TORQUE INDICATING SYSTEM OPERATIONAL CHECK (Continued)

TORQUE INDICATING SYSTEM OPERATIONAL CHECK - TM-55-1520-240-T-2_186

NO. 1 OR NO. 2 ENGINE TORQUE AC CIRCUIT BREAKER WILL NOT STAY CLOSED

TM-55-1520-240-T-2 CH-47D Heilcopter Manual
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TM 55-1520-240-T 8-6.3.1 TORQUE INDICATING SYSTEM OPERATIONAL CHECK (Continued) 8-6.3.1 TASK 1. Check that ENGINE NO. 1 AC TORQUE circuit breaker (2) is closed. 2. Check that ENGINE NO. 1 DC TORQUE circuit breaker (1) is closed. 3. Check that ENGINE NO. 2 AC TORQUE circuit breaker (3) is closed. 4. Check that ENGINE NO. 2 DC TORQUE circuit breaker (4) is closed. 5. Check No. 2 pointer on pilot (5) and copilot (6) torque Indicators. NOTE If pointer is spinning, have helper manually turn rotor blades until spinning stops. If spinning continues after one revolution of the blades, go to next step. 6. Check No. 1 pointer on pilot (5) and copilot (6) torque indicators. NOTE If pointer is spinning, have helper manually turn rotor blades until spinning stops. If spinning continues after one revolution of blades, go to next step. 7. Install electric torquemeter flight line test set on the aircraft. Reference operating manual SE-876-01-1006. 8. Perform an AIRCRAFT SYSTEM TEST. Reference operating manual SE-876-01-1006. 9. After completion of test(s), remove electric flight line test set from the aircraft. Reference operating manual SE-876-01-1006. RESULT If ENGINE NO. 1 AC TORQUE circuit breaker (2) is open, close it. If it opens again, go to task 8-6.4. If ENGINE NO. 1 DC TORQUE circuit breaker (1) is open, close it. If it opens again, go to task 8-6.5.1. If ENGINE NO. 2 AC TORQUE circuit breaker (3) is open, close it. If it opens again, go to task 8-6.4. If ENGINE NO. 2 DC TORQUE circuit breaker (4) is open, close it. If it opens again, go to task 8-6.5.1. No. 2 pointer on both torque indicators (5 and 6) shall be below 10%. If not, adjust torque indicator to zero. (Ref TM 55-1520-240-23.) No. 1 pointer on both torque indicators (5 and 6) shall be below 10%. If not, adjust torque indicator to zero. (Ref TM 55-1520-240-23.) Continue the tests or replace LRUs, depending upon the results of the AIRCRAFT SYSTEM TEST. Reference operating manual SE-876-01-1006. FOLLOW-ON MAINTENANCE: TM 55-1520-240-23: Battery disconnected. Electrical power off. Hydraulic power off. END OF TASK Change 19 8-107

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