206 

14 CFR Ch. I (1–1–19 Edition) 

§ 25.5 

(i) K25.1.4(a), fuel system pressure 

and flow requirements; 

(ii) K25.1.4(a)(3), low fuel alerting; 

and 

(iii) K25.1.4(c), engine oil tank design. 
(2) For ETOPS type design approval 

of an airplane beyond 180 minutes an 
applicant must comply with § 25.1535. 

(c) 

Airplanes with more than two en-

gines. 

An applicant for ETOPS type de-

sign approval must comply with 
§ 25.1535 for an airplane manufactured 
on or after February 17, 2015, except 
that, for an airplane configured for a 
three person flight crew, the applicant 
need not comply with Appendix K, 
K25.1.4(a)(3), of this part, low fuel alert-
ing. 

[Doc. No. FAA–2002–6717, 72 FR 1873, Jan. 16, 
2007] 

§ 25.5

Incorporations by reference. 

(a) The materials listed in this sec-

tion are incorporated by reference in 
the corresponding sections noted. 
These incorporations by reference were 
approved by the Director of the Federal 
Register in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. These mate-
rials are incorporated as they exist on 
the date of the approval, and notice of 
any change in these materials will be 
published in the F

EDERAL

R

EGISTER

. 

The materials are available for pur-
chase at the corresponding addresses 
noted below, and all are available for 
inspection at the National Archives 
and Records Administration (NARA). 
For information on the availability of 
this material at NARA, call 202–741– 
6030, or go to: 

http://www.archives.gov/ 

federal-register/cfr/ibr-locations.html. 

(b) The following materials are avail-

able for purchase from the following 
address: The National Technical Infor-
mation Services (NTIS), Springfield, 
Virginia 22166. 

(1) Fuel Tank Flammability Assess-

ment Method User’s Manual, dated 
May 2008, document number DOT/FAA/ 
AR–05/8, IBR approved for § 25.981 and 
Appendix N. It can also be obtained at 
the following Web site: 

http:// 

www.fire.tc.faa.gov/systems/fueltank/ 
FTFAM.stm. 

(2) [Reserved] 

[73 FR 42494, July 21, 2008, as amended by 
Doc. No. FAA–2018–0119, Amdt. 21–101, 83 FR 
9169, Mar. 5, 2018] 

Subpart B—Flight 

G

ENERAL

 

§ 25.21

Proof of compliance. 

(a) Each requirement of this subpart 

must be met at each appropriate com-
bination of weight and center of grav-
ity within the range of loading condi-
tions for which certification is re-
quested. This must be shown— 

(1) By tests upon an airplane of the 

type for which certification is re-
quested, or by calculations based on, 
and equal in accuracy to, the results of 
testing; and 

(2) By systematic investigation of 

each probable combination of weight 
and center of gravity, if compliance 
cannot be reasonably inferred from 
combinations investigated. 

(b) [Reserved] 
(c) The controllability, stability, 

trim, and stalling characteristics of 
the airplane must be shown for each al-
titude up to the maximum expected in 
operation. 

(d) Parameters critical for the test 

being conducted, such as weight, load-
ing (center of gravity and inertia), air-
speed, power, and wind, must be main-
tained within acceptable tolerances of 
the critical values during flight test-
ing. 

(e) If compliance with the flight 

characteristics requirements is depend-
ent upon a stability augmentation sys-
tem or upon any other automatic or 
power-operated system, compliance 
must be shown with §§ 25.671 and 25.672. 

(f) In meeting the requirements of 

§§ 25.105(d), 25.125, 25.233, and 25.237, the 
wind velocity must be measured at a 
height of 10 meters above the surface, 
or corrected for the difference between 
the height at which the wind velocity 
is measured and the 10-meter height. 

(g) The requirements of this subpart 

associated with icing conditions apply 
only if the applicant is seeking certifi-
cation for flight in icing conditions. 

(1) Paragraphs (g)(3) and (4) of this 

section apply only to airplanes with 
one or both of the following attributes: 

(i) Maximum takeoff gross weight is 

less than 60,000 lbs; or 

(ii) The airplane is equipped with re-

versible flight controls. 

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