spaschal on DSK3GDR082PROD with CFR

Federal Aviation Administration, DOT

Section 29.865

load for which authorization is requested. It must be shown by analysis,
test, or both that the rotorcraft external load attaching means and corresponding personnel carrying device
system for rotorcraft-load combinations to be used for human external
cargo applications can withstand a
limit static load equal to 3.5 or some
lower load factor, not less than 2.5, approved under SectionSection 29.337 through 29.341,
multiplied by the maximum external
load for which authorization is requested. The load for any rotorcraftload combination class, for any external cargo type, must be applied in the
vertical direction. For jettisonable external loads of any applicable external
cargo type, the load must also be applied in any direction making the maximum angle with the vertical that can
be achieved in service but not less than
30Section. However, the 30Section angle may be reduced to a lesser angle if - 
(1) An operating limitation is established limiting external load operations to such angles for which compliance with this paragraph has been
shown; or
(2) It is shown that the lesser angle
can not be exceeded in service.
(b) The external load attaching
means, for jettisonable rotorcraft-load
combinations, must include a quick-release system to enable the pilot to release the external load quickly during
flight. The quick-release system must
consist of a primary quick release subsystem and a backup quick release subsystem that are isolated from one another. The quick release system, and
the means by which it is controlled,
must comply with the following:
(1) A control for the primary quick
release subsystem must be installed either on one of the pilot-s primary controls or in an equivalently accessible
location and must be designed and located so that it may be operated by either the pilot or a crewmember without hazardously limiting the ability to
control the rotorcraft during an emergency situation.
(2) A control for the backup quick release subsystem, readily accessible to
either the pilot or another crewmember, must be provided.
(3) Both the primary and backup
quick release subsystems must - 

(i) Be reliable, durable, and function
properly with all external loads up to
and including the maximum external
limit load for which authorization is
requested.
(ii) Be protected against electromagnetic interference (EMI) from external and internal sources and against
lightning to prevent inadvertent load
release.
(A) The minimum level of protection
required for jettisonable rotorcraftload combinations used for nonhuman
external cargo is a radio frequency
field strength of 20 volts per meter.
(B) The minimum level of protection
required for jettisonable rotorcraftload combinations used for human external cargo is a radio frequency field
strength of 200 volts per meter.
(iii) Be protected against any failure
that could be induced by a failure mode
of any other electrical or mechanical
rotorcraft system.
(c) For rotorcraft-load combinations
to be used for human external cargo
applications, the rotorcraft must - 
(1) For jettisonable external loads,
have a quick-release system that meets
the requirements of paragraph (b) of
this section and that - 
(i) Provides a dual actuation device
for the primary quick release subsystem, and
(ii) Provides a separate dual actuation device for the backup quick release subsystem;
(2) Have a reliable, approved personnel carrying device system that has
the structural capability and personnel
safety features essential for external
occupant safety;
(3) Have placards and markings at all
appropriate locations that clearly state
the essential system operating instructions and, for the personnel carrying
device system, ingress and egress instructions;
(4) Have equipment to allow direct
intercommunication among required
crewmembers and external occupants;
(5) Have the appropriate limitations
and procedures incorporated in the
flight manual for conducting human
external cargo operations; and
(6) For human external cargo applications requiring use of Category A
rotorcraft, have one-engine-inoperative
hover performance data and procedures

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