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LOCATION
COMPONENT /
MEMBER
FS
Honeycomb
44.00-
Panel
57.10
Instrument Panel
21.25-
44.15-
Shroud
37.56
51.95
Front Seat
21.00-
Support
30.41
57.11
Pilot's & Copilot's
57.11-
Seat
74.54
30.41
Center Bulkhead
30.29-
Section
73.04
54.89
21.00-
73.04
30.29
Pilot's & Copilot's
Seat
73.04
30.29
Collective
21.00-
Jackshaft
73.04
30.29
Pedestal
55.14-
20.00-
Structure
73.04
30.17
55.14-
20.00-
73.04
30.17
Lower Shell
36.00-
20.00-
73.00
25.25
36.00-
73.00
20.00
73.00
20.00
Center Post
73.00-
20.00-
85.85
72.00
Table 4-5.
Damage Limits Forward Fuse lage — Condition II (Cont)
ELEMENT
WL
BL
21.00-
5.06R-
Panel Edges
32.50
3.06L
5.02R-
Brace
3.02L
Honeycomb
Bulkhead
19.45L-
Honeycomb Panel
22.15R
Web
10.64-
Vertical Stiffeners
17.31L&R
Aft Attachment Angle
Support Bracket
Channel
5.06R-
Webs
3.06L
5.06R-
Caps/Stiffeners
3.06L
Honeycomb Panel
Inserts for cyclic and
Pedal Controls
12.16 &
Forward Landing
14.58
Gear Attachments
L&R
3.00L-
Caps
3.00R
DAMAGE LIMITS
CAP / FLANGE
SKIN / WEB
CD'
CL'
N
WL'
(D'=N x CL)
(D'=N x WL)
0.35
0.70
5
1.50
3.00
5
1.05
8.50
12.00
2.20
4.40
-
0.70
1.40
5
1.00
2.00
5
1.10
0.85
1.70
5
4.50
No Damage in One Set of Controls Within
3" Radius of Inserts
Two Diagonal Inserts May Be Damage
0.75
1.50
5
NOTES /
CAUTIONS
N
Does Not Include
5
Manufacturer's
Holes
5
5
5
5
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