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(Part #: T60 1001-C9-1A, Supplier: 0N8U4, A/P Effectivity: 737-ALL)
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)
D. Location Zones
Zone Area
112 Area Forward of Nose Landing Gear Wheel Well
311 Area Aft of Pressure Bulkhead - Left
312 Area Aft of Pressure Bulkhead - Right
324 Vertical Fin - Rear Spar To Trailing Edge
E. Access Panels
Number Name/Location
112A Forward Access Door
113AW Forward Nose Wheel Well Panel
113BW Forward Nose Wheel Well Panel
114AW Forward Nose Wheel Well Panel
114BW Forward Nose Wheel Well Panel
311BL Stabilizer Trim Access Door
324AL Vertical Fin, Aft Fin Access Door
324CL Vertical Fin, Access
F. Prepare for the Adjustment
SUBTASK 27-21-00-860-074-002
(1) Make sure the rudder trim indicator is at the zero unit of trim.
SUBTASK 27-21-00-730-014-002
(2) Do this task: Rudder Pedal Adjustment and Limit Travel Test, TASK 27-21-00-700-813-002.
SUBTASK 27-21-00-860-075-002
(3) Do this task: Remove Pressure from the Rudder Hydraulic Systems A, B, and Standby,
TASK 27-21-00-800-802.
SUBTASK 27-21-00-860-076-002
(4) Do this task: Supply Electrical Power, TASK 24-22-00-860-811.
SUBTASK 27-21-00-860-077-002
(5) Make sure that this circuit breaker is closed:
F/O Electrical System Panel, P6-2
Row Col Number Name
D 19 C00787 FLIGHT CONTROL TRIM CONT RUD
SUBTASK 27-21-00-010-022-002
(6) Open these access doors:
Number Name/Location
112A Forward Access Door
311BL Stabilizer Trim Access Door
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 006-099, 101-122; GUN 001-005, 155-157, 201-999
POST SB 737-27-1253
27-21-00
Config 2
Page 512
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(Continued)
Number Name/Location
324CL Vertical Fin, Access
SUBTASK 27-21-00-010-023-002
(7) Open these access panels:
Number Name/Location
113AW Forward Nose Wheel Well Panel
113BW Forward Nose Wheel Well Panel
114AW Forward Nose Wheel Well Panel
114BW Forward Nose Wheel Well Panel
SUBTASK 27-21-00-480-018-002
(8) Use a 40 - 600 lb cable tensiometer, COM-1554 to get the tension measurement.
G. Rudder Control Cables RA and RB Adjustment
SUBTASK 27-21-00-820-008-002
(1) If you install new rudder control cables RA and RB, then do these steps to stretch the cables:
(a) Operate the rudder trim indicator until you can install the rig pin R-5 in the rudder feel and
centering unit easily.
(b) Adjust the turnbuckles in the cables RA and RB to get a tension of 300 lbf (1334 N) ±20 lbf
(89 N)3 each.
1) Make sure you can install the rig pin R-3 from the rig pin kit, SPL-1585 freely in the
captain’s rudder forward quadrant.
(c) Remove the rig pins R-3 and R-5.
(d) Adjust the pressure seals at the aft pressure bulkhead with the control cables RA and RB.
To adjust them, do this task: Location of the Flight Control Cables Air Pressure Seals,
TASK 27-09-17-860-801.
(e) Make sure the cables RA and RB do not touch the pulley or the quadrant flanges for the
total cable travel.
(f) Make sure the cables RA and RB are in less than 2 degrees of the plane of the pulley or the
quadrant.
(g) Make sure you install the cables through the grommets in the structure.
(h) Make sure that the cables do not move from the neutral rig position.
(i) Make sure that the pulleys turn freely with sufficient clearance with the guards.
(j) Remove the nut [50], washer [49], washer [48], and bolt assembly [47] to disconnect the
standby rudder PCU control rod [34] from the rudder control torque tube [33].
(k) Remove the nut [45], washer [44], washer [43], and bolt assembly [42] to disconnect the
main rudder PCU control rod [36] from the rudder control torque tube [33].
(l) Move the rudder pedals 25 times through full travel.
(m) Connect the main rudder PCU control rod [36] to the center crank [41].
1) Install the bolt assembly [42] with the bolt head end up and washer [43].
2) Tighten the outer bolt of the bolt assembly [42] to 70 in-lb (7.9 N
m) -- 85 in-lb (9.6 N
m).
3) Install the washers [44] and nut [45].
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 006-099, 101-122; GUN 001-005, 155-157, 201-999
POST SB 737-27-1253
27-21-00
Config 2
Page 513
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
CAUTION: DO NOT TIGHTEN THE OUTER BOLT OF THE BOLT ASSEMBLY [42]
　
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本文鏈接地址：737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL飛機維護手冊2(52)