Airplane And Systems; The Airplane; Airframe - Piper Cherokee Arrow II PA-28R-200 1973 Pilots Operating Manual

THE AIRPLANE

composed entry and exit of tlie spacious interior Four individual seats allow individual comfort
for extended cross-country flights Sound proofing has been built into the aircraft t o reduce
fatigue and permit restful conversation. Simplicity of operation was designed into the aircraft to
allow the aircraft t o operate in VFR or IFR conditions with unhurried en route planning

AIRFRAME.

thermoplastic are used extensively for wing tip, engine cowling and non-stntcture components.
Tlie airframe lias been designed to a positive limit load factor of 3.8.
Tlie fuselage is a co~iventional semi-monocoque stnicture. External stringers on the bottoni
of tlie fuselage extend the length of the cabin area, and are used to maximize cabin room. On
tlie right side of tlie aircraft are a large cabin door and a large baggage compartment door.
Maintenance has been redticed t o a minimum with advanced fnselage design.
Tlie wing is of co~ivcntional design incorporating a laminar flow NACA 65,-415 airfoil
section. This allows fbr locating the main spar 40% aft of the leading edge, an arrangement
I t allows for a lighter wing strttcture to improve the useful load of the aircraft.
The wing also incorporates a rear spar ;tnd front stub spar. The main spar carries the
bending loads and the rear ;tnd stub spars cany torsional loads. The main spars are bolted into a
spat carry through at both sides of tlie filselage. The rear and stub spars are bolted to
attachments a t each side of tlie fi~selage.
The aileroiis are of modern metal construction i~icorporating a balance weight on the
outboard elid of each aileron, and are controlled by a right or left rotation of tlie control wheel.
Tlie flaps are also of metal constr~iction Wlicn tlit! llaps arc i n tlic retrautcd position, tlie
right flap acts as a step. The flap control is 1oi:ated between the front se:~ts.
The empennage consists of a vertical st;tbilizcr.
Directional and pitch trim are providcd will1 tlie rudder
Tlie trim tab on tlie stabilator also acts as an anti-servo control TIIC clilpc!inag<s < : o ~ i s t r ~ ~ c t i o ~ i
of a modern lightweight design.

AIRPLANE AND SYSTEMS

ISSIJED: JULY 13,1973
AIRPLANE. AND SYSTEMS
ARROW I1
is