Pitot-Static System - Piper PA-28-161 Pilot Operating Handbook

SECTION 7 PIPER AIRCRAFT CORPORATION
DESCRIPTION
&
OPERATION PA-28-161, WARRIOR II
7.21 PITOT-STATIC SYSTEM
The system supplies both pitot and static pressure for the airspeed
indicator, altimeter, and the optional vertical speed indicator (Figure
7~17).
Pitot and static pressure are picked up by a pitot head installed on the
bottom of the left wing and carried through pitot and static Jines within the
wing and fuselage to the gauges on the instrument panel.
An alternate static source is available as optional equipment. The
control valve is located below the left side of the instrument panel. When the
valve is set in the alternate position, the altimeter, vertical speed indicator
and airspeed indicator will be using cabin air for static pressure. The storm
window and cabin vents must be closed and the cabin heater and defroster
must
be
on during alternate static source operation. The altimeter error is
less than 50 feet unless otherwise placarded.
Both the pitot and static Jines can be drained through separate drain
valves located on the left lower side of the fuselage interior.
A heated pitot head, which alleviates problems with icing and heavy
rain, is available as optional equipment. The switch for the heated pi tot head
is located on the electrical switch panel to the left of the right control wheel.
To prevent bugs and water from entering the pitot and static pressure
holes, a cover should be placed over the pi tot head. A partially or completely
blocked pitot head will give erratic or zero readings on the instruments.
NOTE
During the preflight, check to make sure the
pitot cover is removed.
REPORT: VB-1180
7-18
ISSUED: AUGUST 13, 1982