Bell OH-58A - Damage Limits Forward Fuselage - Condition II

T M 55 -1 520-228 -BD
Table 4-5. Damage Limits Forward Fuse lage — Condition II (Cont)
DAMAGE LIMITS
LOCATION
CAP / FLANGE SKIN / WEB
COMPONENT /
MEMBER
FS WL BL
ELEMENT
CD’ CL’ N WL’ N
NOTES /
CAUTIONS
(D’=N x CL) (D’=N x WL)
Honeycomb
Panel
44.00-
57.10
21.00-
32.50
5.06R-
3.06L
Panel Edges
0.35 0.70 5
Instrument Panel
Shroud
21.25-
37.56
44.15-
51.95
5.02R-
3.02L
Brace
1.50 3.00 5
Front Seat
Support
57.11
21.00-
30.41
Honeycomb
Bulkhead 1.05 5
Does Not Include
Manufacturer’s
Holes
Pilot’s & Copilot’s
Seat
57.11-
74.54
30.41
19.45L-
22.15R
Honeycomb Panel
8.50
5
Center Bulkhead
Section 73.04
30.29-
54.89
Web
12.00 5
73.04
21.00-
30.29
10.64-
17.31L&R
Vertical Stiffeners
2.20 4.40
-
Pilot’s & Copilot’s
Seat 73.04 30.29
Aft Attachment Angle
0.70 1.40 5
Collective
Jackshaft 73.04
21.00-
30.29
Support Bracket
Channel
1.00 2.00 5
Pedestal
Structure
55.14-
73.04
20.00-
30.17
5.06R-
3.06L
Webs
1.10
5
55.14-
73.04
20.00-
30.17
5.06R-
3.06L
Caps/Stiffeners
0.85 1.70 5
Lower Shell 36.00-
73.00
20.00-
25.25
Honeycomb Panel
4.50
5
36.00-
73.00 20.00
Inserts for cyclic and
Pedal Controls
No Damage in One Set of Controls Within
3” Radius of Inserts
73.00 20.00
12.16 &
14.58
L&R
Forward Landing
Gear Attachments Two Diagonal Inserts May Be Damage
Center Post 73.00-
85.85
20.00-
72.00
3.00L-
3.00R
Caps
0.75 1.50
5
4-40
AIRFRAME