Eagle ICA-D212-725, Instructions Manual

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ICA-D212-725 (67)
Page 15 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
67.1.8.12
If clearance is less than 0.010 in.
(0.254 mm), verify rigging procedures have been
performed correctly.
NOTE
Maximum exposed thread length on fixed control
rod clevis is 1.00 in. (25.4 mm).
67.1.8.13
Rig and connect force trim as
follows:
67.1.8.13.1
Hold pedals in neutral position.
67.1.8.13.2
Position arm of magnetic brake
(32, Figure 67-5) at center of travel (detail B).
67.1.8.13.3
Adjust tube of force gradient (31)
and connect to bellcrank of pedal adjuster (28).
67.1.8.13.4
Check for clearance of force
gradient and structure at extreme positions of
brake arm. If required to obtain clearance, arm can
be re-indexed on brake shaft by one serration.
67.1.8.14 Operate
system through full travel
to check for any binding or interference.
NOTE
Adjustment of pitch change link length not required
for fixed length pitch change links (Post TB 212-
01-185)
67.1.8.15
Check track of tail rotor in
operation (Chapter 62). If required for track, adjust
pitch change links by half-turn increments,
alternately, in opposite directions.
67.1.8.16
Check complete system for
security and safetying of parts. Check control
system for clearance and freedom of operation.