Piper ARCHER III - Pitot-Static System

SECTION 7
DESCRIPTION & OPERATION PA-28-181, ARCHER III
SECTION 7
DESCRIPTION & OPERATION PA-28-181, ARCHER III
REPORT: VB-1611 ISSUED: JULY 12, 1995
7-18
REPORT: VB-1611 ISSUED: JULY 12, 1995
7-18
7.21 PITOT-STATIC SYSTEM
The system supplies both pitot and static pressure for the airspeed
indicator, altimeter and the
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 lines within the
wing and fuselage to the gauges on the instrument panel.
An alternate static source is standard 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 lines 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 standard equipment. The switch for the heated pitot head is located
on the electrical switch panel above the throttle quadrant.
To prevent bugs and water from entering the pitot and static pressure
holes, a cover should be placed over the pitot 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.
7.21 PITOT-STATIC SYSTEM
The system supplies both pitot and static pressure for the airspeed
indicator, altimeter and the
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 lines within the
wing and fuselage to the gauges on the instrument panel.
An alternate static source is standard 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 lines 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 standard equipment. The switch for the heated pitot head is located
on the electrical switch panel above the throttle quadrant.
To prevent bugs and water from entering the pitot and static pressure
holes, a cover should be placed over the pitot 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.