This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents.

Rules and Regulations Federal Register

49903 

Vol. 86, No. 170 

Tuesday, September 7, 2021 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0334; Project 

Identifier MCAI–2020–01662–T; Amendment 

39–21686; AD 2021–17–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that was 

published in the Federal Register. That 

AD applies to certain Airbus SAS Model 

A318–111, –112, and –122 airplanes; 

Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes; 

and Model A320–211, –212, –214, –231, 

–232, and –233 airplanes. As published, 

the AD number specified in the 

preamble and regulatory text is 

incorrect. This document corrects this 

error. In all other respects, the original 

document remains the same. 

DATES: This correction is effective 

October 5, 2021. 

The effective date of AD 2021–17–03 

remains October 5, 2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 5, 2021 (86 FR 48485, 

August 31, 2021). 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 

8999 000; email ADs@easa.europa.eu; 

internet www.easa.europa.eu. You may 

find this IBR material on the EASA 

website at https://ad.easa.europa.eu. 

You may view this IBR material at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 

216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available in the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0334. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov under 

Docket No. FAA–2021–0334; or in 

person at Docket Operations between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this final rule, any 

comments received, and other 

information. The address for Docket 

Operations is U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3223; email 

Sanjay.Ralhan@faa.gov. 

SUPPLEMENTARY INFORMATION: AD 2021– 

17–03, Amendment 39–21686 (86 FR 

48485, August 31, 2021) (AD 2021–17– 

03), requires repetitive inspections for 

cracking at the left- (LH) and right-hand 

(RH) sides of the fuselage skin at certain 

frames, and repair if necessary, as 

specified in European Union Aviation 

Safety Agency (EASA) AD 2020–0280, 

dated December 14, 2020 (EASA AD 

2020–0280). That AD applies to certain 

Airbus SAS Model A318–111, –112, and 

–122 airplanes; Model A319–111, –112, 

–113, –114, –115, –131, –132, and –133 

airplanes; and Model A320–211, –212, 

–214, –231, –232, and –233 airplanes. 

Need for the Correction 

As the AD was published, the AD 

number specified in the preamble and 

regulatory text is incorrect. AD 2021– 

17–03 incorrectly identified the AD 

number as 2017–17–03. The correct AD 

number for this AD is 2021–17–03. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2020–0280 describes 

procedures for doing repetitive external 

general visual inspections or special 

detailed inspections (i.e., phased array 

ultrasonic technology inspections of the 

external skin, or detailed inspections for 

primer/paint cracks and high frequency 

eddy current inspections of the internal 

skin) and repair for cracking at the LH 

and RH sides of the fuselage skin, above 

stringer 6 from FR35 to FR47. This 

material is reasonably available because 

the interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

Correction of Publication 

This document corrects an error in 

two locations and correctly adds the AD 

as an amendment to 14 CFR 39.13. 

Although no other part of the preamble 

or regulatory information has been 

corrected, the FAA is publishing the 

entire rule in the Federal Register. 

The effective date of this AD remains 

October 5, 2021. 

Since this action only corrects the AD 

number, it has no adverse economic 

impact and imposes no additional 

burden on any person. Therefore, the 

FAA has determined that notice and 

public procedures are unnecessary. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Correction 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration amends part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Corrected] 

■ 2. The FAA corrects § 39.13 by 

correcting the airworthiness directive 

published at 86 FR 48485 (August 31, 

2021) to read: 

2021–17–03 Airbus SAS: Amendment 39– 

21686; Docket No. FAA–2021–0334; 

Project Identifier MCAI–2020–01662–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 5, 2021. 


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49904 Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations 

(b) Affected ADs 

This AD replaces AD 2017–12–13, 

Amendment 39–18928 (82 FR 27983, June 

20, 2017). 

(c) Applicability 

This AD applies to Airbus SAS airplanes 

specified in paragraphs (c)(1) through (3) of 

this AD, certificated in any category, as 

identified in European Union Aviation Safety 

Agency (EASA) AD 2020–0280, dated 

December 14, 2020 (EASA AD 2020–0280). 

(1) Model A318–111, –112, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–211, –212, –214, –231, 

–232, and –233 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of a 

crack found during an inspection of the 

pocket radius of the fuselage frame, and a 

determination that similar cracks may 

develop in nearby areas of the fuselage frame 

and that additional airplanes are subject to 

the unsafe condition. The FAA is issuing this 

AD to address cracking of the pocket radius, 

which could lead to in-flight decompression 

of the airplane and possible injury to the 

passengers. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, EASA AD 2020–0280. 

(h) Exceptions to EASA AD 2020–0280 

(1) Where EASA AD 2020–0280 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where paragraph (9) of EASA AD 2020– 

0280 specifies if any crack is found during 

any inspection to ‘‘contact Airbus for 

approved repair instructions and accomplish 

those instructions accordingly,’’ this AD 

requires if any cracking is found, the cracking 

must be repaired before further flight using 

a method approved by the Manager, Large 

Aircraft Section, International Validation 

Branch, FAA; or EASA; or Airbus SAS’s 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Where paragraph (10) of EASA AD 

2020–0280 specifies credit for actions ‘‘in 

accordance with the instructions of an Airbus 

Repair Design Approval Sheet (RDAS), [and 

to] accomplish the next inspection of each 

repaired area in accordance with the 

instructions of, and within the compliance 

time as specified in, the applicable RDAS,’’ 

this AD requires using ‘‘in accordance with 

repair instructions approved, and within the 

compliance time specified in the repair 

approval, using a method approved by the 

Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature.’’ 

(4) Where paragraph (11) of EASA AD 

2020–0280 specifies terminating actions 

apply only if specified ‘‘in the Airbus RDAS 

instructions for a repaired aeroplane,’’ this 

AD requires using ‘‘in repair instructions 

approved using a method approved by the 

Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature.’’ 

(5) The ‘‘Remarks’’ section of EASA AD 

2020–0280 does not apply to this AD. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2020–0280 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Large Aircraft 

Section, International Validation Branch, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. In accordance with 

14 CFR 39.19, send your request to your 

principal inspector or responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the Large Aircraft 

Section, International Validation Branch, 

send it to the attention of the person 

identified in paragraph (k) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the responsible 

Flight Standards Office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (j)(2) of this AD, if 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(k) Related Information 

For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3223; email Sanjay.Ralhan@

faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on October 5, 2021 (86 FR 

48485, August 31, 2021). 

(i) European Union Aviation Safety Agency 

(EASA) AD 2020–0280, dated December 14, 

2020. 

(ii) [Reserved] 

(4) For EASA AD 2020–0280, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; internet 

www.easa.europa.eu. You may find this 

EASA AD on the EASA website at https://

ad.easa.europa.eu. 

(5) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 216th 

St., Des Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 

(6) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

email fr.inspection@nara.gov, or go to https:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on September 1, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–19245 Filed 9–1–21; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0137; Project 

Identifier MCAI–2020–00269–E; Amendment 

39–21688; AD 2021–17–05] 

RIN 2120–AA64 

Airworthiness Directives; Safran 

Helicopter Engines, S.A. (Type 

Certificate Previously Held by 

Turbomeca S.A.) Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2014–04– 

06 for all Safran Helicopter Engines, 


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