MIl-STD-209K APPENDIX D
APPENDIX D
TRANSPORT BY NAVY/MARINE CORPSAIRCRAFT
D.1 Scope.
This appendix provides the restraint requirements for transport in subject helicop- ter, tilt-rotor, and fixed wing aircraft.
D.2 Applicable Documents.
(a) A1-V22AB-CLG-OOO - Cargo Loading Manual, MV-22B
(b) A1-H53BE-CLG-OOO - Cargo Loading Manual, Navy Models CH-53A, CH-
53D, RH-53D, CH-53E, and MH-53E Helicopters
(c) A1-H46AE-CLG-OOO - Cargo Loading Manual, Navy Models HH-46D/UH-
46D/CH-46E Helicopters
(d) NAVAIR O1-75GAA-9 - Cargo Loading Manual, Navy Models C-13O Series
(e) A1-H6OSA-CLG-OOO - Cargo Loading Manual, Navy Model MH-6OS (f) Appropriate NATOPS Manuals for Specific T/M/S aircraft.
D.3 Requirements. D.3.1 Application.
Cargo equipment to be transported internally by helicopter, tilt-rotor aircraft, or the
USMC C-13O aircraft must be designed for restraint to the values in the following table: Cargo equipment must be properly restrained and have the structural integrity to
Aircraft Type |
Static limit load Restraint Criteria |
|||
Forward G's |
Aft G's |
Lateral G's |
Up G's |
|
USMC C-13O |
3 |
2 |
1.5 |
2 |
Helicopter/ Tilt-rotor |
4 |
3 |
3 |
3 |
Fixed-wing |
3 |
2 |
2 |
2 |
Carrier On- board Delivery (COD) transport |
2O 1 |
7 |
7 |
4 |
1. COD forward G is defined as an ultimate load factor. |
maintain the noted G loads, defined as limit load factors, for the required aircraft. Item weight for calculating restraint requirements for the subject aircraft will be the items transportable weight and its weight distribution. The ultimate load factors are found by multiplying a factor of 1.5 to the limit load cases in paragraph D.3.1.
Source: https://assist.dla.mil -- DDow-n1loaded: 2014-09-28T23:10Z Check the source to verify that this is the current version before use.
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