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cause the overtemperature switch to stop APU operation:
however, should a fire other than normal combustion
occur at the APU, complete the following:
1. APU switch — OFF.
2. ABORT START.
NOTE
Immediately motor engines alternately, until
rotors are stopped, to reduce the possibility of
engine residual fire.
9-1-45. Engine or Fuselage Fire — Flight.
Visible flames, smoke coming from the engine or the
lighting of the respective FIRE PULL handle:
1. Land as soon as possible.
F 2. Confirm Fire.
3. EMER ENG SHUTDOWN (affected engine).
After landing:
EMER ENG SHUTDOWN.
9-1-46. Engine Compartment, Fuselage, or Electrical
Fire — Ground.
1. EMER ENG SHUTDOWN.
2. APU switch — OFF (if operating).
3. BATT switch — OFF.
9-1-47. Electrical Fire — Flight.
Before shutting off all electrical power, the pilot must consider
the equipment that is essential to the current flight regime;
e.g. flight instruments, flight control systems, etc. If a landing
as soon as possible cannot be made, defective circuits may
be isolated by selectively turning off electrical equipment
and/or pulling circuit breakers.
WARNING
A dual engine flameout may occur if both
generator switches are turned off above
6,000 feet PA. All fuel boost pumps will be
inoperative.
1. Airspeed — 100 KIAS or Vne whichever is
slower.
TM 1-1520-240-10
9-1-23
NOTE
LCT and DASH actuators will remain programmed
at the airspeed at which the generators
were turned off. Normal engine trim is
disabled when generators are turned off.
2. GEN 1 and 2 switches — OFF.
3. Land as soon as possible.
After landing:
4. EMER ENG SHUTDOWN.
5. BATT switch — OFF.
9-1-48. Smoke and Fume Elimination.
1. Airspeed — Above 60 KIAS.
2. Pilot’s sliding window— Open.
3. Helicopter attitude —Yaw left, one half to
one ball width on turn and slip indicator.
4. Upper half of main cabin door — Open.
O 5. RAMP EMER switch — As required.
NOTE
The combination of steps 2, 3, and 4 effectively
evacuates the cockpit and forward cabin of
smoke and fumes at airspeeds above 60
KIAS. Opening the cargo loading ramp evacuates
the main cabin. With items in steps 2, 4,
and 5 opened, intensification of a smoldering
fire may occur. If the source of the fire cannot
be determined, close the cargo loading ramp
but keep the pilot’s windows and the upper
half of the main cabin door open. This will
allow the pilots to see the instrument panels
and outside references for landing.
6. Cargo loading ramp — As required.
7. Copilot’s sliding window — Closed.
8. NVG curtain — Open (if applicable).
9-1-49. Fuel System.
9-1-50. Aux Fuel Pump Failure.
An auxiliary fuel pump failure will be indicated by an AUX
PRESS indicating light, on the FUEL CONTROL panel,
illuminating and /or the fuel quantity in the affected tank
remaining at the same level. Should this occur, proceed
as follows:
1. FUEL QUANTITY selector switch — Check.
If one or both auxiliary fuel tanks have fuel remaining:
2. AC-DC FUEL PUMP circuit breakers —
Check in.
3. FWD and AFT AUX FUEL PUMP switches
affected side) — OFF.
4. AUX FUEL PUMP switch — ON (each aux
tank with fuel remaining).
If AUX PRESS indicating light remains on:
5. AUX FUEL PUMP switch(es) (inoperative
pump(s)) — OFF. Monitor FUEL QUANTITY
indicator for the affected tank.
6. AUX FUEL PUMP switche(es) — ON for
operative pumps or OFF for inoperative
pumps.
9-1-51. Fuel venting
Fuel venting from either main tank vent indicates a possibility
of fuel cell overpressurization. Should venting occur:
1. AUX FUEL PUMP switches (affected
side) — OFF.
2. Main tank (affected side) — Monitor.
When 1,000 pounds of fuel remain:
3. AUX FUEL PUMP switches — ON. (monitor
fuel quantity).
When tanks quantity reaches 1,600 pounds:
4. AUX FUEL PUMP switches — OFF.
5. Steps 2 through 4 — Repeat until
auxiliary tanks are empty.
9-1-52. L or R FUEL PRESS Caution.
If both main tank fuel pumps fail, fuel will be drawn from
the main tanks as long as the helicopter is operated
below 6,000 feet pressure altitude. If the L or R FUEL
PRESS caution comes on:
1. XFEED switch — OPEN (above 6,000 feet
PA).
2. FUEL PUMP (S) circuit breakers — Check in.
Pump(s) are operational — Proceed with step 3.
　
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