MIL-DTL-81014B
3.9 Detailed requirements.
3.9.1 General. The hook shall be of the open-throat type. The load sling adapter ring or
other pickup device may be introduced into the load bearing portion of the hook automatically or
in any event it shall not require personal contact with the hook. There shall be no protuberances
or other obstacles to prevent or hinder engagement with the load sling adapter ring or other
pickup device. The open-throat shall face forward when installed on an aircraft.
3.9.1.1 Throat. The throat (see 6.3.5) configuration shall facilitate engagement with the load
sling adapter or other pickup device. The throat shall accept any of the following sling adapter
rings or pickup devices or their equivalents:
a. Nylon strap ring 2.75-inch wide and 0.875-inch thick.
b. A steel ring made of 1.5-inch diameter stock.
c. Two 1.5-inch diameter ropes.
3.9.1.2 Housing. The hook housing shall be constructed to support and enclose the
components and to protect them from environmental conditions. Components subject to water
damage shall be enclosed within a completely waterproof housing or other protective device.
3.9.1.3 Load beam. The load beam shall support all loads under all operational conditions.
The load beam shall be mounted in the hook housing by a pivot near its aft end such that upon
release the front end will swing downward and aft. The configuration of the load beam shall assist
the load sling adapter ring to position itself in the hook while presenting minimum resistance to
disengagement on release.
3.9.1.4 Keeper. A keeper shall be used in the hook throat to positively retain the load sling
adapter ring in the desired position in the hook under all operational flight conditions until release.
The keeper shall permit engagement of pickup devices consisting of more than one part or ring,
each engaged separately without personal contact with any part of the hook.
3.9.1.5 Attachment. The hook shall have two attachment holes on its upper portion; one
near the forward end and one near the aft end as shown on figure 1, such that the point at which
the cargo load is applied is midway between them. The suspension holes shall attach to a
semi-rigid mounting structure (see 6.3.4) beneath the aircraft and shall permit removal of the hook
when desired.
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