783 

Federal Aviation Administration, DOT 

§ 91.701 

(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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