TM 55-1510-215-10
CHAPTER 2
AIRCRAFT AND SYSTEMS DESCRIPTION AND OPERATION
Section I. AIRCRAFT
2-1. Introduction.
2-3. Dimensions.
The purpose of this chapter is to describe the aircraft
Overall aircraft dimensions (fig. 2-3) are as follows:
and its systems and controls which contribute to the
physical act of operating the aircraft. It does not contain
Wing Span
45 ft 10.5 in
descriptions of avionics and mission equipment, covered
elsewhere in this manual.
This chapter contains
Length
35 ft 6 in
descriptive information and does not describe
procedures for operation of the aircraft.
These
Height (at rest)
14 ft 2.56 in
procedures are contained within appropriate chapters in
the manual. This chapter also contains the emergency
Tread (between center
12 ft 9 in
equipment installed. This chapter is not designed to
lines of main wheels)
provide instructions on the complete mechanical and
electrical workings of the various systems; therefore,
2-4. Ground Turning Radius.
each is described only in enough detail to make
comprehension of that system sufficiently complete to
Minimum ground turning radius of the aircraft is 29 ft
allow for its safe and efficient operation.
8.75 in (fig. 2-4).
2-2. General.
2-5. Maximum Weights.
The U-21G is an unpressurized, low wing, all metal
Maximum takeoff gross weight is 9,650 pounds.
aircraft, powered by two T74-CP-700 turbo-prop engines
Maximum landing weight is 9,168 pounds. Maximum
and has all-weather capability (figs. 2-1, 2-2).
ramp weight is 9,705 pounds.
Distinguishable features of the aircraft are the slender,
streamlined engine nacelles, square-tipped wing and tail
2-6. Landing Gear System.
surfaces, a swept-back vertical stabilizer and a ventral
fin below the empennage. The basic mission of the
The landing gear is a retractable, tricycle type,
aircraft is to provide a utility service in the combat zone
electrically operated by a single DC motor. This motor
supporting field commanders and their staff in the
drives the main landing gear actuators through a gear
conduct of command and control functions, troop
box and torque tube arrangement, and also drives a
transport, aero-medical evacuation, administration,
chain mechanism which controls the position of the nose
liaison, and inspection. Cabin accommodations include:
gear. Spring-loaded locks secure the main gear in the
six passenger-controlled reading lights mounted in the
down position, while the jackscrew in the actuator
cabin cold air outlet panels along the ceiling; one relief
secures the nose gear in the down position. The
tube aft of the cabin entrance door. A relief tube is
jackscrew in each actuator holds all three gears in the
installed under the pilot's seat. Special equipment in the
UP position, when the gear is retracted. A friction clutch
passenger-cargo (cabin) compartment is removable.
Cabin entrance is made through a stair-type door on the
motor from electrical overload in the event of a
left side of the fuselage. The pilot and copilot seats are
mechanical malfunction. A 50-ampere push-to-reset
side-by-side and separated from the cabin by a
type circuit breaker, placarded LANDING GEAR
removable curtain. A minimum crew of one pilot is
POWER, located on the copilot's circuit breaker panel
required for normal aircraft operation.
Gear doors are opened and closed through a
mechanical linkage connected to the landing gear. The
nose wheel steering mechanism is automatically
Change 7 2-1
