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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.
1) HYD GEN DC-V 0 + 4
2) HYD GEN AC-V 0 + 5
3) HYD GEN FREQ 0 + 5
K. Push the DISPLAY STATUS switch on the EICAS Display Select Panel (P9).
L. Verify that the HYD GEN ON and HYD GEN VAL Status messages do not appear on the EICAS lower display.
M. Open and then close the HYD GEN CONT circuit breaker on the Main Power distribution panel (P6).
NOTE: Opening and then closing the HYD GEN CONT circuit breaker ensures that the HMG Control Unit is reset following the test.
 
N. If the ACMPs were used to pressurize the hydraulic system, put the PTU switch to the OFF
position.
O. Restore the airplane to its usual condition.
OPERATIONS NOTE
1. If APU Generator is removed, account for effect on airplane weight and balance.
2. Leave APU GEN switch in the OFF position.
3. If external power is not available, accomplish battery start procedure:
A. Accomplish the normal Exterior Inspection and Supplementary Electrical PowerUp procedure to: Electrical Power  Establish
NOTE: Ground air source must be used.
B. Engine Ignition Selector   1 or 2
C. Isolation Switch ON
D. Speedbrake Lever DOWN
E. Reverse Thrust Levers Down
F. Forward Thrust Levers  Closed
G. Flap Lever Set
　
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