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CAUTION: DO NOT ACTUATE DISCONNECT SWITCH FOR LONGER THAN 3 SECONDS. ALLOW A
MINIMUM OF 60 SECONDS BETWEEN ACTUATION PERIODS.
A. Start the engine.
B. After stable idle is reached, momentarily press L (or R) GEN DRIVE DISC switch.
C. Verify the following readings for the left (or right) power channel on lower EICAS display:
 
  B757 - 200 MINIMUM EQUIPMENT LIST
1) AC-V = 0 ± 5
2) FREQ = 0 ± 5
D. Verify the following messages appear on EICAS:
1) L (or R) GEN OFF
2) L (or R) GEN DRIVE
NOTE 1: If the IDG charge pressure switch has been confirmed to be failed, then L(R) GEN DRIVE message and associated illumination of the drive light on the P5 control panel will not annunciate. In this case, checking for voltage, frequency, and the L(R) GEN OFF message per the above steps is sufficient as an alternate means of verifying IDG disconnect.
NOTE 2: During the authorized repair interval, if the associated engine is operated for more than 50 hours with the IDG disconnected, then the IDG should be removed for inspection prior to returning the airplane to service.
NOTE 3: It is acceptable to dispatch with low or no oil in the IDG if the IDG is disconnected. 2. Verify that the HMG operates normally (Ref. AMM 24-25-00):
A. Supply electrical power (AMM 24-22-00/201).
B. Verify that the following circuit breakers on the P11 panel are closed:
1) AC BUS SENSE LEFT
2) AC BUS SENSE RIGHT
3) EICAS circuit breakers
C. Verify that the HYD GEN CONT circuit breaker on the main power distribution panel, P6, is closed.
D. Pressurize the airplane hydraulic system. Perform step 1) or perform steps 2) and 3).
NOTE: A ground service cart or the alternating current motor pumps (ACMP) may be used to supply hydraulic power.
1) Pressurize the left hydraulic system with the hydraulic service cart (AMM 29-11-00).
2) Pressurize the left and right hydraulic systems with the Alternating Current Motor Pumps.
3) Put the PTU switch on the P61 panel to the ON position.
E. Push the DISPLAY STATUS switch on the EICAS Display Select Panel P9.
F. Hold the GND PROX/HYD GEN switch on the P61 panel in the HYD GEN position.
NOTE: THE PITOT HEATER ANNUNCIATOR LIGHTS MAY FLASH WHILE PERFORMING THIS TEST.
G. Verify that the HYD GEN ON and HYD GEN VAL Status messages appear on the EICAS lower display.
H. Push the ELEC/HYD switch on the EICAS Maintenance Panel (P61).
I. Verify that the following values are displayed on the ELEC/HYD EICAS maintenance page:
1) HYD GEN DC-V 28 + 4
2) HYD GEN AC-V 115 + 5
 
3) HYD GEN FREQ 400 + 5
J. Release the GND PROX/HYD GEN switch (P61)and verify that the following values are displayed
on the EICAS maintenance page:
NOTE: On airplanes with 10 KVA HMG, the HMG will continue to operate for approximately 15 seconds after the test switch is released.
　
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