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MIL-A-8629

1953 Edition, August 28, 1953

Complete Document

AIRPLANE STRENGTH AND RIGIDITY



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Superseded By: MIL-A-8860

Additional Comments:
CNCL PER DODISS 82 S/S BY MIL-A-8860 & MIL-A-8870
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Description / Abstract:

General- This specification contains the requirements of the Bureau of Aeronautics Relative to piloted airplanes for:

a. The strength and rigidity of the structure of the airplane which includes surfaces and their supports provided for reacting aerodynamic forces and structures provided for supporting fixed-equipment and useful-load items.

b. The strength of fittings attached to the airplane for the purpose of transmitting forces to the airplane structure.

c. The strength of control systems and their supporting structures that are provided for operating longitudinal, lateral, and directional control surfaces; dive or speed brakes; high-lift devices; tabs; stabilizers; spoilers; landing gears; brakes; and wing-and tail-folding mechanisms.

d. The strength and shock-absorption characteristics of landing-gear and beaching gear units with the exception of wheels, tires, tubes, and brakes.

e. The strength of arresting hooks.

f. The strength of structures integral with the airplane provided for transmitting catapulting forces to the airplane.

g. The strength of structures provided for engaging barrier actuators and barrier cables and barricades.

h. The strength of hoisting slings.

i. The strength of anchor-line clamps.

j Flutter prevention and vibration characteristics.

k. Structural design and test data.

l. Laboratory tests conducted to obtain information regarding strength and rigidity.

Modifications and amplifications. - This specification will be modified and amplified by Bureau of Aeronautics contracts for piloted airplanes and/or by outline and detail specifications and addenda to Bureau of Aeronautics specification SR-6 referred to in such contracts. In general, modifications and amplifications of the design requirements of section 3 of this specification will be contained in outline and detail specifications, and modifications and amplifications data and test requirements of sections 3 and 4 will be contained in addenda to Bureau of Aeronautics specification 3R-6.