BOEING 777-232
ER & LR
PANEL NOTES
Captain Hendricks Edgerton
February 17, 2015
--- WARNING --FOR TRAINING AND REFERENCE USE ONLY
Do not substitute this book for the manuals provided by the airline or the
manufacturer.
None of the material in this book is sanctioned, reviewed or checked by Delta Air
Lines, Boeing or anyone else. Though I have tried to be as accurate as I can, I am
sure there is out dated or incorrect information inadvertently included. This
material is intended for familiarization use only. The final source of current
information must be the aircraft flight manuals.
These notes should not be the primary study document for the electronic system
evaluation as that test is derived from the LOD.
Version:
February 17, 2015
OVERVIEW OF MAJOR CHANGES
SECTION
PAGE
OVERVIEW
All
Updated for Rev. 8
NOTES
The order of these notes does not correspond to the OM Volume 2, but corresponds to the layout of the
panel diagrams provided by flight training. This is for ease of home study. If you wish to print and include
the panel prints, they are posted on Flight Ops., My Delta Fleet, 777, 777 Panel Prints.
Aircraft specific items are shown as <ER only> or <LR only> while operational differences are shown as
<ER/LR difference> .
This is a continuing work in progress. Please send any corrections and suggestions to me at:
hhedgerton@comcast.net
2
TABLE OF CONTENTS
OVERHEAD MAINTENANCE ................................................................................................................................ 5
BACKUP WINDOW HEAT .........................................................................................................................5
STANDBY POWER....................................................................................................................................5
FLIGHT CONTROL HYDRAULIC VALVE POWER ...................................................................................5
MEDICAL OUTLET POWER......................................................................................................................5
APU MAINTENANCE .................................................................................................................................5
EEC MAINTENANCE .................................................................................................................................5
CARGO TEMP SELECT ............................................................................................................................6
GRD TEST .................................................................................................................................................6
COCKPIT VOICE RECORDER .................................................................................................................6
OVERHEAD ............................................................................................................................................................... 7
EMERGENCY LOCATOR TRANSMITTER ...............................................................................................7
ADIRU ........................................................................................................................................................7
FLIGHT COMPUTERS & THRUST ASYM COMP .....................................................................................8
APU ..........................................................................................................................................................10
ELECTRICAL ...............................................................................................................................................13
DOOR LOCK CONTROLLER ..................................................................................................................17
EMERGENCY LIGHTS ............................................................................................................................18
SERVICE INTERPHONE .........................................................................................................................18
PASSENGER OXYGEN ..........................................................................................................................18
WINDOW HEAT .......................................................................................................................................18
HYDRAULIC ............................................................................................................................................19
PASS SIGNS ...........................................................................................................................................21
APU & CARGO FIRE ...............................................................................................................................22
ENGINE ...................................................................................................................................................24
FUEL JETTISON......................................................................................................................................27
FUEL JETTISON INDICATIONS .............................................................................................................28
FUEL ........................................................................................................................................................29
FUEL INDICATIONS ................................................................................................................................31
ANTI-ICE ..................................................................................................................................................32
AIR CONDITIONING ................................................................................................................................33
BLEED AIR ..............................................................................................................................................36
PRESSURIZATION .................................................................................................................................37
WINDSHIELD WIPER ..............................................................................................................................38
LIGHT CONTROL ....................................................................................................................................38
FORWARD CAPTAIN’S AND FIRST OFFICER’S .............................................................................................39
MASTER WARNING / CAUTION .............................................................................................................39
CPDLC .....................................................................................................................................................39
EFIS CONTROL .......................................................................................................................................39
INSTRUMENT SOURCE SELECT ..........................................................................................................41
BRAKE .....................................................................................................................................................42
HEADING / FMC / DISPLAY ....................................................................................................................42
CENTER INSTRUMENT .........................................................................................................................................45
MODE CONTROL PANEL .......................................................................................................................45
DISPLAY SELECT ...................................................................................................................................49
INTEGRATED STANDBY FLIGHT DISPLAY ..........................................................................................51
GND PROX ..............................................................................................................................................52
LANDING GEAR ......................................................................................................................................53
AUTOBRAKE ...........................................................................................................................................54
CONTROL COLUMN / WHEEL & RUDDER / BRAKE PEDALS ....................................................................57
3
CONTROL PEDESTAL ........................................................................................................................................... 61
FUEL CONTROL ..................................................................................................................................... 62
SPEED BRAKE / SPOILERS .................................................................................................................. 62
THRUST / REVERSE THRUST .............................................................................................................. 63
FLAP ....................................................................................................................................................... 63
ALTN FLAPS ........................................................................................................................................... 65
CURSOR CONTROL DEVICE ........................................................................................................................ 66
PARKING BRAKE ........................................................................................................................................ 66
CENTER PEDESTAL .............................................................................................................................................. 67
RADIO TUNING PANELS (L, C, R) ......................................................................................................... 67
AUDIO CONTROL PANEL (L, C, R) ........................................................................................................ 68
WX RDR .................................................................................................................................................. 70
ENGINE FIRE ......................................................................................................................................... 71
EVACUATION CONTROL ...................................................................................................................... 72
TRIM........................................................................................................................................................ 72
FLIGHT DECK DOOR ............................................................................................................................. 73
OBSERVER AUDIO ................................................................................................................................ 73
FLIGHT DECK ACCESS SYSTEM .......................................................................................................... 74
FLIGHT DECK EMERGENCY ACCESS PANEL ................................................................................................ 74
SIDEWALL ............................................................................................................................................................... 75
SIDE WINDOW ....................................................................................................................................... 75
STEERING .............................................................................................................................................. 75
OXYGEN MASK / REGULATOR ............................................................................................................. 75
UPPER CREW REST COMPARTMENTS ........................................................................................................... 77
UPPER CREW REST MASTER CONTROL PANEL ........................................................................................... 77
SMOKE DETECTION.............................................................................................................................. 78
WARNING SYSTEMS ............................................................................................................................................. 79
EICAS...................................................................................................................................................... 79
CREW ALERTNESS MONITOR ............................................................................................................. 79
ENGINE FAILURE ALERT SYSTEM ............................................................................................................. 80
GPWS ..................................................................................................................................................... 80
EGPWS (TERRAIN) ................................................................................................................................ 80
PWS ........................................................................................................................................................ 81
CONFIGURATION .................................................................................................................................. 82
TCAS ....................................................................................................................................................... 83
ALTITUDE ALERT .................................................................................................................................. 83
ENVELOPE PROTECTION .................................................................................................................... 83
SYSTEM SCHEMATICS ......................................................................................................................................... 85
GENERAL INFORMATION ................................................................................................................................... 91
RECALL NON-NORMAL CHECKLISTS ............................................................................................................ 92
RECALL LIMITATIONS ........................................................................................................................................ 93
EMERGENCY EVACUATION FLOW ................................................................................................................. 94
SMOKE / FUMES PRIORITIES ............................................................................................................................. 95
4
OVERHEAD MAINTENANCE
OVERHEAD MAINTENANCE
BACKUP WINDOW HEAT
BACKUP WINDOW HEAT LEFT & RIGHT switch


ON: Automatically provides anti-fog for forward windows only.
OFF
STANDBY POWER
STANDBY POWER switch



OFF: AC standby bus not powered
AUTO: If AC transfer busses unpowered, transfer standby busses to battery power
BAT:
 If AC power not available: Standby busses powered by battery
 If AC power available: Initiates DC/standby self test
FLIGHT CONTROL HYDRAULIC VALVE POWER
TAIL / WING L, C, R switch


NORM: Hydraulic pressure to flight control actuators
SHUT OFF: Hydraulic pressure removed from flight control actuators
 Inhibited in flight
VALVE CLOSED lights: Related flight control actuators hydraulic valve closed
MEDICAL OUTLET POWER
<ER only>
MEDICAL OUTLET POWER switch

DEACT: The system switch and cabin outlets have been deactivated
NOTE: AC power outlets available at each BE seat and first 10 rows of coach.
APU MAINTENANCE
APU POWER switch


NORM
TEST
EEC MAINTENANCE
ENG POWER L & R


NORM
TEST
5
OVERHEAD MAINTENANCE
CARGO TEMP SELECT
AFT selector



OFF: Shuts off airflow
LOW: Normal position, 40 – 50 F temperature range
HIGH: 65 – 75 F temperature range
BULK selector



OFF: Shuts off airflow
LOW: 40 – 50 F temperature range
HIGH: Normal position, 65 – 75 F temperature range
 Turns on bulk cargo ventilation fan for animal carriage
NOTES: Cargo Heat System
 The aft and bulk cargo compartments have independent bleed air heating systems
 An insulated curtain separates the two compartments
 With the CARGO TEMP selector set to LOW or HIGH, the respective cargo heat shutoff valve opens
and the temperature control valve opens and closes to maintain the temperature in the compartment
 The lavatory/galley vent fans draw air across temperature sensors in each compartment
 If both vent fans fail, cargo heat is not provided.
 Forward cargo compartment heated by exhausted forward equipment cooling air.
GRD TEST
GRD TEST switch


NORM
ENABLE
COCKPIT VOICE RECORDER
COCKPIT VOICE RECORDER


TEST: Push and hold for five seconds
 Needle moves into green band during test of all four channels (1/sec.) <ER only>
 Green indicator light illuminates <LR only>
ERASE: Push and hold for three seconds
 Aircraft on ground
 AC power on
 Parking brake set
NOTES:
 Records transmissions and audio as selected on ACP (3 channels) and area microphone (1 channel)
 If needle not in green band or indicator light not illuminated during test, headset can be connected
and tone heard during test.
6
OVERHEAD
OVERHEAD
EMERGENCY LOCATOR TRANSMITTER
<LR only>
ELT switch



ARMED: Remote mounted ELT automatically activated by high deceleration forces
RESET: Resets ELT to off
ON: Activates ELT transmissions
ADIRU
ADIRU switch/light


ON: ADIRU powered
 Requires hot battery bus power
 With static a/c, enters quick alignment after 6 minutes
 Initial power up initiates full alignment cycle
 6 to 15 minutes required, depending on latitude
 6 minutes at the equator, 10 minutes average
OFF: Removes power from ADIRU
 Only if airspeed less than 30 kts.
NOTES:
1. ADIRS (air data inertial reference system): Three components
 ADM (air data module) : Eight, convert pitot static pressure to digital signal
 ADIRU (air data inertial reference unit):
 Six ring laser gyros.
 Three computers
 Three power sources (R & L main DC and hot battery buss)
 SAARU (secondary attitude and air data reference unit)
 If ADIRU fails, automatically provides:
 Attitude, heading (three minutes) and air data to PFD and flight controls
 Must manually set magnetic heading from standby compass
2. ADIRU provides output to:
 PFD: Airspeed, attitude, altitude, and heading
 ND: FMS inertial position
3. ADIRU Alignment/Position Update (Ground Only):
 AUTOMATIC REALIGNMENT:
 When dash prompts appear on the SET INERTIAL POS line of the POS INIT page, enter the
most accurate LAT/LONG position
 New entries display for two seconds. After two seconds, dashes display to allow entry of
another position.
 FULL ALIGNMENT:
 ADIRU switch – OFF 30 seconds, then ON
 Wait an additional 30 seconds.
 When box prompts appear on the SET INERTIAL POS line of the POS INIT page, enter the
most accurate LAT/LONG position
7
OVERHEAD
4. If ADIRU fails:
 Heading is retained 3 mins.
 Must be manually updated in FMS
 GPS provides position to FMC
 Basic autopilot functions only
 Inoperative AFDS modes:
 LNAV, VNAV, TO/GA, LOC, APP, TRK HOLD/SEL, FPA
ON BAT light


Battery or hot battery bus powering ADIRU
 Illuminates only when ADIRU has been aligned on airplane or ground power, and primary power
is subsequently removed or failed
Ground crew call horn sounds
FLIGHT COMPUTERS & THRUST ASYM COMP
PRIMARY FLIGHT COMPUTERS switch


AUTO:
 Flight controls in normal mode
 PFCs provide enhanced a/c handling qualities
 Uses information from air data, inertial, flap & slat position, thrust, radio altitude
 Automatically switches to secondary or direct mode for system fault
 Can be reselected to attempt restoration of secondary or normal mode operation
DISC:
 Disconnect primary flight computers
 Commands system to direct mode
DISC light


Primary flight computers disconnected automatically or manually
System in direct mode
8
OVERHEAD
NOTES:
G
A
T
E
W
A
Y
FLIGHT CONTROL MODES
Mode displayed on flight control synoptic
NORMAL SECONDARY
Gust Suppression
Y
N
Autopilot
Y
N
TAC (10% asymmetry)
Y
N
(centers control wheel)
Rudder Trim
Y
Y
Rudder Trim Canceling
Y
Y
Tail Strike Protection
Y
N
Envelop Protection
Y
N
(stall, over speed, bank angle)
Wheel/Rudder Cross Tie
Y
N
(8 deg. rudder deflection)
< 210 kts.
Automatic Pitch Compensation
Y
N
Auto Speed brakes
Y
N
Yaw Damping
Y
N
or degraded
DIRECT
N
N
N
Y
N
N
N
N
N
N
N
1. System components:
 Primary flight computers (PFCs) – three (L, C, R)
 Actuator control electronics (ACEs) – four (L1, L2, C, R)
2. Normal mode control input path
 Pilot to ACE to PFC back to ACE to flight control
 A/P to PFC to ACE to flight control
 PFC provide full capabilities
3. Secondary mode control input path
 Pilot to ACE to PFC back to ACE to flight control
 PFCs provide simplified computations
 A/P inoperative
 Automatically selected only
4. Direct mode control input path
 Pilot to ACE to flight control
 Automatically selected when ACEs detect
 Failure of three PFCs, or
 Lost communication with PFCs
 Manually selected with PRIMARY FLIGHT COMPUTERS switch to DISC
5. Manual mode control input path
 Pilot through cable to stabilizer & selected spoilers
 Ability to maintain straight and level
6. Tail Strike Protection
 During takeoff and landing, if PFC senses strike imminent
 Decreases elevator deflection
 No feedback through control column
9
OVERHEAD
THRUST ASYM COMP switch/light


AUTO: System functions automatically if 10% thrust asymmetry detected
 TAC applies sufficient rudder for pilot or autopilot to center control wheel
 Rudder is proportional to thrust differential
OFF: Disconnects TAC from flight control system
NOTES:
 10% differential in thrust activates system
 Applies rudder to center control wheel
 Rudder pedals and rudder trim indicator displaced
 Only active above 70 kts.
 Disconnects when:
 Thrust data lost
 Engine damaged
 Engine surges
 Not available when
 Airspeed below 70 knots on the ground
 Reverse thrust is applied
 Automatically disengaged due to system malfunction or loss of engine thrust data.
 Flight controls in secondary or direct modes
APU
APU selector



OFF:
 Closes APU bleed valve
 Initiates normal shutdown sequence
 EICAS memo APU COOLDOWN
 Resets auto shutdown fault logic
ON:
 Opens APU inlet door
 Opens APU fuel valve
 Activates AC or DC fuel pump
 If AC power, L FWD pump provides fuel from left main tank
 If no AC power, DC pump provides fuel from left main tank
 Powers APU controller
START: Initiates automatic start sequence
 May be started up to 43,100 ft.
NOTES:
 APU starts automatically with loss of both AC transfer busses.
 Regardless of selector position
 To shutdown move selector to ON then OFF
 Max. altitude for bleed load is 22,000 ft.
 EICAS memos:
 APU RUNNING: operating normally
 APU SHUTDOWN: automatically shutdown
 APU COOLDOWN: cool down mode (105 secs.)
 APU LIMIT: exceeded a limit
10
OVERHEAD
FAULT light



APU fault/fire
Auto shutdown due to fault/fire
Momentary illumination during start (controller self test)
APU GEN switch/light


ON:
 Arms APU generator breaker to automatically close
 Max. altitude for electrical load 43,100 ft.
OFF:
 Opens APU generator breaker
 APU generator breaker open
NOTES:
1. APU starters
 Air turbine starter: Primary
 Electric motor starter: Secondary
 If insufficient air pressure
 Powered by APU battery
2. Battery power
 APU battery powers:
 Electric motor starter
 APU controller
 Main a/c battery powers:
 Inlet door
 Fuel valve
 Fire detection system
3. Operating Modes
 Attended: Either engine FUEL CONTROL switch in RUN or in flight
 Unattended: On ground and FUEL CONTROL switches in CUTOFF
FIRE
FAULT
OVER
UNDER
APU AUTOMATIC SHUTDOWN
ATTENDED
APU SHUTDOWN
Fire/inlet over temperature
X
Controller failure
X
Over speed/loss of control
X
Speed droop
X
High EGT
Continues to
Operate
Low oil pressure
APU LIMIT
High oil temperature
Gen. oil filter bypass
Intake door failure
No combustion on start
No acceleration on start
11
UNATTENDED
No cool down
X
X
X
X
X
X
X
X
X
X
X
OVERHEAD
4. APU fire signal response
 Attended mode operation
 Fire response initiated from dual fire detector loops
 APU shuts down
 Fire bottle discharged by flight crew with fire handle
 Unattended mode operation
 Fire response initiated from single fire detector loop
 APU shuts down
 Fire bottle automatically discharged
5. APU to pack takeoff mode <LR only>
 Type “APU” into line L1 on THRUST LIMIT page
 One minute after 2nd engine started, reconfigures valves to provide APU bleed to left pack
only
 After takeoff, valves reposition for normal operation
12
OVERHEAD
ELECTRICAL
IFE/PASS SEATS switch/light


ON: Provides power when AC power available
OFF: Removes power from IFE system and passenger seat systems
 Seat motor power, personal computer power outlets, and telephones
CABIN UTILITY switch/light


ON: Provides power
OFF: Removes power from:
 Ground service bus (except battery chargers and L FWD fuel pump)
 Utility busses
 Galleys
 Gasper fan
 Fluorescent cabin lighting
 Beacon, logo and wing lights
 Cabin lights turned on:
 Night and supplemental night lights
 Reading lights
 FA work lights
 Certain galley and crew rest lights
13
OVERHEAD
BATTERY switch/light


ON
 Unpowered airplane on ground:
 APU start possible
 No displays powered
 Few switch annunciator lights illuminate
 On ground after AC power lost / removed:
 Standby busses powered
 Emergency lights powered
 Left inboard and outboard and upper display powered
 Left CDU powered
OFF: On the ground, battery power removed
 Inhibits standby power from battery
 In flight and on ground, EICAS message ELEC BATTERY OFF displays
NOTES: Main battery provides standby power to:
 Hot battery bus
 Battery bus
 Captain’s flight instrument bus
 L & C PSAs & FC buses
 Standby inverter & standby AC bus
Capt. outboard
PFD
Capt. inboard
PFD/ND
Upper center
display
ITEMS POWERED BY BATTERY ONLY IN FLIGHT
(10 minutes in flight)
Stby. Flt. Display
Capt. EFIS control
Capt. CCD
panel
 ADI
Display select
#1 VHF/Capt. audio
 Approach mode from
panel
panel
C ILS
Capt.
CDU
Transponder
 Airseed
 Altimeter
BUS TIE L & R switch/light



AUTO: Arms automatic AC bus tie circuits
Blank: Commands bus tie open
ISLN:
 Bus Tie Breaker is locked open (ISLN is selected with Bus Tie Switch)
 A fault has occurred, automatically opening the Bus Tie Breaker
NOTE:
P
P
I
BUS TIE FUNCTIONS
Prevents paralleling (except on-board transfers)
Powers busses
Isolates faults
GEN CTRL L & R switch/light



ON: Arms generator breaker to close automatically when power available
OFF:
 Generator breaker open
 Opens field and generator breakers
Push OFF then ON: Resets fault trip circuitry
14
OVERHEAD
DRIVE DISC L & R switch/light


Push for one sec.: Disconnects IDG
DRIVE: IDG low oil pressure
 Automatic disconnect
 Manual disconnect
NOTES:
 IDG automatically disconnects for high oil temperature
 IDG can only be reconnected on ground
BACKUP GEN L & R switch/light



ON: Backup generator armed
OFF:
 Opens backup generator control relay
 Backup generator failed
 Circuit fault detected
 Backup generator selected OFF
 Both illuminated indicate backup converter failed
Push OFF then ON: Resets fault trip circuitry
NOTES: Backup AC power system
 Each engine has a separate backup generator
 Each backup generator contains two permanent magnet generators (PMGs) that supply power to the
flight control DC electrical system
 The PMGs operate regardless of the respective BACKUP GEN switch position
 With loss of primary generator, backup generator powers respective AC transfer bus
 Respective main bus not powered (bus tie open)
 APU can be started to repower main bus
 Backup converter can power both AC transfer bus
 Backup converter can only control one backup generator
T
A
P
S
BACKUP GENERATOR OPERATES:
Test after engine start
Approach mode (powers right A/P)
Power interruption to one or both main busses
Single source (includes APU) AC generator
EXTERNAL POWER PRIMARY & SECONDARY switch/light


ON: External power supplying power
AVAIL:
 External power available
 Power quality is acceptable
 Extinguishes when ON selected
15
OVERHEAD
NOTES:
1. Electrical Load Management System (ELMS)
 Detects and isolates faults
 Ensures power available for critical components (downloads)

LOAD SHED displayed on electrical synoptic
G
U
S
DOWNLOAD PRIORITY
Galley power
Utility busses
Single items
 C-2 hydraulic electrical pump
 Right center fuel pump
2. Ground Service Bus
 Provides power on ground or in flight to:
 Battery chargers (main and APU)
 L FWD fuel boost pump (fuel to APU)
 Cabin lights and outlets
 Normally powered by the Right Main Bus.
 Alternate sources of power:
 APU generator
 Primary External Power
 With primary external power connected, L1 FA GROUND SERVICE switch powers bus even
when ext. power not selected (L & R main busses not powered)
3. Ground Handling Bus
 Provides power on ground only to:
 Forward and aft cargo doors
 Bulk cargo door manually operated
 Cargo and maintenance lights
 Fueling/defueling operations
 Only powered by APU or primary external power (connected)
4. Ram Air Turbine (RAT)
 Automatically deployed with loss of both AC transfer busses, in flight only
 Supplies pressure to C hydraulic system
 Supplies electrical power to C1 & C2 TRUs
 Powers captain and first officer flight instrument busses
 Sheds electrical load to maintain hydraulic pressure
5. Failure of both AC Transfer Busses in flight
 The RAT is deployed automatically
 The APU automatically starts
 Regardless of APU selector position
6. DC Power System
 DC power provided by four transformer rectifier units (TRU)
 L & C1 powered by L transfer bus
 C2 & R powered by R transfer bus
 C1 & C2 can be powered by RAT
16
OVERHEAD
7. Flight Control DC System
 PMGs inside each backup generator power L, C & R power supply assemblies (PSA)
 PSAs convert AC power to DC power for three flight control DC busses
 Dedicated battery provides power for one minute to PSAs during power transfer
 Secondary power for L & R PSA is related main DC bus
 Secondary power for C PSA is captain flight instrument bus
 Flight control busses power:
 Actuator control electronics (ACE) (four)
 Primary flight computers (PFC) (L, C & R)
 During standby power operation
 Hot battery bus powers L & C flight control busses through L & C PSA
 Captain flight instrument bus powered by C1 TRU from RAT
 Captain flight instrument bus powers C flight control bus through C PSA
8. Standby Electrical System
 Main battery powers battery, hot battery, Capt. flight inst. buses
 Standby inverter powers standby AC bus
 RAT generator powers C1 & C2 TRUs which power Capt. & FO flight inst. buses
9. Autopilot and flight director power sources
 Normal operations:
 Left and center from left IDG
 Right from right IDG
 Approach mode following bus separation:
 Left from left IDG (left AC transfer, left main DC, Capt. flight inst. buses)
 Center from right IDG (battery and AC standby buses through battery charger)
 Right from right backup generator (right AC transfer, right main DC, FO flight inst. buses)
DOOR LOCK CONTROLLER
<ER only>
Flight Deck Door Lock selector



AUTO: Spring loaded position
UNLK: Push and rotate to unlock door, overrides DENY lockout
DENY: Rotate to cancel the keypad unlock command, starts a 5 min. lockout countdown
LOCK FAIL light:

DOOR LOCK CONTROLLER selector in AUTO and door lock has failed
AUTO UNLK light:



Correct emergency access code entered in keypad
Light flashes and continuous chime sounds until timer expires
Door unlocks after 60 sec. time delay
NOTES:
 First flight of the day check required (OM Vol. 1, SP)
 Locking pin installed on door frame
 ER does not have an electrical cutout switch like LR
17
OVERHEAD
EMERGENCY LIGHTS
EMER LIGHTS switch



ARMED:
 All emergency lights illuminate with loss of main DC busses (failure or turned off)
 If door ARMED, moving the door handle to the open illuminates the exterior fuselage light and the
interior emergency lights at that door only
ON: All emergency lights illuminate
OFF: Prevents illumination, even if power fails
NOTES:
 EMER LIGHTS switch on FA panel overrides all positions of switch.
 Remote batteries provide 15 mins. of operation
SERVICE INTERPHONE
SERV INTPH switch


OFF: Normal position
ON: Connects interphone jacks located at different location to flight interphone system
 Engine pylons, wheel wells, APU compartment, E & E compartments
PASSENGER OXYGEN
PASS OXYGEN switch/light


Push: Deploys the passenger oxygen masks
 Warning: System will deploy anytime switch pushed
ON: Passenger oxygen system activated, masks deployed
NOTES:
 Passenger masks automatically deploy at 13,500 ft. cabin altitude
 No oxygen flow in masks until pin is pulled to activate generator
 Passenger oxygen system uses chemical generators to produce oxygen
 Generators provide about 12 minutes of oxygen flow
 Passenger oxygen system provides no smoke protection for passengers
 Mixes oxygen with cabin air, an extreme fire hazard.
WINDOW HEAT
L & R SIDE & FWD switch/light


ON: Electrical heat applied to all flight deck windows
INOP:
 Switch off
 Overheat
 System fault
NOTES:
 Forward windows have anti-ice and anti-fog.
 Side windows have anti-fog only.
 Backup system automatically provides anti-fog for forward windows only, if primary system fails.
18
OVERHEAD
HYDRAULIC
RAM AIR TURBINE switch/light



Press to manually deploy
 Can deploy on ground
 Deployed by compressed spring
PRESS: Center hydraulic system pressure greater than 1500 psi.
UNLKD: RAT not stowed
NOTES:
 In flight RAT automatically deploys:
 Both AC transfer busses unpowered
 Both engines failed and C hyd. pressure low
 All three hydraulic systems pressure low
 RAT provides:
 Center hydraulic system pressure for flight controls only
 Electrical power to C1 and C2 TRU for Capt. & FO Flight Instrument busses

RAT will reduce electrical load to maintain hydraulic pressure.
 No speed or altitude restrictions on use of RAT.
PRIMARY ENG L & R switch/light



ON: Engine driven pump operates
Blank: Pump off and depressurized
FAULT:
 Low pump pressure
 Excessive pump fluid temperature
 Pump off
19
OVERHEAD
DEMAND ELEC L & R selector



AUTO: Operates when:
 System / primary pump pressure low
 Takeoff and landing
 On ground, R pump operates continuously (normal brakes)
OFF: Pump depowered
ON: Electric pump operates continuously
PRIMARY ELEC C1 & C2 switch/light



ON: Electric pump operates continuously
Blank: Pump off
FAULT:
 Low pump pressure
 Excessive pump fluid temperature
 Pump off
NOTE: C2 Primary Electric Pump Load Shed
 On the ground:
 With only a single ground power source, including the APU, the pump will not operate if
C1primary pump selected
 The pump will not be load shed if
 One engine generator is operating, or
 Primary external power and secondary external power operating, or
 APU generator and primary external power operating
 In flight:
 The C2 primary pump may be load shed when:
 All other electric pumps are running, and
 A single source of electrical power, and
 Generator capacity is exceeded.
 Pump will start automatically when the conditions that shed the pump no longer exist.
 If C2 primary pump is load shed, EICAS message HYD PRESS PRI C2 inhibited
DEMAND AIR C1 & C2 selector



AUTO: Operates when:
 System/primary pump pressure low
 Control logic anticipates a load
 Gear extension/retraction, flap/slat operation
OFF: Pump depowered
ON: Pump operates continuously
NOTE: If both DEMAND AIR pumps ON, only C1 operates, cannot operate simultaneously.
DEMAND pump FAULT lights



Low pump pressure
Excessive pump fluid temperature
Pump off
20
OVERHEAD
NOTES:
HYDRAULIC SYSTEMS
L
C
R
Flight Controls
X
X
X
Thrust reverser
X
X
LE Slats
X
TE Flaps
X
Landing Gear
X
Nose & Main Gear Steering
X
Wheel Brakes
Alternate Normal
Reserve
Backup
RAT to C only
Electric motor
Electric motor
Alt. gear extension
Isolated
Brake accumulator
1. Hydraulic QTY status display
 Numeric – Quantity as percentage of normal service level (1.00)
 RF – refill
 LO – quantity low
 OF – reservoir over filled (inhibited in flight)
2. To prevent fluid transfer:
 R ELEC DEMAND selector must be selected to AUTO first
 R ELEC DEMAND selector must be selected to OFF last
3. If center hydraulic system quantity low and airspeed above 60 kts:
 Reserve brakes are isolated from the center system and remain operable
 C1 pump and reserve fluid are dedicated to operating reserve brakes and nose gear steering
 Nose gear actuation and steering are isolated
 Nose gear actuation and steering reconnected when airspeed below 60 knots
PASS SIGNS
NO SMOKING selector <ER only>



OFF: NO SMOKING signs not illuminated
ON: (replaced AUTO) NO SMOKING signs illuminated
ON: NO SMOKING signs illuminated
CABIN CHIME button <LR only>

Push: Sounds the cabin chime
SEAT BELT selector



OFF: FASTEN SEAT BELTS and RETURN TO SEAT signs not illuminated
AUTO: Seat belt signs illuminated when
 Landing gear not up and locked, or
 Flap lever not up, or
 Airplane altitude below 10,300 ft., or
 Cabin altitude above 10,000 ft., or
 Passenger oxygen on
ON: FASTEN SEAT BELTS and RETURN TO SEAT signs illuminated
NOTE: NO SMOKING and FASTEN SEAT BELTS signs illuminate anytime passenger oxygen system is
deployed, regardless of switch position.
21
OVERHEAD
APU & CARGO FIRE
APU fire handle / Fire Warning light



Unlocked: fire warning
Pull:
 Arms extinguisher bottle (one)
 Close fuel valve
 Closes bleed valve
 Trips generator
 Closes air inlet door
 Shuts down APU
Rotate: discharges fire bottle
APU BTL DISCH light

Extinguisher bottle low pressure
NOTES:
1. APU fire indications:
 Fire bell
 Master WARNING lights illuminate
 EICAS warning message FIRE APU
 Fire handle warning light illuminates
 Fire handle unlocks
2. APU fire detector loops
 Two fire loops in APU compartment
 No overheat detection
 Attended mode - both loops must detect fire to provides fire warning
 APU shuts down but pilot must discharge fire bottle with fire handle
 Unattended mode – single loop detecting fire provides fire warning
 APU shuts down and fire bottle discharges automatically
 If one loop fails, systems switches to single loop operation
 If single loop senses fire, then fire warning produced
22
OVERHEAD
ARM FWD & AFT switch/light


FWD & AFT: Smoke in associated cargo compartment
ARMED
 FWD:
 Arms extinguisher bottles (five)
 Arms compartment extinguisher valve
 Turns off both lower recirculation fans
 Shuts down cargo heat
 Commands packs to minimum airflow
 Commands equipment cooling to override mode
 AFT:
 Arms extinguisher bottles (five)
 Arms compartment extinguisher valve
 Turns off both lower recirculation fans
 Shuts down cargo heat
 Commands pack to minimum airflow
 Shuts down bulk cargo ventilation system
 Shuts down lavatory/galley vent fan
DISCH switch/light


Push: Discharges fire bottles into ARMED compartment
 On ground:
 Two bottles discharge immediately
 One bottle discharges after time delay
 In flight:
 Two bottles discharge immediately
 Three bottles discharges after time delay (20 mins.) at reduced rate (207 mins.)
 If bottles remaining, one discharges on touchdown (reduced rate)
DISCH: Illuminates when first two bottles begin to discharge
 EICAS advisory message BOTTLE DISCH CARGO displayed when first two bottles have
completely discharged
NOTES:
 Cargo fire indications:
 Fire bell
 Master WARNING lights illuminate
 EICAS warning message FIRE CARGO FWD/AFT
 Switch/light CARGO FIRE FWD/AFT illuminates
FIRE/OVHT TEST button


Push and hold: Tests engine, APU, wheel well and cargo compartment fire and overheat detection
systems
Requires first flight of the day for non-ETOPS flights (OM Vol. 1, SP)
NOTES:
 Test indications:
 EICAS message FIRE TEST IN PROGRESS displayed
 Fire bell rings intermittently
 Master WARNING light – Illuminated
 APU fire handle – Illuminated
 FWD and AFT CARGO FIRE warning lights – Illuminated
 FUEL CONTROL switches – Illuminated
 LEFT and RIGHT engine FIRE handles – Illuminated.
 The test is complete when the EICAS message FIRE TEST PASS displayed
23
OVERHEAD
ENGINE
EEC MODE L & R switch/light


NORM: Normal engine control mode for EEC
ALTN: Alternate engine control mode for EEC
NOTES:
EEC MODES
SOFT
HARD
ALTN
ALTN
Switch
Automatic with Switch
NORM
Switch NORM ALTN
NORM
NORM
-------------ALTN
ALTN
ENG EEC MODE
Controls
Blank
Display: Act., Controls
Controls
red line
Display: Act.,
Display: Act, command,
red line
ref/target, max. & red line
Controls
Display: Act, command, ref/target, max. & red line
Over speed
Over speed
Over speed
Protection
Protection
Protection
Over speed
Over speed
Over speed
Protection
Protection
Protection
Over speed
Over speed
Protection
Protection
EEC
None
None
NORM
Selection
Switch
Indication
EICAS
EPR <ER>
N1 <ER>
N1 <LR>
N1
N2
N3
<ER>
Thrust
Protection
Autothrottles
Operate normally
1. EECs commands two idle speeds
 Minimum – normal idle
 Approach Idle
 Selected by EEC:
 Engine anti-ice operating
 Flaps at 25 or 30
 One hyd. air demand pump inop. and flaps not UP
 Opposite engine bleed air valve closed
 Maintained until touchdown then minimum idle
24
OVERHEAD
2. EEC Auto-Relight
 No manual or automatic continuous ignition selection / function
 GE <LR only>:
 Flameout protection
 Activated when rapid decrease in N2, or N2 less than idle
 Sub–idle stall recovery
 Fuel is shut off for one second in an attempt to clear the stall
 Both igniters activated
 Relight attempts discontinued if EGT exceeds red line limit
 RR <ER only>:
 Flameout protection and rain/hail ingestion
 Activated when engine at or below idle with the FUEL CONTROL switch in RUN
 Both igniters activated
 If engine does not recover (continues to run down below 35% N3), EEC shuts off fuel and
ignition and disables the auto–relight function
3. In flight start
 Engine at or below idle speed, or
 Engine shutdown with fire handle in
 EEC displays:
 Airspeed range for current altitude, or
 Airspeed range for maximum restart altitude
 X-BLD displayed above N2 <GE> / N3 <RR> if speed below recommended
 Autostart provides continuous start attempts until either:
 Engine starts, or
 Pilots manually abort starts
 <LR/GE>: Temporarily discontinues start at preset EGT between start and TO limit
 <ER/RR>: Temporarily discontinues start if TO EGT limit reached, no light off, or hung start
 Autostart will windmill engine for 30 secs.
 If starter assisted, there is no motoring of engine with starter
 Fuel and ignition delayed until EGT below 200 C
4. Takeoff bump thrust <LR/GE only>
 Provides improved takeoff performance
 High altitude, above 4,000 ft.
 High temperatures, above 14 C
 Selected by:
 CDU on THRUST LIMIT page
 EICAS displays TO B
 Thrust levers full forward in TO bump region
START L & R selector


NORM: EEC controls two igniters
 Alternates single igniter for successive engine starts
 Both igniters used for:
 In flight starts
 Autostarts after failed start attempt
START: Initiates start sequence
 Returns to NORM at start valve cutout
 <GE>: approx. idle N2
 <RR>: 50% N3
25
OVERHEAD
AUTOSTART switch/light


ON: Arms the autostart system
 <LR/GE>: EEC monitors EGT, N2, other parameters
 <ER/RR>: EEC monitors EGT, N3, other parameters
OFF: Disables autostart system
 EICAS advisory ENG AUTOSTART OFF displayed
 Manual start required
NOTES: <ER/LR difference>:
 ER: engines can be started simultaneously
 LR: must start each engine individually
AUTOSTART PARAMETERS MONITORED
Autostart
Pilots
HOT
Hot start
Oil pressure
HUNG Restart Hung start
Oil temperature
Attempt No EGT
WET
STALL
Compressor stall
Starter
No N1 rotation
Locked Starter shaft failure
Out
Starter duty cycle
Insufficient air pressure
<ER/RR>
N3 < Starter Cutout
Turns off fuel & ignition
Motors 20 to 30 sec.
EGT below 100 C
Re-introduces fuel
Ignition
Uses both igniters
If 2nd attempt fails:
N3 < Starter Cutout
Turns off fuel & ignition
Motors 30 sec.
EGT below 100 C
Start valve closed
START sel. to NORM


AUTOSTART ABNORMAL SEQUENCE
Hot, Hung, Stall, No EGT
<LR/GE>
N2 < Starter Cutout
N2 > Starter Cutout
Turns off fuel & ignition
Turns off fuel & ignition
Motors 6 or 30 sec.
Closes start valve
N2 < 30%
Opens start valve
Motors engine
Re-introduces fuel
Re-introduces fuel
Ignition
Ignition
Uses both igniters
Uses both igniters
If attempt fails: Third attempt made
If all attempts fail:
Turns off fuel & ignition
Motors engine
Start valve closed
START sel. to NORM
EICAS caution
ENG AUTOSTART L/R
Logbook entry required:
 An autostart attempt fails and is accompanied by a related EICAS message
 The crew has to manually abort an automatic start attempt
 A manual start attempt fails
No logbook entry required: The autostart system aborts a start, automatically attempts another start,
and that start is successful
26
OVERHEAD
FUEL JETTISON
ARM switch/light


ARMED: Arms the jettison system
 TO REMAIN replaces TEMP in fuel display
 Jettison time displayed in minutes on fuel synoptic
FAULT:
 System fault
 Jettison inoperative
FUEL TO REMAIN selector


PULL ON: Changes mode from default MLW to MAN
DECR / INCR: Sets the fuel to remain quantity
NOZZLE L & R switch/light



Blank: Valves closed and pumps off
ON:
 In flight only - jettison nozzle valve opens (inhibited on ground)
 Turns on both main tank jettison pumps
 Opens both center tank jettison isolation valves
VALVE: Jettison nozzle valve not in selected position
NOTES:
 Automatically dumps fuel to max. land. weight (460K/492K lbs.)
 Separate jettison pump in each main tank
 Main tanks automatically stop dump at 11,500 lbs. each
 Center tank pumps must be ON to jettison fuel from center tank (no jettison pumps)
 System will delay main tank jettison pump operation to maintain aircraft CG
 When heavy and forward CG
 Approximate dump rate:
 5,400 PPM with four pumps operating (2 jettison & 2 center) (QRH)
 3,100 PPM with two pumps operating (2 jettison only) (QRH)
 4,000 ft. AGL is suggested minimum altitude for fuel jettison (FOM)
27
OVERHEAD
FUEL JETTISON INDICATIONS
(EICAS on Upper Display Panel)
TO REMAIN




Displayed when system ARMED
Replaces TEMP indication
Displays fuel to remain when fuel jettison terminates
Displays either:
 MLW (Maximum Landing Weight): default is fuel on board at MLW
 MAN (Manual): fuel to remain on board when set manually
Fuel Synoptic display:


Displayed when system ARMED
During fuel jettison reference the fuel synoptic to display
 JETT TIME: Time remaining to desired weight
 Status of pumps operating during jettison
28
OVERHEAD
FUEL
CROSSFEED FWD & AFT switch/light



Bar visible: Valve open
Bar not visible: Valve closed
VALVE: Valve not in selected position
FWD & AFT PUMPS L & R switch/light



ON: Pump selected on
Blank: Pump selected off
PRESS: Pump output pressure low
CENTER PUMPS L & R switch/light



ON: Pump selected on
Blank: Pump selected off
PRESS: Pump output pressure low
 Inhibited when switch selected off
 Pumps shut off automatically 15 secs. after light illuminates <LR only>
 Auto shut off disabled during fuel jettison
NOTES:
1. Center tank fuel pumps
 On ground both pumps operate only if two electrical power sources
 With only one power source on ground, right pump will be load shed
 Center pumps are both override and jettison pumps
 Override the main tank pumps so that center tank fuel is used before wing tank fuel
 Pumps shut off automatically after 15 secs. of continuous low pressure
 Feature disabled during fuel jettison
29
OVERHEAD
2. Center tank fuel pump operation
 With more than 10,500 lbs. in center tank
 Turn pumps ON for pushback
 With less than 10,500 lbs. in center tank
 Pumps OFF for pushback, taxi, takeoff and below 10,000 Feet
 When EICAS message FUEL IN CENTER illuminates, turn pumps ON
 On ground and takeoff message inhibited with less than 10,500 lbs. in center tank
 In flight above 10,000 ft. message displayed if body angle less than 5 deg. for 10 mins.
 When EICAS message FUEL LOW CENTER (or PRESS light) illuminates, turn pumps OFF
3. Fuel Scavenge System
 Operates automatically when:
 Main tank pumps ON, and
 Main tank quantity less than 29,000 lbs. <ER> / 52,600 lbs. <LR> and,
 Center tank quantity less than 35,000 lbs.
 EICAS message FUEL SCAVENGE SYS displayed:
 Scavenge system is inop and trapped unusable fuel in center tank
 Main tank fuel qty is less than 18K lbs., and
 Center tank qty is greater than 500 lbs for 15 min
 Trapped fuel is added to FMS reserve fuel (QRH)
4. DC powered fuel pump
 Located in left main tank
 No controls or indicators, other than the fuel synoptic display
 On ground: Operates automatically to provide fuel to APU when
 AC power not available and,
 APU selector ON
 In flight: Operates automatically to provide fuel to left engine with
 Loss of both engines and all AC power
5. Minimum fuel: 10,200 pounds fuel remaining (FOM)
6. Emergency fuel: 8,000 pounds fuel remaining (FOM)
30
OVERHEAD
FUEL INDICATIONS
(EICAS on Upper Display Panel)
Normal Indications


Total fuel quantity in thousands of pounds
 Main tanks must be full if fuel in center tank.
 Exception: Up to 3,000 lbs. may be in center tank if included in ZFW and CG
Fuel TEMP (normally white)
 Display turns amber when within 3 C of fuel freeze temperature in FMS
 EICAS advisory FUEL TEMP LOW
 Temp. probe in left wing tank (coldest due to only one hydraulic heat exchanger)
 Maximum fuel temperature: 49C (OM Vol. 1)
 Prior to takeoff, minimum fuel temperature: (OM Vol. 1)
 LR (GE): -40C
 ER (RR): -37C
 Or 3C above fuel freeze point (whichever higher)
 In flight, minimum fuel temperature: 3C above fuel freeze point (OM Vol. 1)
Expanded Indications

Displayed when:
 The airplane is on the ground and one or both engine(s) off
 One or both cross feed valves open
 One or more fuel tank quantity indications are inoperative
 EICAS message FUEL IN CENTER displayed
 Center tank quantity is amber
 EICAS message FUEL QTY LOW displayed
 Low main tank quantity is amber
 EICAS message FUEL IMBALANCE displayed
Imbalance Indications




A solid white pointer is displayed if:
 Main tank fuel differs more than 1,000 pounds
 Main tank fuel differs more than 200 pounds and a cross feed valve is open
Solid amber pointer replaces the white pointer if EICAS message FUEL IMBALANCE displayed.
Fuel imbalance pointer flashes if fuel balancing is going in the wrong direction.
FUEL BALANCED replaces FUEL QTY on the expanded fuel quantity display
 When fuel within 200 pounds between the main tanks
 Flashes for 5 seconds
31
OVERHEAD
ANTI-ICE
WING selector



OFF: Both wing anti–ice valves commanded closed
AUTO: System controlled by ice detection system (normal position)
 Inhibited on ground
 Inhibited when TAKEOFF mode selected
 Inhibited for 10 minutes after takeoff
ON: In flight only
 Inhibited on ground
 Inhibited for 5 minutes after takeoff, if TAT above 10 deg. C
NOTES:
 WAI displayed below N1 indicator when valve open.
 Heats only three midwing slats
 If one valve fails closed, other valve automatically closed.
 If one engine bleed valve closed, automatically opens isolation valves to provide symmetrical anti-ice.
ENGINE selector



OFF: Engine anti–ice valve commanded closed
AUTO: System controlled by ice detection system (normal position)
 Inhibited on ground
ON: Engine anti-ice valve opens on ground or in flight
NOTES:
 EAI displayed above N1 indicator when valve open
 When anti-ice valve commanded open (AUTO or ON), approach idle selected by EEC
 If leak detected, automatically closes respective engine anti-ice valve
 Heats engine cowl only
NOTES: Anti–Ice Use
 Icing conditions exist when OAT is 10°C or below and
 Visible moisture, or
 Clouds, rain, snow, sleet, ice crystals, fog with visibility less than 1 SM (1600 m)
 Standing water, ice, or snow is present on the ramps, taxiways, or runways
 Engine anti–ice must be ON during all ground operations, and either ON or in AUTO during flight,
when icing conditions exist or are anticipated
 Except when the temperature is below -40°C OAT
32
OVERHEAD
AIR CONDITIONING
EQUIP COOLING switch/light



AUTO: Cooling airflow provided by primary or standby fan
Blank: Off
 Both supply fans not operating
 Smoke / override valve open
 Forward cargo heat valve closed
 OVRD illuminates
OVRD: Override valve open
 In flight aids in smoke evacuation from flight deck
NOTES:
1. Equipment cooling override mode
 Automatically switches to override mode for
 Switch off
 In flight, both supply fans fail
 In flight, low airflow
 Smoke detected in forward supply or ventilation system
 FWD CARGO FIRE ARM switch ARMED
 Override mode uses cabin differential pressure to draw air through the flight deck panels and into
E&E equipment compartment (creates a reverse flow of air across the equipment), then through
the override valve to an overboard vent
 The override mode supplies adequate cooling while the airplane is in cruise
 Airflow decreases as airplane descends and cabin pressure differential decreases
2. Aft equipment cooling
 Primary and backup fans draw air from aft E&E compartment, galleys and lavs.
 Discharges air through aft outflow valve
33
OVERHEAD
GASPER switch/light


ON: Automatic operation of gasper fan
Blank: Fan does not operate
NOTE: Gasper system fan supplies conditioned air from aft cabin distribution duct to passenger service
unit air gasper outlets above each passenger seat
RECIRC FANS UPPER & LOWER switch/light


ON: Automatic operation of recirculation fan
Blank: Off, fan does not operate
 Pack operates at full flow and cabin air exchange rate increased
 Fuel flow increases 0.7% for each fan off
NOTES:
 Lower fans automatically switched off when AFT CARGO FIRE switch ARMED
 Fans should be off when external conditioned air connected (OM Vol. 1)
FLIGHT DECK TEMP selector


AUTO: 65 to 85 F temperature range
 Mid position is 75 F
MAN: Manually controls the flight deck trim air valve
 C: (Cooler) closes the valve
 W: (Warmer) opens the valve
CABIN TEMP selector

C & W: 65 to 85 F temperature range
 Mid position is 75 F
 Each cabin zone may be modulated +/- 10 F (within range 65 to 85 F) by cabin management
system (FA 1L or 4R control panels)
PACK L & R switch/light



AUTO: Packs automatically controlled
 Left pack provides flight deck, A, B, C passenger zones and aft cargo
 Right pack provides D, E, F passenger zones
Blank: Pack flow control valves commanded closed
OFF: Pack flow control valves commanded closed
 Automatically during start
 Automatically due to pack or compressor outlet high temperature,
 Both flow control valves failed closed,
 No pneumatic air, or
 OFF manually selected
NOTE:
 Packs should be off when external conditioned air connected (OM Vol. 1)
NOTES:
1. Flight deck air:
 100% conditioned air from left pack
 No recirculation
 Higher pressure than passenger cabin (smoke/odor prevention)
34
OVERHEAD
2. Standby Cooling Mode
 Pack reverts to standby cooling for certain internal malfunctions
 EICAS message PACK MODE and AIR synoptic STBY COOLING displayed
 Pack cooling capacity less than normal may result in warm cabin temperatures
 One pack in standby cooling
 Shuts down if altitude and outside air temp. do not permit standby cooling
 Both packs in standby cooling or one in standby cooling and other pack inoperative
 Pack or packs continue to operate
TRIM AIR L & R switch/light



ON: Trim air valve commanded open
Blank: Trim air valve commanded closed
FAULT:
 Trim air valve failed closed
 Trim air valve commanded closed due to zone supply duct overheat
 TRIM AIR switch manually selected off
NOTES: Zone temperature control
 Controlled by cabin air conditioning and temperature control system (CACTCS)
 Packs supply cold air as selected by coldest zone
 Hot trim air from bleed air system added through trim air valves in the conditioned air supply ducts
 CACTCS modulates each zone trim air valves to achieve target temperature of the conditioned air in
each zone.
 Trim air from the left engine bleed is added to conditioned air ducts for the flight deck, three
passenger cabin zones, and the aft cargo compartment
 Trim air from the right engine is added to the conditioned air ducts for three passenger cabin zones
and the E & E compartment
 If left or right trim air system is off, the CACTCS attempts to maintain all zones at the average target
temperature
 Flight deck temperature will be maintained between 65 and 85 F
AIR COND RESET button

Push to reset
 Closed pack flow control valves due to
 Overheat, control failure or valve failure
 Closed trim air valves due to
 Overheat, control failure or valve failure
 Failed recirculation fan
 Fault protection
35
OVERHEAD
BLEED AIR
ISLN L, C, R switch/light



AUTO: Bleed isolation valve automatically controlled
Blank: Off, bleed air valve commanded closed
CLOSED:
 Isolation valve closed due to a duct leak or bleed loss
 Isolation valve failed closed
 Switch selected to off
ENGINE L & R switch/light



ON: Engine bleed air valves open when engine bleed air is available
Blank: Off, bleed air valve commanded closed
OFF: Engine bleed valve commanded closed due to
 A protective bleed shut down or duct leak
 Engine not running
 Engine fire switch pulled
 Switch selected to off
APU switch/light



AUTO: APU bleed valve automatically controlled
 Max. altitude for bleed load is 22,000 ft.
Blank: Off, APU bleed valve commanded closed
OFF: APU bleed valve commanded closed due to
 Duct leak
 Valve failed closed
 APU fire switch pulled
 Switch selected to off
NOTES:
 Bleed air supplies: Air conditioning and pressurization, wing and engine anti-ice, APU and engine
start, aft cargo heat, air driven hydraulic pumps, potable water tank pressure, TAT probe aspiration,
and hydraulic reservoir pressure <ER only>
 Normal in flight position of valves:
 L & R ISLN – open and C ISLN – closed
 L & R ENG – open and APU – closed
 Bleed system automatically reconfigures to isolate duct leak
36
OVERHEAD
PRESSURIZATION
OUTFLOW VALVE FWD & AFT switch/light



AUTO: Outflow valve automatically controlled
 Pressurization controlled using ambient pressure and FMC flight plan data
Blank: Outflow valve position displayed on EICAS (M)
MAN: Outflow valve controlled by MANUAL switch
 If both FWD and AFT in MAN, bypasses automatic control and cabin altitude limiter
 OPEN position for 30 seconds will move the valve to full open
MANUAL FWD & AFT switches


OPEN: Drives valve toward open
CLOSE: Drives valve toward close
LDG ALT selector



In: FMS provides landing altitude to cabin altitude controllers
 Landing altitude displayed on AIR synoptic followed by AUTO
 Departure airfield maintained until 400 nm or one-half distance to destination
PULL ON:
 Overrides FMS landing altitude to cabin altitude controllers
 Landing altitude must be manually set
 Landing altitude displayed on EICAS followed by MAN
DECR & INCR: Landing altitude changes by
 First detent – 100 ft. increments
 Second detent – 500 ft. increments
 Landing field elevation limits are -2,500’ to 14,000’ MSL
NOTES:
 Two outflow valves installed, forward and aft
 Most outflow through aft valve for ventilation and smoke removal (20/80% normally)
 System will operate normally on only one valve
 Normally cabin altitude is maximum of 8,000’
 9.4 PSID @ 43,100 ft.
 Loss of cabin pressurization sequence
 10,000’ - EICAS Warning – CABIN ALTITUDE
 11,000’ - Both outflow valves driven full closed
 13,500’ - Oxygen masks drop from PSUs
37
OVERHEAD
WINDSHIELD WIPER
WIPER L & R selector




OFF
INT
LOW
HIGH (Both L & R required for Cat. II/III ILS approaches)
NOTE: Do not use wipers on dry windshield, damage to hydrophobic coating
LIGHT CONTROL
STORM switch/light


ON: Illuminates at full brightness
 Illuminated indicator lights
 Flood lights on glare shield, instrument panel, and aisle stand
 Dome lights
Blank: Off
MASTER BRIGHT selector


PUSH ON/OFF
 Controls brightness of panel lights and displays
 Eleven rheostats with white dot
 Limits adjustment range of individual controls
 Has full range when individual controls in center detent
Outer knob: Always controls brightness of:
 Standby compass
 Standby instruments (ADI, airspeed, altimeter)
 Clocks
IND LTS switch



TEST (hold)
 Illuminates all indicator lights to full brightness for 10 secs. then to dim
BRT
DIM
BEACON switch/light

ON: Two red anti-collision lights operate
 Computer sensed
LANDING LEFT and RIGHT switch


OFF
ON: Illuminates wing root mounted lights
 Optimized for flare and ground roll
 Computer sensed
LANDING NOSE switch


OFF
ON: Illuminates two nose gear strut mounted lights
 Optimized for approach
38
FORWARD CAPTAIN’S AND FIRST OFFICER’S
FORWARD CAPTAIN’S AND FIRST OFFICER’S
MASTER WARNING / CAUTION
WARNING light (red) with aural


Illuminated: EICAS warning message displayed on EICAS panel
 Warning cannot be canceled (must clear warning condition)
Inhibited takeoff only - V1 to 400 RA or 25 secs.
CAUTION light (amber) with aural



Illuminated: EICAS caution message displayed on EICAS panel
 Caution can be canceled / recalled
Inhibited takeoff - 80 kts. to 400 RA or 20 secs. after TO
Inhibited landing - LAND 2/3 below 200 RA to 75 kts, 40 secs, or 800 RA
 Except AUTOPILOT, AUTOTHROTTLE DISC, NO AUTOLAND, S/B EXTENDED
CPDLC
CPDLC switches



ACPT: Push –
 Positive response to displayed message down linked to the origin of displayed message
 Functions the same as selecting an MFD communications display ACCEPT command key.
CANC: Push –
 Message is removed from the display
 Functions the same as selecting an MFD communications display CANCEL command key.
RJCT: Push –
 Negative response to displayed message down linked to the origin of displayed message
 Functions the same as selecting an MFD communications display REJECT command key.
EFIS CONTROL
MINS selector




RADIO: selects radio altitude as the PFD minimums reference
 No line or pointer displayed
BARO: selects barometric altitude as the PFD minimums reference
 Number is also represented as a pointer and line on the altitude scale
RST: Push
 Resets the PFD minimums alert display
 Blanks the minimums display when green
Rotate: adjusts the PFD radio or baro minimums altitude
NOTE:
 When the airplane descends below selected minimum altitude
 Both green displays turn amber and flash for 3 seconds, then
 Turns steady amber
39
FORWARD CAPTAIN’S AND FIRST OFFICER’S
BARO selector




IN: selects inches of mercury as the PFD barometric reference
HPA: selects Hectopascals as the PFD barometric reference
STD selects the standard barometric setting for the PFD barometric reference
 29.92 inches Hg/1013 HPA
 If STD is displayed, selects the preselected barometric setting
 If no preselected barometric setting is displayed, displays the last value before STD was selected.
Rotate: adjusts the PFD barometric reference.
FPV button

Push – displays the PFD flight path vector.
MTRS button

.
Push – displays PFD altitude meters indications.
ND Mode selector





APP:
 Displays localizer and glide slope information in heading–up format
 Displays reference ILS receiver, ILS frequency or identification, course, and DME
 Weather radar and TCAS are not displayed in CTR APP mode.
VOR:
 Displays VOR navigation information in heading–up format
MAP:
 Displays FMC–generated route and map information, airplane position, heading, and track
 Displays waypoints, including the active waypoint, within the selected range
 Displays VNAV path deviation.
PLN
 Displays a nonmoving, true north–up, route depiction
 Airplane symbol represents actual airplane position
 Allows route step–through using the CDU legs page
CTR:
 Push - displays the full compass rose (centered) for APP, VOR, and MAP modes.
VOR/ADF switches

Displays the pointer, frequency, or identification (if tuned and identified) and associated DME
information on the bottom of ND
ND map display switches


Select detailed ND information displays
Displays can generally be selected simultaneously

WXR: Displays weather radar information
 Not displayed in PLN mode
 Cannot be displayed on same ND simultaneously with TERR
STA:
 Displays high and low altitude navigation aids, if ND range selector set 10, 20 or 40 NM
 Displays high altitude navigation aids, if ND range selector set to 80, 160, 320, or 640 NM
WPT:
 Displays waypoints, if the ND range selector is in the 10, 20 or 40 NM range.
APRT: Displays airports on all ranges.
DATA: Displays the FMC estimated time of arrival, altitude at each waypoint, and altitude constraints
at each waypoint.




40
FORWARD CAPTAIN’S AND FIRST OFFICER’S


POS:
 Displays ADIRU and GPS positions
 Displays VOR raw data radials extended from the nose of the airplane to the stations displayed
on the CDU NAV RAD page.
TERR: Displays terrain data
 Not displayed in PLN mode
 Cannot be displayed on same ND simultaneously with WXR
ND Range selector


Selects the desired ND nautical mile range scale
TFC: Push – displays TCAS ND information
NOTE:
 The EFIS control panels normally are used to control display options, mode, and range for the
respective PFDs and NDs.
 If an EFIS control panel fails, the displays can be controlled through the related CDU.
INSTRUMENT SOURCE SELECT
NAV switch/light


Blank: Active FMC provides information to generate ND
 If both FMCs fail, CDU automatically selected
CDU: CDU provides information to generate ND
DSPL CTRL switch/light


Blank: Automatically selects processing channels
 Automatically reconfigures for display or channel failure
ALTN: Alternate processing channel selected
AIR DATA / ATT switch/light


Blank: ADIRU provides air data and attitude to PFD and ND
 Alternate sources or SAARU automatically selected
ALTN:
 Captain:
 Air data: SAARU single channel
 Attitude: SAARU
 FO:
 Air data: ADIRU single channel
 Attitude: SAARU
NOTE:
 Instrument source select switches provide alternate information sources for the PFDs and NDs
 Detected source failures: In the normal position, they provide automatic instrument source selection
 Undetected source failure: The non-normal (ALTN or CDU) position provides the capability for
manual selection of PFD and ND sources
 Display is missing or appears faulty
41
FORWARD CAPTAIN’S AND FIRST OFFICER’S
BRAKE
BRAKE SOURCE light

Primary brakes (right hydraulic) and alt./reserve brakes (center hydraulic) low pressure
 Brake accumulator still available
BRAKE ACCUM gauge


0 – 1: Accumulator precharge
1 – 4: Brake accumulator pressure
 Provides:
 Several brake applications
 Parking brake application
HEADING / FMC / DISPLAY
HDG REF switch/light


NORM
 Magnetic north normally displayed
 Automatically switches to true north when beyond 82 deg. N or S or near magnetic poles
 PFDs, NDs, and FMCs displays are changed
 Only LNAV available to AFDS when in true north mode
TRUE
 Forces switch to true north at all latitudes
 When AFDS roll mode HDG SEL, switching the heading reference switch from NORM to TRUE
or TRUE to NORM engages HDG HOLD
 When AFDS roll mode TRK SEL, switching the heading reference switch from NORM to TRUE or
TRUE to NORM engages TRK HOLD
 When north of 82N or south of 82S Latitude, the HDG REF must be selected to TRUE if HDG
SEL is the active AFDS roll mode
FMC selector



AUTO: Automatically selects other FMC if one fails
 Automatically selects CDU nav. if both fail
L: Left FMC provides guidance
R: Right FMC provides guidance
42
FORWARD CAPTAIN’S AND FIRST OFFICER’S
INBOARD DSPL selector



NORM: The normally selected displays for the inboard display
 MFD: displays selections made on the DSP
 NAV: displays the ND and inhibits selections made from the DSP
EICAS:
 Displays EICAS and blanks the upper center display unit
 Inhibits most selections made from the DSP
 Limited ENG, FUEL, and AIR displays can be selected
PFD: Displays PFD
 Displays the PFD
 Blanks the PFD on the outboard display unit
 Inhibits selections made from the DSP
NOTE: The PFD automatically appears on an inboard display unit if the adjacent outboard display unit
fails, regardless of switch position
NOTES: Display Unit Failure Automatic Switching
 The right inboard, left inboard, and lower center displays may be used as MFDs
 If an outboard display unit fails, the PFD automatically moves to the inboard display unit, regardless
of the Inboard Display Selector position.
 The Inboard Display Selector and the Display Select Panel (DSP) no longer have any control
over that inboard display unit.
 If the upper center display unit fails, the EICAS display automatically moves to the lower center
display unit
43
FORWARD CAPTAIN’S AND FIRST OFFICER’S
INTENTIONAL BLANK PAGE
44
CENTER INSTRUMENT
CENTER INSTRUMENT
MODE CONTROL PANEL
A/P switch/light



Push: either switch can engages the autopilot
If either flight director switch is ON, the autopilot engages in the selected flight director mode(s)
If both flight director switches are OFF, the autopilot engages in:
 Roll Mode:
 Heading hold (HDG HOLD) or track hold (TRK HOLD), or
 If bank angle is greater than five degrees, attitude hold (ATT)
 Pitch Mode: vertical speed (V/S) or flight path angle (FPA)



NOTES: Autopilot Disengagement:
Normal autopilot disengagement is through either control wheel autopilot disconnect switch
The autopilots can also be disengaged by:
 MCP autopilot disengage bar, or
 Overriding with the control column, control wheel, or rudder pedals
 Pedals will only disengage the autopilots with LAND 2 or LAND 3 annunciated
Automatic autopilot disconnect occurs for some failures detected by the autopilot
The EICAS warning AUTOPILOT DISC is displayed if the autopilot is manually or automatically
disconnected
Depending upon the system failure, it may be possible to reengage an autopilot by pushing the
autopilot engage switch



A/T ARM L R switch


ARM
 Arms the respective autothrottle for engagement
 Selecting A/T, FLCH, VNAV, or TO/GA engages the autothrottles
 On takeoff, pushing a TO/GA switch prior to 50 KIAS will engage the autothrottle in the THR REF
mode
 If the autothrottle is not engaged by 50 KIAS, it cannot be engaged until above 400 ft.
OFF: disconnects the selected autothrottle.
NOTES:
 Autothrottle operation is controlled from the MCP and the CDUs
 The MCP provides mode and speed selection
 The CDU provides FMC thrust reference mode selection
 When the VNAV mode is selected, the FMC selects the autothrottle modes and target thrust
values
 The autothrottle can be operated without using the flight director or the autopilot
 The autothrottle can be manually overridden or disconnected by pushing either autothrottle
disconnect
45
CENTER INSTRUMENT
LNAV switch/light

Push (illuminated):
 Illuminated – LNAV armed or engaged.
 Arms, engages, or disarms LNAV as the roll mode.
 When armed LNAV in white displayed on the PFD roll flight mode annunciator
 The previous roll mode remains active.
 When engaged, LNAV in green displayed on the PFD roll flight mode annunciator.
NOTES: LNAV
 LNAV engages if
 Above 50 feet radio altitude, and
 Within 2.5 NM of the active leg
 If not within 2.5 NM of the active leg and on an intercept heading to the active leg, remains
armed then engages when approaching the active leg
 Selection of LNAV with the airplane not on a heading to intercept the active leg, displays NOT ON
INTERCEPT HEADING in the CDU scratch pad.
 Selection of LNAV when an active FMC route is not available displays NO ACTIVE ROUTE in the
CDU scratchpad.
 LNAV maintains current heading when:
 Passing the last active route waypoint
 Passing the last waypoint prior to a route discontinuity
 Passing the last route offset waypoint
 Activating the inactive route
 Activating an airway intercept and not within LNAV engagement criteria.
 LNAV disengages when
 Selecting heading hold (HDG HOLD) or track hold (TRK HOLD)
 Selecting heading select (HDG SEL) or track select (TRK SEL)
 When the localizer captures
 Dual FMC failure
 LNAV may be re–engaged if there is an active CDU ALTN NAV route available
 LNAV is disarmed by pushing the LNAV switch a second time.
VNAV switch/light



Push
Illuminated – VNAV armed or engaged.
Arms, engages, or disarms VNAV as the pitch mode.
 When armed VNAV in white displayed on the PFD pitch flight mode annunciator below 400 feet.
 VNAV engages 400 feet above runway elevation.
 When engaged VNAV SPD, VNAV PTH or VNAV ALT in green displayed on the PFD pitch flight
mode annunciator.
46
CENTER INSTRUMENT
NOTES: VNAV
 If VNAV is selected and the FMC has insufficient data to provide VNAV guidance (such as the gross
weight is invalid or there is no end–of–descent point in descent) displays PERF/VNAV NOT
AVAILABLE in the CDU scratchpad.
 VNAV SPD pitch mode
 AFDS commands pitch to hold target airspeed
 Autothrottle operates in the THR REF, THR, IDLE or HOLD mode, as required by the phase of
flight.
 VNAV PTH pitch mode
 AFDS commands pitch to maintain FMC target altitude or the VNAV path
 Autothrottle maintains speed.
 VNAV ALT pitch mode
 AFDS commands pitch to maintain the MCP selected altitude when that altitude
 Lower than the VNAV commanded altitude in climb, or
 Higher than the VNAV commanded altitude in descent.
 VNAV is disengaged by:
 Engaging TO/GA, FLCH SPD, V/S, FPA, ALT or G/S capture pitch mode.
 Dual FMC failure.
 VNAV is disarmed by:
 Pushing the VNAV switch a second time, or
 Arming APP
FLCH switch/light





Push
Illuminated –flight level change mode engaged
FLCH SPD is displayed on the PFD pitch flight mode annunciator as the pitch mode.
If the IAS/MACH window is blank, the IAS/MACH window opens
 If valid, to the FMC target speed, or
 If not valid, to the current speed
The autothrottle automatically engages:
 Climb – engages in THR mode; the thrust limit is CLB thrust
 Descent – engages in THR mode, followed by HOLD if the thrust levers reach idle
HDG/TRK switch


Push – alternately changes the heading/track window, PFD, and ND selected heading/track
references between heading and track
Changes the PFD roll flight mode annunciator, if the HDG or TRK mode is engaged.
Heading/Track window




Displays the selected heading or track.
The selected heading or track is displayed on the PFD and ND.
If approach is armed, the numbers in the heading/track window automatically changes to the selected
ILS front course heading at LOC capture
Displays 360 degrees when power is first applied.
Heading/Track HOLD switch




Push – selects heading hold (HDG HOLD) or track hold (TRK HOLD) as the roll mode
Displays HDG HOLD or TRK HOLD on the PFD roll flight mode annunciator
AFDS commands wings level and holds the heading or track established when wings level is
established.
Illuminated – the heading/track HOLD mode is engaged.
Heading/Track Selector (middle)

Rotate – sets heading or track in the heading/track window and on the PFDs and NDs.
47
CENTER INSTRUMENT
Heading/Track SEL switch (inner)




Push – selects heading select (HDG SEL) or track select (TRK SEL) as the roll mode
Displays HDG SEL or TRK SEL on the PFD roll flight mode annunciator
AFDS controls roll to fly the selected heading or track
Bank is limited by the bank limit selector.
BANK LIMIT selector (outer)

Rotate – sets the AFDS commanded bank limit when in the heading select (HDG SEL) or track select
(TRK SEL) roll mode:
 AUTO – varies between 15 – 25 degrees, depending on TAS
 5, 10, 15, 20 or 25 – the selected value is the maximum, regardless of airspeed
Altitude Selector (inner)


Rotate – sets the altitude in the altitude window and on the PFD altitude indication display
Push – Only operates when VNAV is engaged.
 During climb or descent with altitude constraints, each push deletes the next waypoint constraint
between the airplane altitude and the altitude window
 During climb with no altitude constraints, and the altitude window set above the FMC cruise
altitude, the cruise altitude is changed to the altitude window value
 During cruise with the altitude window set above or below FMC cruise altitude, the FMC cruise
altitude resets to the altitude window altitude
 In VNAV PTH or VNAV ALT pitch mode, the airplane begins a climb or descent toward the
altitude window altitude
 Within 50 NM of the top–of–descent (T/D) point, with the altitude window set below cruise
altitude, the airplane initiates the descend now (DES NOW) feature
LOC switch/light







Push –
Arms, disarms, engages, or disengages localizer (LOC) as the roll mode
Displays LOC in white (armed) on the PFD roll flight mode annunciator before localizer capture
Displays LOC in green (engaged) on the PFD roll flight mode annunciator after localizer capture
Arms the AFDS to capture and track inbound on the front course
 The capture point varies based on range and intercept angle
 Localizer capture occurs when the intercept track angle is within 120 deg of the localizer course.
The localizer mode can be disarmed before localizer capture by:
 Pushing the localizer switch a second time, or
 Selecting APP or any other roll mode.
The localizer mode can be disengaged after localizer capture by:
 Selecting another roll mode
 Pushing a TO/GA switch
 Disengaging the autopilot and turning both flight director switches off, or
 Pushing the localizer switch a second time above 1,500 feet radio altitude
 Reverts to the default roll mode
48
CENTER INSTRUMENT
APP switch/light








Push –
Arms, disarms, engages, or disengages
 Localizer (LOC) as the roll mode, and
 Localizer capture occurs when the intercept track angle is within 120 deg of the localizer
course
 Glide slope (G/S) as the pitch mode
 Glide slope captures when the intercept track angle is within 80 degrees of the localizer
course.
Glide slope can capture before localizer capture.
 Displays LOC and G/S in white (armed) on the PFD roll and pitch flight mode annunciators prior
to localizer and glide slope capture
Displays LOC and G/S in green (engaged) on the PFD roll and pitch flight mode annunciators after
each is captured
Approach mode can be disarmed before localizer or glide slope capture by
 Selecting APP, LOC, LNAV, or VNAV.
 By pushing the approach switch a second time above 1,500 feet radio altitude
 AFDS reverts to default roll and pitch modes
Approach mode disengages with localizer captured and glide slope armed, by selecting HDG SEL or
HDG HOLD
With glide slope captured and localizer armed, by selecting any other pitch mode except VNAV
After localizer and/or glide slope are captured
 By engaging the TO/GA mode, or
 By disengaging the autopilot and turning both flight director switches off
DISPLAY SELECT
L INBD, LWR CTR, R INBD button
Push: The location of the MFD display is indicated by the illuminated annunciator light
ENG button

Displays secondary engine indication on
 Center lower MFD, or
 Center upper MFD if lower busy or failed
STAT button




Displays EICAS status messages
Displays APU RPM and EGT and oil pressure, temperature and quantity
Displays crew oxygen bottle pressure
 Two bottles located in E & E compartment
 Minimum dispatch pressure 1,000 PSI (OM Vol. 1)
Displays L, C & R hydraulic quantity and pressure
 LO (amber) – quantity low
 RF (white) – system requires service
 OF (white) – system over filled
ELEC button

Displays electrical synoptic
HYD button

Displays hydraulic synoptic
49
CENTER INSTRUMENT
FUEL button

Displays fuel synoptic
AIR button

Displays air systems synoptic
DOOR button




Eight manual passenger entry / emergency exit doors
 Doors are plug type doors with pressure relief panels
 Each door has pneumatic emergency evacuation assist
 Each door has emergency escape slide
 If ARMED door opened from outside, pneumatic assist and slide deployment deactivated
 At greater than 80 kts., flight lock electrically engaged to prevent doors opening
 If electrical power fails, spring loaded locks removed
Forward and aft electrical cargo doors
 Requires ground handling bus be powered to operate
 APU or PRIMARY EXT PWR connected/available
Bulk cargo door
 Manually operated counterbalanced door
Two manual E&E access doors
NOTE:
 A single open door will be identified by an EICAS message identifying the specific door
 If more than one door is open, the EICAS message DOORS will be displayed
GEAR button




Brake temperature
 Blank box & digital – temperature less than 3.0 (normal)
 Solid box & digital white – temperature 3.0 to 4.9 (normal)
 Box & digital amber – temperature 5.0 to 9.9 (overheat)
Gear door status
 Crosshatched – not closed
 CLOSED – door closed
 Empty box – door indicators inoperative
Fault indication
 BRAKE – brake deactivation
 ASKID – antiskid fault
Tire pressure indication <LR only>
 Pressure displayed inside tire symbol
 From 0 to 400 PSI
 Digital white – normal pressure
 Box & digital amber – pressure either high or low or excessive differential between tires on same
axle
 EICAS advisory message TIRE PRESS is displayed
FCTL button

Displays flight control synoptic
50
CENTER INSTRUMENT
CHKL button



Push – displays or deselects electronic checklists
Three types of checklists can be displayed:
 Normal: arranged in the menu sequence. Selecting the NORMAL menu key or the checklist
display switch results in the display of the next incomplete normal checklist in sequence.
 Non-normal associated with EICAS messages (annunciated): annunciated non-normal checklists
are accessed by pushing the checklist display switch. Any non-normal checklist can be accessed
using the NON-NORMAL menu.
 Non-normal not associated with EICAS messages (Unannunciated): Unannunciated checklists
are accessed only through non-normal menu selection.
When multiple EICAS messages exist, the checklist queue priority is Warnings, Cautions, Advisories,
and Unannunciated
COMM button
NAV button

Push: displays navigation and map data on MFD
 Controlled by Captain’s EFIS Control Panel
CANC / RCL button

Push:
NOTES:
 A new display selection automatically replaces the previous one
 A second selection of the same display for the lower center display unit blanks the display.
 A second selection of the same display on either inboard display causes display of the ND.
 If there is more than one page of Status messages, pushing STAT pages through the messages
display
 The cursor automatically appears on the selected display
 Display select panel control is also available through any CDU
 This capability is available at all times
 Once display select panel control is selected on one CDU, it cannot be selected on the other two
CDUs
INTEGRATED STANDBY FLIGHT DISPLAY
Integrated Standby Flight Display (ISFD)







Displays attitude, altitude, airspeed, and magnetic heading
Receives altitude and airspeed from dedicated pitot/static module
Attitude information is provided by internal inertial sensors
ILS information is provided by the center ILS receiver
Heading information received from the same source as the captain’s PFD
 Heading information is not available in polar regions.
Powered by left flight control DC bus
After power up starts 90 sec. initialization
APP button

Push: cycles between APP, BCRS, and blank
 ILS from center receiver
+ / - buttons

Adjust display brightness
51
CENTER INSTRUMENT
ATT RST button

Push and hold (two seconds)
 Aligns horizon with the airplane symbol
 Takes approximately ten seconds
 Starts new initialization sequence if previous attempt failed (ground only).
HP/IN button:

Push: cycles between hectopascals and inches
BARO knob


Turn: sets baro. pressure
Push: cycles between STD and set baro. pressure
GND PROX
G/S INHIBIT switch/light


GND PROX
 GPWS alerts when illuminated:
 GLIDE SLOPE, TOO LOW FLAPS, TOO LOW GEAR
 Push to inhibit/override
 Light inhibited by respective G/S, FLAP, GEAR switch light
G/S INHIB
 Push: Overrides GLIDE SLOPE alert below 1000 RA
FLAP OVRD switch/light


OVRD illuminated
 TOO LOW FLAPS
 Too close to terrain with flaps not in landing configuration
Push: Overrides alert
GEAR OVRD switch/light


OVRD illuminated
 TOO LOW GEAR
 CONFIG GEAR
 Unsafe terrain clearance with gear not down
Push: Overrides alert
TERR OVRD switch/light


OVRD illuminated
Push: Inhibits EGPWS (look ahead) terrain alerts and display
52
CENTER INSTRUMENT
LANDING GEAR
LANDING GEAR lever

UP: Retracts gear
 Gear doors open
 Gear trucks hydraulically tilted to retract position
 Gear retracted, uplocks engaged, doors closed
 Gear hydraulic system depressurized

DN: Extends gear
 Releases door and gear uplocks
 Gear free falls to down and locked
 Downlocks powered over center and doors closed
 Gear trucks hydraulically tilted to flight position
NOTE:
LANDING GEAR LIMIT
RETRACT
270K - .82M
EXTEND
270K - .82M
LOCK OVRD button

Overrides ground sensing lock to allow gear handle to be raised
ALTN GEAR switch


NORM – gear controlled by LANDING GEAR lever
DOWN
 Dedicated DC electric powered hydraulic pump uses center hydraulic system fluid
 Releases door and gear uplocks
 Gear free falls to down and locked
 Gear doors remain open
 EICAS message GEAR DOOR displayed
NOTES:
1. EICAS display of gear
 Normal
 DOWN (green) – gear down and locked
 Cross hatched (white) – gear in transit
 UP (white) – gear up and locked, after 10 seconds display blanks
 Empty box (white) – all gear position indicators inop.
 Expanded non-normal
 Each gear (nose, left and right main) displayed with indication as above
2. Alternate Gear Extension
 The landing gear lever position has no effect on landing gear alternate extension
 Following an alternate extension, the landing gear can be retracted by the normal system, if it is
operating
 Select landing gear lever DN then UP to retract the landing gear
3. Main wheel well fire detection
 Single fire detection loop in main wheel wells
 Fire detection only, no fire extinguishing system
 Lower landing gear to cool brakes (QRH)
53
CENTER INSTRUMENT
4. Main wheel well fire indications:
 Fire bell
 Master WARNING lights illuminate
 EICAS warning message FIRE WHEEL WELL
AUTOBRAKE
AUTOBRAKE selector




OFF: Deactivates and resets system
 After takeoff selector automatically moves to OFF
RTO:
 Activated by both thrust levers to idle above 85 kts. on ground
 Applies maximum brake pressure
 Can only be released by switch to OFF
 After takeoff reverts to OFF position automatically
DISARM:
 Disengages system
 Releases brake pressure
 When disarmed after landing, selector automatically move to DISARM
1, 2, 3, 4, MAX AUTO: Deceleration rates
 Combination of brakes, reversers, speed brakes
 Activated when:
 Both thrust levers idle, and
 Wheel spin up after 2 sec. delay
 MAX AUTO
 Less pressure than maximum manual breaking
 Limited to level 4 until pitch angle less than one deg.
NOTES:
 Autobrakes only available with normal brake system
S
T
O
P
AUTOBRAKES DISARM
Speedbrakes moved to DOWN after ground deployment
Thrust lever advanced after landing
AUTOBRAKE selector to DISARM or OFF
Pedal breaking applied greater that autobrake force
Autobrake fault
Normal antiskid system fault
Autobrakes applied after loss of normal brake hydraulic pressure
Loss of inertial data from ADIRU
54
CENTER INSTRUMENT
DSPL CTRL switch/light (upper and lower center displays)


Blank: Automatically selects processing channels
 Automatically reconfigures for display or channel failure
ALTN: Alternate processing channel selected
EICAS EVENT RCD button


Records currently displayed engine indications and other EICAS information
Up to five events may be recorded
CTR PNL BRIGHTNESS
UPR DSPL

Adjusts upper display unit brightness
LWR DSPL / WXR


Outer knob: Adjusts lower display unit brightness
Inner knob: Adjusts brightness of radar return on lower display unit
55
CENTER INSTRUMENT
INTENTIONAL BLANK PAGE
56
CONTROL COLUMN / WHEEL & RUDDER / BRAKE PEDALS
CONTROL COLUMN / WHEEL & RUDDER / BRAKE PEDALS
Pitch control (control column)




Control column controls left and right elevators
PFCs provide artificial feel based on airspeed, forces increase as
 Airspeed increases for a given displacement (speed)
 Column displacement increases
Normal mode: control column commands PFCs to generate a pitch maneuver
PFCs automatically compensates for pitch forces of:
 Thrust changes
 Landing gear configuration changes
 Flap configuration changes
 Speedbrake configuration changes
 Turns up to 30 deg. bank
Pitch Trim switches



Control column not displaced
On ground: directly sets stabilizer position
In flight:
 Inhibited with auto pilot engaged
 Sets trim reference speed
 At Vmn stall protection inhibits nose up trim
 At Vmo/Mmo overspeed protection inhibits nose down trim
NOTE: Pitch Envelope Protection
 Stall Protection
 Provides enhanced crew awareness of the approach to a stall or to a stalled condition
 Limits the speed to which the airplane can be trimmed
 At approximately the Vmn, trim reference speed limited
 Trim is inhibited in the nose up direction
 Continuous aft column force required to maintain airspeed below the Vmn speed
 Use of the alternate pitch trim levers does not reduce the column forces
 Near stall speed, the column force increases to a higher level than would occur for an
equivalent out–of–trim condition above the Vmn
 Autothrottle supports stall protection if armed and not engaged
 If speed decreases to near stick shaker activation, autothrottles engage in SPD or THR REF
and advance thrust to maintain Vmn (approximately the top of the amber band) or the speed
set in the mode control panel speed window, whichever is greater
 The EICAS message AIRSPEED LOW is displayed
 When pitch mode is FLCH or TO/GA, or the airplane is below 400 feet above the airport on
takeoff, or below 100 feet radio altitude on approach, the autothrottle will not automatically
engage.
 Overspeed Protection
 Limits the speed to which the airplane can be trimmed
 At Vmo/Mmo, overspeed protection limits the trim reference speed so that trim inhibited in
nose down direction
 Continuous forward column force required to maintain airspeed above Vmo/Mmo
 Use of the alternate pitch trim levers does not reduce column forces.
57
CONTROL COLUMN / WHEEL & RUDDER / BRAKE PEDALS
Roll control (control wheel)




Aileron and flapron controlled by control wheel
 Ailerons locked out at high speed
Ailerons move down at flaps 5, 15, and 20 position
Flaprons move down and aft in proportion to TE flaps
Spoilers extend after few degrees of wheel displacement
 Spoilers 4 and 11 mechanically connected by cable to control wheel
 Spoilers 5 and 10 locked out at high speed
NOTE: Roll Envelope Bank Angle Protection
 Provides roll control wheel inputs when airplane bank angle exceeds approximately 35°.
 If boundary is exceeded, control wheel force rolls the airplane back within 30° of bank.
 Roll command force can be overridden by the pilot
 Maximum control wheel deflection always commands maximum control surface deflection
 A/P DISENGAGE bar disables bank angle protection.
 Excessive bank angle indicated on PFD bank indicator
 Indicator changes color to amber at bank angles exceeding 35
Yaw control (rudder pedals)


Rudder pedals control single rudder
 Rudder effective above 60 kts.
 Nose gear turns 7 deg. during taxi
Rudder ratio changer automatically reduces rudder deflection as speed increases
NOTES:
 Wheel to Rudder Cross Tie
 Operates in flight below 210 kts. in normal mode
 Deflects rudder up to 8 degs proportional to control wheel displacement
 During engine failure provides additional controllability
Brakes (brake pedals)


Main gear, left and right, have carbon disc brakes each wheel
Nose gear does not have brakes
 Snubber in wheel well stops rotation on retraction
NOTES:
1. Normal brakes:
 Powered by right hydraulic system
 R ELEC DEMAND pump always operates on ground to ensure pressure
 Antiskid protection for individual main gear wheels
 Autobrakes available
2. Alternate brakes:
 Automatic transfer if normal brake (right hydraulic) pressure low
 Antiskid protection:
 Main gear forward and middle axles – tandem wheel pairs
 Main gear aft axle – individual wheels
 No autobrakes available
58
CONTROL COLUMN / WHEEL & RUDDER / BRAKE PEDALS
3. Reserve brakes:
 Automatic transfer if center hydraulic quantity low
 C1 ELEC pump and reserve fluid isolated from center system
 If airspeed greater than 60 kts.:
 Nose gear actuation and steering isolated
 If/when airspeed less that 60 kts:
 Nose gear actuation and steering reconnected
 Antiskid protection same as alternate brakes
 No autobrakes available
4. Accumulator brakes:
 Located in normal brake system
 If both right and center hydraulic pressure lost, provides several brake application
 Parking brake can be applied
 Antiskid protection
 No autobrakes available
5. Taxi brake release:
 Reduces brake temperature and wear
 Speed less than 45 kts.
 Anti-skid releases brakes of one axle pair on each brake application
 Sequences through axle pairs
6. Antiskid Protection
 Locked wheel – wheel speed comparison
 Touchdown & hydroplaning – inertial ground speed data
Hyd. System
Antiskid
 Locked wheel
 Touchdown
 Hydroplaning
Autobrakes
NORMAL
Right
Each
wheel
BRAKE SYSTEMS
ALTERNATE
Center through alternate
Anti-skid valves
RESERVE
C1 Primary pump
Isolated operation
with fluid from C
reservoir
Fwd & mid axles
 Tandem wheel pairs
Aft axle
 Each wheel
Yes
None
59
ACCUMULATOR
Accumulator
Connected to
normal brake
system
Provided
CONTROL COLUMN / WHEEL & RUDDER / BRAKE PEDALS
INTENTIONAL BLANK PAGE
60
PEDESTAL
CONTROL PEDESTAL
PARKING BRAKE lever





Mechanically latches the pedals in the depressed position
Commands the parking brake valve to close
Sets parking brake using normal, alternate or accumulator brake hydraulic source
Parking brake pressure maintained by brake accumulator, if normal and alternate not pressurized
EICAS memo message PARKING BRAKE SET is displayed
STAB position indicator



Stabilizer green band
 Allowable takeoff trim range
 Display calculated by FMC
 Based on gross weight, takeoff thrust, and CG information
Green band defaults to midrange when:
 No information available
 V1 speed not selected or entered
If stabilizer signal not present or invalid, green band and pointer display blanked
NOTE:
 Nose gear oleo pressure switch provides automatic cross–check of CG
 STAB GREENBAND EICAS advisory message indicates disagreement with the computed
stabilizer greenband
ALTN PITCH TRIM levers

NOSE DOWN / NOSE UP
 Normal mode: Changes reference airspeed and moves stabilizer
 Does not disengage autopilot, if engaged
 Moves stabilizer during stall and overspeed envelope protection
 Secondary and direct mode: moves stabilizer with cable to stab. control modules
STAB C & R switches


NORM
 Hydraulic power to stabilizer trim control module
 If unscheduled stabilizer motion, automatically removes hydraulic power to module
CUTOUT: Shuts off hydraulic power to stabilizer trim control module
61
PEDESTAL
FUEL CONTROL
FUEL CONTROL L & R switches


RUN:
 AUTOSTART ON
 Opens the spar fuel valve
 Arms the engine fuel valve
 EEC opens the valve when required
 Arms the selected igniter(s)
 EEC turns the igniters on when required
 AUTOSTART OFF
 Opens the spar fuel valve
 Opens the engine fuel valve
 Turns igniters on
CUTOFF:
 Closes the fuel valves
 Removes igniter power
 Unlocks the engine fire switch
NOTE:
ENGINE WARM UP/COOL DOWN TIME
ER
LR
RR engine
GE engine
5 mins.
3 mins.
Before takeoff
If engine has been
shutdown less than 1.5 hrs:
NA
3 mins.
After landing
1 min.
3 mins.
SPEED BRAKE / SPOILERS
SPEED BRAKE lever



DOWN: Spoilers normally retracted

Can be extended:
 Manually
 Spoilers extended proportional to lever position
 Reverse thrust lever raised to reverse idle detent
ARMED: Extend when
 Landing gear on ground (not tilted), and
 Thrust levers at IDLE
 Autospoilers not available in secondary and direct flight control modes
UP: Spoilers normally fully extended
 Automatically retracted if thrust lever advanced to takeoff range
62
PEDESTAL
THRUST / REVERSE THRUST
Thrust levers


TO/GA
 On ground: Push by 50 kts. to engage auto throttles
 Inhibited between 50 kts. and 400 ft.
 After takeoff: Second push removes takeoff derate and provides THR REF
 In flight: Armed when flaps extended
 First push: 2000 FPM climb
 Second push: THR REF/GA climb
DISCONNECT: Disconnects autothrottles
Reverse Thrust levers
NOTES:
 Powered by respective engine hydraulic system
 To deploy requires:
 On ground
 Engine running
 Thrust levers in idle position
 Hydraulic pressure to reverser system
 EEC controls:
 Reverser isolation valve
 Thrust limits in reverse
 When reverse levers raised to interlock position:
 Autothrottles disengages
 Auto speedbrakes deploy
 Amber REV above EPR/N1 display – thrust reverser in transit
 When interlock removed and the reverser system is activated:
 Reverser translating sleeves hydraulically move aft
 Fan flow blocker doors rotate to direct fan air through stationary cascade guide vanes
 Thrust Levers cannot be moved forward until the Reverse Thrust Levers are fully down
 Full reverse thrust available
 Green REV above EPR/N1 display – thrust reverser fully deployed
FLAP
LR LIMIT
(kts.)
>275 or
>20K ft.
265
245
230
225
Flaps
1
5
15
20
ER LIMIT
(kts.)
>265 or
>20K ft.
255
235
215
195
25
30
185
170
200
180
UP
FLAP LEVER
Slats
Use
Up
Ret
Up
5
15
20
Mid
Mid
Mid
Mid
25
30
Full
Full
Deployment
inhibited
Autoslats
Load Relief
N/A
Cruise Inhibit
N/A
Takeoff
Armed
Takeoff and
Eng. out landing
Normal
Landing
63
Armed
N/A
PEDESTAL
NOTES:
1. Flap EICAS display on upper display panel



Primary mode (left): Single tape with digital of flap lever position
 Removed after 10 secs. when flaps up
 Digits indicate in transit (magenta) or commanded position (green)
Secondary mode (center): Expanded left and right tapes with separate LE and TE display with
 Digits indicate in transit (magenta) or commanded position (green)
Alternate mode (right): Expanded left and right tapes with separate LE and TE display with
 Marks at each flap setting
 Digits at 5 and 20
2. Expanded display when:
 Flap / slat control in secondary mode
 Flap / slat control in alternate mode
 Non-normal condition detected
3. Flaps and Slats Asymmetry Protection System:
 Monitors operation of flaps and slats and loss of most slats
 Flap asymmetry shuts down flap drive
 Slat asymmetry or slat loss shuts down slat drive
4. EICAS caution: FLAPS DRIVE and SLATS DRIVE
 Associated drive unit has failed
 Flaps/slats cannot be moved from current position
5. Flaps/slats/kruger flaps
 Flaps: One inboard and one outboard flap each wing trailing edge
 Slats: One inboard and six outboard each wing leading edge
 Kruger flaps: One inboard of engine nacelle each wing leading edge
64
PEDESTAL
Control
Display
Drive
EICAS Caution
Flap/Slat
Operation
Engaged
Limits
Load Relief
Cruise Inhibit
Flap/Slat
Asym.
Uncomm.
Motion
Autoslats
FLAP / SLAT MODES
SECONDARY
FSEU & flap lever
Expanded
Electric
FLAP PRIMARY FAIL
SLATS PRIMARY FAIL
Independent
Independent
NOTE: Slats do not extend
NOTE: If slats midrange
beyond midrange until flaps 25 when engaged, remain
midrange until the flaps
UP or beyond 20
Primary
Automatically with
primary failure
Flaps – 30
Flaps – 30
Slats - Full
Slats - Full
Flap 15 to 30
Slats only
Retract to position for speed
> 239 kts. <ER>
(Limited to flap 5)
> 256 kts. <LR>
retract to midrange
Active
Active
Shuts down drives
PRIMARY
FSEU & flap lever
Normal
Hydraulic (Center)
None
ALTERNATE
ALTN FLAPS switch
Expanded
Electric
FLAP/SLAT
CONTROL
Combined
ALTN FLAPS switch
Flaps – 20
Slats - Mid
N/A
N/A
N/A
Reverts to Secondary
Shuts down drive
N/A
Armed at flaps
1, 5, 15, 20
Drive slats from mid to full,
when approaching stall
N/A
N/A
ALTN FLAPS
ARM switch/light

ALTN
 Arms alternate flap mode
 Disables primary & secondary flap/slat mode
 Asymmetry/skew and uncommanded motion protection, autoslat, and flap/slat load relief
are not available
 Arms alternate flap selector
 Engages the electric motors
 Disables the flap lever
Selector



OFF: Alternate flaps deactivated
RET: Flaps/slats electrically retracted
 Slat retraction inhibited until the flaps UP
EXT: Flaps/slats electrically extended
 Flaps: 20
 Slats: Midrange
NOTE:
 Extension from UP to EXT position can take up to 5 minutes
65
PEDESTAL
CURSOR CONTROL DEVICE
CCD left & right


Respective CCD controls respective inboard and lower center display unit cursor position and
operation.
<ER only> Respective CCD also controls the respective electronic flight bag
CCD location switch lights




INBD: Illuminated, display selected
LWR CTR: Illuminated, display selected
SIDE <LR only>: Illuminated, display selected (EFB)
INOP: <ER only>
NOTES:
 The last pilot who selects the cursor on the selected MFD has control
 The other cursor will disappear from the display and the cursor location light on the CCD will
extinguish
CCD touch pad



Finger movement on the touch pad moves the cursor on the selected display.
Lifting the finger off the pad and putting it back down in a different location (except the corner areas)
does not move the cursor
 The cursor only moves when the finger is moved on the touch pad surface
Placing a finger in one of the four corners puts the cursor in that respective corner of the screen
 Moving the cursor into a corner region without lifting the finger from the pad does not have this
effect
.
CCD select switch

Push – Activates the area of the screen that the cursor is currently in
 Such as a menu item or command button
 The area is highlighted by a white border to indicate it can be selected
 The switch is used to select menus, checklists, checklist steps, and other functions.
PARKING BRAKE
Parking Brake lever


Set the aircraft brakes using normal or alternate brake pressure
If either not pressurized, uses brake accumulator to set and hold brakes
Notes:
 ACARS OUT time: sent when parking brakes is released and all external doors (cargo and
passenger) are closed.

 ACARS IN time: sent when first passenger cabin doors is opened and last time parking brakes was
set
66
PEDESTAL
CENTER PEDESTAL
RADIO TUNING PANELS (L, C, R)
Offside Tuning light


Extinguished:
 Left panel controls VHF L and HF L
 Right panel controls VHF R and HF R
 Center panel controls VHF C
Illuminated:
 Radio normally tuned now being tuned by another panel (ex. right panel tuning VHF L)
 Panel being used to tune another radio (ex. left panel tuning HF 2)
Frequency Transfer button

Moves STANDBY frequency to ACTIVE frequency and tunes remote radio
OFF switch / light


Push: disconnects the panel from all radios
Illuminated: Panel is off/disconnected
Radio Tuning buttons


Push: selects the desired radio to tune and display
 Only one radio can be selected at a time
Illuminated: active radio selected
AM switch / light


Push: Sets the selected HF radio from default USB to AM mode
Illuminated: Selected HF radio in AM mode
HF SENS selector

Rotate counter clockwise to reduce sensitivity of on-side HF radio
NOTES:
 Panel Indications
 DATA mode: Selected radio in data mode
 Rotate STANDBY tuning knob until DATA is displayed then transfer to ACTIVE frequency
 Only VHF C and R can operate in data mode
 Radio fail: - - - - - - displayed in frequency windows
 Panel failure: PANEL FAIL displayed in frequency windows
67
PEDESTAL
AUDIO CONTROL PANEL (L, C, R)
MIC switch/light



Push: Selects / deselects the radio, interphone, or PA system to be connected to the microphones for
this crew station (Capt., FO, or Observer)
 Only one MIC can be selected at a time
 Activates the audio for the selected communication mode
Pushing CAB twice in one sec. activates priority call
Illuminated: Active MIC selected
CALL lights:




VHF, HF, or SAT: SELCAL indicated
FLT: call from ground crew
CAB: call from flight attendant handset
Reset: Select respective MIC or key microphone
MIC / INT switch


MIC: keys boom or oxygen mask microphone for MIC switch selected
INT: keys boom or oxygen mask microphone for flight interphone only
Receiver lights



Push: Activates audio from selected source
 Any combination can be activated at any time
Illuminated: Indicates audio activated
Rotate: Increases / decreases audio volume on only that source
SPKR switch/light




Push: Activates speaker at that crew station only
Only Capt and FO have speakers
Illuminated: Indicates speaker activated
Rotate: Increases / decreases audio volume on speaker
VOR / ADF switch

Selects VOR or ADF system to be monitored
APP switch

Selects ILS or marker beacon to be monitored
68
PEDESTAL
V B R switch

Filters navigation radio audio
 V: Voice only
 B: Both voice and range
 R: Range only
Notes:
1. VHF System:
 Three independent radios controlled by radio tuning panels
 VHF L is voice only, powered on standby power
 VHF C is normally in data mode but voice capable
 VHF R is normally voice mode and set to guard (121.5) but data mode capable
2. HF System
 Two independent radios controlled by radio tuning panels
 Both HF radios share a common antenna
 When either radio transmitting, other radio disconnected from antenna
 Both radios can receive simultaneously
 After a frequency change, antenna tunes to new frequency when mic. first activated
 Tone in HF audio indicates antenna tuning in progress
 Tone lasting more than seven seconds indicates failure to tune
 Tuning data stored for last 100 frequencies to reduce tuning time
 Predeparture HF check requires only antenna tuning tone and HF audio to be heard (AM)
3. Stuck Mic Protection
 In flight: VHF or HF transmission for greater than 30 seconds displays EICAS RADIO TRANSMIT
message
 On ground with both engines shutdown: VHF transmission for more than 35 seconds disconnects
radio and dashes display in tuning window
 Resets when mic switch released
4. Cabin Medical Communication
 Headphone audio/mic. jacks above center seat
 <LR> Rows 3, 12, 33, 40, 47 & 55
 <ER> Within 1 or 2 rows of above
 Allows flight attendants to communicate directly through radios
 First Observer audio control panel used to establish comm.
5. Second Observer Audio Control Panel <LR only>
 Gives second observer (relief captain) the ability to transmit
69
PEDESTAL
WX RDR
TILT control


Tilts radar antenna up and down
With AUTO selected tilt is automatically controlled
GAIN control


Adjusts receiver sensitivity (by detent) in MAP, WX, and WX+T modes
 Arrow at 12 o’clock position is standard calibrated reflectivity level
 Rotating clockwise increases sensitivity; rotating counterclockwise decreases sensitivity
With AUTO selected and GAIN arrow at 12 o’clock position, gain is automatically controlled
AUTO switch


In - both Captain’s and First Officer’s controls operate in automatic
 Ground clutter suppression operative
 Manual tilt control not available
Out - both Captain’s and First Officer’s controls operate manually
 Ground clutter suppression not available
System select switch


L (out) - selects left system
R (in) - selects right system
NOTE: Thought there are two radar systems (dual T/Rs, etc.) installed, there are common / shared
components such as antenna and wave guide switch.
TFR switch - selects opposite display.

Selecting both TFR switches at the same time results in the TEST mode and test pattern
WX switch - displays weather returns at range selected on DCP
WX + T switch - displays weather returns and turbulence out to 40 nm for all ranges

Clear air turbulence cannot be detected by radar
MAP switch - displays ground returns at selected gain level.
GC switch - allows ground clutter to display when pushed and held.
TEST switch - tests weather radar system operation without transmitting

Displays test pattern and PWS symbol at the end of the test and any fault message on ND with WXR
selected (except in PLAN, CTR VOR, and CTR APP modes)
70
PEDESTAL
ENGINE FIRE
Fire Handles LEFT & RIGHT / Fire Warning lights



Unlocked: fire warning or FUEL CONTROL switch in CUTOFF
Pull:
 Arms both extinguisher bottles
 Close fuel valves (spar & engine)
 Closes bleed valve
 Trips generator
 Shuts off fluid to engine hydraulic pump
 Depressurizes engine hydraulic pump
 Depowers thrust reverser isolation valve
DISCH 1 & 2: Discharges fire bottle one or two
ENG BTL DISCH 1 & 2 lights

Extinguisher bottle has low pressure
NOTES:
1. Engine fire indications:
 Fire bell
 Master WARNING lights illuminate
 EICAS warning message FIRE ENG L/R
 Fire switch LEFT or RIGHT fire warning light illuminates
 Fire switch unlocks
 FUEL CONTROL L/R switch fire warning light illuminates.
2. Engine overheat indications:
 Caution beeper sounds
 Master CAUTION lights illuminate
 EICAS caution message OVERHEAT ENG L/R
3. Engine fire detector loops
 Two fire and overheat loops in each engine nacelle
 Both loops must detect fire/overheat to produce warning/caution
 If one loop fails, systems switches to single loop operation
 If single loop senses fire/overheat, then warning/caution produced
 In unattended mode, single loop detecting fire shuts down APU and discharges fire bottle
71
PEDESTAL
EVACUATION CONTROL
<ER only>
EVAC light: COMMAND switch is ON
COMMAND switch


ON:
 EVAC light flashes
 FA EVAC light (amber) flashes sounds at each panel
 Horn sounds at each panel
OFF:
HORN SHUTOFF switch: Silences the flight deck horn
NOTE: Flight attendant evacuation control has been deactivated by E.O.
TRIM
RUDDER TRIM indicator



Monitored by Takeoff Configuration warning system
Displays trim input by TAC
Does not display wheel to rudder trim input
RUDDER knob


NOSE L & R
 First detent: Low speed trim rate
 Full deflection: High speed trim rate
Operates in all flight control modes
MANUAL TRIM CANCEL button



Centers rudder trim at high speed trim rate
Does not affect TAC inputs
Not as accurate as manual trimming to “0”
AILERON switches

LEFT & RIGHT WING DOWN
 Ailerons, flaprons and spoilers trimmed in selected direction
 Control wheel displaced
72
PEDESTAL
FLIGHT DECK DOOR
<LR only>
Flight Deck Door Lock selector



AUTO: Spring loaded position
UNLK: Push and rotate to unlock door, overrides DENY lockout
DENY: Rotate to cancel the keypad unlock command, starts a 5 min. lockout countdown
LOCK FAIL light:


DOOR LOCK CONTROLLER selector in AUTO and door lock has failed, or
Flight Deck Access System switch in OFF
AUTO UNLK light:



Correct emergency access code entered in keypad
Light flashes and continuous chime sounds until timer expires
Door unlocks after 60 sec. time delay
NOTE: First flight of the day check required (OM Vol. 1, SP)
OBSERVER AUDIO
OBS AUDIO switch



NORM: Connects observer to center ACP
 Hand microphone, headphone, boom microphone/headset and oxygen mask microphone
CAPT Connects captain to center ACP
 Hand microphone, headphone, boom microphone/headset, oxygen mask microphone, speaker,
and mic/interphone switches
FO Connects observer to center ACP
 Hand microphone, headphone, boom microphone/headset, oxygen mask microphone, speaker,
mic/interphone switches
73
PEDESTAL
FLIGHT DECK ACCESS SYSTEM
(Located on flight deck door side post)
<LR only>
FLIGHT DECK ACCESS SYSTEM Switch


NORM: System powered
OFF: System electrically depowered, door unlocked
FLIGHT DECK EMERGENCY ACCESS PANEL
(Located on passenger cabin side of door)
Keypad lights



Red:
 Door locked, or
 Flight Deck Access System Switch OFF <LR only>
Amber: Correct emergency access code entered
Green: Door unlocked
Keypad keys: Used to enter emergency entry code
74
SIDEWALL
SIDEWALL
SIDE WINDOW
Window Lock lever


Forward: With the window fully closed, locks the window
 If the lock lever is properly locked, the orange indicator is not visible below the release button
 The EICAS message WINDOW FLT DECK L, R displays if a window is not properly latched
Aft: Unlocks the window so it can be cranked open
STEERING
Steering tiller



Overrides rudder pedals
Nose gear turns 70 deg. vs. 7 deg. for rudder pedals
 Powered by the center/reserve hydraulic system
Main gear aft axle steering slaved to nose wheel
 When nose gear exceeds 13 deg., aft axle steering active
 Powered by the center hydraulic system
 Sensed by takeoff warning system
 EICAS warning CONFIG GEAR STEERING and aural alert if main gear aft axles not centered
and locked when takeoff thrust applied
 EICAS advisory MAIN GEAR STEERING if main gear steering actuators not locked in centered
position when commanded to center position
OXYGEN MASK / REGULATOR
TEST/RESET button


OXY ON: Indicates oxygen system activated (right door open)
TEST RESET
 Push:
 With mask stowed activates momentary oxygen flow for test
 After mask removed, resets mask microphone when right door closed
 Resets microphone with mask either stowed or removed from box
Regulator selector



EMER: Provides 100% oxygen under pressure at all times
100%: Provides 100% oxygen on demand
NORM: Provides ambient air / oxygen mixture depending on cabin altitude
 Due to mixing, do not use in smoke / fumes
Flow indicator

Yellow cross displayed when oxygen flowing
NOTES:
1. Minimum 1000 psi required for dispatch (OM Vol. 1, SP)
 Displayed on MFD STATUS page
2. 10 sec. “purge check” not required
 Accomplished automatically after engine start
 EICAS CREW OXYGEN LOW if low pressure
75
SIDEWALL
INTENTIONAL BLANK PAGE
76
UPPER CREW REST COMPARTMENTS
UPPER CREW REST COMPARTMENTS
UPPER CREW REST MASTER CONTROL PANEL
AIRFLOW OFF light <ER only>

Illuminated (amber)
 Area airflow is off
 Airplane is below 25,000 feet, or
 During smoke detection mode operations
 Hi/Lo chime sounds 5 times in the area whenever air supply shutoff valve commanded closed
NOTE: The door 1 upper crew rest area should not be occupied when the amber AIRFLOW OFF light
is illuminated.
AIRFLOW RESET switch <ER only>

Illuminated (red)
 Push and hold 2 seconds - resets airflow to the area.
 Inoperative when the airplane is below 25,000 feet.
NOTE: If a smoke test is initiated, or a smoke condition exists, partial aft galley power isolation will occur.
Galley power can be restored by depressing the AIRFLOW RESET switch.
SUPPLY AIRFLOW OFF light <LR only>

Illuminated (amber)
 Area airflow is off
 Area airflow exhaust valves open
 Smoke detection mode operations
 HI/LO chime will sound 5 times in the area whenever the air supply shutoff valve is commanded
closed
AIRFLOW/SMOKE RESET switch <LR only>

Push and hold 2 seconds - resets the airflow to the area
NOTE: If the SUPPLY AIRFLOW OFF light is illuminated, push the AIRFLOW / SMOKE RESET switch
one (1) time and wait 10 minutes before closing the enclosure door.
NOTES: Upper Crew Rest Compartments
 <ER only>
 The upper crew rest compartments may not be occupied below 25,000 feet

<LR only>
 Door 1 upper crew rest compartment may be occupied in all phases of flight
 Maximum occupancy during takeoff and landing - two
 Maximum occupancy in remaining phases of flight - four.
 Entrance door must be latched open for taxi, takeoff, climb, and landing
 Door 4 upper crew rest compartment may be occupied above 25,000 feet
 Maximum occupancy - six
77
UPPER CREW REST COMPARTMENTS
SMOKE DETECTION
<ER only>
POWER light: Six area smoke detectors powered
SMOKE DETECT light: Smoke detected by one detector or system test mode

Crew rest compartment air supply valves are closed and compartment exhaust valves are opened
Smoke Detector Location Indicator lights


Location of detector in alarm
During TEST mode, location of detector in fault condition
HORN INTERRUPT switch


Silences the smoke detection alarm
Smoke Detector Location Indicator lights remain illuminated
TEST: Push and hold

System test mode
 All six Smoke Detector Location Indicator lights illuminate
 Alarm horn sounds
FAULT light


Illuminates after system test if fault is detected
Smoke Detector Location Indicator lights with fault will be illuminated
RESET switch

Resets smoke detector system
NOTE:
 Smoke detection system activation. either by smoke or test, will deactivate galley ovens and vent
fans.
 Pushing AIRFLOW RESET switch will restore power to both.
78
WARNING SYSTEMS
WARNING SYSTEMS
EICAS
TAKEOFF INHIBITS
Inhibited
Message
Description
WARNING
Red
Cannot be canceled
Amber
Can be cancelled
Aural
Master WARNING
Aural
Master CAUTION
Amber & indented
Can be canceled
White
All
80 kts.
All, except
CABIN ALERT
Takeoff
Thrust
Inhibit
Ends
400 RA
25 sec. after begin
400 RA
20 sec. after LO
< 75 kts.
400 RA
20 sec. after LO
400 RA
20 sec. after LO
All
Eng.
Start
Top of climb, or
30 mins after LO
CAUTION
ADVISORY
COMM
MEMO
STATUS
White
Blue
Cannot be canceled
LANDING INHIBITS
Inhibited
Message
ALTITUDE ALERT
All
COMM
All, except
CABIN ALERT
STATUS
ADVISORY
CAUTION
All
Aural, except
AUTOPILOT
AUTOTHROTTLE DISC
NO AUTOLAND
S/B EXTENDED
Inhibit
Begins
V1
80 kts.
Inhibit
Begins
G/S capture
Land config.
800 RA
Inhibit
Ends
75 kts.
800 RA
200 RA
LAND 2/3 &
200 RA
75 kts.
75 kts.
75 kts
40 secs
800 RA
CREW ALERTNESS MONITOR
Switches monitored
 EFIS control panel
 DSP
 CDU
 Radio microphone
Alert
Advisory
PILOT RESPONSE
Caution
PILOT RESPONSE
Warning
PILOT RESPONSE
Cruise
30 mins.
Descent
10 mins.
45 mins.
12 mins.
60 mins.
14 mins.
79
WARNING SYSTEMS
ENGINE FAILURE ALERT SYSTEM
Engine Failure Alert System
 Takeoff
 Red ENGINE FAIL on PFD
 “Engine Fail” aural warning
 Active: from 65 kts to V1 minus 6 kts.
 Inhibited: from V1 -6 kts. to 65 kts. on next takeoff
 Actual thrust less than commanded thrust
 EICAS caution ENG FAIL
 Unexpectedly decelerates to less than idle
 The message remains displayed until
 Engine recovers
 Fuel control switch moved to CUTOFF
 EICAS message ENG THRUST
 Active: airspeed V1 or greater
 Actual thrust is significantly less than commanded thrust
 Actual thrust is not increasing to commanded thrust
GPWS
GPWS alerts:
 Altitude loss after takeoff or GA
 Excessive descent rate
 Excessive terrain closure rate
 Too low and not in landing configuration
 Excessive deviation below ILS glide slope
 Wind shear
GPWS WINDSHEAR
TAKEOFF AND APPROACH
WARNING
Visual
Master Warning Light
Aural
WINDSHEAR
PFD display Red WINDSHEAR message
ND display
Red WINDSHEAR message
Red windshear symbol
Excessive windshear detected by GPWS
EGPWS (TERRAIN)
EGPWS alerts
 TERRAIN PULL UP: 20 to 30 seconds from projected impact
 CAUTION TERRAIN: 40 to 60 seconds from projected impact
Terrain colors
 Magenta: No data
 Green: -500 (-250 w/gear down) to -2000 ft.
 Amber: -500 (-250 w/gear down) to +2000 ft.
 Red: > +2000 ft.
80
WARNING SYSTEMS
PWS
PWS alerts
 On ground:
 Begins:
 12 sec. after radar on
 12 sec. after thrust levers in takeoff range
 Ends: 1200 ft. RA
 Inhibited:
 New caution: 80 kts. to 400 ft. RA
 New warning: 100 kts. to 50 ft. RA
 In flight:
 Radar starts scan below 2300 ft. RA
 Alerts enabled below 1200 ft. RA
PWS WINDSHEAR
TAKEOFF
Visual
Aural
PFD
display
ND
display
Visual
Aural
PFD
display
ND
display
WARNING
Master Warning Light
GO AROUND WINDSHEAR AHEAD
Red WINDSHEAR message
ALERT
MONITOR RADAR DISPLAY
Red WINDSHEAR message
Red windshear symbol
Windshear predicted close to and directly
ahead of airplane.
Enabled during takeoff, below 1,200 feet radio
altitude.
APPROACH
Master Warning Light
GO AROUND WINDSHEAR AHEAD
Red WINDSHEAR message
Amber WINDSHEAR message
Red windshear symbol
Windshear predicted within 3 miles and
ahead of the airplane.
Red WINDSHEAR message
Red windshear symbol
Enabled during approach, below 1,200 feet
radio altitude
Windshear predicted within 1.5 miles and
directly ahead of the airplane
Amber WINDSHEAR message
Red windshear symbol
Windshear predicted within 3 miles and
ahead of the airplane.
81
MONITOR RADAR DISPLAY
WARNING SYSTEMS
CONFIGURATION
Landing Configuration warning
 Landing gear: in flight, and
 Any landing gear not down and locked, and
 Either thrust lever closed below 800. RA, or
 Flap lever not 25 or 30
 Flaps: in flight, and
 Flaps 25 or 30 and landing gear not down, or
 Low altitude and flaps not 25 or 30
Takeoff Configuration warning
 Begins:
 On ground with speed less than V1
 FUEL CONTROL switches in RUN
 Either engine thrust in takeoff range
 Thrust reversers stowed
 Ends: V1
 Items checked:
 Any door not closed, latched, and locked - CONFIG DOORS
 Main gear steering not locked - CONFIG GEAR STEERING
 Rudder trim not centered - CONFIG RUDDER
 Flaps not 5, 15, 20 - CONFIG FLAPS
 Parking brake set - CONFIG PARKING BRAKE
 SPEED BRAKE lever not DOWN - CONFIG SPOILERS
 Stab. trim not in green band - CONFIG STABILIZER
Notes:
TAKEOFF CONFIG
Any door not closed, latched, and locked
Main gear steering not locked
Rudder trim not centered
Flaps not 5, 15, 20
Parking brake set
SPEED BRAKE lever not DOWN
Stab. trim not in green band

LANDING CONFIG
Flap 25/30 & gear not down
Below 800 ft. & gear not down
Low alt. & flaps not 25/30
When CONFIG displayed, pushing Master WARNING/CAUTION reset switch
 Resets the Master WARNING lights
 Does not silence the siren
 If thrust is decreased below takeoff range and airspeed less than V1 but the airplane is still not
configured for takeoff, the Master WARNING lights are extinguished and the siren is silenced
 The CONFIG message remains displayed for 10 seconds after thrust is reduced
 Aids in identifying the takeoff misconfiguration.
Speedbrake Lever beyond ARMED in Climb <LR ONLY>
 EICAS warning CONFIG SPOILERS
 In flight and
 SPEEDBRAKE lever extended beyond ARMED
 Either thrust lever at climb or higher thrust
82
WARNING SYSTEMS
TCAS
Traffic Display
 Traffic
 Hollow white diamond
 Traffic within 40 nm.
 Proximate Traffic
 Filled white diamond
 Within 6 nm. horizontal and 1200 ft. vertical
 TA
 Filled amber circle
 25 to 45 secs. of protected area
 ND: Amber TRAFFIC
 Aural: Traffic
 RA
 Filled red square
 20 to 30 secs. of protected area
 ND: Red TRAFFIC
 PFD: Red no fly zone on pitch and V/S display
 Aural: Guidance
ALTITUDE ALERT



Approaching MCP altitude
 Within 750 ft. white box around PFD altitude and altitude set
 Removed when within 250 ft.
Departing MCP altitude
 When 200 ft. <LR> / 250 ft.<ER> off of selected altitude amber box, master caution and aural
 Removed when within 200 ft. <LR> / 250 ft.<ER>
 More than 900 ft. <LR> / 750 ft. <ER>
Inhibited when
 Glide slope capture
 Configured for landing
ENVELOPE PROTECTION

Stall Warning
 Warning of an impending stall is provided by left and right stick shakers
 Independently vibrate the left and right control columns

Airspeed Low
 EICAS caution message AIRSPEED LOW is displayed
 Box around the current airspeed indication on the PFD highlighted amber when airspeed below
minimum maneuvering speed

Overspeed Warning
 The EICAS warning message OVERSPEED is displayed
 The message remains displayed until airspeed reduced below VMO/MMO
83
WARNING SYSTEMS
INTENTIONAL BLANK PAGE
84
SYSTEM SCHEMATICS
SYSTEM SCHEMATICS
BLEED AIR
85
SYSTEM SCHEMATICS
AIR CONDITIONING
ANTI ICE
86
SYSTEM SCHEMATICS
ELECTRICAL AC
ELECTRICAL BACKUP AC
87
SYSTEM SCHEMATICS
ELECTRICAL DC
STANDBY ELECTRICAL
88
SYSTEM SCHEMATICS
FUEL SYSTEM
FUEL JETTISON
89
SYSTEM SCHEMATICS
HYDRAULIC
90
RECALL
GENERAL INFORMATION
Type
Primary indication
Thrust
Description
N1 shaft
N2 shaft
N3 shaft
Gearbox drive
ENGINES
ER
Rolls Royce
Trent 895
EPR
95,000 lbs.
Three rotor
Axial flow
Fan
Low press. turbine
Inter. press. compressor
Inter. press. turbine
High press. compressor
High press. turbine
N3
LR
General Electric
90-110B1
N1
110,000 lbs.
plus “thrust bump”
Dual rotor
Axial flow
Fan
Low press. compressor
Low press. turbine
High press. compressor
High press. turbine
NA
MAXIMUM WEIGHTS (lbs.)
ER
LR
Taxi
657,000 768,000
Takeoff
656,000 766,000
Landing
460,000 492,000
Zero Fuel 430,000 461,000
FUEL CAPACITY (lbs.)
ER
LR
Left Main
64,100
69,000
Right Main
64,100
69,000
Center
174,900 182,800
Total
303,100 320,800
DIMENSIONS
ER
LR
Wing Span 199’ 11” 212’ 7”
Length
206’ 6”
Tail Height
60’ 6”
61’ 4”
TURN RADIUS
ER
LR
Min. Pavement Width
155.8’
For 180 deg. Turn
(47.5M)
Wing Tip
145’ 152’
Nose
110’ 112’
Tail
131’ 131’
91
N2
RECALL
RECALL NON-NORMAL CHECKLISTS
ABORTED ENGINE START L, R
ENGINE AUTOSTART L, R
1. FUEL CONTROL switch (affected side) … CUTOFF
AIRSPEED UNRELIABLE
1.
2.
3.
4.
Autopilot disengage switch . . . Push
A/T ARM switches (both) … OFF
F/D switches (both) . . . OFF
Set the following gear up pitch attitude and thrust:
 Flaps extended … 10 degrees and 85% N1
 Flaps up … 4 degrees and 70% N1
CABIN ALTITUDE
1. Don the oxygen masks.
2. Establish crew communications.
DUAL ENGINE FAILURE / STALL
1. FUEL CONTROL switches (both) ... CUTOFF, then RUN
2. RAM AIR TURBINE switch … Push and hold for 1 second
ENGINE SEVERE DAMAGE / SEPARATION L, R
FIRE ENGINE L, R
1. A/T ARM switch (affected side) … Confirm … OFF
2. Thrust lever (affected side) … Confirm … Idle
ENGINE LIMIT / SURGE / STALL L, R
1. A/T ARM switch (affected side) … Confirm … OFF
2. Thrust lever (affected side) … Confirm … Retard until engine indications stay
within limits or the thrust lever is at idle.
STABILIZER
1. STAB cutout switches (both) … CUTOUT
2. Do not exceed the current airspeed.
92
RECALL
RECALL LIMITATIONS
AIRPLANE GENERAL
Maximum Operating Altitude
Crosswind Limit, including gusts
Maximum Tailwind, Takeoff and Landing
43,100 ft. PA
40 kts.
10 kts., or
per DAL Special Page
Turbulent Air Penetration Speed below 25,000 ft.
270 kts.
Turbulent Air Penetration Speed at/above 25,000 ft.
280 kts./.82 M,
whichever lower
Maintain minimum speed of 15 knots above minimum maneuvering speed (amber band) at all altitudes
when below 0.82 Mach
AUTO PILOT / FLIGHT DIRECTOR SYSTEM
Autopilot must not be engaged below 200 ft. AGL after takeoff.
AUTOMATIC LANDING
Maximum Autoland Headwind
25 kts.
Maximum Autoland Tailwind
10 kts.
Maximum Autoland Crosswind
25 kts.
(15 kts. by Ops. Specs.)
93
RECALL
EMERGENCY EVACUATION FLOW
STOP
PARKING brake … Set
CONFIGURE
OUTFLOW VALVE switches (both) … MAN
OUTFLOW VALVE MANUAL switches (both) … Push to OPEN and
hold until outflow valve displays show fully open to depressurize the airplane
SHUTDOWN
FUEL CONTROL switches (both) … CUTOFF
Engine fire switches (both)… Pull
APU fire switch … Override and pull
If an engine or APU fire warning light is illuminated:
 Illuminated fire switch … Rotate to the stop and hold for 1 second.
EVACUATE
Notify flight attendants “EASY VICTOR” three times.
Notify flight attendants "THIS IS THE CAPTAIN. EVACUATE. EVACUATE."
 EVAC COMMAND switch …ON <ER only>
Advise the tower.
CAPTAIN duties:
 Forward door area
 Assist with evacuation
 Ensure all passengers off aircraft
 Exit from the rear
 Take smoke hood and flashlight
FIRST OFFICER duties:
 Exit from the forward exits
 Assist with evacuation
Assemble the passengers and crew 300 feet off the nose or tail
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RECALL
SMOKE / FUMES PRIORITIES
DIVERSION
Diversion may be needed
OXYGEN MASKS
Don oxygen masks, if needed.
CREW AND CABIN COMMUNICATION
Establish crew and cabin communications.
 Direct FAs:
 Inspect cabin
 Move passengers
 ATC …Notify
IDENTIFICATION / ELIMINATION
SMOKE, FIRE, OR FUMES checklist
 IFE/PASS SEATS switch … Off, or
 Advise the cabin to turn off the main IFE switch.
 RECIRCULATION FANS switches (both) … Off
 GASPER switch … Off
 APU BLEED AIR switch… Off
ASSESSMENT
Known Source
Unknown Source
REMOVAL
Accomplish SMOKE OR FUMES REMOVAL CHECKLIST
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