737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(17)

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A.  Rudder Sling Assembly - F80025-1
B.  Rudder loading block
(1)  Loading block to distribute loads over a minimum of 5 square inches of rudder trailing edge. Suggested loading blocks: 0.125-inch thick (minimum) by 3 inches by 3 inches, approximately. Wood or fiberglass, suitably padded to prevent skin damage.
C.  Corrosion Preventive Compound - MIL-C-11796, Class 3 (AMM 20-30-21/201)
D.  Rudder Offset Screwdriver - F80190-1 (Preferred) or SE27-2007 (Optional).
E.  Milliohmmeter - 0 to 0.1 ohm range
2.  Prepare for Removal (Fig. 401)
A.  Remove rudder systems A, B, and standby hydraulic power (Ref 27-21-0 MP).
B.  Remove access panels 9512, 9514, and 9515 from vertical fin.
C.  Remove hinge coverplates and fairings from both sides of rudder.
D.  Remove seals and seal attachment plates from both sides of fin at rudder balance weight slots. Use special offset screwdriver fabricated per SE27-2007 , or equivalent to remove screws in radius of seal attachment plates.
E.  Install rudder removal/installation sling.
(1)  
Remove vertical fin trailing edge seal segments covering rudder hinge locations No. 4 and

5.

(2)  
Remove vertical fin hinge segments and rudder hinge bearing bars at hinge locations No. 4 and 5

(3)  
Remove sling attachment bolts from stowed positions in sling sides.

(4)  
Install sling crossarms on rudder at hinge locations No. 4 and 5 with sling attachment bolts.

(5)  
Assemble remainder of sling per Fig. 402.

(6)  
Attach crane hook to sling.

May 01/99 27-21-11 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

G07052 G07054 G07057 G07058
 Rudder Installation  500 
27-21-11 Page 402  Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 15/70 

500  Rudder Installation 
Feb 20/88  Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-21-11 Page 403 

 Rudder Installation  500 
27-21-11 Page 404  Figure 401 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 15/70 

500  Rudder Sling Assembly 
Feb 15/73  Figure 402  27-21-11 
Page 405 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

3.  Remove Rudder (Fig. 401)
A.  Disconnect rudder power control unit and standby actuator from rudder (details A and B).
B.  Disconnect bonding jumpers from hinges No. 2 and 7. codes
C.  Remove hinge pivot bolts at hinges No. 2, 3, and 6. 
D.  Remove hinge pivot bolts at hinges No. 1 and 7.
WARNING:  CRANE MUST BE READY TO SUPPORT WEIGHT OF RUDDER STEADILY WHEN HINGE BOLTS ARE REMOVED.  SUPPORT UPPER AND LOWER ENDS OF RUDDER TO GUARD AGAINST DAMAGE. PERSONNEL MUST EXERCISE CAUTION AGAINST INJURY.
E.  Remove rudder while using guy ropes to keep rudder clear of structure. 
NOTE: Approximate weight of rudder is 257 pounds.
F.  Hoist rudder onto padded temporary support. 
4.  Prepare for Installation
A.  If a rudder with three balance weights is to be used on an airplane made to accept a rudder with only two balance weights, rework the fin with spares kit 65-90353-1.
B.  Remove rudder systems A, B, and standby hydraulic power (Ref 27-21-0 MP).
C.  Check that access panels 9512, 9514, and 9515 are removed from vertical fin, and check that hinge coverplates and fairings on both sides of rudder are removed.
D.  Check for allowable wear at rudder installation points as follows:
(1)  
Check for wear at rudder hinges (Ref 27-21-11 I/C).

(2)  
Check for wear at rudder power control unit attachment to rudder (Ref 27-21-91 I/C).

(3)  
Check for wear at standby rudder actuator attachment to rudder (Ref 27-21-141 I/C).

E.  If not installed, install rudder sling assembly (Fig. 402).
F.  Loosen rudder hinge segment internal-wrenching attach bolts on rudder front spar at all rudder hinges except No. 1 (Ref 27-21-21 R/I). Segments should move freely up and down in shear plates.
G.  Remove seals and seal attachment plates from both sides of fin at rudder balance weight slots, if not removed in par. 2.D. This is necessary to provide adequate clearance at balance weights when positioning rudder.
500 
27-21-11 Page 406  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Apr 01/97 
　
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