(4)  
Elevator tab lock mechanism upper and lower access panels. Panels are located at elevator inboard leading edge (Fig. 401).

(5)  
Tab pushrod access panel (Fig. 401).

C.  Set horizontal stabilizer B dimension at 41.57 +0.05 inches, using trammel bar (Fig. 402).
D.  Install rigging pin E-5 in aft quadrant.
3.  Remove Elevator Tab Lock Linkage
A.  Remove elevator tab lock actuator upper and lower mounting bolts (Fig. 401).
B.  Withdraw actuator from tab lock linkage. Tie actuator to adjacent structure to prevent interference when removing linkage.
500 
Feb 20/88  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-121 Page 401 

G09802G09859 G09977G09993
Elevator Tab Lock Linkage Installation  527 
27-31-121  Figure 401 (Sheet 1)  May 01/74 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

527  Elevator Tab Lock Linkage Installation 
May 01/74  Figure 401 (Sheet 2)  27-31-121 
Page 403 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Elevator Tab Lock Linkage Installation  527 
27-31-121  Figure 401 (Sheet 3)  May 01/74 
Page 404 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500  Stabilizer Trim Jackscrew Setting 
Aug 15/68  Figure 402  27-31-121 
Page 405 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

C.  Remove elevator tab lock linkage bolt retainer shield to obtain access for removal of frame attach bolts.
D.  Remove tab pushrod aft mounting bolt (two places).
E.  Disconnect return springs.
F.  Remove two mounting bolts securing forward end of frame to stabilizer structure.
G.  Remove two bolts attaching aft end of frame to elevator front spar (View 1, Fig. 401).
H.  Remove elevator tab lock linkage with tab pushrods attached.
4.  Prepare for Installation
A.  Check that return springs are disconnected.
B.  Remove elevator systems A and B hydraulic power (Ref 27-31-0, MP).
C.  Check that rigging pin E-5 is installed in aft quadrant.
D.  Check for allowable wear at elevator tab lock linkage installation points (Ref 27-31-121, I/C).
5.  Install Elevator Tab Lock Linkage
CAUTION:  IF THE NUTS ARE NOT TORQUED PROPERLY, THEN THE PUSHRODS CAN BECOME DETACHED AND CAUSE DAMAGE TO THE ELEVATORS AND STABILIZERS.
A.  Position linkage with tab pushrods installed inside horizontal stabilizer (Fig. 401).
(1)  Torque tab pushrod nuts to 30-50 pound-inches. If castellated nuts are used, make sure torque remains at 30-50 pound-inches after alignment of the nut castellations and bolt cotter pin holes. If non-castellated nuts are used, torque to 50-80 pound-inches.
B.  Secure aft end of frame to elevator front spar. Install inboard bolt with head facing outboard, and outboard bolt with head facing inboard, with washers as required. Tighten nut on inboard bolt 40 to 55 pound- inches (View 1, Fig. 401).
C.  Attach forward end of frame to stabilizer structure. Install mounting bolts with a washer under each nut (Detail C, Fig. 401).
D.  Refer to detail A, Fig. 401, and install tab pushrods as follows:
(1)  
Install tab pushrod aft mounting bolts. Install outboard bolt with head facing outboard and inboard bolt with head facing inboard.

(2)  
Install nut and washer on each tab pushrod aft mounting bolt.

27-31-121 May 01/99 Page 406
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

E.  Install retainer shield.
F.  Connect return springs.
G.  Install tab lock actuator, shown in Fig. 401, as follows:
(1)  
Position actuator within tab lock linkage.

(2)  
Install upper mounting bolt with head facing outboard. Place special washer on inboard side of actuator upper terminal and a standard washer under nut and bolthead.

(3)  
Install lower mounting bolt with head facing inboard and a washer placed under the nut.

H.  Remove rigging pin E-5.
I.  Adjust and test elevator tab pushrods and linkage per 27-31-0 A/T.
6.  Restore Airplane to Normal
A.  Close or replace all access panels.
B.  Restore airplane to normal hydraulic configuration (Ref 27-31-0 MP).
527 
Feb 20/93  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-121 Page 407/408 
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 2(109)