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

48483 

Vol. 86, No. 166 

Tuesday, August 31, 2021 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0376; Project 

Identifier AD–2021–00062–T; Amendment 

39–21689; AD 2021–17–06] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 747–100, 

–100B, –100B SUD, –200B, –200C, 

–200F, –300, –400, –400D, –400F, 

747SR, and 747SP airplanes. This AD 

was prompted by reports of cracks 

found in the front spar shear tie and at 

the intercostal lug fitting at certain 

locations. This AD requires repetitive 

detailed and surface high frequency 

eddy current (HFEC) inspections of the 

front spar shear tie and intercostal lug 

fitting at certain locations for any 

cracking, and applicable on-condition 

actions. 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 service information 

identified in this final rule, 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. 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. 

It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0376. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0376; 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: 

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. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all The Boeing Company Model 

747–100, –100B, –100B SUD, –200B, 

–200C, –200F, –300, –400, –400D, 

–400F, 747SR, and 747SP airplanes. The 

NPRM published in the Federal 

Register on June 7, 2021 (86 FR 30216). 

The NPRM was prompted by reports of 

cracks found in the front spar shear tie 

and at the intercostal lug fitting at 

certain locations. In the NPRM, the FAA 

proposed to require repetitive detailed 

and surface HFEC inspections of the 

front spar shear tie and intercostal lug 

fitting at certain locations for any 

cracking, and applicable on-condition 

actions. The FAA is issuing this AD to 

address any cracking in these areas that 

could result in the loss of limit load 

capability in a principal structural 

element, the potential inability to 

restrain the cargo for certain cargo 

configurations, and the potential for a 

center fuel tank rupture for certain cargo 

configurations under limit load 

conditions, which could adversely affect 

the structural integrity of the airplane. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received a comment from 

Boeing who supported the NPRM 

without change. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comment received, and 

determined that air safety requires 

adopting this AD as proposed. Except 

for minor editorial changes, this AD is 

adopted as proposed in the NPRM. 

None of the changes will increase the 

economic burden on any operator. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Boeing Alert 

Requirements Bulletin 747–53A2904 

RB, dated December 16, 2020. This 

service information specifies procedures 

for repetitive detailed and surface HFEC 

inspections of the station 1000 front 

spar shear tie at the left and right side 

buttock line (BL) 11.33, BL 33.99, BL 

57.50, and BL 75.92, and of the 

intercostal lug fitting at the left and right 

side BL 11.33, for any cracking, and 

applicable on-condition actions. Oncondition actions include repair, 

installing a new front spar shear tie, and 

installing a new intercostal lug fitting. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in ADDRESSES. 

Costs of Compliance 

The FAA estimates that this AD will 

affect 117 airplanes of U.S. registry. The 

FAA estimates the following costs to 

comply with this AD: 


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48484 Federal Register / Vol. 86, No. 166 / Tuesday, August 31, 2021 / Rules and Regulations 

ESTIMATED COSTS

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

operators 

Inspections ........ Up to 314 work-hours × $85 per hour = Up to 

$26,690.

$0 Up to $26,690 .............. Up to $3,122,730. 

The FAA estimates the following 

costs to do any necessary installations 

and repairs that would be required 

based on the results of the inspection. 

The agency has no way of determining 

the number of aircraft that might need 

these installations and repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Installations ........ Up to 368 work-hour × $85 per hour = Up to 

$31,280.

Up to $38,446 (for shear ties and intercostal lug 

fittings).

Up to $69,726. 

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. 

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 adding 

the following new airworthiness 

directive: 

2021–17–06 The Boeing Company: 

Amendment 39–21689; Docket No. 

FAA–2021–0376; Project Identifier AD– 

2021–00062–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 5, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 747–100, –100B, –100B 

SUD, –200B, –200C, –200F, –300, –400, 

–400D, –400F, 747SR, and 747SP airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

in the station (STA) 1000 front spar shear tie 

at the left and right side buttock line (BL) 

11.33, BL 33.99, BL 57.50, and BL 75.92, and 

in the intercostal lug fitting at the left and 

right side BL 11.33. The FAA is issuing this 

AD to address any cracking in these areas 

that could result in the loss of limit load 

capability in a principal structural element, 

the potential inability to restrain the cargo for 

certain cargo configurations, and the 

potential for a center fuel tank rupture for 

certain cargo configurations under limit load 

conditions, which could adversely affect the 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Except as specified by paragraph (h) of this 

AD: At the applicable times specified in the 

‘‘Compliance’’ paragraph of Boeing Alert 

Requirements Bulletin 747–53A2904 RB, 

dated December 16, 2020, do all applicable 

actions identified in, and in accordance with, 

the Accomplishment Instructions of Boeing 

Alert Requirements Bulletin 747–53A2904 

RB, dated December 16, 2020. 

NOTE 1 TO PARAGRAPH (G): Guidance for 

accomplishing the actions required by this 

AD can be found in Boeing Alert Service 

Bulletin 747–53A2904, dated December 16, 

2020, which is referred to in Boeing Alert 

Requirements Bulletin 747–53A2904 RB, 

dated December 16, 2020. 

(h) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Requirements 

Bulletin 747–53A2904 RB, dated December 

16, 2020, uses the phrase ‘‘the original issue 

date of Requirements Bulletin 747–53A2904 

RB,’’ this AD requires using ‘‘the effective 

date of this AD.’’ 

(2) Where Boeing Alert Requirements 

Bulletin 747–53A2904 RB, dated December 

16, 2020, specifies contacting Boeing for 

repair instructions: This AD requires doing 

the repair using a method approved in 

accordance with the procedures specified in 

paragraph (i) of this AD. 


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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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