375 

Federal Aviation Administration, DOT 

§ 125.507 

(b) [Reserved] 

[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] 

§ 125.503 [Reserved] 

§ 125.505 Repairs assessment for pres-

surized fuselages. 

(a) No person may operate an Airbus 

Model A300 (excluding the –600 series), 
British Aerospace Model BAC 1–11, Boe-
ing Model 707, 720, 727, 737 or 747, 
McDonnell Douglas Model DC–8, DC–9/ 
MD–80 or DC–10, Fokker Model F28, or 
Lockheed Model L–1011 beyond the ap-
plicable flight cycle implementation 
time specified below, or May 25, 2001, 
whichever occurs later, unless oper-
ations specifications have been issued 
to reference repair assessment guide-
lines applicable to the fuselage pres-
sure boundary (fuselage skin, door 
skin, and bulkhead webs), and those 
guidelines are incorporated in its 
maintenance program. The repair as-
sessment guidelines must be approved 
by the responsible Aircraft Certifi-
cation Service office for the type cer-
tificate for the affected airplane. 

(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