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PWR lever to IDLE.
l ENG START light extinguishes prior to
52% NG.
I 2. LAND AS SOON AS POSSIBLE.
9.10.6 Smoke and Fume Elimination.
1. Airsneed - Slow to 20 KIAS maximum.
2. Canonv door (affected crew nosition) - Onen to intermediate
position,
/ 3. LAND AS SOON AS POSSIBLE.
9.10.7 Aborting Englne Start.
W Aborted engine starts may cause fuel
to collect in the engine nacelle. Subsequent
engine starts may be attempted only
after the nacelle door/work platform is
opened and the nacelle inspected for fuel.
If during the initial start an abnormal TGT
rise was evident, or fuel is evident in the
nacelle, the ignition system shall be
checked IAW standard maintenance procedures.
Abort start procedures are as follows:
1. PWR lever - OFF
2 . ENG START switch - IGN OVRD for 30 seconds or
until TGT is below 540 “C.
----
TM l-1520-238-10
9.11 ELECTRICAL SYSTEM FAILURES.
In the event any circuit breaker opens for
unknown reasons, do not attempt to reset
the breaker more than one time. Repeated
tripping of a circuit breaker is an indication
of a possible problem with equipment
or electrical wiring. Multiple attempts to
reset the circuit breaker may result in
equipment damage and/or an electrical
fire.
NOTE
l If generator fails in flight do not place generator
switch of failed generator in test position.
l During an electrical system malfunction and
operating on EMERG BATT power, the HSI/
RMI will not provide adequate indications to
the station. I
9.11.1 GEN 1 and GEN 2 Caution Light On.
NOTE
In the event both generacars are lost, turn offal1
unnecessary equipment on the emergency bus
to conserve battery power. Battery power, assuming
a 90% charge, is normally sufficient for
12 minutes emergency bus operation. When the
battery heater is inoperative/disconnected and
operating at temperatures below -30 “C
(-22 “F), power may only be available for one
minute of emergency operation.
1. GEN switches 1 and 2 - OFF/RESET - GEN.
If power is not restored:
2. GEN switches - OFF
3. LAND AS SOON AS PRACTICABLE.
9.12 HYDRAULIC SYSTEM FAILURES.
9.12.1 PRI HYD PSI and UTIL HYD PSI Light On.
1. EMSR HYD switch - On.
2. LAND WITHOUT DELAY. I
.
Change 7 9-13
--B----B---B----TM l-1520-23%10
Immediate emergency action must follow
failure of both hydraulic systems. Any hesitation
could result in loss of helicopter
control. With emergency hydraulic power
- in use, flight control inputs must be kept to
imperative that a landing be executed
without delay.
9.12.2 PRI HYD PSI and OIL LOW UTIL HYD Llght On. In
the event of a PRI HYD PSI failure and OIL LOW UTIL
HYD condition, hydraulic power to the tail rotor servo may
be lost. This may require a landing in accordance with TAIL
ROTOR FIXED PITCH MALFUNCTION paragraph 9..9.5.
1. LAND
9.13 LANDING AND DITCHING.
9.13.1 Emergency Landlng In Wooded Areas (Power Oft).
1. AUTOROTATE,
2. Collective - Adjust to maximum before main rota
acts tree branches.
9.13.2 Ditching (Power On). The decision to ditch the helicopter
shall be made by the pilot when an emergency makes
further flight unsafe.
1 .
2.
3.
4.
5.
6.
7.
8.
9.
Approach to hover.
Pilot shoulder harness - Lock.
CPG - Exit helicopter.
Hover downwind a safe distance.
PWR levers - OFF.
Perform hovering autorotation - Apply full collective
to decay RPM as helicopter settles.
Cyclic - Position in direction of roll.
Exit when main rotor has stopped.
9.13.3 Ditching (Power Off). If autorotational landing over
water becomes necessary
1 . AIJTOROTm - Apply full collective to decay rotor
RPM as helicopter settles.
2. ~oDies-J&tiso&r~ entw
3. &lic - position in d&&on of roll
Change 7
9.14 FLIGHT CONTROL FAILURES AND MALFUNCTIONS.
a . Failure of components within the flight control system
may be indicated through varying degrees of feedback, binding,
resistance, sloppiness or abnormal control response.
These conditions should not be mistaken for the malfunction
of the DASE.
b . Imminent failure of main rotor components may be indicated
by a sudden increase in main rotor vibration and/or
unusual noise. Severe changes in lift characteristics and/or
balance condition can occur due to blade strikes, skin separation,
shift or loss of balance weights or other material. Malfunctions
may result in severe main-rotor flapping. If the
　
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