MIL-A-8860G(AS)
20 May 1987
SUPERSEDING
MIL-A-8860(ASG)
18 May 1960
MILITARY SPECIFICATION
AIRPLANE STRENGTH AND RIGIDITY
GENERAL SPECIFICATION FOR
Thts specification ts approved for use within the Naval
Air Systems Command, Department of the Navy, and is
available for use by all Departments and Agencies of the
Department of Defense.
1.
SCOPE
1.1 Scope.
This specification contains general requirements, which, in
combination with other applicable specifications, define the structural
design, analysls, test, and data requirements for fixed wing piloted
airplanes.
These requirements include, but are not IIm!ted to, the following:
a.
The strength and rlgldlty of the structure of the airplane
Including supporting and carry-through structures for fixed
equipment and useful load Items.
b. The strength and rigidityof control systems for operation of
lateral, longitudinal, and directional control surfaces; dive or
speed brakes;
htgh lift devices; tabs; stabilizers; spoilers;
certain other mechanisms; and their respective carry-through
structures.
c.
The shock-absorption characteristics and strength of landing-gear
units and the strength and rigidity of their control systems and of
their carry-through structures. Requirements for wheels, tires, and
brakes are also included.
d.
The strength of structures Integral with the airplane provided for
transmitting catapulting forces to the airplanes, and for engaging
shipboard and shorebase arresting gear, and barricades.
Beneficial comments (recommendations, additions, deletions) and any pertinent
data which may be of use in improving this document should be addressed to:
Naval Air Engineering Center,
Systems Engineering and Standardization
Department (Code 93), Lakehurst, NJ 08733-5100, by using the self-addressed
Standardization Document Improvement Proposal (EIDForm 1426) appearing at the
I
end of this document, or by letter.
DISTRIWTION STATEMENT A.
Approved for publ!c release; distribution Is unlimitei.
Downloaded from http://www.everyspec.com
