(b)
Damage you see such as gouges, grooves, and cracks are not permitted.
TASK 72-33-05-404-025-C00
3. Install the N1 Speed Sensor Guide Tube O-rings
______________________________________________
A. Consumable Materials
(1)
Graphite Grease - CP2101
(2)
Engine Oil
B. References
(1)
AMM 71-00-00/501, Power Plant
(2)
AMM 77-12-01/201, N1 Speed Sensor
C. Access
(1) Location Zones
506 Engine No. 1 - Fan Frame
606 Engine No. 2 - Fan Frame
D. Install the Guide Tube O-rings For the N1 Speed Sensor
S 644-018-C00
(1)
Lightly lubricate the new O-rings with engine oil and install them in the grooves of the guide tube.
S 424-022-C00
(2)
Engage the guide tube in the No. 5 fan frame strut until it is fully installed in the strut bore.
(3)
Lightly lubricate the threads of the bolts with graphite grease.
S 434-021-C00
(4)
Install the sleeve on the fan frame and attach with the bolts.
S 644-019-C00
(a) Tighten the bolts to 110-120 pound-inches (12.5-13.5 N.m.).
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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 ////////////////////////
(5) S 644-020-C00Lightly lubricate new O-rings with engine oil and install them on the end of the guide tubes.
(6) S 414-017-C00Install the N1 speed sensor (AMM 77-12-01/201).
S 414-011-C00
WARNING: OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
_______ REVERSER. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(7)
Close the right thrust reverser (AMM 78-31-00/201).
S 414-012-C00
(8)
Close the right fan cowl panel (AMM 71-11-02/201).
S 864-013-C00
(9)
Do the activation procedure for the thrust reverser (AMM 78-31-00/201).
S 864-024-C00
(10)
Remove the DO-NOT-OPERATE tags from the start levers.
S 714-010-C00
(11)
Do the leak check for engine operation at 70% N1 as shown in the Test Reference Table (AMM 71-00-00/501).
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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 ////////////////////////
HIGH PRESSURE COMPRESSOR ROTOR - DESCRIPTION AND OPERATION
__________________________________________________________
1. General
_______
A. The high pressure compressor (HPC) rotor is a 9-stage, high speed, unitized spool-disk structure (Fig. 1). The rotor consists of five major components:
(1)
Front shaft
(2)
1st- and 2-stage spool
(3)
4th- through 9th-stage spool
(4)
HPC rear rotating (CDP) air seal
B. The front shaft, disk, and spools are joined at a single bolted joint to form a smooth, rigid unit. Intefering rabbetted diameters are used for proper positioning of parts and for rotor stability.
2. Front Shaft
___________
A. The front shaft is bolted between the 1st-and 2nd-stage spool and the 3rd-stage disk, and is the forward support for the rotor. The shaft is splined to and secured to the inlet gearbox (IGB) horizontal bevel gear by a coupling nut. The IGB contains the thrust bearing for the core engine. The front shaft is made of a titanium alloy.
3. Disk and Spools
_______________
A. The 1st-and 2nd-stage spool and the 3rd-stage disk are made of titanium alloy forgings and retain the 1st-through 3rd-stage blades in axial slots. The 4th-through 9th-stage spool is made of a nickel alloy and retains 4th-through 9th-stage blades in circumferential grooves. The disk and 4th-through 9th-stage spool are internally cooled by low pressure compressor (booster) discharge air which enters the rotor through holes in the front shaft. There are abrasive coated seals between the rotor blade stages for improved compressor performance.
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