Eagle ICA-D212-725, Instructions Manual

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ICA-D212-725 (67)
Page 47 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
67.4.7 Magnetic Brake
67.4.7.1 Removal
67.4.7.1.1
Remove pilot seat.
67.4.7.1.2
Remove access panels from cabin
floor, as necessary.
67.4.7.1.3
Remove aft end of force gradient
from arm of magnetic brake.
67.4.7.1.4
Disconnect electrical plug from
magnetic brake.
67.4.7.1.5
Remove four bolts with washers
and lift assembly from helicopter.
67.4.7.1.6
Remove arm from magnetic
brake.
67.4.7.2 Installation
MATERIALS REQUIRED
NUMBER NOMENCLATURE
C-405 Lockwire
67.4.7.2.1
Align arm on magnetic brake shaft
so that the D is next to mark on shaft. Tighten arm
attaching bolt.
67.4.7.2.2
Position magnetic brake in
helicopter and secure magnetic brake to bulkhead
with four bolts and washers.
67.4.7.2.3
Connect electrical plug to
magnetic brake. Secure connector with lockwire
(C-405)
67.4.7.2.4 Check
rigging of magnetic brake
and force gradient in accordance with paragraph
67.1.6 or 67.1.7 and connect force gradient to
magnetic brake. Install cotter pin.
67.4.7.2.5
Install cabin floor access panel.
67.4.7.2.6
Install pilot seat.
67.4.8 Miscellaneous Control
Components
Control components between tail rotor control
pedals and pitch change mechanism mounted
on tail rotor gearbox includes control tubes,
bellcranks, levers, a walking beam, a force
gradient with magnetic brake and a hydraulic
power cylinder.
67.4.8.1 Removal
NOTE
Parts of control system can be removed
separately as need arises, or completely in any
practical sequence. Take precaution against
damage by accidental movement of linkage
while disconnected.
67.4.8.1.1
Remove access covers on cabin
floor and lower skin of fuselage and tailboom as
necessary.
NOTE
Remove tail rotor gearbox prior to removing
control tube (8, Figure 67-5) .
67.4.8.1.2 Remove control tubes,
bellcranks, levers and walking beam by
removing attaching hardware.
67.4.8.2 Inspection and repair
67.4.8.2.1
Inspect linkage parts for wear,
elongated bolt holes, cracks, nicks, and
damage. Inspect bearings for wear and
roughness.
NOTE
Maximum allowable elongation to a
bushing or clevis hole in the control system
is 0.003 in. (0.076 mm).
67.4.8.2.2 Inspect control tubes for wear
and damage (BHT-212-CR&O).