Eagle ICA-D212-725, Инструкция по эксплуатации

Страница: 511 / 729

ICA-D212-725 (67)
Page 36 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
67.3.4 Cyclic Control Force Gradient
The force gradient is a link equipped with an
internal spring and connects arm of magnetic
brake to a lever in fore-and-aft system and a
bellcrank in lateral system.
67.3.4.1 Removal
67.3.4.1.1
Remove access panels from cabin
floor and from lower fuselage skin as necessary.
67.3.4.1.2 Disconnect
link from bellcrank (23,
Figure 67-3) in lateral system by removing nut,
washers, and bolt.
67.3.4.1.3
Disconnect clevis from lever on
cyclic jackshaft (26) in fore-and-aft system by
removing bolt.
67.3.4.1.4
Remove spring (35) if installed.
Note rigging.
67.3.4.1.5
Remove nut to detach brake from
force gradient (18 or 21).
67.3.4.1.6
If force gradient is to be replaced,
remove link or clevis for use on replacement.
67.3.4.2 Installation
MATERIALS REQUIRED
NUMBER NOMENCLATURE
C-405 Lockwire
NOTE
All force gradients are similar in appearance
but each installation requires a different part
number because of different spring assembly.
67.3.4.2.1
Adjust spring preload on force
gradient as follows:
67.3.4.2.1.1
Remove cap (3, Figure 67-14).
67.3.4.2.1.2
Remove spring assembly (1) from
housing (2).
67.3.4.2.1.3
Adjust nuts (6) to hold 2.5 to 3.0
lbs. (11.1 to 13.3 N) force against spring (1) on
lateral force gradient. Tighten nuts together.
67.3.4.2.1.4
Adjust nuts (6) to hold 5.5 to 6.5
lbs. (24.5 to 29.0 N) force against spring
assembly (1) on fore-and-aft force gradient.
Tighten nuts together.
67.3.4.2.1.5
Insert spring assembly (1) into
housing (2) and install cap (3) and tighten until
all noticeable end play is eliminated. Secure with
lockwire (C-405) as shown to prevent turning in
either direction.
67.3.4.2.2
Install spring (35, Figure 67-3)
as required.
67.3.4.2.3
Adjust and connect force trim in
accordance with cyclic controls rigging
procedure (paragraph 67.1.6 or 67.1.7).
67.3.4.2.4
Install access panels on cabin
floor and lower fuselage skin.
67.3.5 Magnetic Brake
Two magnetic brakes are used with force
gradient assemblies for stick centering and force
trim in fore-and-aft and lateral cyclic control
linkage. The brake assemblies are identical to
each other except for position of arm on brake
and position of mounting on structure.
67.3.5.1 Removal
67.3.5.1.1
Remove access panels from
cabin floor and from lower fuselage skin as
necessary.
67.3.5.1.2
Disconnect force gradient from
arm of magnetic brake.
67.3.5.1.3
Disconnect electrical plug from
magnetic brake (17 or 20, Figure 67-3). Note
rigging of spring (35) in plate (34) if installed.
Remove spring (35) and four bolts with washers.