(a) Check that opposite midflaps are symmetrical within 1 degree. Measure along lower surface at midspan of midflap using protractor. If angles are not within limits adjust flap transmissions (Ref 27-51-01, Adjust Flap Transmissions).
NOTE: If flaps are readjusted repeat step (8) thru (9).
(10)
Extend trailing edge flaps then position flap control lever in FLAP UP detent to retract flaps so that angular clearance between ball screw upstop and jackscrew upstop is 170 to 190 degrees (1/2 turn +10 degrees) turn of jackscrew.
(11)
After waiting 2 minutes, remove hydraulic system A power (Ref 27-51-0).
(12)
Check that misfair between wing lower trailing edge panel and lower surface of midflap does not exceed limits shown in section C-C. If misfair exceeds limits, adjust trailing edge panel tie rods to reduce it to as near zero as possible.
(13)
With flaps in full up position, check that clearance of seal support (on wing lower trailing edge panel) with respect to leading edge of midflap is per section C-C. If adjustment is necessary, loosen seal support retaining screws, position seal support to obtain clearance, and tighten retaining screws. Fill gap between skin and seal support with aerodynamic smoother.
NOTE: If gap between edge of trailing edge panel and bottom surface of seal support is more than shown in section C-C, it should be filled with aerodynamic smoother. If existing gap is filled, smoother must be removed before adjustment.
(14)
Check that clearance between nacelle fairing closure door and guide on foreflap torque tube is per section A-A, Fig. 401. If adjustment is necessary loosen bolt on guide and position guide to required clearance.
501
27-51-12 Page 410 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/89
S. Install hinged flap (Ref AMM 27-51-51, Removal /Installation).
T. Adjust flap drive screw preload as follows (Fig. 403):
(1)
Provide hydraulic system A power (Ref AMM 27-51-0).
(2)
Place flap control lever at 1-unit detent, wait 5 minutes, then remove system A hydraulic power (Ref AMM 27-51-0).
(3)
Check fit of flap outboard drive screw end fitting (1) in preload pad (2). Check that radial gap between screw end fitting and preload pad is as shown in view 1 (Fig. 403) for entire surface of pad. If necessary, adjust preload as follows:
(a)
Remove retaining two bolts (3) from gimbal shaft (5).
(b)
Rotate and shift indexing plate (4) as necessary to position drive screw end fitting. Rotate indexing plate to the nearest aligning hold with the bearing support fitting (7).
(c)
Adjust thickness of shims (6) to fill gap between indexing plate (4) and bearing support fitting (7) and install bolts (3).
(d)
Recheck that clearance between pad and screw end fitting is as shown in View 1.
(4)
With flaps at 1-unit position, check position of flap inboard drive screw (jackscrew) end fitting (11) as follows:
(a) Check location of jackscrew as follows (Fig. 404): 1) Locate point A on outside diameter of drive screw by measuring aft from ball
bearing nut. 2) Check that distance from point A to midflap rib fitting is as shown.
500
May 20/82 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-12 Page 411
G12609G12262 G12285
Inboard Flap Drive Screw Preload Adjustment 500
27-51-12 Figure 403 (Sheet 1) May 15/78
Page 412
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
501 Inboard Flap Drive Screw Preload Adjustment
Feb 01/74 Figure 403 (Sheet 2) 27-51-12
Page 413
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Inboard Drive Screw Rigging 501
27-51-12 Figure 404 May 20/82
Page 414
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(b)
If necessary, relocate jackscrew as follows: 1) Remove gimbal shaft retaining bolts (14, Fig. 403) from end of inboard midflap
torque shaft (12). Pull gimbal shaft (13) inboard just enough to free shims (15). 2) Adjust total thickness of shims (15) to position point A as shown on Fig. 404. 3) Replace bolts (14) and recheck position as in step (a).
(c)
Check for clearance of 0.13 to 0.15 inch between jackscrew end fitting (11, Fig. 403) and preload pad (10). If necessary, adjust clearance as follows: 1) Loosen preload pad retaining bolts (9). 2) Shift preload pad vertically to obtain clearance between pad and jackscrew end
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 3(9)
