Mooney M20TN, Руководство по обслуживанию и ремонту

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MOONEY AVIATION COMPANY, INC.
M20TN SERVICE & MAINTENANCE MANUAL
Date
2006
Rev Date
Page 5
34--00--00 -- GENERAL
M20TN aircraft are equipped with a GARMIN G1000
Integrated Avionics System utilizing two Garmin
10XX
Multi Function Display
Units (CDUs) installed in the
M20 instrument panel. One is configured as a Primary
Flight Display (PFD) and the other as a Multi--Function-
al Display (MFD). The displays are located side--by--
side, with the GMA 1347 Audio Panel located in the
middle.
The PFD displays graphical flight instrumentation in
place of traditional gyro instruments. Attitude, heading,
airspeed, altitude, and vertical speed are all shown on
one display. The MFD shows a full--color moving map
with navigation information. Both displays offer control
over COM and NAV frequency selectors, as well as
heading, course/baro and altitude reference functions.
On the left of the MFD display, an Engine Indication
System (EIS) cluster shows graphical depictions of en-
gine and airframe instrumentation.
Both displays are installed in the instrument panel us-
ing built--in ¼ --turn fasteners. Each display uses a
single Garmin 62--pin connector. Electrical power to
both the PFD and MFD is supplied from the ‘Essential’
buss.
On the panel, traditional attitude, altitude, and airspeed
indicators are retained as backup instruments. These
are mounted in a vertical configuration to the right of the
MFD.
A “Traditional” magnetic compass is mounted on the
windshield center post.
Service, maintenance and troubleshooting instructions
specific to the Garmin G1000 Integrated System are
provided in the Garmin G1000 System Maintenance
Manual.
The glareshield must be removed and plumbing dis-
connected on traditional flight instruments before they
can be removed. Remove glareshield attaching
screws, center post cover screws. Carefully lift center
post cover and glareshield from panel. Disconnect gla-
reshield and compass lights.
Reinstall glareshield in reverse sequence.
34--10--00 -- PITOT & STATIC AIR PRESSURE
SYSTEM
Static pressure instruments are extremely sensitive to
pressure changes; therefore, the Pitot and static sys-
tem must be kept free from moisture and obstructions.
Drain Pitot and static systems after humid or wet
weather. If instrument operation is erratic or inoperative
after draining, perform the following:
1. Pitot system hose inspections -- Inspect hose sec-
tions for signs of deterioration. Check all tubing for
brittleness, checks or cracks particularly at bends or
connecting points. When new hose is installed, check
system for leaks using PITOT SYSTEM LEAK TEST
procedure.
2. Pitot system leak test -- (Make sure Master Switch
is OFF and Gear Control is in DOWN position).
A. Slip end of a short rubber hose over Pitot tube.
B. Close open end of hose; slowly roll up hose until
traditional airspeed indicator reads 150 MPH.
C. Clamp hose and hold for one minute.
D. If airspeed indicator falls more than 9 KIAS,
within one minute, check system for leaks and tighten
line fittings.
E. Repeat steps B, C, and D until obtaining less
than a 9 KIAS indicator reading drop.
-- CAUTION --
Release air pressure slowly by unrolling rubber
tubing. A sudden release of the air pressure may
damage airspeed indicator.
3. Static system cleaning -- Blow low air pressure
(10--25 PSI) through lines from disconnected line at air-
speed indicator to static ports. Cover each static port
separately when blowing to insure that each line is
clear. Instrument error or possible damage may result if
even one port is clogged with dirt or foreign matter.
-- CAUTION --
NEVER BLOW AIR through the line TOWARD the
INSTRUMENT panel; to do so will seriously dam-
age instruments. When blowing back through
line from instrument panel, make sure that no air
is blown into instruments.
4. Static system leak test -- The static system should be
checked for leaks in accordance with instructions in
Federal Aviation Regulation 91.411, paragraph (c), ap-
pendix E, part 43.
-- CAUTION --
To avoid damaging either the airspeed indicator
or the landing gear airspeed safety switch an
equal pressure should be applied to the Pitot
side of the indicator while leak testing the static
system.
5. Alternate static source -- An alternate static source
valve is provided to change the static air source from
outside the aircraft to inside the cabin. The valve is lo-
cated on the lower panel under the pilots control col-
umn. Airspeed indicator and altimeter readings will be
slightly affected when using the alternate static source.
AUGUST 2010
34--00--00