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main rotor system malfunctions, proceed as follows:
piiii-1
Danger exists that the main rotor system
could dollapse or separate from the aircraft
after landing. A decision must be
made whether occupant egress occurs before
or after the rotor has stopped.
1. LAND
2. EMRR ENG(S) SHUTDOWN after la&ng,
c. During ground operations any abnormal control inputs
required to maintain desired fuselage attitude may be
indicative of a problem. If this condition occurs, complete a
normal engine shutdown.
9.14.1 Stabllator Automatic Mode Failure.
1. Stabilator RESET button - Press. If automatic
mode is not restored:
2. Use manual stabilator.
9.14.2 Stabilator Auto/Manual Mode Failure.
1. Airspeed - Use placard limits. If both crew-station
indicators are inoperative (90 knots maximum):
2. LAND AS SOON AS PRACTICABLE.
9.14.3 DASE Malfunction. DASE malfunctions may manifest
themselves as uncommanded control inputs, which may
cause unusual rotor disc movement, or aircraft attitude/
heading changes.
1. ASE switch - Prem
2. SAS - &engage unaffected axes.
PIN: 073188-007
9.14.3 DASE Malfunction. DASE malfunctions may
manifest themselves as uncommanded control inputs,
which may cause unusual rotor disc movement, or aircraft
attitude/heading changes.
1. ASE release switch - Press.
2. SAS - Re-engage unaffected axes.
9.14.4 BUCS Failure.
Illumination of the BUCS FAIL warning
light in flight shall be treated as a
flight control system emergency. Exercise
extreme care in making large
or rapid control inputs.
1. LAND AS SOON AS POSSIBLE,
9.15 CAUTION/WARNING LIGHT EMERGENCY
PROCEDURES.
For caution/warning light emergency procedures, reference
table 9-1.
TM 1-1520-238-10
NOTE
During maneuvering flight, a momentary
reduction of oil pressure may occur
in the main transmission and engine
nose gearboxes causing a low oil pressure
caution/warning light. As long as
the caution/warning light goes out
within 10 seconds, no action is required.
During approaches, maneuvering flight
and other areas of 4/rev vibration, the
VIB GRBX caution light may illuminate.
As long as the caution light extinguishes
within 5-10 seconds after exiting
the 4/rev environment, no action is
required.
FD/LS 19 Pressure indications of 50 or
99 lbs are normally wiring problems. If
these indications are observed, make
appropriate entry on DA form 2408-13
series forms.
Table 9-1. Caution/Warning Light Corrective Actions
WORD SEGMENT CORRECTIVE ACTION
NOTE
Illumination of a light that is informationlsystem status shows condition of system components.
Mission accomplishments may be degraded. Mission requirements will dictate further actions.
For conditions which cause the lights to illuminate, see Tables 2-3, 2-4, and 2-5.
MASTER CAUTION PANELS:
MASTER CAUTION
LOW RPM ROTOR
FIRE APU
ENGINE 1 OUT
ENGINE CHOP
ENGINE 2 OUT
Check Master/Caution Warning and Caution Panels for
other lights. If no other light is flashing LAND AS SOON
AS POSSIBLE.
See LOW RPM ROTOR (Warning Light On) Np Failed Low
(paragraph 9.98).
See APU Compartment Fire (paragraph 9.10.3).
See Single-Engine Failure Low Altitude/Low Airspeed and
Cruise (paragraph 95.3).
See Single-Engine Failure Low Altitude/Low Airspeed and
Cruise (paragraph 9.5.3).
Change 4 9-15
Chop collar - Reset
TM 1-1520-238-10
Table 9-1. Caution/Warning Light Corrective Actions - continued
WORD SEGMENT CORRECTIVE ACTION
NOTE
ENG 1 and 2 out. See Dual-Engine Failure Low Altitude/Low Airspeed and Cruise.
HIGH RPM ROTOR See HIGH RPM ROTOR (Rotor Light On) Np Failed High
(paragraph 9.9.7).
BUCS FAIL
CAUTION/WARNING PANELS:
FUEL LOW FWD
EXT EMP
FUEL XFR
FUEL XFR (Green)
Modified C/W panel
FUEL XFR (Amber)
Modified C/W panel
X FEED (Green)
Modified C/W panel
X FEED (Amber)
Modified C/W panel
PRI HYD PSI
UTIL HYD PSI
MAN STAB
BUCS ON
BUCS ON
ADS
FUEL LOW AFT
BOOST PUMP ON
OIL LOW PRI HYD
OIL LOW UTIL HYD
PRI HYD PSI and UTIL HYD PSI
9-16 Change 3
LAND AS SOON AS POSSIBLE.
LAND AS SOON AS PRACTICABLE.
Information/system status.
Information/system status.
Information/system status.
Evaluate remaining fuel per cell.
Information/system status.
Achieve safe single engine airspeed and restore previous switch
position. If caution segment extinguishes, continue mission. If
　
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