(2)
Provide system A hydraulic power (par. 3).
(3)
Position flap control lever to FLAPS UP position to fully retract leading edge devices.
(4)
Depressurize hydraulic system A (par. 4).
C. Install lock assembly on standby hydraulic module to prevent extension of leading edge flaps and slats (Fig. 201).
NOTE: The leading edge control surfaces shutoff and bypass valve lock may be used to lock the leading edge devices in the retracted position. The lock is installed on the shutoff valve at the standby hydraulic module, located on the aft bulkhead of the main wheel well.
(1) Install lock on standby hydraulic module as follows:
(a)
Check that alternate flap master switch is in OFF position and tag switch DO NOT OPERATE.
(b)
Disconnect electrical connector from leading edge devices shutoff valve.
(c)
Manually move override lever at leading edge devices shutoff valve to position 2.
(d)
Install lock on standby hydraulic module and insert attaching lockpin.
WARNING: INSTALL LOCKS TO PREVENT INADVERTENT OPERATION OF LEADING EDGE FLAPS AND SLATS. FLAPS AND SLATS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.
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D. Restore airplane to normal.
(1) Remove lock assembly from standby hydraulic module as follows (Fig. 201).
(a)
Remove attaching lockpin and remove lock from standby hydraulic module.
(b)
Manually move override lever at leading edge devices shutoff valve to position 1.
(c)
Connect electrical connector to leading edge devices shutoff valve.
(d)
Remove DO NOT OPERATE tag from alternate flap master switch.
(e)
Provide System A hydraulic power (par. 3).
(f)
Position flap control lever to UP to retract flaps and slats.
(g)
Remove System A hydraulic power (par. 4).
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Sep 20/82 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-81-0 Page 205
LEADING EDGE FLAPS AND SLATS - ADJUSTMENT/TEST
1. General
A. The trailing edge flap system must be adjusted and tested per 27-51-0, A/T prior to adjusting and testing the leading edge flap and slat system. Rigging of the leading edge flap and slat system consists of adjusting the leading edge flap and slat control valve, adjustment of the nose fairing linkage on each leading edge flap and adjusting each leading edge slat to the faired position.
B. The leading edge flaps and slats may be adjusted in any condition with airplane on or off jacks, with no fuel or any amount of fuel in tanks. However, gap and mismatch tolerance are to be met under the same conditions that flaps and slats were adjusted.
C. During slat extension or retraction tests, chatter or vibration of the surfaces, especially at low
hydraulic operating pressures, is normal. 1A. Test For Uncommanded Leading Edge Extension With Standby Hydraulic Power
A. Provide electrical power.
B. Provide system B hydraulic power (Ref. 27-81-0 MP).
C. Set parking brake.
D. Verify ALTERNATE FLAP master arming switch on forward overhead panel (P5) is in OFF position and switch guard is closed.
E. Verify flap control lever is in FLAP UP detent with leading edge flaps and slats and trailing edge flaps retracted.
F. If not, open GRD INTERCONNECT switch (P5 panel) to pressurize system A hydraulic power. Place flap control lever to FLAP UP detent and verify leading edge flaps and slats and trailing edge flaps retract (Ref. 27-81-0 MP).
G. Depressurize system A hydraulic power and system B hydraulic power (Ref. 27-81-0 MP).
H. Close GRD INTERCONNECT switch (P5 panel) when residual pressure is less than 100 psi.
I. Actuate A or B FLT CONTROL switch on forward overhead panel (P5) to STDBY RUD position.
(1)
Check that STANDBY HYD LOW PRESSURE light comes on.
(2)
Check that standby hydraulic pump starts and that STANDBY HYD LOW PRESSURE light goes off.
J. Observe leading edge flaps and slats for 60 seconds. Verify that flaps and slats do not extend.
Note: Leading edge flaps may slowly extend due to gravity.
K. Return FLT CONTROL switch on pilot's forward overhead panel (P5) to ON position.
L. Remove electrical power.
2. Leading Edge Flaps and Slats Adjustment
A. General
(1) Three rigging pins are used in the trailing edge flap system. One of these rigging pins is used when adjusting the leading edge flap and slat system.
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