title-14-part-27-sec27-1461

559

Federal Aviation Administration, DOT

§ 27.1461

flight data recorders under this part
are met.

[Amdt. 27–22, 53 FR 26144, July 11, 1988, as
amended by Amdt. 27–43, 73 FR 12563, Mar. 7,
2008; 74 FR 32800, July 9, 2009; Amdt. 27–45, 75
FR 17045, Apr. 5, 2010]

§ 27.1459

Flight data recorders.

(a) Each flight recorder required by

the operating rules of Subchapter G of
this chapter must be installed so that:

(1) It is supplied with airspeed, alti-

tude, and directional data obtained
from sources that meet the accuracy
requirements of §§ 27.1323, 27.1325, and
27.1327 of this part, as applicable;

(2) The vertical acceleration sensor is

rigidly attached, and located longitu-
dinally within the approved center of
gravity limits of the rotorcraft;

(3)(i) It receives its electrical power

from the bus that provides the max-
imum reliability for operation of the
flight data recorder without jeopard-
izing service to essential or emergency
loads.

(ii) It remains powered for as long as

possible without jeopardizing emer-
gency operation of the rotorcraft.

(4) There is an aural or visual means

for preflight checking of the recorder
for proper recording of data in the stor-
age medium;

(5) Except for recorders powered sole-

ly by the engine-driven electrical gen-
erator system, there is an automatic
means to simultaneously stop a re-
corder that has a data erasure feature
and prevent each erasure feature from
functioning, within 10 minutes after
any crash impact; and

(6) Whether the cockpit voice re-

corder and digital flight data recorder
are installed in separate boxes or in a
combination unit, no single electrical
failure external to the recorder may
disable both the cockpit voice recorder
and the digital flight data recorder.

(b) Each nonejectable recorder con-

tainer must be located and mounted so
as to minimize the probability of con-
tainer rupture resulting from crash im-
pact and subsequent damage to the
record from fire.

between the flight recorder readings of
airspeed, altitude, and heading and the
corresponding readings (taking into ac-
count correction factors) of the first pi-

lot’s instruments. This correlation
must cover the airspeed range over
which the aircraft is to be operated,
the range of altitude to which the air-
craft is limited, and 360 degrees of
heading. Correlation may be estab-
lished on the ground as appropriate.

(d) Each recorder container must:
(1) Be either bright orange or bright

yellow;

(2) Have a reflective tape affixed to

its external surface to facilitate its lo-
cation under water; and

(3) Have an underwater locating de-

vice, when required by the operating
rules of this chapter, on or adjacent to
the container which is secured in such
a manner that they are not likely to be
separated during crash impact.

(e) When both a cockpit voice re-

corder and a flight data recorder are
required by the operating rules, one
combination unit may be installed,
provided that all other requirements of
this section and the requirements for
cockpit voice recorders under this part
are met.

[Amdt. 27–22, 53 FR 26144, July 11, 1988, as
amended by Amdt. 27–43, 73 FR 12564, Mar. 7,
2008; 74 FR 32800, July 9, 2009; Amdt. 27–45, 75
FR 17045, Apr. 5, 2010]

§ 27.1461

Equipment containing high

energy rotors.

(a) Equipment containing high en-

ergy rotors must meet paragraph (b),
(c), or (d) of this section.

(b) High energy rotors contained in

equipment must be able to withstand
damage caused by malfunctions, vibra-
tion, abnormal speeds, and abnormal
temperatures. In addition—

(1) Auxiliary rotor cases must be able

to contain damage caused by the fail-
ure of high energy rotor blades; and

(2) Equipment control devices, sys-

tems, and instrumentation must rea-
sonably ensure that no operating limi-
tations affecting the integrity of high
energy rotors will be exceeded in serv-
ice.

equipment containing high energy ro-
tors can contain any failure of a high
energy rotor that occurs at the highest
speed obtainable with the normal speed
control devices inoperative.

(d) Equipment containing high en-

ergy rotors must be located where

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560

14 CFR Ch. I (1–1–24 Edition)

§ 27.1501

rotor failure will neither endanger the
occupants nor adversely affect contin-
ued safe flight.

[Amdt. 27–2, 33 FR 964, Jan. 26, 1968]

Subpart G—Operating Limitations

and Information

§ 27.1501

General.

(a) Each operating limitation speci-

fied in §§ 27.1503 through 27.1525 and
other limitations and information nec-
essary for safe operation must be es-
tablished.

(b) The operating limitations and

other information necessary for safe
operation must be made available to
the crewmembers as prescribed in
§§ 27.1541 through 27.1589.

(Secs. 313(a), 601, 603, 604, and 605 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354(a),
1421, 1423, 1424, and 1425); and sec. 6(c) of the
Dept. of Transportation Act (49 U.S.C.
1655(c)))

[Amdt. 27–14, 43 FR 2325, Jan. 16, 1978]

PERATING

IMITATIONS

§ 27.1503

Airspeed limitations: general.

(a) An operating speed range must be

established.

(b) When airspeed limitations are a

function of weight, weight distribution,
altitude, rotor speed, power, or other
factors, airspeed limitations cor-
responding with the critical combina-
tions of these factors must be estab-
lished.

§ 27.1505

Never-exceed speed.

(a) The never-exceed speed, V

NE,

must

be established so that it is—

(1) Not less than 40 knots (CAS); and
(2) Not more than the lesser of—
(i) 0.9 times the maximum forward

speeds established under § 27.309;

(ii) 0.9 times the maximum speed

shown under §§ 27.251 and 27.629; or

(iii) 0.9 times the maximum speed

substantiated for advancing blade tip
mach number effects.

(b) V

may vary with altitude,

r.p.m., temperature, and weight, if—

(1) No more than two of these vari-

ables (or no more than two instru-
ments integrating more than one of
these variables) are used at one time;
and

(2) The ranges of these variables (or

of the indications on instruments inte-
grating more than one of these vari-
ables) are large enough to allow an
operationally practical and safe vari-
ation of V

power-off V

denoted as V

(power-

off) may be established at a speed less
than V

established pursuant to para-

graph (a) of this section, if the fol-
lowing conditions are met:

(1) V

(power-off) is not less than a

speed midway between the power-on
V

and the speed used in meeting the

requirements of—

(i) § 27.65(b) for single engine heli-

copters; and

(ii) § 27.67 for multiengine heli-

copters.

(2) V

(power-off) is—

(i) A constant airspeed;
(ii) A constant amount less than

power-on V

; or

(iii) A constant airspeed for a portion

of the altitude range for which certifi-
cation is requested, and a constant
amount less than power-on V

for the

remainder of the altitude range.

(Secs. 313(a), 601, 603, 604, and 605 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354(a),
1421, 1423, 1424, and 1425); and sec. 6(c) of the
Dept. of Transportation Act (49 U.S.C.
1655(c)))

[Amdt. 27–2, 33 FR 964, Jan. 26, 1968, and
Amdt. 27–14, 43 FR 2325, Jan. 16, 1978; Amdt.
27–21, 49 FR 44435, Nov. 6, 1984]

§ 27.1509

Rotor speed.

(a)

Maximum power-off (autorotation).

The maximum power-off rotor speed
must be established so that it does not
exceed 95 percent of the lesser of—

(1) The maximum design r.p.m. deter-

mined under § 27.309(b); and

(2) The maximum r.p.m. shown dur-

ing the type tests.

(b)

Minimum power off. The minimum

power-off rotor speed must be estab-
lished so that it is not less than 105
percent of the greater of—

(1) The minimum shown during the

type tests; and

(2) The minimum determined by de-

sign substantiation.

(c)

Minimum power on. The minimum

power-on rotor speed must be estab-
lished so that it is—

(1) Not less than the greater of—