Section I. AIRCRAFT SYSTEMS
9-1. AIRCRAFT SYSTEMS.
This section describes the aircraft systems
emergencies that may reasonably be expected to
occur and presents the procedures to be followed.
Emergency procedures are given in checklist form
when applicable. A condensed version of these
procedures is contained in the Operator's and
Emergency operation of avionics equipment is covered
in the appropriate Chapter 3, Avionics, and is repeated
in this section only if safety of flight is affected.
9-2. IMMEDIATE ACTION EMERGENCY CHECKS.
underlined for reference and shall be committed to
The urgency of certain emergencies
requires immediate action by the crew.
The most important single consideration is
aircraft control. All procedures are
subordinate to this requirement. Reset
after each malfunction to allow systems to
respond to subsequent malfunctions.
9-3. DEFINITION OF LANDING TERMS.
The term, "Land as soon as possible" is defined
as landing at the nearest suitable landing area (e.g.,
open field) without delay. The primary consideration is
to ensure the survival of the occupants.
The term, "Land as soon as practicable" is
defined as landing at a suitable landing area. The
9-4. AFTER EMERGENCY ACTION.
After a malfunction has occurred, appropriate
emergency actions have been taken, and the aircraft is
on the ground, make an entry in the remarks section of
DA Form 2408-13-1 describing the malfunction.
9-5. EMERGENCY EXITS AND EQUIPMENT.
Emergency exits and equipment are shown in
9-6. EMERGENCY ENTRANCE.
Entry can be made through the cabin emergency
hatch. Refer to Figure 9-1. The hatch can be
released by pulling on its flush-mounted, pull-out
handle, placarded EMERGENCY EXIT PULL
HANDLE TO RELEASE. The hatch is of the non-
hinged, plug type, which removes completely from the
frame when the latches are released. After the latches
are released, the hatch may be pushed into the
9-7. ENGINE MALFUNCTION.
a. Flight Characteristics Under Partial Power
characteristics during single-engine operation as long
as airspeed is maintained above minimum control
speed (Vmc) and power-off stall speed. The capability
of the aircraft to climb or maintain level flight depends
on configuration, weight, altitude, and free air
temperature. Performance and aircraft control will
improve by feathering the propeller of the inoperative
engine, retracting the landing gear and flaps, and
establishing the appropriate airspeed.
b. Engine Malfunction During and After
Takeoff. The action to be taken in the event of an
engine malfunction during takeoff depends upon
whether or not decision speed (V1) has been attained.
If an engine fails immediately after V1 , the takeoff will
be continued single-engine.
c. Engine Malfunction Before V1 (Abort). If
an engine fails and the aircraft has not accelerated to
recommended decision speed (V1), retard POWER
levers to IDLE and stop the aircraft.
1. POWER IDLE.
2. Braking As required.