771 

Federal Aviation Administration, DOT 

§ 29.865 

least 5 minutes under any foreseeable 
powerplant fire conditions. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 27–26, 55 FR 8005, Mar. 6, 
1990] 

§ 29.863

Flammable fluid fire protec-

tion. 

(a) In each area where flammable 

fluids or vapors might escape by leak-
age of a fluid system, there must be 
means to minimize the probability of 
ignition of the fluids and vapors, and 
the resultant hazards if ignition does 
occur. 

(b) Compliance with paragraph (a) of 

this section must be shown by analysis 
or tests, and the following factors must 
be considered: 

(1) Possible sources and paths of fluid 

leakage, and means of detecting leak-
age. 

(2) Flammability characteristics of 

fluids, including effects of any combus-
tible or absorbing materials. 

(3) Possible ignition sources, includ-

ing electrical faults, overheating of 
equipment, and malfunctioning of pro-
tective devices. 

(4) Means available for controlling or 

extinguishing a fire, such as stopping 
flow of fluids, shutting down equip-
ment, fireproof containment, or use of 
extinguishing agents. 

(5) Ability of rotorcraft components 

that are critical to safety of flight to 
withstand fire and heat. 

(c) If action by the flight crew is re-

quired to prevent or counteract a fluid 
fire (e.g. equipment shutdown or actu-
ation of a fire extinguisher), quick act-
ing means must be provided to alert 
the crew. 

(d) Each area where flammable fluids 

or vapors might escape by leakage of a 
fluid system must be identified and de-
fined. 

(Secs. 313(a), 601, 603, 604, Federal Aviation 
Act of 1958 (49 U.S.C. 1354(a), 1421, 1423, 1424), 
sec. 6(c), Dept. of Transportation Act (49 
U.S.C. 1655(c))) 

[Amdt. 29–17, 43 FR 50600, Oct. 30, 1978] 

E

XTERNAL

L

OADS

 

§ 29.865

External loads. 

(a) It must be shown by analysis, 

test, or both, that the rotorcraft exter-
nal load attaching means for rotor-

craft-load combinations to be used for 
nonhuman external cargo applications 
can withstand a limit static load equal 
to 2.5, or some lower load factor ap-
proved under §§ 29.337 through 29.341, 
multiplied by the maximum external 
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. 

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