Cessna 150J - Wing Struts; Fin; Horizontal Stabilizer

fittings. Be sure eccentric bushings are positioned
as marked.
b. Install bolts, spacers, and nuts to secure upper
and lower ends of wing strut to wing and fuselage fit-
tings.
c. Route flap and aileron cables, using guide wires.
(See note in paragraph 4-4. )
d. Connect:
1.
Electrical wires at wing root disconnects.
2. Fuel lines at wing root. (Refer to precau-
tions outlined in paragraph 12-3. )
3.
Pitot line (if left wing is being installed).
4. Wing leveler vacuum tube, if installed, at
wing root.
e. Rig aileron aystem. (Section 6. )
f. Rig flap system. (Section 7. )
g. Refuel wing tank and check for leaks. (Refer to
precautions outlined in paragraph 12-3. )
h. Check
operation of wing tip and landing and taxi
lights. (thru 1970 Models).
i. Check operation of fuel gage.
j. Install wing root fairings.
NOTE
Beginning with 1972 Models, a extruded fillet
sealant (576.1 Permagum: Presstite Engin-
eering Company) of equivalent is applied be-
tween cabin top skin and wing skin, also across
top of lower strut fitting at skin cutout. Gap
between windshield and wing leading edge is
sealed with (Polyken 230 or Polyken 231;
Kendall-Polyken Division, Tuck 92T, Techni-
cal Tape Corporation) or equivalent.
NOTE
Be sure to insert soundproofing panel in wing
gap, if such a panel was installed originally,
before replacing wing root fairings.
k. Install all wing inspection plates, interior panels
and upholstery.
4-7. ADJUSTMENT (CORRECTING "WING-HEAVY"
CONDITION.
(See figure 4-1.) If considerable con-
trol wheel pressure is required to keep the wings
level in normal flight, a wing-heavy condition exists.
a. Remove wing fairing strip on the wing-heavy
side of the airplane.
b. Loosen nut (10) and rotate bushings (8) simul-
taneously until the bushings are positioned with the
thick side of the eccentrics up. This will lower the
trailing edge of the wing, and decrease wing-heavi-
ness by increasing angle-of-incidence of the wing.
Be sure to rotate the eccentric bushings simul-
taneously. Rotating them separately will de-
stroy the alignment between the off-center bolt
holes in the bushings, thus exerting a shearing
force on the bolt, with possible damage to the
hole in the wing spar.
c. Tighten nut and reinstall fairing strip.
d. Test-fly the aircraft. If the wing-heavy condition
still exists, remove fairing strip on the "lighter"
wing, loosen nut and rotate bushings simultaneously
until the bushings are positioned with the thick side
of the eccentric down. This will raise the trailing
edge of the wing, thus increasing wing-heaviness to
balance heaviness in the opposite wing.
e. Tighten nut, install fairing strip, and repeat
test flight.
4-8. WING STRUTS. (See figure 4-2.)
4-9. DESCRIPTION. Each wing has a Single lift
strut which transmits a part of the wing load to the
lower portion of the fuselage. The strut consists of
a streamlined tube riveted to two end fittings for
attachment at the fuselage and wing.
4-10. REMOVAL AND INSTALLATION.
a. Remove screws from strut fairings and slide
fairings along strut.
b. Remove fuselage and wing inspection plates at
strut junction points.
c. Support wing securely, then remove nut and bolt
securing strut to fuselage.
d. Remove nut, bolt, and spacer used to attach
strut to wing, then remove strut from aircraft.
e. Reverse preceding steps to install strut.
4-11. REPAIR. Wing strut repair is limited to re-
placement of tie-downs and attaching parts. A badly
dented, cracked, or deformed wing strut should be
replaced.
4-12. FIN. (See figure 4-3.)
4-13. DESCRIPTION. The fin is primarily of metal
construction, conSisting of ribs and spars covered
with skin. Fin tips are of ABS or glass fiber con- I
struction. Hinge brackets at the fin rear spar attach
the rudder.
4-14. REMOVAL AND INSTALLATION. A fin may
be removed without first removing the rudder. How-
ever, for access and ease of handling, the rudder
may be removed by following procedures outlined in
Section 10.
a. Remove fairings on either side of fin.
b. Disconnect flashing beacon lead, tail navigation
light lead, antennas and antenna leads, and rudder
cables, if rudder has not been removed.
c. Remove bolts attaching rear fin brackets to
horizontal stabilizer.
d. Remove bolts attaching front fin brackets to
fuselage; remove fin.
e. Install fin by reversing preceding steps. Be
sure to check and reset rudder and elevator travel if
any stop bolts were removed or settings disturbed.
4-15. REPAIR. Fin repair should be accomplished
in accordance with applicable instructions outlined in
Section 18. .
4-16. HORIZONTAL STABILIZER. (See figure 4-4.)
4-17. DESCRIPTION. The horizontal stabilizer is
primarily of all-metal construction, conSisting of
ribs and spars covered with skin. Stabilizer tips
Change 2 4-3