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|  MIL-T-18232B(AS)
3.2.2
EXTERNAL STORES. - Limitations imposed by carrying external
stores such as tanks, radar, etc. shall be specified for the
mission for which the stores are carried.
STRUCTURAL DESIGN CRITERIA
3.3
3.3.1
STRENGTH REQUIREMENTS. - The following applicable data shall
be tabulated in the detail specification for information.
The contractual obligation shall be as required in 3.3.2 of the detail specifica-
tion.
pounds
Basic flight design gross weight
pounds
Basic landing design gross weight
pounds
Basic catapulting design gross weight
Positive limit load factor at basic flight
design gross weight
Catapult load factor at basic catapulting
design gross weight
Captive flight
3.3.2
DETAIL STRENGTH REQUIREMENTS
3.3.2.1
STRENGTH REQUIREMENTS. - Strength and rigidity shall be pro-
vided for all captive flight, launching, free flight, recovery,
and handling loads. For all conditions the gross weight shall be that with
maximum load. At the design limit load, no elastic deformation which will
adversely affect operation is permitted. Failure shall not occur at the design
ultimate loads. Weight variations of government-furnished equipment and govern-
ment responsible changes shall not increase or decrease the design gross weights
specified by the original contract specification unless specifically stated other-
wise by a contract change. However, the contractor shall provide the required
strength at the gross weights specified by the original contract detail specifi-
cation increased by any contractor responsible overweight. In the event of over-
weight of government-furnished equipment, strength shall be provided for actual
weight of the government-furnished equipment and the useful load shall be adjusted
to maintain the specified overall design gross weights and design conditions.
Any weight empty increase incurred by providing strength for government-furnished
equipment overweight shall be considered as government responsibility and shall
be negotiated with NAVAIR.
3.3.2.2
FREE FLIGHT CONDITIONS. - For free flight conditions, the loads
shall be all those capable of being imposed by the control
system and by upsets experienced when encountering gusts. Gust velocities in level
and maneuvering flight shall be based on statistical analyses. The loads shall
include but not be limited to loads caused by maximum rate of control deflection;
transient overshoots in excess of trimmed, "steady state" bad factors; reverse of
controls at extreme attitudes; and inertia coupling loads. The limit speed shall
be the maximum attainable in dives. TO insure freedom from flutter, analyses and/
or experimental data shall show that an increase of 15 percent in equivalent air-
speeds from all points on the limit speed-altitude, design boundary, both at con-
stant Mach number and separately at constant altitude, will not result in flutter~
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