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B 3 C01046 AFCS SYS B FCC DC
B 12 C00204 FLIGHT CONTROL SHUTOFF VALVES SPOILER
B 13 C00363 FLIGHT CONTROL SHUTOFF VALVES FLT CONT
C 11 C00362 FLIGHT CONTROL SHUTOFF VALVES STBY RUD
C 13 C01074 FLIGHT CONTROL SHUTOFF VALVES FLT CONT
D 13 C00841 FLIGHT CONTROL ALTN T.E. FLAP DRIVE
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-09-45
Page 404
Jun 10/2006
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
F/O Electrical System Panel, P6-3
Row Col Number Name
B 12 C00132 MASTER CAUTION ANNUNCIATOR BUS 1
B 13 C00131 MASTER CAUTION ANNUNCIATOR BAT
D 12 C00310 INDICATOR MASTER DIM BAT
D 13 C00311 INDICATOR MASTER DIM BUS 1
D 14 C00312 INDICATOR MASTER DIM BUS 2
E 14 C00316 INDICATOR MASTER DIM SECT 4
F/O Electrical System Panel, P6-4
Row Col Number Name
F 10 C01283 GENERATOR CONT UNIT 1
F 11 C01284 GENERATOR CONT UNIT 2
SUBTASK 27-09-45-860-004
(3) Do this task: Supply Electrical Power, TASK 24-22-00-860-811.
SUBTASK 27-09-45-710-006
(4) Do this test of the hydraulic system valve control:
(a) Open these circuit breakers and install safety tags:
F/O Electrical System Panel, P6-2
Row Col Number Name
D 13 C00841 FLIGHT CONTROL ALTN T.E. FLAP DRIVE
F/O Electrical System Panel, P6-3
Row Col Number Name
D 15 C01401 LANDING GEAR AIR/GND RELAY
Power Distribution Panel Number 2, P92
Row Col Number Name
F 2 C01449 STANDBY HYDRAULIC PUMP
NOTE: With these circuit breakers open the standby pump and the alternate flap drive
motor will not operate.
(b) Make sure these switches on the module assy [1] are in the OFF position:
1) FLT CONTROL A, and FLT CONTROL B
2) SPOILER A, and SPOILER B
3) ALTERNATE FLAPS arm switch
4) ALTERNATE FLAPS control switch
(c) Do this test of the control of the system A and system B flight control hydraulic valves from
the module assy [1]:
NOTE: The flight control hydraulic valves are installed on the left and right sides of the
forward bulkhead of the landing gear wheel well.
1) Move the FLT CONTROL A switch to the ON position.
a) Make sure the system A flight control valve moves to position 1.
b) Make sure the system B flight control valve does not move (stays in position 2).
2) Move the FLT CONTROL B switch to the ON position.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-09-45
Page 405
Jun 10/2006
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
a) Make sure the system B flight control valve moves to position 1.
3) Move the FLT CONTROL A switch to the OFF position.
a) Make sure the system A flight control valve moves to position 2.
b) Make sure the system B flight control valve does not move (stays in position 1).
4) Move the FLT CONTROL B switch to the OFF position.
a) Make sure the system B flight control valve moves to position 2.
(d) Do this test of the control of the system A and system B spoiler hydraulic valves from the
module assy [1]:
NOTE: The spoiler hydraulic valves are installed on the left and right sides of the forward
bulkhead of the landing gear wheel well.
1) Move the SPOILER A switch to the ON position.
a) Make sure the system A spoiler valve moves to position 1.
b) Make sure the system B spoiler valve does not move (stays in position 2).
2) Move the SPOILER B switch to the ON position.
a) Make sure the system B spoiler valve moves to position 1.
3) Move the SPOILER A switch to the OFF position.
a) Make sure the system A spoiler valve moves to position 2.
b) Make sure the system B spoiler valve does not move (stays in position 1).
4) Move the SPOILER B switch to the OFF position.
a) Make sure the system B spoiler valve moves to position 2.
(e) Remove the safety tags and close these circuit breakers:
F/O Electrical System Panel, P6-2
Row Col Number Name
D 13 C00841 FLIGHT CONTROL ALTN T.E. FLAP DRIVE
F/O Electrical System Panel, P6-3
Row Col Number Name
D 15 C01401 LANDING GEAR AIR/GND RELAY
Power Distribution Panel Number 2, P92
Row Col Number Name
F 2 C01449 STANDBY HYDRAULIC PUMP
NOTE: If you will perform the "Test of the hydraulic system indications and lights" next,
do not close the STANDBY HYDRAULIC PUMP circuit breaker on the P92 panel.
SUBTASK 27-09-45-710-001
(5) Do this test of the hydraulic system indications and lights:
(a) Open this circuit breaker and install safety tag:
Power Distribution Panel Number 2, P92
Row Col Number Name
F 2 C01449 STANDBY HYDRAULIC PUMP
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL飞机维护手册1(69)
