846 

14 CFR Ch. I (1–1–24 Edition) 

§ 39.27 

§ 39.27

What do I do if the airworthi-

ness directive conflicts with the 
service document on which it is 
based? 

In some cases an airworthiness direc-

tive incorporates by reference a manu-
facturer’s service document. In these 
cases, the service document becomes 
part of the airworthiness directive. In 
some cases the directions in the service 
document may be modified by the air-
worthiness directive. If there is a con-
flict between the service document and 
the airworthiness directive, you must 
follow the requirements of the air-
worthiness directive. 

PART 43—MAINTENANCE, PREVEN-

TIVE MAINTENANCE, REBUILD-
ING, AND ALTERATION 

Sec. 
43.1

Applicability. 

43.2

Records of overhaul and rebuilding. 

43.3

Persons authorized to perform mainte-

nance, preventive maintenance, rebuild-
ing, and alterations. 

43.5

Approval for return to service after 

maintenance, preventive maintenance, 
rebuilding, or alteration. 

43.7

Persons authorized to approve aircraft, 

airframes, aircraft engines, propellers, 
appliances, or component parts for re-
turn to service after maintenance, pre-
ventive maintenance, rebuilding, or al-
teration. 

43.9

Content, form, and disposition of main-

tenance, preventive maintenance, re-
building, and alteration records (except 
inspections performed in accordance 
with part 91, part 123, part 125, 
§ 135.411(a)(1), and § 135.419 of this chap-
ter). 

43.10

Disposition of life-limited aircraft 

parts. 

43.11

Content, form, and disposition of 

records for inspections conducted under 
parts 91 and 125 and §§ 135.411(a)(1) and 
135.419 of this chapter. 

43.12

Maintenance records: Falsification, re-

production, or alteration. 

43.13

Performance rules (general). 

43.15

Additional performance rules for in-

spections. 

43.16

Airworthiness Limitations. 

43.17

Maintenance, preventive maintenance, 

and alterations performed on U.S. aero-
nautical products by certain Canadian 
persons. 

A

PPENDIX

A 

TO

P

ART

43—M

AJOR

A

LTER

-

ATIONS

, M

AJOR

R

EPAIRS

, 

AND

P

REVENTIVE

 

M

AINTENANCE

 

A

PPENDIX

B 

TO

P

ART

43—R

ECORDING

OF

 

M

AJOR

R

EPAIRS AND

M

AJOR

A

LTERATIONS

 

A

PPENDIX

C 

TO

P

ART

43 [R

ESERVED

] 

A

PPENDIX

D 

TO

P

ART

43—S

COPE AND

D

ETAIL

 

OF

I

TEMS

(

AS

A

PPLICABLE TO THE

P

AR

-

TICULAR

A

IRCRAFT

) T

O

B

E

I

NCLUDED

IN

 

A

NNUAL AND

100-H

OUR

I

NSPECTIONS

 

A

PPENDIX

E 

TO

P

ART

43—A

LTIMETER

S

YSTEM

 

T

EST AND

I

NSPECTION

 

A

PPENDIX

F 

TO

P

ART

43—ATC T

RANSPONDER

 

T

ESTS AND

I

NSPECTIONS

 

A

UTHORITY

: 42 U.S.C. 7572; 49 U.S.C. 106(f), 

106(g), 40105, 40113, 44701–44702, 44704, 44707, 
44709, 44711, 44713, 44715, 45303. 

S

OURCE

: Docket No. 1993, 29 FR 5451, Apr. 

23, 1964, unless otherwise noted. 

E

DITORIAL

N

OTE

: For miscellaneous tech-

nical amendments to this part 43, see Amdt. 
43–3, 31 FR 3336, Mar. 3, 1966, and Amdt. 43– 
6, 31 FR 9211, July 6, 1966. 

§ 43.1

Applicability. 

(a) Except as provided in paragraphs 

(b) and (d) of this section, this part pre-
scribes rules governing the mainte-
nance, preventive maintenance, re-
building, and alteration of any— 

(1) Aircraft having a U.S. airworthi-

ness certificate; 

(2) Foreign-registered civil aircraft 

used in common carriage or carriage of 
mail under the provisions of Part 121 or 
135 of this chapter; and 

(3) Airframe, aircraft engines, propel-

lers, appliances, and component parts 
of such aircraft. 

(b) This part does not apply to— 
(1) Any aircraft for which the FAA 

has issued an experimental certificate, 
unless the FAA has previously issued a 
different kind of airworthiness certifi-
cate for that aircraft; 

(2) Any aircraft for which the FAA 

has issued an experimental certificate 
under the provisions of § 21.191(i)(3) of 
this chapter, and the aircraft was pre-
viously issued a special airworthiness 
certificate in the light-sport category 
under the provisions of § 21.190 of this 
chapter; or 

(3) Any aircraft that is operated 

under part 107 of this chapter, except 
as described in § 107.140(d). 

(c) This part applies to all life-lim-

ited parts that are removed from a 
type certificated product, segregated, 
or controlled as provided in § 43.10. 

(d) This part applies to any aircraft 

issued a special airworthiness certifi-
cate in the light-sport category except: 

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§ 43.3 

(1) The repair or alteration form 

specified in §§ 43.5(b) and 43.9(d) is not 
required to be completed for products 
not produced under an FAA approval; 

(2) Major repairs and major alter-

ations for products not produced under 
an FAA approval are not required to be 
recorded in accordance with appendix B 
of this part; and 

(3) The listing of major alterations 

and major repairs specified in para-
graphs (a) and (b) of appendix A of this 
part is not applicable to products not 
produced under an FAA approval. 

[Doc. No. 1993, 29 FR 5451, Apr. 23, 1964, as 
amended by Amdt. 43–23, 47 FR 41084, Sept. 
16, 1982; Amdt. 43–37, 66 FR 21066, Apr. 27, 
2001; Amdt. 43–38, 67 FR 2109, Jan. 15, 2002; 
Amdt. 43–39, 69 FR 44863, July 27, 2004; Amdt. 
43–44, 75 FR 5219, Feb. 1, 2010; Docket FAA– 
2015–0150, Amdt. 43–48, 81 FR 42208, June 28, 
2016; Docket FAA–2018–1087, Amdt. 43–51, 86 
FR 4381, Jan. 15, 2021] 

§ 43.2

Records of overhaul and rebuild-

ing. 

(a) No person may describe in any re-

quired maintenance entry or form an 
aircraft, airframe, aircraft engine, pro-
peller, appliance, or component part as 
being overhauled unless— 

(1) Using methods, techniques, and 

practices acceptable to the Adminis-
trator, it has been disassembled, 
cleaned, inspected, repaired as nec-
essary, and reassembled; and 

(2) It has been tested in accordance 

with approved standards and technical 
data, or in accordance with current 
standards and technical data accept-
able to the Administrator, which have 
been developed and documented by the 
holder of the type certificate, supple-
mental type certificate, or a material, 
part, process, or appliance approval 
under part 21 of this chapter. 

(b) No person may describe in any re-

quired maintenance entry or form an 
aircraft, airframe, aircraft engine, pro-
peller, appliance, or component part as 
being rebuilt unless it has been dis-
assembled, cleaned, inspected, repaired 
as necessary, reassembled, and tested 
to the same tolerances and limits as a 
new item, using either new parts or 
used parts that either conform to new 
part tolerances and limits or to ap-

proved oversized or undersized dimen-
sions. 

[Amdt. 43–23, 47 FR 41084, Sept. 16, 1982, as 
amended by Amdt. 43–43, 74 FR 53394, Oct. 16, 
2009] 

§ 43.3

Persons authorized to perform 

maintenance, preventive mainte-
nance, rebuilding, and alterations. 

(a) Except as provided in this section 

and § 43.17, no person may maintain, re-
build, alter, or perform preventive 
maintenance on an aircraft, airframe, 
aircraft engine, propeller, appliance, or 
component part to which this part ap-
plies. Those items, the performance of 
which is a major alteration, a major re-
pair, or preventive maintenance, are 
listed in appendix A. 

(b) The holder of a mechanic certifi-

cate may perform maintenance, pre-
ventive maintenance, and alterations 
as provided in Part 65 of this chapter. 

(c) The holder of a repairman certifi-

cate may perform maintenance, pre-
ventive maintenance, and alterations 
as provided in part 65 of this chapter. 

(d) A person working under the su-

pervision of a holder of a mechanic or 
repairman certificate may perform the 
maintenance, preventive maintenance, 
and alterations that his supervisor is 
authorized to perform, if the supervisor 
personally observes the work being 
done to the extent necessary to ensure 
that it is being done properly and if the 
supervisor is readily available, in per-
son, for consultation. However, this 
paragraph does not authorize the per-
formance of any inspection required by 
Part 91 or Part 125 of this chapter or 
any inspection performed after a major 
repair or alteration. 

(e) The holder of a repair station cer-

tificate may perform maintenance, pre-
ventive maintenance, and alterations 
as provided in Part 145 of this chapter. 

(f) The holder of an air carrier oper-

ating certificate or an operating cer-
tificate issued under Part 121 or 135, 
may perform maintenance, preventive 
maintenance, and alterations as pro-
vided in Part 121 or 135. 

(g) Except for holders of a sport pilot 

certificate, the holder of a pilot certifi-
cate issued under part 61 may perform 
preventive maintenance on any air-
craft owned or operated by that pilot 
which is not used under part 121, 129, or 

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§ 43.5 

135 of this chapter. The holder of a 
sport pilot certificate may perform 
preventive maintenance on an aircraft 
owned or operated by that pilot and 
issued a special airworthiness certifi-
cate in the light-sport category. 

(h) Notwithstanding the provisions of 

paragraph (g) of this section, the Ad-
ministrator may approve a certificate 
holder under Part 135 of this chapter, 
operating rotorcraft in a remote area, 
to allow a pilot to perform specific pre-
ventive maintenance items provided— 

(1) The items of preventive mainte-

nance are a result of a known or sus-
pected mechanical difficulty or mal-
function that occurred en route to or 
in a remote area; 

(2) The pilot has satisfactorily com-

pleted an approved training program 
and is authorized in writing by the cer-
tificate holder for each item of preven-
tive maintenance that the pilot is au-
thorized to perform; 

(3) There is no certificated mechanic 

available to perform preventive main-
tenance; 

(4) The certificate holder has proce-

dures to evaluate the accomplishment 
of a preventive maintenance item that 
requires a decision concerning the air-
worthiness of the rotorcraft; and 

(5) The items of preventive mainte-

nance authorized by this section are 
those listed in paragraph (c) of appen-
dix A of this part. 

(i) Notwithstanding the provisions of 

paragraph (g) of this section, in accord-
ance with an approval issued to the 
holder of a certificate issued under part 
135 of this chapter, a pilot of an air-
craft type-certificated for 9 or fewer 
passenger seats, excluding any pilot 
seat, may perform the removal and re-
installation of approved aircraft cabin 
seats, approved cabin-mounted stretch-
ers, and when no tools are required, ap-
proved cabin-mounted medical oxygen 
bottles, provided— 

(1) The pilot has satisfactorily com-

pleted an approved training program 
and is authorized in writing by the cer-
tificate holder to perform each task; 
and 

(2) The certificate holder has written 

procedures available to the pilot to 
evaluate the accomplishment of the 
task. 

(j) A manufacturer may— 

(1) Rebuild or alter any aircraft, air-

craft engine, propeller, or appliance 
manufactured by him under a type or 
production certificate; 

(2) Rebuild or alter any appliance or 

part of aircraft, aircraft engines, pro-
pellers, or appliances manufactured by 
him under a Technical Standard Order 
Authorization, an FAA-Parts Manufac-
turer Approval, or Product and Process 
Specification issued by the Adminis-
trator; and 

(3) Perform any inspection required 

by part 91 or part 125 of this chapter on 
aircraft it manufactured under a type 
certificate, or currently manufactures 
under a production certificate. 

(k) Updates of databases in installed 

avionics meeting the conditions of this 
paragraph are not considered mainte-
nance and may be performed by pilots 
provided: 

(1) The database upload is: 
(i) Initiated from the flight deck; 
(ii) Performed without disassembling 

the avionics unit; and 

(iii) Performed without the use of 

tools and/or special equipment. 

(2) The pilot must comply with the 

certificate holder’s procedures or the 
manufacturer’s instructions. 

(3) The holder of operating certifi-

cates must make available written pro-
cedures consistent with manufacturer’s 
instructions to the pilot that describe 
how to: 

(i) Perform the database update; and 
(ii) Determine the status of the data 

upload. 

[Doc. No. 1993, 29 FR 5451, Apr. 23, 1964, as 
amended by Amdt. 43–4, 31 FR 5249, Apr. 1, 
1966; Amdt. 43–23, 47 FR 41084, Sept. 16, 1982; 
Amdt. 43–25, 51 FR 40702, Nov. 7, 1986; Amdt. 
43–36, 61 FR 19501, May 1, 1996; Amdt. 43–37, 66 
FR 21066, Apr. 27, 2001; Amdt. 43–39, 69 FR 
44863, July 27, 2004; Amdt. 43–43, 74 FR 53394, 
Oct. 16, 2009; Amdt. 43–45, 77 FR 71096, Nov. 
29, 2012] 

§ 43.5

Approval for return to service 

after maintenance, preventive 
maintenance, rebuilding, or alter-
ation. 

No person may approve for return to 

service any aircraft, airframe, aircraft 
engine, propeller, or appliance, that 
has undergone maintenance, preventive 
maintenance, rebuilding, or alteration 
unless— 

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§ 43.9 

(a) The maintenance record entry re-

quired by § 43.9 or § 43.11, as appro-
priate, has been made; 

(b) The repair or alteration form au-

thorized by or furnished by the Admin-
istrator has been executed in a manner 
prescribed by the Administrator; and 

(c) If a repair or an alteration results 

in any change in the aircraft operating 
limitations or flight data contained in 
the approved aircraft flight manual, 
those operating limitations or flight 
data are appropriately revised and set 
forth as prescribed in § 91.9 of this chap-
ter. 

[Doc. No. 1993, 29 FR 5451, Apr. 23, 1964, as 
amended by Amdt. 43–23, 47 FR 41084, Sept. 
16, 1982; Amdt. 43–31, 54 FR 34330, Aug. 18, 
1989] 

§ 43.7

Persons authorized to approve 

aircraft, airframes, aircraft engines, 
propellers, appliances, or compo-
nent parts for return to service 
after maintenance, preventive 
maintenance, rebuilding, or alter-
ation. 

(a) Except as provided in this section 

and § 43.17, no person, other than the 
Administrator, may approve an air-
craft, airframe, aircraft engine, pro-
peller, appliance, or component part 
for return to service after it has under-
gone maintenance, preventive mainte-
nance, rebuilding, or alteration. 

(b) The holder of a mechanic certifi-

cate or an inspection authorization 
may approve an aircraft, airframe, air-
craft engine, propeller, appliance, or 
component part for return to service as 
provided in Part 65 of this chapter. 

(c) The holder of a repair station cer-

tificate may approve an aircraft, air-
frame, aircraft engine, propeller, appli-
ance, or component part for return to 
service as provided in Part 145 of this 
chapter. 

(d) A manufacturer may approve for 

return to service any aircraft, air-
frame, aircraft engine, propeller, appli-
ance, or component part which that 
manufacturer has worked on under 
§ 43.3(j). However, except for minor al-
terations, the work must have been 
done in accordance with technical data 
approved by the Administrator. 

(e) The holder of an air carrier oper-

ating certificate or an operating cer-
tificate issued under Part 121 or 135, 
may approve an aircraft, airframe, air-

craft engine, propeller, appliance, or 
component part for return to service as 
provided in Part 121 or 135 of this chap-
ter, as applicable. 

(f) A person holding at least a private 

pilot certificate may approve an air-
craft for return to service after per-
forming preventive maintenance under 
the provisions of § 43.3(g). 

(g) The holder of a repairman certifi-

cate (light-sport aircraft) with a main-
tenance rating may approve an aircraft 
issued a special airworthiness certifi-
cate in light-sport category for return 
to service, as provided in part 65 of this 
chapter. 

(h) The holder of at least a sport 

pilot certificate may approve an air-
craft owned or operated by that pilot 
and issued a special airworthiness cer-
tificate in the light-sport category for 
return to service after performing pre-
ventive maintenance under the provi-
sions of § 43.3(g). 

[Amdt. 43–23, 47 FR 41084, Sept. 16, 1982, as 
amended by Amdt. 43–36, 61 FR 19501, May 1, 
1996; Amdt. 43–37, 66 FR 21066, Apr. 27, 2001; 
Amdt. 43–39, 69 FR 44863, July 27, 2004] 

§ 43.9

Content, form, and disposition of 

maintenance, preventive mainte-
nance, rebuilding, and alteration 
records (except inspections per-
formed in accordance with part 91, 
part 125, § 135.411(a)(1), and 
§ 135.419 of this chapter). 

(a) 

Maintenance record entries. Except 

as provided in paragraphs (b) and (c) of 
this section, each person who main-
tains, performs preventive mainte-
nance, rebuilds, or alters an aircraft, 
airframe, aircraft engine, propeller, ap-
pliance, or component part shall make 
an entry in the maintenance record of 
that equipment containing the fol-
lowing information: 

(1) A description (or reference to data 

acceptable to the Administrator) of 
work performed. 

(2) The date of completion of the 

work performed. 

(3) The name of the person per-

forming the work if other than the per-
son specified in paragraph (a)(4) of this 
section. 

(4) If the work performed on the air-

craft, airframe, aircraft engine, pro-
peller, appliance, or component part 
has been performed satisfactorily, the 
signature, certificate number, and kind 

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§ 43.10 

of certificate held by the person ap-
proving the work. The signature con-
stitutes the approval for return to 
service only for the work performed. 

(b) Each holder of an air carrier oper-

ating certificate or an operating cer-
tificate issued under Part 121 or 135, 
that is required by its approved oper-
ations specifications to provide for a 
continuous airworthiness maintenance 
program, shall make a record of the 
maintenance, preventive maintenance, 
rebuilding, and alteration, on aircraft, 
airframes, aircraft engines, propellers, 
appliances, or component parts which 
it operates in accordance with the ap-
plicable provisions of Part 121 or 135 of 
this chapter, as appropriate. 

(c) This section does not apply to per-

sons performing inspections in accord-
ance with Part 91, 125, § 135.411(a)(1), or 
§ 135.419 of this chapter. 

(d) In addition to the entry required 

by paragraph (a) of this section, major 
repairs and major alterations shall be 
entered on a form, and the form dis-
posed of, in the manner prescribed in 
appendix B, by the person performing 
the work. 

[Amdt. 43–23, 47 FR 41085, Sept. 16, 1982, as 
amended by Amdt. 43–37, 66 FR 21066, Apr. 27, 
2001; Amdt. 43–39, 69 FR 44863, July 27, 2004] 

§ 43.10

Disposition of life-limited air-

craft parts. 

(a) 

Definitions used in this section. For 

the purposes of this section the fol-
lowing definitions apply. 

Life-limited part means any part for 

which a mandatory replacement limit 
is specified in the type design, the In-
structions for Continued Airworthi-
ness, or the maintenance manual. 

Life status means the accumulated 

cycles, hours, or any other mandatory 
replacement limit of a life-limited 
part. 

(b) 

Temporary removal of parts from 

type-certificated products. When a life- 
limited part is temporarily removed 
and reinstalled for the purpose of per-
forming maintenance, no disposition 
under paragraph (c) of this section is 
required if— 

(1) The life status of the part has not 

changed; 

(2) The removal and reinstallation is 

performed on the same serial numbered 
product; and 

(3) That product does not accumulate 

time in service while the part is re-
moved. 

(c) 

Disposition of parts removed from 

type-certificated products. Except as pro-
vided in paragraph (b) of this section, 
after April 15, 2002 each person who re-
moves a life-limited part from a type- 
certificated product must ensure that 
the part is controlled using one of the 
methods in this paragraph. The method 
must deter the installation of the part 
after it has reached its life limit. Ac-
ceptable methods include: 

(1) 

Record keeping system. The part 

may be controlled using a record keep-
ing system that substantiates the part 
number, serial number, and current life 
status of the part. Each time the part 
is removed from a type certificated 
product, the record must be updated 
with the current life status. This sys-
tem may include electronic, paper, or 
other means of record keeping. 

(2) 

Tag or record attached to part. A 

tag or other record may be attached to 
the part. The tag or record must in-
clude the part number, serial number, 
and current life status of the part. 
Each time the part is removed from a 
type certificated product, either a new 
tag or record must be created, or the 
existing tag or record must be updated 
with the current life status. 

(3) 

Non-permanent marking. The part 

may be legibly marked using a non- 
permanent method showing its current 
life status. The life status must be up-
dated each time the part is removed 
from a type certificated product, or if 
the mark is removed, another method 
in this section may be used. The mark 
must be accomplished in accordance 
with the instructions under § 45.16 of 
this chapter in order to maintain the 
integrity of the part. 

(4) 

Permanent marking. The part may 

be legibly marked using a permanent 
method showing its current life status. 
The life status must be updated each 
time the part is removed from a type 
certificated product. Unless the part is 
permanently removed from use on type 
certificated products, this permanent 
mark must be accomplished in accord-
ance with the instructions under § 45.16 
of this chapter in order to maintain the 
integrity of the part. 

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§ 43.11 

(5) 

Segregation.  The part may be seg-

regated using methods that deter its 
installation on a type-certificated 
product. These methods must include, 
at least— 

(i) Maintaining a record of the part 

number, serial number, and current life 
status, and 

(ii) Ensuring the part is physically 

stored separately from parts that are 
currently eligible for installation. 

(6) 

Mutilation. The part may be muti-

lated to deter its installation in a type 
certificated product. The mutilation 
must render the part beyond repair and 
incapable of being reworked to appear 
to be airworthy. 

(7) 

Other methods. Any other method 

approved or accepted by the FAA. 

(d) 

Transfer of life-limited parts. Each 

person who removes a life-limited part 
from a type certificated product and 
later sells or otherwise transfers that 
part must transfer with the part the 
mark, tag, or other record used to com-
ply with this section, unless the part is 
mutilated before it is sold or trans-
ferred. 

[Doc. No. FAA–2000–8017, 67 FR 2110, Jan. 15, 
2002, as amended by Amdt. 43–38A, 79 FR 
67055, Nov. 12, 2014] 

§ 43.11

Content, form, and disposition 

of records for inspections con-
ducted under parts 91 and 125 and 
§§ 135.411(a)(1) and 135.419 of this 
chapter. 

(a) 

Maintenance record entries. The 

person approving or disapproving for 
return to service an aircraft, airframe, 
aircraft engine, propeller, appliance, or 
component part after any inspection 
performed in accordance with part 91, 
125, § 135.411(a)(1), or § 135.419 shall 
make an entry in the maintenance 
record of that equipment containing 
the following information: 

(1) The type of inspection and a brief 

description of the extent of the inspec-
tion. 

(2) The date of the inspection and air-

craft total time in service. 

(3) The signature, the certificate 

number, and kind of certificate held by 
the person approving or disapproving 
for return to service the aircraft, air-
frame, aircraft engine, propeller, appli-
ance, component part, or portions 
thereof. 

(4) Except for progressive inspec-

tions, if the aircraft is found to be air-
worthy and approved for return to 
service, the following or a similarly 
worded statement—‘‘I certify that this 
aircraft has been inspected in accord-
ance with (insert type) inspection and 
was determined to be in airworthy con-
dition.’’ 

(5) Except for progressive inspec-

tions, if the aircraft is not approved for 
return to service because of needed 
maintenance, noncompliance with ap-
plicable specifications, airworthiness 
directives, or other approved data, the 
following or a similarly worded state-
ment—‘‘I certify that this aircraft has 
been inspected in accordance with (in-
sert type) inspection and a list of dis-
crepancies and unairworthy items 
dated (date) has been provided for the 
aircraft owner or operator.’’ 

(6) For progressive inspections, the 

following or a similarly worded state-
ment—‘‘I certify that in accordance 
with a progressive inspection program, 
a routine inspection of (identify wheth-
er aircraft or components) and a de-
tailed inspection of (identify compo-
nents) were performed and the (aircraft 
or components) are (approved or dis-
approved) for return to service.’’ If dis-
approved, the entry will further state 
‘‘and a list of discrepancies and unair-
worthy items dated (date) has been 
provided to the aircraft owner or oper-
ator.’’ 

(7) If an inspection is conducted 

under an inspection program provided 
for in part 91, 125, or § 135.411(a)(1), the 
entry must identify the inspection pro-
gram, that part of the inspection pro-
gram accomplished, and contain a 
statement that the inspection was per-
formed in accordance with the inspec-
tions and procedures for that par-
ticular program. 

(b) 

Listing of discrepancies and plac-

ards.  If the person performing any in-
spection required by part 91 or 125 or 
§ 135.411(a)(1) of this chapter finds that 
the aircraft is unairworthy or does not 
meet the applicable type certificate 
data, airworthiness directives, or other 
approved data upon which its air-
worthiness depends, that persons must 
give the owner or lessee a signed and 
dated list of those discrepancies. For 

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14 CFR Ch. I (1–1–24 Edition) 

§ 43.12 

those items permitted to be inoper-
ative under § 91.213(d)(2) of this chapter, 
that person shall place a placard, that 
meets the aircraft’s airworthiness cer-
tification regulations, on each inoper-
ative instrument and the cockpit con-
trol of each item of inoperative equip-
ment, marking it ‘‘Inoperative,’’ and 
shall add the items to the signed and 
dated list of discrepancies given to the 
owner or lessee. 

[Amdt. 43–23, 47 FR 41085, Sept. 16, 1982, as 
amended by Amdt. 43–30, 53 FR 50195, Dec. 13, 
1988; Amdt. 43–36, 61 FR 19501, May 1, 1996; 71 
FR 44188, Aug. 4, 2006] 

§ 43.12

Maintenance records: Falsifica-

tion, reproduction, or alteration. 

(a) No person may make or cause to 

be made: 

(1) Any fraudulent or intentionally 

false entry in any record or report that 
is required to be made, kept, or used to 
show compliance with any requirement 
under this part; 

(2) Any reproduction, for fraudulent 

purpose, of any record or report under 
this part; or 

(3) Any alteration, for fraudulent 

purpose, of any record or report under 
this part. 

(b) The commission by any person of 

an act prohibited under paragraph (a) 
of this section is a basis for suspending 
or revoking the applicable airman, op-
erator, or production certificate, Tech-
nical Standard Order Authorization, 
FAA-Parts Manufacturer Approval, or 
Product and Process Specification 
issued by the Administrator and held 
by that person. 

[Amdt. 43–19, 43 FR 22639, May 25, 1978, as 
amended by Amdt. 43–23, 47 FR 41085, Sept. 
16, 1982] 

§ 43.13

Performance rules (general). 

(a) Each person performing mainte-

nance, alteration, or preventive main-
tenance on an aircraft, engine, pro-
peller, or appliance shall use the meth-
ods, techniques, and practices pre-
scribed in the current manufacturer’s 
maintenance manual or Instructions 
for Continued Airworthiness prepared 
by its manufacturer, or other methods, 
techniques, and practices acceptable to 
the Administrator, except as noted in 
§ 43.16. He shall use the tools, equip-
ment, and test apparatus necessary to 

assure completion of the work in ac-
cordance with accepted industry prac-
tices. If special equipment or test appa-
ratus is recommended by the manufac-
turer involved, he must use that equip-
ment or apparatus or its equivalent ac-
ceptable to the Administrator. 

(b) Each person maintaining or alter-

ing, or performing preventive mainte-
nance, shall do that work in such a 
manner and use materials of such a 
quality, that the condition of the air-
craft, airframe, aircraft engine, pro-
peller, or appliance worked on will be 
at least equal to its original or prop-
erly altered condition (with regard to 
aerodynamic function, structural 
strength, resistance to vibration and 
deterioration, and other qualities af-
fecting airworthiness). 

(c) 

Special provisions for holders of air 

carrier operating certificates and oper-
ating certificates issued under the provi-
sions of Part 121 or 135 and Part 129 oper-
ators holding operations specifications. 
Unless otherwise notified by the ad-
ministrator, the methods, techniques, 
and practices contained in the mainte-
nance manual or the maintenance part 
of the manual of the holder of an air 
carrier operating certificate or an op-
erating certificate under Part 121 or 135 
and Part 129 operators holding oper-
ations specifications (that is required 
by its operating specifications to pro-
vide a continuous airworthiness main-
tenance and inspection program) con-
stitute acceptable means of compliance 
with this section. 

[Doc. No. 1993, 29 FR 5451, Apr. 23, 1964, as 
amended by Amdt. 43–20, 45 FR 60182, Sept. 
11, 1980; Amdt. 43–23, 47 FR 41085, Sept. 16, 
1982; Amdt. 43–28, 52 FR 20028, June 16, 1987; 
Amdt. 43–37, 66 FR 21066, Apr. 27, 2001] 

§ 43.15

Additional performance rules 

for inspections. 

(a) 

General.  Each person performing 

an inspection required by part 91, 125, 
or 135 of this chapter, shall— 

(1) Perform the inspection so as to 

determine whether the aircraft, or por-
tion(s) thereof under inspection, meets 
all applicable airworthiness require-
ments; and 

(2) If the inspection is one provided 

for in part 125, 135, or § 91.409(e) of this 

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§ 43.17 

chapter, perform the inspection in ac-
cordance with the instructions and pro-
cedures set forth in the inspection pro-
gram for the aircraft being inspected. 

(b) 

Rotorcraft. 

Each person per-

forming an inspection required by Part 
91 on a rotorcraft shall inspect the fol-
lowing systems in accordance with the 
maintenance manual or Instructions 
for Continued Airworthiness of the 
manufacturer concerned: 

(1) The drive shafts or similar sys-

tems. 

(2) The main rotor transmission gear 

box for obvious defects. 

(3) The main rotor and center section 

(or the equivalent area). 

(4) The auxiliary rotor on heli-

copters. 

(c) 

Annual and 100-hour inspections. (1) 

Each person performing an annual or 
100-hour inspection shall use a check-
list while performing the inspection. 
The checklist may be of the person’s 
own design, one provided by the manu-
facturer of the equipment being in-
spected or one obtained from another 
source. This checklist must include the 
scope and detail of the items contained 
in appendix D to this part and para-
graph (b) of this section. 

(2) Each person approving a recipro-

cating-engine-powered aircraft for re-
turn to service after an annual or 100- 
hour inspection shall, before that ap-
proval, run the aircraft engine or en-
gines to determine satisfactory per-
formance in accordance with the manu-
facturer’s recommendations of— 

(i) Power output (static and idle 

r.p.m.); 

(ii) Magnetos; 
(iii) Fuel and oil pressure; and 
(iv) Cylinder and oil temperature. 
(3) Each person approving a turbine- 

engine-powered aircraft for return to 
service after an annual, 100-hour, or 
progressive inspection shall, before 
that approval, run the aircraft engine 
or engines to determine satisfactory 
performance in accordance with the 
manufacturer’s recommendations. 

(d) 

Progressive inspection. (1) Each per-

son performing a progressive inspec-
tion shall, at the start of a progressive 
inspection system, inspect the aircraft 
completely. After this initial inspec-
tion, routine and detailed inspections 
must be conducted as prescribed in the 

progressive inspection schedule. Rou-
tine inspections consist of visual exam-
ination or check of the appliances, the 
aircraft, and its components and sys-
tems, insofar as practicable without 
disassembly. Detailed inspections con-
sist of a thorough examination of the 
appliances, the aircraft, and its compo-
nents and systems, with such dis-
assembly as is necessary. For the pur-
poses of this subparagraph, the over-
haul of a component or system is con-
sidered to be a detailed inspection. 

(2) If the aircraft is away from the 

station where inspections are normally 
conducted, an appropriately rated me-
chanic, a certificated repair station, or 
the manufacturer of the aircraft may 
perform inspections in accordance with 
the procedures and using the forms of 
the person who would otherwise per-
form the inspection. 

[Doc. No. 1993, 29 FR 5451, Apr. 23, 1964, as 
amended by Amdt. 43–23, 47 FR 41086, Sept. 
16, 1982; Amdt. 43–25, 51 FR 40702, Nov. 7, 1986; 
Amdt. 43–31, 54 FR 34330, Aug. 18, 1989; 71 FR 
44188, Aug. 4, 2006] 

§ 43.16

Airworthiness limitations. 

Each person performing an inspec-

tion or other maintenance specified in 
an Airworthiness Limitations section 
of a manufacturer’s maintenance man-
ual or Instructions for Continued Air-
worthiness shall perform the inspec-
tion or other maintenance in accord-
ance with that section, or in accord-
ance with operations specifications ap-
proved by the Administrator under 
part 121 or 135, or an inspection pro-
gram approved under § 91.409(e). 

[71 FR 44188, Aug. 4, 2006] 

§ 43.17

Maintenance, preventive main-

tenance, and alterations performed 
on U.S. aeronautical products by 
certain Canadian persons. 

(a) 

Definitions.  For purposes of this 

section: 

Aeronautical product means any civil 

aircraft or airframe, aircraft engine, 
propeller, appliance, component, or 
part to be installed thereon. 

Canadian aeronautical product means 

any aeronautical product under air-
worthiness regulation by Transport 
Canada Civil Aviation. 

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Pt. 43, App. A 

U.S. aeronautical product means any 

aeronautical product under airworthi-
ness regulation by the FAA. 

(b) 

Applicability. This section does not 

apply to any U.S. aeronautical prod-
ucts maintained or altered under any 
bilateral agreement made between 
Canada and any country other than the 
United States. 

(c) 

Authorized persons. (1) A person 

holding a valid Transport Canada Civil 
Aviation Maintenance Engineer license 
and appropriate ratings may, with re-
spect to a U.S.-registered aircraft lo-
cated in Canada, perform maintenance, 
preventive maintenance, and alter-
ations in accordance with the require-
ments of paragraph (d) of this section 
and approve the affected aircraft for 
return to service in accordance with 
the requirements of paragraph (e) of 
this section. 

(2) A Transport Canada Civil Avia-

tion Approved Maintenance Organiza-
tion (AMO) holding appropriate ratings 
may, with respect to a U.S.-registered 
aircraft or other U.S. aeronautical 
products located in Canada, perform 
maintenance, preventive maintenance, 
and alterations in accordance with the 
requirements of paragraph (d) of this 
section and approve the affected prod-
ucts for return to service in accordance 
with the requirements of paragraph (e) 
of this section. 

(d) 

Performance requirements. A person 

authorized in paragraph (c) of this sec-
tion may perform maintenance (includ-
ing any inspection required by Sec. 
91.409 of this chapter, except an annual 
inspection), preventive maintenance, 
and alterations, provided— 

(1) The person performing the work is 

authorized by Transport Canada Civil 
Aviation to perform the same type of 
work with respect to Canadian aero-
nautical products; 

(2) The maintenance, preventive 

maintenance, or alteration is per-
formed in accordance with a Bilateral 
Aviation Safety Agreement between 
the United States and Canada and asso-
ciated Maintenance Implementation 
Procedures that provide a level of safe-
ty equivalent to that provided by the 
provisions of this chapter; 

(3) The maintenance, preventive 

maintenance, or alteration is per-
formed such that the affected product 

complies with the applicable require-
ments of part 36 of this chapter; and 

(4) The maintenance, preventive 

maintenance, or alteration is recorded 
in accordance with a Bilateral Aviation 
Safety Agreement between the United 
States and Canada and associated 
Maintenance Implementation Proce-
dures that provide a level of safety 
equivalent to that provided by the pro-
visions of this chapter. 

(e) 

Approval requirements. (1) To re-

turn an affected product to service, a 
person authorized in paragraph (c) of 
this section must approve (certify) 
maintenance, preventive maintenance, 
and alterations performed under this 
section, except that an Aircraft Main-
tenance Engineer may not approve a 
major repair or major alteration. 

(2) An AMO whose system of quality 

control for the maintenance, preven-
tive maintenance, alteration, and in-
spection of aeronautical products has 
been approved by Transport Canada 
Civil Aviation, or an authorized em-
ployee performing work for such an 
AMO, may approve (certify) a major re-
pair or major alteration performed 
under this section if the work was per-
formed in accordance with technical 
data approved by the FAA. 

(f) No person may operate in air com-

merce an aircraft, airframe, aircraft 
engine, propeller, or appliance on 
which maintenance, preventive main-
tenance, or alteration has been per-
formed under this section unless it has 
been approved for return to service by 
a person authorized in this section. 

[Amdt. 43–33, 56 FR 57571, Nov. 12, 1991, as 
amended by Amdt. 43–40, 71 FR 40877, July 14, 
2005] 

A

PPENDIX

A 

TO

P

ART

43—M

AJOR

A

LTER

-

ATIONS

, M

AJOR

R

EPAIRS

, 

AND

P

RE

-

VENTIVE

M

AINTENANCE

 

(a) 

Major alterations—(1)  Airframe major al-

terations.  Alterations of the following parts 
and alterations of the following types, when 
not listed in the aircraft specifications 
issued by the FAA, are airframe major alter-
ations: 

(i) Wings. 
(ii) Tail surfaces. 
(iii) Fuselage. 
(iv) Engine mounts. 
(v) Control system. 
(vi) Landing gear. 
(vii) Hull or floats. 

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(viii) Elements of an airframe including 

spars, ribs, fittings, shock absorbers, brac-
ing, cowling, fairings, and balance weights. 

(ix) Hydraulic and electrical actuating sys-

tem of components. 

(x) Rotor blades. 
(xi) Changes to the empty weight or empty 

balance which result in an increase in the 
maximum certificated weight or center of 
gravity limits of the aircraft. 

(xii) Changes to the basic design of the 

fuel, oil, cooling, heating, cabin pressuriza-
tion, electrical, hydraulic, de-icing, or ex-
haust systems. 

(xiii) Changes to the wing or to fixed or 

movable control surfaces which affect flutter 
and vibration characteristics. 

(2) 

Powerplant major alterations. The fol-

lowing alterations of a powerplant when not 
listed in the engine specifications issued by 
the FAA, are powerplant major alterations. 

(i) Conversion of an aircraft engine from 

one approved model to another, involving 
any changes in compression ratio, propeller 
reduction gear, impeller gear ratios or the 
substitution of major engine parts which re-
quires extensive rework and testing of the 
engine. 

(ii) Changes to the engine by replacing air-

craft engine structural parts with parts not 
supplied by the original manufacturer or 
parts not specifically approved by the Ad-
ministrator. 

(iii) Installation of an accessory which is 

not approved for the engine. 

(iv) Removal of accessories that are listed 

as required equipment on the aircraft or en-
gine specification. 

(v) Installation of structural parts other 

than the type of parts approved for the in-
stallation. 

(vi) Conversions of any sort for the purpose 

of using fuel of a rating or grade other than 
that listed in the engine specifications. 

(3) 

Propeller major alterations. The following 

alterations of a propeller when not author-
ized in the propeller specifications issued by 
the FAA are propeller major alterations: 

(i) Changes in blade design. 
(ii) Changes in hub design. 
(iii) Changes in the governor or control de-

sign. 

(iv) Installation of a propeller governor or 

feathering system. 

(v) Installation of propeller de-icing sys-

tem. 

(vi) Installation of parts not approved for 

the propeller. 

(4) 

Appliance major alterations. Alterations 

of the basic design not made in accordance 
with recommendations of the appliance man-
ufacturer or in accordance with an FAA Air-
worthiness Directive are appliance major al-
terations. In addition, changes in the basic 
design of radio communication and naviga-
tion equipment approved under type certifi-
cation or a Technical Standard Order that 

have an effect on frequency stability, noise 
level, sensitivity, selectivity, distortion, 
spurious radiation, AVC characteristics, or 
ability to meet environmental test condi-
tions and other changes that have an effect 
on the performance of the equipment are 
also major alterations. 

(b) 

Major repairs—(1) Airframe major repairs. 

Repairs to the following parts of an airframe 
and repairs of the following types, involving 
the strengthening, reinforcing, splicing, and 
manufacturing of primary structural mem-
bers or their replacement, when replacement 
is by fabrication such as riveting or welding, 
are airframe major repairs. 

(i) Box beams. 
(ii) Monocoque or semimonocoque wings or 

control surfaces. 

(iii) Wing stringers or chord members. 
(iv) Spars. 
(v) Spar flanges. 
(vi) Members of truss-type beams. 
(vii) Thin sheet webs of beams. 
(viii) Keel and chine members of boat hulls 

or floats. 

(ix) Corrugated sheet compression mem-

bers which act as flange material of wings or 
tail surfaces. 

(x) Wing main ribs and compression mem-

bers. 

(xi) Wing or tail surface brace struts. 
(xii) Engine mounts. 
(xiii) Fuselage longerons. 
(xiv) Members of the side truss, horizontal 

truss, or bulkheads. 

(xv) Main seat support braces and brack-

ets. 

(xvi) Landing gear brace struts. 
(xvii) Axles. 
(xviii) Wheels. 
(xix) Skis, and ski pedestals. 
(xx) Parts of the control system such as 

control columns, pedals, shafts, brackets, or 
horns. 

(xxi) Repairs involving the substitution of 

material. 

(xxii) The repair of damaged areas in metal 

or plywood stressed covering exceeding six 
inches in any direction. 

(xxiii) The repair of portions of skin sheets 

by making additional seams. 

(xxiv) The splicing of skin sheets. 
(xxv) The repair of three or more adjacent 

wing or control surface ribs or the leading 
edge of wings and control surfaces, between 
such adjacent ribs. 

(xxvi) Repair of fabric covering involving 

an area greater than that required to repair 
two adjacent ribs. 

(xxvii) Replacement of fabric on fabric cov-

ered parts such as wings, fuselages, stabi-
lizers, and control surfaces. 

(xxviii) Repairing, including rebottoming, 

of removable or integral fuel tanks and oil 
tanks. 

(2) 

Powerplant major repairs. Repairs of the 

following parts of an engine and repairs of 

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the following types, are powerplant major re-
pairs: 

(i) Separation or disassembly of a crank-

case or crankshaft of a reciprocating engine 
equipped with an integral supercharger. 

(ii) Separation or disassembly of a crank-

case or crankshaft of a reciprocating engine 
equipped with other than spur-type propeller 
reduction gearing. 

(iii) Special repairs to structural engine 

parts by welding, plating, metalizing, or 
other methods. 

(3) 

Propeller major repairs. Repairs of the 

following types to a propeller are propeller 
major repairs: 

(i) Any repairs to, or straightening of steel 

blades. 

(ii) Repairing or machining of steel hubs. 
(iii) Shortening of blades. 
(iv) Retipping of wood propellers. 
(v) Replacement of outer laminations on 

fixed pitch wood propellers. 

(vi) Repairing elongated bolt holes in the 

hub of fixed pitch wood propellers. 

(vii) Inlay work on wood blades. 
(viii) Repairs to composition blades. 
(ix) Replacement of tip fabric. 
(x) Replacement of plastic covering. 
(xi) Repair of propeller governors. 
(xii) Overhaul of controllable pitch propel-

lers. 

(xiii) Repairs to deep dents, cuts, scars, 

nicks, etc., and straightening of aluminum 
blades. 

(xiv) The repair or replacement of internal 

elements of blades. 

(4) 

Appliance major repairs. Repairs of the 

following types to appliances are appliance 
major repairs: 

(i) Calibration and repair of instruments. 
(ii) Calibration of radio equipment. 
(iii) Rewinding the field coil of an elec-

trical accessory. 

(iv) Complete disassembly of complex hy-

draulic power valves. 

(v) Overhaul of pressure type carburetors, 

and pressure type fuel, oil and hydraulic 
pumps. 

(c) 

Preventive maintenance. Preventive 

maintenance is limited to the following 
work, provided it does not involve complex 
assembly operations: 

(1) Removal, installation, and repair of 

landing gear tires. 

(2) Replacing elastic shock absorber cords 

on landing gear. 

(3) Servicing landing gear shock struts by 

adding oil, air, or both. 

(4) Servicing landing gear wheel bearings, 

such as cleaning and greasing. 

(5) Replacing defective safety wiring or 

cotter keys. 

(6) Lubrication not requiring disassembly 

other than removal of nonstructural items 
such as cover plates, cowlings, and fairings. 

(7) Making simple fabric patches not re-

quiring rib stitching or the removal of struc-

tural parts or control surfaces. In the case of 
balloons, the making of small fabric repairs 
to envelopes (as defined in, and in accord-
ance with, the balloon manufacturers’ in-
structions) not requiring load tape repair or 
replacement. 

(8) Replenishing hydraulic fluid in the hy-

draulic reservoir. 

(9) Refinishing decorative coating of fuse-

lage, balloon baskets, wings tail group sur-
faces (excluding balanced control surfaces), 
fairings, cowlings, landing gear, cabin, or 
cockpit interior when removal or dis-
assembly of any primary structure or oper-
ating system is not required. 

(10) Applying preservative or protective 

material to components where no dis-
assembly of any primary structure or oper-
ating system is involved and where such 
coating is not prohibited or is not contrary 
to good practices. 

(11) Repairing upholstery and decorative 

furnishings of the cabin, cockpit, or balloon 
basket interior when the repairing does not 
require disassembly of any primary struc-
ture or operating system or interfere with an 
operating system or affect the primary 
structure of the aircraft. 

(12) Making small simple repairs to fair-

ings, nonstructural cover plates, cowlings, 
and small patches and reinforcements not 
changing the contour so as to interfere with 
proper air flow. 

(13) Replacing side windows where that 

work does not interfere with the structure or 
any operating system such as controls, elec-
trical equipment, etc. 

(14) Replacing safety belts. 
(15) Replacing seats or seat parts with re-

placement parts approved for the aircraft, 
not involving disassembly of any primary 
structure or operating system. 

(16) Trouble shooting and repairing broken 

circuits in landing light wiring circuits. 

(17) Replacing bulbs, reflectors, and lenses 

of position and landing lights. 

(18) Replacing wheels and skis where no 

weight and balance computation is involved. 

(19) Replacing any cowling not requiring 

removal of the propeller or disconnection of 
flight controls. 

(20) Replacing or cleaning spark plugs and 

setting of spark plug gap clearance. 

(21) Replacing any hose connection except 

hydraulic connections. 

(22) Replacing prefabricated fuel lines. 
(23) Cleaning or replacing fuel and oil 

strainers or filter elements. 

(24) Replacing and servicing batteries. 
(25) Cleaning of balloon burner pilot and 

main nozzles in accordance with the balloon 
manufacturer’s instructions. 

(26) Replacement or adjustment of non-

structural standard fasteners incidental to 
operations. 

(27) The interchange of balloon baskets and 

burners on envelopes when the basket or 

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burner is designated as interchangeable in 
the balloon type certificate data and the bas-
kets and burners are specifically designed for 
quick removal and installation. 

(28) The installations of anti-misfueling de-

vices to reduce the diameter of fuel tank 
filler openings provided the specific device 
has been made a part of the aircraft type 
certificiate data by the aircraft manufac-
turer, the aircraft manufacturer has pro-
vided FAA-approved instructions for instal-
lation of the specific device, and installation 
does not involve the disassembly of the ex-
isting tank filler opening. 

(29) Removing, checking, and replacing 

magnetic chip detectors. 

(30) The inspection and maintenance tasks 

prescribed and specifically identified as pre-
ventive maintenance in a primary category 
aircraft type certificate or supplemental 
type certificate holder’s approved special in-
spection and preventive maintenance pro-
gram when accomplished on a primary cat-
egory aircraft provided: 

(i) They are performed by the holder of at 

least a private pilot certificate issued under 
part 61 of this chapter who is the registered 
owner (including co-owners) of the affected 
aircraft and who holds a certificate of com-
petency for the affected aircraft (1) issued by 
the holder of the production certificate for 
that primary category aircraft that has a 
special training program approved under 
§ 21.24 of this subchapter; or (2) issued by an-
other entity that has a course approved by 
the Administrator; and 

(ii) The inspections and maintenance tasks 

are performed in accordance with instruc-
tions contained by the special inspection and 
preventive maintenance program approved 
as part of the aircraft’s type design or sup-
plemental type design. 

(31) Removing and replacing self-con-

tained, front instrument panel-mounted 
navigation and communication devices that 
employ tray-mounted connectors that con-
nect the unit when the unit is installed into 
the instrument panel, (excluding automatic 
flight control systems, transponders, and 
microwave frequency distance measuring 
equipment (DME)). The approved unit must 
be designed to be readily and repeatedly re-
moved and replaced, and pertinent instruc-
tions must be provided. Prior to the unit’s 
intended use, and operational check must be 

performed in accordance with the applicable 
sections of part 91 of this chapter. 

(Secs. 313, 601 through 610, and 1102, Federal 
Aviation Act of 1958 as amended (49 U.S.C. 
1354, 1421 through 1430 and 1502); (49 U.S.C. 
106(g) (Revised Pub. L. 97–449, Jan. 21, 1983); 
and 14 CFR 11.45) 

[Doc. No. 1993, 29 FR 5451, Apr. 23, 1964, as 
amended by Amdt. 43–14, 37 FR 14291, June 
19, 1972; Amdt. 43–23, 47 FR 41086, Sept. 16, 
1982; Amdt. 43–24, 49 FR 44602, Nov. 7, 1984; 
Amdt. 43–25, 51 FR 40703, Nov. 7, 1986; Amdt. 
43–27, 52 FR 17277, May 6, 1987; Amdt. 43–34, 57 
FR 41369, Sept. 9, 1992; Amdt. 43–36, 61 FR 
19501, May 1, 1996; Amdt. 43–45, 77 FR 71096, 
Nov. 29, 2012; Docket No. FAA–2021–0237, 
Amdt. No. 43–52, 87 FR 31414, May 24, 2022] 

A

PPENDIX

B 

TO

P

ART

43—R

ECORDING OF

 

M

AJOR

R

EPAIRS AND

M

AJOR

A

LTER

-

ATIONS

 

(a) Except as provided in paragraphs (b), 

(c), and (d) of this appendix, each person per-
forming a major repair or major alteration 
shall— 

(1) Execute FAA Form 337 at least in dupli-

cate; 

(2) Give a signed copy of that form to the 

aircraft owner; and 

(3) Forward a copy of that form to the FAA 

Aircraft Registration Branch in Oklahoma 
City, Oklahoma, within 48 hours after the 
aircraft, airframe, aircraft engine, propeller, 
or appliance is approved for return to serv-
ice. 

(b) For major repairs made in accordance 

with a manual or specifications acceptable 
to the Administrator, a certificated repair 
station may, in place of the requirements of 
paragraph (a)— 

(1) Use the customer’s work order upon 

which the repair is recorded; 

(2) Give the aircraft owner a signed copy of 

the work order and retain a duplicate copy 
for at least two years from the date of ap-
proval for return to service of the aircraft, 
airframe, aircraft engine, propeller, or appli-
ance; 

(3) Give the aircraft owner a maintenance 

release signed by an authorized representa-
tive of the repair station and incorporating 
the following information: 

(i) Identity of the aircraft, airframe, air-

craft engine, propeller or appliance. 

(ii) If an aircraft, the make, model, serial 

number, nationality and registration marks, 
and location of the repaired area. 

(iii) If an airframe, aircraft engine, pro-

peller, or appliance, give the manufacturer’s 
name, name of the part, model, and serial 
numbers (if any); and 

(4) Include the following or a similarly 

worded statement— 

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14 CFR Ch. I (1–1–24 Edition) 

Pt. 43, App. D 

‘‘The aircraft, airframe, aircraft engine, 

propeller, or appliance identified above was 
repaired and inspected in accordance with 
current Regulations of the Federal Aviation 
Agency and is approved for return to service. 

Pertinent details of the repair are on file 

at this repair station under Order No. 

___

, 

Date 

lllllllllllllllllllll

Signed 

llllllllllllllllllll

For signature of authorized representative) 

Repair station name)

(Certificate No.) 

____________

.’’ 

(Address) 

(c) Except as provided in paragraph (d) of 

this appendix, for a major repair or major al-
teration made by a person authorized in 
§ 43.17, the person who performs the major re-
pair or major alteration and the person au-
thorized by § 43.17 to approve that work shall 
execute an FAA Form 337 at least in dupli-
cate. A completed copy of that form shall 
be— 

(1) Given to the aircraft owner; and 
(2) Forwarded to the Federal Aviation Ad-

ministration, Aircraft Registration Branch, 
Post Office Box 25504, Oklahoma City, OK 
73125, within 48 hours after the work is in-
spected. 

(d) For extended-range fuel tanks installed 

within the passenger compartment or a bag-
gage compartment, the person who performs 
the work and the person authorized to ap-
prove the work by § 43.7 shall execute an FAA 
Form 337 in at least triplicate. A completed 
copy of that form shall be— 

(1) Placed on board the aircraft as specified 

in § 91.417 of this chapter; 

(2) Given to the aircraft owner; and 
(3) Forwarded to the Federal Aviation Ad-

ministration, Aircraft Registration Branch, , 
Post Office Box 25724, Oklahoma City, OK 
73125, within 48 hours after the work is in-
spected. 

(Secs. 101, 610, 72 Stat. 737, 780, 49 U.S.C. 1301, 
1430) 

[Doc. No. 1993, 29 FR 5451, Apr. 23, 1964, as 
amended by Amdt. 43–10, 33 FR 15989, Oct. 31, 
1968; Amdt. 43–29, 52 FR 34101, Sept. 9, 1987; 
Amdt. 43–31, 54 FR 34330, Aug. 18, 1989; 71 FR 
58495, Oct. 4, 2006; Amdt. 43–41, 72 FR 53680, 
Sept. 20, 2007; Doc. No. FAA–2018–0119, Amdt. 
43–50, 83 FR 9170, Mar. 5, 2018] 

A

PPENDIX

C 

TO

P

ART

43 [R

ESERVED

] 

A

PPENDIX

D 

TO

P

ART

43—S

COPE AND

D

E

-

TAIL OF

I

TEMS

(

AS

A

PPLICABLE TO

 

THE

P

ARTICULAR

A

IRCRAFT

) T

O

B

E

 

I

NCLUDED IN

A

NNUAL AND

100-H

OUR

 

I

NSPECTIONS

 

(a) Each person performing an annual or 

100-hour inspection shall, before that inspec-
tion, remove or open all necessary inspection 

plates, access doors, fairing, and cowling. He 
shall thoroughly clean the aircraft and air-
craft engine. 

(b) Each person performing an annual or 

100-hour inspection shall inspect (where ap-
plicable) the following components of the fu-
selage and hull group: 

(1) Fabric and skin—for deterioration, dis-

tortion, other evidence of failure, and defec-
tive or insecure attachment of fittings. 

(2) Systems and components—for improper 

installation, apparent defects, and unsatis-
factory operation. 

(3) Envelope, gas bags, ballast tanks, and 

related parts—for poor condition. 

(c) Each person performing an annual or 

100-hour inspection shall inspect (where ap-
plicable) the following components of the 
cabin and cockpit group: 

(1) Generally—for uncleanliness and loose 

equipment that might foul the controls. 

(2) Seats and safety belts—for poor condi-

tion and apparent defects. 

(3) Windows and windshields—for deterio-

ration and breakage. 

(4) Instruments—for poor condition, 

mounting, marking, and (where practicable) 
improper operation. 

(5) Flight and engine controls—for im-

proper installation and improper operation. 

(6) Batteries—for improper installation and 

improper charge. 

(7) All systems—for improper installation, 

poor general condition, apparent and obvious 
defects, and insecurity of attachment. 

(d) Each person performing an annual or 

100-hour inspection shall inspect (where ap-
plicable) components of the engine and na-
celle group as follows: 

(1) Engine section—for visual evidence of 

excessive oil, fuel, or hydraulic leaks, and 
sources of such leaks. 

(2) Studs and nuts—for improper torquing 

and obvious defects. 

(3) Internal engine—for cylinder compres-

sion and for metal particles or foreign mat-
ter on screens and sump drain plugs. If there 
is weak cylinder compression, for improper 
internal condition and improper internal tol-
erances. 

(4) Engine mount—for cracks, looseness of 

mounting, and looseness of engine to mount. 

(5) Flexible vibration dampeners—for poor 

condition and deterioration. 

(6) Engine controls—for defects, improper 

travel, and improper safetying. 

(7) Lines, hoses, and clamps—for leaks, im-

proper condition and looseness. 

(8) Exhaust stacks—for cracks, defects, and 

improper attachment. 

(9) Accessories—for apparent defects in se-

curity of mounting. 

(10) All systems—for improper installation, 

poor general condition, defects, and insecure 
attachment. 

(11) Cowling—for cracks, and defects. 

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Federal Aviation Administration, DOT 

Pt. 43, App. E 

(e) Each person performing an annual or 

100-hour inspection shall inspect (where ap-
plicable) the following components of the 
landing gear group: 

(1) All units—for poor condition and inse-

curity of attachment. 

(2) Shock absorbing devices—for improper 

oleo fluid level. 

(3) Linkages, trusses, and members—for 

undue or excessive wear fatigue, and distor-
tion. 

(4) Retracting and locking mechanism—for 

improper operation. 

(5) Hydraulic lines—for leakage. 
(6) Electrical system—for chafing and im-

proper operation of switches. 

(7) Wheels—for cracks, defects, and condi-

tion of bearings. 

(8) Tires—for wear and cuts. 
(9) Brakes—for improper adjustment. 
(10) Floats and skis—for insecure attach-

ment and obvious or apparent defects. 

(f) Each person performing an annual or 

100-hour inspection shall inspect (where ap-
plicable) all components of the wing and cen-
ter section assembly for poor general condi-
tion, fabric or skin deterioration, distortion, 
evidence of failure, and insecurity of attach-
ment. 

(g) Each person performing an annual or 

100-hour inspection shall inspect (where ap-
plicable) all components and systems that 
make up the complete empennage assembly 
for poor general condition, fabric or skin de-
terioration, distortion, evidence of failure, 
insecure attachment, improper component 
installation, and improper component oper-
ation. 

(h) Each person performing an annual or 

100-hour inspection shall inspect (where ap-
plicable) the following components of the 
propeller group: 

(1) Propeller assembly—for cracks, nicks, 

binds, and oil leakage. 

(2) Bolts—for improper torquing and lack 

of safetying. 

(3) Anti-icing devices—for improper oper-

ations and obvious defects. 

(4) Control mechanisms—for improper op-

eration, insecure mounting, and restricted 
travel. 

(i) Each person performing an annual or 

100-hour inspection shall inspect (where ap-
plicable) the following components of the 
radio group: 

(1) Radio and electronic equipment—for 

improper installation and insecure mount-
ing. 

(2) Wiring and conduits—for improper rout-

ing, insecure mounting, and obvious defects. 

(3) Bonding and shielding—for improper in-

stallation and poor condition. 

(4) Antenna including trailing antenna—for 

poor condition, insecure mounting, and im-
proper operation. 

(j) Each person performing an annual or 

100-hour inspection shall inspect (where ap-

plicable) each installed miscellaneous item 
that is not otherwise covered by this listing 
for improper installation and improper oper-
ation. 

A

PPENDIX

E 

TO

P

ART

43—A

LTIMETER

 

S

YSTEM

T

EST AND

I

NSPECTION

 

Each person performing the altimeter sys-

tem tests and inspections required by § 91.411 
of this chapter must comply with the fol-
lowing: 

(a) Static pressure system: 
(1) Ensure freedom from entrapped mois-

ture and restrictions. 

(2) Perform a proof test to demonstrate the 

integrity of the static pressure system in a 
manner acceptable to the Administrator. For 
airplanes certificated under part 25 of this 
chapter, determine that leakage is within 
the tolerances established by § 25.1325. 

(3) Determine that the static port heater, 

if installed, is operative. 

(4) Ensure that no alterations or deforma-

tions of the airframe surface have been made 
that would affect the relationship between 
air pressure in the static pressure system 
and true ambient static air pressure for any 
flight condition. 

(b) Altimeter: 
(1) Test by an appropriately rated repair 

facility in accordance with the following 
subparagraphs. Unless otherwise specified, 
each test for performance may be conducted 
with the instrument subjected to vibration. 
When tests are conducted with the tempera-
ture substantially different from ambient 
temperature of approximately 25 degrees C., 
allowance shall be made for the variation 
from the specified condition. 

(i) 

Scale error. With the barometric pres-

sure scale at 29.92 inches of mercury, the al-
timeter shall be subjected successively to 
pressures corresponding to the altitude spec-
ified in Table I up to the maximum normally 
expected operating altitude of the airplane 
in which the altimeter is to be installed. The 
reduction in pressure shall be made at a rate 
not in excess of 20,000 feet per minute to 
within approximately 2,000 feet of the test 
point. The test point shall be approached at 
a rate compatible with the test equipment. 
The altimeter shall be kept at the pressure 
corresponding to each test point for at least 
1 minute, but not more than 10 minutes, be-
fore a reading is taken. The error at all test 
points must not exceed the tolerances speci-
fied in Table I. 

(ii) 

Hysteresis.  The hysteresis test shall 

begin not more than 15 minutes after the al-
timeter’s initial exposure to the pressure 
corresponding to the upper limit of the scale 
error test prescribed in subparagraph (i); and 
while the altimeter is at this pressure, the 
hysteresis test shall commence. Pressure 
shall be increased at a rate simulating a de-
scent in altitude at the rate of 5,000 to 20,000 

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14 CFR Ch. I (1–1–24 Edition) 

Pt. 43, App. E 

feet per minute until within 3,000 feet of the 
first test point (50 percent of maximum alti-
tude). The test point shall then be ap-
proached at a rate of approximately 3,000 
feet per minute. The altimeter shall be kept 
at this pressure for at least 5 minutes, but 
not more than 15 minutes, before the test 
reading is taken. After the reading has been 
taken, the pressure shall be increased fur-
ther, in the same manner as before, until the 
pressure corresponding to the second test 
point (40 percent of maximum altitude) is 
reached. The altimeter shall be kept at this 
pressure for at least 1 minute, but not more 
than 10 minutes, before the test reading is 
taken. After the reading has been taken, the 
pressure shall be increased further, in the 
same manner as before, until atmospheric 
pressure is reached. The reading of the al-
timeter at either of the two test points shall 
not differ by more than the tolerance speci-
fied in Table II from the reading of the al-
timeter for the corresponding altitude re-
corded during the scale error test prescribed 
in paragraph (b)(i). 

(iii) 

After effect. Not more than 5 minutes 

after the completion of the hysteresis test 
prescribed in paragraph (b)(ii), the reading of 
the altimeter (corrected for any change in 
atmospheric pressure) shall not differ from 
the original atmospheric pressure reading by 
more than the tolerance specified in Table 
II. 

(iv) 

Friction.  The altimeter shall be sub-

jected to a steady rate of decrease of pres-
sure approximating 750 feet per minute. At 
each altitude listed in Table III, the change 
in reading of the pointers after vibration 
shall not exceed the corresponding tolerance 
listed in Table III. 

(v) 

Case leak. The leakage of the altimeter 

case, when the pressure within it cor-
responds to an altitude of 18,000 feet, shall 
not change the altimeter reading by more 
than the tolerance shown in Table II during 
an interval of 1 minute. 

(vi) 

Barometric scale error. At constant at-

mospheric pressure, the barometric pressure 
scale shall be set at each of the pressures 
(falling within its range of adjustment) that 
are listed in Table IV, and shall cause the 
pointer to indicate the equivalent altitude 
difference shown in Table IV with a toler-
ance of 25 feet. 

(2) Altimeters which are the air data com-

puter type with associated computing sys-
tems, or which incorporate air data correc-
tion internally, may be tested in a manner 
and to specifications developed by the manu-
facturer which are acceptable to the Admin-
istrator. 

(c) Automatic Pressure Altitude Reporting 

Equipment and ATC Transponder System In-
tegration Test. The test must be conducted 
by an appropriately rated person under the 
conditions specified in paragraph (a). Meas-
ure the automatic pressure altitude at the 

output of the installed ATC transponder 
when interrogated on Mode C at a sufficient 
number of test points to ensure that the alti-
tude reporting equipment, altimeters, and 
ATC transponders perform their intended 
functions as installed in the aircraft. The 
difference between the automatic reporting 
output and the altitude displayed at the al-
timeter shall not exceed 125 feet. 

(d) Records: Comply with the provisions of 

§ 43.9 of this chapter as to content, form, and 
disposition of the records. The person per-
forming the altimeter tests shall record on 
the altimeter the date and maximum alti-
tude to which the altimeter has been tested 
and the persons approving the airplane for 
return to service shall enter that data in the 
airplane log or other permanent record. 

T

ABLE

I 

Altitude 

Equivalent 

pressure 

(inches of 

mercury) 

Tolerance 

±

(feet) 

¥

1,000 ..........................................

31.018 20 

0 .....................................................

29.921 20 

500 .................................................

29.385 20 

1,000 ..............................................

28.856 20 

1,500 ..............................................

28.335 25 

2,000 ..............................................

27.821 30 

3,000 ..............................................

26.817 30 

4,000 ..............................................

25.842 35 

6,000 ..............................................

23.978 40 

8,000 ..............................................

22.225 60 

10,000 ............................................

20.577 80 

12,000 ............................................

19.029 90 

14,000 ............................................

17.577 100 

16,000 ............................................

16.216 110 

18,000 ............................................

14.942 120 

20,000 ............................................

13.750 130 

22,000 ............................................

12.636 140 

25,000 ............................................

11.104 155 

30,000 ............................................

8.885 180 

35,000 ............................................

7.041 205 

40,000 ............................................

5.538 230 

45,000 ............................................

4.355 255 

50,000 ............................................

3.425 280 

T

ABLE

II—T

EST

T

OLERANCES

 

Test 

Tolerance 

(feet) 

Case Leak Test ...............................................

±

100 

Hysteresis Test: 

First Test Point (50 percent of maximum 

altitude) .................................................

75 

Second Test Point (40 percent of max-

imum altitude) .......................................

75 

After Effect Test ...............................................

30 

T

ABLE

III—F

RICTION

 

Altitude (feet) 

Tolerance 

(feet) 

1,000 ....................................................................

±

70 

2,000 ....................................................................

70 

3,000 ....................................................................

70 

5,000 ....................................................................

70 

10,000 ..................................................................

80 

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Federal Aviation Administration, DOT 

Pt. 43, App. F 

T

ABLE

III—F

RICTION

—Continued 

Altitude (feet) 

Tolerance 

(feet) 

15,000 ..................................................................

90 

20,000 ..................................................................

100 

25,000 ..................................................................

120 

30,000 ..................................................................

140 

35,000 ..................................................................

160 

40,000 ..................................................................

180 

50,000 ..................................................................

250 

T

ABLE

IV—P

RESSURE

-A

LTITUDE

D

IFFERENCE

 

Pressure (inches of Hg) 

Altitude dif-

ference 

(feet) 

28.10 ....................................................................

¥

1,727 

28.50 ....................................................................

¥

1,340 

29.00 ....................................................................

¥

863 

29.50 ....................................................................

¥

392 

29.92 ....................................................................

0 

30.50 ....................................................................

+ 531 

30.90 ....................................................................

+ 893 

30.99 ....................................................................

+ 974 

(Secs. 313, 314, and 601 through 610 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354, 1355, 
and 1421 through 1430) and sec. 6(c), Dept. of 
Transportation Act (49 U.S.C. 1655(c))) 

[Amdt. 43–2, 30 FR 8262, June 29, 1965, as 
amended by Amdt. 43–7, 32 FR 7587, May 24, 
1967; Amdt. 43–19, 43 FR 22639, May 25, 1978; 
Amdt. 43–23, 47 FR 41086, Sept. 16, 1982; Amdt. 
43–31, 54 FR 34330, Aug. 18, 1989; Doc. No. 
FAA–2015–1621, Amdt. 43–49, 81 FR 96700, Dec. 
30, 2016] 

A

PPENDIX

F 

TO

P

ART

43—ATC 

T

RANSPONDER

T

ESTS AND

I

NSPECTIONS

 

The ATC transponder tests required by 

§ 91.413 of this chapter may be conducted 
using a bench check or portable test equip-
ment and must meet the requirements pre-
scribed in paragraphs (a) through (j) of this 
appendix. If portable test equipment with ap-
propriate coupling to the aircraft antenna 
system is used, operate the test equipment 
for ATCRBS transponders at a nominal rate 
of 235 interrogations per second to avoid pos-
sible ATCRBS interference. Operate the test 
equipment at a nominal rate of 50 Mode S in-
terrogations per second for Mode S. An addi-
tional 3 dB loss is allowed to compensate for 
antenna coupling errors during receiver sen-
sitivity measurements conducted in accord-
ance with paragraph (c)(1) when using port-
able test equipment. 

(a) Radio Reply Frequency: 
(1) For all classes of ATCRBS tran-

sponders, interrogate the transponder and 
verify that the reply frequency is 1090 

±

3 

Megahertz (MHz). 

(2) For classes 1B, 2B, and 3B Mode S tran-

sponders, interrogate the transponder and 

verify that the reply frequency is 1090 

±

3 

MHz. 

(3) For classes 1B, 2B, and 3B Mode S tran-

sponders that incorporate the optional 1090 

±

1 MHz reply frequency, interrogate the 

transponder and verify that the reply fre-
quency is correct. 

(4) For classes 1A, 2A, 3A, and 4 Mode S 

transponders, interrogate the transponder 
and verify that the reply frequency is 1090 

±

1 

MHz. 

(b) Suppression: When Classes 1B and 2B 

ATCRBS Transponders, or Classes 1B, 2B, 
and 3B Mode S transponders are interrogated 
Mode 3/A at an interrogation rate between 
230 and 1,000 interrogations per second; or 
when Classes 1A and 2A ATCRBS Tran-
sponders, or Classes 1B, 2A, 3A, and 4 Mode S 
transponders are interrogated at a rate be-
tween 230 and 1,200 Mode 3/A interrogations 
per second: 

(1) Verify that the transponder does not re-

spond to more than 1 percent of ATCRBS in-
terrogations when the amplitude of P

2

pulse 

is equal to the P

1

pulse. 

(2) Verify that the transponder replies to 

at least 90 percent of ATCRBS interrogations 
when the amplitude of the P

2

pulse is 9 dB 

less than the P

1

pulse. If the test is con-

ducted with a radiated test signal, the inter-
rogation rate shall be 235 

±

5 interrogations 

per second unless a higher rate has been ap-
proved for the test equipment used at that 
location. 

(c) Receiver Sensitivity: 
(1) Verify that for any class of ATCRBS 

Transponder, the receiver minimum trig-
gering level (MTL) of the system is 

¥

73 

±

4 

dbm, or that for any class of Mode S trans-
ponder the receiver MTL for Mode S format 
(P6 type) interrogations is 

¥

74 

±

3 dbm by use 

of a test set either: 

(i) Connected to the antenna end of the 

transmission line; 

(ii) Connected to the antenna terminal of 

the transponder with a correction for trans-
mission line loss; or 

(iii) Utilized radiated signal. 
(2) Verify that the difference in Mode 3/A 

and Mode C receiver sensitivity does not ex-
ceed 1 db for either any class of ATCRBS 
transponder or any class of Mode S trans-
ponder. 

(d) Radio Frequency (RF) Peak Output 

Power: 

(1) Verify that the transponder RF output 

power is within specifications for the class of 
transponder. Use the same conditions as de-
scribed in (c)(1)(i), (ii), and (iii) above. 

(i) For Class 1A and 2A ATCRBS tran-

sponders, verify that the minimum RF peak 
output power is at least 21.0 dbw (125 watts). 

(ii) For Class 1B and 2B ATCRBS Tran-

sponders, verify that the minimum RF peak 
output power is at least 18.5 dbw (70 watts). 

(iii) For Class 1A, 2A, 3A, and 4 and those 

Class 1B, 2B, and 3B Mode S transponders 

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862 

14 CFR Ch. I (1–1–24 Edition) 

Pt. 45 

that include the optional high RF peak out-
put power, verify that the minimum RF peak 
output power is at least 21.0 dbw (125 watts). 

(iv) For Classes 1B, 2B, and 3B Mode S 

transponders, verify that the minimum RF 
peak output power is at least 18.5 dbw (70 
watts). 

(v) For any class of ATCRBS or any class 

of Mode S transponders, verify that the max-
imum RF peak output power does not exceed 
27.0 dbw (500 watts). 

N

OTE

: The tests in (e) through (j) apply 

only to Mode S transponders. 

(e) Mode S Diversity Transmission Channel 

Isolation: For any class of Mode S trans-
ponder that incorporates diversity operation, 
verify that the RF peak output power trans-
mitted from the selected antenna exceeds 
the power transmitted from the nonselected 
antenna by at least 20 db. 

(f) Mode S Address: Interrogate the Mode S 

transponder and verify that it replies only to 
its assigned address. Use the correct address 
and at least two incorrect addresses. The in-
terrogations should be made at a nominal 
rate of 50 interrogations per second. 

(g) Mode S Formats: Interrogate the Mode 

S transponder with uplink formats (UF) for 
which it is equipped and verify that the re-
plies are made in the correct format. Use the 
surveillance formats UF = 4 and 5. Verify 
that the altitude reported in the replies to 
UF = 4 are the same as that reported in a 
valid ATCRBS Mode C reply. Verify that the 
identity reported in the replies to UF = 5 are 
the same as that reported in a valid ATCRBS 
Mode 3/A reply. If the transponder is so 
equipped, use the communication formats 
UF = 20, 21, and 24. 

(h) Mode S All-Call Interrogations: Inter-

rogate the Mode S transponder with the 
Mode S-only all-call format UF = 11 and 
verify that the correct address and capa-
bility are reported in the replies (downlink 
format DF = 11). 

(i) ATCRBS-Only All-Call Interrogation: 

Interrogate the Mode S transponder with the 
ATCRBS-only all-call interrogation (0.8 
microsecond P

4

pulse) and verify that no 

reply is generated. 

(j) Squitter: Verify that the Mode S trans-

ponder generates a correct acquisition 
squitter approximately once per second. 

(k) Records: Comply with the provisions of 

§ 43.9 of this chapter as to content, form, and 
disposition of the records. 

[Amdt. 43–26, 52 FR 3390, Feb. 3, 1987; 52 FR 
6651, Mar. 4, 1987, as amended by Amdt. 43–31, 
54 FR 34330, Aug. 18, 1989; Amdt. 43–53, 88 FR 
71476, Oct. 17, 2023] 

PART 45—IDENTIFICATION AND 

REGISTRATION MARKING 

Subpart A—General 

Sec. 
45.1

Applicability. 

Subpart B—Marking of Products and 

Articles 

45.10

Marking. 

45.11

Marking of products. 

45.13

Identification data. 

45.15

Marking requirements for PMA arti-

cles, TSO articles, and Critical parts. 

45.16

Marking of life-limited parts. 

Subpart C—Nationality and Registration 

Marks 

45.21

General. 

45.22

Exhibition, antique, and other air-

craft: Special rules. 

45.23

Display of marks; general. 

45.25

Location of marks on fixed-wing air-

craft. 

45.27

Location of marks; nonfixed-wing air-

craft. 

45.29

Size of marks. 

45.31

Marking of export aircraft. 

45.33

Sale of aircraft; removal of marks. 

A

UTHORITY

: 49 U.S.C. 106(f), 106(g), 40103, 

40113–40114, 44101–44105, 44107–44111, 44504, 
44701, 44708–44709, 44711–44713, 44725, 45302– 
45303, 46104, 46304, 46306, 47122. 

S

OURCE

: Docket No. 2047, 29 FR 3223, Mar. 

11, 1964, unless otherwise noted. 

E

DITORIAL

N

OTE

: Nomenclature changes to 

part 45 appear at 74 FR 53394, Oct. 16, 2009. 

Subpart A—General 

§ 45.1

Applicability. 

This part prescribes the requirements 

for— 

(a) Marking products and articles 

manufactured under— 

(1) A type certificate; 
(2) A production approval as defined 

under part 21 of this chapter; and 

(3) The provisions of an agreement 

between the United States and another 
country or jurisdiction for the accept-
ance of products and articles; and 

(b) Nationality and registration 

marking of aircraft registered in the 

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jspears on DSK121TN23PROD with CFR