Maintenance and Inspection Procedures Manual
Type:
CT
Series:
CTLS
LSA
Page: 4-74
AF 04800001
Revision No. 3
Date: 14 Sep 2008
5. Install the stabilator KA3010200 (Fig. 1) into the bracket
КА
3010120 by matching holes (pos.3) in
the bracket with holes in the top and bottom skins of the stabilator.
6. Set the bolts C9996259N (Bolt DIN 931 M6x110-8.8) throw the matched holes in the bracket
КА
3010120 and stabilator skins, put washers C9996504 Washer DIN 125 A2B-6.4 mm, and
tighten them by the nuts C9996334 (Self-locking nut DIN 985-M6, regular) using two 8x10
wrenches to torque 80 lb-in / 9 N*m. Make sure that the heads of the bolts are on the top of the
stabilator.
7. Check balancing of the stabilator, i.e. after some rotation around the axle KA3010001 the
stabilator KA3010200 returns to horizontal position. If the top skin does not stabilize at horizontal
position, remove the bracket and correct the balancer (refer to 4.2.1.8).
8. Inspect stabilator “cross incidence” with respect to the fuselage roof (set the level across the
fuselage first on the stabilator skin behind the bracket, then on the roof nearby the spars. The
difference should not be more then 0.5
°
. Otherwise do the following.
•
Remove the stabilator from the bracket.
•
Using a hex-nut wrench 3 and 8x10 wrench loosen the body KA3010011 Bearing body, by
taking the bolts C9996207 Bolt DIN 7991 M5x16-8.8 out either from one side of the fuselage,
or from both, depending on stabilator angle of “cross incidence”.
•
Correct stabilator “cross incidence” using eccentricity of the KA3010011 Bearing bodies.
•
Attach the bearing body KA3010011 (Bearing body) by bolts C9996207 Bolt DIN 7991
M5x16-8 nuts (during adjustment it is allowable to use non- self-locking nuts, which have to
be replace for final installation).
•
Install the stabilator into the bracket and check angle of “cross incidence” with respect to the
fuselage roof.
•
Repeat described above operations, if necessary, to get the roof and stabilator parallel (The
difference should not be more then 0.5
0
)
•
Secure KA3010011 Bearing bodies by tightening new nuts C9996333 (Self-locking nut DIN
985-M5) to torque 94 lb-in / 5,5 N*m on bolts C9996207 (Bolt DIN 7991 M5x16-8.8).
9. Following Fig. 3 stretch the safety Bowden cables (pos. 1) and press them out by shrinking hose,
art. 3172G, in the places of connection with Stabilizer bracket (pos. 2).
10. Find the middle of the trim tab cable (d=1,5 mm, l=8,0 m). Put ends of the cable on the sheaves
(pos. 4) and turn each end around its slot (pos. 5) of the sheave 1,5 times in the opposite
directions; then insert them into the safety Bowden cables.
11. Insert the safety Bowden cables with trim tab cables into the holes of the frame 3.
12. Mount the stabilizer bracket (pos. 3) on the fuselage.
13. Stretch the trim tab rods in the tale part of the fuselage through one of the miniblocks (pos. 6).
14. Set the thimble (2 mm) on the trim tab rods, connect the free part of the rods with main part by
flat clip DUPLEX, 1.4401 for 3 mm cable.
15. With the help of turnbuckles (pos. 7) connect the trim tab rods with the trim tab rods stretching
from the throttle box (pos. 8).
16. Tighten the cables by turnbuckles.
17. Attach two trim tab control rods to two brackets on the rear wall of the fuselage.
18. Connect trim tab control rods KA6060010 (Rod) with an 8x10 wrench and 4 hex-nut wrench.
Tighten the nuts C9996333 (Self-locking nut DIN 985-M5) to torque 49 lb-in / 5.5 N*m. Make sure
that rod tips C9997006C (Rods end bearings, ext. thread GA5) are secured by C9996333 (Self-
locking nut DIN 985-M5) to torque 49 lb-in / 5.5 N*m).
19. Using a bolt C9996060 Bolt DIN 912 M6x35-8.8 connect to rod tip C9997004 (Rod end bearing,
int. thread SI6E) to the stabilator bracket B3010120. Tighten the nut C9996334 (Self-locking nut
DIN 985-M6, regular) using two 10x13 wrenches to torque 80 lb-in / 9 N*m) (Fig. 2).
