MOONEY INTERNATIONAL CORPORATION
M20V SERVICE AND MAINTENANCE MANUAL
Page
Date
5
MAR 2017
Rev Date
24- 00- 00 - GENERAL
Main Alternator System
A 28 volt, 100 AMP alternator (90 amps max. output)
utilizing a transistorized voltage regulator/over voltage
control supplies electrical power for the main alternator
source. Two 24 volt, 11 AMP HR storage batteries are
installed in the tailcone. The alternator, during normal
operation, supplies power in conjunction with the se-
lected battery when the Master Switch and Alternator
Field Switch is - ON. The circuit breaker panel is on the
right subpanel. The electrical system is capable of sup-
plying current for simultaneous operation of multiple ra-
dios, anti- collision lights and navigation lights.
Standby Alternator System
An optional standby system provides 30 volts, with 20
amps of power to support continued flight in the event of
primary alternator failure. The Standby alternator is
installed on the accessory pad location. Panel mounted
equipment includes two standard pull type circuit
breakers (1 amp and 5 amp). Appropriate placards are
provided for each panel mounted device. The regulator
is mounted in the RH nosegear wheelhouse area on the
M20V model aircraft. If the primary alternator fails in
flight, the pilot activates the standby alternator. If the
current requirement is over 26.5 volts when the stand-
by alternator is activated, the annunciation will flash.
The pilot is advised to choose which equipment he
needs for the given flight conditions by simply keeping
the total load below the flashing point of the annunci-
ation. This will reserve battery energy for transient
loads during approach (refer to the M20V POH/AFM
for specific equipment limitations). Loads may be
beyond the flashing point of the G1000 annunciation for
up to 5 minutes without damaging the standby alterna-
tor.
-NOTE-
The standby alternator system is required equip-
ment for the installation of the certified flight into
known icing TKS STC kit on the M20V aircraft.
GARMIN G1000
Refer to Garmin G1000 Maintenance
and Configura-
tion
Manual for electrical system status and displays
and the Garmin G1000 System Maintenance Manual
190- 00907- 00.
24- 30- 00 - D.C. GENERATION
24- 31- 01 - CHARGING SYSTEM MAINTENANCE
MAIN ALTERNATOR
1. Alternator Systems Servicing
When the ammeter (Garmin G1000 MFD display)
shows a discharge at higher RPM, a charging system
component (alternator, voltage regulator, circuit break-
er or wiring) is malfunctioning. On- the- plane testing
should identify which component(s) may be faulty and
needs to be removed from the aircraft for bench test
and subsequent repair or replacement.
The alternator charging system requires no special
attention; however, improper maintenance procedures
can damage the alternator and wiring. There are sever-
al precautions that must be observed when servicing
the alternator system:
A. Be sure the Master Switch is OFF when repair-
ing the alternator or voltage regulator.
-CAUTION-
Only when performing functional checks on
ground, First connect t he approved Auxiliary
Power Cable to the booster battery and then in-
sert the plug into the auxiliary power receptacle.
B. Refer to 24-31-04 for Auxiliary Power System in-
structions.
-CAUTION-
Both batteries MUST BE in aircraft for flight.
C. When either battery is removed from the aircraft
for charging, be sure that the charger is correctly con-
nected. Use the correct charging rate when charging
battery, refer to manufacturer’s procedures.
D. Be sure to check battery polarity by using a volt-
meter prior to reinstallation into the aircraft.
E. Do not leave Master Switch ”ON” when aircraft
is parked.
F. Use an auxiliary ground power unit when trou-
bleshooting electrical accessory equipment or when
performing electrical landing gear maintenance and re-
traction system testing.
-CAUTION-
DO NOT ATTEMPT TO POLARIZE ALTERNA-
TOR. Alternator is polarized every time Master
Switch is turned ON causing wire lead to Al-
ternator to become energized “Live Wire”.
2. Alternator System Inspection
A. Check alternator circuit breaker on the main cir-
cuit breaker panel. Reset breaker, if open.
B. Check alternator field circuit breaker on main
circuit breaker panel. Reset, if open.
C. Inspect batteries for corroded cable connec-
tions; remove and clean cable(s) if corrosion is found.
D. Check charging system wiring and connectors
to be sure they are clean and tight.
E. Inspect alternator, voltage regulator, and wiring
for damage.
3. Alternator Removal and Installation
A. Alternator Removal
24-00-00
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