Mooney 33-0001, Service And Maintenance Manual

Page: 276 / 1047

MOONEY INTERNATIONAL CORPORATION
M20V SERVICE AND MAINTENANCE MANUAL
Page
Date
13
MAR 2017
Rev Date
Level IV Maintenance Practice (con’t.) Procedures
Check Porous Panels 1. Remove Access panels for access to applicable Pro-
portioning Unit. Disconnect Nylon tube connecting sus-
pect panel from outlet of Proportioning Unit. Connect
suitable pressureable supply of filtered fluid to this tube.
Purge tube and panel at a pressure not exceeding 40
lbf/in
2
(2,6 bar). If a blockage exists, it will probably be-
come apparent at this stage. Reduce pressure to 4 lbf/
in
2
(0,26 bar) and examine porous region of panel for
even fluid coverage.
OR
2. Bench test. This is last resort due to having to remove
panel from Airframe.
Check fluid delivery from Windshield Pump. 1. Remove panels to gain access to pump(s). Discon-
nect Nylon tube connecting Pump to Solenoid Valve.
Operate pump by pressing ”WINDSHIELD” switch on
control panel. Collect fluid over a timed period of 5 sec-
onds. The fluid quantity dispensed should not be less
than 25 ml.
OR
2. Remove Windshield Pump and bench test.
Check Solenoid Valve.
NOTE:
Solenoid Valves have a history of reliability. It is
recommended that all other components be
checked out prior to further troubleshooting of
Solenoid Valves.
1. Check Windshield Pump as detailed above. Recon-
nect Windshield Pump to Solenoid Valve. Operate
pump by pressing ”WINDSHIELD” switch on control
panel. Fluid should be discharged onto the windshield,
if not, disconnect Nylon tube from outlet of Solenoid
Valve and repeat test. Fluid should be discharged from
outlet of Solenoid Valve. If not, check electrical power at
connections to Solenoid valve (ref. Figure 30- 1) when
pump is operating. If Solenoid Valve is suspected of not
closing, disconnect electrical power to the valve and
operate Windshield Pump. No fluid should be dis-
charged from the spraybar (or Solenoid Valve outlet).
OR
2. Remove Solenoid Valve and bench test.
Check Control Panel.
NOTE:
Voltages specified in Procedures are based on a
voltmeter with a resistance of at least 10,000
ohms per volt. Readings marked with * will differ
if a lower resistance voltmeter is used.
1. Remove screws and pull Control Panel out as far as
wiring will allow. Use voltmeter probe to measure volt-
age at the various pins in connectors C1 & C2 on rear
panel (Figure 30- 1 Schematic)
(1) Aircraft Power ON - all switches OFF
All pins zero volts except:
C1 - 3 to be aircraft voltage.
C1 - 2 to be 7.5 volts * .
C2 - 1 to be +5 volts.
C2 - 2 to be between zero and +2 volts *
(depending on tank contents)
C2 - 3 to be - 5 volts.
30-12-02