767 Flight Deck and Avionics
January 2002
767 Size Comparison
767-200ER/-300ER/-400ER
767-200ER
767-300ER
156 ft 1 in
(47.57 m)
767-200ER
61 ft 1 in
(18.60 m)
52 ft 0 in
(15.8 m)
64 ft 7 in
(19.6 m)
155 ft 0 in
(47.2 m)
767-400ER
170 ft 4 in
(51.92 m)
767-300ER
52 ft 0 in
(15.8 m)
61 ft 1 in
(18.60 m)
74 ft 8 in
(22.76 m)
176 ft 1 in
(53.67 m)
767-400ER
55 ft 4 in
(16.8 m)
85 ft 10 in
(26.1 m)
201 ft 4 in
(61.37 m)
797-FD-0052C
1-18-2-MT/CF
767 Evolution
767-400ER
450,000 lb (204,120 kg)
(767-400ER covered in
separate book)
767-300ER
767-300 Freighter
412,000 lb (186,880 kg)
412,000 lb (186,880 kg)
767-300ER
387,000 lb (175,540 kg)
767-300*
351,000 lb (159,210 kg)
767-200*
767-200*
767-200ER
767-200ER
300,000 lb (136,080 kg)
315,000 lb (142,880 kg)
351,000 lb (159,210 kg)
395,000 lb (179,170 kg)
*No longer offered.
797-FD-0053C
1-18-2-MT/CF
BOEING PROPRIETARY
797-FD-0054C
11/27-0-MT
Boeing Flight Deck Design Philosophy
• The pilot is the final authority for safe airplane
operation; the hierarchy of tasks is
• Safety
• Passenger comfort
• Efficiency
• Automation is applied as a tool to aid but not
replace the pilot
• New technology is used only when there is a
clear advantage with no adverse impact on
human-machine interface
• System designs are error tolerant; the hierarchy
of design alternatives is
• Simplicity
• Redundancy
• Automation
• Designs address fundamental human strengths,
limitations, individual differences, and pilots’
past operational experience
797-FD-0055C
1-18-2-whp/CF
757/767 Commonality
Design Features
• Similar handling characteristics
• Same crew procedures
• Identical recall items
• Identical aural warnings
• Similar checklists
• Similar visual alerts
• Same flight deck arrangement
• Windshield
• Main instrument panel
• Overhead panel
• Aislestand
• Glareshield panels
• Panels/controls
- Location
- Arrangement
- Nomenclature
• Initial and recurring training will
qualify crew for both airplanes
Pilots’ main
instrument panel
No. 1
windshields
Flt
kit
Captain’s
seat
First
Officer’s
seat
Flt
kit
Aislestand
Overhead panel
• Same flight training simulator can
be used for both airplanes
797-FD-0056C
1-18-2-whp/CF
767 Flight Deck - General
Flight Deck and Forward Cabin
767-200ER/-300ER Passenger
First Observer
First Officer
Galley
Closet
Galley
Lavatory
Captain
Second Observer
(optional)
STA
239
797-FD-0058C
1-18-2-MT/CF
Flight Deck and Forward Cabin
767-300 Freighter
STA
273.5
Supernumerary seats
First Observer
(track mounted)
Lavatory
First Officer
Rigid barrier
Access door
to cargo bay
Captain
Galley
Entry door
STA
360.7
797-FD-0059C
1-18-2-MT/CF
Flight Deck Accommodations
767-200ER/-300ER Passenger
• Emergency evacuation can be
accomplished through the
no. 2 side windows.
Hat stowage
Fire extinguisher,
crash axe, and
spare bulb stowage
Coat stowage
• Flight deck escape ropes are
attached to the airplane structure
above each sliding window. They
are stowed in compartments in
the overhead lining above the
pilots’ seats.
Portable light
First Observer’s seat
• Oxygen mask, smoke goggles,
and life vest are located at each
crewmember station.
Suitcase stowage
Coat stowage
Second
Observer’s
seat (optional)
Suitcase
stowage
Captain’s seat
Flight kit stowage
(2 places)
797-FD-0067C
1-18-2-whp/PW
Flight Deck Accommodations
767-300 Freighter
Overhead stowage
Spare bulb stowage
Coat and
hat stowage
Lavatory
Supernumerary
seats (3)
Main deck
cargo door
control panel
Galley
First
Officer’s
seat
Captain’s
seat
Life raft stowage
Fire extinguisher
Suitcase
stowage (2)
Illuminated step
797-FD-0068
1-18-2-whp/CF
Pilots’ Main Panel
767-200ER/-300ER
Standby magnetic compass
Mode control panel
VOR (2)
Lighting
controls (2)
15
12
E
NS
A/T ARM
F
R
E
Q
WARNING
C
R
S
L NAV
3 3 0
VERT SPD
HDG
IAS/MACH
F/D
ON
1 2 6
A/P ENGAGE
ALT
3 2 0 0 0
0 0 0 0
L
CMD
B CRS
C
R
CMD
CMD
CWS
CWS
F/D
ON
F
R
E
Q
OFF
SEL
EPR
CAUTION
Master caution and
warning lights (2)
6
EW
V NAV
OFF
5
NORM
AUTO
MAN
SPD
FL CH
SEL
25
BANK
LIMIT
DN
CWS
LOC
V/S
HOLD
HOLD
C
R
S
AUTO
MAN
DISENGAGE
UP
VOR/DME
WARNING
CAUTION
OFF
APP
VOR/DME
CLOCK
CLOCK
PANEL
PANEL
OFF
OFF
CHART
CHART
FLOOD
Miscellaneous warning,
caution, and advisory lights
OFF
MAP
PTT
PTT
1
Instrument source
select (2)
HDG SEL
LAND 3
FD
BRAKE
TEMP w
CAUTION
1.63
2
a
1.8 1.47
1.4
TRUE
1.0
D
O
O
R
Sa
TAIL
SKID
a
NOSE
g
G
E
A
R
Altimeter (2)
CLB
CON
CRZ
1
Marker beacon
lights (2)
1
PRESS
PSI
X 1000
0
2
g
TO
GA
AUTOLAND STATUS
BRAKE
4
3
P/RST
LAND 2
TEST
a
1
THR HLD
NO AUTOLND
VNAV PTH
HDG SEL
FD
2
RIGHT
LEFT
1.8 1.47
1.4
1.0
Thrust
management
g
2
EPR
ILS
OFF
B/CRS
MIDDLE
599
5
a
3
TRK
DME-L
OVSPD
r
2
6
MA C H
583
LEADING TRAILING
EDGE a
EDGE a
140
KNOTS
160
180
200
N1
1114
.
650
EGT
650
UP
FLAPS
STW
BWZ
SBJ
KILMR
12000
30
190K
1055
.
AUTO
CHR
7
V
10
40
IN. HG
5
a
OUTER
b
INSTR SOURCE SEL
FLT DIR
R
a
29 92
4
3
PRESS
118
OIL
TEMP
13
4
4.4 NM
252
TRK
M
0835.4
0
Z
NAV
FMC-L
CDU-L
6
OFF
DME-L
ALTN GEAR
EXTEND
250K-.75M
20
QTY
.5
DME-R
4
1
KTEB
OFF
2
JFK
LGA KJFK
KLGA
7.0
167 343
AMBO
COL
25
30
7.0
LE
SAX
DN
TE
ALTN
MMU
KILMR
12000
40
FF
GND PROX
ALTN
w
w
w
w
FLAP OVRD
N1
0.5
VIB
GEAR OVRD
TERR OVRD
STW
BWZ
SBJ
CHR
BLM
ALTN
w
60
EFI
w
50
REV
10
GMT
HARRY
ET/CHR
OVRD
OVRD
KTTN
ARB
12000
KPNE
MUI
OVRD
w
w
w
w
w
w
40
ALTN
20
RUN
30
HLD
w
HLD
SS
FS
20
ADE ABE
WARNT
12000
FS
RESET
AIR
DATA
w
w
IRS
RUN
HLD
SS
RESET
ALTN
FMC-R
1000 FPM
ALTN FLAPS
5
15
NORM
13
OIL
N2
0.5
RTO
1
UP
N2
4
KEWP
118
MAX
AUTO
OFF
BARO
95
232
OIL
2
VERTICAL
SPEED
.5
LOCK OVRD
DN
RUN
30
HLD
MIDDLE
3
IN.HG
29 92
4
1
20
RUN
ABE
a
AUTO BRAKES
2
3
1
DISARM
ALT
MB
1013
6
BRAKE
SOURCE a
ET/CHR
T
K
w
ADE
R ENG
OIL PRESS
AUTO
BRAKESa
95
232
L ENG
OIL PRESS
a
50
GMT
WARNT
12000
2
8
VALVE
60
REV
KTTN
20
1
w
HARRY
ARB
12000
KPNE
MUI
IRS
5
BARO
599
EXTEND OR
EXTENDED
270K-.82M
162K
N2
ON
ON
259
40
EFI
ALTN
.730
C
195K
20
25
T
0
079
SAX
ALTN
700
GS
A S
15
L
1114
.
1055
.
BLM
COL
1013
6
KNOTS
OFF
210K
5
120
9
167 343
AMBO
INNER/
AIRWAYSw
2
MB ALT
IN
OP
MO
FLAP LIMIT IAS
220K
EGT
1
RESERVE
BKS & STRG
KEWP
MMU
1
NEG
R
584
240K
4
2
8
EPR
IAS
250
240
220
4
OFF
1
w
0
9
a
PROX
G/S INHB
a
100
300
VERTICAL
SPEED
.5
JFK
LGA KJFK
KLGA
KTEB
ALT
RETRACT
270K
UP
N1
r
GND
a
FMC
80
1000 FPM
DME-R
w
88.3
a
60
0
FMC-R
AUTO
PILOT
a
0
350
NAV
FMC-L
ALT
ALERT a
A/T
DISC
b
400
1
CABIN
ALT
OUTER
29 92
4
BARO
.5
SPEED
BRAKESa
259
2
MB ALT IN.HG
1013
6
700
GS
.730
88.2
r
MACH
8 NEG
R
IN
OP
AS
r
INNER/
AIRWAYSw
079
MA C H
KNOTS
TEMP SEL
r
A/P
DISC
PULL UP
r
1
R
w
1.63
CONFIG
r
WINDSHEAR
w
0
C
w
CRZ
CANCEL RECALL
FIRE
ALT
FLT DIR
L
CDU-L
WHL WELL
FIRE r
TAT - 46 C
TEST
g
NO LAND 3
9
MACH
MO
INSTR SOURCE SEL
VNAV PTH
Electronic attitude
director indicator
(EADI)
REG
SELCAL
HDG REF
NORM
AUTOLAND STATUS
P/RST
THR HLD
Heading
reference
Engine indication
and crew alerting
system (EICAS)
Standby
attitude indicator
Autoland
status (2)
Mach/airspeed
indicator (2)
FLOOD
OFF
MAP
AIR
DATA
ALTN
w
w
w
Radio distance
magnetic indicator
(RDMI) (2)
Reserve brakes
and steering
Vertical speed
indicator (2)
Standby airspeed
Standby altimeter
Standby engine indicator
Autobrakes
Clock (2)
Alternate gear
Alternate flaps
Flap position indicator
Enhanced ground
proximity warning
system (EGPWS)
override
Electronic horizontal
situation indicator (EHSI)
797-FD-0060C
1-18-2-whp/CF
Overhead Panel
767-200ER/-300ER
Emergency lights
Miscellaneous annunciation
Cargo heat
Passenger oxygen*
Engine start
Window heat
EMER
DOORS
CARGO
DOORS
ACCESS
DOORS
CAPT
PITOT
FO
PITOT
L AOA
R AOA
L AUX
PITOT
R AUX
PITOT
TAT
ENTRY
DOORS
IRS MODE SEL
W
DSPL SEL
PPOS
WIND
TK/GS
Inertial reference
1
N
2
3
W
4
H
5
E
6
7
S
8
9
ENT
0
CLR
HDG
FWD
Yaw damper
STAB
TRIM
SPOILERS
UNSCHED
STAB TRIM
RUDDER
RATIO
ARMED
AUTO
SPDBRK
BULK
ON
ON
OVHT
OVHT
ON
ON
WINDOW HEAT
L
R
FWD
FWD
SIDE
PRESS
ON
ON
ON
ON
UNLKD
INOP
INOP
INOP
INOP
INOP
R
ALIGN
ALIGN
ALIGN
BOTH
L
ON DC
ON DC
ON DC
DC FAIL
DC FAIL
VALVE
C
ALIGN NAV ATT
OFF
C
W
AUTO
AUTO
OFF
OFF
GND
ON
CONT
CONT
FLT
FLT
OFF
ON
ON
INOP
INOP
FAULT
ELEC
ENG
CONT
ALTN
ON
D
I
S
C
H
NORM
ALTN
SYS
PRESS
O
F
F
QTY
QTY
L
ENG
APU GEN EXT PWR
QTY
R
ENG
C
1-ELEC-2
ON
ON
ON
PRESS
PRESS
PRESS
I
A
OVHT
OVHT
Y
R
PUMPS
VALVE
PRESS
AIR
ELEC
PRESS
PRESS
PRESS
BUS
OFF
R
P
R
E
S
S
R BUS
R
ON
ON
OFF
OFF
MANUAL
ON
BUS
OFF
P
R
E
S
S
DESCEND
034 0
OVHT
MODE SELECT
AUTO 2
LB
KG
LB
KG
FUEL QTY
X 1000
M
AUTO
AUTO
A
OFF
ON
OFF
AUTO
ON
OFF
O
F
F
A
ON
N
O
F
F
ON
DRIVE
DRIVE
TEMP
LB
CABIN
WING ANTI-ICE
ON
START
OFF
FAULT
2
8
4
6
L
R
ON
ON
VALVE
VALVE
R
VALVE
VALVE
PSI
DIFF
DUCT
LEAK
ERASE
BLEED
L ENG
1 2
FT X
1000
ALT
Bleed air and
pneumatic
FPM X
RATE 1000
O
F
F
V
A
L
V
E
OVHT
ADP
APU
R ENG
Fuel jettison
O
F
F
EQUIP COOLING
VALVE
AUTO
PRESS DIFF
LIMIT: T/O &
LDG .125 PSI
OFF
Electrical
V
A
L
V
E
1 2
0
CABIN
ALTITUDE
WIPER
TEST
VALVE
DL
UE
CA
TK
OVHT
0
2
25
4
20
15
6
10 8
0
10
ENGINE
ON
L
RUN
R ISLN
BLEED
C
ON
0
C ISLN
KG
TOTAL
D
APU
80
MAN
AUTO 1
R
DUCT
LEAK
GEN
CONT
R
E
OVHT
OVHT
GEN DRIVE DISC
L
C
L
R
L
GEN
CONT
60
20
VALVE
AUTO INOP
R
S
T
B
Y
W
DUCT
PRESS
PSI
L ISLN
LDG ALT
L
C
W
MAX
MIN
ON
S
T
B
Y
AUTO RATE
CLIMB
CL
UTILITY BUS
L
VALVE
OP
FUEL
CONFIG
N
OFF
C
PRESS
C PUMPS
M
D
M
D
VALVE
PRESS
PACK
OFF
AUTO
N
AFT
FWD
FWD
INOP
W
MAN
ON
OFF
OFF
ON
ON
ISLN
L BUS
ON
Y
ELEC
D
N
BUS TIE
RESET
C
PACK
OFF
ON
PRESS
AVAIL
AUTO
A
OVHT
ON
ISLN
R PACK
INOP
SEATBELTS
AUTO
AUTO
FUEL
XFEED
W
AUTO
L PACK
CABIN ALTITUDE CONTROL
AUTO
R
ON
PRESS
OVHT
AFT
P
I
E
Passenger signs*
C
PASS SIGNS
ON
O
F
F
BUS TIE
PUMPS
HYD
R
INOP
RESET
OFF
L
PUMPS
GND
CALL
ALERT
NO SMOKING
AUTO
OFF
SYS
PRESS
AFT
ALERT
BAT
OFF
MID
ON
ON
VALVE
ON
SYS
PRESS
FWD
OFF
ON
VALVE
STBY POWER
AUTO
R
NORM
M
INOP
INOP
CABIN CALL
FUEL
JETTISON
L
Hydraulic
ON
R
L–NOZZLE–R
R
ON
FLT DK
BAT
P
Air-conditioning
W
OFF
L - RECIRC FAN - R
YAW DAMPER
Electronic engine
control (EEC)
C
W
OFF
TRIM AIR
OFF
GND
L
Pilot’s call panel
AFT CAB
AUTO
R
2
1
VALVE
FAULT
FAULT
ALIGN NAV ATT
INOP
MID CAB
AUTO
ENG START
DC FAIL
OFF
INOP
FWD CAB
AUTO
C
NAV ATT
COMPT TEMP
AIL
LOCK
ANTISKID
Compartment
temperature
UNARMED
RAM AIR TURB
L
FAULT
ALIGN
CARGO HEAT
PASS OXY
SIDE
SYS DSPL
C
R
L
OFF
EMER LIGHTS
OFF
N
STBY
LOW
OVHT
OVRD
SMOKE
NO
COOLING
HIGH
COCKPIT VOICE RECORDER
HEADPHONE
CKT BKR
OVHD PANEL
DOME
Cabin altitude
PANEL/FLOOD
APU
GLARESHIELD
LT OVRD
ANTI
COLLISION
POSITION
RED
ON
OFF
Voice recorder
AISLE STAND
OFF
ON
WING
OFF
ON
OFF
FLT DK DOOR
ON
UNLKD
UNLKD
R
Fuel
Equipment cooling
LANDING
WING
L
NOSE GEAR
R
ON
Miscellaneous lighting
LOGO
ON
TAXI RUNWAY TURNOFF
L
OFF
OFF
WHITE
ON
OFF
OFF
ON
ON
IND LTS
DIM
TEST
BRT
Wing/engine anti-ice
Windshield controls
*Passenger airplanes only.
797-FD-0061C
12-5-1-whp
Center Aislestand
767-200ER/-300ER
EICAS control
C
VNAV
C
MM
PROG
C
SP
INIT
REF
RTE
FIX
LEGS
MENU
NAV
RAD
BRT
EXEC
E
D
H
I
J
M
N
O
R
S
T
W
X
DEL
/
M
S
G
D
S
P
Y
O
F
S
T
F
A
I
L
PREV
PAGE
DE
AR
NEXT
PAGE
1
2
3
4
5
6
Y
7
8
9
CLR
.
0
+/-
Fuel control
RS
MCDU (2)
Throttle levers
Stab trim switches
Flap lever
Speed brake lever
TE
EFIS control (2)
Stab trim cutout
20
10
PLAN
APL
NOSE DN
APL
NOSE UP
Stab trim indicator (2)
ALTN
STAB TRIM
0
APL
NOSE
ON
S
T
A
B
ENG
VALVE
SPAR
VALVE
ENG
VALVE
SPAR
VALVE
2
4
Parking brake
L
6
FUEL CONTROL R
RUN
T
R
I
M
APL O
NOSE F
UP F
8
NORM
CUT OFF
10
12
L O
E F
F
14
CUT
OUT
L
Weather radar
C
STAB TRIM
WX
EST
L ENG
OVHT
MAP
ATC/TCAS
+5
TILT
+10
0
1
-15
-10
VE
ENG BTL
2 DISCH
DISCH
-5
ILS
ENG BTL
1 DISCH
R ENG
OVHT
+15
ARMED
FWD
AFT
1
2
A
C
A
R
G
O
DISCH
2
F
I
R
E
DISCH
Radio communications
panel (3)
STANDBY
VHF C
VHF R
AM
HF R
R
ACTIVE
FLT
VHF
CAB
L
VHF L
VHF C
VHF R
HF L
AM
HF R
HF SOL
PA
L
VHF
BOOM
R
Engine, cargo, and APU
fire control
BTL DISCH
R
I
G
H
T
L
E
F
T
O
F
F
ADF
ARMED
R
C
VHF
R
VHF
FLT
Audio selector (2)
ALT OFF ALT ON
SAT
OXY
VOR
V B R
APP
C R
L
MKR
ATC
ATC 2
TA
STBY
TEST
MIC
TA/RA
FAIL
L
1
ATC
2
IDENT
INT
ATC
VOR
ADF
R L R
L
R
TONE
L
R
L
R
HF
SAT
VOR
V B R
F.
F
R
E
Q
C
R
S
TEST
ILS
RUDDER TRIM
Fire/overheat test
15
STANDBY
VHF C
VHF R
AM
HF R
10
NOSE LEFT
0
5
10
15
UNITS NOSE RIGHT
AILERON
NOSE
LEFT
FIRE/OVHT TEST
ENG/APU
CARGO
5
SYS FAIL
LEFT
WING
DOWN
RIGHT
WING
DOWN
R
U
D
D
E
R
NOSE
RIGHT
Aileron/rudder trim
FAIL
P-RESET
797-FD-0062C
1-18-2-whp
Right Side Panel
767-200ER/-300ER
Gasper air
Flight recorder and
service interphone
Avionics cooling monitor
Data loader selector switch
AIR DATA
L COMPTR R
TEST
FLT REC
CONFIG
T/O
Miscellaneous test
SERV INTPH
First Observer’s oxygen
TEST
OFF
OFF
WING
ANTI ICE
TO
ON
ON
NORM
TEST
GND PROX
LDG
EADI
DUCT LEAK
VOR-L
EHIS
E1 / E2
FMCDU-L
IRU-C
IRU-R
E5
IRU-L
RESET
TEST
YAW DMPR
L
EQUIP COOL
STRUT LEAK
E / E COOLING MONITOR
Squib test
R
WINDOW/
FUEL QTY
PROBE HEAT
SQUIB TEST
TEST
ENG
R
L
Generator reset
L
1
DATA LOAD SELECTOR
1
APU
L
(k / mgk
(k / mgk
EMER ESCAPE
R
TEST 1
SLIDE
TEST 2
SPOILER
CARGO
2
2A
TEST 1
FWD
TEST 2
AFT
C
(k / mgkcjcj fg
C
FIELD
OFF
Portable data loader connection
(shown here) or airborne data loader
R
fhfdhfh
(k / mgk
(k / mgk
Smoke goggles
SYSTEM SELECT
(k / mgkzz
(k / mgkzz
(k / mgkzz
(k / mgkzz
zzOzz
zzOzz
(zzhfh / C lknmv
zzOzz
l zzOzz
zzOzz
Flight control shutoff
MO173
OXYGEN
MASK
2
APU
FIELD
OFF
l zzOzz
zzOzz
zzOzz
zzOzz
zzOzz
GEN FIELD MAN RESET
L
N
100%
PUSH
HYD GEN
FIELD
OFF
lCOC
l zzOzz
lFlS
zzOzz
zzOzz
DATA TRANSFER
UNIT RECEPTICAL
MO173
FLT CONTROL SHUTOFF - GND USE ONLY
L
C
T
A
I
L
ON
OFF
OFF
W
I
N
G
ON
OFF
R
T
A
I
L
ON
ON
OFF
W
I
N
G
ON
OFF
ON
OFF
EICAS MAINT
EVENT
READ
DISPLAY SELECT
AUTO
ECS
ELEC
PERF
MSG
HYD
APU
CONF
ENG
MCDP
EXCD
EEC maintenance
TEST
REC
MAN
ERASE
EPCS
Book stowage
RESERVE BRAKES & STRG
RESET/
DISABLE
C HYD SYS
ISLN
NORM
FLIGHT RECORDER SYS
TEST PLUG
Lighting control
L
VHF
C
VHF
R
VHF
FLT
CAB
PA
EICAS maintenance
EEC MAINT
L ENG
POWER
R ENG
POWER
MIC
BOOM
L
TEST
INT
First Observer’s
audio
First Observer’s
jack panel
MAP
R
L
HF
VOR
ADF
R L R
L
NORM
LIGHTING
R
SAT
VOR
V B R
OXY
APP
C R
L
MKR
PANEL
BOOM MIC/HEADSET
HEADPHONE
HANDMIC
Flight recorder system test plug
OFF
Reserve brakes
and steering test
Ashtray/cup holder
797-FD-0063C
2-27-2-whp/CF
767 Flight Deck - EFIS
Electronic Flight Instrument System (EFIS)
767-200ER/-300ER
Captain’s
instrument
source
select
panel
Left
EADI
Right
EHSI
Left
EHSI
Left
EFIS
control
panel
Left
EFIS
symbol
generator
• Thrust management system
• ILS navigation system
• Radio altimeter system
• PWS system
• VOR system
• DME system
Right
EADI
Right
EFIS
control
panel
Center
EFIS
symbol
generator
First Officer’s
instrument
source
select
panel
Right
EFIS
symbol
generator
• Autopilot flight director system
• Weather radar system
• ADC system
• ADF system
• EGPWS
• FMCS
• TCAS
• IRS
797-FD-0069C
2-26-2-whp/CF
797-FD-0071
1-18-2-PW/CF
EFIS/IRS Switching
767-200ER/-300ER
Captain’s
instruments
EADI - Electronic attitude
director indicator
EHSI - Electronic horizontal
situation indicator
EFI
- Electronic flight
instrument
IRS
- Inertial reference
system
RDMI - Radio distance
magnetic indicator
SG
- EFIS symbol generator
-Vertical speed indicator
VSI
First Officer’s
instruments
EADI
EADI
RDMI
RDMI
EHSI
EHSI
VSI
VSI
N
Capt
EFIS
control
panel
Capt
EFI
switch
ALTN
Capt
IRS
switch
ALTN
A
C-SG
L-SG
N
R-SG
1
N
N
F/O
EFIS
control
panel
ALTN
F/O
EFI
switch
ALTN
F/O
IRS
switch
A
A
L-IRS
1
A
A
C-IRS
N
R-IRS
This switch remains in the N position when
the Capt EFI switch is selected to ALTN.
797-FD-0070
1-18-2-whp/CF
Electronic Attitude Director Indicator
767-200ER/-300ER
Attitude comparator annunciations
Pitch limit indicator
PITCH
Ground speed
GS250
20
ROLL
DH100
2500
20
Selected decision height
Radio altitude
F
10
Speed deviation
scale and pointer
Autothrottle status
Autothrottle mode
AFDS pitch mode
Localizer deviation
scale and pointer
Split axis flight director cue
10
Glideslope deviation scale
and pointer
10
S
A/T
SPD
G/S
VNAV
10
WINDSHEAR
20
20
Windshear annunciation
CMD
AFDS status
LOC
LNAV
AFDS roll mode
Slip/skid indicator
797-FD-0073
2-26-2-whp/CF
Electronic Horizontal Situation Indicator
767-200ER/-300ER—Expanded Map Mode
• Map mode displays include reference data
programmed in the FMC, such as
• ETA, distance to go, range to altitude
• Top-of-climb, step-climb, top-of-descent,
and bottom-of-descent points
• Holding pattern
• Procedure turns
Distance to active waypoint
Magnetic (M) or
true (T) reference
L ADF (head)
Track-up annunciation
Aircraft track
18.3
NM
TRK
252 M
0835.4z
VAR/+TWX
+12
Selected heading
Aircraft heading
ETA at active
waypoint
Waypoint not on
flight plan (selectable)
Weather radar mode,
gain, and antenna tilt
R ADF (head)
Compass rose
MLF
Instantaneous track
Airport (selectable)
AST
VORTAC
(selectable)
40
STW
Estimated time and
altitude at waypoint
(selectable)
KILMR
12000
0841Z
Active flight plan
Range scale
(number is half
selected range)
Range to selected
altitude
KTTN
0
32
Weather radar return
(selectable)
0
14
WARNT
20
Wind speed and direction
Vertical deviation
scale and pointer
Waypoint on
flight plan
Manually selected
VOR course
Airplane symbol
Trend vector
797-FD-0074
2-26-2-whp
Electrical Horizontal Situation Indicator
767-200ER/-300ER—Center Map Mode
Current track
Magnetic/true
reference
ETA at active
waypoint
Distance to
active waypoint
25.5
TRK
NM
138
1335.4z
WX
+12
M
FGH I J
15
12
Weather radar
mode, gain,
and tilt
Selected heading
bug
9
18
Heading pointer
20
KLMNO
35000
1335Z
Active route
6
21
NOP
3
24
Position trend
vector
Airplane symbol
Vertical deviation
scale and pointer
20
27
VWXYZ
0
30
33
20
797-FD-0075C
12-4-1-whp
Electronic Horizontal Situation Indicator
767-200ER/-300ER—Expanded VOR/Approach Mode
DME distance to
VOR or LOC
DME
140
HDG
262 M VAR/WX +T
+12
Selected course (VOR mode) or
runway heading (approach mode)
Instantaneous track
20
Course deviation scale
and pointer
(VOR or approach mode)
Glideslope deviation
scale and pointer
(approach mode only)
To-from VOR station
(VOR mode only)
System source
annunciation
(VOR or approach mode)
20
TO
VOR R
110.10
ILS frequency
(approach mode only)
797-FD-0076C
1-19-2-whp
Electronic Horizontal Situation Indicator
767-200ER/-300ER—Center VOR/Approach Mode
Drift angle
pointer
DME
140
HDG 038
To-from VOR station
(VOR mode only)
M
Airplane symbol
Glideslope deviation
(approach mode only)
20
VOR R
TO
110.10
797-FD-0077C
1-19-2-whp
Electronic Horizontal Situation Indicator
767-200ER/-300ER—Plan Mode
ACT
RTE
1
LEGS
1 / 9
250 • H D G
ACY
028 •
158 /
530A
178 /
FL560
.824 /
FL340
.824 /
FL340
4.4 NM
TRK
252
M
0835.4 Z
2 NM
WTP 08
322 •
<CTR>
1 1 1 NM
SBY
032 •
9 6 NM
WPT 07
055 •
3 9 NM
WPT 06
.824 / FL340
M AP C TR
<RTE 2 LEGS
STEP>
WPT 10
INIT
REF
RTE
CLB
CRZ
DES
ACY
BRT
WPT 11
SBY
WPT 08
FLY P1
HAR
N
Plan mode displays
active flight plan
referenced to true
north. Pilots can step
through flight plan on
MCDU and EHSI by
pushing “STEP” line
select key.
797-FD-0078C
1-19-2-whp
EFIS Control Panel
767-200ER/-300ER
EHSI brightness control
• Outer knob - EHSI display
• Inner knob - weather radar
return
Decision height alert reset
ADI
RST
BRT
DH REF
EADI brightness control
1 0 0
Terrain data displayed when
in MAP, CENTER MAP,
EXPANDED APPROACH, and
EXPANDED VOR modes
Decision height selector
TERR
WXR
BRT
EHSI range selection
• Outer knob - selects desired
nautical mile display range for
MAP, CENTER MAP, EXPANDED
APPROACH, and EXPANDED VOR
modes
• Center switch (TFC) - displays
TCAS data when in MAP,
CENTER MAP, EXPANDED
APPROACH, and EXPANDED
VOR modes
NOTE: Terrain data and weather radar cannot be
shown on the same EFIS display at the
same time. Selection of the TERR switch
turns off weather radar display if showing.
Selection of the WXR switch turns off
terrain display if showing. It is possible, and
a common practice, to show weather radar
on one pilot’s EFIS display and show terrain
data on the other pilot’s EFIS display.
40
80
160
20
10
TFC
320
APP
VOR
ON
PLAN
CTR
MAP
NAVAID ARPT
INOP
MAP
ON
DATA
WPT
ON
ON
Weather radar return displayed
when in MAP, CENTER MAP,
EXPANDED APPROACH, and
EXPANDED VOR modes
EHSI mode selector
• Outer knob - selects VOR,
APPROACH, MAP, and PLAN
display modes
• Center switch (CTR) - alternates
display modes between center
and expanded formats for VOR,
APPROACH, and MAP modes
Map switches - select information to be
displayed in MAP or CENTER MAP mode:
• NAVAID - displays high altitude navigation
aids in FMC database if selected range is
80 nmi or greater
• ARPT - displays airports in FMC database
• DATA - displays altitude and ETA for each
waypoint on the active route
• WPT - displays waypoints in the FMC
database but not on the active route if
selected range is 40 nmi or less
797-FD-0079C
1-19-2-whp
Weather Radar
767-200ER/-300ER
ADI
RST
BRT
DH REF
Brightness control (inner knob)
• Adjusts brightness of WXR
return on EHSI
1 0 0
18.3
NM
TRK
252 M
0835.4z
VAR/+TWX
+12
Weather radar
mode, gain, and
antenna tilt data
displayed on
EHSI.
MLF
AST
WXR
TERR
40
BRT
40
10
160
TFC
320
APP
VOR
ON
0
32
MAP
0
14
WARNT
PLAN
CTR
MAP
NAVAID ARPT
INOP
KILMR
12000
0841Z
KTTN
80
20
STW
ON
20
DATA
WPT
ON
ON
Weather radar switch
• Pushing the WXR switch displays
returns on the MAP, EXPANDED
MAP, EXPANDED APPROACH,
and EXPANDED VOR modes of
the EHSI.
Weather radar returns
• When the WXR switch is pushed on the EFIS
control panel, the weather radar returns are
displayed on the respective on-side EHSI.
• The most intense areas of precipitation are
displayed in red, less intense in amber, and
least intense in green.
• Detected turbulence is displayed in magenta.
Aislestand
WX
Gain control
• AUTO presents an optimum
receiver sensitivity for best
weather radar display.
• Preset gain occurs automatically
only in WX mode.
• Rotate manually to set receiver gain.
TEST
MAP
TILT
+10
+5
+15
GAIN
Radar mode selector
• TEST – displays maintenance test pattern
• WX – displays weather radar returns
• MAP – displays ground returns
0
-5
AUTO
MAX
-15
-10
Antenna tilt control
• Controls antenna tilt angle with
reference to horizon
Weather radar panel
(representative)
797-FD-0080 C
1-19-2-whp
Flight Instruments
767
ALT
9
MACH
604
8
0
1 3,6 9 5
MB ALT
6
245
4
1013
6
KNOTS
Mach/airspeed indicator
• Each Mach/airspeed indicator displays
airspeed, Mach, and Vmo data from its
on-side air data computer (ADC).
• Each indicator displays data from the
off-side ADC when the respective air data
switch is selected to the ALTN position.
• The command speed bug can be moved
automatically from the FMC CDU or manually
from the IAS/Mach selector on the MCP.
5
IN.HG
2
1
w
1
VERTICAL
SPEED
.5
2
4
0
3
29 92
4
6
1000 FPM
.5
4
1
2
BARO
Altimeter
• Each primary altimeter displays altitude
data from its on-side ADC.
• Each indicator displays data from the
off-side ADC when the respective air data
switch is selected to the ALTN position.
• An ALT light on each indicator provides
visual indication of altitude alerting.
Vertical speed indicator (VSI)
• Each vertical speed indicator
displays vertical speed data from
its on-side inertial reference unit (IRU)
and on-side ADC.
• Each indicator displays data from the
center IRU when the respective IRS
switch is selected to the ALTN position
and from the off-side ADC when the
respective ADC switch is selected to
the ALTN position.
0 3 6.0 0 9 5.7
DME-L
DME-R
CHR
DATE
60
50
10
GMT
ET/CHR
40
20
RUN
RUN
30
HLD
HLD
SS
FS
RESET
Radio distance magnetic indicator (RDMI)
• Each indicator displays magnetic heading;
VOR and/or ADF bearings; and VOR, ILS,
DME, or VORTAC distance.
• Each indicator displays magnetic heading
data from its on-side IRU.
• Each indicator displays magnetic heading
data from the center IRU when the respective
IRS switch is selected to the ALTN position.
• Both indicators display magnetic heading
when the HSI heading reference switch is
in the NORM position and the airplane is
between 73 N and 60 S latitude (with
standard MAGVAR table) or 82 N and 82 S
latitude (with extended MAGVAR table).
The heading flag is displayed when the
switch is in the TRUE position or the
airplane is outside of these latitudes.
Clock
• Provides Greenwich mean time
(GMT) in day, month, and year or
hours and minutes on the GMT
indicator. Provides elapsed time
or chronograph on the ET/CHR
indicator.
• The chronograph is controlled by
the pushbutton on the clock or the
remote switch on the glareshield.
797-FD-0081 C
1-18-2-whp/CF
Instrument Source Select Panel
767-200ER/-300ER
Flight director selector
• Selects the flight control computer (L, C, or R)
for flight director command bar operation
INSTR SOURCE SEL
FLT DIR
L
C
IRS switch
(alternate action)
BLANK - selects normal configuration:
• L IRS supplies L and C EFIS SG, CAPT VSI,
and F/O RDMI
• R IRS supplies R and C EFIS SG, F/O VSI,
and CAPT RDMI
• C IRS is available as the alternate IRS source
ALTN - selects center IRS for attitude, heading,
and track data for the appropriate systems
above
Air data switch
(alternate action)
R
NAV
FMC-L
CDU-L
FMC-R
ALTN
w
EFI
w
NAV instrument source selector
• Selects source supplying FMS information to
symbol generators and flight control computers
Captain’s side:
- FMC-L – supplies L and C EFIS SG, and L
and C FCC
- FMC-R – supplies L and C EFIS SG, and L
and C FCC
- CDU-L– supplies L and C EFIS SG
First Officer’s side:
- FMC-R – supplies R EFIS SG and R FCC
- FMC-L – supplies R EFIS SG and R FCC
- CDU-R – supplies R EFIS SG
ALTN
w
IRS
w
BLANK - selects normal configuration:
• L ADC supplies CAPT MACH/AIRSPEED and
primary altimeter
• R ADC supplies F/O MACH/AIRSPEED and
primary altimeter
ALTN - selects opposite air data computer to
supply above instruments
INSTR SWITCH
EICAS advisory message
• Indicates each pilot has selected
ALTN with EFI switch
ALTN
w
AIR
DATA
w
INSTR SWITCH
EFI switch
(alternate action)
BLANK - selects normal configuration:
• L EFIS SG supplies CAPT ADI and HSI
• R EFIS SG supplies F/O ADI and HSI
• C EFIS SG is available as the alternate SG
ALTN - selects center EFIS SG for ADI and
HSI display
• CAPT has display control if each pilot
has selected ALTN (C-SG)
• Causes EICAS message of INSTR SWITCH
if each pilot has selected ALTN
EICAS display
797-FD-0082C
1-19-2-whp/CF
Standby Flight Instruments
767-200ER/-300ER
15
Standby attitude indicator
• The self-contained standby
attitude indicator incorporates
an ILS display with backcourse
capability.
12
NS
OFF
E
6
Standby magnetic compass
• A direct reading compass
is installed on the
center window post.
EW
ILS
B/CRS
0
Standby airspeed indicator
• The standby airspeed indicator
(pneumatic) receives input from
the L AUX pitot and the alternate
static system.
60
80
400
100
350
IAS
120
15
12
NS
E
6
EW
300
250
240
220
140
KNOTS
200
160
180
0
Standby altimeter
• The standby altimeter (pneumatic)
receives input from the alternate
static system.
1
9
8
7
03
ALT
MB
1013
6
BARO
6 95
IN. HG
2
3
29 92
4
5
Pilots’ main panel
797-FD-0083C
1-19-2-whp/CF
767 Flight Deck - EICAS
and Other Alerting Systems
797-FD-0085C
1-19-2-MT/CF
Engine Indication and Crew Alerting System
767-200ER/-300ER (EICAS)
Engine indication and crew alerting system (EICAS) features:
• Operational displays:
• Primary and secondary engine parameters
• Crew alerting messages
• Status page provides additional systems data for determining
the readiness of the airplane for dispatch
• Maintenance pages
• Automatic and manual recording of maintenance data
• Automatic display of in-flight start envelope
Pilots’ main panel
797-FD-0084C
1-19-2-whp/CF
EICAS Display
Upper
display
Standby
engine
indicator
EPR
Lower
display
EICAS
maintenance panel
104.7
N1
104.7
625
EGT
625
102
N2
102
AUTO
ON
Analog data
Digital data
Discrete inputs
From airplane
subsystems
CAUTION
CANCEL
Warning
electronic
unit
Speaker
Speaker
Speaker
Speaker
Dedicated
caution and
warning lights
RECALL
EICAS
fail
Left
EICAS
computer
unit
Right
EICAS
computer
unit
Engine
sensors
splay select pa
WARNING WARNING
CAUTION CAUTION
Master caution/warning switches
797-FD-0086C
1-19-2-whp/CF
EICAS Display Select Panel
767-200ER/-300ER
EICAS display
brightness control
• Inner knob controls
brightness of upper
display unit
• Outer knob controls
brightness of lower
display unit
EICAS computer select knob
AUTO Selects the left computer
and automatically switches
to the right computer upon
detected failure
L, R
Manually selects the left or
right computer
DISPLAY
COMPUTER
ENGINE STATUS
EVENT
RECORD
L
AUTO
R
Aislestand
Engine display switch
• Pushing selects or
deselects SECONDARY
ENGINE display on
lower CRT
Status display switch
• Pushing selects or
deselects the STATUS
display on lower CRT
BRT
THRUST REF SET
L
BOTH
R MAX IND
RESET
PULL
Event record switch
• Records maintenance data
into nonvolatile memory
Maximum indication
reset switch
• Resets displayed
overlimit readouts
Manual thrust set knob
• Inner knob
• Push - reference thrust automatically set by TMC
• Pull and rotate - manually sets reference thrust
bug on PRIMARY ENGINE display
• Outer knob
• Rotate - selects engine(s) for manual thrust
reference control
797-FD-0087C
1-19-2-whp/CF
Typical Normal EICAS Formats
767-200ER/-300ER
TAT
-12o C
TAT -12oC
1.63
2.0
1.63
CRZ
2.0
1.32
1.0
1.63
2.0
1.32
1.0
1.5
TAT -12oC
2.0
1.32
1.0
1.5
1.5
EPR
54.2
54.2
55.3
N1
70
OIL PRESSURE
105 OIL TEMP
428
441
1.32
1.0
1.5
N1
428
2.0
EPR
55.3
1.63
CRZ
1.32
1.0
1.5
EPR
54.2
2.0
1.0
1.5
1.63
1.63
CRZ
1.32
441
18
OIL QTY
3.1 VIS
55.3
N2
70
105
528
EGT
528
18
104
N2
104
3.1
15.3
FF
15.3
EGT
EGT
L
0.76
HYD QTY
92
70
OIL
105
OIL
18
OIL
0.6
94
APU
R
0.25RF
CABIN ALT AUTO1
CARGO FAN
OXY PRESS 1750
35
PRESS
N2
70
TEMP
12.4
12.6
12
RUD
FF
QTY
2.0
AIL
DISPLAY
ENGINE STATUS
C
1.00
EGT 640
COMPUTER
EVENT
RECORD
L
AUTO
R
BRT
THRUST REF SET
L
BOTH
PULL
R
MAX IND
RESET
ELEV
AIL
DISPLAY
ENGINE STATUS
COMPUTER
EVENT
RECORD
L
AUTO
R
BRT
THRUST REF SET
L
BOTH
R
MAX IND
RESET
PULL
797-FD-0088R1C
1-19-2-MT/CF
797-FD-0089C
1-19-2-MT/CF
797-FD-0090C
1-19-2-MT/CF
797-FD-0091C
2-19-2-MT/CF
EICAS Maintenance Displays
767-200ER/-300ER
Postflight
• Logbook entry of status and
maintenance messages and data
• MCDP checkout
PERF/APU
________
_______
ECS/MSG
GROSS WT
227.5
CAS
L
2
9
1
96
44
171
193
40
62
0.75
0.62
PACK OUT
TURB IN
SEC HX OUT
COMPR OUT
PRIM HX OUT
PRIM HX IN
PRECOOL OUT
DUCT PRESS
PACK FLOW
TEMP VALVE
RAM IN DOOR
FLT DK
TRIM VALVE
3
10
3
98
46
173
196
42
64
0.80
0.71
FWD
30
0.75
DUCT TEMP
28
0.80
R
FWD EQ SUP FAN 1
TAT
MACH
ZONE TEMP BITE
95
130
12
OIL PRESS
OIL TEMP
OIL QTY
ALT
95
130
12
1.008
1.008
VIB
0.7
0.5
18.8
0.3
0.9
N1
N2
428
APU:
BULK CARGO TEMP
AUX FWD
28
0.80
MID
17
0.00
AUX MID
17
0.00
25
AFT
EGT
640
RPM
100
EPR
CMD
EPR
ACT
+15
21030
1.008
1.008
18.8
N1
428
EGT
60.4
N2
60.4
1.013
FF
1.010
86
FP
84
17
0.00
AFT CABIN TEMP
APU OIL QTY
ECS/status messages
STATUS
ELEC/HYD
________
A
21.3
TRA
54.2
LOAD
9.3
SVA
12.4
AC-V
12
BVA
102
FREQ
104.2
NC
2
T2
73.2
12
12
IDG OUT
10.5
PS
9.2
IDG RISE
12.3
P2
11.3
-0.2
RP
-12.7
12
OIL T YEL
SCAV
HYD
GEN
STBY
/BAT
0
0
120
400
+10
28
DC-A
DC-V
0
L
R
0.78
120
402
140
28
145
35
0.85
125
398
150
28
150
36
L
RSVR PRESS
10
HYD QTY
79
P5
106
HYD PRESS
46
AOC
102
HYD TEMP
4
TCC
6
LOW
0.76
3230
50
C
APU
/BAT
GND
PWR
0.00
120
400
0
28
0.04
120
400
R
RF
Electrical/hydraulics
:06
:12
STATUS
N1 RED
EGT START
EGT RED
113.9
N2RED
649
NORM HIGH
1.29 OF 0.25
3210
2140
47
115
ENG
EXCD
________
116.7
649
MAX
EGT RED
Electronic propulsion control system
EGT RED
Performance APU
PAGE 1
EPCS
____
B
N1 RED
:03
PART NO
S242N701-603
ENGINE CONFIGURATION
EICAS
PW 4060
PW 4060
TMC
FMC
PW 4060
PW 4060
PW 4060
PW 4060
EPCS A
PW 40603-B5
EPCS B
PW 40603-B5
L EGT START
645
635
625
615
605
595
585
575
565
555
545
:02.7
:03.5
:04.4
:05.2
:06.3
:07.6
:08.5
:09.1
:10.4
:11.3
:12.2
PROG PINS
1
9C23
SUPL PINS
1
1000
EICAS
ADC
TMC
R EGT REDLINE
MAX
MCDP
680
660
640
620
687
AVM
1:09.5
1:11.2
1:13.3
1:15.7
Engine exceedance
PW 40603-B5
PW 40603-B5
6FE8
32
MCDP OFF
16
DSP
ON
TEST
RA
ON
FMC
OFF
FUEL
ON
ON EPCS A ON
ON EPCS B ON
ON
OFF
ON
ON
Configuration MCDP
797-FD-0092R1C
1-19-2-MT/CF
Non-Normal EICAS Operation
767-200ER/-300ER
TAT -12oC
TAT
1.50
1.50
2.0
2.0
1.28
1.0
1.28
1.0
1.5
DISPLAY
ENGINE STATUS
COMPUTER
EVENT
RECORD
L
AUTO
R
BRT
-12o C
1.50
THRUST REF SET
L
BOTH
R
2.0
MAX IND
RESET
1.50
CRZ
2.0
1.28
1.0
1.5
1.28
1.0
1.5
1.5
EPR
EPR
PULL
54.2
54.2
54.2
N1
428
N1
428
428
EGT
70
25
OIL
PRESS
70
OIL
TEMP
18
12
OIL
QTY
93
OIL
105
OIL
18
OIL
0.2
Low oil pressure, temperature, and
quantity are displayed automatically
428
EGT
70
105
54.2
93
35
PRESS
N2
70
TEMP
12.4
12.4
12
QTY
FF
2.0
Secondary engine
parameters selected
797-FD-0093R1C
1-19-2-whp/CF
Standby Engine Indicator
767-200ER/-300ER
The standby engine indicator (SEI)
display is in view automatically if
• AC power is lost
• Either EICAS CRT fails
and status is selected
on the ground
• Both EICAS CRTs fail
EPR
104.7
N1
104.7
625
EGT
625
102
N2
102
AUTO
ON
The ON position manually
activates the SEI
797-FD-0094C
1-19-2-whp/CF
Crew Alerting Features
767-200ER/-300ER
• Master warning and caution lights in Pilots’ primary field of view
• Discrete alert lights repeated by EICAS messages
• Consistent use of colors
• Red for warnings
• Amber for cautions and advisories
• White for communications
• Reduced number of aurals: bell, siren, beeper, voice, and chime
• Sound intensity automatically adjusted to compensate for flight
deck background noise
• Predictive windshear and reactive windshear detection
systems installed
• Enhanced ground proximity warning system (EGPWS) installed
• Traffic alert and collision avoidance system (TCAS) installed
797-FD-0095C
1-19-2-MT/CF
Crew Warning and Alerting System
767-200ER/-300ER
Captain’s
warning
speaker
First Officer’s
warning
speaker
Speaker
Speaker
Speaker
Speaker
CAUTION
CANCEL
RECALL
CONFIG
FIRE
r
r
WINDSHEAR
r
PULL UP
r
WARNING
SPEED
BRAKES
a
CABIN
ALT
r
ALT
ALERT
a
AUTO
PILOT
a
A/P
DISC
r
OVSPD
r
GND
a
CAUTION
Level B
aural command
Siren/owl
modules
(L and R)
Master
warning
module
Bell/chime
module
Warning electronic
unit
•
•
•
•
•
Master warning module
Bell/chime module
Siren/owl module (left or right)
Takeoff configuration module
Landing configuration module
EICAS computers
(L and R)
•
•
•
•
•
A/T
DISC
Fire warnings
Other warnings
Communications system
Ground proximity warning system
Altitude alert module
Takeoff
configuration
module
PROX
G/S INHB
FMC
a
a
a
Landing
configuration
module
Radio
altitude
Airplane configuration
• Flaps position
• Stabilizer position
• Parking brake position
• Speedbrake handle position
• Air/ground
Airplane configuration
• Throttle position
• Flaps position
• Gear position
• Speedbrake handle
position
797-FD-0096C
1-19-2-whp/CF
Crew Alerting System
767
Discrete alerting lights
Warnings
CAUTION
TAT
Advisories
CANCEL RECALL
Communication
CONFIG
FIRE
r
r
WINDSHEAR
r
PULL UP
r
SPEED
BRAKESa
CABIN
ALT
r
ALT
ALERT a
AUTO
PILOT
a
A/P
DISC
r
OVSPD
r
-15o C
+46C
88.0
CABIN ALTITUDE
OVERSPEED
R ENG OVHT
L FUEL SYS PRESS
FMC MESSAGE
PASS OXYGEN ON
R ENG FUEL VAL
AFT CARGO DOOR
•SATVOICE AVAIL
•PRINTER
RECALL
PAGE 1
D-TO
88.0
88.0
88.0
N1
760
760
EGT
GND
a
a
A/T
DISC
PROX
G/S INHB
FMC
a
a
WARNING
CAUTION
Speaker
Speaker
Master warning and
caution switch lights
Aural speakers
797-FD-0028
2-26-2-whp/CF
EICAS Message Definitions
767-200ER/-300ER
Warning (red)
An operational or aircraft system condition that requires
immediate corrective or compensatory action by the crew
• Associated with warning aural or fire bell and red master
warning lights and dedicated system warning annunciators
Caution (amber)
An operational or aircraft system condition that requires
immediate crew awareness and future compensatory action
• Associated with master caution aural and amber master
caution lights and dedicated system caution annunciators
Advisory (amber)
An operational or aircraft system condition that requires
crew awareness
• Associated with system alert annunciators
Communication
(white)
A normal communications condition that may require
crew attention
• Associated with chime aural
Status (white)
An MEL-related aircraft system fault requiring crew awareness
prior to dispatch
• Displayed on status page
797-FD-0097C
1-19-2-MT/CF
Alerting Inhibits During Takeoff
767-200ER/-300ER
Master warning lights
and aural alerts for takeoff
configuration are inhibited
Master warning lights
and aural alerts for fire, cabin
altitude, and overspeed
are inhibited
Master caution lights
and aural alerts for all
cautions are inhibited
80
knots
V1
Air-ground
transition
400-ft radio altitude
or 20 seconds after air-ground transition
797-FD-0098C
1-19-2-MT/CF
Altitude Alert System
767-200ER/-300ER
+900 ft
Visual and
aural alerts
Visual and
aural alerts
+300 ft
Selected
altitude
(MCP)
Visual and
aural alerts
-300 ft
-900 ft
No indications
White light on primary
altimeters illuminated
EICAS caution message ALTITUDE ALERT
Dedicated amber light ALT ALERT
Caution aural
Indications and aurals are inhibited
when landing gear is down and locked
797-FD-0099C
1-19-02-MT/DD
TCAS EADI Display
767-200ER/-300ER
Resolution advisory (RA)
• Displayed automatically when the traffic alert and collision
avoidance system (TCAS) calculates a collision threat with
another aircraft
• Provides vertical guidance for a pitch maneuver to ensure
adequate vertical separation with the traffic airplane
797-FD-0100C
1-18-02-MT/DD
TCAS EHSI Display
767-200ER/-300ER
Aislestand
4.4nm
TRK
140
M
0325.4z
ADI
RST
15
12
BRT
DH REF
1 0 0
DADES
18
TCAS mode
annunciation
• TFC
• TA only
• TCAS fail
• TCAS test
• TCAS off
10
TFC
BRT
HOM
+05
20
10
-11
TFC
Other traffic
symbol
160
320
APP
VOR
MAP
PLAN
CTR
MAP
NAVAID ARPT
ON
ON
DATA
WPT
ON
ON
RA
Definition of
RA
- Resolution advisory
Other aircraft is 15 to 35 seconds from closest point of approach
TA
- Traffic advisory
Other aircraft is 20 to 48 seconds from closest point of approach
Proximate traffic
- Other aircraft is less than 6 nmi away and within 앐 1,200 vertical
feet from own aircraft and not currently a potential conflict
Other traffic
40 80
INOP
Proximate
traffic
WXR
TERR
TRAFFIC
+06
-10
TA display
annunciation
TA or RA
annunciation
(red or amber)
CAMPO
- Other aircraft is more than 6 nmi away or greater than 앐 1,200
vertical feet from own aircraft and not currently a potential conflict
Arrow
- Indicates traffic climbing or descending at a rate greater than or
equal to 500 fpm
Altitude
- Number and associated sign (+ or -) indicates altitude of traffic
in hundreds of feet relative to the airplane. The number is below
the traffic symbol when the traffic is below and above the traffic
symbol when the traffic is above
TCAS mode selector (TFC)
• Push for TCAS display
Traffic symbols are available
in the EHSI modes:
• Center map
• Expanded map
• Expanded VOR
• Expanded approach
797-FD-0101C
1-19-2-whp
Enhanced Ground Proximity
Warning System (EGPWS)
767-200ER/-300ER
The enhanced ground proximity warning system (EGPWS) is a basic installation on
Boeing airplanes. EGPWS provides caution and warning level alerts to the flight crew
about potential terrain conflicts. The alerts are based primarily on airplane position,
flight path, and barometric altitude information in conjunction with the EGPWS
self-contained worldwide airport and terrain databases.
Master
warning
lights (2)
ADI
RST
Terrain display
select switch
BRT
DH REF
1 0 0
TERR
WXR
WARNING
BRT
20
10
40 80
TFC
160
320
CAUTION
APP
VOR
MAP
PLAN
CTR
PU
MAP
NAVAID ARPT
DATA
WPT
I
Aislestand
Terrain
display
on EHSI (2)
EGPWS
flap
override
switch
EGPWS
landing
gear
override
switch
EGPWS
terrain
override
switch
797-FD-0103C
1-19-2-whp
Enhanced Ground Proximity Warning System
767-200ER/-300ER
25.5
Look-ahead
distance
Speaker
Altitude
offset
NM
TRK
136
M
1335.4z
"CAUTION TERRAIN,
CAUTION TERRAIN"
Caution
Warning
20 to 30 seconds
40 to 60 seconds
40
GND
TERRAIN
TERR
PROX
The enhanced ground proximity warning system computes
two levels of terrain alerting envelopes: caution and warning.
EHSI
The enhanced ground proximity warning system
look-ahead caution alert includes unique voice
aural, terrain display, and map annunciations.
Airplane
altitude
25.5
NM
TRK
136
M
1335.4z
+2,000 ft
25.5
Speaker
+1,000 ft
TRK
136
M
1335.4z
"TERRAIN TERRAIN,
PULL UP!"
40
0 ft
NM
40
TERRAIN
-500 ft
PULL UP
-1,000 ft
WARNING
TERR
TERR
CAUTION
-2,000 ft
EHSI
EGPWS display color coding
EHSI
Terrain display colors indicate the height of the
terrain relative to the current airplane altitude.
The enhanced ground proximity warning system lookahead warning alert aurals are nearly identical to those
for the basic GPWS warnings in order to elicit the same
pilot response. In addition, threatening terrain is
presented on the map display.
797-FD-0102C
1-19-2-whp
Reactive and Predictive Windshear Systems
767-200ER/-300ER
Both a reactive windshear system (RWS) and a predictive windshear system (PWS)
are basic equipment on Boeing airplanes. The systems provide windshear detection
capability during all operations below 1,500 feet (460 m) above ground level.
1,500 AGL (RWS)
RWS
WARNING
PWS
WARNING
CAUTION
1,200 AGL
(PWS)
Leading
edge
0.5 nmi
1.5 nmi
3 nmi
797-FD-0104C
19-1-02-MT/DD
Reactive and Predictive Windshear Systems
767-200ER/-300ER
• Predictive windshear system
• Provides aural and visual alerts of an impending windshear
condition based on weather radar returns
• Reactive windshear system
• Provides recovery guidance and aural and visual alerts when
the EGPWS detects the aircraft has entered a windshear
condition
• The AFDS provides windshear recovery guidance by means of
the normal go-around pitch and roll modes when windshear is
detected:
– If an autopilot is engaged and the go-around mode is
armed, the autopilot commands a pitch-up of 15 degrees
or slightly below the pitch limit (whichever is lower) when
a GA switch is actuated
– If an autopilot is not engaged when the go-around is
initiated, the pilot must fly the windshear recovery
following the flight director commands. If the autothrottle
is not armed or engaged, the pilot must advance the
throttle levers manually
797-FD-0042
1-19-02-CF/DD
Predictive Windshear System (PWS)
767-200ER/-300ER
The predictive windshear system begins the windshear alerting sequence
with a caution to the flight crew, including a voice aural alert and an amber
WINDSHEAR message on the EHSI. The predictive windshear alerts are
generated by the weather radar system.
Speaker
Speaker
F
“MONITOR
"MONITOR
RADAR
DISPLAY"
DISPLAY”
S
A/P ENGAGE
L
0 0
B CRS
LOC
CMD
CWS
C
R
CMD
CMD
CWS
CWS
F/D
ON
F
R
E
Q
C
R
S
OFF
AUTO
APP
DISENGAGE
MAN
VOR/DME
25.5 NM
TRK
136 M
1335.4z
15
12
40
797-FD-0105C
1-19-2-whp
Predictive Windshear System (PWS)
767-200ER/-300ER
The predictive windshear system next generates one of two warning voice aural alerts,
as well as a red WINDSHEAR message on the EHSI and EADI, and illumination of the
master warning lights. “WINDSHEAR AHEAD” voice aural alert is annunciated during
takeoff phase of flight. “GO AROUND, WINDSHEAR AHEAD” voice aural alert is
annunciated during the approach phase of flight.
Speaker
Speaker
F
S
“WINDSHEAR
"WINDSHEAR AHEAD
WINDSHEAR AHEAD”
AHEAD"
or
“GO
"GO AROUND
WINDSHEAR AHEAD”
AHEAD"
WARNING
WINDSHEAR
A/P ENGAGE
L
B CRS
LOC
CMD
CWS
C
R
CMD
CMD
CWS
CWS
F/D
ON
F
R
E
Q
C
R
S
OFF
AUTO
APP
DISENGAGE
MAN
VOR/DME
25.5 NM
TRK
136 M
1335.4z
WINDSHEAR
15
12
40
WINDSHEAR
797-FD-0105 R1C
1-19-2-whp
Reactive Windshear System (RWS)
767-200ER/-300ER
The reactive windshear system warning provides a voice aural alert and a
red WINDSHEAR message when the airplane enters a performance-decreasing
windshear. The reactive windshear alert is generated by the EGPWS.
Speaker
Speaker
F
S
“WINDSHEAR
"WINDSHEAR
WINDSHEAR
WINDSHEAR"
WINDSHEAR”
WARNING
WINDSHEAR
A/P ENGAGE
L
0 0
B CRS
LOC
CMD
CWS
C
R
CMD
CMD
CWS
CWS
F/D
ON
F
R
E
Q
C
R
S
OFF
AUTO
APP
DISENGAGE
MAN
VOR/DME
25.5 NM
TRK
136 M
1335.4z
15
12
WINDSHEAR
40
797-FD-0106C
1-19-2-whp
767 Flight Deck - Autoflight
Autopilot Flight Director System
767-200ER/-300ER
(MCP)
WARNING
WARNING
CAUTION
CAUTION
Electronic
de director
Engine
Thrus
mode
selec
utoland status
(ASA
The autopilot flight director
system (AFDS) provides
• Triple-redundant flight control
computers (FCC), autopilot
servos, multi-mode receivers (MMR),
and radio altimeters
• Autopilot available from 200 ft after
takeoff through climb, cruise, descent,
landing, and go-around
• Category IIIb, 0 ft decision height and
300 ft RVR, approach, landing, and
rollout capability
Flight
management
computer
Thrust
management
computer
• Automatic thrust management through
full-flight regime
Flight control computer
• Flap placard and alpha floor protection
• Optimum vertical and lateral navigation
capabilities when coupled to the flight
management computer (FMC)
Throttle
quadrant
Autopilot servo
797-FD-0108C
1-19-02-whp/DD
Autopilot Flight Director
System Diagram
Flight
management
computer
A/T ARM
Flight director
command bars
L NAV
F/D
ON
OFF
SEL
OFF
VERT SPD
HDG
IAS/MACH
V NAV
Roll
1 2 6
Pitch
5
NORM
25
BANK
LIMIT
ALT
C
R
CMD
CMD
CMD
DN
V/S
FLT DIR
L
F/D
ON
F
A
I
L
RTE
DEP
ARR
ATC
VNAV
FIX
LEGS
HOLD
FMC
COMM
PROG
NAV
RAD
PREV
PAGE
BRT
EXEC
A
B
F
G
H
I
J
K
L
M
N
O
P
Q
R
S
T
9
U
V
W
X
Y
+/-
Z
SP
DEL
/
CLR
NEXT
PAGE
1
2
3
4
5
6
7
8
.
0
C
D
E
M
S
G
O
F
S
T
OFF
HOLD
DISENGAGE
UP
INSTR SOURCE SEL
D
S
P
Y
A/P ENGAGE
L
INIT
REF
MENU
Multipurpose
control display
unit
Left
flight control
computer
C
R
NAV
FMC-L
CDU-L
FMC-R
Center
flight control
computer
Right
flight control
computer
Left hyd
sys servo
Center hyd
sys servo
Right hyd
sys servo
Autoland
status
annunciator
Flight control actuators
Flight controls
797-FD-0044C
1-19-02-whp/DD
Mode Control Panel
767-200ER/-300ER
Vertical
navigation
switch
IAS/Mach
window
Autothrottle
arm switch
A/T ARM
F/D
ON
Heading
window
Lateral
navigation
switch
L NAV
3 3 0
Vertical
speed
window
VERT SPD
HDG
IAS/MACH
Altitude
window
1 2 6
Backcourse
switch
A/P ENGAGE
ALT
0 0 0 0
Autopilot
engage
switches
3 2 0 0 0
B CRS
L
C
R
CMD
CMD
CMD
F/D
ON
OFF
Thrust mode
switch (EPR on
PW and RR
powered aircraft
or N1 on GE
powered aircraft)
SEL
OFF
V NAV
EPR
Autothrottle
speed mode
Speed select switch
• Alternates display
between IAS and Mach
5
NORM
FL CH
SPD
SEL
25
BANK
LIMIT
DN
LOC
V/S
HOLD
HOLD
APP
OFF
DISENGAGE
UP
Flight
level
change
switch
Speed
select
knob
Heading
select
knob
Heading
hold
switch
Bank-angle
limit select
knob
Localizer mode
select switch
Altitude
select
knob
Vertical
speed
switch
Altitude
hold
switch
Flight
director
on/off
switches
Autopilot
disengage
bar
Approach
mode
select
switch
Vertical
speed
selector
797-FD-0109C
1-19-02-PW/DD
Thrust Management System
767-200ER/-300ER
Mode control panel
* Thrust mode
select panel
Thrust management
computer
Autothrottle
servo
* Thrust mode select panel
Thrust rating
• Thrust limit computation
• Thrust reduction
• Fixed climb derates
• Variable reduction by
assumed temperature
Autothrottle control
• Controls to thrust limit
• Controls to IAS/Mach or
selected thrust setting
• Speed protection
Selector switches
• TO/GA - Selects takeoff limit
while on the ground
and go-around limit
while in flight
• CLB
- Selects maximum
climb thrust
• CON - Selects maximum
continuous thrust
• CRZ
- Selects maximum
cruise thrust
TO
GA
CLB
CON
CRZ
1
2
Derate switches
• Select fixed derate
for climb
TEMP SEL
Temperature selector
• Selects assumed temperature
reduced thrust for takeoff
• Reduced thrust assumed
temperature shown in degrees
Celsius on EICAS primary
display
• Maximum 25% assumed
temperature reduced thrust
797-FD-0110C
1-19-02-MT/DD
Maintenance Control and Display Panel
767-200ER/-300ER
Collins
GROUND TEST SEL
UP
• The maintenance control and display
panel (MCDP) provides flight fault
recording for the FCC, TMC, and FMC
systems and ground test BITE for the
flight control and thrust management
systems.
• The MCDP can store up to 350 faults
for up to 99 flights.
01 R/P DISC
ROC SYST L
DOWN
POWER OFF
FLT FAULTS
INSTRUCTIONS
XXXXXXXXXXXX XXXXXX XXXX
GRD TEST
NO/SKIP
EICAS
maintenance
panel (P61)
MCDP
(located in
E/E bay)
GROUND TESTS
XXXXX XXXXX XXXX XXXXXXXXXXXX XXXXXXXXXXX
XXXX
YES/ADV
LRU
XXXXXXX
SUPPORT
XXX XXXXXX XXXXXXXXX XXXXXX XXXXXXXXX
XXXXX XXXXX XXXXXXXXX
XXXXXXXXXXXX
XXXXXX
XXX
XXXXXX
XX XXXXXXXXXX XXXXXXXX
XXXXXX XXXXXXXXXXX
XXXXXXXXXXX
XXXXXXXXXXX
XXXXX XXXXXX XXXXXXXXX
XXX XXXXXX XXXXXX XXXXXX XXX
XXXXXXXXXXXXXXX
XXXXX XXXXXXXXXX XXXX
XXX XXXX XXXXXXXXXX
XXXXX XXXXX XXXX XXXX XXXXX XXX XXXXXXXXX
XXXXXXX
XXXX XXX
XXX XXXX XXXX XXXXXXXX
XXXX
XXXX
XXXX XXXX XXXX XXXX
XXXXXX XXXXXX XXXX
XXX XXXXXXXXX
XXXXXXXX XXXX
XXX XXXXXX XXXXXXXXX X XXXX XXXXX
XXX XXX XXX XXXXXXX
XXXXXXXXXXXX XXXXXX XXXX
XXXXXXX
XXX XXXXXX XXXXXXXXX XXXXXX XXXXXXXXX
XXXXXXX XXX XXX
SYSTEM
XXXXX XXXXX XXXX XXXXXXXX XX XXXXXXXXXXXX
XXXX
XXX
XXXX
XXX XXXXXXXX
XXXXX XXX XXX XX
XXXXXXX
XXX
XXXXXX XXXXX
XXXX
XXXXX XXXX X
XXXXX XXXXXX XXXXX XXX
XXXXXXX
EICAS
computer
XXXXXXX XXXXXX XXXX
XXXXX XXX XXXXX
XXXXXX
XXXXXXX
XXXXX
Flight
management
computers
Thrust
management
computer
Flight
control
computers
• Central fault recording and fault isolation
• Allow faster airplane turnaround
• Ensure that the proper LRU is replaced
• Help lower the cost of ownership
Lower EICAS
display
STATUS
PART NO
S242N701-603
ENGINE CONFIGURATION
EICAS
PW 4060
TMC
PW 4060
PW 4060
FMC
PW 4060
PW 4060
PW 4060
EPCS A
PW 40603-B5
EPCS B
PW 40603-B5
PROG PINS
1
9C23
SUPL PINS
1
1000
EICAS
ADC
TMC
MCDP
AVM
PW 40603-B5
PW 40603-B5
6FE8
32
MCDP OFF
16
ON
DSP
RA
TEST
ON
FMC
OFF
FUEL
ON
ON EPCS A ON
ON EPCS B ON
ON
OFF
ON
ON
Configuration MCDP
MCDP
maintenance
page
Inertial
reference unit
• Faults and diagnostic data are displayed
on the MCDP or on the EICAS
maintenance page.
Air data
computer
Clock
VOR
Airline warning
annunciators
Flap
position
Mode control
panel
EFIS CP
Caution/warning
system
Instrument
landing system
Thrust mode
select panel
DME
EICAS
Flight
management
MCDU
Servos
Speed brake
handle position
Radio
altimeter
Stabilizer
position
797-FD-0111C
1-19-02-MT/DD
767 Flight Deck - FMS and MCDU
Flight Management Computer System
767-200ER/-300ER
LNAV and VNAV engage
VOR/DME tuning
FMC speed
low
ator
speed
mmand
g
nate FMC
rce select
switch
EHSI
D
S
P
Y
F
A
I
L
MCDU
INIT
REF
RTE
DEP
ARR
ATC
FIX
LEGS
HOLD
FMC
COMM
MENU
NAV
RAD
PREV
PAGE
A
NEXT
PAGE
F
BRT
VNAV
EXEC
PROG
B
C
G
H
D
E
I
J
INIT
REF
RTE
DEP
ARR
ATC
FIX
LEGS
HOLD
FMC
COMM
MENU
NAV
RAD
PREV
PAGE
A
NEXT
PAGE
BRT
VNAV
EXEC
PROG
B
C
D
E
F
I
J
K
G
H
L
M
N
O
L
M
N
O
4
5
6
P
Q
R
S
T
4
5
6
P
Q
R
S
T
7
8
9
U
V
W
X
Y
7
8
9
U
V
W
X
Y
.
0
+/-
Z
SP
DEL
/
CLR
.
0
+/-
Z
SP
DEL
/
CLR
1
2
3
K
M
S
G
D
S
P
Y
O
F
S
T
F
A
I
L
M
S
G
1
2
3
O
F
S
T
Flight control
computers
Inertial
reference
units
Left
FMC
Thrust
management
Right
FMC
Navigation
and system
sensors
797-FD-0112C
1-19-2-PW-whp
Flight Management Computer System
767-200ER/-300ER
Pegasus FMC is basic
Pegasus FMC features:
• FANS-1 capable
• Performance management
• Economically efficient flight profiles
– Climb
– Cruise
– Descent
– Holding
– Nonprecision approach
• Cost index selection
• Speed schedules
• Engine out performance
• Clean or speedbrake descent
distances displayed
• En route winds
• Step-climb planning improvements
• Flight planning
• Range/fuel data
• Takeoff and landing
• Top of descent
• Optimum altitude and step-climb point
• Alternate airports
• Required navigation performance (RNP)
• Route offsets available
• Active waypoint distance and predicted
fuel displayed
• Navigation/guidance calculations
• FMC calculates airplane position using
navigation sensor data in the following priority:
– GPS/LOC/INERTIAL
– DME/DME/LOC/INERTIAL
– DME/VOR/LOC/INERTIAL
– LOC/INERTIAL
– GPS/INERTIAL
– DME/DME/INERTIAL
– DME/VOR/INERTIAL
– INERTIAL ONLY
– GPS ONLY
– All navigation sensors failed - none
• Point-to-point great circle paths
• Guidance commands (LNAV, VNAV, and autothrottle)
• Auto tuning of DME and VOR for position updating
• Database storage
• Airplane and engine performance
• Navigation data (VHF NAVAIDS, airports, SIDs,
STARs, runways, airway approaches, and
missed approaches)
• Display data processing
• Crew alertness monitor
797-FD-0113
1-19-02-MT/DD
Multipurpose Control Display Unit (MCDU)
767-200ER/-300ER
• Keyboard layout similar to 747-400 FANS CDU
D
S
P
Y
F
A
I
L
INIT
REF
RTE
DEP
ARR
ATC
VNAV
FIX
LEGS
HOLD
FMC
COMM
PROG
MENU
NAV
RAD
A
B
C
D
E
PREV
PAGE
NEXT
PAGE
F
G
H
I
J
K
L
M
N
O
1
2
3
BRT
EXEC
4
5
6
P
Q
R
S
T
7
8
9
U
V
W
X
Y
.
0
+/-
Z
SP
DEL
/
CLR
M
S
G
O
F
S
T
• NAV RAD key - access to NAV RADIO page
– VOR radio tuning
• ATC COMM key - access to ATC data link
• FMC COMM key - access to ACARS FMC
data link
• VNAV key - access to active CLB, CRZ,
DES page
• Alternate navigation function - The MCDUs
can be used as an alternate navigation system
if both FMCs fail. The MCDUs perform lateral
navigation computations. LNAV and VNAV are
not available. Each MCDU can display route
information on its on-side EHSI.
797-FD-0114C
1-19-02-PW/DD
FMCS Position Updating
767-200ER/-300ER
• The FMCS determines aircraft position using the available
sources in this priority:
1. GPS/LOC/INERTIAL
2. DME/DME/LOC/INERTIAL
3. DME/VOR/LOC/INERTIAL
4. LOC/INERTIAL
5. GPS/INERTIAL
6. DME/DME/INERTIAL
7. DME/VOR/INERTIAL
8. INERTIAL ONLY
9. GPS ONLY
Multi-mode
receivers
IRU
VOR/DME
receivers
GPS position
FCC airplane
guidance
FMC
Radio
updating
(autotune)
FMCS LNAV
guidance
• The FMCS automatically tunes VOR/DME radios.
• If both VOR/DMEs are manually tuned, the FMC will use
the range/bearing information as long as signal criteria
are satisfied.
F
R
E
Q
C
R
S
AUTO
Nav tuning panels
(manual tuning)
MAN
• The frequency of a navigational aid on an active leg will
be tuned if it is part of a published terminal area procedure.
VOR/DME
GPS satellites
Waypoint
Active leg
VOR/DME
VOR/DME
797-FD-0123C
1-19-02-whp/DD
Global Positioning System
767-200ER/-300ER
• Global positioning system (GPS)
provides precision navigation for
• FMC position
• RNP operations
• EGPWS
• FANS operation
• GPS supports required navigation
performance (RNP) operations
down to 0.2 nmi
Onboard GPS
• FMC automatically selects best sensors
(GPS, DME, VOR, LOC)
797-FD-0115C
1-19-02-PW/DD
Global Positioning System With Pegasus FMC
767-200ER/-300ER
EHSI d
splay
GPS antenna
POS REF
FMC position
FMC (GPS)
N47 32.4 W 122 18.6
IN E R TIAL
Nav sensor
positions
Multi-mode
receiver
left
Multi-mode
receiver
right
Nav
performance
2/4
Nav
mode
N47 32.4 W 122 18.7
GP S
N47 32.4 W 122 18.6
R AD IO
N47 32.4 W 122 18.6
RNP/ACTUAL
2.00/0.30 NM
<INDEX
MCDU display
FMC
(L and R)
EFIS SG
(L, C, R)
797-FD-0116C
1-19-02-PW/DD
Required Navigation Performance (RNP)
767-200ER/-300ER
Default RNP Values
En route domestic
Oceanic remote area
RNP = 2.0 nmi
RNP = 12.0 nmi
Terminal
RNP = 1.0 nmi
Takeoff
Approach
RNP = 1.0 nmi
RNP = 0.5 nmi
Note: RNP values shown here are default values and do
not reflect the maximum capability of the airplane.
797-FD-0117C
1-19-02-MT/DD
FMCS Databases
767-200ER/-300ER
Performance
database
Basic
• Engine data
• Drag polars
• Operational limits
Customized
• Airplane factors
• Cost factors
• Preflight startup
• Navigation
• Guidance
Navigation
database
Operational program
configuration (OPC)
database
Basic
• VHF NAVAID data
• Airport and runway data
• Performance management
• Map display processing
Customized
• Airway data
• Terminal area procedures
• ILS data
• Airline-tailored data
Basic
• Default values
Modified by Boeing
Customized
• Customer requested features
Basic
• Default values
Airplane modifiable
information (AMI)
database
Specified by customer
Customized
• Customer tailored parameters
797-FD-0120
1-19-02-whp/DD
FMCS Databases - OPC and AMI
767-200ER/-300ER
Operational program configuration (OPC)
Airline modifiable information (AMI) file
• The OPC is a loadable database used to selectively • The AMI is a loadable database that provides for
enable those features requested by the customer
software designation of various FMC parameters.
within the operational program software (OPS). The
Each airline has the ability to tailor their AMI to
OPC can be changed only by Boeing. This is done
suit their specific operations by selecting the AMI
during aircraft configuration or with a service bulletin.
parameters. In the event the AMI parameters are not
modified by the customer or are not available, the
• The OPC enables these following optional FMC
FMC provides hard-coded default parameters in the
features:
basic software.
• Runway distance and offset position shift in units
of feet or meters (must enable either feet or meters) • Some AMI parameters may be viewed by the crew
• Crew alertness monitor
on the CDU airline policy page.
• Non-directional beacon approaches
• A summary of types of parameters that can be
• Non-precision GPS approaches
specified by the AMI are:
• Display of vertical bearing, flight path angle (FPA)
• Performance, guidance, and takeoff data
and vertical speed
• Crew alertness monitor configuration data
• Scanning DME operations
• Alternate function parameters
• Altitude intervention
• Data link request/report prompt inhibits
• Airline operational communications data link
• Data link Imbedded element identifier (IEI)/
(AOC DL)
response/trigger enables
• Air traffic services data link (ATS DL)
• Down link trigger for position report enable
• Takeoff data link
• Down link trigger for progress report enable
• Required time of arrival (RTA)
• Request uplink Imbedded message identifiers (IMI)
• FMC printer interface
table
• Down link address table
797-FD-0121
1-19-02-whp/DD
Inertial Reference System
767-200ER/-300ER
IRS features
• Triple-redundant laser gyros
• Certified for extended
navigation over water
• Maximum alignment time
of 10 min
• 30-sec quick alignment for
through-stops
• Initial position input through
either the inertial reference
mode panel or FMS MCDU
• Flight crew selectable alternate
data sources
EADI
Navigation systems
• WXR
• EGPWS
• FMC
• MMR (GPS)
EADI
EHSI
EHSI
VSI
VSI
Autopilot systems
• FCC
• TMC
• Yaw damper
IRS outputs
•
•
•
•
•
•
•
•
•
Antiskid/autobrake
system
• EICAS
Magnetic/true heading
Magnetic/true track
Primary attitude
Ground speed
Wind velocity and direction
Vertical speed
Navigation position/drift angle
Inertial velocity vectors
Acceleration and angular rates
Air data
computers (2)
jgiihc oijfod
jgiihc oijfod
EFIS
symbol
generator
Left
IRU
Instrument
source
select
switch
Center
IRU
Instrument
source
select
switch
Right
IRU
Inertial reference
mode panel
IRS MODE SEL
N
W
DSPL SEL
PPOS
WIND
TK/GS
HDG
SYS DSPL
C
L
R
1
N
2
3
W
4
H
5
E
6
7
S
8
9
ENT
0
CLR
jgiihc oijfod
L
C
ALIGN
ALIGN
OFF
True airspeed
Altitude
Altitude rate
R
ALIGN
ALIGN
ON DC
ON DC
ON DC
DC FAIL
DC FAIL
DC FAIL
FAULT
FAULT
FAULT
NAV
ATT
ALIGN
OFF
NAV
ATT
ALIGN
NAV
ATT
OFF
Initialization
control
display
797-FD-0122C
1-19-02-whp/DD
767 Flight Deck - Systems
Air-Conditioning and Pneumatics
767-200ER/-300ER Passenger
Air-conditioning system
• Two independent packs with
one-pack dispatch capability
• Automatic temperature control
for the flight deck, forward, mid,
and aft passenger cabin zones
CARGO HEAT
FWD
AFT
ON
ON
OVHT
OVHT
Passenger compartment
temperature
COMPT TEMP
INOP
INOP
FWD CAB
AUTO
Passenger compartment
temperature control
INOP
AFT CAB
AUTO
MID CAB
AUTO
Trim air
C
OFF
C
W
C
W
OFF
W
OFF
TRIM AIR
L - RECIRC FAN - R
ON
ON
ON
INOP
INOP
OFF
Recirculation fan
Flight deck trim air
FLT DK
INOP
Pack reset
C
W
AUTO
R PACK
L PACK
Pack control
RESET
RESET
INOP
Pneumatic duct
pressure
C
MAN
PACK
OFF
INOP
W
PACK
OFF
AUTO
AUTO
N
OFF
N
OFF
S
S
Pneumatic system
• Provides air for
• Engine starting
• Cabin air-conditioning
• Pressurization
• Wing and engine anti-icing
• Potable water tank and hydraulic
reservoir pressurization
• TAT probe aspiration
• Bleed air normally isolated to
its associated pack
C
T
C
Flight deck compartment
temperature
T
B
B
Y
Y
W
W
Isolation valve
60
80
20
0
DUCT
PRESS
PSI
L ISLN
R ISLN
VALVE
VALVE
C ISLN
APU bleed air
V
A
L
V
E
DUCT
LEAK
DUCT
LEAK
BLEED
Engine bleed air
OVHT
BLEED
DL
UE
CA
TK
L ENG
O
F
F
V
A
L
V
E
OVHT
ADP
APU
Duct leak
Engine bleed valve
Engine bleed overheat
R ENG
O
F
F
Normal in-flight procedures: none
797-FD-0124C
1-19-02-whp/DD
Air-Conditioning and Pneumatics
767-300 Freighter
Air-conditioning system
• Two independent packs with
one-pack dispatch capability
• Automatic temperature control
for the flight deck, forward, and
aft main deck cargo zones
• Automatic temperature control
for forward lower lobe cargo
compartment (General Market
Freighter)
CARGO HEAT
FWD
AFT
ON
ON
OVHT
OVHT
Flight deck
temperature
Main deck
temperature
COMPT TEMP
AUTO
Fwd Cargo Air Cond
Flight deck
trim air
M1819
ON
OVHT
INOP
INOP
INOP
C
W
OFF
TEMP CONTROL
Flight deck
temperature
control
Main deck
temperature
control
W
C
FLT DECK
AUTO
C
FWD CAB
AUTO
AFT CAB
AUTO
C
W
MAN
W
OFF
C
Forward cargo
air-conditioning panel
(767 General Market
Freighter Only)
W
OFF
TRIM AIR
ON
Pack reset
OFF
Pneumatic duct
pressure
L PACK
R PACK
RESET
RESET
INOP
INOP
PACK
OFF
PACK
OFF
AUTO
Pack control
AUTO
N
OFF
N
OFF
S
C
S
T
C
B
W
Pneumatic system
• Provides air for
• Engine starting
• Cabin air-conditioning
• Pressurization
• Wing and engine anti-icing
• Potable water tank and hydraulic
reservoir pressurization
• TAT probe aspiration
• Bleed air normally isolated to
its associated pack
T
B
Y
W
Y
Isolation valve
60
80
20
0
DUCT
PRESS
PSI
L ISLN
R ISLN
VALVE
VALVE
C ISLN
APU bleed air
V
A
L
V
E
DUCT
LEAK
DUCT
LEAK
BLEED
BLEED
DL
UE
CA
TK
OVHT
Engine bleed air
L ENG
O
F
F
OVHT
ADP
APU
V
A
L
V
E
Duct leak
Engine bleed valve
Engine bleed overheat
R ENG
O
F
F
Normal in-flight procedures: none
797-FD-0125C
1-19-02-whp/DD
Cabin Pressure Control
767-200ER/-300ER
Cabin altitude manual control
• Controls outflow valve with
mode selector in manual
CABIN ALTITUDE CONTROL
VALVE
MANUAL
AUTO RATE
CLIMB
OP
MAX
MIN
CL
DESCEND
Cabin altitude auto rate control
• Sets limit for cabin altitude rate of
climb or descent during auto control
• Establishes approximately 500 ft/min
climb and 300 ft/min descent when
set on index
LDG ALT
AUTO INOP
034 0
MODE SELECT
AUTO 2
MAN
AUTO 1
Landing altitude selector
• Selects landing altitude from
1,000 ft below sea level up
to 14,000 ft
CABIN
0
2
25
4
20
15
6
10 8
0
10
2
8
4
6
DIFF
PSI
ALT
FT X
1000
1 2
0
1
2
RATE
FPM X
1000
Cabin pressurization mode control
• Dual automatic system with auto
switching in event of failure
• Maintains sea level up to 22,500 ft
and 8,000 ft up to maximum cruise
• Maximum pressure differential 8.6 psi
Cabin rate of climb indicator
Differential pressure indicator
Cabin altitude indicator
797-FD-0126C
1-19-2-whp/CF
Cargo and APU Fire Protection
767-200ER/-300ER Passenger
• Fire detection and extinguishing systems are installed for both
engines, the APU, and cargo compartments. The main wheel wells
have detection only.
• Two fire extinguisher bottles are installed for engine fire control
for General Electric and Pratt & Whitney engines. Four fire extinguishing
bottles are installed for engine fire control for Rolls-Royce engines.
• One fire extinguisher bottle is installed for APU fire control.
• Three fire extinguishing bottles are installed for cargo fire control.
Engine overheat light
Engine fire bottle discharge light
APU fire bottle
discharged light
L ENG
OVHT
ENG BTL
1 DISCH
Fire warning light and
engine fire switch
ENG BTL
2 DISCH
R ENG
OVHT
DISCH
1
L
E
F
T
1
2
R
ARMED
FWD
AFT
FWD-ARM-AFT
CARGO FIRE
DISCH
2
ARMED
2
BTL DISCH
F
I
R
E
I
G
H
APU BTL
DISCH
C
A
R
G
O
DISCH
APU
1
DISCH
T
APU fire warning
and APU fire switch
Fire/overheat detection
test panel
FIRE/OVHT TEST
WHL
WELL
ENG/APU
CARGO
SYS FAIL
FAIL
P-RESET
Fire test
switch for
wheel wells
System fail light
System fail
reset switch
Fire override switch
(under fire switch)
Fire/overheat test
switch for engines,
APU, and cargo
797-FD-0127C
1-19-2-whp/CF
Cargo and APU Fire Protection
767-300 Freighter
• Fire detection and extinguishing systems are installed
for both engines, the APU, and cargo compartments.
The main wheel wells have detection only.
• Two fire extinguisher bottles are installed for engine
fire control for General Electric and Pratt & Whitney
engines. Four fire extinguishing bottles are installed
for engine fire control for Rolls-Royce engines.
• One fire extinguisher bottle is installed for APU
fire control.
• Three fire extinguishing bottles are installed for cargo
fire control.
General Market
Freighter Configuration
Engine overheat light
Engine fire bottle discharge light
APU fire bottle discharged light
CARGO FIRE
L ENG
OVHT
ENG BTL
1 DISCH
R ENG
OVHT
ARMED
FWD
A
R
M
AFT
FWD
DISCH
1
Fire warning
light and engine
fire switch
ENG BTL
2 DISCH
2
L
E
F
T
ARMED
DISCH
1
R
I
G
H
T
2
A
R
M
AFT
ARMED
MAIN
APU BTL
DISCH
DEPR/
DISCH
2
DISCH
APU
DISCH
DEPR
1
MAIN
APU fire warning
and APU fire switch
Fire override switch
(under fire switch)
Package Freighter Configuration
APU fire bottle discharged light
DEPR/
DISCH
APU BTL
DISCH
DEPR
CARGO
Fire/overheat detection
test panel
FIRE/OVHT TEST
WHL
WELL
ENG/APU
CARGO
SYS FAIL
FAIL
P-RESET
Fire test switch
for wheel wells
2
System fail light
System fail
reset switch
Fire/overheat test switch
for engines, APU, and cargo
DISCH
MAIN
FWD
APU
1
AFT
APU fire warning
and APU fire switch
797-FD-0127R1C
1-19-2-whp
Fire Protection
767-200ER/-300ER APU Ground Service Control Panel
APU FIRE
WARNING
HORN
APU fire warning horn
APU fire bottle armed light
APU FIRE
Fwd
FIRE BOTTLE
ARMED
APU fire bottle discharged light
BOTTLE
DISCHARGED
APU bottle discharge switch
APU fire light
APU FIRE
SHUTDOWN
APU BOTTLE
DISCHARGE
APU shutdown switch
APU ground control panel
on nose landing gear strut
797-FD-0128C
1-19-2-whp/CF
Equipment Cooling
767-200ER/-300ER
Equipment
cooling
selector
EQUIP COOLING
CABIN
ALTITUDE
VALVE
AUTO
PRESS DIFF
LIMIT: T/O &
LDG .125 PSI
STBY
OVHT
OVRD
SMOKE
NO
COOLING
No cooling
light
Conditioned
pack air
(3)
(4)
Flight
deck
panels
Override
valve ( p)
Override
valve ( p)
(2)
EE
equipment
Air cleaner
Supply
fan
Manifold
interconnect
valve
Flight
deck
panels
Override
valve ( p)
EE
equipment
Check
valves
AUTO – Automatically controls
equipment cooling system
STBY – Positions equipment cooling
system for inboard airflow
OVRD – Positions equipment cooling
system for reverse airflow
Valve light
Overheat light
Smoke light
Overboard
exhaust
valve (1)
Inboard
supply
valve
Check
valves
Supply
fan
EE
equipment
Air cleaner
Air cleaner
Exhaust
fan
(ON)
Flight
deck
panels
Exhaust
fan
Overboard
exhaust
valve
Check
valves
Supply
fan
Exhaust
fan
Overboard
exhaust
valve
Inboard
supply
valve
Inboard
supply
valve
(5)
Bypass
valve (1)
Automatic (AUTO) mode
Bypass
valve
Standby (STBY) mode
(1) These valves reverse if OAT below 45oF/7oC or in flight
or on ground with both engines running.
(2) These valves reverse if cargo fire switch is in DEPR (Freighter only).
Bypass
valve (2)
Override (OVRD) mode
(3) This valve is open on the 767 Freighter only in
flight or on the ground with both engines running.
(4) This valve is open on the 767 Freighter.
(5) This valve is closed during flight.
797-FD-0129C
1-19-2-whp/CF
Auxiliary Power Unit
767-200ER/-300ER
Auxiliary power unit (APU)
• Installed in unpressurized tail cone
• Ground or in-flight use
• 90-kVA electrical generator
• Generator power available to
airplane’s maximum certified altitude
• Bleed air for packs and engine start
• Automatic start
• Crew monitoring not required
• Start up to 35,000 ft
• Automatic cooldown on shutdown
• Automatic shutdown for fault/fire
• EGT readout on EICAS status page
APU
ON
OFF
START
RUN
FAULT
797-FD-0130C
1-19-2-whp/CF
Fuel System
767-200ER/-300ER
• Three-tank system
• Independent fuel system for each engine with
crossfeed capability
• Two boost pumps in each wing tank
• Two override pumps in center tank
• Automatic scavenge system for center tank
• APU supplied from the left fuel manifold
• Normal fuel configuration is tank to engine
• Solid-state fuel quantity and temperature indication
• Fuel configuration alerts for
• Fuel imbalance
• Low fuel
• Center tank pumps off with fuel in tank
• Minimum crew workload
• All pumps turned on before flight
• Center tank pumps turned off when center
tank is empty
L
PUMPS
FUEL
XFEED
R
PUMPS
VALVE
PRESS
VALVE
PRESS
ON
ON
AFT
AFT
PRESS
ON
ON
FWD
FWD
767-200ER
138,037 lb (20,450 U.S. gal)
62,600 kg (77,410 liters)
PRESS
C PUMPS
ON
FUEL
CONFIG
P
R
E
S
S
P
R
E
S
S
R
L
C
L
LB
TEMP
ON
KG
C
LB
KG
FUEL QTY
X 1000
R
LB
KG
TOTAL
767-200ER*, -300ER
161,700 lb (24,140 U.S. gal)
73,350 kg (91,380 liters)
* Option
797-FD-0131C
1-19-2-whp/CF
Fuel Jettison
767-200ER/-300ER
• A fuel jettison system is installed on 767 airplanes
with gross takeoff weights in excess of 360,000 lb.
FUEL
JETTISON
FAULT
L–NOZZLE–R
• Fuel is pumped from the center auxiliary tank by dedicated
jettison pumps through jettison transfer valves to the jettison
nozzles located on the outboard trailing edges of the wings.
OFF
ON
ON
ON
VALVE
VALVE
Center
auxiliary
tank
Jettison and
override pumps
P
P
Jettison
nozzle valve
Jettison
transfer
valve
Jettison
nozzle
Left wing shown, right wing identical
Existing fuel system
Fuel jettison system
797-FD-0132C
1-19-2-whp/CF
Communication Radios and Equipment
767-200ER/-300ER
Left RCP
Right RCP
ACTIVE
STANDBY
VHF L
VHF C
VHF R
HF L
AM
HF R
HF SENS
O
F
F
Radio communications
panel (representative)
Center RCP
NOSE
RIGHT
• Three radio communications panels are each capable of tuning the
VHF and HF radios.
• Radio communications panels support VHF data link, HF data link,
8.33-kHz frequency spacing, VDL mode 2, and voice mode protection.
Separate options are available to enable each of these functions.
• Separate option is available, contingent on selection of compatible HF
and VHF transceivers, to display transceiver fault status on the radio
communications panel by monitoring the CMC output bus.
BOEING PROPRIETARY
797-FD-0133C
2-26-2-CF
Pilots’ Call Panel
767-200ER/-300ER
CABIN CALL
FWD
MID
AFT
GND
ALERT
CALL
ALERT
SELCAL call lights/switches (blue)
• Illuminate when attendant at respective
station calls flight crew
• Accompanied by flight deck high chime
• Reset when call is answered or
switch is pressed
• Sound high-low chime and illuminate
pink light at attendant station
• Inhibited if handset at selected station
is off hook
Alert call light/switch (amber)
• Illuminates when cabin
attendant activates alert call
• Accompanied by flight deck
high chime
• Resets when call is answered,
the calling handset is reset, or
when switch is pressed
• Sounds high-low chime three
times and flashes pink lights
at all attendant stations when
pressed
Ground call light/switch (blue)
• Illuminates when ground personnel
at APU ground control panel call
the flight crew
• Accompanied by flight deck high
chime
• Press to reset
• As long as the switch is held down,
a horn sounds in the wheel well to
call ground personnel
797-FD-0134C
1-19-2-whp/CF
Audio Selector Panel
767-200ER/-300ER
Microphone selector
switches/lights (white)
• Illuminate when selected
• Select desired transmitting system
• Interlocked to permit only one
switch to be selected at a time
• Automatically activate respective
receiver
Ground call light
• Ground crew call to pilots
• 30-sec reset
MIC
MIC
MIC
MIC
MIC
MIC
CALL
CALL
CALL
CALL
CALL
IN USE
L
VHF
Receiver control
• Push to select ON/OFF
(alternate action)
• Rotate for volume control
C
VHF
MIC
R
VHF
L
CAB
MIC
MIC
MIC
MIC
CALL
CALL
CALL
R
L
VOR
FLT
CALL
L
HF
INT
Push-to-talk switch
• Transmits on selected system
with boom microphone or
oxygen mask microphone
• Resets SELCAL light for
selected radio
Call lights (9)
• VHF, HF, and SATCOM
• ACARS call on VHF-C
• Flight attendant call on
cabin interphone
• Resets with transmit switch
or PTT activation; SATCOM
resets upon termination of call
ADF
R L
R
PA
Receive light
• Indicates respective
receiver is selected
BOOM
R
SAT
OXY
APP
V B R
L
C R
MKR
Boom-oxygen switch
• Selects either boom or
oxygen mask microphone
for use with selected system
Filter selector
• Filters audio from VOR,
ADF, ILS, DME
• VOICE – voice only
• RANGE – range (code) only
• BOTH – voice and range
797-FD-0135C
2-26-2-whp
Antenna Locations
767-200ER/-300ER
VOR (L, R)
HF
ATC (L)
TCAS
ATC (R)
GPS (L, R)
SATCOM 2
ADF (L)
ADF (R)
VHF (C)
VHF (L)
Weather radar
Localizer (L, C, R)
Glideslope (L, C, R)
Airphone 1
TCAS
ATC (L)
ATC (R)
VHF (R)
Marker beacon
DME-R
Radio altimeter receiver (L, C, R)
Radio altimeter transmitter (L, C, R)
DME (L)
1
Structural provisions.
2
Optional installation.
797-FD-0136C
1-19-2-whp/CF
Electrical System
767-200ER/-300ER
90-kVA engine-driven generators
• Integrated drive generator (IDG)
BAT
STBY POWER
AUTO
ON
90-kVA APU generator
• Automatic start/shutdown
• Start with separate APU battery
• Ground or in-flight use
• APU generator allows for dispatch
with one engine IDG inoperative
D
I
S
C
H
BAT
OFF
OFF
O
F
F
APU GEN EXT PWR
ON
O
BUS TIE
One generator can supply all loads
except utility
ON
F
BUS TIE
AVAIL
F
AUTO
AUTO
ISLN
Nonparallel system
• Left and right sides powered by
separate power sources
ISLN
UTILITY BUS
R
ON
ON
OFF
OFF
R BUS
BUS
BUS
OFF
Automatic load transfer
Automatic load shed of utility buses
• For generator loss
• For overload
• For engine start from APU
L
L BUS
OFF
R
L
GEN DRIVE DISC
GEN
CONT
L
R
DRIVE
DRIVE
GEN
CONT
O
Standby ac and dc buses
• Powered by main battery
• 30-min minimum
F
O
ON
F
F
APU
ON
OFF
Flight instrument transfer bus
• Automatic transfer
• No normal in-flight procedures
ON
F
START
RUN
FAULT
797-FD-0137C
1-19-2-whp/CF
Electrical Power System
767-200ER/-300ER
External ac power
APU
gen
L
IDG
L GCB
EPC
APB
R GCB
R BTB
L BTB
Left main ac bus
R
IDG
Right main ac bus
AC tie bus
Left
utility bus
Right
utility bus
F/O flight inst
transfer bus
Left
TRU
Right
TRU
Captain flight
inst trans bus
Left ac
transfer bus
AC
gen
Standby
ac bus
DC
gen
HMG
Flight ac
transfer bus
Left dc bus
DC tie bus
Static
inverter
Center
ac bus
Right dc bus
Ground service bus
Center
dc bus
Standby
dc bus
Battery bus
Hot battery bus
Main
batt chrgr
APU
batt chrgr
APU battery bus
Main battery
Standby tie bus
APU battery
797-FD-0043
1-21-2-whp/CF
Hydraulic Motor-Driven Generator (HMG)
767-200ER/-300ER
• Backup electrical power source for extended twin-engine
operations
• Additional generator to supply 5-kVA ac and 50-A dc power
• Powered by center hydraulic system air-driven pump
• Located in left-hand wheel well on keel beam
• An independent power supply for the Captain’s flight
instruments as well as selected navigation, communication,
lighting, and anti-icing loads
• Activated automatically when the airplane is airborne with
loss of the engine-driven and APU generators
797-FD-0138C
1-19-2-whp/CF
Hydraulic Motor Generator (HMG)
767-200ER/-300ER
ENTRY
EMER
DOORS
CARGO
DOORS
CAPT
ACCESS
DOORS
DOORS
FO
L AOA
L AUX
PASS OXY
EMER LIGHTS
FWD
R AUX
BULK
TAT
PITOT
PITOT
OFF
ON
ARMED
W
STAB
N
2
3
W
4
H
5
E
6
7
S
8
9
ENT
0
CLR
1
ON
UNARMED
AUTO
SPOILERS
ON
SPDBRK
OVHT
COMPT TEMP
AIL
RUDDER
UNSCHED
OVHT
ON
TRIM
DSPL SEL
PPOS
WIND
CARGO HEAT
R AOA
PITOT
PITOT
IRS MODE SEL
N
ANTISKID
STAB TRIM
LOCK
RATIO
WINDOW HEAT
TK/GS
HDG
L
RAM AIR TURB
R
FWD
FWD
SIDE
SYS DSPL
C
L
R
SIDE
PRESS
ON
ON
ON
ON
UNLKD
INOP
INOP
INOP
INOP
INOP
INOP
FWD CAB
L
C
ALIGN
ON DC
NAV
OFF
NAV
ALIGN
BOTH
OFF
ALIGN
NAV
INOP
AUTO
VALVE
C
FAULT
ATT
AFT CAB
R
2
VALVE
DC FAIL
FAULT
ATT
1
ON DC
DC FAIL
FAULT
AUTO
ENG START
ALIGN
L
ON DC
DC FAIL
ALIGN
MID CAB
AUTO
R
ALIGN
C
W
OFF
ATT
TRIM AIR
OFF
AUTO
OFF
GND
ON
CONT
CONT
FLT
FLT
OFF
L
FUEL
JETTISON
ON
ON
INOP
INOP
BAT
L
AUTO
ON
D
NORM
ON
ON
VALVE
VALVE
FUEL
XFEED
QTY
QTY
BUS TIE
PUMPS
HYD
ENG
ON
ON
ON
PRESS
PRESS
PRESS
OVHT
OVHT
OVHT
OVHT
I
A
Y
AIR
AUTO
AUTO
ISLN
BUS
A
OFF
R BUS
R
ON
OFF
L
P
R
R
E
E
S
S
S
S
DESCEND
00340
0 4
AUTO
ON
OFF
F
N
VALVE
C ISLN
MAN
AUTO 1
R
V
A
L
V
E
DUCT
LEAK
LB
O
ON
F
DRIVE
F
DRIVE
ON
KG
LB
KG
FUEL QTY
X 1000
LB
KG
WING
BLEED
DL
UE
CA
T K
OVHT
ON
START
OFF
L
L
RUN
FAULT
2
8
ENGINE
4
VALVE
6
2
L ENG
1
2
R
R
VALVE
0
2
25
4
20
15
6
10 8
0
10
ANTI-ICE
ON
ON
ON
VALVE
VALVE
DIFF
PSI
ALT
FT X
F
1000
RATE
O
F
F
V
A
L
V
E
OVHT
R ENG
O
F
F
VALVE
AUTO
PRESS DIFF
LIMIT: T/O &
LDG .125 PSI
WIPER
OFF
ERASE
F
FPM
1000
ADP
APU
EQUIP COOLING
CABIN
ALTITUDE
TEST
DUCT
LEAK
BLEED
TOTAL
C
TEMP
F
D
APU
R ISLN
0
MODE SELECT
AUTO 2
O
A
ON
20
VALVE
AUTO INOP
R
PSI
L ISLN
LDG ALT
ON
C
L
CONT
M
OFF
MAX
MIN
CL
FUEL
P
GEN
R
L
CONT
E
OVHT
AUTO
ON
Y
80
PRESS
R
GEN DRIVE DISC
GEN
D
OFF
T
B
60
OFF
L
D
ON
BUS
ON
OFF
S
C
W
OP
CONFIG
L
AUTO RATE
Battery switch
• ON - Provides backup power from the
hot battery bus to the battery and
standby buses
• OFF - Disconnects battery bus from hot
battery bus
DUCT
UTILITY BUS
M
PRESS
OVHT
AUTO
A
N
Y
W
MANUAL
CLIMB
FWD
PRESS
VALVE
PRESS
C PUMP
L BUS
VALVE
FWD
ELEC
PRESS
OVHT
M
N
ON
ON
Y
ELEC
PRESS
E
PACK
OFF
AUTO
OFF
T
B
CABIN ALTITUDE CONTROL
BUS TIE
AVAIL
ISLN
R
D
W
MAN
N
C
ON
ON
F
R
ON
PRESS
INOP
C
AUTO
OFF
PRESS
VALVE
P
I
RESET
INOP
PACK
OFF
ON
ON
AFT
R
C
1-ELEC-2
R PACK
L PACK
AUTO
S
F
L
ALERT
OFF
F
R
PUMPS
AFT
PRESS
O
ENG
W
AUTO
RESET
L
PUMPS
ON
APU GEN EXT PWR
QTY
C
CALL
SEATBELTS
ON
OFF
F
F
F
H
SYS
PRESS
ALERT
NO SMOKING
AUTO
O
C
SYS
PRESS
GND
AFT
PASS SIGNS
BAT
OFF
S
ALTN
CONT
SYS
PRESS
MID
OFF
OFF
I
ENG
ALTN
R
Battery discharge
light illuminated
- The main battery
is discharging
INOP
ON
STBY POWER
R
ELEC
NORM
FWD
FAULT
L–NOZZLE–R
M
ON
INOP
R
CABIN CALL
R
ON
INOP
FLT DK
YAW DAMPER
P
W
OFF
L - RECIRC FAN - R
AUTO
OFF
GND
C
W
OFF
STBY
OVHT
LOW
OVRD
SMOKE
NO
COOLING
HIGH
HEADPHONE
COCKPIT VOICE RECORDER
CKT BKR
OVHD PANEL
DOME
PANEL/FLOOD
GLARESHIELD
AISLE STAND
ANTI
LT OVRD
POSITION
WING
COLLISION
RED
ON
OFF
ON
OFF
OFF
OFF
WHITE
LOGO
OFF
ON
ON
FLT DK DOOR
ON
UNLKD
ON
TAXI RUNWAY TURNOFF
Standby power bus off light
• Illuminated - standby ac
or dc bus
not powered
UNLKD
L
OFF
R
LANDING
WING
L
NOSE GEAR
R
IND LTS
DIM
TEST
BRT
ON
OFF
OFF
ON
ON
Battery
charger
BAT
AUTO
ON
Hot bat
bus dc
D
I
S
C
H
Battery
Flow lines
not on panel
DC power
AC power
DC
output
Hydraulic
motor-driven AC
generator output
(HMG)
BAT
OFF
OFF
O
F
F
Battery
bus dc
Left
dc
Captain flight
instrument transfer
bus
Left
transfer
bus
Right
transfer
bus
Standby
dc
bus
Standby
ac
bus
Standby power selector
• OFF - The standby buses
are unpowered
• AUTO - The standby buses powered
from main ac and dc
transfers to battery power
if normal ac power is lost
• BAT - The standby buses
are powered from the
main battery
797-FD-0032
1-19-2-whp/CF
Hydraulic Motor Generator System
767-200ER/-300ER
Systems powered by
battery or hydraulic motor
generator if operational
• Fire extinguishing systems
• Engine, APU, and cargo and wheel
well fire detection systems
• Spar fuel valves
• APU fuel valve
• Fueling system
• Fuel crossfeed valves
• DC fuel pump
• Fuel quantity system
• Engine fuel control valves
• Clock time references
• Captain’s clock
• IRS (L and C continuous; R 5 minutes)
• RAT manual deployment
• RAT automatic deployment system
• Parking brake valve
• Landing gear alternate extension
• Passenger address system
• Interphone systems
• Generator controls
• Engine-driven hydraulic pump shutoff valves
• Air-driven hydraulic pump control
• E/E cooling override system
• Antiskid for inboard wheels
• Air/ground system
• Passenger oxygen deployment system
• Standby engine indicating
• Engine start controls
• Engine ignition system
• Engine thrust reverse control
• Left and right pack valves
• Manual wing anti-ice
• Manual engine anti-ice
Additional systems powered
by hydraulic motor generator
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
Alternate stabilizer trim
Stab trim shutoff valves
Manual cabin altitude control
Aislestand floodlight
Left yaw damper
Three spoiler pairs
Left VHF
Left stick shaker
Standby attitude indicator
Left aural warning speaker
Rudder trim
Main panel floodlights
Left VOR/marker beacon
Left air data computer
Left RDMI
Center MMR
Duct leak detection
E/E cooling standby mode
Standby instrument panel lights
Right ADF
WEU (channel B)
Standby electrical power control
APU control
Cabin altitude indicator
Cabin differential pressure indicator
Cabin emergency lights
Emergency evacuation system
(if installed)
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
Left EADI
Left EHSI
Left altimeter
Left Mach/airspeed indicator
Left EFIS symbol generator
Center EFIS symbol generator
Left EFIS control panel
Left VSI
Left MMR
Left radio altimeter
Captain’s instrument and panel lights
Left FMC and MCDU
Left DME
Left HF
Flap and rudder trim position indicators
Aislestand and overhead panel lights
Captain’s pitot heat
Right auxiliary pitot heat
Left angle of attack heat
Left and right pneumatic isolation valve
Cabin pressure controller auto 1 and 2
Lavatory lights
Left and right engine probe heat
Left ATC system
Cargo heat override control
Passenger cabin ceiling and
night lighting
• Manual flight deck temperature control
• Trim air
Note: Standby altimeter and
standby airspeed indicator
are pneumatically driven.
797-FD-0139R1C
1-19-2-whp/CF
Flight Controls
767-200ER/-300ER
• The primary flight controls are the ailerons, elevators,
and rudder. Flight controls are powered from the three
hydraulic systems. There is no manual reversion.
• Spoilers assist the ailerons in providing roll control
and, in addition, operate as speed brakes.
• A variable-pitch stabilizer assists the elevators in providing
pitch control. The stabilizer provides trim by varying the
horizontal stabilizer angle.
• High lift for takeoff and landing is provided by trailing edge
flaps and leading edge slats. The flaps and slats can also be
operated by an alternate electrical system.
Outboard aileron
Inboard
leading
edge slat
Inboard aileron
Rudder
Spoilers
Outboard
leading
edge slats
Elevator
Stabilizer
• Two independent yaw damper systems operate continuously
in flight to improve the airplane’s directional stability and turn
coordination.
Trailing edge flaps
• The EICAS status display of flight control surface positions
shows the amount of deflection.
L
C
R
HYD QTY 0.76 FULL 0.25
APU EGT 640
CABIN ALT AUTO1
CARGO FAN
OXY PRESS 1750
RUD
AIL
ELEV
AIL
EICAS status page
797-FD-0142C
1-19-2-whp/CF
Hydraulic Power
767-200ER/-300ER
Center
system
Left system
• The left and right hydraulic systems are
each powered by one primary engine-driven
pump and one electric demand pump.
• The center hydraulic system is normally
powered by two electric primary pumps and
one air-driven demand pump.
• The center system provides power for the
hydraulic motor generator during standby
electrical power operation.
• Each hydraulic system reservoir is equipped
with a low-quantity measuring system to
provide information to the EICAS status display
for quantity and refill indications.
• RAT (ram air turbine) provides hydraulic
pressure to center hydraulic system when
deployed.
Primary
pumps
Demand
pumps
Engine
pump
Electric
pump
Electric
pump
Right
system
Electric
pump
Electric
pump
Air-driv
pump
Valve
Tail
* skid
Flaps
and slats
HMG
Main gear
Left thrust
reverser
Engine
pump
Check
valve
Right thrust
reverser
Nose gear
Rudder ratio
PUMPS
HYD
L
R
R
C
1-ELEC-2
ENG
P
ENG
ON
ON
ON
ON
PRESS
PRESS
PRESS
PRESS
Alternate
brakes
Normal
brakes
OVHT
OVHT
OVHT
OVHT
Spoilers
Spoilers
I
M
Spoilers
A
Y
R
AIR
ELEC
PRESS
PRESS
PRESS
OVHT
OVHT
OVHT
Right inboard
aileron
Left inboard
aileron
Y
ELEC
D
Elevators
D
E
E
M
Rudder
Outboard
ailerons
Center
autopilot
servos
Right
autopilot
servos
M
AUTO
A
N
Elevator feel
Stabilizer trim
R
A
R
Nose wheel
steering
P
I
M
Yaw dampers
OFF
AUTO
ON
OFF
AUTO
ON
OFF
D
A
ON
N
D
Left
autopilot
servos
Hydraulic control panel
* 767-300ER models only.
RAT
pump
Hydraulic system diagram
797-FD-0144C
1-19-2-whp/CF
Ice and Rain Protection
Probe and Window Heat, Windshield Wipers
Probe heat
• Operation is fully automatic
Window heat
• Heat control is automatically
provided for both left and right
no. 1 and no. 2 windows
Windshield wipers
• Hydrophobic coating on windshield
Overhead panel
Window heat switch
• Signals window heat
controller to apply heat
to associated window
WINDOW HEAT
R
L
SIDE
FWD
SIDE
ON
ON
ON
ON
INOP
INOP
INOP
INOP
Window heat inoperative lights
• Associated window is not
being heated
Probe
locations
L
WIPER
OFF
INT
Pitot static probes (2 per side)
Angle of attack probe (1 per side)
Total air temperature probe
(left side only)
FWD
LOW
HIGH
R
OFF
INT
LOW
HIGH
Standard selections baseline is
dual three-speed (with intermittent)
wiper switches
Windshield wiper selector
OFF – Wipers turned off and
sequenced to the stowed
position
INT – Intermittent operation
LOW – Low-speed operation
HIGH – High-speed operation
797-FD-0145C
1-19-02-whp/DD
Wing and Engine Anti-Ice
767-200ER/-300ER
Wing anti-ice switch
• In-flight operation only
Overhead panel
WING
To right wing
anti-ice valve
ANTI-ICE
ENGINE
L
R
ON
Air/gnd
logic
R
L
VALVE
ON
ON
VALVE
VALVE
D
VALVE
Engine anti-ice switches
Pneumatic
manifold
T
P
Heated
slats
Temperature
sensor
Wing
anti-ice
valve
Cowl
anti-ice
Bleed air
manifold
PRV
LP
P
Wing thermal anti-ice
overpressure switch
T
Wing TAI overheat switch
HP
797-FD-0146C
1-19-02-whp/DD
Wheel Braking System
767-200ER/-300ER
• Normal braking is powered for all main
wheels by the right hydraulic system.
• Alternate braking is powered by the center
hydraulic system.
• A single brake pressure accumulator is
charged from the center hydraulic system.
PARK
BRAKE
P
A
R
K
• An antiskid system is provided to all main
wheel brakes for skid protection, locked wheel,
hydroplane, and touchdown protection.
AUTO
BRAKES
B
R
A
K
E
AUTO BRAKES
2
3
1
a
4
DISARM
MAX
AUTO
OFF
RTO
• An autobrake system permits automatic
braking at preselected deceleration rates
following touchdown.
• An RTO (rejected takeoff) feature applies
maximum braking if both thrust levers are
retarded to idle above 85 knots during takeoff roll.
Altn
brake
press
Accumulator
isolation valve
BRAKE
4
PRESS
PSI
Park
brake
valve
X 1000
3
0
2
Hydraulic
system
1
Metering
valve
Accumulator
Antiskid
valves
Auto brake
valve
Antiskid
return
Metering
valve
Antiskid
valves
Antiskid
controller
Antiskid
797-FD-0147C
1-19-02-whp/DD
Landing Gear
767-200ER/-300ER
• The 767 has two main gear and steerable
nose gear
D
O
O
R
Sa
• Landing gear actuation is powered by the
center hydraulic system
TAIL
SKID
a
NOSE
g
a
RIGHT
LEFT
g
• A tailskid is installed on 767-300ER airplanes
G
E
A
R
UP
OFF
g
RETRACT
270K
EXTEND OR
EXTENDED
270K-.82M
LOCK
OVRD
DN
Landing gear level
UP – Releases downlocks
– Pressurizes upside of gear actuator
OFF – Depressurizes landing gear
hydraulic system
DN – Releases uplocks
– Pressurizes downside of gear
actuator
Tailskid light (amber)
(767-300ER airplanes)
• Tailskid disagrees with
lever position
Landing lock override switch
Push – Manually releases
lever lock
ALTN GEAR
EXTEND
250K-.75M
OFF
DN
Alternate gear extension switch
(toggle, guarded)
OFF – Resets alternate gear
extension system
DN – Releases all gear
uplocks
797-FD-0148C
1-19-02-whp/DD
Nose Wheel Steering
767-200ER/-300ER
• Nose wheel steering is powered by the center
hydraulic system
• Steering is controlled primarily through the
left-hand tiller wheel
• Rudder pedals provide up to 6˚ of steering control
Minimum turning radius
Tiller steering
angle 65˚
Minimum width of
pavement for 180˚ turn is
129.0 ft (39.32 m) -200 series
146.0 ft (44.50 m) -300 series
Center of turn for
minimum turning radius
(slow continuous turn,
no differential braking)
,
Captain s
sidewall
Nose wheel steering tiller
• Turns nose wheel up to
65˚ in desired direction
• Overrides rudder pedal
steering
Nose wheel indicator
shows direction and
angle of nose wheel
steering signal
797-FD-0149C
1-19-02-whp/DD
Air Data System
767-200ER/-300ER
Flush static
ports (2)
Pitot static probes (4)
Captain’s
auxiliary pitot
First
Officer’s
main pitot
R-AOA
Right
ADC
RAT arm
pressure
switch
Standby
altimeter
Elevator
feel
computer
Standby
airspeed
indicator
Left
ADC
Captain’s
main
pitot
•
•
•
•
Differential
pressure
sensor
TAT L-AOA
First
Officer’s
auxiliary
pitot
Dual ARINC 706 digital air data computers
Independent standby instruments
Auto probe heat
Dual-level pitot static probe heat
• Dual angle-of-attack (AOA) vanes
• Aspirated TAT probe provides certified
TAT for takeoff thrust computations
• TAT display on EICAS
• TAS and SAT available in FMC MCDU
797-FD-0150 C
1-19-02-whp/DD
Flight Crew Oxygen
767-200ER/-300ER
Flow indicator
• Shows a yellow cross
when oxygen is flowing
Release levers
Squeeze and pull
• Releases mask
from stowage box
• Oxygen turns on and
mask harness inflates
RESET
PUSH
Stowed oxygen
mask regulator
(crewmember station)
100%
PUSH
OXYGEN
BASE
HYD QTY
L
0.76
APU EGT
640
OXY PRESS
1750
C
R
1.00 0.25 RF
Oxygen pressure
• Pressure at the
crew oxygen
cylinder
CABIN ALT AUTO 1
CARGO FAN
RUD
AIL
Reset/test slide lever
Push
• Mask stowed, turns
oxygen on momentarily
to test regulator
ELEV
AIL
EICAS status display
center panel
Normal/100% selector
Normal
• Air/oxygen mixture on demand
• Ratio is dependent on cabin
altitude
100%
• Pushing selector supplies pure
oxygen on demand
Harness
(shown inflated)
N
Mask
100%
PUSH
EMERGENCY
Microphone
Regulator
PRESS
TO
TEST
Emergency/test selector
• 100% oxygen is supplied
under positive pressure
at all cabin altitudes
797-FD-0151 C
1-19-02-whp/DD
Flight Deck and Emergency Lighting
767-200ER/-300ER
Panel light control
• Regulates the brightness of the
internal lighting in the Captain’s
and center panels and standby
magnetic compass
Chart light control
• Regulates the brightness of the Captain’s
and First Officer’s chart light
CLOCK
PANEL
Map light control
• Regulates the brightness of the Captain’s
and First Officer’s map light
OFF
Floodlight control
• Regulates the brightness of the
floodlighting in the Captain’s,
center, and First Officer’s panels
CHART
FLOOD
OFF
MAP
PTT
Emergency lights switch (guarded)
OFF
– Prevents activation of emergency
lighting system when electrical
power fails or is turned off
ARMED – All interior and exterior emergency
lights illuminated automatically if
dc power fails or is turned off
ON
– All emergency lights illuminate
Lights override switch
(alternate action)
ON
– Turns on the following
lights to full brightness:
Captain’s, center, and
First Officer’s main
panel floodlights, forward
and aft dome lights, and
aislestand floodlight
Emergency lights switch
unarmed light (amber)
EMER LIGHTS
OFF
ARMED
UNARMED
ON
PASS SIGNS
NO SMOKING
SEAT BELTS
AUTO
AUTO
OFF
ON
OFF
ON
LT OVRD
ON
No smoking/seat belt selector
OFF – Turns off the associated passenger signs
AUTO – Selects automatic control of the
associated passenger signs
• NO SMOKING signs on when landing
gear is down
• SEAT BELT signs on when landing
gear is down or flaps are not up
ON
– Turns on the associated passenger signs
797-FD-0152 C
1-19-02-DD/DD
Exterior Lighting
767-200ER/-300ER
Right position lights
(green and white)
Taxi runway
turnoff lights
(left and right)
Landing lights
(left, right,
and nose)
Logo
lights
(white)
LOGO
ON
RUNWAY TURNOFF
L
OFF
R
Logo light
switch
ON
Runway turnoff
light switch
Red and white anticollision light
switch (alternate action)
ON – Turns on the corresponding
red or white strobe lights
Position light switch
(alternate action)
ON – Turns on the red, green,
and white position lights
Wing landing light switch
(alternate action)
ON – Turns on the corresponding left
or right wing landing light
– Light intensity is at maximum only
when the landing gear lever is down
Taxi lights
(optional)
Upper anticollision
light (red strobe)
Wing illumination
lights
Lower
anticollision
(red strobe)
Left position lights
(red and white)
Anticollision lights
(left and right)
(white strobe)
ANTI
COLLISION
RED
WHITE
POSITION
ON
ON
WING
ON
ON
Wing light switch (alternate action)
ON – Turns on the wing leading edge lights
– Light intensity is at maximum only when
the landing gear lever is down
LANDING
WING
L
NOSE GEAR
R
OFF
OFF
ON
ON
Nose gear landing light switch
ON – Turns on the two nose gear landing lights
– Inhibited if nose landing gear is retracted
797-FD-0153C
1-19-02-whp/DD
767 Flight Deck and Avionics - Options
767 Options
767-200ER/-300ER
1
Electronic Flight Instrument System
2
Engine Indication and Crew Alerting System
3
Autoflight Systems
4
Flight Management Computer System
5
Communications
6
Navigation System
7
Crew Accommodations
8
Airframe Systems
797-FD-0154 C
2-25-02-PW-whp
Options 1 —Electronic Flight Instrument System
767-200ER/-300ER
EADI
Feature
Flight Mode Annunciation (FMA)
Airspeed Tape
Flight Director Command
Display and Airplane Symbol
Basic
Bottom of EADI
Fast/Slow Indicator
Split Axis
Option
Top of EADI
Airspeed Tape with Rolling Digits and Trend Vector
(Contingent on Top FMA)
Airspeed Tape with Hollow Cursor and Trend Vector
(Contingent on Top FMA)
Filled Integrated CueHollow Integrated Cue
Radio Altitude Display
Digital Display
Digital and Round Dial Display
Rising Runway Display
None
Provided on EADI
Radio Altitude Height Alert
None
Shown at 1000 feet
Shown at 1500 feet
Shown at 2500 feet
ILS Deviation Alert
None
Provided on EADI
EHSI
Feature
Map Mode Orientation
Range Arcs
True Airspeed and Ground
Speed display
Wind Bearing Digital Display
Basic
Option
Track Up
Heading Up
Range Marks
Range Arcs
Ground Speed on EADI only
Wind Speed and
Direction displayed
Ground Speed on EADI and
EHSI. True Airspeed on EHSI
Wind Speed, Direction,
and Bearing displayed
ADF Pointers
None
Provided on EHSI
TCAS 3nm Range Ring
None
Provided on EHSI
797-FD-0211C
2-25-2-whp
Options 1 —Electronic Flight Instrument System
767-200ER/-300ER
Electronic Attitude Director Indicator (EADI)
Flight mode
annunciation
on top of ADI
Airspeed
tape
GS138
SPD
A/T
DH150
20
LOC
ROLLOUT
20
20
10
10
10
10
20
20
CMD
200
20
F
10
G/S
FLARE
Integrated
cue flight
director
160
10
132
120
10
S
10
100
A/T
SPD
FLARE
G/S
20
20
CMD
ROLLOUT
LNAV
ALT
GS
138
200
Radio altitude
height alert
1,000, 1,500,
or 2,500 ft RA
Rising
runway
Rolling digits and
trend vector
Basic EADI
ILS deviation
warning
Round dial
radio altitude
Optional EADI features
797-FD-0155 C
2-26-2-whp/CF
Options 1 —Electronic Flight Instrument System
767-200ER/-300ER
Electronic Horizontal Situation Indicator (EHSI)
True airspeed
and ground speed
27.5 NM
TRK 142 M
27.5 NM
0835.4 Z8
WX+T
+12
TAS 270
GS 298
HDG 127
M
12
15
12
ADF pointers
DIDES
Heading up
9
0835.4 Z
WX+T
+12
15
DIDES
CAMP
CAMP
20
20
BUGLE
BUGLE
Range arcs
Note: Range arcs
are visible full time
in map mode and
when weather, TCAS,
or terrain is displayed
in expanded VOR/APP
mode.
20
115˚ /20
Digital wind bearing
Basic EHSI map mode
Optional EHSI map mode features
El797-FD-0156C
2-26-2-whp
Options 2 —EICAS
767-200ER/-300ER
Feature
Engine Fuel Flow Display
APU Oil Quantity Display
Generator Off and Engine
Oil Pressure EICAS Messages
ECS Parameters
Basic
Display when Secondary
Engine page is selected
Low APU Oil Quantity message
on Maintenance page
Advisory Level
Basic ECS Parameters on
Maintenance page
Option
Full Time Display
APU Oil Quantity Level on Status
and Maintenance page
Caution Level
Basic and Additional ECS Parameters
on Maintenance page
Hydraulic Pressure
Display on
Maintenance page
Display on Status and
Maintenance pages
APU RPM
Display on
Maintenance page
Display on Status and
Maintenance pages
Bulk Cargo Compartment
Temperature
None
Display on Maintenance and
Status page
Ram Air Door Outlet Position
None
Display on Maintenance Page
Display on Maintenance page
for GE and RR engines
Display on Maintenance page
for PW engines
Engine Fuel Pressure
EICAS Maintenance Pages
Available during flight
Available above 10,000 feet
Not Available during flight
ECS Precooler Outlet Temperature
None
Display on Maintenance page
Brake Temperature Display
None
Display on Status page
Tire Pressure Display
None
Display on Status page
Caution and Warning Options
Feature
Autopilot Disengage Warning
Firebell Aural Warning
Overspeed Aural Warning
Basic
Aural Warning Siren - Aural Inhibited when
Autopilot Disconnect Switch double pushed
Option
Aural Warning Wailer - Aural activated
for one second when Autopilot Disconnect
Switch double pushed
1 second on, 9 seconds off
2 seconds on, 3 seconds off
Resettable Warning Siren
Non-resettable Warning Siren
797-FD-0212C
2-25-2-whp
Options 2 —EICAS
767-200ER/-300ER
Caution level messages
• Generator off
• Engine oil pressure
TAT
L GEN OFF
R GEN OFF
L ENG OIL PRESS
R ENG OIL PRESS
(Default selection shows
these messages as
advisory level)
-12o C
1.50
2.0
1.50
CRZ
2.0
1.28
1.0
1.28
1.0
1.5
1.5
EPR
54.2
54.2
Metric engine
parameters
• Fuel flow (FF) shows in
kilograms per hour
• Oil quantity shows in
liters
N1
428
428
EGT
95
70
PRESS
105
105
OIL
TEMP
OIL
3.1
95
70
OIL
18
Note: This is part of a
broader option
to show all
instrumentation
with metric units.
N2
11.3
Full-time display of fuel flow
11.3
18
QTY
FF
0.9
(Default selection shows
this only when secondary
engine display is selected)
Primary and secondary displays
797-FD-0157C
1-18-02-CF/DD
Options 2 —EICAS
767-200ER/-300ER
Hydraulic
pressure
indication
L
HYD QTY
HYD PRESS
APU
EGT
R
OIL
12.4 FF 15.3
0.25RF
2140
CABIN ALT AUTO 1
CARGO FAN
Q 0.75
1750
OXY PRESS
APU oil quantity
level indication
RUD
AIL
ELEV
Full-time fuel
flow
26
BULK CARGO TEMP
Bulk cargo
compartment
temperature
indication
C
0.76
1.29
3230
3210
640 RPM 103
AIL
160
160
160
2 3
50
160
4 5
160
160
5 1
160
160
2 3
160
APU RPM
indication
BRAKE TEMP / TIRE PRESS
Brake temperature indications
Tire pressure indications
Status page
797-FD-0158C
1-19-02-MT/DD
Options 2 —EICAS
767-200ER/-300ER
ECS/MSG maintenance page
PERF/APU maintenance page
PERF/APU
ECS/MSG
L
PACK OUT
TURB IN
SEC HX OUT
COMPR OUT
Additional
ECS
parameters
PRIM HX OUT
PRIM HX IN
PRECOOL OUT
DUCT PRESS
PACK FLOW
TEMP VALVE
RAM IN DOOR
RAM OUT DOOR
Ram air
outlet door
position
FLT DK
DUCT TEMP
TRIM VALVE
30
0.75
2
9
1
96
44
171
193
40
0
0.75
0.62
0.73
3
10
3
98
46
173
196
42
0
0.80
0.71
0.72
FWD
28
0.80
R
FWD EQ FAN 1
CAS
ZONE TEMP BITE
MACH
95
130
12
OIL QTY
0.7
0.5
95
130
12
0.3
0.9
N1
N2
MID
17
0.00
AUX MID
17
0.00
25
AFT
17
0.00
EGT
640
RPM
100
0.25
OIL Q
TAT
ALT
1.523
EPR
ACT
EPR
ACT
104.0
N1
1.284
54.2
1.013
APU:
BULK CARGO TEMP
187.6
245
0.015
60.4
AFT CABIN TEMP
ECS precooler
outlet temperature
OIL TEMP
VIB
AUX FWD
28
0.80
OIL PRESS
GROSS WT
86
EGT
+15
21030
0.902
1.001
104.0
21.3
N2
82.5
FF
1.010
FP
N1 RED
EGT RED
84
APU OIL QTY
Bulk cargo
compartment
temperature
APU oil quantity level
Interstage fuel pump
pressure (basic with
General Electric and
Rolls-Royce engines)
797-FD-0159 C
1-19-02-MT/DD
Options 3 —Autoflight Systems
767-200ER/-300ER
Feature
Glideslope Capture
Mach Display on Mode
Control Panel (MCP)
Basic
Inhibit Glideslope Capture
prior to Localizer Capture
Two-digit Mach display
Autopilot Triple-Channel
Selection in Approach Mode
Automatic
Autopilot Command Engage
Default Roll Mode
Heading Hold
Flight Director
Mode Control Panel (MCP)
Fixed Derates
Climb Fixed Derate Washout
FCC Software Loading Capability
Part Time Display (Flight Director
display inhibited whenautopilot
and flight director are referenced to
the same FCC)
757/767 Baseline MCP
Climb Fixed Derates
10,000 feet to 12,000 feet
On-board Software Loadable
Option
Enable Glideslope Capture prior to
Localizer Capture
Three-digit Mach display
Manual
Bank Angle Hold
Full Time Display (Flight Director always
displays when selected)
757/767 Baseline MCP without Backcourse
Switch747-400 MCP
Takeoff and Climb Fixed Derates
10,000 feet to 30,000 feet
Not Software Loadable
797-FD-0213C
2-25-2-whp
Options 3 —Autoflight Systems
767-200ER/-300ER
747-400 mode control panel
Knob shape modified
to provide tactile difference
from heading and altitude knobs
A/T ARM
VERT SPD
HDG
IAS/MACH
F/D
ON
L NAV
2 0 0
1 2 6
1
Backcourse mode deleted
A/P ENGAGE
ALT
7 0 0 0
1 7 0 0 0
L
C
R
CMD
CMD
CMD
F/D
ON
OFF
SEL
V NAV
THR
OFF
5
NORM
FL CH
SPD
SEL
25
BANK
LIMIT
LOC
DN
V/S
HOLD
HOLD
OFF
APP
DISENGAGE
UP
All pushbutton
switches modified
to provide positive
tactile feel
Changed EPR or N1
nomenclature to THR
(provides commonality with
all engine types)
Added push action switch
to altitude select knob
(provides VNAV altitude
intervention capability)
757 and 767 mode control panel options
Three-digit Mach display
A/T ARM
F/D
ON
.8 0 5
VERT SPD
HDG
IAS/MACH
L NAV
Backcourse mode deleted
2 7 0
1
A/P ENGAGE
ALT
7 0 0 0
1 7 0 0 0
L
C
R
CMD
CMD
CMD
F/D
ON
OFF
SEL
EPR
V NAV
OFF
5
NORM
SPD
FL CH
Full-time flight director:
Command bars stay in view
when same A/P is selected
SEL
25
BANK
LIMIT
LOC
DN
V/S
HOLD
HOLD
APP
OFF
DISENGAGE
UP
Bank angle hold on A/P or F/D
engagement if bank between
5 and 30
Individual channel
selection in
approach mode
797-FD-0160C
1-19-02-whp/DD
Options 4 —Flight Management Computer System
767-200ER/-300ER
Feature
Runway Position Shift Units
Flight Crew Alertness Monitor
Navigation Database
Basic
Feet
Inhibited
Boeing Supplied
Option
Meters
Enabled
Customer Supplied
Offpath Descent Circles & DME Range Rings
Inhibited
Displayed
Altitude Intervention
Inhibited
Enabled (Contingent on
selecting 747-400 MCP)
Airline Modifiable Information (AMI)
Boeing Supplied
Customer Supplied
Required Time of Arrival (RTA)
Inhibited
Enabled
Air Traffic Services Datalink (ATS DL)
Inhibited
Enabled (Contingent on
selecting Datalink capability)
Airline Operational Communciations
Datalink (AOC DL)
Inhibited
Enabled (Contingent on
selecting Datalink capability)
Takeoff Datalink
Inhibited
Enabled (Contingent on
selecting AOC DL)
FMC Printer Interface
Inhibited
Enabled (Contingent on
selecting a printer)
ADF Approaches
Inhibited
Enabled
GPS Approaches
Inhibited
Enabled
Display of Vertical Bearing, Flight
Path Angle, and Vertical Speed
Inhibited
Enabled
797-FD-0214C
2-25-2-whp
Options 4 —Flight Management Computer System
767-200ER/-300ER
Future Air Navigation System (FANS)
FANS is an International Civil Aviation
Organization (ICAO) concept of a phased
approach to Communication Navigation
Surveillance/Air Traffic Management
(CNS/ATM) implementation.
FANS 1 allows:
• Reduced separations
• More timely altitude change authorizations
• Flexible routine operations
• Dispatch on required navigation
performance (RNP) only routes
• Efficient crossing track operations
EICAS messages
DATALINK LOST
UNABLE RNP
FMC MESSAGE
ATC
MCDU pages
ATC LOGON
RTE PROGRESS
ATC INDEX
POS REF
The Pegasus FMC is FANS 1 capable.
Global positioning system (GPS) and
required navigation performance (RNP)
are basic features.
These options are required to enable
FANS operation:
• Air traffic services data link (ATS DL).
This option also provides automatic
dependent surveillance (ADS)
• ACARS or VDL mode 2/AOA data link
• SATCOM, if FANS operations are
desired outside of VHF data link range
These options are available, but not
required for FANS operations:
• Required time of arrival (RTA)
• FMC printer interface
ACT ECON CRZ
ACT RTE LEGS
ATC REQUEST
ATC REPORT
ATC LOG
Printer
EMERGENCY
Communication
management units
FMCs
VHF
receiver
GPS
(MMR)
receivers
SATCOM
receiver
Air traffic control
797-FD-0166C
1-21-2-whp/cf
Options 4 —Flight Management Computer System
767-200ER/-300ER
Crew Alertness Monitor
Master
caution/warning
EICAS message
Pilot response
Monitors time since last pilot button-push
• Mode control panel
• EFIS control panels
• EICAS control panel
• MCDUs
• VHF/HF microphone push-to-talk
• VOR control panel
Typical Implementation
TIME
ALERT
- - - - - - - - - - - - Cruise - - - - - - - - - - - 15 min
EICAS advisory
20 min
EICAS caution
EICAS warning
25 min
- - - - - - - - - - - Descent- - - - - - - - - - - 5 min
EICAS advisory
6 min
EICAS caution
EICAS warning
7 min
Airline defines criteria in policy file
• Entire feature selectable on or off
• EICAS alerting levels selectable on or off
• Timing criteria selectable within predefined limits
• Requires option for customer supplied Airline
Modifiable Information (AMI)
797-FD-0163C
1-19-2-whp/CF
Options 4 —Flight Management Computer System
767-200ER/-300ER
Required Time of Arrival (RTA)
• RTA provides the capability to specify a required
time of arrival for an existing flight plan fix
Santa Monica (SMO)
RTA 1307.5Z
FMC computes RTA speed
Airplane maintains RTA speed
Airplane arrives at SMO 1307.5Z
• RTA computed for CRZ segment
• CLB and DES are ECON
• 앐 30 seconds accuracy
RTA fix
• Any waypoint in active
flight plan
FIX
RTA PROGRESS
3 /3
RTA
.
AL T / E T A
FL- - - /- - - . - z
T/O
---- .-Z
Maximum speed
• Defaults to MMO minus 0.02
• Crew can enter a maximum
speed if desired
MAX S P D
. 840
Takeoff
• Initially displays dashes
• Displays recommended takeoff
time following entry of RTA time
• If no RTA fix or time is entered,
expected takeoff time can be
entered and all trip predictions will
be based on entered takeoff time
- - - - - - - - - - - - - - - - - - - -
797-FD-0164C
1-19-2-whp/CF
Options 4 —Flight Management Computer System
767-200ER/-300ER
ACARS Interface
Options can be selected for
• Airline operations communication data link (AOC DL)
• Air traffic services data link (ATS DL)
• Takeoff data link
• Contingent on installation of ACARS MU/CMU system
MENU
C
ARS
MENU
FMCS/ACARS data link
• Access ACARS menu through FMC
(MCDU) or multipurpose interactive display unit (MIDU)
• Provides adequate message flexibility
while minimizing communication load
• Mode S function compatibility
• SATCOM compatibility
• Requires MCDU or MIDU and ACARS or VDL mode 2
• Provisions for ACARS or VDL mode 2 offered that
would provide for future implementation of ACARS
or VDL mode 2
• Partial provisions offered for future upgrade from
ARINC 724B ACARS to ARINC 758 communication
management units (CMU)
• Voice mode protection available to allow
center VHF system to be used for both voice
and data transmission
MS
DEP
RTE
LEGS
NAV
RAD
NEXT
PAGE
F
I
J
3
K
N
O
6
P
S
T
M
S
G
O
F
S
T
9
Multifunction CDU (MCDU)
Airplane
Confirmation
(FPR)
Flight
plan
request
(FPR)
Route mod
Flight
plan
(FPR)
Confirmation
(ATC)
Route
clearance
(ATC)
Airline
dispatch
office
ATC
center
797-FD-0161C
1-19-2-whp/CF
Options 4 —Flight Management Computer System
767-200ER/-300ER
ATS Data Link
• Air traffic services data link (ATS DL) is an optional feature of the Pegasus FMC. ATS DL is contingent on
selection of VDL mode 2/AOA or ACARS data link.
• The ATS DL combines the functions of ATS facilities notification (AFN), automatic dependent
surveillance (ADS), and air traffic control data link (ATC DL). The AFN notifies air traffic control that
the airplane is equipped and ready to receive data link communications. ADS allows for automatic
reporting of aircraft position and intent data. The ADS is capable of simultaneously reporting to four
ATC facilities and one airline facility. The capability to disable ADS through the multifunction
control display unit (MCDU) is provided.
• The ATC DL allows two-way text messages to be sent between pilot and controller. The messages
are received and created using the MCDU. The capability to store and recall messages and to load
rate information into the flight plan is provided.
ATC LOGON/STATUS
ATC INDEX
L O G O N TO
<EMERGENCY
POS REPORT>
FL T
<REQUEST
N O
WHEN CAN WE>
BOE001
FREE TEXT>
N757BB
T AI L
<REPORT
A C T C TR
N O
KOAK
A T C C O M M
<LOG
CLEARANCE>
N EX T C TR
<SELECT OFF
A D S ( A C T)
<LOGON / STATUS
AD S
< O F F < > ARM
VOICE>
EM E R
O FF <
>
ON
DA TA LINK
<ATC INDEX
<PRINT LOG
INIT
REF
RTE
CLB
CRZ
DES
BRT
INIT
REF
RTE
READY
CLB
CRZ
DES
BRT
797-FD-0167C
1-19-2-MT-CF
Options 4 —Flight Management Computer System
767-200ER/-300ER
Airline Operational Communications Data Link (AOC DL)
FMC COMM
< RTE 1
POS REPORT >
< ALTN
< PERF
< TAKEOFF
< WIND
DATA LINK
< DES FORECAST
READY
INIT
REF
RTE
CRZ
CLB
• AOC data link is an optional feature
of the Pegasus FMC. AOC data link
is contingent on selection of VDL
mode 2 or ACARS data link.
BRT
DES
• This feature provides data link
communication of performance,
takeoff route, waypoint winds,
reporting waypoints, descent
forecasts, route modifications,
and alternate airport information
directly into the FMC.
PERF INIT UPLINK
< REJECT
ACCEPT >
< INDEX
POS INIT >
PERF INIT UPLINK
ALTN UPLINK
< REJECT
ACCEPT >
ALTN UPLINK
INIT
REF
RTE
CLB
CRZ
DES
BRT
797-FD-0168C
1-19-2-whp/CF
Options 4 —Flight Management Computer System
767-200ER/-300ER
Takeoff Data Link
• FMCS takeoff data link (shown below) is a separate
option contingent on selection of AOC DL. This
feature allows uplinks of takeoff data to the FMC.
TAKEOFF REF UPLINK 1/2
TAKEOFF REF UPLINK 1/2
V1
V1
134
134
VR
VR
140
140
V2
V2
147
GRWT
197.2
147
TOGW
GRWT
198.6
197.2
TAKEOFF DATA
< REJECT
ACCEPT >
< INDEX
POS INIT >
TAKEOFF DATA UPLINK
TOGW
198.6
TAKEOFF DATA
< REJECT
ACCEPT >
< INDEX
POS INIT >
TAKEOFF DATA LOADED
INIT
REF
RTE
CLB
CRZ
DES
BRT
797-FD-0168 R1C
1-19-2-whp/CF
Options 4 —Flight Management Computer System
767-200ER/-300ER
Printer Interface
• Provides for the printing of the FMC
flight plan and ATC data link messages
------ CURRENT AIRCRAFT DATA --------LAST POS: YKM
ATA AT LAST POS: 1328Z
FUEL AT LAST POS: 131.7
FMC LAT/LON: N4700.0W12516.4
NAV SOURCE: INERTIAL
RNP/ACTUAL: 2.0/0.4
FLT PHASE: CRZ
ALT: 21100
TAS: 405KT
GS: 425KT
WIND: 270T/14KT
OAT: -38C
CURRENT FUEL: 128.7
ORIGIN/ATD: KBFI/1300Z
DEST/ETA: KMWH/1610Z
CO ROUTE: BFIMWH
CRZ ALT: FL210
ZFW: 300.0
RESERVES: 25.0
CRZ CG: 30.0%
COST INDEX: 90
------------- ACT RTE 1 -------------VIA/TO
SPD/ALT
ETA/FUEL
-------------------------------------LACRE3.VAMPS
080
1199NM
1320Z/141.3
VAM01
250/FL270AFL290B
V2
070
30NM
1325Z/140.3
ELN
(305)/(FL210)
DIRECT
120
40NM
1330Z/139.3
----------- ENTERED WINDS -----------FIX
ALT
DIR/SPD
ALT/OAT
-------------------------------------VAM01
FL270 240/130
FL210/-44C
FL250 240/120
FL230 230/ 80
FL210 220/ 30
---------- DESCENT FORECAST ---------ALT
WIND DIR/SPD
FL210
180/ 30KT
17000
170/ 20KT
13000
150/ 10KT
9000
120/ 5KT
• Option available for
FMC printer interface
• FMC prints uplinked
and downlinked ATC messages
<PRINT
Prints entire flight plan
• FMC interfaces with an
ARINC 740, 744 or 744A printer
1/3
A CT R TE 1
OR IGIN
DEST
K MW H
K B FI
FLT NO
RUN WA Y
R W 13R
AB 345
CO ROUTE
REQUEST
<SEN D
B F IM W H
REPORT
<SEN D
ROUTE
< P R IN T
R TE C O PY>
- - - - - - - - - - - - A L TN >
OFFSE T
- - -
< IN D E X
INIT
REF
RTE
CLB
CRZ
DES
BRT
---------- RTA FIX/TIME -------------YKM/1329.1Z
--------- ALTERNATE AIRPORTS --------KRNT
1335Z
132.2
KSEA <SEL> 1333Z
130.2
KPDX
1334Z
131.2
KPWT
1336Z
133.2
797-FD-0169C
1-19-2-whp/CF
Options 4 —Flight Management Computer System
767-200ER/-300ER
GPS and NDB Approaches
• Option available for selection of
FMC nondirectional radio beacon
(ADF) approaches in the NAV
database
• Separate option available
for selection of FMC GPS
“nonprecision” approaches
in the NAV database
KBLI ARRIVALS
S TA R S
<SEL> GPS34
ILS16
NDB16
R UNW AYS
16
<INDEX
RTE
TUBTY INTC>
CLB
CRZ
DES
BRT
APPRO A C H E S
TUBTY
170 / 3100
345 ˚
5 NM
170 / 2200
G P 3.00˚
OHADO
345 ˚
5 NM
RW34
155 / 0050
<RTE 2 LEGS
RTE DATA>
INIT
REF
NDB and GPS
approaches
are selected
on arrivals
page on MCDU
GPS16
1/1
5 NM
345 ˚
A P P R OACHES
- NONE -
INIT
REF
ACT RTE 1 LEGS
1/2
RTE
CLB
CRZ
DES
GPS final approach and any
approach with a specified vertical
angle (on which the VNAV approach
path is based) results in display
of angle on RTE LEGS page
BRT
797-FD-0171 C
1-19-2-MT/CF
Options 4 —Flight Management Computer System
767-200ER/-300ER
Flight Path Angle—Vertical Bearing—Vertical Speed
3 / 3
AC T D E S
E / D
A T
AT
E C O N
N OLLA
2200A
2200 RW13R
• Flight path angle
• Actual
S P D
• Vertical bearing
320
SP D T R A N S
W P T / A L T
NOLL A / 2200
240 / 10000
FPA
SP D REST R
V / B
V / S
2.9
3.1
1754
- --/- - - - - - - - - - - - - - - - - - - - - - - < OFFPATH
DES
FORECAST>
DES DIR>
• To waypoint and
altitude in 3R
• Vertical speed
• Required to maintain
vertical bearing
797-FD-0162C
1-19-2-PW/CF
Options 5 —Communications
767-200ER/-300ER
Feature
Basic
Option
HF Data Link
None
Installation and Activation of HF
Data LinkPartial Provisions
8.33 kHz VHF Channel
None
Activation
Spacing
Partial Provisions
SATCOM
None
SATCOM System Installation
Partial Provisions
ACARS/Data Link
None
VDL Mode 2/AOA Installation Level
0A CMU InstallationARINC 724B ACARS
InstallationPartial Provisions
Voice Mode Protection
None
Provided
Emergency Locator Transmitter (ELT)
None
ELT InstallationPartial Provisions
Pilots Call Panel
PA-in-Use Light not included
PA-in-Use Light included
Boom Microphone Headset Jacks
Two Pin Jacks
Five Pin Jacks
Push to Talk Switch on Glareshield
None
Provided
Cockpit Voice Recorder Monitor Jack
None
Provided
797-FD-0215C
2-25-2-whp
Options 5 —Communications
767-200ER/-300ER
Satellite Communications (SATCOM)
• Options available for SATCOM system, or partial provisions for SATCOM
• SATCOM provides two-way voice/data communication for the flight crew and cabin passengers anywhere in the
world covered by INMARSAT global/spot beam
• The services include
• Flight deck voice, allowing instantaneous communication with Operations, Maintenance and Air Traffic Control
• Flight deck data link data communication
• 64 kbps circuit mode PC data communication planned for future with AERO-H+ system
• A SATCOM installation consists of the following equipment
• Avionics equipment
— Satellite data unit (SDU)
— Radio frequency unit (RFU) – not required on all SATCOM systems
— High power amplifier (HPA)
• Antenna systems – customers can select either an AERO-H+ or AERO-I system
— High-gain antenna (HGA) – AERO-H+ system
— Intermediate-gain antenna (IGA) – AERO-I system
• Pilot interface
— Multipurpose control and display unit (MCDU) – basic feature – no option required
— Audio control panel (ACP) – basic feature
— EICAS (communication messages) – basic features – no option required
797-FD-0033
1-19-02-PW/DD
Options 5 —Communications
767-200ER/-300ER
Satellite Communications (SATCOM)
INMARSAT 3
L-band
digital link
1.5/1.6 GHz
RF C-band
4/6 GHz
Airborne earth
station (AES)
Ground earth
station (GES)
• PSTN - Publish switched
telephone network
• PSTDN - Publish switched
telephone data network
• Private networks
• Aeronautical fixed network
(AFTN, CIDN, SITA, ATN)
Airline operational control (AOC)
or air traffic control (ATC)
Service
provider
network
797-FD-0034
1-19-02-whp/DD
Options 5 —Communications
767-200ER/-300ER
Data Link
• Data link provides a high-speed digital data transmission between the airplane and ground facilities. By
transmitting and receiving data automatically, without the flight crew intervening, data link reduces flight crew
workload. Pilots use the MCDU or an optional MIDU to interface with the data link system. Data link is used to
exchange airline operations information and airplane operating data.
• Options are available for installation of a flight deck printer.
• Options are available for airline operational control data link (AOC DL) and air traffic services data link (ATS DL).
See FMC system options 4 for further information on these optional features.
• Three levels of data link provisions/installations are available: ARINC 724B ACARS, ARINC 758 level 0A, and
ARINC 758 VDL mode 2/AOA.
ARINC 724B ACARS
• ARINC 724B aircraft communications addressing and reporting system (ACARS) transmits character-oriented
data at 2.4 kbits/second. The modem, converting data to/from VHF sound transmission, is contained in the
ACARS management unit.
• The following options are required for ARINC 724B ACARS operations:
• Partial provisions for a single ARINC 724B ACARS management unit.
• Installation of an ARINC 724B ACARS management unit into partial provisions.
797-FD-0035C
1-19-02-PW/DD
Options 5 —Communications
767-200ER/-300ER
Data Link
ARINC 758 level 0A data link
• Level 0A data link transmits character-oriented data at 2.4 kbits/second. The modem is contained in the
communications management unit (CMU).
• The following options are required for level 0A data link operation.
• Partial provisions for a single ARINC 724B ACARS management unit
• Limited partial provisions for dual ARINC 758 CMUs compatible with existing single ARINC 724B ACARS
provisions
• Installation of an ARINC 758 CMU into partial provisions
ARINC 758 VDL mode 2/AOA data link
• VDL mode 2/AOA (VHF data link mode 2/aircraft communications addressing and reporting system over
aviation VHF link control) transmits high-speed character-oriented data at 31.5 kbits/second to suitably
equipped ground stations. VDL model 2/AOA transmits character-oriented data at 2.4 kbits/second to ground
stations not equipped for VDL mode 2/AOA high-speed data. The modem is contained in the VHF data radio
transceivers (VDR).
• The following options are required for VDL mode 2/AOA operation.
• Partial provisions for a single ARINC 758 CMU. Partial provisions are also available for dual ARINC 758
CMUs to provide a possible future installation of a second CMU
• Installation of an ARINC 758 CMU into partial provisions
• Installation of ARINC 716/750 capable VHF data radio (VDR) transceivers
797-FD-0036C
1-19-02-PW/DD
Options 5 —Communications
767-200ER/-300ER - Data Link Installations
ARINC 724B ACARS with dual
ARINC 758 CMU provisions
Level 0A data link with single ARINC 724B, ACARS MU
provisions, and dual ARINC 758 CMU provisions
CMU
ACARS
Left tray
ARINC
758
Left tray
ARINC
758
Right tray
ARINC
724B
Right tray
ARINC
758
APM
ARINC 716
VHF wiring
429 bus
ARINC 758
CMU wiring
1 VHF
429 bus
ARINC 724B
ACARS
wiring
ARINC 716
VHF wiring
ARINC 724B
ACARS
wiring
429 bus
429 bus
3 VDRs
ARINC 758
CMU wiring
ARINC 758
CMU wiring
ARINC 758
CMU wiring
Other
airplane systems
Other
airplane systems
VDL mode 2 / AOA data link with
dual ARINC 758 CMU provisions
CMU
Left tray
ARINC
758
Right tray
ARINC
758
APM
429 bus
429 bus
3 VDRs
ARINC 758
CMU wiring
ARINC 758
CMU wiring
Other
airplane systems
797-FD-0037C
1-19-02-whp/DD
Options 5 —Communications
767-200/767-300 - VDL Mode 2/AOA Architecture
Data Link
Air
Ground
VDL
mode
Interface
systems:
• FMC
• ACMS
• Printer
CMU
VDL
ground
network
Airline
operational
control
(AOC)
ACARS
ground
network
ATC
VDR
ACARS
• VDL mode 2/AOA data link interface with
VDL mode 2/AOA ground stations and
conventional ACARS ground stations
797-FD-0038C
1-19-02-whp/DD
Options 6 —Avionics
767-200ER/-300ER
Feature
Data Loader
Printer
ACMS - Expanded Engine
Parameter Recording
MIDU (Multipurpose Interactive
Display Unit)
Engine out Takeoff Thrust Operation
Basic
Airborne Data Loader
None
Basic Parameters
None
Five Minutes
Option
Portable Data Loader Connector
ARINC 744 PrinterARINC 740 Printer
Basic and Expanded Parameters
Provided
Ten Minutes
ECS Temperature Indications
Celsius
Fahrenheit
Instrumentation Display Units
English units
Metric units
Navigation Systems
Feature
Metric Altimeters
Standby Attitude Indicator
Weather Radar System
EGPWS Peaks & Obstacles
Basic
None
Backcourse Switch Included
Single System
Inhibited
Option
Two Metric Altimeters with Digital
Display One Metric Altimeter
with Analog DisplayTwo Metric
Altimeters with Digital Display and
One Metric Altimeter with Analog Display
Backcourse Switch Deactivated
Dual System Single System with Auto-Tilt
Dual System with Auto-Tilt
Enabled
EGPWS Altitude Callout Volume
Standard Volume
Low Volume
EGPWS "Smart 500" foot Callout
Inhibited
Enabled
EGPWS Altitude Callouts
Inhibited
Many options available
797-FD-0216C
2-25-2-whp
Options 6 —Navigation Systems
767-200ER/-300ER
Peaks and Obstacles
• Option provides for the display of
man-made obstacles on the EHSI
when an obstacle is contained in
the Enhanced Ground Proximity
Warning Computer (EGPWC)
terrain database and a conflict is
identified. Aural and visual caution
and warning alerts are provided.
8.8 NM
TRK
194
18
“CAUTION
CAUTION OBSTACLE
CAUTION OBSTACLE
OBSTACLE”
1717.1Z
21
15
Speaker
Speaker
M
24
10
Amber for caution
Red for warning
OBSTACLE
TERR
797-FD-0029
2-26-2-WHP/CF
Options 6 —Navigation Systems
767-200ER/-300ER
EGPWS Peaks and Obstacles
Peaks Display
8.8 NM
TRK
194 M
18
•
Provides a “look down” to
the highest terrain ahead of
the airplane
•
Displays terrain
•
Displays terrain altitudes
•
Blends with normal terrain
colors when flying near
terrain altitude
•
Peaks display when more
than 2,000 feet above terrain
1717.1Z
24
10
Height of
surrounding
terrain
Peaks and obstacles is an
optional feature of the EGPWS
21
15
Highest
peak
•
TERR
144
050
797-FD-0030
2-26-2-whp/CF
Options 7 —Crew Accommodations
767-200ER/-300ER
Flight Deck Accommodations
Feature
Captain's and First Officer's Seats
First Observer's Seat
Second Observer's Seat
Sun Visors
Basic
Manually Operated Seats
Wall Mounted
None
Standard Sun Visors
Option
Power Operated Seats
Track Mounted
Provided
Roller Sunshades and
improved Sun Visors
Portable Breathing Equipment
None
Provided
Flight Deck Flashlights
None
One Flashlight with ShieldTwo Flashlights
Two Flashlights with Shield
Emergency Evacuation Signal System
None
Provided
797-FD-0217C
2-26-2-whp
Options 7 —Crew Accomodations
767-200ER/-300ER
• Powered IPECO Captain’s and
First Officer’s seats
• Second Observer’s station
(not available on 767 Freighter)
• Track-mounted First Observer’s seat
(basic on 767 Freighter)
First Officer’s
tiller wheel
• Flashlights
• Protective breathing equipment
• Emergency evacuation signal system
• First Officer’s nose wheel steering
tiller (not available on 767 Freighter)
Second Observer’s seat
• Two headphone jacks
• Oxygen mask
• Life vest
• Audio selector panel
(optional)
797-FD-0177C
2-26-2-whp
Options 8 —Airframe Systems
767-200ER/-300ER
Feature
Basic
Option
Bulk Cargo Heating and Ventilation
None
Provided
Catalytic Converters for Ozone Control
None
Provided
APU - Additional Starting Capability
None
Provided
Duct Leak Detection System
Single Loop System
APU Fire Extinguisher Bottle
Single Standard APU Bottle
Dual Loop System (PW & GE
engines only)
Single APU Bottle, common with
Engine fire bottlesDual Standard
APU BottlesDual APU Bottles, common
with Engine fire bottles
Ice Detection
None
Advisory Ice DetectionAutomatic
Anti-Ice System
APU Hour Meter
None
Provided on Flight Deck
Provided in E/E Bay
APU Cycle Meter
None
Provided on Flight Deck
Provided in E/E Bay
797-FD-0218C
2-25-2-whp
Acronyms and Abbreviations
ACARS
ACMS
ADC
ADF
ADL
AFDS
A/G
ALTN
AOA
A/P
APU
ASP
ATC
AUX
BFE
BITE
CONF
CRT
DME
EADI
ECS
E/E
EEC
EFIS
EGPWS
EGT
EHSI
EICAS
ELEC
ENG EXCD
EPCS
EPR
ER
ETOPS
FADEC
FCC
F/D
FMC
FPR
GA
GMT
GPS
GS
HDG
HMG
HYD
– Aircraft communications addressing and reporting system
– Airplane condition monitoring system
– Air data computer
– Automatic direction finder
– Airborne data loader
– Autopilot/flight director system
– Air-ground
– Alternate
– Angle of attack
– Autopilot
– Auxiliary power unit
– Audio selector panel
– Air traffic control
– Auxiliary
– Buyer-furnished equipment
– Built-in test equipment
– Configuration
– Cathode ray tube
– Distance measuring equipment
– Electronic attitude director indicator
– Environmental control system
– Electrical/electronic
– Electronic engine control
– Electronic flight instrument system
– Enhanced ground proximity warning system
– Exhaust gas temperature
– Electronic horizontal situation indicator
– Engine indication and crew alerting system
– Electrical
– Engine exceedance
– Electronic propulsion control system
– Engine pressure ratio
– Extended range
– Extended-range twin-engine operations
– Full-authority digital engine control
– Flight control computer
– Flight director
– Flight management computer
– Flight plan request
– Go-around
– Greenwich mean time
– Global positioning system
– Ground speed
– Heading
– Hydraulic motor generator
– Hydraulics
IAS
ILS
IRS
LAT/LON
LNAV
LRC
LRU
MASI
MCDP
MCDU
MCP
MMR
MSG
OVRD
PA
PERF
PLI
PWS
QAR
RA
RAT
RDMI
RTO
RVR
SAT
SATCOM
SEL
SELCAL
SID
STAR
STBY
TAI
TAS
TAT
TCAS
TMC
TMSP
TO
TRK
VHF
VNAV
VOR
VSI
WEU
WPT
WXR
– Indicated airspeed
– Instrument landing system
– Inertial reference system
– Latitude/longitude
– Lateral navigation
– Long-range cruise
– Line replaceable unit
– Mach/airspeed indicator
– Maintenance control and display panel
– Multifunction control display unit
– Mode control panel
– Multi-mode receiver
– Message
– Override
– Passenger address
– Performance
– Pitch limit indicator
– Predictive windshear system
– Quick access recorder
– Resolution advisory (or radio altimeter)
– Ram air turbine
– Radio distance magnetic indicator
– Refused takeoff
– Runway visual range
– Static air temperature
– Satellite communications
– Standby engine indicator
– Selective calling
– Standard instrument departure
– Standard terminal arrival route
– Standby
– Thermal anti-ice
– True airspeed
– Total air temperature
– Traffic alert and collision avoidance system
– Thrust management computer
– Thrust mode select panel
– Takeoff
– Track
– Very high frequency
– Vertical navigation
– Very high frequency omni range
– Vertical speed indicator
– Warning electronics unit
– Waypoint
– Weather radar
797-FD-0178C
1-19-2-whp/CF