NOTE: The tension on the ESS2A and the ESS2B cables may be
____ more than the value for the ambient temperature because of the force requirement on the start lever.
S 226-055-C00
(12) Make sure the thrust control push-pull cable is correctly adjusted.
(a)
Install a rig pin 3 into the "P" (part power stop) rig pin hole on the fuel control box for each engine.
(b)
Move the forward thrust levers forward until the two rig pins are touched.
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(c)
Make sure the two knobs of the forward thrust levers are aligned approximately 0.06 inch with each other.
(d)
Move the forward thrust levers to the idle position.
(e)
Remove the rig pins from the fuel control boxes.
S 216-056-C00
(13) Make sure the thrust control push-pull cable is correctly installed and not damaged.
(a)
Make sure the disconnect clamp and the thrust control push-pull cable is correctly installed to the MEC fuel control box.
(b)
Make sure the disconnect clamp and the thrust control push-pull cable is correctly installed to the strut control box.
S 216-057-C00
(14) Make sure the start control push-pull cable is correctly installed and is not damaged.
(a)
Make sure the start levers are at the CUTOFF position.
(b)
Make sure the disconnect clamp and the start control push-pull cable is correctly installed to the fuel shutoff assembly at the strut control box.
(c)
Make sure the start control push-pull cable is correctly installed to the MEC fuel shutoff lever.
(d)
Measure the clearance between the fuel shutoff lever and the cutoff stop on the MEC. 1) The clearance must be 0.01-0.05 inch.
S 216-058-C00
(15) Make sure the MEC fuel control box is correctly installed and is not damaged.
F. Put the Airplane Back to Its Usual Condition
S 416-022-C00
(1)
Install the forward fairing (AMM 54-32-01/401).
S 416-023-C00
(2)
Install these access doors from the upper and side surfaces of the strut (AMM 12-31-91/201).
(a) ON ENGINE NO. 1; install the access doors, 5726, 5727, 5728, 5729 and 5731.
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(b) ON ENGINE NO. 2; install the access doors, 5826, 5827, 5828, 5829 and 5831.
(3) S 416-059-C00Install the access panel, 6302 or 6402, to the leading edge (AMM 12-31-71/201).
(4) S 416-060-C00Install the access panel, 6301 or 6401, to the upper aft surface of the strut (AMM 12-31-71/201).
(5) S 416-024-C00Install the left fan cowl panel (AMM 71-11-02/401).
(6) S 416-025-C00Install the ceiling lining in the forward cargo compartment (AMM 25-52-65/401).
(7) S 416-026-C00Close the forward cargo door, 4404R.
(8) S 416-027-C00Close the access door, 1201L.
(9) S 416-028-C00Close the access door, 1103L.
S 446-029-C00
(10)
Remove the flap locks and retract the leading edge flaps (AMM 27-81-00/201).
S 446-030-C00
(11)
Do the activation procedure for the thrust reverser for ground maintenance (AMM 78-31-00/201).
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本文链接地址：737-300 400 500 AMM 飞机维护手册 发动机控制 ENGINE CONTROLS(18)
