MOONEY INTERNATIONAL CORPORATION
M20V SERVICE AND MAINTENANCE MANUAL
Page
Date
19
MAR 2017
Rev Date
3. Reading Lights.
A momentary switch operates 4
overhead lamps in 3 modes. Reading Light Switch
UP position, only the Pilot reading light is activated.
With Reading Light Switch in Down position, ALL
reading lights are activated. Passenger switches lo-
cated on each passenger’s arm rest (excluding front
seat passenger) can now activate On, Off or DIM in-
dividual reading lights. Front seat passenger’s light
switch is located forward of cabin door hinge on side
panel.
4. Strobe light combination switch turns wing tip
and tail strobe lights ON. Should a short occur, the
combination switch/circuit breaker will automatically
trip to the OFF position
.
5. Recognition Lights -
Recognition light combina-
tion switch/circuit breaker turns recognition light ON.
Should a short occur, combination switch/circuit
breaker will automatically trip to OFF position.
6. Glareshield and Panel Lights. A momentary light
switch UP position will illuminate full strength or
DOWN increases/decreases light intensity for the in-
strument panel area.
7. Reading and OH Lights - Overhead lights illumi-
nate the cabin, 1 dome and 4 reading lights. All pas-
senger reading lights are controlled by a main switch
located on the instrument panel below the PFD. With
Reading Light Switch UP position, only the Pilot
reading light is activated. With Reading Light Switch
in Down position, ALL reading lights are activated.
Passenger switches located on each passenger ’s
arm rest (excluding front seat passenger) can now
activate On, Off or DIM individual reading lights.
Front seat passenger’s light switch is located for-
ward of cabin door hinge on side panel. A moment-
ary light switch has been installed on both cabin and
baggage doors. When one of the cabin or baggage
doors are opened, the overhead dome light will illu-
minate for approximately 5 minutes and then distin-
guish until door has been shut and reopened again.
-CAUTION-
The cabin and baggage interior lights are not
connected to the Master Swi tch circuitry and
can be operated with Master Switch in the - Off
- position. Care must be exercised to prevent
leaving switch(es) ON and discharging one of
the batteries.
8. Map Light -
Map lights are installed on the bot-
tom of the pilot and co- pilot’s wheel. These lights are
turned on when the INSTRUMENT light control on
the panel is turned on. The intensity of the map light
maybeadjustedwiththeMAPLITEknoblocated
(while facing the wheel) on the right aft side of the pi-
lot’s and co- pilot’s control wheel.
24- 36- 00 - LANDING GEAR CIRCUITS
1. Limit switches and relays operate the reversible
landing gear actuator motor. A landing gear, air pres-
sure, safety switch, actuated by pitot air pressure, pre-
vents landing gear retraction until a safe flying speed is
attained. The landing gear control switch operates ac-
tuator motor through the safety switch and relays.
When the landing gear control switch is UP and a safe
flying speed has been attained, the safety switch
closes to activate the control relay and the actuator
starts. As the gear reaches the up and locked position,
a mechanical up stop opens the limit switch and the ac-
tuator stops. When landing gear control switch is
placed in the DOWN position, the gear motor down-
relay closes and the actuator starts. When the gear
reaches the down- and- locked position, a mechanical
down stop opens the limit switch and the actuator
stops. The gear- up limit switch controls the landing
gear un- safe light. The RED light comes on when the
gear is in transit. The green light comes on when the
gear reaches the down- and- locked position; the gear-
down limit switch controls the green gear- down light.
The GEAR DOWN annunciation is displayed on the
G1000.
2. Gear Safety By- Pass Switch.
Gear safety over-
ride switch is a manual means of electrically by-
passing the Air speed Safety Switch. In the event the
landing gear switch is placed in gear-up position, a
properly operating Airspeed Safety Switch prevents
gear from being retracted before take off speed of
approximately 60 5 KTS is reached. To retract
landing gear at a lower air speed, the GR SAFETY
BY PASS switch may be held de-pressed until land-
ing gear is completely retracted.
24- 37- 00 - FUEL SYSTEM CIRCUITS
The fuel system has an electric fuel boost pump. The
fuel quantity indicating system is comprised of two
transmitters in each fuel tank (inboard and outboard)
and is displayed on the G1000 screen.
1. Fuel Pump Circuit. - A single, auxiliary electric boost
fuel pump is controlled by two switches and a relay (lo-
cated behind PFD mtg. on Air Data Computer bracket).
The LOW BOOST switch is utilized for engine starting
procedures and to purge fuel vapors from system dur-
ing high temperature conditions, either heat soak con-
ditions or high OAT.
The HIGH BOOST is utilized for use if the engine driven
fuel pump malfunctions and will provide sufficient fuel
for partial power operation of the engine.
2. Fuel Quantity is displayed on the G1000 screen.
Changes in fuel level vary fuel quantity transmitter re-
sistance (two in each tank work in series with each oth-
er) that operates the fuel quantity gauges. The Master
Switch activates the fuel quantity indicating system.
Refer to Garmin G1000 Line Maintenance
and Config-
uration M
anual and/or an Authorized Garmin Service
Center.
24-36-00
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