(d)
New cables installed:
1) Rig cables to 100 pounds tension.
2) Cycle system 25 times.
3) Return start lever to cutoff detent.
(e)
New cables or rerigged cables:
514
Feb 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 76-11-0 Page 515
Reverse Thrust Detent Adjustment 577
76-11-0 Figure 507 Feb 20/86
Page 516
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
1) Using tensiometer to measure load, adjust tension in ESS( )A and ESS( )B cables to rigging load for appropriate temperature as given in Table II, Fig. 502A. See Fig. 501 for turnbuckle locations.
2) Check that engine start drum, located above engine at wing front spar, is against start system stop (Fig. 503). 3) Increase tension in ESS( )B cable until a 6.0 +2.0/-2.0-pound force is required at start lever knob to unseat the start lever from the detent face. 4) Install all turnbuckle locking clips.
(f) If no further adjustments to the engine start control system are to be performed:
1) Install bolt retainer around cross-shaft left start crank fork and under bolthead. Insert bolt through aligned holes in start push-pull cable rod end and start crank. Bolt shall fit freely prior to attaching nut. Install self-locking nut on connecting bolt with washer. Tighten nut 100 to 140 pound-inches and bend retainer tab over bolthead (Fig. 504).
2) Perform Engine Start Control System Test procedure.
(4) Adjust engine start push-pull cable.
(a)
With forward thrust lever in the idle position on control stand, place start lever in cutoff detent.
(b)
Disconnect the engine start push-pull cable at the left start crank on the engine cross-shaft (Fig. 504).
(c)
Install type 3 rig pin through right start crank extension and rig pin bracket (Fig. 505, Detail A).
(d)
Do a check of the gap between the start crank and its stop on the fuel control unit (Fig. 505, Detail B). 1) If the gap is not 0.017 +0.003 inch, adjust the start rod.
(e)
Remove lockwire, loosen jamnut, and adjust length of start push-pull cable at lower rod end. Install bolt retainer around crank fork and under bolthead. Insert bolt through aligned holes in rod end and start crank. Bolt shall fit freely prior to attaching nut. Install bolt locknut on bolt with washer. Tighten nut 100 to 140 pound-inches and bend retainer tab over bolthead. Tighten rod end jamnut and lockwire as shown (Detail A, Fig. 504).
(f)
Remove rig pin from right start crank.
(g)
Perform Engine Start Control System Test procedure.
545
Aug 01/94 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 76-11-0 Page 517
548
76-11-0 Page 518 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 01/94
3. Engine Control System Test
A. Forward Thrust Control System Test
(1)
Equipment and Materials
(a)
Spring scale - 0- to 25-pound capacity
(b)
Type 1 Rig Pin - F70207-8 (1 required), 0.311 +0.000/-0.002-inch diameter.
(2)
Test engine forward thrust control system.
(a)
Remove engine side removable cowl panels (Ref Chapter 71, Removable Cowl Panels).
(b)
Test engine forward thrust control system friction.
1) Using spring scale, advance forward thrust lever from aft stop to forward stop. Check that force required at 70°F or above does not exceed 5.5 pounds through entire forward thrust travel. For thrust lever force at temperatures below 70°F, see Fig. 508.
NOTE: All control lever loads are to be measured at knob centerline and perpendicular to the control lever.
(c)
Test engine forward thrust control system travel. 1) Move forward thrust lever to idle stop on control stand. 2) Advance forward thrust lever until fuel control unit forward stop is contacted. At
this position, the forward edge of the thrust control lever shall be 0.10 in. minimum from the control stand stop.
(d)
Test engine thrust push-pull cable.
1) Install Type 1 rig pin through engine thrust drum and its support bracket located above engine at wing front spar (Fig. 503).
NOTE: With rig pin installed care must be taken not to exceed the cable test loads specified below.
2) Apply 10 lbs push load to cross shaft end of the cable (Fig. 509).
3) Apply 10 lbs pull load to the cable and check the thrust crank travel. A travel of more than 0.14 inch indicates excessive backlash of push-pull cable assembly which should be replaced.
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 发动机控制 ENGINE CONTROLS(10)
