Piper Aircraft Corporation Malibu Mirage PA-46-350P, Airplane Maintenance Manual

Page: 929 / 1956

PAGE 1
Feb 28/07 5C11
34-10-00
PIPER AIRCRAFT, INC.
PA-46-350P, MALIBU MIRAGE
MAINTENANCE MANUAL
FLIGHT ENVIRONMENT DATA
The instrument air system consists of pitot air and static air sources. The system supplies both pitot and
static air pressure for the airspeed indicator, and static pressure for the altimeter, vertical speed
indicator, and the triple indicator (cabin pressure differential, vertical speed, and altitude). When
installed, pitot and static air pressure is also provided for either the Meggitt EFIS or Avidyne Entegra
EFIS Air Data and Attitude Heading Reference System (ADAHRS).
1. Pitot and Static Systems
A. Description and Operation
The pitot air system consists of pitot mast (located on the underside of the left wing, Avidyne
installations include pitot mast locations on the underside of both the left and right wing) with its
related plumbing. Impact air pressure entering the pitot tube is transmitted from the pitot inlet,
through hose and tubing, routed through the wing to the airspeed indicator(s), located on the
instrument panel; and, if installed, to the ADAHRS unit located on the aft equipment shelf (Meggitt)
or in each PFD (Avidyne). A partially or completely blocked pitot head will give erratic, erroneous, or
zero reading on the instruments.
The static air source consists of either two static por ts, one on each side of the fuselage
(S/N’s 4636001 thru 4636374) or four static ports, two on each side of the fuselage (S/N’s 4636375
and up) aft of F.S. 265.80. The static air system is connected to the airspeed indicator(s),
altimeter(s), vertical speed indicator and the triple indicator (cabin pressure differential, vertical
speed, and altitude), located on the instrument panel; and, if installed, to the ADAHRS unit located
on the aft equipment shelf (Meggitt) or in each PFD (Avidyne); by means of hose and tubing routed
through the fuselage. In the event the primary static source becomes blocked, the system
incorporates an external alternate static por t located on the bottom of the fuselage aft of
F.S. 241.50. A shutoff valve, located below the instrument panel to the left of the pilot, opens or
closes the alternate static port as required. A placard giving instructions for use of alternate static
pressure, is located on the instrument panel or pilot’s window frame.
WARNING: DO NOT ATTEMPT TO DRAIN STATIC SYSTEM DURING PRESSURIZED FLIGHT.
If one or more of the pitot static instruments malfunction, the system should be checked for dirt,
leaks or moisture. A partially or completely blocked pitot head will give erratic, erroneous, or zero
reading on the instruments. Pitot and static lines can be drained through the drain valve located on
the left lower side of the fuselage interior.
The holes in the sensors for pitot and static pressure must be fully open and free from blockage.
Blocked sensor holes will give erratic or zero readings on the instruments.
The heated pitot head(s) is(are) standard equipment. The pitot heat switch is located on the right
overhead switch panel. Static source pads have been demonstrated to be non-icing; however, in the
event that icing does occur, selecting the alternate static source will alleviate the problem.
B. Troubleshooting
See Chart 1. With the optional Meggitt EFIS installation, see also, Appendix 1 (grid 5K19).
C. Test
(PIR-PPS 60035, Rev. M / FTP2001-8, Rev. E.)
This test requires a pitot/static test fixture (i.e. - Aerosonic Air Data Test Set - Model 90000-0168,
Barfield P/N 101-00164, or equivalent) and calibrated air source (i.e. - airspeed simulator) and
should be performed at any time an instrument, fitting, line, pitot head, or static button is
disconnected. The test should be performed prior to the next flight.
NOTE: Ensure the lines and fittings are free of any entrapped moisture or restrictions.