76-11-00
ALL ú ú C02 Page 518 ú Jul 12/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
TABLE 501
CABLE TENSION_____________
Temperature___________ Load____
°F °C Lb|5
120 48.9 68.5
110 43.3 66
90 32.2 61
70 21.1 55
50 10.0 50
30 -1.1 44
10 -12.2 39
0 -17.8 36
-10 -23.3 33
-20 -28.9 30.5
-30 -34.4 28
(a)
Adjust the tension in the cables in the forward loop: 1) Move the thrust lever slowly to the idle stop position. 2) Adjust the cables in the forward loop so that rig pin 1
(F70207-23) can be freely inserted in the torque switch mechanism of the autothrottle (View B, Fig. 504).
(b)
Install the rig pin 1 in the torque switch mechanism of the autothrottle.
(c)
Adjust the tension in the cables in the aft loop.
1) Adjust the cables in the aft loop so that rig pin 2 (F70207-8) can be freely inserted throught the IDLE hole in the strut drum control box (View A, Fig. 504) and into the throttle gearshaft within the box.
(d)
Remove the rig pins.
(e)
Move the thrust lever to the full forward position and rearward to the idle position.
NOTE: Remove the warning sign that tells personnel not to
____ operate the engine controls.
(f) Install the rig pins 1 and 2. 1) Make sure the rig pins turn freely when they are installed.
S 095-138-C00
(12)
Remove the rig pins.
S 435-139-C00
(13)
Install the locking clips on the turnbuckles.
(14)
Retract the forward airstairs (AMM 52-61-00/001).
S 865-141-C00
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
76-11-00
ALL ú ú C05 Page 519 ú Jul 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
S 415-142-C00
(15) Close the access door to the electronic equipment bay, No. 1201 (AMM 12-31-11/201).
NOTE: Do not do the next two steps if you want to continue with the
____
adjustment of the start control cables.
S 415-143-C00
CAUTION: MAKE SURE THAT THE VISIBLE PARTS OF THE CONTROL CABLES AND THE
_______ QUADRANTS IN THE WING LEADING EDGE AREA ARE NOT MOIST BEFORE YOU INSTALL THE ACCESS PANEL 6301 OR 6401. MOISTURE COULD FREEZE DURING FLIGHT AND PREVENT CORRECT SYSTEM OPERATION.
(16)
Install the access panel No. 6301 or No. 6401 (AMM 12-31-71/201).
S 845-144-C00
(17)
Do the procedure: Put the Airplane Back to Its Usual Condition.
G. Adjust the Tension of the Start Control Cables (Fig. 504).
NOTE: These are the tension cables ESS1A/ESS1B/ESS2A/ESS2B.
____ S 845-160-C00
(1)
Do the procedure: Prepare for the Adjustment.
S 015-161-C00
(2)
Remove the ceiling panels in the forward cargo compartment as necessary to get access to the turnbuckles on the start control cable.
S 015-162-C00
(3)
Remove the access panel No. 6301 (left wing) or No. 6401 (right wing) from upper aft surface of the nacelle strut (AMM 12-31-71/201).
(4)
Make sure that the start lever is in the CUTOFF detent.
S 495-164-C00
(5)
At the fuel shutoff assembly (View A, Fig. 504), put the retainer pin on the fuel shutoff quadrant against the stop plate.
S 865-163-C00
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