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727.00 - Left
134 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Right
D. Procedure
SUBTASK 27-61-31-020-008
(1) Disconnect the Spoiler Ratio Changer Input Rod from the upper control crank.
SUBTASK 27-61-31-020-009
(2) Use this tool to check for wear on the parts of the spoiler ratio changer input rod:
(a) micrometer (0-1 Inch, readable to 1/1000 Inch), STD-1096
(b) readable to 1/1000 inch vernier 0 - 6 inch caliper, STD-1097
SUBTASK 27-61-31-020-010
(3) Examine the parts of the spoiler ratio changer rod for worn areas:
(a) Remove the parts to be checked.
(b) Measure the parts as necessary with the micrometer (0-1 Inch, readable to 1/1000 Inch),
STD-1096 and readable to 1/1000 inch vernier 0 - 6 inch caliper, STD-1097.
(c) Compare the dimensions you measured with the permitted wear dimensions that follow.
(d) If the parts are not in the tolerance, replace or repair the part as required.
Table 601/27-61-31-993-801
NAME OF THE PARTS
THAT ARE IN CONTACT
DIM.
DIAMETER DESIGN LIMITS WEAR LIMITS
MINIMUM
inches/mm
MAXIMUM
inches/mm
PERMITTED
MAXIMUM I.D./
MINIMUM O.D. OF
WORN PART
MINIMUM
SERVICE
DIAMETRIC
CLEARANCE
BEARING I.D. 0.2497 in 0.2500 in 0.2505 in
6.342 mm 6.350 mm 6.363 mm 0.0020 in
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(Continued)
NAME OF THE PARTS
THAT ARE IN CONTACT
DIM.
DIAMETER DESIGN LIMITS WEAR LIMITS
MINIMUM
inches/mm
MAXIMUM
inches/mm
PERMITTED
MAXIMUM I.D./
MINIMUM O.D. OF
WORN PART
MINIMUM
SERVICE
DIAMETRIC
CLEARANCE
BOLT O.D. 0.2485 in 0.2495 in 0.2481 in 0.051 mm
6.312 mm 6.337 mm 6.302 mm
SUBTASK 27-61-31-020-011
(4) Connect the spoiler ratio controller input rod to the upper control crank.
------------------------- END OF TASK ---------------------------
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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Spoiler Ratio Changer Wear Limits
Figure 601 (Sheet 1 of 2)/27-61-31-990-802
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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Spoiler Ratio Changer Wear Limits
Figure 601 (Sheet 2 of 2)/27-61-31-990-802
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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SPOILER CONTROL QUADRANT - REMOVAL/INSTALLATION
1. General
A. This procedure has these tasks:
(1) A removal of the spoiler control quadrant.
(2) An installation of the spoiler control quadrant.
(3) A functional test of the spoiler control quadrant.
TASK 27-61-41-000-801
2. Spoiler Control Quadrant Removal
(Figure 401)
A. References
Reference Title
25-22-00-000-801 Passenger Seat Removal (P/B 401)
25-27-15-000-801 Carpet Removal (P/B 401)
53-21-00-000-801 Passenger Cabin Floor Panel Removal (P/B 401)
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-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
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
210 Subzone - Control Compartment - Body Station 178.00 to Body
Station 259.50
231 Forward Passenger Compartment - Forward Entry Door to Sta 663.75
- Left
232 Forward Passenger Compartment - Forward Entry Door to Sta 663.75
- Right
D. Access Panels
Number Name/Location
112A Forward Access Door
E. Prepare for the Removal
SUBTASK 27-61-41-860-001
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737-600-700-800-900 飞机维护手册6 AIRCRAFT MAINTENANCE MANUA(43)
