756
14 CFR Ch. I (1–1–24 Edition)
§ 91.611
manufactured before April 7, 2010, must
by April 7, 2012, have a cockpit voice
recorder that also—
(1) Meets the requirements of
§ 23.1457(d)(6) or § 25.1457(d)(6) of this
chapter, as applicable; and
(2) If transport category, meets the
requirements of § 25.1457(a)(3), (a)(4),
and (a)(5) of this chapter.
(i) All airplanes or rotorcraft re-
quired by this section to have a cockpit
voice recorder and flight data recorder,
that are manufactured on or after
April 7, 2010, must have a cockpit voice
recorder installed that also—
(1) Is installed in accordance with the
requirements of § 23.1457 (except for
paragraphs (a)(6) and (d)(5)); § 25.1457
(except for paragraphs (a)(6) and (d)(5));
§ 27.1457 (except for paragraphs (a)(6)
and (d)(5)); or § 29.1457 (except for para-
graphs (a)(6) and (d)(5)) of this chapter,
as applicable; and
(2) Retains at least the last 2 hours of
recorded information using a recorder
that meets the standards of TSO–C123a,
or later revision.
(3) For all airplanes or rotorcraft
manufactured on or after April 6, 2012,
also meets the requirements of
§ 23.1457(a)(6) and (d)(5); § 25.1457(a)(6)
and (d)(5); § 27.1457(a)(6) and (d)(5); or
§ 29.1457(a)(6) and (d)(5) of this chapter,
as applicable.
(j) All airplanes or rotorcraft re-
quired by this section to have a cockpit
voice recorder and a flight data re-
corder, that install datalink commu-
nication equipment on or after April 6,
2012, must record all datalink messages
as required by the certification rule ap-
plicable to the aircraft.
(k) An aircraft operated under this
part under deviation authority from
part 125 of this chapter must comply
with all of the applicable flight data
recorder requirements of part 125 appli-
cable to the aircraft, notwithstanding
such deviation authority.
[Doc. No. 18334, 54 FR 34318, Aug. 18, 1989, as
amended by Amdt. 91–226, 56 FR 51621, Oct.
11, 1991; Amdt. 91–228, 57 FR 19353, May 5,
1992; Amdt. 91–300, 73 FR 12564, Mar. 7, 2008;
Amdt. 91–304, 73 FR 73178, Dec. 2, 2008; Amdt.
91–300, 74 FR 32800, July 9, 2009; Amdt. 91–313,
75 FR 17045, Apr. 5, 2010; Docket No. FAA–
2022–1355, Amdt. No. 91–366, 87 FR 75846, Dec.
9, 2022]
§ 91.611
Authorization for ferry flight
with one engine inoperative.
(a)
General. The holder of an air car-
rier operating certificate or an oper-
ating certificate issued under part 125
may conduct a ferry flight of a four-en-
gine airplane or a turbine-engine-pow-
ered airplane equipped with three en-
gines, with one engine inoperative, to a
base for the purpose of repairing that
engine subject to the following:
(1) The airplane model has been test
flown and found satisfactory for safe
flight in accordance with paragraph (b)
or (c) of this section, as appropriate.
However, each operator who before No-
vember 19, 1966, has shown that a model
of airplane with an engine inoperative
is satisfactory for safe flight by a test
flight conducted in accordance with
performance data contained in the ap-
plicable Airplane Flight Manual under
paragraph (a)(2) of this section need
not repeat the test flight for that
model.
(2) The approved Airplane Flight
Manual contains the following per-
formance data and the flight is con-
ducted in accordance with that data:
(i) Maximum weight.
(ii) Center of gravity limits.
(iii) Configuration of the inoperative
propeller (if applicable).
(iv) Runway length for takeoff (in-
cluding temperature accountability).
(v) Altitude range.
(vi) Certificate limitations.
(vii) Ranges of operational limits.
(viii) Performance information.
(ix) Operating procedures.
(3) The operator has FAA approved
procedures for the safe operation of the
airplane, including specific require-
ments for—
(i) Limiting the operating weight on
any ferry flight to the minimum nec-
essary for the flight plus the necessary
reserve fuel load;
(ii) A limitation that takeoffs must
be made from dry runways unless,
based on a showing of actual operating
takeoff techniques on wet runways
with one engine inoperative, takeoffs
with full controllability from wet run-
ways have been approved for the spe-
cific model aircraft and included in the
Airplane Flight Manual:
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Federal Aviation Administration, DOT
§ 91.611
(iii) Operations from airports where
the runways may require a takeoff or
approach over populated areas; and
(iv) Inspection procedures for deter-
mining the operating condition of the
operative engines.
(4) No person may take off an air-
plane under this section if—
(i) The initial climb is over thickly
populated areas; or
(ii) Weather conditions at the takeoff
or destination airport are less than
those required for VFR flight.
(5) Persons other than required flight
crewmembers shall not be carried dur-
ing the flight.
(6) No person may use a flight crew-
member for flight under this section
unless that crewmember is thoroughly
familiar with the operating procedures
for one-engine inoperative ferry flight
contained in the certificate holder’s
manual and the limitations and per-
formance information in the Airplane
Flight Manual.
(b)
Flight tests: reciprocating-engine-
powered airplanes. The airplane per-
formance of a reciprocating-engine-
powered airplane with one engine inop-
erative must be determined by flight
test as follows:
(1) A speed not less than 1.3 V
S1
must
be chosen at which the airplane may be
controlled satisfactorily in a climb
with the critical engine inoperative
(with its propeller removed or in a con-
figuration desired by the operator and
with all other engines operating at the
maximum power determined in para-
graph (b)(3) of this section.
(2) The distance required to accel-
erate to the speed listed in paragraph
(b)(1) of this section and to climb to 50
feet must be determined with—
(i) The landing gear extended;
(ii) The critical engine inoperative
and its propeller removed or in a con-
figuration desired by the operator; and
(iii) The other engines operating at
not more than maximum power estab-
lished under paragraph (b)(3) of this
section.
(3) The takeoff, flight and landing
procedures, such as the approximate
trim settings, method of power applica-
tion, maximum power, and speed must
be established.
(4) The performance must be deter-
mined at a maximum weight not great-
er than the weight that allows a rate of
climb of at least 400 feet per minute in
the en route configuration set forth in
§ 25.67(d) of this chapter in effect on
January 31, 1977, at an altitude of 5,000
feet.
(5) The performance must be deter-
mined using temperature account-
ability for the takeoff field length,
computed in accordance with § 25.61 of
this chapter in effect on January 31,
1977.
(c)
Flight tests: Turbine-engine-powered
airplanes. The airplane performance of
a turbine-engine-powered airplane with
one engine inoperative must be deter-
mined by flight tests, including at
least three takeoff tests, in accordance
with the following:
(1) Takeoff speeds V
R
and V
2
, not less
than the corresponding speeds under
which the airplane was type certifi-
cated under § 25.107 of this chapter,
must be chosen at which the airplane
may be controlled satisfactorily with
the critical engine inoperative (with
its propeller removed or in a configura-
tion desired by the operator, if applica-
ble) and with all other engines oper-
ating at not more than the power se-
lected for type certification as set
forth in § 25.101 of this chapter.
(2) The minimum takeoff field length
must be the horizontal distance re-
quired to accelerate and climb to the
35-foot height at V
2
speed (including
any additional speed increment ob-
tained in the tests) multiplied by 115
percent and determined with—
(i) The landing gear extended;
(ii) The critical engine inoperative
and its propeller removed or in a con-
figuration desired by the operator (if
applicable); and
(iii) The other engine operating at
not more than the power selected for
type certification as set forth in § 25.101
of this chapter.
(3) The takeoff, flight, and landing
procedures such as the approximate
trim setting, method of power applica-
tion, maximum power, and speed must
be established. The airplane must be
satisfactorily controllable during the
entire takeoff run when operated ac-
cording to these procedures.
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14 CFR Ch. I (1–1–24 Edition)
§ 91.613
(4) The performance must be deter-
mined at a maximum weight not great-
er than the weight determined under
§ 25.121(c) of this chapter but with—
(i) The actual steady gradient of the
final takeoff climb requirement not
less than 1.2 percent at the end of the
takeoff path with two critical engines
inoperative; and
(ii) The climb speed not less than the
two-engine inoperative trim speed for
the actual steady gradient of the final
takeoff climb prescribed by paragraph
(c)(4)(i) of this section.
(5) The airplane must be satisfac-
torily controllable in a climb with two
critical engines inoperative. Climb per-
formance may be shown by calcula-
tions based on, and equal in accuracy
to, the results of testing.
(6) The performance must be deter-
mined using temperature account-
ability for takeoff distance and final
takeoff climb computed in accordance
with § 25.101 of this chapter.
For the purpose of paragraphs (c)(4)
and (5) of this section,
two critical en-
gines means two adjacent engines on
one side of an airplane with four en-
gines, and the center engine and one
outboard engine on an airplane with
three engines.
§ 91.613
Materials for compartment in-
teriors.
(a) No person may operate an air-
plane that conforms to an amended or
supplemental type certificate issued in
accordance with SFAR No. 41 for a
maximum certificated takeoff weight
in excess of 12,500 pounds unless within
1 year after issuance of the initial air-
worthiness certificate under that
SFAR the airplane meets the compart-
ment interior requirements set forth in
§ 25.853 (a), (b), (b–1), (b–2), and (b–3) of
this chapter in effect on September 26,
1978.
(b) Thermal/acoustic insulation ma-
terials. For transport category air-
planes type certificated after January
1, 1958:
(1) For airplanes manufactured before
September 2, 2005, when thermal/acous-
tic insulation is installed in the fuse-
lage as replacements after September
2, 2005, the insulation must meet the
flame propagation requirements of
§ 25.856 of this chapter, effective Sep-
tember 2, 2003, if it is:
(i) Of a blanket construction or
(ii) Installed around air ducting.
(2) For airplanes manufactured after
September 2, 2005, thermal/acoustic in-
sulation materials installed in the fu-
selage must meet the flame propaga-
tion requirements of § 25.856 of this
chapter, effective September 2, 2003.
[Doc. No. 18334, 54 FR 34318, Aug. 18, 1989, as
amended by Amdt. 91–279, 68 FR 45083, July
31, 2003; Amdt. 91–290, 70 FR 77752, Dec. 30,
2005]
§§ 91.615–91.699
[Reserved]
Subpart H—Foreign Aircraft Oper-
ations and Operations of U.S.-
Registered Civil Aircraft Out-
side of the United States; and
Rules Governing Persons on
Board Such Aircraft
S
OURCE
: Docket No. 18334, 54 FR 34320, Aug.
18, 1989, unless otherwise noted.
§ 91.701
Applicability.
(a) This subpart applies to the oper-
ations of civil aircraft of U.S. registry
outside of the United States and the
operations of foreign civil aircraft
within the United States.
(b) Section 91.702 of this subpart also
applies to each person on board an air-
craft operated as follows:
(1) A U.S. registered civil aircraft op-
erated outside the United States;
(2) Any aircraft operated outside the
United States—
(i) That has its next scheduled des-
tination or last place of departure in
the United States if the aircraft next
lands in the United States; or
(ii) If the aircraft lands in the United
States with the individual still on the
aircraft regardless of whether it was a
scheduled or otherwise planned landing
site.
[Doc. No. FAA–1998–4954, 64 FR 1079, Jan. 7,
1999]
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