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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. Expendables/Parts
AMM Item Description AIPC Reference AIPC Effectivity
20 Quadrant 27-21-61-01-060 GUN ALL
24 Pin 27-21-61-01-005 GUN ALL
D. Location Zones
Zone Area
112 Area Forward of Nose Landing Gear Wheel Well
311 Area Aft of Pressure Bulkhead - Left
324 Vertical Fin - Rear Spar To Trailing Edge
E. Access Panels
Number Name/Location
112A Forward Access Door
113AC Fwd Nose Wheel Well Upper Access Panel
114AC Fwd Nose Wheel Well Upper Access Panel
311BL Stabilizer Trim Access Door
323FL Vertical Fin, Access
323GL Vertical Fin, Access
324CL Vertical Fin, Access
F. Rudder Aft Quadrant Installation
(Figure 402)
SUBTASK 27-21-61-860-002
(1) Make sure that pressure to the rudder hydraulic systems A, B, and Standby is removed. To
remove it, do this task: Remove Pressure from the Rudder Hydraulic Systems A, B, and
Standby, TASK 27-21-00-800-802.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-21-61
Page 409
Oct 10/2006
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
SUBTASK 27-21-61-420-001
(2) Install the rudder aft quadrant:
(a) Put the washer [21], plate [18], and the right bearing housing [27] on the right side of the
quadrant shaft [17].
1) Make sure the countersunk side of the washer [21] is toward the center of the quadrant
shaft [17].
(b) Install the washer [22] and nut [23] on the right side of the quadrant shaft [17].
1) Tighten the nut [23] to 190-280 pound-inches (21.5-31.6 newton-meters).
(c) Install a new pin [24].
(d) Put all the parts through the access hole.
(e) Slide the quadrant [20] onto the quadrant shaft [17].
(f) Install the bolts [4], spacers [8], washers [5], washers [6], and nuts [7] to attach the
quadrant [20] to the quadrant shaft [17].
(g) Put the left housing bearing [19] on the left side of the quadrant shaft [17].
(h) Put the quadrant shaft [17] and plate [18] in its position.
(i) Install the bolts [25] and washers [26] to attach the left bearing housing [19] and right
bearing housing [27] to the airplane structure.
SUBTASK 27-21-61-420-002
(3) Turn the quadrant shaft [17].
(a) Make sure that the quadrant shaft [17] moves freely in the left bearing housing [19] and
right bearing housing [27].
SUBTASK 27-21-61-420-003
(4) Connect the cable RA [2] and cable RB [1] to the quadrant [20].
(a) Install the cable retainers [10], bolts [9], washers [11], and nuts [12].
SUBTASK 27-21-61-420-004
(5) Tighten the turnbuckles [3] until the cable RA [2] and RB [1] are not loose.
SUBTASK 27-21-61-420-005
(6) Install the bolt [13], washer [14], and nut [15] to connect the control rod [16] to quadrant [20].
SUBTASK 27-21-61-480-002
(7) Install the rig pin R-5 from the rig pin kit, SPL-1585 to the rudder feel and centering unit
(Figure 402).
SUBTASK 27-21-61-820-001
(8) Adjust the cables RA and RB. To adjust them, do this task: Rudder Control Cables RA and RB
Adjustment, TASK 27-21-00-820-808-001 or Rudder Control Cables RA and RB Adjustment,
TASK 27-21-00-820-808-002.
SUBTASK 27-21-61-080-001
(9) Remove the rig pins R-3 and R-4 from the rudder forward quadrants (Figure 401).
SUBTASK 27-21-61-080-002
(10) Remove the rig pins R-5 from the rudder feel and centering unit.
SUBTASK 27-21-61-710-001
(11) Do this task: Rudder Travel Test, TASK 27-21-00-700-817-001 or Rudder Travel Test,
TASK 27-21-00-700-817-002.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-21-61
Page 410
Oct 10/2006
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
G. Put the Airplane Back to Initial Condition
SUBTASK 27-21-61-410-004
(1) Close this access panel:
Number Name/Location
112A Forward Access Door
SUBTASK 27-21-61-940-001
(2) Install these access panels:
Number Name/Location
113AC Fwd Nose Wheel Well Upper Access Panel
114AC Fwd Nose Wheel Well Upper Access Panel
and .
SUBTASK 27-21-61-410-001
(3) Close this access panel:
Number Name/Location
324CL Vertical Fin, Access
SUBTASK 27-21-61-410-002
(4) Close this access panel:
Number Name/Location
　
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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(98)