CABLE
QUICK-RELEASE CLAMPS
CLAMP
SEE D
CLAMP
ENGINE NO. 1
BLOCKS
A
SEE B QUICK-RELEASE
CLAMPS
SEE D
1
FOR THESE THREE CLAMP BLOCKS ONLY,
AS AN OPTIONAL METHOD, YOU CAN
ENGINE NO. 2
INSTALL THE CABLES LIKE THE
OPPOSITE ENGINE.
A
Thrust Control Push-Pull Cable Installation
Figure 401 (Sheet 1)
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76-11-07
ALL ú ú C01 Page 402 ú Jul 15/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
FAN COWL
PENETRATION
SUPPORT BEAM
FITTING
THRUST CONTROL
B CABLE
"PT PWR" RIG PIN HOLE (UNDER SEAL)
STRUT DRUM CONTROL BOX
DISCONNECT CLAMP
THRUST
CONTROL
CABLE
FWD
NOTE: ENGINE NO. 1 INSTALLATION SHOWN ENGINE NO. 2 INSTALLATION SIMILAR
C
Thrust Control Push-Pull Cable Installation Figure 401 (Sheet 2)
//////////////////////// / /
CFM56 ENGINES
/ / ////////////////////////
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
CABLE CONTROL THRUST CABLE CONTROL THRUST
CLAMP DISCONNECT (IF INSTALLED) SHIM CLAMP DISCONNECT
HOLE RIG PIN HOLE RIG PIN
BOX CONTROL MEC FUEL R P BOX CONTROL MEC FUEL R P
START CONTROL CABLES WITH START CONTROL CABLES WITH FIXED LOWER END FITTING ADJUSTABLE LOWER END FITTING
D
Thrust Control Push-Pull Cable Installation
Figure 401 (Sheet 3)
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ALL ú ú C02 Page 404 ú Jul 15/88
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
S 044-002-C00
WARNING: DO THE DEACTIVATION PROCEDURE FOR THE THRUST REVERSER TO
_______ PREVENT THE OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF THE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO THE EQUIPMENT.
(1) Do the deactivation procedure for the thrust reverser for ground maintenance (AMM 78-31-00/201).
S 044-003-C00
WARNING:_______THE LEADING EDGE FLAPS CAN OPERATE QUICKLY. THE FLAPS CAN CAUSE INJURY TO PERSONS.
(2)
Do the deactivation procedure for the leading edge flaps (Ref 27-81-00/201).
S 014-004-C00
(3)
Remove the left fan cowl panel (AMM 71-11-02/201).
S 014-005-C00
(4)
Remove the access panel, 6301 or 6401, from the upper aft surface of the strut (AMM 12-31-71/201).
S 014-006-C00
(5)
Remove these access doors from the upper and side surfaces of the strut (AMM 12-31-91/201).
(a)
ON ENGINE NO. 1;
remove the access doors, 5726, 5727, 5728, 5729 and 5731.
(b)
ON ENGINE NO. 2;
remove the access doors, 5826, 5827, 5828, 5829 and 5831.
S 014-007-C00
(6)
Remove the forward fairing (AMM 54-32-01/401).
S 864-008-C00
(7)
Move the forward thrust lever to approximately 20° thrust lever angle (TLA).
NOTE: This puts the push-pull cable in the correct position to
____ disconnect the cable from the strut drum box and the MEC box when you remove the disconnect clamps.
S 864-009-C00
(8) Install the F70207-8 rig pin through the PT PWR rig pin hole in the strut drum control box (into the gearshaft in the housing).
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