曝光臺(tái) 注意防騙 網(wǎng)曝天貓店富美金盛家居專營(yíng)店坑蒙拐騙欺詐消費(fèi)者

SUBTASK 27-31-54-420-004
(5) Install the applicable control column. To install it, do this task: Control Column - Installation,
TASK 27-31-51-400-801.
SUBTASK 27-31-54-080-001
(6) Remove the rig pin E-1 of rig pin kit, SPL-1585 from the left forward quadrant.
SUBTASK 27-31-54-080-002
(7) Remove the rig pin E-5 of the rig pin kit, SPL-1585 from the aft control quadrant.
SUBTASK 27-31-54-710-001
(8) Do a check of the control column:
(a) Move the control column full forward then full aft.
1) Make sure the control column operates correctly and smoothly.
SUBTASK 27-31-54-820-001
(9) Adjust the elevator control cables EA and EB. To adjust them, do this task: Elevator Control
Cables EA and EB and Pitch Force Transducers - Adjustment, TASK 27-31-00-820-801.
F. Put the Airplane Back To Its Usual Condition
SUBTASK 27-31-54-410-001
(1) Install this access panel:
Number Name/Location
318BR Tailcone Access Door
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-31-54
Page 411
Oct 10/2006
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
SUBTASK 27-31-54-410-002
(2) Close this access panel:
Number Name/Location
112A Forward Access Door
SUBTASK 27-31-54-860-002
(3) Do this task: Put the Elevator Systems A and B Back to the Condition Before the Pressure
Removal, TASK 27-31-00-840-802.
------------------------- END OF TASK ---------------------------
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-31-54
Page 412
Oct 10/2006
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
ELEVATOR FORWARD CONTROL QUADRANT ASSEMBLY - REMOVAL/INSTALLATION
1. General
A. This procedure has these tasks:
(1) A removal of the elevator forward control quadrant assembly
(2) An installation of the elevator forward control quadrant assembly.
B. The elevator forward control quadrant assembly is referred to as "forward quadrant assembly" in
this procedure.
TASK 27-31-61-000-801
2. Elevator Forward Control Quadrant Assembly Removal
(Figure 401, Figure 402)
A. References
Reference Title
22-11-92-000-801 Pitch Force Transducer Removal (P/B 401)
27-31-00-800-802 Remove Pressure from the Elevator Hydraulic Systems A and B
(P/B 201)
B. Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference Description
SPL-1569 Clamp - Control Cable
(Part #: A20005-9, Supplier: 81205, A/P Effectivity: 737-100, -200,
-200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800, -900,
-900ER, -BBJ)
SPL-1585 Kit - Rigging Pins, All Systems
(Part #: F70207-109, Supplier: 81205, A/P Effectivity: 737-600, -700,
-700C, -700ER, -700QC, -800, -900, -900ER, -BBJ)
C. Location Zones
Zone Area
112 Area Forward of Nose Landing Gear Wheel Well
211 Flight Compartment - Left
212 Flight Compartment - Right
318 Tail Cone Compartment - Right
D. Access Panels
Number Name/Location
112A Forward Access Door
318BR Tailcone Access Door
E. Prepare for the Removal
SUBTASK 27-31-61-860-001
(1) Do this task: Remove Pressure from the Elevator Hydraulic Systems A and B,
TASK 27-31-00-800-802.
SUBTASK 27-31-61-010-001
(2) To get access to the elevator forward quadrant, do this task:
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-31-61
Page 401
Oct 10/2006
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Open this access panel:
Number Name/Location
112A Forward Access Door
SUBTASK 27-31-61-010-002
(3) To get access to the elevator aft quadrant, do this task:
Remove this access panel:
Number Name/Location
318BR Tailcone Access Door
SUBTASK 27-31-61-480-001
(4) Install the rig pin E-5 from the test set rig pin kit, SPL-1585 in the elevator aft quadrant
(Figure 401).
SUBTASK 27-31-61-480-002
(5) Install the rig pin E-1 from the rig pin kit, SPL-1585 in the left side of forward quadrant assembly
(Figure 402).
SUBTASK 27-31-61-020-001
(6) Remove the pitch control wheel steering force transducers from the forward quadrant assembly.
To remove them, do this task: Pitch Force Transducer Removal, TASK 22-11-92-000-801.
F. Forward Quadrant Assembly Removal
　
中國(guó)航空網(wǎng) 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(jī)維護(hù)手冊(cè)3(76)