MOONEY INTERNATIONAL CORPORATION
M20V SERVICE AND MAINTENANCE MANUAL
Date
MAR 2017
Rev Date
Page
5
57-00-00 - GENERAL
The M20V all metal wing is a one piece assembly at-
tached to the fuselage at structural hard points with
structural hardware. (See Section 53-40-01). The full
span, main spar assembly is connected to stub spar
and rear spar ass
embly by ribs, doublers and skins.
The main landing gear forward attach assembly is an
integral part of main spar and rear fitting is bolted to
wing stub spar assembly. The spar caps are 7075- T6
aluminum and the webs, ribs and doublers are
2024- T3, T4 or T42 aluminum. Repair of these compo-
nents is covered in Section 51-13-00.
The wing tips are fabricated from fiberglass and house
the navigation and strobe lights.
Fuel is contained in wet wing type fuel cells between
main spar and baffles forward of spar. The tanks are
sealed during manufacturing with current technology
sealant. (See Chapter 28 for fuel system details).
57-00-01 - WING REMOVAL AND INSTALLATION
The major subassemblies of wing may be removed in-
dividually, or wing may be removed as a unit. To remove
wing, a fuselage supporting cradle is needed.
1. Wing removal:
A. Remove wing- root fairings and bottom fuselage
access panels.
B. Drain all fuel from tanks (See Section 28-30-00).
C. Drain brake lines and reservoir (See Section
32-40-04). Disconnect hydraulic lines at wing main
spar.
D. Remove front and rear seats. Remove the two
inspection plates under rear seat area.
E. Jack aircraft per Section 7-10-00.
F. Dis connect or remove the following:
(a) Two landing gear assist springs.
(b) Aileron control tubes at inboard bellcranks.
(c) Trim control tube.
(d) Main gear retraction tubes.
(e) Rudder control tubes.
(f) Elevator control tube.
(g) Elevator and rudder push- pull tubes.
(h) Floorboards at rear attach points.
(i) Belly skin stringer splice angles.
(j) Airspeed indicator line, pitot lines and pitot
heater wires (if installed).
(k) Hardware shown in (Figure 57- 1).
-CAUTION-
Have suitable cradle ready to carry fuselage
before removing all mating hardware.
2. Wing installation: Installation of the wing assembly
is direct reversal of removal.
57-00-02 - STALL STRIP INSTALLATION
1. Adjust stall strips so that, during stall recovery, nor-
mal use of flight controls should prevent:
A. More than 15º roll.
B. More than 15º yaw.
C. More than 30º pitch below flight level.
2. Place stall strips on leading edge at stations shown
on (Figure 57- 2), attach securely with duct tape for test
flights. Adjust stall strips until aircraft flies to criteria in
paragraph 57-00-02, 1, A, B and C. Secure stall strip
per installation instructions in (Figure 57- 2).
57-10-00 - MAIN FRAME
The integral fuel cells (1,
Figure 57- 3) start at wing sta-
tion 24.5 and continue to rib, station 1 18.25 (LH/RH) on
wing. Sealer is applied to all joints on ribs, spar and
baffle plates. (See Section 28-11-00 for resealing pro-
cedures).
The wing is manufactured in three sections; center sec-
tion (2), left outboard section (3) and an opposite right
outboard section (not shown) (Figure 57- 3). These
three sections are then assembled into one full span
wing assembly as final two, LH/RH, skins are installed.
LH & RH spares configuration, wing tip assembly, are
available. Each includes completed section, from Wing
Station 103.50 and outboard. The assembly includes
stringers (4) required to complete splice to old center
section. A spar splice plate is required to reinforce spar
(5) at it’s attachment location. These components, with
instructions, are available through any Authorized
Mooney Service Center, visit www.mooney.com and
view the Support tab.
57-00-00
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