639 

Federal Aviation Administration, DOT 

§ 29.1001 

(c) Each flexible connection in fuel 

lines that may be under pressure or 
subjected to axial loading must use 
flexible hose assemblies. 

(d) Flexible hose must be approved. 
(e) No flexible hose that might be ad-

versely affected by high temperatures 
may be used where excessive tempera-
tures will exist during operation or 
after engine shutdown. 

§ 29.995

Fuel valves. 

In addition to meeting the require-

ments of § 29.1189, each fuel valve 
must— 

(a) [Reserved] 
(b) Be supported so that no loads re-

sulting from their operation or from 
accelerated flight conditions are trans-
mitted to the lines attached to the 
valve. 

(Secs. 313(a), 601, and 603, 72 Stat. 759, 775, 49 
U.S.C. 1354(a), 1421, and 1423; sec. 6(c), 49 
U.S.C. 1655 (c)) 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–13, 42 FR 15046, Mar. 17, 
1977] 

§ 29.997

Fuel strainer or filter. 

There must be a fuel strainer or filter 

between the fuel tank outlet and the 
inlet of the first fuel system compo-
nent which is susceptible to fuel con-
tamination, including but not limited 
to the fuel metering device or an en-
gine positive displacement pump, 
whichever is nearer the fuel tank out-
let. This fuel strainer or filter must— 

(a) Be accessible for draining and 

cleaning and must incorporate a screen 
or element which is easily removable; 

(b) Have a sediment trap and drain, 

except that it need not have a drain if 
the strainer or filter is easily remov-
able for drain purposes; 

(c) Be mounted so that its weight is 

not supported by the connecting lines 
or by the inlet or outlet connections of 
the strainer or filter inself, unless ade-
quate strengh margins under all load-
ing conditions are provided in the lines 
and connections; and 

(d) Provide a means to remove from 

the fuel any contaminant which would 
jeopardize the flow of fuel through 
rotorcraft or engine fuel system com-

ponents required for proper rotorcraft 
or engine fuel system operation. 

[Amdt. 29–10, 39 FR 35462, Oct. 1, 1974, as 
amended by Amdt. 29–22, 49 FR 6850, Feb. 23, 
1984; Amdt. 29–26, 53 FR 34217, Sept. 2, 1988] 

§ 29.999

Fuel system drains. 

(a) There must be at least one acces-

sible drain at the lowest point in each 
fuel system to completely drain the 
system with the rotorcraft in any 
ground attitude to be expected in serv-
ice. 

(b) Each drain required by paragraph 

(a) of this section including the drains 
prescribed in § 29.971 must— 

(1) Discharge clear of all parts of the 

rotorcraft; 

(2) Have manual or automatic means 

to ensure positive closure in the off po-
sition; and 

(3) Have a drain valve— 
(i) That is readily accessible and 

which can be easily opened and closed; 
and 

(ii) That is either located or pro-

tected to prevent fuel spillage in the 
event of a landing with landing gear re-
tracted. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–12, 41 FR 55473, Dec. 20, 
1976; Amdt. 29–26, 53 FR 34218, Sept. 2, 1988] 

§ 29.1001

Fuel jettisoning. 

If a fuel jettisoning system is in-

stalled, the following apply: 

(a) Fuel jettisoning must be safe dur-

ing all flight regimes for which jetti-
soning is to be authorized. 

(b) In showing compliance with para-

graph (a) of this section, it must be 
shown that— 

(1) The fuel jettisoning system and 

its operation are free from fire hazard; 

(2) No hazard results from fuel or fuel 

vapors which impinge on any part of 
the rotorcraft during fuel jettisoning; 
and 

(3) Controllability of the rotorcraft 

remains satisfactory throughout the 
fuel jettisoning operation. 

(c) Means must be provided to auto-

matically prevent jettisoning fuel 
below the level required for an all-en-
gine climb at maximum continuous 
power from sea level to 5,000 feet alti-
tude and cruise thereafter for 30 min-
utes at maximum range engine power. 

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