S 015-004-C00
(2)
Open the left fan cowl panel (AMM 71-11-02/201).
S 015-005-C00
(3)
Remove the aft cover from the fuel control box on the main engine control (MEC).
S 015-039-C00
(4)
Remove the access panel No. 6301 (left wing) or No. 6401 (right wing) from the upper aft surface of the nacelle strut (AMM 12-31-71/201).
S 865-006-C00
(5)
Make sure that the applicable start lever is at the CUTOFF detent and that the retainer pin on the fuel shutoff quadrant is against the stop plate of the Fuel Shutoff Assembly (Fig. 501).
S 225-008-C00
(6)
At the fuel control box, look for a clearance of 0.01-0.05 inch (0.25-1.27 mm) between the fuel shutoff lever and the cutoff stop on the MEC.
S 225-043-C00
(7)
Measure the distance between the start cable link and the cable support plate (Dimension A, Fig. 503).
S 865-044-C00
(8)
Move the start lever to IDLE.
S 225-045-C00
(9)
Measure the distance between the link and the cable support plate again (Dimension B).
(10)
The value of B - A must not be less than 1.35 inches (34.3 mm).
S 225-046-C00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
Engine Control Cables
Figure 501 (Sheet 1)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
"PT PWR" RIG PIN HOLE (80` PLA-UNDER SEAL)
STRUT DRUM CONTROL BOX
"IDLE" RIG PIN HOLE (55` PLA-UNDER SEAL) RETAINER PIN STOP PLATE FUEL SHUTOFF ASSEMBLY
FWD FUEL SHUTOFF
START CONTROL QUADRANT
PUSH-PULL CABLE CABLE SUPPORT BRACKET
JAMNUTS
A
THRUST CONTROL
PUSH-PULL CABLE
TURNBARREL
START CONTROL PUSH-PULL CABLE CABLE SUPPORT BRACKET
SHIM PART POWER STOP PIN HOLE JAMNUTS
(92.5` PLA) CUTOFF STOP
RIG PIN HOLE
(80` PLA)
P
PR 0.01-0.05 INCH
0.01-0.05 INCH
MEC FUEL
ROD END
CONTROL BOX
LINK - CLAMP
FITTING SHUTOFF LEVER -
SHUTOFF LEVER-
CUTOFF POSITION
CUTOFF POSITION AFT COVER AFT COVER
START CONTROL CABLES WITH START CONTROL CABLES WITH FIXED LOWER END FITTINGS ADJUSTABLE LOWER END FITTINGS
NOTE: POWER LEVER OMITTED B FOR CLARITY.
Engine Control System Adjustment Locations
Figure 501 (Sheet 2)
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ALL ú ú C01 Page 505 ú Nov 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
SEE A
PROTRACTOR
ADAPTOR PROTRACTOR LEVER KNOB FORWARD THRUST THRUST LEVER REVERSE PROTRACTOR
STAND CONTROL
FORWARD THRUST LEVER REVERSE THRUST LEVER
A
Thrust Lever Angular Positioning Figure 502
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú 中國航空網(wǎng) m.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：737-300 400 500 AMM 飛機(jī)維護(hù)手冊 發(fā)動機(jī)控制 ENGINE CONTROLS(8)
