Eagle ICA-D212-725, Инструкция по эксплуатации

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ICA-D212-725 (67)
Page 17 of 55
CHAPTER 67 – FLIGHT CONTROLS (67-00-00)

COPYRIGHT

2007 BY DART AEROSPACE LTD.

THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED OR COMMUNICATED TO
ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTD.
Revision:
6
Date: 13.08.26
Figure 67-5. Anti-Torque Controls (Sheet 2 of 2)
67.1.9
Anti-Torque Controls (212-011-701
Hub and Blade) (Helicopter s/n 31175 and Sub.)
MATERIALS REQUIRED
NUMBER NOMENCLATURE
C-405 Lockwire
NOTE
Refer to paragraph 67.1.4 prior to beginning
rigging.
67.1.9.1
Check linkage is complete, except
for the following adjustable links and control tubes
disconnected:
67.1.9.1.1
Pitch change links (3, Figure 67-5)
from tail rotor blades.
67.1.9.1.2
Link (6) from lever on left side of
tail rotor gearbox.
67.1.9.1.3
Control tube (12) from bellcrank
(13) above hydraulic cylinder.
67.1.9.1.4
Force gradient (31) from pedal
adjuster (28).
NOTE
Refer to appropriate Service Instruction for
rigging copilot pedals if dual controls are
installed.
67.1.9.2
Retract all adjustable stop bolts
(Detail E) as far as possible.
NOTE
Adjustment of pitch change link length not
required for fixed length pitch change links (Post
TB 212-01-185)
67.1.9.3
Adjust both pitch change links
(3) to initial length of 6.180 ±0.010 in. (156.972
±0.254 mm) between centers of rod end
bearings. Connect each link to blade pitch horn
with bolt and floating bushing. Torque bolt to 135
in.lbs. (15.26 Nm). Secure with Iockwire (C-405).
67.1.9.4.
Position tail rotor blades to