S 434-021-N00
(7)
If the bolt is not welded on the bracket, attach the small ground
lead and clamp to the bracket and install the clamp bolt to the
bracket.
S 434-033-N00
(8)
Tighten the clamp bolt to 36-40 pound-inches (4.1-4.5 newton-meters) or the clamp nut to 32-36 pound-inches (3.6-4.1 newton-meters).
S 434-022-N00
(9)
Tighten the nut on the smaller stud to 15-18 pound-inches
(1.7-2.0 newton-meters).
S 434-013-N00
(10)
Tighten the nut on the larger stud to 18-22 pound-inches (2.0-2.5
newton-meters).
D.
Put the Airplane Back to Its Usual Condition.
S 414-031-N00
WARNING: OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
_______
THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS,
INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
(1) Close the thrust reverser (AMM 78-31-00/201).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ENGINES WITH 2.9 BLEED ú
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
S 414-026-N00
(2) Close the core cowl panel (AMM 71-11-06/201).
S 414-027-N00
(3) Close the fan cowl panel (AMM 71-11-04/201).
S 444-028-N00
(4) Do the activation procedure for the thrust reverser (AMM 78-31-00/201).
S 864-017-N00
(5) For the applicable engine, remove the DO-NOT-CLOSE tags and close these circuit breakers as follows:
(a) AIRPLANES WITH THE AUTOMATIC ENGINE START; P6 Main Power Distribution Panel
1) 2) 3) 4) 5) 6) 7) 8) 6G15 SCU ALT PWR ENG 16G23 ENG SCU 16G16 SCU ALT PWR ENG 26G24 ENG SCU 26G17 SCU ALT PWR ENG 36G25 ENG SCU 36G18 SCU ALT PWR ENG 46G26 ENG SCU 4
(b) AIRPLANES WITHOUT THE AUTOMATIC ENGINE START; P414 Power Distribution Center - Left
1) 2) 3) 4) 414D21 EEC GND TEST PWR ENG 1414D22 EEC GND TEST PWR ENG 2414D23 EEC GND TEST PWR ENG 3414D24 EEC GND TEST PWR ENG 4
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ENGINES WITH 2.9 BLEED ú
75-32-06
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
HPC SECONDARY FLOW CONTROL SYSTEM - DESCRIPTION AND OPERATION
_____________________________________________________________
1. General
_______
A. The high pressure compressor (HPC) secondary flow control system controls the 9th-stage airflow to the HPC inner cavity to optimize the engine performance.
B. The system includes two HPC secondary flow control valves, three HPC secondary flow control valve filters, a HPC secondary flow control valve and turbine vane and blade cooling air (TVBCA) valve solenoid, and a HPC secondary flow control valve and IDG air/oil heat exchanger valve override solenoid.
C. The system is controlled by the electronic engine control (EEC) as a function of altitude and high pressure rotor speed (N2).
2. HPC Secondary Flow Control Valve (Fig. 1)
________________________________
A. The HPC secondary flow control valves, which are pneumatically actuated and spring operated, control 9th-stage compressor heating airflow into the HPC inner cavity (drum area).
B. The valves are installed on the HPC forward case at the 3:30 and 9:30 o'clock positions.
C. Each valve includes a visual position indicator. The indicator pin is extended or retracted when the valve is fully opened or fully closed respectively.
D. The position switch on each valve feeds the valve position back to the EEC. The position switches on both valves are continuously cooled by fan air.
3. PS3 Air Filter (Fig. 1)
______________
A. There are four PS3 air filters which clean muscle air for the HPC Secondary Flow Control System, Turbine Vane and Blade Cooling Air System, and 2.9 Bleed System. Three filters clean muscle air for the HPC Secondary Flow Control System, while the other filter cleans muscle air for the Turbine Vane and Blade Cooling Air System. One of the three filters, which cleans muscle air for the HPC Secondary Flow Control System, also cleans muscle air for the 2.9 Bleed System.
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