(b)
P6-11 Circuit Breaker Panel
1) STBY HYD PUMP NORMAL
2) ELEC HYD PUMP SYS B
(c)
P6-12 Circuit Breaker Panel
1) STBY HYD PUMP (ALT)
2) ELEC HYD PUMP SYS A
S 862-024
(10)
Remove the remaining hydraulic power:
(a)
Operate the rudder pedals until there is no rudder movement to bleed out hydraulic system B.
(b)
Set the FLT CONTROL B switch to STDBY RUD.
(c)
Operate the rudder again.
(d)
Set the FLT CONTROL A and B switches to OFF.
S 862-025
(11)
If you remove hydraulic connections, make sure to release pressure from the system B and standby hydraulic reservoirs (AMM 29-09-00/201).
S 492-026
(12)
Install the lock on the standby hydraulic module (Fig. 201):
(a)
Disconnect the electrical connector from the leading edge devices shutoff valve at the standby hydraulic module.
(b)
Make sure the override lever at the leading edge devices shutoff valve is in position 1.
(c)
Install the lock on the shutoff valve.
(d)
Install the lockpin.
F.
Put the Airplane Back to Its Usual Condition
S 092-027
(1)
Remove the lock from the standby hydraulic module shutoff valve with the steps that follow:
(a)
Connect the electrical connector to the leading edge devices shutoff valve at the standby hydraulic module.
(b)
Remove the lock from the shutoff valve.
(c)
Make sure the override lever at the leading edge devices shutoff valve is in position 1.
(d)
Remove the lockpin.
S 862-010
(2)
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a)
P6-2 Circuit Breaker Panel
1) PTU/LG BYP V CONT 1
2) PTU/LG BYP V CONT 2
3) FLAP SHUTOFF VALVES or
FLAP
SHUTTOFF VALVES
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A
737-300/400/500MAINTENANCE MANUAL
(b)
P6-11 Circuit Breaker Panel
1) STBY HYD PUMP NORMAL
2) ELEC HYD PUMP SYS B
(c)
P6-12 Circuit Breaker Panel
1) STBY HYD PUMP (ALT)
2) ELEC HYD PUMP SYS A
S 862-042
(3)
Remove the DO-NOT-OPERATE tags from the ENG 1 HYD PUMPS A and ENG 2 HYD PUMPS B switches.
S 862-043
(4)
Put the ENG 1 AND ENG 2 HYD PUMPS switches (P5 panel) back to the ON position.
S 862-041
(5)
Make sure the ELEC 1 AND ELEC 2 HYD PUMPS switches are in the OFF position.
S 862-019
(6)
Put the FLT CONTROL A and B switches back to the ON position.
TASK 27-81-00-042-009
4. Leading Edge Flaps and Slats Deactivation from Trailing Edge Flaps__________________________________________________________________
A. General
(1)
The deactivation of the (PTU) Power Transfer Unit, System B (which includes pressurization originated by (EDP) Engine Driven Pump and (EMDP) Electric Motor Driven Pump), and the Standby Systems will isolate the leading edge flaps and slats from the operation of the trailing edge flaps.
(2)
This procedure has two tasks:
(a)
To operate the trailing edge flaps in the alternate (fully electric) mode, with the leading edge flaps and slats deactivated (isolated), and with no hydraulic power systems A, B, and Standby available.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-81-00
ALL ú ú 02 Page 206 ú Mar 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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本文链接地址：737-300 400 500 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 6(22)
