曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

TASK 27-51-00-860-801.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-00
Page 560
Jun 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(b) Use the air data model test set, COM-1914 to raise the airspeed to 164 knots, on the
Captain’s disply unit.
NOTE: When you apply or remove pressure to the pitot system, the rate must not be
more than 300 knots for each minute.
(c) Make sure the trailing edge flaps retract to the 30-unit position.
GUN 155, 201-999
1) Make sure the FLAP LOAD RELIEF light on the P3-1 panel comes on.
GUN ALL
(d) Use the air data model test set, COM-1914 to lower the airspeed to 157 knots.
(e) Make sure the trailing edge flaps extend to the 40-unit position.
GUN 155, 201-999
1) Make sure the FLAP LOAD RELIEF light goes out.
GUN ALL
SUBTASK 27-51-00-720-014
(7) Do a test of the load relief system with the flaps at 30 units:
(a) Use the primary system to retract the flaps to the 30-unit position. To extend the flaps, do
this task: Trailing Edge Flap System Operation With Primary Control,
TASK 27-51-00-860-801.
(b) Use the air data model test set, COM-1914 to raise the airspeed to 177 knots.
NOTE: When you apply or remove pressure to the pitot system, the rate must not be
more than 300 knots for each minute.
(c) Make sure the trailing edge flaps retract to the 25-unit position.
GUN 155, 201-999
1) Make sure the FLAP LOAD RELIEF light on the P3-1 panel comes on.
GUN ALL
(d) Use the air data model test set, COM-1914 to lower the airspeed to 170 knots.
(e) Make sure the trailing edge flaps extend to the 30-unit position.
GUN 155, 201-999
1) Make sure the FLAP LOAD RELIEF light goes out.
GUN ALL
H. Put the Airplane Back to Its Usual Condition
SUBTASK 27-51-00-860-079
(1) Move the flap control lever to the UP position to retract the flaps.
SUBTASK 27-51-00-860-080
(2) Put the system back to ambient pressure.
NOTE: When you apply or remove pressure to the pitot system, the rate must not be more than
300 knots for each minute.
SUBTASK 27-51-00-080-004
(3) Disconnect the pitot/static system tester from the pitot system:
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-00
Page 561
Jun 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
CAUTION: DO NOT DISCONNECT THE PITOT SYSTEM TEST ADAPTER WHEN THE PITOTSTATIC
SYSTEM IS NOT AT AMBIENT PRESSURE. IF YOU DO, DAMAGE TO THE
AIR DATA MODULES CAN OCCUR.
(a) Disconnect the Test Set air data test set, RVSM compatible, STD-883 from the adapter, kit,
COM-1916.
(b) Remove the adapter, kit, COM-1916, from the pitot probe.
(c) Remove the safety tags and close these circuit breakers:
CAPT Electrical System Panel, P18-3
Row Col Number Name
C 2 C00238 HEATERS TEMP PROBE
D 3 C01071 HEATERS ALPHA VANE RIGHT
D 5 C00525 HEATERS F/O PITOT
D 6 C00524 HEATERS AUX PITOT
SUBTASK 27-51-00-860-081
(4) Remove system B hydraulic power, do this task: Hydraulic System A or B Power Removal,
TASK 29-11-00-860-805.
SUBTASK 27-51-00-410-013
(5) For the main equipment center, do this task.
Close this access panel:
Number Name/Location
117A Electronic Equipment Access Door
------------------------- END OF TASK ---------------------------
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-00
Page 562
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
TRAILING EDGE FLAP SYSTEM - INSPECTION/CHECK
1. General
A. This procedure has these inspections:
(1) An inspection of the trailing edge flap drive system components
(2) An inspection of the trailing edged flap actuation system.
TASK 27-51-00-210-801
2. Trailing Edge Flap Drive System Inspection
(Figure 601)
A. References
Reference Title
27-51-00-040-801 Trailing Edge Flap System Deactivation (P/B 201)
27-51-00-440-801 Trailing Edge Flap System Reactivation (P/B 201)
27-51-00-860-803 Extend the Trailing Edge Flaps (P/B 201)
27-51-00-860-804 Retract the Trailing Edge Flaps (P/B 201)
32-00-01-480-801 Landing Gear Downlock Pins Installation (P/B 201)
B. Location Zones
Zone Area
133 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Left
134 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Right
541 Left Wing - Fairing Flap Support No. 4
542 Left Wing - Fairing Flap Support No. 3
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-600-700-800-900 AIRCRAFT MAINTENANCE MANUAL飛機維護手冊4(62)