Bell OH-58A - Page 75

Table 4-2. Dam
COMPONENT/
LOCATION
MEMBER
FS
WL
BL
Console,
1.00-
20.00-
5.06R-
Forward
32.75
44.50
3.06L
1.00-
20.00-
5.06R-
32.75
44.50
3.06L
32.75- 21.00-
5.06R-
55.10
32.50
3.06L
32.75-
23.39-
5.06R-
44.00
32.50
3.06L
32.75-
21.00-
5.06R-
44.00
23.39 3.06L
Honeycomb
44.00-
21.00-
5.06R-
Panel
57.10 32.50
3.06L
44.00- 21.00-
5.06R-
57.10
32.50
3.06L
Instrument
Panel
21.25-
44.15-
5.02R-
Shroud
37.57
51.95 3.02L
Front
Seat
21.00-
Support
57.11
30.41
Pilot's &
Copilot's
57.11-
19.45L-
Seat
74.54
30.41
22.15R
Center
Bulkhead
30.29-
Section
73.04
54.89
Center
Bulkhead
21.00-
10.65-
Section 73.04
30.29
17.31L&R
Pilot’s &
Copilot’s
73.04
30.29
Collective
21.00-
Jackshaft
73.04
30.29
Pedestal
55.14-
20.00-
5.06R-
Structure
73.04
30.17
3.06L
age Limits Forward Fuselage - Condition I
DAMAGE LIMITS
ELEMENT CAP/FLANGE
SKIN/WEB
CD ' CL' N
WL '
NOTES/CAUTIONS
Caps, Stiffeners,
(D’=NxCL) (D'=NxWL)
Doublers
1.05 2.10 10
N
Skins/Webs 2.5 5
Caps, Stiffeners,
Doublers
0.15 0.30 10
Skins/Webs
2.5 5
No Damage
Skin Allowed
Honeycomb Panel
7.50 5
Panel Edges 0.20 0.40 10
Brace 1.25 2.50 10
Honeycomb
No Damage
Bulkhead
Allowed
Honeycomb Panel 3.5 5
Web 10.0
5 Behind Pilots
Vertical
Sum of Damage
Stiffeners
2.0 4.0 - on All Elements
Aft Attachment
Angle No Damage Permitted
Support Bracket
Channel 0.70 1.50 10
Webs
0.75 5
TM 55-1520-228-BD
AIRFRAME
4-31