131 

Federal Aviation Administration, DOT 

§ 21.4 

(6) Flammable fluid leakage in areas 

where an ignition source normally ex-
ists. 

(7) A brake system failure caused by 

structural or material failure during 
operation. 

(8) A significant aircraft primary 

structural defect or failure caused by 
any autogenous condition (fatigue, un-
derstrength, corrosion, etc.). 

(9) Any abnormal vibration or buf-

feting caused by a structural or system 
malfunction, defect, or failure. 

(10) An engine failure. 
(11) Any structural or flight control 

system malfunction, defect, or failure 
which causes an interference with nor-
mal control of the aircraft for which 
derogates the flying qualities. 

(12) A complete loss of more than one 

electrical power generating system or 
hydraulic power system during a given 
operation of the aircraft. 

(13) A failure or malfunction of more 

than one attitude, airspeed, or altitude 
instrument during a given operation of 
the aircraft. 

(d) The requirements of paragraph (a) 

of this section do not apply to— 

(1) Failures, malfunctions, or defects 

that the holder of a type certificate 
(including amended or supplemental 
type certificates), PMA, TSO author-
ization, or the licensee of a type cer-
tificate determines— 

(i) Were caused by improper mainte-

nance or use; 

(ii) Were reported to the FAA by an-

other person under this chapter; or 

(iii) Were reported under the accident 

reporting provisions of 49 CFR part 830 
of the regulations of the National 
Transportation Safety Board. 

(2) Failures, malfunctions, or defects 

in products or articles— 

(i) Manufactured by a foreign manu-

facturer under a U.S. type certificate 
issued under § 21.29 or under an ap-
proval issued under § 21.621; or 

(ii) Exported to the United States 

under § 21.502. 

(e) Each report required by this sec-

tion— 

(1) Must be made to the Aircraft Cer-

tification Office in the region in which 
the person required to make the report 
is located within 24 hours after it has 
determined that the failure, malfunc-
tion, or defect required to be reported 

has occurred. However, a report that is 
due on a Saturday or a Sunday may be 
delivered on the following Monday and 
one that is due on a holiday may be de-
livered on the next workday; 

(2) Must be transmitted in a manner 

and form acceptable to the FAA and by 
the most expeditious method available; 
and 

(3) Must include as much of the fol-

lowing information as is available and 
applicable: 

(i) The applicable product and article 

identification information required by 
part 45 of this chapter; 

(ii) Identification of the system in-

volved; and 

(iii) Nature of the failure, malfunc-

tion, or defect. 

(f) If an accident investigation or 

service difficulty report shows that a 
product or article manufactured under 
this part is unsafe because of a manu-
facturing or design data defect, the 
holder of the production approval for 
that product or article must, upon re-
quest of the FAA, report to the FAA 
the results of its investigation and any 
action taken or proposed by the holder 
of that production approval to correct 
that defect. If action is required to cor-
rect the defect in an existing product 
or article, the holder of that produc-
tion approval must send the data nec-
essary for issuing an appropriate air-
worthiness directive to the appropriate 
aircraft certification office. 

[Amdt. 21–36, 35 FR 18187, Nov. 28, 1970, as 
amended by Amdt. 21–37, 35 FR 18450, Dec. 4, 
1970; Amdt. 21–50, 45 FR 38346, June 9, 1980; 
Amdt. 21–67, 54 FR 39291, Sept. 25, 1989; Amdt. 
21–92, 74 FR 53385, Oct. 16, 2009] 

§ 21.4

ETOPS reporting requirements. 

(a) 

Early ETOPS: reporting, tracking, 

and resolving problems. The holder of a 
type certificate for an airplane-engine 
combination approved using the Early 
ETOPS method specified in part 25, Ap-
pendix K, of this chapter must use a 
system for reporting, tracking, and re-
solving each problem resulting in one 
of the occurrences specified in para-
graph (a)(6) of this section. 

(1) The system must identify how the 

type certificate holder will promptly 
identify problems, report them to the 
responsible FAA aircraft certification 
office, and propose a solution to the 

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