MOONEY INTERNATIONAL CORPORATION
M20V SERVICE AND MAINTENANCE MANUAL
Page
Date
5
MAR 2017
Rev Date
27-00-00 − GENERAL
The aircraft has dual flight controls and can be flown
from either the pilot or co−pilot seat. Dual pairs of foot
pedals control the rudder and nose wheel steering
mechanisms. Push pull tubes actuate the all−metal
flight control surfaces. Rod−end bearings are used
throughout the flight control systems. These bearings
are simple and require little maintenance other than oc-
casional lubrication. Specially designed aluminum−
alloy extrusions, that permit flush skin attachment, form
the leading edges of the rudder and elevators. Electri-
cally actuated wing flap systems are installed on all
models. Longitudinal pitch trim is achieved through a
trim control system which pivots the entire empennage
around tailcone attachment points.
Flight control surfaces that have been stripped, re-
painted, repaired or altered are required to be re−
checked for balance per instructions provided in Sec-
tion 27−93−00.
Garmin G1000 system programs must be calibrated to
these and other systems, as described in the Garmin
service literature:
− Flap Position
− Rudder Trim
− Elevator Trim
− Stall Warning Switch
− Autopilot Systems
Refer to Garmin G1000 Line Maintenance and Config-
uration Manual for detailed calibration instructions. The
Garmin G1000 instructions for Flight Control calibra-
tion may, as applicable, utilize the procedures as pro-
vided in this chapter.
Auto Pilot Systems (Optional)
Mooney M20V aircraft come equipped with optional
auto pilot systems. Refer to Chapter 22 and also the au-
topilot manufacturer documentation for specific instal-
lation, rigging, maintenance, adjustments, trouble-
shooting procedures and equipment specifications.
27-10-00 − AILERON SYSTEM
The ailerons are of all−metal construction with beveled
trailing edges. Three hinges attach the ailerons to the
aft wing spar outboard of the wing flaps. The ailerons
link to the control wheel through push−pull tubes and
bellcranks. Lead counter−weights static balance the ai-
lerons.
1. Aileron Removal and Installation.
A. Remove control tube attaching bolt, nut and
washer at aileron horn.
B. Remove bolts, nuts and washers from the three
attaching hinges.
C. Remove aileron by pulling it straight aft until
hinges are clear; rotate inboard portion down and for-
ward to allow aileron balance weights to clear wing tip.
D. Reinstall aileron in reverse sequence of remov-
al.
E. Recheck bolts for security and safety.
2. Aileron Rigging.
A. Level control wheels − (A) (Fig. 27−1).
B. Install 3/16 dia. rig−pins at:
(1) Bellcrank (E) (Fig. 27
−1)
(2) Bellcranks (9) (Fig. 27−2) (L.H. and R.H.)
C. To position ailerons at 0
o
to 2
o
down, Loosen
jam nut (7) at control tubes (J) at (Fig. 27−2) (L.H. and
R.H.). Disconnect (J) at aileron horn. Turn (J) one revo-
lution in direction desired. Reconnect (J) at aileron
horn. Tighten jam nut (7).
D. Adjust remaining control tubes (F) at 6, (B) at 1
and (D) at 2, (Fig. 27−1) (L.H. and R.H., if applicable) in
order to freely attach to bellcranks and jackshaft.
E. Remove rig−pins.
F. Adjust aileron stops (8) (Fig. 27−2) per the fol-
lowing procedures:
(1) Position travel board, GSE030003−200, at
W.S. 147.75 (Fig. 27−3).
-NOTE-
Wing station 147.75 is located at skin splice line
between flap outboard end and aileron inboard
end.
(2) Adjust static position from 0
°
to 2
°
DOWN.
(Ref. point is 0
°
mark on travel board).
(3) DOWN travel: 8
°
1
°
from static position.
(4) UP travel: 12.5
°
to 14.5
°
from static position.
-NOTE-
The above aileron rigging and adjustment in-
structions apply to both the left and right
ailerons.
27-20-00 − RUDDER AND STEERING SYSTEM
The rudder attaches to the aft vertical fin spar at four
hinge points. Push−pull tubes and bellcranks link the
rudder to the rudder pedals. A rudder trim system is in-
corporated into the M20V aircraft for pilot comfort for
high−power settings during climb and, if needed, for
cruise power settings
1. Rudder Removal and Installation.
A. Detach rudder push−pull tube from rudder horn.
B. Disconnect Strobe Light per Section 33−41−03.
C. Remove attaching hardware at rudder hinges.
D. Remove rudder by pulling it straight aft.
E. Install rudder in reverse sequence of removal.
Recheck attaching bolts for security and safety.
27-00-00
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