steering actuators.
Location
The steering metering valve is on the upper steering plate on the front of
the nose landing gear.
Physical Description
A towing lever on the steering metering valve module controls a towing
shutoff valve.
The towing lever lets you depressurize the nose wheel steering system.
Because of this, you do not have to depressurize hydraulic system A to
tow the airplane.
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INTENTIONALLY LEFT BLANK
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ATA 36-00-00
PNEUMATICS
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CONTENTS
ATA 36 – PNEUMATICS
PNEUMATIC – INTRODUCTION ...................................................................................................................................................................................................................... 4
PURPOSE ................................................................................................................................................................................................................................................................ 4
GENERAL DESCRIPTION ......................................................................................................................................................................................................................................... 4
PNEUMATIC - FUNCTIONAL DESCRIPTION ............................................................................................................................................................................................... 6
GENERAL ............................................................................................................................................................................................................................................................... 6
ENGINE BLEED AIR ................................................................................................................................................................................................................................................ 6
ENGINE BLEED AIR PRECOOLER SYSTEM .............................................................................................................................................................................................................. 6
APU BLEED AIR .................................................................................................................................................................................................................................................... 6
PNEUMATIC MANIFOLD ......................................................................................................................................................................................................................................... 6
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PNEUMATIC – INTRODUCTION
Purpose
The pneumatic system supplies compressed air to the airplane user
systems.
The controls and indications use these types of electric power:
General Description
- 28vdc
- 115vac
These are the sources of pneumatic power:
CAUTION: The air in the pneumatic system is hot and under great
pressure.
Make sure you depressurize the pneumatic system before you work on it.
- Engine 1 bleed air system
- Engine 2 bleed air system
- Auxiliary Power Unit (APU) bleed air system
- Pneumatic ground air connection
The pneumatic manifold collects the compressed air from the sources and
supplies it to the user systems.
Valves in the manifold do these things:
- Control the flow of bleed air into the manifold
- Isolate the manifold into left and right sides
- Control the flow of manifold air into the user systems
These are the airplane systems that use pneumatic power:
- Engine start systems
- Air conditioning and pressurization systems
- Engine inlet cowl anti-ice systems
- Wing thermal anti-ice systems
- Water tank pressurization system
- Hydraulic reservoir pressurization system
The pneumatic system controls and indications are on the P5-10 panel.
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PNEUMATIC - FUNCTIONAL DESCRIPTION
General
Engine Bleed Air Precooler System
The pneumatic system supplies hot, high pressure air to the systems on
the airplane that use air.
These are the sources of pneumatic power:
The precooler system controls the engine bleed air temperature. The
precooler system cools the engine bleed air with engine fan air. The
precooler system operation is automatic and uses pneumatic control.
APU Bleed Air
- Engine bleed air
- APU load compressor
- Ground source
The APU load compressor supplies compressed air to the pneumatic
manifold. The load compressor inlet guide vane and surge valve systems
control the flow and pressure of the air. The APU Bleed Air Valve (BAV)
controls the flow of air from the load compressor to the pneumatic
manifold. The APU BAV operates from pneumatic pressure. It gets
electrical control from the APU ECU.
The APU ECU gets signals from these sources:
Engine Bleed Air
There is one bleed air system for each engine. The engine bleed system
controls bleed air temperature and pressure.
Engine bleed air comes from the 5th and 9th stages of the high pressure
compressor. A high stage valve system controls the flow of 9th stage
bleed air.
The high stage system is pneumatic and has no electric controls.
The Pressure Regulator and Shutoff Valve (PRSOV) controls the flow and
pressure of the engine bleed air. Control pressure from the Bleed Air
Regulator (BAR) operates the PRSOV. The Air Conditioning Accessory
Unit (ACAU) electrically controls the BAR.
The ACAU receives signals from these components:
- The P5-10 APU BLEED switch
- APU sensors and switches
- Airplane logic
Pneumatic Manifold
The pneumatic manifold gets high pressure air from the source systems
and supplies it to the user systems.
The pneumatic manifold has these features:
- P8-1 fire control panel engine FIRE switch
- P5-10 air conditioning panel engine BLEED switch
- 490F (254C) over temperature and 220 psi overpressure switches
(BLEED
TRIP OFF protection)
- The Display Electronics Unit (DEU) (engine start reverse flow protection)
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- An isolation valve that can separate the manifold into left and right sides
- Two duct pressure transmitters (for left and right manifold pressure
indication)
- A ground pneumatic connector with a check valve (for an external source
of pneumatic power)
- Pressure taps and interfaces for user system valves.
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ATA 49-00-00
APU
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CONTENTS
ATA 49 – APU
AIRBORNE AUXILIARY POWER – INTRODUCTION ................................................................................................................................................................................. 4
PURPOSE ................................................................................................................................................................................................................................................................ 4
ALTITUDE OPERATIONAL LIMITS........................................................................................................................................................................................................................... 4
APU ENGINE – INTRODUCTION ...................................................................................................................................................................................................................... 6
PURPOSE ................................................................................................................................................................................................................................................................ 6
GENERAL DESCRIPTION ......................................................................................................................................................................................................................................... 6
AIRBORNE AUXILIARY POWER - APU COOLING ..................................................................................................................................................................................... 8
GENERAL ............................................................................................................................................................................................................................................................... 8
COMPARTMENT COOLING ...................................................................................................................................................................................................................................... 8
MISCELLANEOUS EXTERIOR SERVICE DOORS – APU ACCESS DOOR ............................................................................................................................................ 10
PURPOSE .............................................................................................................................................................................................................................................................. 10
DOOR FRAME AND STRUCTURE ........................................................................................................................................................................................................................... 10
HINGES ................................................................................................................................................................................................................................................................ 10
LATCHES .............................................................................................................................................................................................................................................................. 10
DOOR SUPPORT RODS .......................................................................................................................................................................................................................................... 10
FLUID DRAIN SYSTEM ......................................................................................................................................................................................................................................... 10
LOWER APU FIRE DETECTION ELEMENT ............................................................................................................................................................................................................ 10
APU POWER PLANT - AIR INLET DOOR COMPONENTS ....................................................................................................................................................................... 12
PURPOSE .............................................................................................................................................................................................................................................................. 12
AIR INLET DOOR ACTUATOR ............................................................................................................................................................................................................................... 12
AIR INLET DOOR SWITCH .................................................................................................................................................................................................................................... 12
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 12
APU CONTROLS – INTRODUCTION ............................................................................................................................................................................................................. 14
PURPOSE .............................................................................................................................................................................................................................................................. 14
FLIGHT COMPARTMENT CONTROLS AND PANELS ................................................................................................................................................................................................ 14
OTHER CONTROL COMPONENTS .......................................................................................................................................................................................................................... 14
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AIRBORNE AUXILIARY POWER –
INTRODUCTION
Purpose
The AlliedSignal 131-9(B) Auxiliary Power Unit (APU) supplies electrical
and pneumatic power to other airplane systems. This permits airplane
systems to operate without the use of ground power sources or the
engines. The APU can also supply electrical and pneumatic power in the
air.
Altitude Operational Limits
The APU generator can supply 90 KVA electrical power up to 32,000 feet
(9,754 meters) and 66 KVA to 41,000 feet (12,500 meters). Electrical and
pneumatic power is available at the same time up to 10,000 feet (3,048
meters).
Pneumatic power alone is available up to 17,000 feet (5,183 meters).
The APU can be started at 41,000 feet or below.
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APU ENGINE – INTRODUCTION
Purpose
The APU engine supplies power to operate the load compressor and the
APU starter-generator.
General Description
The APU engine has these main sections:
- Accessory gear box
- Single stage load compressor
- Single stage engine compressor
- Combustor chamber
- Two stage axial flow turbine
All the components in the engine that turn are on a common shaft.
The shaft turns the accessory gearbox and the load compressor. The
accessory gear box turns the APU generator and other components.
The engine operates at a constant speed to provide 400 Hz generator
output.
The APU engine also supplies air for airplane systems.
An inlet screen prevents Foreign Object Damage (FOD) to the APU
compressors.
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AIRBORNE AUXILIARY POWER - APU COOLING
General
The APU cooling air system cools the APU compartment and the APU
engine oil.
Compartment Cooling
APU compartment cooling uses an eductor to pull outside air through the
APU compartment. The high speed flow of the APU exhaust forms a low
pressure area. This low pressure pulls outside air through the eductor inlet
duct to the APU compartment. The cooling air then goes through the oil
cooler and out the APU exhaust duct.
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MISCELLANEOUS EXTERIOR SERVICE DOORS –
APU ACCESS DOOR
Latches
Purpose
Three push-button latches hold the door closed. Moderate pressure on the
push-button trigger will cause the latch to open. They are a fail-safe
design.
Failure of the trigger return mechanism will not cause the latch to open.
When the latch is secure, the outer surface is similar in colour to adjacent
structure. The other surfaces of the latch are a bright red fluorescent
colour.
This allows rapid visual detection of an unsecure latch.
The APU access door gives access to the APU and its accessories.
Location
The APU access door is part of the lower surface of the fuselage. It is
under the horizontal stabilizer.
General Description
Door Support Rods
The APU access door has hinges on the right side. Three latches on the
left side hold the door closed. The door swings downward as it opens.
The APU access door has these parts:
Door support rods hold the door in the open position. You deploy and stow
the support rods manually.
- Door frame and structure
- Hinges
- Latches
- Door support rods
- Fluid drain system
- Lower APU fire detection element
- Fire resistant liner and insulation
Fluid Drain System
A fluid drain system drains fluids from the APU compartment. Fluid
collects in drain cups and flows in drain lines to the drain mast. The fluids
then drain overboard through the mast. The drain mast has been relocated
to an area forward of the APU access door.
Door Frame and Structure
Lower APU Fire Detection Element
The door frame and structure is aluminium alloy extrusions and clad
aluminium alloy sheet. The door does not hold pressure.
The lower APU fire detection element is on the inner door liner.
Hinges
Fire Resistant Liner and Insulation
Two hinges give the door a pivot axis. You remove the hinge pins to
remove the door.
B737 NG
GEN FAM APU
REFRESHER COURSE
The inner surface of the door is fire resistant. The inside surface is
covered with an insulating blanket and a titanium fire wall liner.
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APU POWER PLANT - AIR INLET DOOR
COMPONENTS
Purpose
The air inlet door opens to let air into the engine and load compressor.
The air inlet door closes at shutdown.
The air inlet door is on the right forward side of the aft fuselage.
Air Inlet Door Actuator
The air inlet door actuator is a rotary electric actuator that opens and
closes the air inlet door. The air inlet door actuator is on the inboard side
of the inlet door housing forward of the APU compartment.
Air Inlet Door Switch
The air inlet door switch supplies a door open and door not open signal to
the ECU. The switch is on the inboard side of the inlet door housing.
Training Information Point
You can open the air inlet door without a start cycle on the APU. To open
the door, put the APU switch to the ON position.
The air inlet door does not fully close. This prevents APU rotation during
flight when the APU air inlet door is in the closed position.
The air inlet door and actuator are adjustable.
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APU CONTROLS – INTRODUCTION
Purpose
The APU controls provide control for the APU for all operating conditions.
Flight Compartment Controls and Panels
These are the APU controls and panels in the flight compartment:
- APU switch (P5)
- APU bleed air switch (P5)
- APU generator switch (P5)
- APU fire warning switch (P8)
Other Control Components
The P28 APU remote control panel is on the right wheel well aft bulkhead.
The Electronic Control Unit (ECU) controls the APU operation when the
ECU receives a signal from the controls in the flight compartment. The
ECU is in the aft cargo compartment right side.
The ECU also uses signals from certain APU and airplane systems for
correct operation of the APU.
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ATA 52-00-00
DOORS
B737 NG
GEN FAM DOORS
REFRESHER COURSE
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CONTENTS
ATA 52 – DOORS
DOORS – INTRODUCTION ................................................................................................................................................................................................................................. 4
PURPOSE ................................................................................................................................................................................................................................................................ 4
GENERAL DESCRIPTION ......................................................................................................................................................................................................................................... 4
LOCATION .............................................................................................................................................................................................................................................................. 4
TRAINING INFORMATION POINT............................................................................................................................................................................................................................. 4
FORWARD ENTRY DOOR .................................................................................................................................................................................................................................. 6
PURPOSE ................................................................................................................................................................................................................................................................ 6
GENERAL DESCRIPTION ......................................................................................................................................................................................................................................... 6
DOOR CONTROL MECHANISMS .............................................................................................................................................................................................................................. 6
DOOR SUPPORT ...................................................................................................................................................................................................................................................... 6
DOOR SEALS .......................................................................................................................................................................................................................................................... 6
DOOR DRAINS ........................................................................................................................................................................................................................................................ 6
DOOR WARNING .................................................................................................................................................................................................................................................... 6
TRAINING INFORMATION POINT............................................................................................................................................................................................................................. 6
ENTRY AND SERVICE DOOR - ESCAPE SLIDES ......................................................................................................................................................................................... 8
PURPOSE ................................................................................................................................................................................................................................................................ 8
PHYSICAL DESCRIPTION ........................................................................................................................................................................................................................................ 8
LOCATION .............................................................................................................................................................................................................................................................. 8
TRAINING INFORMATION POINT............................................................................................................................................................................................................................. 8
ENTRY AND SERVICE DOOR - ESCAPE SLIDE OPERATION ................................................................................................................................................................ 10
OPERATION .......................................................................................................................................................................................................................................................... 10
EMERGENCY EXIT DOOR – INTRODUCTION ........................................................................................................................................................................................... 12
PURPOSE .............................................................................................................................................................................................................................................................. 12
LOCATION ............................................................................................................................................................................................................................................................ 12
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 12
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DOORS - CARGO - INTRODUCTION ............................................................................................................................................................................................................. 14
LOCATION ............................................................................................................................................................................................................................................................ 14
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 14
DOOR WARNING .................................................................................................................................................................................................................................................. 14
DOORS - FORWARD AIRSTAIR AND DOOR – AIRSTAIR ........................................................................................................................................................................ 16
PURPOSE .............................................................................................................................................................................................................................................................. 16
LOCATION ............................................................................................................................................................................................................................................................ 16
PHYSICAL DESCRIPTION ...................................................................................................................................................................................................................................... 16
GENERAL DESCRIPTION ....................................................................................................................................................................................................................................... 16
OPERATIONAL DISPLAYS ..................................................................................................................................................................................................................................... 16
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 16
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DOORS – INTRODUCTION
Purpose
Training Information Point
The doors are removable units that give access to the airplane
compartments.
You can open and close entry, galley service, and cargo doors in winds up
to 40 knots without structural damage. You can let these doors stay
latched open in winds up to 65 knots without structural damage.
If a door is left open for a long time, a protective cover should be put over
the door frame. This prevents bad weather damage to the airplane.
General Description
These are the types of doors on the airplane:
- Forward and aft entry doors
- Forward and aft galley service doors
- Emergency exit hatches (including pilots’ sliding windows)
- Cargo doors
- Interior doors (crew door and lavatory doors)
- Miscellaneous access doors
A door warning system shows the crew that pressure bearing doors are
closed and properly latched before flight.
All doors have silicon rubber seals. The seals do these things:
- Seal air and light leaks
- Act as acoustic and thermal barriers
- Supply aerodynamic smoothness
Location
The entry doors are on the left side of the airplane.
The galley service doors are on the right side of the airplane.
The pilots’ sliding windows are in the flight compartment.
The cargo doors are on the right side of the airplane.
The crew door and lavatory doors are inside the airplane.
The miscellaneous access doors are near the systems they serve.
B737 NG
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FORWARD ENTRY DOOR
Purpose
To close the door, first release the hinge lock and then do the open
operations in reverse order.
A guide pin on the door and a guide pin track on the door frame align the
door in the door frame as it closes.
The forward entry door gives access to the airplane passenger cabin.
Location
The forward entry door is on the left side of the upper, forward fuselage.
General Description
Door Support
The forward entry door is the largest passenger entry door on the airplane.
The door is a plug-type door.
The door has these parts:
When the airplane is unpressurized, the hinges support the door. When
the airplane is pressurized, cabin pressure pushed the door slightly
outboard. This causes the door seals to compress and the door stop pins
contact the frame stop fittings. This transmits the door pressure loads to
the door frame structure which unloads the door latches.
- Centre door assembly
- Upper gate
- Lower gate
Door Seals
A liner covers the door’s interior surface. The centre door assembly has
hard points at the bottom for the emergency escape slide installation. The
centre door assembly has a window.
The door has edge seals (flap and bulb type) and gate hinge seals
(diaphragm type).
Door Drains
Door Control Mechanisms
The door structure has internal drain paths. The door sections drain into
the door frame threshold. The door threshold drains overboard through
bladders in the lower fuselage.
You can open and close the door from the interior or exterior of the
airplane. You operate the door manually. Unlatch the door with the control
handle. When you turn the handle in the OPEN direction, internal
mechanisms do these things:
Door Warning
The forward entry door has an interface with the door warning system.
There is a proximity switch assembly on the door frame adjacent to an
upper latch track.
The switch senses the position of the door latch roller. When the door is
latched, it causes the P5 panel warning light to go out.
- Disengage the door roller latches
- Fold the door gates inward
- Tilt the door’s hinge edge inward to the cocked position
Then push the door through the door frame until it is fully open. Use the
assist handles for this operation.
A lock mechanism in the upper hinge locks the door in the fully open
position.
B737 NG
GEN FAM DOORS
REFRESHER COURSE
Training Information Point
The forward entry door is used as an example. All entry and galley service
doors are similar in construction and operation.
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ENTRY AND SERVICE DOOR - ESCAPE SLIDES
Each slide has these additional features:
Purpose
- Lifelines
- Mooring line with a frangible link
- Red handgrips
Escape slides help passengers and crew evacuate the airplane in an
emergency. If the airplane lands in water, you may disconnect the escape
slides from the airplane and use them as flotation devices.
Location
Physical Description
An escape slide is on the lower inboard face of each entry and service
door.
Escape slides are made of neoprene-coated nylon fabric. An aluminium
coating provides protection from the effects of radiant heat. The sliding
surface is a high strength, urethane-coated, nylon fabric.
Each escape slide packs in a valise and stows inside a compartment on
the aircraft exit door.
Escape slides have quick-release detachable girts. This feature allows the
escape slides to separate easily from the aircraft so you may use them as
flotation devices in the event of a ditching. It also provides for simple girt
replacement.
Each escape slide installation has these parts:
Training Information Point
You arm and disarm the escape slide manually. When the escape slide is
armed, the girt bar is secure in the escape slide floor brackets. When the
escape slide is stowed (not armed), the girt bar is in the girt bar retainer
hooks.
Make sure the slide is not armed before you open the door. If you open
the door when the slide is armed, the slide will deploy.
- Escape slide compartment
- Escape slide pack
- Two floor brackets
The escape slide compartment holds the slide pack in the stowed position
and opens when you use the slide.
The escape slide pack is inside the escape slide compartment.
The entire assembly attaches to the lower inboard face of each entry and
service door.
The floor brackets are at the forward and aft ends of the doorways,
inboard of the door sill.
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ENTRY AND SERVICE DOOR - ESCAPE SLIDE
OPERATION
Operation
To arm the escape slide, remove the girt bar from the stowage hooks on
the door and install it in the floor brackets.
Open the door as usual but do not hesitate until it is fully open.
The girt strap will extend while you open the door.
As you open the door, the girt latch assembly will let the slide pack fall out
of the slide cover.
As the slide pack falls, it will start the slide inflation.
The escape slide will fully inflate in approximately six seconds.
If the escape slide does not inflate automatically, pull the inflation handle
sharply to inflate the escape slide manually.
To remove the escape slide from the airplane, lift the cover flap and pull
the girt release handle.
The escape slide will remain connected to the airplane by the mooring line
until the line is released, cut, or the frangible link breaks under load.
Activation of the incandescent lighting system is automatic during inflation
of the slide.
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EMERGENCY EXIT DOOR – INTRODUCTION
Purpose
Emergency exit doors supply additional exits for the passengers in the
event of an emergency.
Location
The emergency exit doors are above the wings.
General Description
There are four emergency exit doors on the 800 and two on the 700 and
600 aircraft.
They all have the same construction features, but are adjusted separately
to fit their fuselage frames. The doors have a window with an internal
shade.
An EXIT light attaches to the door cut-out lining above each door. An
independent wash light fixture below the sign illuminates the hatch area.
You can open the emergency exit door from inside or outside the airplane.
The emergency exit doors operate with a spring loaded vent panel at the
top of the hatch.
The emergency exit doors connects with the door warning system. Each
hatch frame has a switch on two of its latch tracks. A latch roller actuates
the switch.
With the hatch locked the P5 panel OVERWING EXIT warning lights goes
out.
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DOORS - CARGO - INTRODUCTION
Door Warning
Location
The cargo doors have an interface with the door warning system. Each
door has a switch on its latch mechanism, and a warning light on the P5
forward overhead panel.
The cargo compartment doors are on the right side of the fuselage, on the
lower lobe, forward and aft of the wing.
General Description
These are the two cargo doors:
- Forward cargo door
- Aft cargo door.
The doors are similar in shape, design, and operation, but they are slightly
different in size.
The doors are plug-type. They open inward, and hinge at the top. Seals
around the door edge and door handle shaft prevent pressurization loss.
You operate the doors manually. This may be done from outside of the
airplane or from inside the cargo compartment. A counter balance inside
the door reduces the effort necessary to lift the door. An uplock detent in
the counter balance mechanism holds the door in the fully open position. A
door snubber makes sure the door does not fall quickly if the counter
balance mechanism fails.
A manual strap device in the cargo compartment ceiling can be used to
hold the door in the fully open position.
A bungee lanyard with a soft-grip handle on the door makes it easy to
lower the door.
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DOORS - FORWARD AIRSTAIR AND DOOR –
AIRSTAIR
Purpose
The NORMAL mode uses airplane ac and dc power for operation.
The STANDBY mode uses airplane dc and/or battery dc power. Battery
power is locked out when there is a supply of airplane dc power.
The forward airstair lets passengers and crew enter and exit the airplane
without any ground support equipment.
Location
You can operate the airstair from inside or outside the airplane.
The forward airstair is below the forward entry door.
The interior control panel is on the forward attendant’s panel.
The exterior control panel is aft of the airstair door on the fuselage skin.
Mechanical and electrical interlocks prevent the accidental extension of
the airstair in flight. The mechanical interlock is a lock pin that prevents the
airstair door from opening. The electrical interlock is a circuit that disarms
the interior control panel when the airplane is not on the ground.
Physical Description
The forward airstair has these parts:
Operational Displays
- Carriage
- Upper ladder
- Lower ladder
- Handrails with extensions
- Interior and exterior controls.
The STAIRS OPERATING light on the interior control panel comes on
during airstair operation. The light stays on as long as the airstair or
airstair door is in any position other than end of extension or retraction.
The airstair is part of the door warning system. The amber
AIRSTAIR light comes on panel P5 when the airstair door is not closed
and locked.
General Description
The airstair design allows for a height deviation from the airstair to the
ground of 15 inches. This compensates for airplane loading and field
deviations from level.
The airstair is an electromechanical system and can operate in these
modes:
Training Information Point
Do not operate the airstair when the airplane is jacked.
Do not operate the airstair in any attitude that prevents the lower ladder
from firm ground contact.
Do not load the airstair if the lower ladder is not firmly on the ground or
damage may result.
- NORMAL mode when there is a supply of ac and dc power
- STANDBY mode for operations when ac power is not available, or there
is a failure in the normal circuits
- Manually in the event of failure of all electric circuits.
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ATA 70/80-00-00
CFM56-7 ENGINE
B737 NG
GEN FAM ENGINE
REFRESHER COURSE
1
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70/80-00-00
Version 1
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CONTENTS
ATA 70/80– CFM56-7 ENGINE
ENGINE – INTRODUCTION ............................................................................................................................................................................................................................... 4
GENERAL ............................................................................................................................................................................................................................................................... 4
ENGINE - GENERAL DESCRIPTION ............................................................................................................................................................................................................... 6
GENERAL ............................................................................................................................................................................................................................................................... 6
FAN AND BOOSTER / LOW PRESSURE COMPRESSOR (LPC) ................................................................................................................................................................................... 6
HIGH PRESSURE COMPRESSOR (HPC) ................................................................................................................................................................................................................... 6
COMBUSTOR .......................................................................................................................................................................................................................................................... 6
POWER PLANT - ENGINE COWLING ............................................................................................................................................................................................................. 8
GENERAL ............................................................................................................................................................................................................................................................... 8
INLET COWL .......................................................................................................................................................................................................................................................... 8
FAN COWLS ........................................................................................................................................................................................................................................................... 8
IDG ACCESS DOOR ................................................................................................................................................................................................................................................ 8
CHIP DETECTOR/PRESSURE RELIEF DOOR ............................................................................................................................................................................................................. 8
VORTEX CONTROL DEVICE.................................................................................................................................................................................................................................... 8
OIL TANK ACCESS DOOR ....................................................................................................................................................................................................................................... 8
POWER PLANT - FAN COWL .......................................................................................................................................................................................................................... 10
GENERAL ............................................................................................................................................................................................................................................................. 10
FAN COWL LATCHES ........................................................................................................................................................................................................................................... 10
FAN COWL HOLD OPEN RODS ............................................................................................................................................................................................................................. 10
THRUST REVERSER - TENSION LATCHES ................................................................................................................................................................................................ 12
PURPOSE .............................................................................................................................................................................................................................................................. 12
GENERAL ............................................................................................................................................................................................................................................................. 12
LOCATION ............................................................................................................................................................................................................................................................ 12
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 12
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REFRESHER COURSE
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THRUST REVERSER - THRUST REVERSER OPENING ACTUATOR .................................................................................................................................................... 14
PURPOSE .............................................................................................................................................................................................................................................................. 14
LOCATION ............................................................................................................................................................................................................................................................ 14
FUNCTIONAL DESCRIPTION.................................................................................................................................................................................................................................. 14
OPERATION .......................................................................................................................................................................................................................................................... 14
TRAINING INFORMATION POINT........................................................................................................................................................................................................................... 14
ENGINE CONTROLS - GENERAL DESCRIPTION ...................................................................................................................................................................................... 16
GENERAL ............................................................................................................................................................................................................................................................. 16
THRUST LEVERS .................................................................................................................................................................................................................................................. 16
START LEVERS ..................................................................................................................................................................................................................................................... 16
REVERSE THRUST INTERLOCK SOLENOIDS .......................................................................................................................................................................................................... 16
ENGINE CONTROL - ELECTRONIC ENGINE CONTROL (EEC) ............................................................................................................................................................ 18
GENERAL ............................................................................................................................................................................................................................................................. 18
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ENGINE – INTRODUCTION
General
General engine data for the CFM56-7 engine is shown.
These items show on the engine nameplate:
- Regulatory agency data
- Engine manufacture data
- Engine performance data
Six additional blank lines are available to show performance information if
the engine thrust rating changes.
This permits six different thrust rating changes before you must replace
the nameplate.
The nameplate also shows the thrust rating history of the engine.
The engine nameplate is on the right fan case aft of the oil tank. B737 NG
GEN FAM ENGINE
REFRESHER COURSE
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ENGINE - GENERAL DESCRIPTION
General
High Pressure Compressor (HPC)
The CFM56-7 is a high bypass, dual rotor, axial flow turbofan engine. The
engine fan diameter is 61 inches (1.55 meters). The bare engine weight is
5257 pounds (2385 kilograms).
The engine has these sections:
The HPC is a nine-stage compressor. It increases the pressure of the air
from the LPC and sends it to the combustor. The HPC also supplies bleed
air for the aircraft pneumatic system and the engine air system.
- Fan and booster / Low Pressure Compressor (LPC)
- High Pressure Compressor (HPC)
- Combustor
- High Pressure Turbine (HPT)
- Low Pressure Turbine (LPT)
- Accessory drive
The combustor mixes air from the compressors and fuel from the fuel
nozzles. This mixture of air and fuel burns in the combustion chamber to
make hot gases. The hot gases go to the HPT.
Combustor
High Pressure Turbine (HPT)
The HPT is a single-stage turbine. It changes the energy of the hot gases
into a mechanical energy. The HPT uses this mechanical energy to turn
the HPC rotor and the accessory drive.
The fan and booster rotor and the LPT rotor are on the same low pressure
shaft (N1). The HPC rotor and HPT rotor are on the same high pressure
shaft (N2).
Low Pressure Turbine (LPT)
Fan and Booster / Low Pressure Compressor (LPC)
The LPT is a four-stage turbine. It changes the energy of the hot gases
into a mechanical energy. The LPT uses this mechanical energy to turn
the fan and booster rotor.
The fan and booster is a four-stage compressor. The fan increases the
speed of the air.
The primary air flow goes into the core of the engine. The booster
increases the pressure of this air and sends it to the HPC. The secondary
air flow goes in the fan duct. It supplies approximately 80 percent of the
thrust during take-off.
Accessory Drive
The accessory drive is driven by the N2 shaft and operates the airplane
accessories and the engine accessories.
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POWER PLANT - ENGINE COWLING
IDG Access Door
General
The IDG access door permits access to the IDG for servicing. It is on the
left fan cowl panel.
The engine cowling gives an aerodynamically smooth surface into and
over the engine. It also gives a protective area for engine components and
accessories.
These are the parts of the engine cowling:
Chip Detector/Pressure Relief Door
The chip detector access door permits access to the chip detectors. It also
is a pressure relief door. It is on the left fan cowl.
- Inlet cowl
- Fan cowl
- Thrust reverser
Vortex Control Device
Inlet Cowl
The vortex control device smoothes airflow around the wing. It is on the
inboard fan cowl.
The inlet cowl sends air into the engine. The inlet cowl attaches to the
engine.
Oil Tank Access Door
Fan Cowls
The oil tank access door permits access to the oil tank for servicing. It is
on the right fan cowl
The fan cowls give an aerodynamically smooth surface over the fan case.
The fan cowls attach to the fan cowl support beam. The fan cowls open for
maintenance.
These items are on the fan cowls:
- IDG access door
- Chip detector/pressure relief door
- Vortex control device
- Oil tank access door
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POWER PLANT - FAN COWL
General
There are two fan cowls for each engine. Each fan cowl attaches to the
strut with three hinges.
The fan cowls are made of aluminium. The left fan cowl weighs 80 lbs (36
kg). The right fan cowl weighs 96 lbs (44 kgs).
Each fan cowl has two fan cowl hold open rods.
Fan Cowl Latches
Three fan cowl latches secure the left and right fan cowls together. All
latches are along the bottom of the fan cowls.
Fan Cowl Hold Open Rods
One end of each hold open rod attaches to the fan cowl. When the cowl is
closed, the other end attaches to a receiver on the fan cowl. When the
cowl is open, the other end attaches to a receiver on the engine. Each
hold open rod is telescopic.
Each hold open rod has a collar that locks the hold open rod in place. A
yellow lock indication shows when the hold open rod is in the locked
position.
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THRUST REVERSER - TENSION LATCHES
Purpose
The tension latches hold the T/R halves together.
General
There are six tension latches for each T/R. Numbers identify each latch.
Latch number one is the latch most forward. Latch number six is the latch
most aft. All latches are interchangeable.
Location
All tension latches are at the bottom of the T/R halves. The latch handles
and mechanisms are on the left T/R half. The latch keeper pins are on the
right T/R half.
Training Information Point
Always open the latches in order from aft (No. 6) to forward (No. 1).
Always close the latches in order from forward (No. 1) to aft (No. 6).
You can use the latch lever tool (special tool) to help bring the T/R halves
together. This makes it easy to close the tension latches.
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THRUST REVERSER - THRUST REVERSER
OPENING ACTUATOR
Training Information Point
Purpose
The leading edge flaps can extend and damage the T/R cowls (halves)
when they are in the open (maintenance) position. Follow the AMM
procedures to prevent the leading edge flap operation before you open the
T/Rs. An actuator safety lock is usually put around the T/R opening
actuator's rod after the T/R cowl is open. The actuator safety lock is a
safety device and backs up the lock collar if it fails. Two quick release pins
hold the actuator safety lock around the T/R opening actuator rod.
You use a hold open fitting (special tool) to keep the T/R halves open
during an engine change. This fitting holds the T/R halves at
approximately 45 degrees open. The outboard T/R halves can open more
than 45 degrees. A hold open rod can keep these T/R halves open at 55
degrees.
You use the T/R opening actuator to open the T/R cowl (half). Each
engine has two T/R opening actuators. Each actuator opens its cowl to
approximately 45 from the closed position.
Location
Each T/R opening actuator is on the forward face of its T/R cowl. The
upper end of the T/R opening actuator attaches to the T/R cowl. The lower
end attaches to the engine fan frame extension ring. You open the fan
cowls to gain access to the T/R opening actuators.
Functional Description
WARNING: MAKE SURE YOU DO THE DEACTIVATION PROCEDURE
FOR THE THRUST REVERSER. IF THE THRUST REVERSER IS NOT
LOCKED, IT CAN ACCIDENTALLY OPERATE AND CAUSE INJURY TO
PERSONS AND DAMAGE TO EQUIPMENT.
Fluid from the hand pump causes the T/R opening actuator rod to extend
and open the T/R cowl. As the actuator approaches the full extend
position, the lock collar goes into the lock position. A red band on the rod
shows when the collar is in the lock position.
Fluid goes from the opening actuator back to the hand pump when you
close the T/R cowl.
WARNING: DO NOT OPERATE THE OPENING SYSTEM FOR THE
THRUST REVERSER IF THE WIND VELOCITY IS MORE THAN 40
KNOTS. THE OPENING SYSTEM FOR THE THRUST REVERSER CAN
HAVE A FAILURE IN LARGE WINDS WHICH CAN CAUSE INJURY TO
PERSONS AND DAMAGE TO EQUIPMENT.
Operation
WARNING: IF YOU USE THE MANUAL PROCEDURE TO OPEN THE
THRUST REVERSER AGAIN AND AGAIN, THE HYDRAULIC FLUID
FOR THE POWER OPENING SYSTEM CAN DECREASE. THIS WILL
DECREASE THE SNUBBING ACTION. IF THE HYDRAULIC FLUID IN
THE POWER OPENING SYSTEM DECREASES, THE REVERSER HALF
CAN CLOSE TOO FAST. THIS CAN CAUSE INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT. YOU MUST OPEN AND CLOSE THE
REVERSER HALVES REGULARLY WITH THE PUMP METHOD TO
REPLACE THE HYDRAULIC FLUID. There are two procedures to open the T/Rs. The pump procedure is the
best. You use the manual procedure only if no pump is available.
You usually use a hand pump to operate the T/R opening actuator. As the
rod extends, the T/R cowl opens and the lock collar moves into the lock
position. You can see and hear the lock collar move to the lock position.
The red band confirms the lock collar position.
With the manual procedure, you lift and move the cowl up until the
actuator lock goes into the lock position.
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ENGINE CONTROLS - GENERAL DESCRIPTION
Reverse Thrust Interlock Solenoids
General
There are two reverse thrust interlock solenoids, one for each engine.
Each reverse thrust interlock solenoid limits the range of motion of a
reverse thrust lever. You can make the thrust reverser deploy, but you can
not increase the reverse thrust until the thrust reverser sleeves are near
the full deployed position. The engine control system supplies manual and automatic control inputs
to operate the engine.
The engine control system has these components:
- Thrust levers (forward and reverse)
- Engine start levers and switches
- Thrust lever interlock solenoids
Thrust Levers
You use the thrust levers to supply the manual inputs to the engine control
system. There are two thrust lever assemblies, one for each engine. For
each engine, there is a forward thrust lever and a reverse thrust lever. The
reverse thrust lever is on the forward thrust lever.
For each engine, the thrust levers supply a thrust command signal to the
Electronic Engine Control (EEC) through a resolver. Each thrust lever
assembly connects mechanically to a resolver through an adjustable rod.
An interlock latch prevents the operation of the forward thrust lever and
the reverse thrust lever at the same time.
Start Levers
There are two start levers, one for each engine. You use the engine start
lever during an engine start. You also use it to shutdown the engine. The
start levers operate switches which supply signals to different aircraft and
engine systems and components.
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ENGINE CONTROL - ELECTRONIC ENGINE
CONTROL (EEC)
General
The Electronic Engine Control (EEC) is the primary control for the engine
fuel and control system. The EEC uses digital and analogue signals for
other systems control and monitoring data.
The EEC is a two channel computer with an active control channel and a
standby channel. The two channels are A and B. The two channels
operation. The EEC receives information to calculate command logic
signals from channel A or channel B. The EEC sends the control signals to
operate the engine.
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INTENTIONALLY LEFT BLANK
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