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31-51-01-820-801 Flap Landing Warning Switch Adjustment (P/B 401)
53-21-00-400-801 Passenger Cabin Floor Panel Installation (P/B 401)
SWPM 20-60-03 Standard Wiring Practices Manual
B. Consumable Materials
Reference Description Specification
A00247 Sealant - Pressure And Environmental - Chromate
Type
BMS5-95
A02315 Sealant - Low Density, Synthetic Rubber. 2 Part BMS5-142
C00913 Compound - Nondrying Resin Mix Corrosion
Inhibiting Material
BMS3-27
D00633 Grease - Aircraft General Purpose BMS3-33
G50171 Compound - Corrosion Inhibiting Compound,
Interior Application - D5026NS or ZC-026
C. Expendables/Parts
AMM Item Description AIPC Reference AIPC Effectivity
2 Clip 27-51-00-21-005 GUN 001-099, 155-157,
201-999
27-51-00-24-005 GUN 101-122
4 Pin 27-51-00-21-150 GUN 001-099, 155-157,
201-999
27-51-00-24-125 GUN 101-122
5 Quadrant 27-51-62-01-020 GUN 001-007, 014-026,
109-120, 155-157, 201-
999
6 Pin 27-51-62-01-010 GUN 001-007, 014-026,
109-120, 155-157, 201-
999
8 Pin 27-51-62-01-005 GUN 001-007, 014-099,
109-122, 155-157, 201-
999
9 Unit assembly 27-51-61-02-050 GUN 001-007, 014-030,
109-122, 155-157, 201-
999
10 Strap 27-51-00-21-155 GUN 001-099, 155-157,
201-999
27-51-00-24-120 GUN 101-122
47 Pin 27-51-61-01-080 GUN 001-007, 014-030,
109-122, 155-157, 201-
999
49 Clip 27-51-00-21-010 GUN 001-099, 155-157,
201-999
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AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-61
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(Continued)
AMM Item Description AIPC Reference AIPC Effectivity
49 (cont.) 27-51-00-24-130 GUN 101-122
D. Location Zones
Zone Area
114 Area Above and Outboard of Nose Landing Gear Wheel Well - Right
134 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Right
212 Flight Compartment - Right
240 Subzone - Passenger Compartment - Body Station 663.75 to Body
Station 1016.00
E. Access Panels
Number Name/Location
112A Forward Access Door
114AC Fwd Nose Wheel Well Upper Access Panel
F. Prepare for the Installation
SUBTASK 27-51-61-820-001
(1) Install the rig pin [38] in the flap control unit assembly [9] (Figure 402):
NOTE: This will make sure the flap control unit assembly [9] is in the adjusted position.
(a) Remove the screws [36] and washers [55] and the lower pan [37] from the flap control unit
assembly [9].
(b) Install the rig pin through the cam follower arm and the valve cam.
SUBTASK 27-51-61-420-001
(2) If they are not installed, install the cables [48] WFFA and WFFB on the flap control unit
assembly [9]:
(a) Remove the bolts [45], washers [46] and the drum guard [44] from the flap control unit
assembly [9].
(b) Put the cables [48] in their location on the cable drum [43].
NOTE: Wrap cable WFFA around the cable drum [43] 1/2 turns. Wrap cable WFFB around
the cable drum [43] 1 1/2 turn.
(c) Install the cotter pins [47] to hold the cables [48] on the cable drum [43].
(d) Put the drum guard [44] in its location on the flap control unit assembly [9].
(e) Apply compound, C00913 to the shank and threads of the bolts [45].
(f) Install the bolts [45] and washers [46] to attach the drum guard [44].
G. Flap Control Unit Installation
SUBTASK 27-51-61-420-002
(1) Install the flap control unit assembly [9]:
(a) Make sure the area around four of the seven holes for the bolts [15] on the flap control unit
assembly [9] is clean for electrical bonding.
(b) Apply a layer of sealant, A00247 to the mating surface of the flap control unit assembly [9]
and the structure.
(c) Apply a layer of compound, C00913 to the shank and threads of the bolts [41].
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-61
Page 413
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(d) Lift the flap control unit assembly [9] to its position.
(e) Install the bolts [41] and washers [43] to attach the flap control unit assembly [9].
(f) Install the bolts [15] and washers [14] from above to attach the flap control unit assembly [9]
(Figure 401).
(g) Make sure the resistance between the flap control unit assembly [9] and the structure is a
maximum of 8 milliohms.
(h) Apply a bead of sealant, A02315 to the heads of the bolts [15].
SUBTASK 27-51-61-420-003
(2) Install the quadrant [5] on the flap control unit assembly [9] (Figure 401):
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737-600-700-800-900 飞机维护手册5 AIRCRAFT MAINTENANCE MANUA(99)
