NOTE:  It is not necessary to use corrosion preventive compound or wet primer when temporarily installing flap.
Do not readjust aftflap.
508 
May 01/99  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-161 Page 404A 

black arrows at WBL 147.200 or hand position inboard flap rigging beam to black stripes located at WBL 147.200 on front and rear spar (View 3, Fig 401).
NOTE:  If black stripes are not on airplane, stencil 0.25 inch wide stripes per tool drawing F80209.
3)  Support flap track and remove bolts attaching track to wing at aft attach point.
4)  Raise or lower flap track to position trailing edge of aftflap within 0.25 inch of theoretical wing chord plane (WCP). Measurement must be made with aftflap deadweight rollers contacting flap track.
5) Position tapered shim between wing and flap track and rotate to fill gap. 6) Mark periphery and bolt hole locations on tapered shim and remove shim. 7) Remove inboard flap rigging tool and install plug screws if required. 8) Temporarily install bolts attaching flap track to wing at aft attach point and
remove track support.
9) Trim tapered shim to size and drill boltholes.

(f)  
Remove temporarily installed trailing edge flap (Ref 27-51-12, R/I).

(g)  
Remove nuts, bolts, bushings, and spacers and remove temporarily installed flap track.

(h)  
Fabricate pressure plate from 0.50 inch minimum thick aluminum alloy plate. Drill three holes to match holes in wing structure.

NOTE:  May use same pressure plate used to bond rub strip to wing lower surface.

(i)  
Bond tapered shim to track upper surface with sealant.

(j)  
Apply pressure plate and attach with three 7/16 inch diameter bolts and tighten nuts 360 to 420 pound-inches.

NOTE:  Tighten nuts before expiration of sealant work life.

(k)  
Allow sealant to cure and remove pressure plate.

(4)  If tapered shim has been damaged, install new tapered shim as follows: (ON AIRPLANES INCORPORATING SB 57-1203)
(a)  
Remove damaged tapered shim and sealant from upper surface of flap track.

(b)  
Bond tapered shim to track upper surface with sealant and apply 100 ±25 pounds per square inch pressure until sealant is cured.

CAUTION:  DO NOT INSTALL TRACK UNTIL SEALANT HAS CURED. SEALANT MAY EXTRUDE FROM FAYING SURFACE.
(5)  
Attach flap track to forward support fitting.

(a)  
Align track with forward support fitting. Ensure that shim is bonded to support fitting. Coat bolts with a thin film of grease and install with countersunk washer under head.

(b)  
Install center bolt and tighten 900 to 1100 pound-inches.

(c)  
Install washer and nut on inboard and outboard bolts. Tighten nuts 800 to 1000 pound-inches.

(d)  
Lockwire adjacent boltheads together.

(6)  
Ensure that bushings are installed in skin at aftflap track support. If not install bushings with primer. Spacers will be located above inboard and outboard bushings.

(7)  
Align track with holes in track support fitting on rear spar.

(8)  
Clean all excess sealant from boltholes before installing bolts.

NOTE:  Excess sealant may bind bolt during tightening and may result in loose bolts.

(9)  
Coat bolts with corrosion preventive compound and install with countersunk washer under head. On airplanes with aluminum rub strips, install torque indicating washer on center bolt. Ensure that bushings at inboard and outboard bolt do not protrude above skin into track support fitting.

(10)
Install washers and nuts finger-tight.

(11)
Tighten inboard and outboard bolts 360 to 420 pound-inches.

(12)
If center bolt does not have torque indicating washer under head, tighten bolt 480 to 600 pound-inches. If center bolt has torque indicating washer under bolthead, tighten center bolt until the outer ring of the torque indicating washer is no longer free to turn, maximum torque is 1300 pound-inches. Check that minimum of one thread extends through nut.

508 
27-51-161 Page 404B  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/99 

NOTE:  Do not reuse torque indicating washer. Use new torque indicating washer before tightening bolt.
If outer ring of torque indicating washer is still free to turn at 1300 pound-inches, the holes are not properly aligned.
(13)
Lockwire adjacent boltheads together.

(14)
Clean area around boltheads.

(15)
Apply fillet of sealant around boltheads.

E.  Restore Airplane to Normal Configuration
　
中國(guó)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(cè) 飛行操縱 FLIGHT CONTROLS 3(51)