Lockheed C-5M, Техническое руководство

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NOTE
APU BATTERY ISO CONTACTOR CLOSED light will be defaulted to NVIS (very dim) until core processing
system power is applied.
ag. Place APU BATTERY CHARGER switch (1) to BYPASS. DC VOLTS meter should indicate a steady 28 (±3) volts.
Ensure APU BATTERY ISO CONTACTOR CLOSED light (2) comes on.
ah. Place APU BATTERY CHARGER switch (1) to ON. Ensure APU BATTERY ISO CONTACTOR CLOSED light (2)
goes off. DC VOLTS meter should indicate a voltage increase indicating Battery Charger Electronic Module (BCEM)
is supplying a charge to the battery. Battery voltage may intermittently decrease, then increase indicating BCEM is
supplying a pulse charge to the battery.
ai. Place VOLT SEL switch (3) to ACFT BATT.
aj. Place ACFT BATT switch (11) to ON. DC VOLTS meter should indicate a voltage increase indicating BCEM is
supplying a charge to the battery. Battery voltage may intermittently decrease, then increase indicating BCEM is
supplying a pulse charge to the battery.
ak. Place VOLT SEL switch (3) to RTRU 1 or RTRU 2.
1.3.9 Apply Control and Display Electrical Power and Core Processing Electrical Power. Use the following proce-
dure to apply control and display and core processing power.
•
Temperature limits for core avionics equipment must be observed as directed in Paragraph 1.5. Failure to
observe temperature limits may result in damage to core avionics equipment.
•
If VIA/AIU fan fail message is received, remove core power from affected LRU within 30 minutes. If a
VIA/AIU overtemp message is received, remove power from affected LRU immediately. Failure to comply will
result in damage to core processing equipment.
NOTE
Versatile Integrated Avionics (VIA) and Avionics Interface Unit (AIU) startup cannot be accomplished without
aircraft battery power.
a. Perform Connecting External Electrical Power in accordance with Paragraph 1.3.8.
NOTE
If airplane is on jacks, landing gear is in a nonstandard con
¿
guration, or airplane touchdown system is not
operational, the VIA and AIU may not boot up. If boot up is accomplished, Multifunction Control Display Unit
(MCDU) maintenance pages will not be available.
b. If airplane is on jacks or landing gear is in a nonstandard con
¿
guration and access to MCDU maintenance pages is
desired or core processing does not boot up, perform the following steps. Otherwise, proceed to Step c.
(1) Ensure the two TOUCH DOWN circuit breakers on
À
ight engineer circuit breaker panel No. 2 are closed.
(2) Simulate touchdown switches of each affected MLG to on-ground position by placing a sensor activation target
(ferrous metal plate) directly in front of the touchdown sensor (Figure 1-26, 1) for each affected MLG.
(3) Targets may be removed after desired maintenance is accomplished without rebooting core processing.
c. Ensure that the following circuit breakers (Figure 1-21) are closed:
(1) Pilot emergency circuit breaker panel, EMERGENCY AC BUS PH A
TO 1C-5M-2-1
1-18