Eagle ICA-D212-725, Инструкция по эксплуатации

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ICA-D212-725 (67)
Page 37 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
Lift magnetic brake from helicopter.
67.3.5.1.4
If force gradient is to be replaced,
remove arm for use on replacement.
67.3.5.2 Installation
MATERIALS REQUIRED
NUMBER NOMENCLATURE
C-405 Lockwire
67.3.5.2.1
Install arm on magnetic brake as
follows:
67.3.5.2.1.1
Align arm on magnetic brake (20,
Figure 67-3) so L is next to mark on shaft (view
C). Tighten attaching bolt.
67.3.5.2.1.2
Align arm on magnetic brake (17)
so F is next to mark on shaft (view B). Tighten
attaching bolt.
67.3.5.2.1.3 Attach
magnetic brake to structure
by installing four bolts with washers and install
spring (35) if required. Attach electrical plug to
magnetic brake and secure with lockwire (C-405).
67.3.5.2.1.4 Attach
magnetic brake (17 and
20) to force gradient (18 and 21) by installing nut
and cotter pin.
67.3.5.2.1.5 Adjust
and connect force trim in
accordance with cyclic controls rigging procedure
(paragraph 67.1.6 or 67.1.7).
NOTE
Check clearance between force gradient and
structure at extreme positions of magnetic brake
arm. Re-index arm relative to shaft by one
serration, if required for clearance, then repeat,
paragraph 67.1.6, step 67.6.11 or paragraph
67.1.7, step 67.1.7.11.
67.3.5.2.1.6 Install
access panels on cabin
floor and lower fuselage skin.
67.3.6 Miscellaneous Control
Components
Cyclic control components include push-pull
tubes, bellcranks, jackshaft, mixing lever, and
supports.
NOTE
For maintenance practices on cyclic controls
dual control kit, refer to appropriate Service
Instruction.
67.3.6.1 Removal
NOTE
Parts of control system can be removed
separately as need occurs, or completely in any
practical sequence. Take precautions against
damage by accidental movement of linkage
while disconnected.
67.3.6.1.1
Remove access covers on cabin
floor, front of pylon island, and lower skin of
fuselage, as required.
67.3.6.1.2
Disconnect control tubes (22
and 24 Figure 67-3) from pilot cyclic stick (25).
67.3.6.1.3
To remove the bellcrank
assembly (23), proceed as follows:
67.3.6.1.3.1 Disconnect
the control tubes (22
and 27), force gradient (21) and transducer (36).
67.3.6.1.3.2
Remove the cotter pin (46), bolt
(43) washers (44) and nut (45) from bellcrank
assembly (23). Discard cotter pin.
67.3.6.1.3.3
Remove the bellcrank assembly
(23) for the support assembly (37).
67.3.6.1.4
To remove the support
assembly (37), remove the bolts (38), washers
(39) and nuts (40).
67.3.6.1.5
When removal of cyclic
jackshaft (26) is required, remove bolts and
tapered bushings to separate jackshaft tubes