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 Crewmember s Checklist, TM 1-1510-262-CL. Emer-
gency operation of avionics equipment is covered, when appropriate, in Chapter 3, Avionics, and is repeated in
this section only if safety of light is affected.
9-2. IMMEDIATE ACTION EMERGENCY CHECKS.
Immediate action emergency items are underlined for your reference and shall be committed to memory.
The urgency of certain emergencies requires immediate action by the pilot. The most important
single consideration is aircraft control. All procedures are subordinate to this requirement.
9-3. DEFINITION OF LANDING TERMS.
The term LAND AS SOON AS POSSIBLE is deined as landing at the nearest suitable landing area (i.e., open
ield) without delay. (The primary consideration is to ensure the survival of occupants.)
The term LAND AS SOON AS PRACTICABLE is deined as landing at a suitable landing area. (The primary con-
sideration is the urgency of the emergency.)
9-4. EMERGENCY EXITS AND EQUIPMENT.
Emergency exits and equipment are shown in igure 9-2.
9-5. EMERGENCY ENTRANCE.
Entry may be made through the cabin emergency hatch. The hatch may be released by pulling on its lush-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 in.
9-6. ENGINE MALFUNCTION.
a. Flight Characteristics Under Partial Power Conditions. There are no unusual light characteristics dur-
ing single engine operation as long as airspeed is maintained at or above minimum control speed (VMCa). The
capability of the aircraft to climb or maintain level light depends on coniguration, gross 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 laps, and establishing the single engine best rate-of-climb speed (Vy).
b. Engine Malfunction Prior To or At V 1 , (Abort). If an engine should fail, or the crew determines that an
abort is warranted prior to or at V 1 , utilize the following procedures:
1. POWER levers -- GROUND FINE.
2. Braking -- As required.
3. Reverse thrust -- As required.
If insuficient runway remains for stopping, perform the following:
$ CONDITION levers -- FUEL CUTOFF.