G06670
Rudder Power Control Switches 500
27-21-0Page 202 Figure 201 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73
(6)
Position ground interconnect switch on forward overhead panel to OPEN.
(7)
Check that flight control switches A and B, located in upper left corner of forward overhead panel, are positioned to ON position.
NOTE: To pressurize system A or system B separately, position flight control switches A and B to ON or OFF as required.
C. Restore airplane to normal.
NOTE: Perform following steps after completing rudder control system maintenance that required pressurization.
(1)
Position No. 1 and 2 system hydraulic system B pump switches to OFF.
(2)
Position grd interconnect switch to CLOSE.
(3)
Position flight control switches A and B to ON.
(4)
Close FLT CONTR and STDBY RUD circuit breaker on panel P6.
(5)
Remove electrical power, if no longer required.
(6)
Remove ground lock assembly from nose gear.
3. Rudder Hydraulic Systems A, B, and Standby Depressurization
A. Equipment and Materials
(1) Lock Assembly - Flight Controls, F80049-12 (Preferred), F80049-1 (Optional) (3 required).
B. Depressurize rudder hydraulic systems A, B, and standby.
(1)
Turn hydraulic pump switches A and B, located in center of forward overhead panel, to OFF position (Fig. 201).
(2)
Ensure that ground interconnect switch is at CLOSE position.
(3)
Turn flight control switches A and B, located in upper left corner of forward overhead panel, to OFF position.
(4)
Open FLT CONTR and STBY RUD circuit breakers located on P6-2 load control panel.
(5)
If any hydraulic components are to be removed, depressurize hydraulic system reservoirs (Ref 29-09-300, Maintenance Practices).
(6)
Cycle rudder pedals until rudders stop operating hydraulically.
501
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-0 Page 203
G06684G06721
Flight Controls Hydraulic Module Lock Installation 500
27-21-0 Figure 202 May 01/99
Page 204
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Standby Hydraulic Module Lock Installation
May 01/99 Figure 203 27-21-0
Page 205
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(7)
Check that manual override levers on flight controls shutoff valve of both flight controls hydraulic modular packages (A and B) is in OFF position (Fig. 202). Check that manual override lever on standby rudder actuator shutoff valve of standby hydraulic modular package is in OFF position (Fig. 203). Manually place levers in OFF position if required
(8)
Disconnect electrical connector from flight controls shutoff valve motor on Flight Controls A hydraulic modular package in left wheel well, from flight controls shutoff valve motor on Flight Controls B modular package in right wheel well, and from standby rudder actuator shutoff valve motor on standby hydraulic modular package.
(9)
Install lock to each of the two flight controls shutoff valves and to the standby rudder actuator shutoff valve and insert attaching lockpins.
C. Restore airplane to normal.
NOTE: Perform following steps after completing rudder control system maintenance that required depressurization.
(1)
Remove locks from System A and System B Flight Controls hydraulic module shutoff valve and from rudder standby actuator shutoff valve on standby hydraulic module, and reconnect electrical connectors.
(2)
Position flight control switches A and B on forward overhead panel to ON.
(3)
Close FLT CONTR and STDBY RUD circuit breakers on panel P6.
(4)
Pressurize hydraulic reservoirs as required. Refer to 29-09-300.
500
27-21-0 Page 206 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/80
RUDDER AND RUDDER TRIM CONTROL SYSTEM - ADJUSTMENT/TEST
EFFECTIVITY
AIRPLANES PRE-SB 27-1252
(For airplanes POST-SB 27-1252, see 27-21-1/501)
1. Rudder and Rudder Trim Control System Adjustment
A. General
(1)
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