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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Control Column Installation
Figure 401 (Sheet 2 of 6)/27-31-51-990-801
737-600/700/800/900
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EFFECTIVITY
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Control Column Installation
Figure 401 (Sheet 3 of 6)/27-31-51-990-801
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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Page 405
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D633A101-GUN
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Control Column Installation
Figure 401 (Sheet 4 of 6)/27-31-51-990-801
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AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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Control Column Installation
Figure 401 (Sheet 5 of 6)/27-31-51-990-801
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EFFECTIVITY
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Control Column Installation
Figure 401 (Sheet 6 of 6)/27-31-51-990-801
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TASK 27-31-51-400-801
3. Control Column - Installation
(Figure 401)
A. References
Reference Title
23-51-04-400-801 Control Wheel PTT Switch Installation (P/B 401)
24-22-00-860-811 Supply Electrical Power (P/B 201)
27-31-00-700-804 Elevator Travel Limit - Test (P/B 501)
27-31-00-700-807 Manual Mode - Test (P/B 501)
27-31-00-700-808 Control Column Travel and Centering - Test (P/B 501)
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-1680 Protractor - Assembly, Control Column
(Part #: 4MIT65B80307-1, Supplier: 81205, A/P Effectivity: 737-100,
-200, -200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800,
-900, -900ER, -BBJ)
(Part #: A27021-29, Supplier: 81205, A/P Effectivity: 737-100, -200,
-200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800, -900,
-900ER, -BBJ)
C. Consumable Materials
Reference Description Specification
A00247 Sealant - Pressure And Environmental - Chromate
Type
BMS5-95
D. Location Zones
Zone Area
112 Area Forward of Nose Landing Gear Wheel Well
211 Flight Compartment - Left
212 Flight Compartment - Right
E. Access Panels
Number Name/Location
112A Forward Access Door
F. Control Column Installation
SUBTASK 27-31-51-420-001
(1) Put the control column [1] in its position.
(a) Set the control wheel to the neutral position to engage the spade [4] with the clevis [6].
SUBTASK 27-31-51-480-002
(2) Use the control column assembly protractor, SPL-1680 to set the control column to 6.9 +/- 0.8
degrees forward of a vertical line from the floor (Figure 401).
SUBTASK 27-31-51-420-002
(3) Install the control column [1]:
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(a) Engage the face splines on the control column [1] with the splines on the forward quadrant
connector [10].
(b) Install the outboard couplings [9]:
1) Install the bolts [12], washers [8], and nuts [7] on the outboard couplings [9].
NOTE: Make sure that you use the correct bolts.
(c) Do these steps to make the clearances equal at each end of each outboard coupling:
1) Tighten the bolts [12] to 50 pound-inches (5.7 newton-meters) of torque.
2) Tighten the one bolt and then the other to 50 +30 / -0 in-lb (5.6 +3.4 / -0.0 Nm) in
approximately 10 in-lb (1.1 Nm) increments until you get the clearances equal to +/-
0.03 inch (+/- 0.8 millimeter) of each other.
(d) Make sure that the control column angle is 6.9 +/- 0.8 degrees forward of the vertical line
from the floor.
(e) Connect the electrical wire [5] and electrical wire [11] to the terminal strip in the lower nose
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737-600-700-800-900 AIRCRAFT MAINTENANCE MANUAL飛機維護手冊3(72)
