623 

Federal Aviation Administration, DOT 

§ 29.865 

load for which authorization is re-
quested. It must be shown by analysis, 
test, or both that the rotorcraft exter-
nal load attaching means and cor-
responding personnel carrying device 
system for rotorcraft-load combina-
tions 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, ap-
proved under §§ 29.337 through 29.341, 
multiplied by the maximum external 
load for which authorization is re-
quested. The load for any rotorcraft- 
load combination class, for any exter-
nal cargo type, must be applied in the 
vertical direction. For jettisonable ex-
ternal loads of any applicable external 
cargo type, the load must also be ap-
plied in any direction making the max-
imum angle with the vertical that can 
be achieved in service but not less than 
30

°

. However, the 30

° 

angle may be re-

duced to a lesser angle if— 

(1) An operating limitation is estab-

lished limiting external load oper-
ations to such angles for which compli-
ance 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-re-
lease system to enable the pilot to re-
lease the external load quickly during 
flight. The quick-release system must 
consist of a primary quick release sub-
system and a backup quick release sub-
system that are isolated from one an-
other. 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 ei-
ther on one of the pilot’s primary con-
trols or in an equivalently accessible 
location and must be designed and lo-
cated so that it may be operated by ei-
ther the pilot or a crewmember with-
out hazardously limiting the ability to 
control the rotorcraft during an emer-
gency situation. 

(2) A control for the backup quick re-

lease subsystem, readily accessible to 
either the pilot or another crew-
member, 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 electro-

magnetic interference (EMI) from ex-
ternal and internal sources and against 
lightning to prevent inadvertent load 
release. 

(A) The minimum level of protection 

required for jettisonable rotorcraft- 
load 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 rotorcraft- 
load combinations used for human ex-
ternal 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 sub-
system, and 

(ii) Provides a separate dual actu-

ation device for the backup quick re-
lease subsystem; 

(2) Have a reliable, approved per-

sonnel 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 instruc-
tions and, for the personnel carrying 
device system, ingress and egress in-
structions; 

(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 applica-

tions requiring use of Category A 
rotorcraft, have one-engine-inoperative 
hover performance data and procedures 

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