Federal Register / Vol. 86, No. 166 / Tuesday, August 31, 2021 / Rules and Regulations 48485 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO 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 manager of the 

certification office, send it to the attention of 

the person identified in Related Information. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by The Boeing Company 

Organization Designation Authorization 

(ODA) that has been authorized by the 

Manager, Seattle ACO Branch, FAA, to make 

those findings. To be approved, the repair 

method, modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(j) Related Information 

(1) For more information about this AD, 

contact Stefanie Roesli, Aerospace Engineer, 

Airframe Section, FAA, Seattle ACO Branch, 

2200 South 216th St., Des Moines, WA 

98198; phone and fax: 206–231–3964; email: 

Stefanie.N.Roesli@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (k)(3) and (4) of this AD. 

(k) 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 the AD specifies otherwise. 

(i) Boeing Alert Requirements Bulletin 

747–53A2904 RB, dated December 16, 2020. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; internet https://

www.myboeingfleet.com. 

(4) 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. 

(5) 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, 

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

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

Issued on August 7, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–18705 Filed 8–30–21; 8:45 am] 

BILLING CODE 4910–13–P 

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 2017–17–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2017–12– 

13, which applied to certain Airbus SAS 

Model A320–212, –214, –232, and –233 

airplanes. AD 2017–12–13 required 

repetitive low frequency eddy current 

inspections or repetitive high frequency 

eddy current inspections of the pocket 

radius at certain areas of the fuselage 

frame, and repair if necessary. This AD 

requires new repetitive inspections at 

the left- (LH) and right-hand (RH) sides 

of the fuselage skin at certain frames for 

any cracking, and repair if necessary, as 

specified in a European Union Aviation 

Safety Agency (EASA) AD, which is 

incorporated by reference. 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 the 

unsafe condition on these products. 

DATES: This AD is effective 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. 

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 on 

the internet 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 on 

the internet at https://

www.regulations.gov by searching for 

and locating 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: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2020–0280, 

dated December 14, 2020 (EASA AD 

2020–0280) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for 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. 

EASA AD 2020–0280 supersedes EASA 

AD 2014–0278, dated December 19, 

2014 (which corresponds to FAA AD 

2017–12–13, Amendment 39–18928 (82 

FR 27983, June 20, 2017) (AD 2017–12– 

13)). 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2017–12–13. 

AD 2017–12–13 applied to certain 

Airbus SAS Model A320–212, –214, 

–232, and –233 airplanes. The NPRM 

published in the Federal Register on 

April 22, 2021 (86 FR 21228). The 

NPRM 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 


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48486 Federal Register / Vol. 86, No. 166 / Tuesday, August 31, 2021 / Rules and Regulations 

develop in nearby areas of the fuselage 

frame and that additional airplanes are 

subject to the unsafe condition. The 

NPRM proposed to require new 

repetitive inspections at the LH and RH 

sides of the fuselage skin at certain 

frames for any cracking, and repair if 

necessary, as specified in EASA AD 

2020–0280. 

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. See the MCAI for additional 

background information. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The following presents 

the comments received on the NPRM 

and the FAA’s response to each 

comment. 

Support for the NPRM 

United Airlines indicated its support 

for the NPRM. 

Request To Use a Certain Approval 

Forms 

Delta Air Lines (DAL) requested that 

paragraph (h)(3) of the proposed AD 

reference both the Repair and Design 

Approval Form (RDAF) and the Airbus 

Repair Design Approval Sheet (RDAS). 

DAL stated that Airbus has entered into 

service the RDAF which supersedes the 

RDAS. DAL commented that if the 

proposed AD does not reflect this 

change, operators may be required to 

obtain an alternative method of 

compliance (AMOC) in order to use the 

RDAF to comply with the requirements 

specified in paragraph (h)(3) of the 

proposed AD. 

The FAA disagrees with the 

commenter’s request. The exception in 

paragraph (h)(3) removes any need to 

reference the RDAS or the RDAF. 

Instead, the specific reference to a 

specific repair instructions document is 

replaced 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 Design 

Organization Approval (DOA). The 

RDAS and the RDAF are within the 

provision to use a method approved by 

Airbus SAS’s EASA DOA. The FAA has 

not changed this AD in this regard. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

editorial changes. The FAA has 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

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) at the LH and RH sides of the 

fuselage skin, above stringer 6 from 

FR35 to FR47, for any cracking, and 

repair if necessary. 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. 

Costs of Compliance 

The FAA estimates that this AD 

affects 439 airplanes of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Retained actions from AD 2017–12–13 3 work-hours × $85 per hour = $255 ..... $0 $255 ....................... $111,945. 

Repetitive inspections (new actions) ...... Up to 30 work-hours × $85 per hour = 

Up to $2,550.

0 Up to $2,550 .......... Up to 

$1,119,450. 

The FAA has received no definitive 

data on which to base the cost estimates 

for the repairs specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701: General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 [Amended] 

■ 2. The FAA amends § 39.13 by: 


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Federal Register / Vol. 86, No. 166 / Tuesday, August 31, 2021 / Rules and Regulations 48487 

■ a. Removing Airworthiness Directive 

(AD) 2017–12–13, Amendment 39– 

18928 (82 FR 27983, June 20, 2017); and 

■ b. Adding the following new AD: 

2017–17–03 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. 

(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. 

(i) European Union Aviation Safety Agency 

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

2020. 

(ii) [Reserved] 

(3) 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. 

(4) You may view this 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. This material may be found 

in the AD docket on the internet at https:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2021–0334. 

(5) You may view this material 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 August 4, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–18702 Filed 8–30–21; 8:45 am] 

BILLING CODE 4910–13–P 


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