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Fairings / 220 / 53-20-04
Skins / 220 / 53-20-03
Fittings 2 220 222 53-20-05
3. DESCRIPTION 1 A. Frames
The rear fuselage structure is limited by frames C7 and C9.
The vertical stabilizer front attachment is secured to frame C7.
The vertical stabilizer rear attachment is secured to frame C8.
The elevator hinge fittings are secured to frame C9.
I B. Skins
The skins are made of formed and riveted light alloys.
I C. Fairings
The tail cone ensures the aerodynamic continuity of the fuselage.
The tail cone is screwed to frame C9 of the rear fuselage.
I D. Fittings
The elevator fittings are secured to frame C9.
AAAA
Validity : S / N 1 - 9999 53 20-00Page 1
(BA) SEP 04
A - Frames
B - Cross beams and stringers C - Fairings
D - Skins
E - Fittings
Rear fuselage - Identification and location of components
Figure 1
WA
Validity : S / N 1 - 9999 53-20-00Page 2
(BA) SEP 04
FRAMES
REPAIR
1. REPLACEMENT OF THE FLIGHT CONTROL REAR SUPPORT ON FRAME C9 (Figures 801 and 802) A. Tools and consumable materials
1 padded support for frame C8
- Grease (TB 04-004A)
- Alodine (TB 13-002)
- Primer (TB 16-901)
- Drill dia. 1/8" (3.2 mm)
- Drill No. 20 (dia. 4.1 mm)
- Drill No. 7 (dia. 5.1 mm)
- Kit OPT10 908600, composed of
? 1 L.H. doubler TB10 21013103 (27)
? 1 R.H. doubler TB10 21013104 (32)
1 L.H. support TB10 27088004 (18)
1 R.H. support TB10 27088005 (35)
1 L.H. unfolding wedge TB10 27088118 (16)
1 R.H. unfolding wedge TB10 2008811 7 (15)
1 pin TB10 27000131 (23)
1 spacer dia. 0.47 in (12 mm),
L 5.52 in (140.3 mm) TB10 27000158 (21)
1 spacer dia. 0.63 in (16 mm), L 0.59 in (15 mm) TB10 27000159 (34)
1 spacer dia. 0.63 in (16 mm), L 0.39 in (10 mm) TB10 27000160 (19)
6 bolts Z00.N5101229079 (29)
6 bolts ZOO. N5101229175 (25)
2 bolts Z00.N5101229174 (17)
2 bolts Z00.N5101229179 (12)
6 washers ZOO. N5701039160 (30)
10 washers Z00.N5701039240 (13)
? 2 cotter pins ZOO.N5783009087 (22)
? 6 nuts Z00.N5401458159 (31)
? 10 nuts Z00.N5401458239 (14)
AAAA
Validity : S / N 1 - 450 53-20-01 Page 801
(BA) SEP 04
B. Procedure
CAUTION : THE SUPPORT MUST FIT TO FUSELAGE PROFILE PERFECTLY AND BEARING
FACES MUST BE PADDED TO AVOID DAMAGING THE STRUCTURE.
1) Install a padded support under the rear fuselage, at frame C8.
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本文链接地址：TB20 MAINTENANCE MANUAL 53 机身 TB20飞机维护手册(11)
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