H. Following engine control cable maintenance, observe these requirements:
(1)
Control cables should not be deflected by fairleads, rub strips, or grommets from the rigged or normal operation position.
(2)
All pulleys should rotate freely with no interference with cable guards.
(3)
Control cables should not contact pulley or drum flanges for entire travel of cable.
(4)
Control cable pressure seals should be adjusted after cable rigging to eliminate any binding or deflection of cables (Ref 20-10-101, Control Cable Air Pressure Seal - Removal Installation).
K11085 K11434
Engine Control System Adjustment Locations 5C8
76-11-0 Figure 501 (Sheet 1) May 01/99
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
5C8 Engine Control System Adjustment Locations
Jun 20/85 Figure 501 (Sheet 2) 76-11-0
Page 503
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
2. Engine Control System Adjustment
A. Forward Thrust Control System Adjustment
(1)
Equipment and Materials
(a)
Tensiometer - 0- to 125-pound capacity
(b)
Rig Pin Kit - F70207-3, -52 or -61 1) Type 1 - F70207-8 (2 required), 0.311 +0.000/-0.002-inch diameter rod 2) Type 2 - Fuel Control Unit Idle Rig Pin - F70207-50, 0.0940 (+0.0000/-0.0005)-
inch thick x 0.20-inch wide x 2.0-inch long flat rig pin made from hardened steel 3) Type 3 - F70207-23, 0.248 +0.000/-0.002-inch diameter rod
(c)
Airplane Control Surfaces Protractor - 4MIT65B80307-1 or F52485-500
(d)
Protractor Adapter, Cross-Shaft - 2MIT65-45109-22
(e)
Protractor Adapter, Thrust Lever - F72952-15 (Preferred), F72952-2 (Optional)
(f)
Spring scale - 0- to 30-pound capacity
(2)
Prepare engine forward thrust control system for adjustment/test.
(a)
Remove engine side removable cowl panels (Ref Chapter 71, Removable Cowl Panels).
(b)
Remove access door No. 6301 (left wing) or No. 6401 (right wing) from wing leading edge above wing-to-engine fairing (Ref Chapter 12, Access Doors and Panels).
(c)
Open electronic equipment access door No. 1201. Remove forward cargo ceiling panels as required for turnbuckle access.
(d)
Extend forward airstairs (Ref Chapter 52, Forward Airstairs and Door).
(e)
When adjusting control cables, leading edge flaps must be extended to provide access to control cable turnbuckles in wing leading edge. Extend flaps and install leading edge flap locks (Ref 27-81-0 MP).
WARNING: REFER TO 27-81-0 MP FOR LOCK INSTALLATION PROCEDURE. FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.
514
76-11-0 Page 504 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/00
EFFECTIVITY
GJ ALL EXCEPT B-2509, B-2510
K93571
5C8 Drum and Friction Brake Rig Pin Location
Jun 20/85 Figure 502 (Sheet 1) 76-11-0
Page 504A/504B
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
EFFECTIVITY
BA G-BKYA AND ON GJ B-2509, B-2510
579 Autothrottle Clutch or Servomechanism Rig Pin Location
Oct 20/84 Figure 502 (Sheet 2) 76-11-0
Page 505
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(3) Adjust thrust control cables.
(a)
Disconnect engine thrust push-pull cable from thrust crank on left side of engine cross-shaft.
(b)
Install Type 1 rig pin through engine thrust drum and its support bracket located above engine at wing front spar (Fig. 503).
(c)
Place thrust lever at idle stop and install a Type 1 rig pin through the drum and brake support into the drum and friction brake assembly (Fig. 502, Sheet 1) or install a Type 3 rig pin into torque switch mechanism quadrant (Sheet 2), as applicable.
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