376
14 CFR Ch. I (1–1–24 Edition)
§ 125.509
have been developed in accordance
with the applicable provisions of SFAR
88 of this chapter or § 25.1529 and part
25, Appendix H, of this chapter, in ef-
fect on June 6, 2001 (including those de-
veloped for auxiliary fuel tanks, if any,
installed under supplemental type cer-
tificates or other design approval) and
that have been approved by the respon-
sible Aircraft Certification Service of-
fice.
(e) After December 16, 2008, before re-
turning an aircraft to service after any
alteration for which fuel tank ICA are
developed under SFAR 88, or under
§ 25.1529 in effect on June 6, 2001, the
certificate holder must include in the
inspection program for the airplane in-
spections and procedures for the fuel
tank system based on those ICA.
(f) The fuel tank system inspection
program changes identified in para-
graphs (d) and (e) of this section and
any later fuel tank system revisions
must be submitted to the Principal In-
spector for review and approval.
(g) This section does not apply to the
following airplane models:
(1) Bombardier CL–44
(2) Concorde
(3) deHavilland D.H. 106 Comet 4C
(4) VFW–Vereinigte Flugtechnische
Werk VFW–614
(5) Illyushin Aviation IL 96T
(6) Bristol Aircraft Britannia 305
(7) Handley Page Herald Type 300
(8) Avions Marcel Dassault—Breguet
Aviation Mercure 100C
(9) Airbus Caravelle
(10) Lockheed L–300
[Amdt. 125–53, 72 FR 63412, Nov. 8, 2007, as
amended by Docket FAA–2018–0119, Amdt.
125–68, 83 FR 9174, Mar. 5, 2018]
§ 125.509 Flammability reduction
means.
(a)
Applicability.
Except as provided
in paragraph (m) of this section, this
section applies to transport category,
turbine-powered airplanes with a type
certificate issued after January 1, 1958,
that, as a result of original type cer-
tification or later increase in capacity
have:
(1) A maximum type-certificated pas-
senger capacity of 30 or more, or
(2) A maximum payload capacity of
7,500 pounds or more.
(b)
New Production Airplanes.
Except
in accordance with § 125.201, no person
may operate an airplane identified in
Table 1 of this section (including all-
cargo airplanes) for which the State of
Manufacture issued the original certifi-
cate of airworthiness or export air-
worthiness approval after December 27,
2010 unless an Ignition Mitigation
Means (IMM) or Flammability Reduc-
tion Means (FRM) meeting the require-
ments of § 26.33 of this chapter is oper-
ational.
T
ABLE
1
Model—Boeing
Model—Airbus
747 Series
A318, A319, A320, A321 Series
737 Series
A330, A340 Series
777 Series
767 Series
(c)
Auxiliary Fuel Tanks.
After the ap-
plicable date stated in paragraph (e) of
this section, no person may operate
any airplane subject to § 26.33 of this
chapter that has an Auxiliary Fuel
Tank installed pursuant to a field ap-
proval, unless the following require-
ments are met:
(1) The person complies with 14 CFR
26.35 by the applicable date stated in
that section.
(2) The person installs Flammability
Impact Mitigation Means (FIMM), if
applicable, that is approved by the re-
sponsible Aircraft Certification Service
office.
(3) Except in accordance with
§ 125.201, the FIMM, if applicable, are
operational.
(d)
Retrofit.
Except as provided in
paragraph (j) of this section, after the
dates specified in paragraph (e) of this
section, no person may operate an air-
plane to which this section applies un-
less the requirements of paragraphs
(d)(1) and (d)(2) of this section are met.
(1) Ignition Mitigation Means (IMM),
Flammability Reduction Means (FRM),
or FIMM, if required by §§ 26.33, 26.35, or
26.37 of this chapter, that are approved
by the responsible Aircraft Certifi-
cation Service office, are installed
within the compliance times specified
in paragraph (e) of this section.
(2) Except in accordance with § 125.201
of this part, the IMM, FRM or FIMM,
as applicable, are operational.
