Federal Aviation Administration, DOT

Section 91.701

(4) The performance must be determined at a maximum weight not greater than the weight determined under
Section 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 satisfactorily controllable in a climb with two
critical engines inoperative. Climb performance may be shown by calculations based on, and equal in accuracy
to, the results of testing.
(6) The performance must be determined using temperature accountability for takeoff distance and final
takeoff climb computed in accordance
with Section 25.101 of this chapter.
For the purpose of paragraphs (c)(4)
and (5) of this section, two critical engines means two adjacent engines on
one side of an airplane with four engines, and the center engine and one
outboard engine on an airplane with
three engines.

kpayne on VMOFRWIN702 with $$_JOB

Section 91.613 Materials for compartment interiors.
(a) No person may operate an airplane 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 airworthiness certificate under that
SFAR the airplane meets the compartment interior requirements set forth in
Section 25.853 (a), (b), (b-1), (b-2), and (b-3) of
this chapter in effect on September 26,
1978.
(b) Thermal/acoustic insulation materials. For transport category airplanes type certificated after January
1, 1958:
(1) For airplanes manufactured before
September 2, 2005, when thermal/acoustic insulation is installed in the fuselage as replacements after September
2, 2005, the insulation must meet the

flame propagation requirements of
Section 25.856 of this chapter, effective September 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 insulation materials installed in the fuselage must meet the flame propagation requirements of Section 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]

SectionSection 91.615-91.699

[Reserved]

Subpart H - Foreign Aircraft Operations and Operations of U.S.Registered Civil Aircraft Outside of the United States; and
Rules Governing Persons on
Board Such Aircraft
SOURCE: Docket No. 18334, 54 FR 34320, Aug.
18, 1989, unless otherwise noted.

Section 91.701

Applicability.

(a) This subpart applies to the operations 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 aircraft operated as follows:
(1) A U.S. registered civil aircraft operated outside the United States;
(2) Any aircraft operated outside the
United States - 
(i) That has its next scheduled destination 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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