(2)
D00511 Oil - Engine (AMM 70-10-01/201)
B. References
(1)
AMM 71-00-00/501, Power Plant
(2)
AMM 71-11-02/201, Fan Cowl Panel
C. Access
(1)
Location Zone
506 Engine No. 1 - Fan Frame
606 Engine No. 2 - Fan Frame
(2)
Access Panel
5746 Fan Cowl Panel (LH) - Engine No. 1
5846 Fan Cowl Panel (LH) - Engine No. 2
D. Procedure (Fig. 401)
S 034-009-C00
(1)
Remove the caps from the timer fittings and disconnected tubes.
(2)
Lubricate the HPTCC Timer bolts with grease for installation.
S 824-011-C00
(3)
Align the bolt holes in the HPTCC Timer with the bolt holes in forward and aft brackets on the engine flanges E and H.
S 644-010-C00
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ENGINES WITH THE HIGH PRESSURE TURBINE ú
75-24-02
CLEARANCE CONTROL (HPTCC) TIMER ú ú C01 Page 403 ú Jul 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
(4) S 434-012-C00Install the bolt that attaches the HPTCC Timer to the forward bracket on the engine flange E.
(5) S 434-013-C00Install the two bolts that attach the HPTCC Timer to the aft bracket on the engine flange H. (a) Tighten the bolts (3 locations) to 100-110 pound-inches (11.3-12.4 Newton meters).
S 644-020-C00
WARNING:_______DO NOT LET ENGINE OIL STAY ON YOUR SKIN. USE ENGINE OIL IN AREA WITH GOOD VENTILATION. ENGINE OIL IS POISONOUS AND CAN BE ABSORBED THROUGH YOUR SKIN. ENGINE OIL FUMES CAN IRRITATE YOUR RESPIRATORY TRACT.
(6)
Lightly lubricate the tube fittings on the HPTCC Timer with engine oil.
S 434-015-C00
(7)
Connect the seven tubes that follow to the HPTCC Timer:
(a)
PB tube.
(b)
PC tube.
(c)
TC1 tube.
(d)
TC2 tube.
(e)
TC3 tube.
(f)
TS5 tube.
(g)
TS9 tube.
(h)
Tighten the tube nuts to 135-150 pound-inches (15-17 Newton meters).
S 434-016-C00
(8) Install the bolt and nut that attaches the clamp on the TC1 tube to the bracket.
(a) Tighten the bolt to 55-70 pound-inches (6.2-7.9 Newton meters).
S 414-017-C00
(9)
Close the left fan cowl panel (AMM 71-11-02/201).
S 734-018-C00
(10)
Do the leak check at idle power (AMM 71-00-00/501, Test No. 3) for fuel tube connections.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ENGINES WITH THE HIGH PRESSURE TURBINE ú
75-24-02
CLEARANCE CONTROL (HPTCC) TIMER ú ú C01 Page 404 ú Jul 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
VARIABLE STATOR VANE ACTUATION SYSTEM - DESCRIPTION AND OPERATION
_________________________________________________________________
1. General (Fig. 1)
_______
A. The variable stator vane (VSV) actuation system controls primary airflow through the high pressure compressor (HPC). The system consists of two VSV hydraulic actuators, two bellcrank assemblies and linkage and a flexible feedback cable.
B. The VSV actuation system maintains satisfactory compressor performance over a wide range of operating conditions. The system varies the angle of the inlet guide vanes (IGV) and the three stages of variable vanes to aerodynamically match the low pressure stages of compression with the high pressure stages. This variation of vane position changes the effective angle at which air flows across the rotor blades. The angle determines the compression characteristics (direction and velocity) for any particular stage of compression. By varying the variable vane position in accordance with a predetermined schedule as a function of those conditions affecting compressor performance (compressor inlet temperature (CIT) and core engine speed (N2)), the critical low pressure stages are automatically realigned or rematched to maintain satisfactory airflow and compressor performance during all engine operating conditions within the requirements of the system.
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