(3)
At stabilizer trailing edge rib No. 2, adjust bulb seal to maintain compression of 0.00 to
0.03 inch (Fig. 502, View H).
(4)
At stabilizer trailing edge ribs No. 1, 2, 3 and 4, adjust bulb seals to maintain compression of 0.10 + 0.04 inch (Fig. 502, Views G, I and J).
(5)
At stabilizer trailing edge rib No. 1 adjust bulb seal on nose rib to maintain compression of
0.1 + 0.10/-0.040 inch (Fig. 502, View I).
(6)
At stabilizer trailing edge rib No. 4 adjust bulb seal on nose rib to maintain compression of
0.03 + 0.03 inch (Fig. 502, View J).
(7)
At stabilizer trailing edge ribs No. 1, 2, 3 and 4 adjust bulb seals between balance panel and stabilizer trailing edge rib as follows (Fig. 502, View L):
(a)
Loosen seal mounting bolts and adjust seal to provide 0.02 + 0.01 inch clearance between seal and rib.
(b)
Tighten seal mounting bolts and recheck seal clearances.
(8)
At stabilizer trailing edge ribs No. 1, 2, 3 and 4 adjust flat seals between balance panel idler hinge and stabilizer trailing edge rib as follows (Fig. 502, View L).
(a)
Loosen seal mounting bolts and adjust seal to provide 0.01 (+ 0.06/-0.00) inch clearance between seal and rib.
(b)
Before tightening seal mounting bolts, check 0.20-inch gap exists between idler hinge flat seal and balance panel bulb seal.
(c)
Tighten seal mounting bolts and recheck seal clearances.
(9)
At the elevator inboard rib, adjust elevator to body seals between elevator and tail cone as follows (Fig. 502, View K).
(a)
Loosen seal mounting bolts and adjust seal to provide 0.02 +0.01 inch clearance between seal and tail cone.
(b)
Tighten seal mounting bolts and recheck seal clearance.
500
27-31-171 Page 506 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 01/95
E. At the elevator inboard rib No. 1; adjust the gap between the bulb seal on the stabilizer and the elevator (Fig. 502, Sheet 3):
(1)
Loosen the adjustment screw.
(2)
Adjust the screw to have a clearance of 0.00 + 0.03 inch gap between the bulb seal on the stabilizer and the elevator.
(3)
Tighten the screw.
(4)
Make sure the clearance between the bulb seal on the stabilizer and the elevator is 0.00
+ 0.03 inch.
F. Restore Airplane to Normal
(1)
Install access panels removed in steps B.(4).
(2)
Restore airplane to normal hydraulic configuration (Ref 27-31-0).
500
Aug 01/95 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-171 Page 507
CONTROL COLUMN SUPPORT BEARING - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
E-1 E-5 -11 -11 0.309-0.311 0.309-0.311 6.7 ±0.25 6.7 ±0.25 FWD Control Quadrant Aft Control Quadrant
2. Prepare for Removal
A. Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
B. Remove control column adjacent to support bearing requiring removal (Ref 27-31-51 R/I)
C. If not installed, install rigging pin E-1 in forward quadrant and E-5 in aft quadrant.
D. Open stabilizer jackscrew compartment access door.
3. Remove Control Column Support Bearing
A. Release tension in elevator control cables at turnbuckles in stabilizer jackscrew compartment. Do not disconnect turnbuckles.
B. Support elevator forward control quadrant and remove inboard coupling by removing two coupling bolts (Fig. 401).
CAUTION: ENSURE THAT FORWARD QUADRANT IS ADEQUATELY SUPPORTED BEFORE AND AFTER COUPLING IS REMOVED OTHERWISE STRUCTURAL DAMAGE MAY RESULT.
C. Withdraw connector from bearing housing (detail A).
D. Remove four mounting bolts attaching bearing housing to structure.
E. Remove bearing housing and shims from airplane (detail A).
F. Rotate bearing at right angles to housing. Align bearing with slots in housing and withdraw bearing.
4. Prepare for Installation
A. Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
B. Check that rigging pin is installed in forward quadrant and that rigging pin E-5 is installed in aft quadrant.
500
Feb 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-181 Page 401
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊 飛行操縱 FLIGHT CONTROLS 2(123)
