MOONEY INTERNATIONAL CORPORATION
M20V SERVICE AND MAINTENANCE MANUAL
Page
Date
5
MAR 2017
Rev Date
30-00-00 - GENERAL
The M20V aircraft incorporates an alternate air sy
stem
that is designed to open automatically any time the air
induction system becomes blocked. This system
should be inspected to assure that no heated air is en-
tering the induction system during routine engine op-
eration. (See Section 71-62-00 for rigging instructions).
This aircraft includes, as standard equipment, a heated
pitot tube assembly. The aircraft may also include, as
optional equipment, a propeller and airframe anti/de-
ice system. Refer to the manufacturers service data for
specific maintenance information (refer to the AS & T
08153- 01 or later revision Installation Manual).
-WARNING-
On M20V aircraft, if the primary alternator sys-
tem becomes inoperative and the Stand-by Al-
ternator system is the only power generatin g
source, the Stall Warning Horn will not sound.
30-10-00 - AIRFRAME ICING PROTECTION (TKS
SYSTEM – OPTIONAL)
The optional airframe icing protection system utilizes a
thin film of glycol based de- icing fluid to minimize the
adherence of ice. The system is comprised of porous,
titanium, panels fitted to the leading edges of the wing,
horizontal and vertical stabilizer. A slinger ring on the
propeller hub “slings” the same fluid over rubber boots
on each propeller blade. The installation also provides
icing protection for the pilot’s side of the windshield.
The de- icing fluid is stored in two interconnected tanks
located under the rear seat. These tanks have a total
capacity of 6.0 U.S. gallons (plus line capacity) and are
filled through a filler on the right side of the aft fuselage.
Fluid is pumped through nylon lines to proportioning
units located in each wing and in the aft fuselage. From
these, the fluid is routed to the porous panels and
pumped through laser drilled holes in the panels to flow
over the Airframe surfaces. The pilot’s side of the wind-
shield is provided fluid through a spray bar fed by a sep-
arate pump.
Approved de- icing fluids include:
-TKS-80
- TKS R238
- AL- 5 (DTD 406B)
30-11-00 - SERVICING - AIRFRAME ICING
PROTECTION
De- icing fluid absorbs and retains moisture. Residual
fluid that is not washed from the aircraft at recom-
mended intervals can get into skin laps and other fay-
ing surfaces and hold moisture. This may eventually
dissolve lubricants, and break down corrosion- protec-
tion coatings. Solid particles of various foreign materi-
als may attach themselves to the fluid and cause corro-
sive action of adjacent structural or rotating
components.
30-11-01 - WASHING
-CAUTION-
Do not use MEK (Methyl Ethyl Ketone) to clean
titanium panels. Discoloration will result.
Porous panels contain plastic parts which may
be damaged by some solvents including MEK
and some paint thinners.
The following solvents ONLY are permitted for
cleaning porous panels:
- Water (with soap or detergents)
- De- Icing Fluids (TKS 80, TKS R238, DTD
406B)
- Isopropyl or Ethyl Alcohol
- Aircraft Fuels (Gasoline or Kerosene)
It is recommended that the aircraft be rinsed with clear
water after each flight in which glycol based de- icing
fluid is used for icing protection. Special cleaning atten-
tion should be given to skin lap areas and areas where
antennas are mounted if de- icing fluid tends to flow
there.
30-11-02 - LUBRICATION
1. Rod End bearings on Flight Controls and Landing
Gear systems should be inspected frequently for indi-
cation of lubrication being washed off by ice protection
fluid. Re- lubricate as needed.
2. Inspect hinge point of all flight control surfaces,
landing gear doors, linkages, bellcranks, etc. for indica-
tion of lubrication being washed off by ice protection
fluid.
30-11-03 - ELECTRICAL
1. Clean electrical circuitry, I.E., contacts, terminals,
pins switches, relays, potentiometers, etc. in areas
where ice protection fluid flows.
2. Inspect and check operation of electrical compo-
nents/systems which have circuitry in ice protection
fluid flow areas prior to each flight.
30-12-00 - MAINTENANCE - AIRFRAME ICE
PROTECTION
1. Inspect ice protection system for proper fluid flow
at all panels.
2. Check for leaks at all panels with pump in the OFF
and ON position.
3. Check system metering pumps (2 each, located
under rear seats), for proper operating pressure. Use
system Control Panel for valid pressure verification.
A. Select “De- Ice”.
(1) The “De- Ice” LED should flash alternating
RED/GREEN and the “Anti- Ice” LED should flash
RED/OFF as system pressure rises.
-NOTE-
It may take a few minutes to build to proper
operating pressure.
30-00-00
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