Piper Cherokee Arrow II Pilots Operating Manual page 20

ARROW I1
DESCRIPTION
AIRPLANE AND SYSTEMS
THE AIRPLANE
The Cherokee Arrow I1 is a single-engine, retractable landing gear, all metal aircraft.
Increased fuselage length has enhanced the comfort in the rear seats. A large cabin door allows
composed entry and exit of the spacious interior. Four individual seats allow individual comfort
for extended cross-country flights. Sound proofing has been built into the aircraft to reduce
fatigue and permit restful conversation. Simplicity of operation was designed into the aircraft to
allow the aircraft to operate in
VFR
or
IFR
conditions with unhurried en route planning.
AIRFRAME
Aluminum alloy construction has been used throughout for the primary structure except
for the steel tube engine mount, steel landing gear struts and isolated areas. Fiberglass and
thermoplastic are used extensively for wing tip, engine cowling and non-structure components.
The airframe has been designed to a positive limit load factor of 3.8.
The fuselage is a conventional semi-monocoque structure. External stringers on the bottom
of the fuselage extend the length of the cabin area, and are used to maximize cabin room. On
the right side of the aircraft are a large cabin door and a large baggage compartment door.
Maintenance has been reduced to a minimum with advanced fuselage design.
The wing is of conventional design incorporating a laminar flow NACA 652-415 airfoil
section. This allows for locating the main spar 40% aft of the leading edge, an arrangement
which benefits the structure in two ways.
1. It provides unobstructed cabin space for the rear passengers.
2.
It allows for a lighter wing structure to improve the useful load of the aircraft.
The wing also incorporates a rear spar and front stub spar. The main spar carries the
bending loads and the rear and stub spars carry torsional loads. The main spars are bolted into a
spar carry through at both sides of the fuselage. The rear and stub spars are bolted t o
attachments at each side of the fuselage.
The ailerons are of modern metal construction incorporating a balance weight on the
outboard end of each aileron, and are controlled by a right or left rotation of the control wheel.
The flaps are also of metal construction. When the flaps are in the retracted position, the
right flap acts as a step. The flap control is located between the front seats.
The empennage consists of a vertical stabilizer, a rudder and a horizontal stabilator. The
empennage construction is of a modem lightweight design.
AIRPLANE AND SYSTEMS
REVISED: JUNE 27,1975