378.50 STA
349.50
STA
332.50
FAULT INDICATION FAULTS
A
T.62T.40.1
DECODED BITE INFORMATION
1234
RESET
START FUEL VALVE & EXCITER SIGNAL OUT (5%)
BITE #
START MAIN FUEL VALVE SIGNAL OUT (14%)SEQUENCE
START FUEL VALVE & EXCITER SIGNAL OFF (70%)
90% RPM SWITCH ON
READY FOR SERVICE (90% + 1.5 SEC)
PROCESSOR BOARD FAILURE
SENSOR / DATA BOARD FAILURE
OVERTEMPERATURE
OVERSPEED
UNDERSPEED
OPERATION
FAIL TO START
LOW OIL PRESSURE
HIGH OIL TEMPERATURE (WARNING)
FAIL TO LIGHT (NO DATA)
SHORTED THERMOCOUPLE PROBE (WARNING)
OPEN THERMOCOUPLE
PROCESSOR SEQUENCE FAIL
NO DATA
GUST LOCK GUST LOCK
RELEASE HANDLE
APU ELECTRONIC SEQUENCE UNIT FAULT INDICATION
BUTTON (ON HELICOPTERS EQUIPPED WITH T.62T.40.1 APU) GUST LOCK CONTROL
C
FAULT INDICATION FAULTS
GTC.P36.150
B
DECODED BITE INFORMATION
1234
RESET (START INITIATED)
BITE #
ACCUMULATOR
START
PRESSURE GAGE
SEQUENCE
FUEL VALVE AND IGNITION SIGNAL ON (5%)
START VALVE SIGNAL OFF (70%)
ACCUMULATOR
IGNITION SIGNAL OFF (95%)
HAND PUMP
READY FOR SERVICE (LOSS OF DC POWER)
ESU FAILURE
A / C START SYSTEM FAILURE
OVERTEMPERATURE
OVERSPEED
UNDERSPEED
ACCUMULATOR FAIL TO START
OPERATION LOW OIL PRESSURE
MANUAL OIL PRESSURE SWITCH FAILED
START THERMOCOUPLE FAILED
VALVE MONOPOLE FAILED
ACCUMULATOR
FUEL SOLENOID FAILED
PISTON POSITION
FUEL TORQUE MOTOR FAILED
INDICATOR
IGNITION UNIT FAILED
HOT SENSOR FAILED
APU ACCUMULATOR
(LOOKING UP)
NO DATA
APU ELECTRONIC SEQUENCE UNIT FAULT INDICATION (ON HELICOPTERS EQUIPPED WITH GTC.P36.150 APU)
AB0695
SA
Figure 2-5. Cabin Interior
2.6 UPPER AND LOWER CONSOLES.
All cockpit electrical controls are on the upper and lower consoles and instrument panel. The upper console (Figure 2-6), overhead between pilot and copilot, contains engine controls, .re emergency controls, heater and windshield wiper controls, internal and external light controls, electri-cal systems and miscellaneous helicopter system controls. The rear portion of the upper panel contains the dc essential bus circuit breaker panels. The copilot’s side of the upper console contains the auxiliary circuit breaker panel. The lower console (Figure 2-7) next to the base of the instru-
ment panel and extending through the cockpit between the pilot and copilot, is easily reached by either pilot. The con-sole is arranged with communication panels, navigational panels and .ight attitude/stability controls. The rear part of the console houses the battery bus and battery utility bus circuit breaker panels, and parking brake handle.
2.7 LANDING GEAR SYSTEM.
The helicopter has a nonretractable landing gear consist-ing of two main gear assemblies and a tailwheel assembly. The landing gear permits helicopter takeoffs and landings on slopes in any direction. The system incorporates a jack and kneel feature that permits manual raising or lowering of the fuselage for air transportability. A landing gear weight-on-wheels (WOW) switch is installed on the left landing gear to control operation of selected systems (Table 2-1). The switch is deactivated when the weight of the he-licopter is on the landing gear. WOW switch is also in-stalled on the right landing gear drag beam to provide ac underfrequency cutout and external stores jettison. The left WOW switch provides all other WOW functions as without ESSS provisions and the EMER JETT ALL capabilities. See Table 2-1 for reference.
2.7.1 Main Landing Gear. The main landing gear is mounted on each side of the helicopter forward of center of gravity (Figure 2-1). Each individual landing gear has a single wheel, a drag beam, and a two-stage oleo shock strut. The lower stage will absorb energy from landings up to 10 feet-per-second (fps). Above 10 fps the upper stage and lower stage combine to absorb loads up to 39 fps (about
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