7.21 PlTOT-STATlC SYSTEM
The pitot-static system supplies pressure to operate the airspeed
indicator, the altimeter and the optional vertical speed indicator (Figure
7-15). Pitot pressure is picked up by a pitot head installed on the bottom of
the left wing and static pressure is picked up by the pads on both sides of the
aft fuselage.
A static valve located below the center instrument panel under the left
side of the control quadrant provides an alternate static source for the
system when opened.* A static drain and static valve located on the lower left
side panel provides an alternate static source for the system when opened.**
A correction card, indicating the change in altimeter reading and indicated
airspeed when the alternate static source is in use, is mounted on the left side
of the control quadrant cover. Static lines can be drained through a valve
located inside an opening on the lower left 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 pitot head is
located on the electrical switch panel to the left of the control quadrant.
To prevent bugs and water entering the pitot hole, a cover should be
placed over the pitot head while the airplane is moored. A partially or
completely blocked pitot head will give erratic or zero readings on the
instruments.
NOTE
During preflight, check to make sure the pitot
cover is removed.
*S/N 38-78A0001 thru 38-81A0006
**S/N 38-78A0001 thru 38-81A0006, and S/N 38-81A0007 and up.
SECTION 7 PIPER AIRCRAFT CORPORATION
DESCRIPTION & OPERATION PA-38-112, TOMAHAWK
REPORT: 2126 ISSUED: JANUARY 20, 1978
7-16 REVISED: APRIL 28, 1989
7.21 PlTOT-STATlC SYSTEM
The pitot-static system supplies pressure to operate the airspeed
indicator, the altimeter and the optional vertical speed indicator (Figure
7-15). Pitot pressure is picked up by a pitot head installed on the bottom of
the left wing and static pressure is picked up by the pads on both sides of the
aft fuselage.
A static valve located below the center instrument panel under the left
side of the control quadrant provides an alternate static source for the
system when opened.* A static drain and static valve located on the lower left
side panel provides an alternate static source for the system when opened.**
A correction card, indicating the change in altimeter reading and indicated
airspeed when the alternate static source is in use, is mounted on the left side
of the control quadrant cover. Static lines can be drained through a valve
located inside an opening on the lower left 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 pitot head is
located on the electrical switch panel to the left of the control quadrant.
To prevent bugs and water entering the pitot hole, a cover should be
placed over the pitot head while the airplane is moored. A partially or
completely blocked pitot head will give erratic or zero readings on the
instruments.
NOTE
During preflight, check to make sure the pitot
cover is removed.
*S/N 38-78A0001 thru 38-81A0006
**S/N 38-78A0001 thru 38-81A0006, and S/N 38-81A0007 and up.
SECTION 7 PIPER AIRCRAFT CORPORATION
DESCRIPTION & OPERATION PA-38-112, TOMAHAWK
REPORT: 2126 ISSUED: JANUARY 20, 1978
7-16 REVISED: APRIL 28, 1989
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