Piper PA-28-161 Maintenance Manual

PIPER AIRCRAFT, INC.
PA-28-161, WARRIOR III
MAINTENANCE MANUAL
PAGE 1
Nov 30/06
3G9
34-10-00
FLIGHT ENVIRONMENT DA
T
A
1. Pitot-Static System
The pitot air system consists of a pitot mast on the underside of the left wing with its related plumbing.
Impact air pressure entering the pitot is transmitted from the pitot inlet through hose and tubing routed
through the wing to the airspeed indicator (and Avidyne Entegra PFD, if installed) on the instrument
panel. A partially or completely blocked pitot head will result in erratic or zero instrument readings.
The static air system consists of interconnected static ports on the underside and aft side of the (pitot)
static mast. The ports are connected to the airspeed indicator, altimeter, and vertical speed indicator
(and Avidyne Entegra PFD, if installed) by hose and tubing routed through the wing.
An alternate static air source is located below the instrument panel in front of the pitot. The alternate
static source is part of the standard system. It incorporates a shutoff valve to close the port when not
needed.
Pitot and static lines are drained through separate drain valves on the left lower side of the fuselage
interior.
Pitot / Static System Installation
Figure 1 (Sheet 1 of 2)

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)