Eagle ICA-D212-725, Инструкция по эксплуатации

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ICA-D212-725 (53)
Page 10 of 19
CHAPTER 53 – FUSELAGE (53-00-00)
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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: 4
Date: 11.06.01
53.5 TAILBOOM
The tailboom (Figure 53-6) is of semi-monocoque
construction. External components consist of
formed aluminum alloy skins and driveshaft
covers, a fiberglass fairing, aluminum honeycomb
panels, and one aluminum alloy honeycomb
cover. Internal components of the boom and
synchronized elevator are of aluminum alloy. The
tailboom supports the tail rotor driveshafts,
gearboxes, and driveshaft hangers. The cargo
compartment is located in the forward end with the
door on the right side.
53.5.1 Removal
SPECIAL TOOLS REQUIRED
NUMBER NOMENCLATURE
T102012 Tailboom support
53.5.1.1
Remove left and right tail pipe lower
fairings.
53.5.1.2
Remove clamps from number two
driveshaft, remove driveshaft section (Chapter 63).
53.5.1.3
Open access door on right aft side of
forward fuselage. Disconnect electrical harnesses
and antenna cables.
53.5.1.4
Disconnect tail rotor and synchronized
elevator control tubes (Figure 53-7 and Chapter
63).
53.5.1.5
Remove plug buttons (Carr fasteners)
from four tailboom attaching points.
53.5.1.6
Place T102012 or equivalent tailboom
support under tailboom (Figure 53-8) and remove
bolts attaching tailboom to fuselage (Figure 53-9).
NOTE
If tailboom is to be hoisted, refer to Chapter 7.
53.5.1.7 Remove
tailboom.
53.5.2 Inspection
MATERIALS REQUIRED
NUMBER NOMENCLATURE
C-308 Sealant
C-309 Methyl-Ethyl-Ketone
(MEK)
53.5.2.1
Inspect doors, covers, and access
panels for misalignment, damage, and security
of mounting.
53.5.2.2 Inspect tailboom skin for dents,
corrosion, scratches, or other damage.
53.5.2.3
Inspect structure (longerons, spar
caps, bulkheads and ribs) for cracks, distortion,
corrosion, or loose rivets.
53.5.2.4
Inspect forward side of vertical fin
spar caps and web from upper tailboom skin to
approximately 4.0 inches (101.6 mm) below
upper tailboom skin as follows:
53.5.2.4.1 Remove aft tailboom flight control
inspection door (Chapter 52).
NOTE
If necessary, clean area to be inspected with
cloth dampened with MEK (C-309).
53.5.2.4.2 Face aft from inside of tailboom and
use bright light and small mirror to inspect areas
for cracks. Pay particular attention to areas
near rivet holes, especially cold worked holes
(ASB 212-90-63).
53.5.2.5
Inspect tailboom upper longerons as
follows:
53.5.2.5.1 Remove plug button at B.S. 99.00.
NOTE
Paint fissures are common in the splice area.
Cracks will be evident by black powder
emanating from cracked area, and corrosion will
leave evidence of white powder.
53.5.2.5.2 Using a borescope or suitable
means, inspect inside of longeron paying
particular attention to cracking and/or corrosion