(2)  
Temporarily install flap track as follows:

(a)  
Align track with forward support fitting and install bushings, spacers, bolt, washers and nut (View 2, Fig. 401).

NOTE: Rub strip must be installed on lower surface prior to fitting shim.

(b)  
On airplanes with phenolic rub strip, tighten nut as follows:

1)  If forward attach bolt has a castle nut, tighten 350 to 600 pound-inches, and install cotter pin. If forward attach bolt is 7/16 inch diameter with self locking nut, tighten 260 to 425 pound-inches. If forward attach bolt is 3/8 inch diameter with self locking nut, tighten 300 to 500 pound-inches.

(c)  
On airplanes with aluminum rub strip, tighten nut as follows: 1) AIRPLANES WITHOUT SB 57-1203 AND GUN B-2501-B-2505; on inboard

track, tighten nut 270 to 300 pound-inches. On outboard track, tighten nut 350 to 600 pound-inches.

(d)  
Position flap track and temporarily install bushings, bolts, washers and nut at aft attach point (Section A-A).

(3)  
Temporarily install trailing edge flap (Ref 27-51-72 R/I).

NOTE:  It is not necessary to use corrosion preventive compound or wet primer when temporarily installing flap. Do not readjust aftflap.

(4)  
Determine flap track shim thickness as follows:

(a)  
Check that flaps are in fully retracted position.

(b)  
Remove plug screws and attach outboard flap rigging tool at location marked by black arrows at WBL 228.5 or hand position outboard flap rigging beam to black stripes located at WBL 228.5 on front and rear spar (View 2, Fig. 401).

NOTE:  If black stripes are not on airplane, stencil 0.25 inch wide stripes per tool drawing F80209.

(c)  
Support flap track and remove bolts attaching track to wing at aft attach point.

(d)  
Raise or lower flap track to position trailing edge of aftflap within 0.00 to 0.25 inch below theoretical wing chord plane (WCP). Measurement must be made with aftflap deadweight rollers contacting flap track while applying 30 pound upward force against minimum 4.0 x 6.0 inch aluminum plate at aft edge of aftflap near rigging tool.

(e)  
Deleted.

(f)  
Position tapered shim between wing and flap track and rotate to fill gap.

(g)  
Mark periphery and bolt hole locations on tapered shim and remove shim.

(h)  
Remove outboard flap rigging tool and install plug screw if required.

(i)  
Temporarily install bolts attaching flap track to wing at aft attach point and remove track support.

(j)  
Trim tapered shim to size and drill bolt holes.

(5)  
Remove temporarily installed trailing edge flap (Ref 27-51-72 R/I).

(6)  
Remove nuts, bolts, bushings, and spacers and remove temporarily installed flap track.

(7)  
Bond Tapered shim to flap track upper surface with sealant.

505 
27-51-151 Page 404  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/99 

NOTE:  Install track before expiration of sealant work life.
5C8 
May 01/99  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-151 Page 405 

C.  If tapered shim has been damaged, install new tapered shim as follows: (ON AIRPLANES INCORPORATING SB 57-1203)
(1)  
Remove damaged tapered shim and sealant from upper surface of flap track.

(2)  
Bond new tapered shim to flap track upper surface with sealant.

NOTE:  Install track before expiration of sealant work life.
D.  Align track with forward support fitting and secure as follows:
(1)  
Ensure that one bushing is in each forward lug of flap track and two bushings are in forward support fitting.

(2)  
Position spacer in forward support fitting.

(3)  
Coat bolt with corrosion preventive compound and install with countersunk washer under bolt head.

(4)  
On airplanes with phenolic rub strip, install washer under nut and tighten nut as follows:

(a)  If forward attach bolt has a castle nut, tighten 350 to 600 pound-inches and install cotter pin. If forward attach bolt is 7/16 inch diameter with self locking nut, tighten 260 to 420 pound-inches. If forward attach bolt is 3/8 inch diameter with self locking nut, tighten 300 to 500 pound-inches.

(5)
On airplanes with aluminum rub strip, install washer under nut and tighten nut as follows:

(a)  
AIRPLANES WITHOUT SB 57-1203 AND GUN B-2501-B-2505; on inboard track, tighten nut 270 to 300 pound-inches. On outboard track, tighten nut 350 to 600 pound-inches.
　
中國航空網 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 3(47)