.
APU operation (start attempts not recommended above 25,000 feet)
Communications
.
flight interphone system
.
passenger address system
.
VHF No. 1
Electrical
.
APU & engine generator power control (switched hot battery bus)
.
external power control (hot battery bus)
.
standby bus volts indication
.
STANDBY POWER OFF light
Copyright . The Boeing Company. See title page for details.
6.20.16 June 7, 2002
Electrical -System Description 737 Operations Manual
Flight Instruments
.
Captain’s altimeter (on some airplanes)
.
Captain’s EFIS (on some airplanes)
.
Captain’s mach/airspeed indicator (on some airplanes)
.
Captain’s vertical speed indicator (on some airplanes)
.
clocks (hot battery bus)
.
standby airspeed/altitude indicator
.
standby horizon indicator
.
standby magnetic compass
Fire Protection
.
APU and engine fire extinguisher bottles (hot battery bus)
.
APU and engine fire detection system
Fuel
.
crossfeed valve
.
engine fuel shutoff valves (hot battery bus)
.
fuel quantity indicators
.
FUEL VALVE CLOSED lights (switched hot battery bus)
Hydraulics
.
engine hydraulic shutoff valves
.
standby rudder shutoff valves
Landing Gear
.
air/ground relay
.
ANTISKID INOP light
.
inboard antiskid system
.
parking brake
.
landing gear indicator lights
Navigation
.
ADF No. 1
.
Captain’s RDMI
.
First Officer’s RDMI (as installed)
.
left IRS - AC
.
left & right IRS - DC (switched hot battery bus)
.
VHF NAV No. 1
Electrical -System Description 737 Operations Manual
Warnings
.
aural warnings
.
master caution recall system
.
stall warning system
Copyright . The Boeing Company. See title page for details.
6.20.18 August 1, 2003
Electrical -System Description 737 Operations Manual
Intentionally
Blank
Copyright . The Boeing Company. See title page for details.
August 1, 2003 6.20.19
Electrical -System Description
737 Operations Manual
Basic Equipment Operating – Instrument Panels Captain Instrument Panel
1
A/P A/T
P/RST P/RST
TEST2
0
1 07009
2 3
21013 IN.HG. MB 992 6 5 4 ALT
BARO IASKNOTS 350380 43 B/CRS ILS OFF ILS
CHR DATE CTR
60
RUN HLD 30 10 20 50 HLD RUN 40 ET/CHR TIME R O V ADF ADF R O V QTY TEST 1 FUEL ERR KGS % 2
RESET FS SS
FUEL FUEL
ERR KGS ERR KGS
% %
NOSE WHEEL STEERING
NA OL
RT M
The standby power system utilizes the battery as a source of power to supply the following minimum essential instruments, communication, and navigation equipment:
-
Left IRS
-
No. 1 RDMI
-
Standby Horizon Indicator
-
No. 1 VHF Navigation System (VOR, GS, and LOC)
-
No. 1 ADF Navigation System
-
No. 1 VHF Communications System
-
N1, EGT
-
N2, Fuel Flow (EIS)
_______ AS SOON AS THE AIRPLANE LANDS, THE STANDBY POWERCAUTION: SWITCH SHOULD BE POSITIONED TO "BAT" TO ENERGIZE
THE ABOVE ELECTRONICS AND FOR VHF-1 COMMUNICATIONS.
NOTE: All of the Captain's instruments that are powered by standby power are integrally lighted on standby power.
Airplane Configuration - Inflight This illustration shows the Indicates Battery Switch - ON instruments which are useable Inoperative Standby Power Switch - AUTO with only the battery and Instrumentsstandby busses powered.
(As installed)
Copyright . The Boeing Company. See title page for details.
6.20.20 August 1, 2003
Electrical -System Description
First Officer Instrument Panel
COCKPIT COMMUNICATION COCKPIT LIGHTS
Audio Selector Panels Standby Instrument Floodlight Flight Interphone White Dome Light Passenger Address System Magnetic Compass Light Service Interphone
Standby Power Switch - AUTO Battery Switch - ON Airplane Configuration - In Flight standby busses powered. with only the battery and instruments which are useable This illustration shows the Instruments Inoperative Indicates
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