363 

Federal Aviation Administration, DOT 

§ 125.507 

(1) For the Airbus Model A300 (ex-

cluding the –600 series), the flight cycle 
implementation time is: 

(i) Model B2: 36,000 flights. 
(ii) Model B4–100 (including Model 

B4–2C): 30,000 flights above the window 
line, and 36,000 flights below the win-
dow line. 

(iii) Model B4–200: 25,500 flights above 

the window line, and 34,000 flights 
below the window line. 

(2) For all models of the British Aero-

space BAC 1–11, the flight cycle imple-
mentation time is 60,000 flights. 

(3) For all models of the Boeing 707, 

the flight cycle implementation time is 
15,000 flights. 

(4) For all models of the Boeing 720, 

the flight cycle implementation time is 
23,000 flights. 

(5) For all models of the Boeing 727, 

the flight cycle implementation time is 
45,000 flights. 

(6) For all models of the Boeing 737, 

the flight cycle implementation time is 
60,000 flights. 

(7) For all models of the Boeing 747, 

the flight cycle implementation time is 
15,000 flights. 

(8) For all models of the McDonnell 

Douglas DC–8, the flight cycle imple-
mentation time is 30,000 flights. 

(9) For all models of the McDonnell 

Douglas DC–9/MD–80, the flight cycle 
implementation time is 60,000 flights. 

(10) For all models of the McDonnell 

Douglas DC–10, the flight cycle imple-
mentation time is 30,000 flights. 

(11) For all models of the Lockheed 

L–1011, the flight cycle implementation 
time is 27,000 flights. 

(12) For the Fokker F–28 Mark, 1000, 

2000, 3000, and 4000, the flight cycle im-
plementation time is 60,000 flights. 

(b) [Reserved] 

[Doc. No. 29104, 65 FR 24126, Apr. 25, 2000; 65 
FR 50744, Aug. 21, 2000, as amended by Amdt. 
125–36, 66 FR 23131, May 7, 2001; Amdt. 125–40, 
67 FR 72834, Dec. 9, 2002; Amdt. 125–46, 69 FR 
45942, July 30, 2004. Redesignated by Amdt. 
125–53, 72 FR 63412, Nov. 8, 2007; Docket FAA– 
2018–0119, Amdt. 125–68, 83 FR 9174, Mar. 5, 
2018] 

§ 125.507

Fuel tank system inspection 

program. 

(a) Except as provided in paragraph 

(g) 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 certification 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 

7500 pounds or more. 

(b) For each airplane on which an 

auxiliary fuel tank is installed under a 
field approval, before June 16, 2008, the 
certificate holder must submit to the 
responsible Aircraft Certification Serv-
ice office proposed maintenance in-
structions for the tank that meet the 
requirements of Special Federal Avia-
tion Regulation No. 88 (SFAR 88) of 
this chapter. 

(c) After December 16, 2008, no certifi-

cate holder may operate an airplane 
identified in paragraph (a) of this sec-
tion unless the inspection program for 
that airplane has been revised to in-
clude applicable inspections, proce-
dures, and limitations for fuel tank 
systems. 

(d) The proposed fuel tank system in-

spection program revisions must be 
based on fuel tank system Instructions 
for Continued Airworthiness (ICA) that 
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 

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