(c)
When moving reverse thrust lever toward OFF position, it shall require a load of 7.0 +5.0/-0 pounds to move lever out of the No. 1 detent toward the OFF position.
(d)
Position reverse thrust lever in OFF position and install reverse thrust detent cover.
(e)
Depressurize hydraulic system.
577
76-11-0 Page 524 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/87
C. Engine Start Control System Test
(1)
Equipment and Materials
(a)
Spring scale - 0- to 25-pound capacity
(b)
Airplane Control Surfaces Protractor - 4MIT65B80307-1 or F52485-500
(2)
Test engine start control system.
(a)
Remove left removable cowl panel (Ref Chapter 71, Removable Cowl Panels).
(b)
Test engine start control system friction.
1) Using spring scale, move start lever in either direction between detents. Force required at 700F or above should not exceed 5.25 pounds as measured at knob centerline. For start lever force at temperatures below 700F, see Fig. 508. The force required to unseat the start lever from the detent face shall be 4 to 8 pounds after moving into the CUTOFF detent. The lever shall return to the detent face when released.
(c)
Test engine start control system travel. 1) Check that start lever is in the CUTOFF detent. 2) Hold protractor on left start crank on engine cross-shaft (Fig. 509), center
protractor bubble and record degrees shown.
NOTE: Protractor should be placed in same position on start crank after start lever advancement, as it was in step 2). Difference between step 2) and step 3) determine degrees of travel.
3) Advance start lever to IDLE detent. Place protractor on start crank, center bubble and record degrees shown. Left start crank shall have traveled a minimum of 55 degrees (Fig. 506).
4) Return start lever to CUTOFF.
575
May 01/01 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 76-11-0 Page 525
4. Return Airplane to Normal Configuration
A. Install left upper side door on control stand using 10 attachment screws (Fig. 507).
B. Install left stabilizer trim control wheel. Secure with tie rod nut.
NOTE: Handles on stabilizer trim control wheels should be 90士15 degrees apart when installed on control stand.
C. Restore all circuit breakers to pre-test position.
D. If desired, install ground lock assemblies F80109-3 in isolation valves.
E. Deleted.
F. If removed, install side removable cowl panels (Ref Chapter 71, Removable Cowl Panels).
G. If removed, install access doors No. 6301 and 6401 in wing leading edges above each wing-to-engine fairing (Ref Chapter 12, Access Doors and Panels).
H. Retract forward airstairs (Ref Chapter 52, Forward Airstairs and Door).
I. Close electronic equipment access door No. 1201 and install nose gear wheel well right and left aft panels as necessary.
J. Remove leading edge flap locks (Ref 27-81-0 MP).
WARNING: LEADING EDGE FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.
K. If no longer required, remove electrical and hydraulic power.
575
76-11-0 Page 526 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/87
THRUST LEVERS - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Tensiometer - 0- to 125-pound capacity.
B. Rig Pin Kit - F70207-3, -52 or -61.
(1) SB-1 - F70207-11, 0.311 + 0.000/-0.002-inch diameter rod
C. C-Clamps - as required.
D. Dowel Set - Thrust Lever, Control Stand - F80195-1 or Dowel, Thrust Lever Control Stand -SE76-1004 (2 required).
2. Prepare for Thrust Levers Removal
A. Depressurize hydraulic systems A and B.
(1)
Provide electrical power.
(2)
On forward overhead panel, position switches as follows:
(a)
Hydraulic system A ENG 1 and ENG 2 pump switches to OFF.
(b)
Hydraulic system B ELEC 1 and ELEC 2 pump switches to OFF.
(3)
Open circuit breakers as follows:
(a)
Pump B on P6-11 panel.
(b)
Pump B on P6-12 panel.
中國航空網(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) 發(fā)動(dòng)機(jī)控制 ENGINE CONTROLS(12)
