Eagle ICA-D212-725, Instructions Manual

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ICA-D212-725 (53)
Page 11 of 19
CHAPTER 53 – FUSELAGE (53-00-00)

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: 4
Date: 11.06.01
in area of splice.
53.5.2.5.3 Report any cracks to Product Support
Engineering.
53.5.2.5.4 Install plug button with sealant (C-
308).
53.5.2.6
Inspect tailboom bonded panels for
dents, scratches delaminations and corrosion.
53.5.2.7 Inspect diameter of tailboom-to-
fuselage attaching bolt holes in tailboom fittings for
elongation. The allowable limits are as follows:
LOCATION MINIMUM
DIAMETER
INCH
MAXIMUM
DIAMETER
INCH
Upper right 0.501 (12.72 mm) 0.516 (13.11 mm)
Upper left 0.563 (14.30 mm) 0.578 (14.68 mm)
Lower left 0.376 (9.55 mm) 0.391 (9.93 mm)
Lower right 0.376 (9.55 mm) 0.391 (9.93 mm)
53.5.2.8
Inspect corresponding four tailboom-
to-fuselage attaching bolt holes in fuselage fittings
for elongation. The allowable limits are as shown,
above.
53.5.2.9 Inspect tail rotor gearbox support
fitting in accordance with Figure 53-10.
53.5.3 Repair
MATERIALS REQUIRED
NUMBER NOMENCLATURE
C-222 Catalyzed Epoxy Primer
C-233 Polyurethane Enamel
C-309 Methyl-Ethyl-Ketone (MEK)
53.5.3.1
Replace damaged or unserviceable
doors, cover, and access panels.
53.5.3.2
Touch up paint on mating surfaces of
tail rotor driveshaft covers as follows:
53.5.3.2.1
Clean area with MEK (C-309).
Allow to air dry.
53.5.3.2.2 Apply one coat of catalyzed epoxy
primer (C-222). Allow to dry 1 hour. Apply one
coat of polyurethane enamel (C-233).
53.5.3.3 Perform
necessary structural repairs
in accordance with BHT-MED-SRM-1.
53.5.3.4
Replace damaged or unserviceable
fasteners and hinges on tail rotor driveshaft
covers.
53.5.3.5
Replace tailboom if attaching holes
in tailboom fittings exceed maximum allowable
diameter.
NOTE
If a new tailboom is installed, an alignment is
recommended (Chapter 65).
53.5.3.6 When replacing tailboom, remove
the following and install on replacement
tailboom:
- Tail rotor controls (Chapter 67)
- Electrical and avionics (Chapter 96 and 97)
- Synchronized elevator controls (Chapter 67)
- Synchronized elevator (Chapter 67)
- Tail rotor driveshaft, hangers and bearings
(Chapter 65)
- Intermediate gearbox (Chapter 65)
- Tail rotor gearbox (Chapter 65)
- Tail rotor driveshaft covers and vertical fin
cover
- Access doors and inspection panels
53.5.4 Installation
MATERIALS REQUIRED
NUMBER NOMENCLATURE
C-104 Corrosion Preventive
Compound
53.5.4.1 Position tailboom to forward
fuselage, line up bolt holes.
53.5.4.2. Apply a coating of corrosion
preventive compound (C-104) to all bolt shanks
prior to installation. Do not apply corrosion
preventive compound to threads of bolts.