title-14-part-125-sec125-501

374

14 CFR Ch. I (1–1–24 Edition)

§ 125.407

(1) Identify in its operations manual

the person having custody of the copies
of documents retained in accordance
with paragraph (d) of this section; and

(2) Retain at its principal operations

base either the original or a copy of the
records required by this section for at
least 30 days.

§ 125.407 Maintenance log: Airplanes.

(a) Each person who takes corrective

action or defers action concerning a re-
ported or observed failure or malfunc-
tion of an airframe, aircraft engine,
propeller, or appliance shall record the
action taken in the airplane mainte-
nance log in accordance with part 43 of
this chapter.

(b) Each certificate holder shall es-

tablish a procedure for keeping copies
of the airplane maintenance log re-
quired by this section in the airplane
for access by appropriate personnel and
shall include that procedure in the
manual required by § 125.249.

§ 125.409 Service difficulty reports.

(a) Each certificate holder shall re-

port the occurrence or detection of
each failure, malfunction, or defect, in
a form and manner prescribed by the
Administrator.

(b) Each certificate holder shall sub-

mit each report required by this sec-
tion, covering each 24-hour period be-
ginning at 0900 local time of each day
and ending at 0900 local time on the
next day, to the FAA office in Okla-
homa City, Oklahoma. Each report of
occurrences during a 24-hour period
shall be submitted to the collection
point within the next 96 hours. How-
ever, a report due on Saturday or Sun-
day may be submitted on the following
Monday, and a report due on a holiday
may be submitted on the next work
day.

[Doc. No. 19779, 45 FR 67235, Oct. 9, 1980, as
amended by Amdt. 125–49, 70 FR 76979, Dec.
29, 2005]

§ 125.411 Airworthiness release or

maintenance record entry.

(a) No certificate holder may operate

an airplane after maintenance, preven-
tive maintenance, or alteration is per-
formed on the airplane unless the per-
son performing that maintenance, pre-

ventive maintenance, or alteration pre-
pares or causes to be prepared—

(1) An airworthiness release; or
(2) An entry in the aircraft mainte-

nance records in accordance with the
certificate holder’s manual.

(b) The airworthiness release or

maintenance record entry required by
paragraph (a) of this section must—

(1) Be prepared in accordance with

the procedures set forth in the certifi-
cate holder’s manual;

(2) Include a certification that—
(i) The work was performed in ac-

cordance with the requirements of the
certificate holder’s manual;

(ii) All items required to be inspected

were inspected by an authorized person
who determined that the work was sat-
isfactorily completed;

(iii) No known condition exists that

would make the airplane unairworthy;
and

(iv) So far as the work performed is

concerned, the airplane is in condition
for safe operation; and

(3) Be signed by a person authorized

in part 43 of this chapter to perform
maintenance, preventive maintenance,
and alteration.

form is prepared, the certificate holder
must give a copy to the pilot in com-
mand and keep a record of it for at
least 60 days.

(d) Instead of restating each of the

conditions of the certification required
by paragraph (b) of this section, the
certificate holder may state in its
manual that the signature of a person
authorized in part 43 of this chapter
constitutes that certification.

Subpart M—Continued Airworthi-

ness and Safety Improve-
ments

OURCE

: Amdt. 125–53, 72 FR 63412, Nov. 8,

2007, unless otherwise noted.

§ 125.501 Purpose and definition.

(a) This subpart requires operators to

support the continued airworthiness of
each airplane. These requirements may
include, but are not limited to, revising
the inspection program, incorporating
design changes, and incorporating revi-
sions to Instructions for Continued
Airworthiness.

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.

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