501
27-51-0 Page 202 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
G11721
500 Trailing Edge Flap Bypass Valve Lock Installation
May 01/99 Figure 201 27-51-0
Page 203
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(5)
To dissipate remaining hydraulic power, cycle rudder pedals until rudder stops moving.
(6)
If any hydraulic connections are to be disturbed, depressurize hydraulic system A reservoirs. Refer to 29-09-300, Hydraulic Reservoir Pressurization System - Maintenance Practices.
(7)
Install flap bypass valve lock as follows: See figure 201.
(a)
Disconnect electrical connector from trailing edge flap bypass valve located in right wheel well.
(b)
Place manual override lever on bypass valve to position 2.
(c)
Install lock on bypass valve and insert attaching lock pin.
C. Restore Airplanes to Normal
NOTE: Perform following steps after completing system maintenance requiring
depressurization.
(1)
Remove lock from trailing edge flap bypass valve.
(2)
Connect electrical connector to bypass valve.
(3)
Close FLAP circuit breaker on P6 circuit breaker panel.
500
27-51-0 Page 204 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73
TRAILING EDGE FLAP SYSTEM - ADJUSTMENT/TEST
1. Trailing Edge Flap System Adjustment
A. General
(1)
The flap drive system may creep for several minutes after initially stopping at a selected position. To minimize measurement error, it is necessary to wait 2 minutes at each flap position before taking measurements.
(2)
With flaps hydraulically retracted, the trailing edge flap system is properly adjusted when the individual components meet the following conditions. See Fig. 501 for rigging pin locations and cable tension requirements.
(a)
Flap Control Cables WFA and WFB
1) The flap control lever shall spring back 0.187 +0.005 inch from the FLAP UP detent. Tension of WFA and WFB cables shall be within limits of that specified in temperature-tension chart, Fig. 501. These conditions may be obtained by adjusting turnbuckles in fuselage lower nose compartment per par. C.(2).
(b)
Trailing Edge Flap Control Valve
1) Rigging pin F-1 shall fit freely in the flap control unit. This condition may be obtained by adjusting trailing edge flap cam link in flap control unit per par. C.(4).
(c)
Flap Follow-Up Cables WFFA and WFFB
1) With rigging pin F-1 installed, index mark on drum shall align within + 0.03 inch with matching mark on flap power unit housing. Tension in WFFA and WFFB cables shall be within limits of that specified in temperature-tension chart, Fig.
501. These conditions may be obtained by adjusting turnbuckles in right wheel well per paragraph C.(3).
(d) Flap Transmissions
1) At each flap transmission, angular clearance between ball screwnut and upstop on jackscrew yoke shall be 170 to 190 degrees (1/2 turn + 10 degrees) turn of jackscrew and seal support on aft lower wing panel should contact midflap nose.
535
Aug 15/80 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-01 Page 501
TO ENSURE THAT PROPER CABLE TENSION IS OBTAINED, ALLOW A MINIMUM OF ONE HOUR AT CONSTANT AMBIENT TEMPERATURE (±50F) FOR AIRFRAME TEMPERATURE TO STABILIZE.
FOR REQUIRED PERIODIC CHECKS WITHOUT SYSTEM DISCREPANCY REPORTS, THE CABLE TENSIONS MAY DEVIATE +15/-30 POUNDS FROM TABLE VALUES. FOR CABLE TENSION CHECKS RESULTING FROM SYSTEM DISCREPANCY REPORTS, THE TENSIONS MAY DEVIATE ±15 POUNDS FROM TABLE VALUES. WHENEVER CABLES ARE READJUSTED, TABLE VALUES MUST BE MET.
FOR REQUIRED PERIODIC CHECKS WITHOUT SYSTEM DISCREPANCY REPORTS, THE CABLE TENSIONS MAY DEVIATE +20/-20 POUNDS FROM TABLE VALUES. FOR CABLE TENSION CHECKS RESULTING FROM SYSTEM DISCREPANCY REPORTS, THE TENSIONS MAY DEVIATE ±15 POUNDS FROM TABLE VALUES. WHENEVER CABLES ARE READJUSTED, TABLE VALUES MUST BE MET.
CABLES FORWARD OF TURNBUCKLES ARE 3/32 INCH DIAMETER AND CABLES AFT OF TURNBUCKLES ARE 1/8 INCH DIAMETER.
AF F-GBYA THRU F-GBYM; GJ B-2501 THRU B-2516; YB 9H-ABA THRU 9H-ABC
ALL EXCEPT
Trailing Edge Flap System Adjustment 5C1
27-51-01 Figure 501 (Sheet 1) Feb 20/89
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
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