Code of Federal Regulations - Title 14

786

14 CFR Ch. I (1–1–14 Edition)

§ 29.991

from the maximum pressure, including
surge, that is likely to occur during
fueling. The maximum surge pressure
must be established with any combina-
tion of tank valves being either inten-
tionally or inadvertently closed.

(d) The rotorcraft defueling system

(not including fuel tanks and fuel tank
vents) must withstand an ultimate
load that is 2.0 times the load arising
from the maximum permissible
defueling pressure (positive or nega-
tive) at the rotorcraft fueling connec-
tion.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–12, 41 FR 55473, Dec. 20,
1976]

UEL

YSTEM

OMPONENTS

§ 29.991

Fuel pumps.

(a) Compliance with § 29.955 must not

be jeopardized by failure of—

(1) Any one pump except pumps that

are approved and installed as parts of a
type certificated engine; or

(2) Any component required for pump

operation except the engine served by
that pump.

(b) The following fuel pump installa-

tion requirements apply:

(1) When necessary to maintain the

proper fuel pressure—

(i) A connection must be provided to

transmit the carburetor air intake
static pressure to the proper fuel pump
relief valve connection; and

(ii) The gauge balance lines must be

independently connected to the carbu-
retor inlet pressure to avoid incorrect
fuel pressure readings.

(2) The installation of fuel pumps

having seals or diaphragms that may
leak must have means for draining
leaking fuel.

(3) Each drain line must discharge

where it will not create a fire hazard.

[Amdt. 29–26, 53 FR 34217, Sept. 2, 1988]

§ 29.993

Fuel system lines and fittings.

(a) Each fuel line must be installed

and supported to prevent excessive vi-
bration and to withstand loads due to
fuel pressure, valve actuation, and ac-
celerated flight conditions.

(b) Each fuel line connected to com-

ponents of the rotorcraft between
which relative motion could exist must
have provisions for flexibility.

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;

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

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