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XMSN AUX OIL PRESS caution will illuminate on the
master caution panel.
e. OVERTEMP Magnetic Indicators. Each OVER
TEMP magnetic indicator is electrically connected to a
temperature probe in the reservoir of each transmission.
If oil temperature in the transmission reservoir exceeds
140
C, a switch closes. When the switch closes, the
XMSN OIL HOT caution illuminates on the master caution
panel and trips the corresponding OVERTEMP magnetic
indicator on the MAINTENANCE PANEL, thus identifying
the hot transmission.
2-9-5. HYDRAULICS Section.
This section monitors the FLT CONT NO 1, FLT CONT
NO 2, and UTILITY hydraulic systems. It consists of three
PRESSURE indicators, three fluid TEMPERATURE indicators,
two RESERVOIR LEVEL indicators, six FILTER
CHANGE indicating PRESS-TO-TEST lights, and four
PUMP FAULT indicating PRESS-TO-TEST lights. Power
to operate the indicators is supplied by the No. 2 DC bus
TM 1-1520-240-10
2-9-3
through the HYDRAULICS MAINT PNL LTS circuit
breaker on the No. 2 PDP.
a. PRESSURE Indicators. The FLT CONT NO. 1
and NO. 2 PRESSURE indicators are electrically connected
to a corresponding pressure transmitter on the respective
power control module. The UTILITY PRESSURE indicator
is electrically connected to a pressure transmitter on the
pressure control module. Indicator operation is independent
of caution capsule operation. Power to operate the indicators
is supplied by the No. 2 DC bus through the HYDRAULICS
PRESS IND circuit breaker on the No. 2 PDP.
b. TEMPERATURE Indicators. The indicators are
below the PRESSURE indicators. They indicate the temperature
of the hydraulic fluid at the outlet of the corresponding
reservoir-cooler. Power to operate the indicators is supplied
by the No. 2 DC bus through the HYDRAULICS FLUID
TEMP circuit breaker on the No. 2 PDP.
c. RESERVOIR LEVEL Indicators. The left indicator
is dedicated to the No. 1 and No. 2 flight control hydraulics
system. In addition, a two–position FLT CONT switch labeled
NO. 1 and NO. 2 is used to select the system of which
the fluid level is to be indicated. The reservoir should be
serviced to the FULL mark before flight. The right indicator
is dedicated to the utility hydraulic system. When the pushbutton
LEVEL CHECK switch is pressed, the fluid level in
each reservoir-cooler will be indicated by the appropriate
indicator.
d. FILTER CHANGE Indicating Lights. The indicating
lights are arranged in three sets of two for each hydraulic
system. Each set of indicating lights are labeled PRESS and
RTN. The PRESS indicating light in each set monitors the
pressure line filter in each system. The RTN indicating light
monitors the return line filter in each system. When the
pressure drop across a filter exceeds 75 psi, indicating
impending filter bypass, the corresponding filter change indicating
light will illuminate. Power to operate the filter change
indicating lights is supplied by the No. 2 DC bus through the
HYDRAULICS MAINT PNL LTS circuit breaker on the No.
2 PDP.
e. PUMP FAULT Indicating Lights. The indicating
lights are labeled NO. 1, NO. 2, APU, and UT. They are
connected to sensors in the case drain line of each pump.
If the flow rate from the case drain of a pump increases to
the point which causes an increased pressure drop across
the sensor, the sensor turns on the corresponding PUMP
FAULT light ( a high flow rate from the case drain of a pump
may indicate impending pump failure). Power to operate the
lights is supplied by the No. 1 DC bus through the HYDRAULICS
MAINT PNL circuit breaker on the No. 1 PDP.
2-9-6. ENGINE CHIP DETECTOR Section.
This section consists of two magnetic indicators labeled
NO. 1 and NO. 2. When the corresponding ENGINE CHIP
DETECTOR is bridged by ferrous particles, the associated
chip detector indicator changes from all-black to black-andwhite.
In addition, the ENG CHIP DET caution will illuminate
on the master caution panel.
2-9-7. GROUND CONTACT Section.
CAUTION
Should either or both GROUND CONTACT
indicating lights remain illuminated after
lift-off to hover, the indicated system(s)
DASH will not function properly in forward
flight. If both GROUND CONTACT indicating
lights remain illuminated after lift-off,
the AUTO function of both cyclic trims
system will be inoperative.
This section consists of two indicating lights labeled L and
R. When the landing gear proximity switch is activated, the
appropriate GROUND CONTACT indicating light will illuminate.
2-9-8. GND Switch.
NOTE
While in flight, the flight engineer shall alert
　
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