247 

Federal Aviation Administration, DOT 

§ 121.1107 

specified by the Administrator, to-
gether with records containing the fol-
lowing information: 

(1) Total years in service of the air-

plane; 

(2) Total time in service of the air-

frame; 

(3) Total flight cycles of the air-

frame; 

(4) Date of the last inspection and 

records review required by this section; 

(5) Current status of life-limited 

parts of the airframe; 

(6) Time since the last overhaul of all 

structural components required to be 
overhauled on a specific time basis; 

(7) Current inspection status of the 

airplane, including the time since the 
last inspection required by the inspec-
tion program under which the airplane 
is maintained; 

(8) Current status of applicable air-

worthiness directives, including the 
date and methods of compliance, and if 
the airworthiness directive involves re-
curring action, the time and date when 
the next action is required; 

(9) A list of major structural alter-

ations; and 

(10) A report of major structural re-

pairs and the current inspection status 
for those repairs. 

(e) 

Notification to Administrator. 

Each 

certificate holder must notify the Ad-
ministrator at least 60 days before the 
date on which the airplane and air-
plane records will be made available 
for the inspection and records review. 

[Doc. No. FAA–1999–5401, 67 FR 72761, Dec. 6, 
2002, as amended by Amdt. 121–284, 70 FR 
5532, Feb. 2, 2005; Amdt. 121–310, 70 FR 23936, 
May 6, 2005. Redesignated by Amdt. 121–336, 
72 FR 63412, Nov. 8, 2007] 

§ 121.1107

Repairs assessment for pres-

surized fuselages. 

(a) No certificate holder may operate 

an Airbus Model A300 (excluding the 
–600 series), British Aerospace Model 
BAC 1–11, Boeing 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 
airplane beyond the applicable flight 
cycle implementation time specified 
below, or May 25, 2001, whichever oc-
curs later, unless operations specifica-
tions have been issued to reference re-
pair assessment guidelines applicable 

to the fuselage pressure boundary (fu-
selage skin, door skin, and bulkhead 
webs), and those guidelines are incor-
porated in its maintenance program. 
The repair assessment guidelines must 
be approved by the responsible Aircraft 
Certification Service office for the type 
certificate 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 24125, Apr. 25, 2000; 65 
FR 50744, Aug. 21, 2000, as amended by Amdt. 
121–282, 66 FR 23130, May 7, 2001; ; Amdt. 121– 
305, 69 FR 45942, July 30, 2004. Redesignated 
and amended by Amdt. 121–336, 72 FR 63412, 
Nov. 8, 2007; Docket FAA–2018–0119, Amdt. 
121–380, 83 FR 9173, Mar. 5, 2018] 

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