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- 6 nuts Z00.N5401458159 (12)
- 8 rivets Z00.N5528371382 (8)
- 18 rivets Z00.N5529308001 (19) and (21)
- 1 rivet Z00.N5529308004 (5)
B. Procedure (Figure 801)
1) Remove the wings - refer to 57-00-00.
2) Inspect the fitting of front attachment (7) on the fuselage, make sure that there are no screw head marks in the bent sections.
3) Remove wing upper surface stiffener (20) forward of footstep area.
4) Flatten the wrinkled area of the skin.
5) Install intermediate stiffener (2) with blind rivets (21).
NOTE : Stiffener (2) is to be cut from a rib P / N TB10 11016100 or fabricated from a sheet -see Figure 802 for fabrication details.
6) Drill a hole with a drill No. 22 (dia. 4 mm) to install rivet (5) attaching the wing root half-ribs.
7) Using a drill No. 22 (dia. 4 mm) , drive out rivet (6) and flat round head rivets (18) and (9).
8) Counterdrill both holes (a) with a drill No. 9 (dia. 5 mm).
9) Install R.H. shim (3) and L.H. shim (4) on wing root rib (1). Replace flat round head rivets dia. 0.157 in (4 mm) with screws (10), (13), (14) and (15), washers (11) and (16), nuts (12) and (17).
ABAA
Validity : S / N 1 - 9999 57-00-00PageJUN 801
(cA) 01
10) Replace the 8 rivets dia. 0.126 in (3.2 mm) (8) securing, on the upper surface, the skin to the front small spar with flat round head rivets (AU4G) dia. 0.157 in (4 mm) P / N Z00.N5528371382.
NOTE : Some aircraft are already factory-fitted with rivets dia. 0.157 in (4 mm) on wing lower surface.
11) Plug skin holes (b) with blind rivets (21).
12) Vacuum-clean any chips from the leading edge box.
13) Make sure all the tools and materials are removed and the work area is clean and free from debris.
14) Perform paint touch-ups - refer to 20-00-03.
15) Install the wings - refer to 57-00-00.
1 - Wing root rib
2 - Stiffener
3 - R.H. shim
4 - L.H. shim
5 - Rivet
6 - Rivet
7 - Front attachment
8 - Rivet
9 - Flat round head rivet
10 - Screw
11 - Washer
12 - Nut
13 - Screw
14 - Screw
15 - Screw
16 - Washer
17 - Nut
18 - Flat round head rivet
19 - Rivet
20 - Stiffener
21 - Blind rivet
Installation details
Key to Figure 801
ABAA
Validity : S / N 1 - 9999 57 00-00Page 802
(CA) JUN 01
Installation details
Figure 801
ABAA
Validity : S / N 1 - 9999 57-00 00Page 803
(CA) JUN 01
2. PRINCIPLE OF BLANKING OFF A CORE SAMPLE (Table 801 and Figure 806)
NOTE : If the repair area is located between N1 and N2 ribs, install an additional door on the wing
lower surface, between N1 and N2 ribs, forward of the spar. Order Kit OPT10 918800. CAUTION : DEPENDING ON THE LOCATION OF THE CORE SAMPLE, THE SKIN THICKNESSES
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