Piper PA-28-161 User Manual

PIPER AIRCRAFT CORPORATION
PA-28-161,
WARRIOR II
SECTION 1
GENERAL
(C)
{d)
Indicated
Pressure
Altitude
Pressure Altitude
Station Pressure
Wind
Power TL·rminology
Takeoff Power
Maximum Con-
tinuous Power
Maximum Climb
Power
Maximum Cruise
Power
Engine I1Hruments
EGT l•aug..:
ISSUED: Al'Gl'S'f 13. 1982
REVISED: Jl ;q: 28. 1984
The number actually read rrom an
altimeter when the barometric subscale has
been set
to 29.92 inches of mercury { (Q 13.2 ·
millibars).
Altitude
measured from standard sea~level
pressure {29.92 in. Hg) by a pressure or
barometric altimeter. It is the indicated-
pressure altitude corrected for position: a.nct
instrument error. In this handbook.
altimeter instrument errors are assumed
to be zero.
Actual atmospheric pressure at field·
elevation.
The wind velocities recorded as variables
on the charts of this handbook are to be
understood as the headwind or tailwind
components of the reported winds.
Maximum power permissible for takeoff.
Maximum power permissible continuously
during flight.
Maximum power
permissible during
climb.
Maximum power
permissible during
cruise.
Exhaust Gas Temperature liauge
REPORT: VB-1180
1-7

Piper PA-28-161 Specifications

General

Manufacturer	Piper Aircraft
Model	PA-28-161 Warrior II
Engine	Lycoming O-320-D3G
Horsepower	160 hp
Seating Capacity	4
Wingspan	35 ft (10.7 m)
Length	24 ft 0 in
Maximum Speed	127 knots
Cruise Speed	122 knots
Maximum Takeoff Weight	2, 325 lb (1, 055 kg)
Fuel Capacity	48 US gallons (182 L)