26964 Federal Register / Vol. 87, No. 88 / Friday, May 6, 2022 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0685; Project 

Identifier AD–2021–00432–T; Amendment 

39–22015; AD 2022–08–12] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2020–21– 

17, which applied to all The Boeing 

Company Model 757 airplanes. AD 

2020–21–17 required repetitive 

inspections for skin cracking and shim 

migration at the upper link drag fittings, 

diagonal brace cracking, and fastener 

looseness; and applicable on-condition 

actions. This AD was prompted by 

reports of bolt rotation in the engine 

drag fitting joint and fastener heads and 

cracks found in the skin of the fastener 

holes, and the need to reduce the 

compliance time for certain groups. This 

AD retains the requirements of AD 

2020–21–17 with reduced compliance 

times for certain airplane groups. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective June 10, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 10, 2022. 

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– 

0685. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0685; 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: 

David Truong, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5224; email: 

david.truong@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2020–21–17, 

Amendment 39–21290 (85 FR 79418, 

December 10, 2020) (AD 2020–21–17). 

AD 2020–21–17 applied to all The 

Boeing Company Model 757 airplanes. 

The NPRM published in the Federal 

Register on September 9, 2021 (86 FR 

50485). The NPRM was prompted by 

reports of bolt rotation in the engine 

drag fitting joint and fastener heads and 

cracks found in the skin of the fastener 

holes, and the need to reduce the 

compliance time for certain groups. In 

the NPRM, the FAA proposed to retain 

the requirements of AD 2020–21–17 

with reduced compliance times for 

certain airplane groups. The FAA is 

issuing this AD to address cracking in 

the wing upper skin and forward drag 

fittings, which could lead to a 

compromised upper link and reduced 

structural integrity of the engine strut, 

and possible separation of a strut and 

engine from the airplane during flight. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from the 

Air Line Pilots Association, 

International (ALPA), Boeing, and 

FedEx who supported the NPRM 

without change. 

The FAA received additional 

comments from three commenters, 

including Aviation Partners Boeing 

(APB), United Airlines (UAL), and 

United Parcel Service (UPS). The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

APB stated that accomplishing 

Supplemental Type Certificate (STC) 

ST01518SE does not affect the actions 

specified in the proposed AD. 

The FAA concurs with the 

commenter. The FAA has redesignated 

paragraph (c) of the proposed AD as 

paragraph (c)(1) of this AD and added 

paragraph (c)(2) to this AD to state that 

installation of STC ST01518SE does not 

affect the ability to accomplish the 

actions required by this AD. Therefore, 

for airplanes on which STC ST01518SE 

is installed, a ‘‘change in product’’ 

alternative method of compliance 

(AMOC) approval request is not 

necessary to comply with the 

requirements of 14 CFR 39.17. 

Request To Clarify Certain Figures in 

the Service Information 

UAL requested clarification of Figures 

21 and 22 for an open-hole high 

frequency eddy current (HFEC) 

inspection as specified in Boeing Alert 

Requirements Bulletin 757–57A0073 

RB, Revision 2, dated March 1, 2021. 

UAL stated that in note (a) of Figures 21 

and 22, it specifies to ‘‘Do an open-hole 

HFEC inspection for any crack in 

accordance with 757 NDT [NonDestructive Test] Manual Part 6, 51–00– 

16,’’ at the ‘‘Fastener Holes and Drag 

Fitting.’’ UAL also stated that this is 

different than the inspection specified 

in note (a) of Figures 7 and 8 which 

specifies to ‘‘Do an open-hole HFEC 

inspection for any crack of the holes of 

loose fasteners only in accordance with 

757 NDT Manual Part 6, 51–00–16’’ at 

the ‘‘Fastener Holes.’’ 

UAL stated that the NDT manual 

references are the same in Figures 7 and 

8, and Figures 21 and 22. UAL 

commented that Figures 7 and 8 are 

used in Part 4 inspections (only at loose 

fastener hole locations found at 

locations 11 through 18) of the service 

information; and Figures 21 and 22 are 

used in Part 8 inspections (inspections 

of all fastener locations 11 through 18) 

of the service information. UAL 

commented that it is not clear what the 

intent is of making step 1 in Figures 21 

and 22 specify ‘‘Fastener Holes’’ and 

‘‘Drag Fitting,’’ (listed as two separate 

items) and if these are different 

inspections of the fastener holes. 

The FAA agrees to provide 

clarification. Part 4 inspections use 

Figures 7 and 8 of the service 

information to inspect for any cracking, 

and are an on-condition action required 

only for any fastener holes that are 

found (during Part 2 inspections) to 

have loose fasteners in the wing upper 

skin. Part 8 inspections use Figures 21 

and 22 to inspect for any cracking in the 

fastener holes of the upper wing skin 

and drag fitting, and are required for all 

airplanes. Accomplishing an open hole 


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Federal Register / Vol. 87, No. 88 / Friday, May 6, 2022 / Rules and Regulations 26965 

HFEC inspection as a result of 

Condition 5 (which requires 

accomplishing figures 7 and 8), meets 

the requirement of the open hole HFEC 

inspection of fastener holes 11 through 

18 for only the fastener hole(s) 

inspected (as specified in note (a) of 

Tables 4 and 7 in the Accomplishment 

Instructions of Boeing Alert 

Requirements Bulletin 757–57A0073 

RB, Revision 2, dated March 1, 2021). 

The open hole HFEC inspection for any 

cracking of fastener holes 11 through 18 

specified in Figures 7 and 8 and Figures 

21 and 22 are the same, however the 

‘‘Drag Fitting’’ specified in Figures 21 

and 22 is emphasized so the drag fitting 

fastener holes are not missed when 

performing the open hole HFEC 

inspection through the fastener hole 

shared between the upper wing skin and 

drag fitting. Part 4 and Part 8 have 

different compliance times and 

repetitive inspection intervals. The FAA 

has not changed this AD in this regard. 

Request To Include Previously 

Approved AMOCs 

UPS requested that the FAA include 

previously approved AMOCs in the 

proposed AD for AD 2018–16–05, 

Amendment 39–19345 (83 FR 38250, 

August 6, 2018) (AD 2018–16–05), 

which was superseded by AD 2020–21– 

17. 

The FAA agrees with the request. 

AMOCs for AD 2018–16–05 that are still 

applicable to the corresponding 

provisions of Boeing Alert Requirements 

Bulletin 757–57A0073 RB, Revision 2, 

dated March 1, 2021, which are required 

by paragraph (g) of this AD, are 

approved as AMOCs for this AD. The 

FAA has added paragraph (j)(5) to this 

AD to include AMOCs approved for AD 

2018–16–05. 

Conclusion 

The FAA reviewed the relevant data, 

considered any comments received, and 

determined that air safety requires 

adopting this AD as proposed. Except 

for minor editorial changes, and any 

other changes described previously, 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 757–57A0073 

RB, Revision 2, dated March 1, 2021. 

This service information specifies 

procedures for repetitive general visual 

and detailed inspections for loose 

fasteners, skin cracking, and shim 

migration at the upper link drag fittings, 

and for cracking in the diagonal brace 

and diagonal brace fittings; repetitive 

open-hole high frequency eddy current 

inspections for cracking of the fastener 

holes and loose bolt holes; and 

applicable on-condition actions. Oncondition actions include installing the 

upper link and upper link pins; 

replacing drag fittings; installing bolts, 

washers, and nuts; performing a torque 

check of fasteners on the affected shims; 

trimming affected shims and applying 

chemical conversion coating on the 

shims, fillet seal, and drag fittings; and 

repairing cracks, migrated shims, 

mistorqued bolts, and loose fasteners. 

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 

would affect 450 airplanes of U.S. 

registry. The FAA estimates the 

following costs to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts 

cost 

Cost per 

product 

Cost on U.S. 

operators 

Repetitive HFEC inspections 85 work-hours × $85 per hour = 

$7,225 per inspection cycle.

$0 $7,225 per inspection cycle .. $3,251,250 per inspection 

cycle. 

The FAA has received no definitive 

data on which to base the cost estimates 

for the on-condition actions 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: 

■ a. Removing Airworthiness Directive 

(AD) 2020–21–17, Amendment 39– 

21290 (85 FR 79418, December 10, 

2020); and 

■ b. Adding the following new AD: 

2022–08–12 The Boeing Company: 

Amendment 39–22015; Docket No. 


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26966 Federal Register / Vol. 87, No. 88 / Friday, May 6, 2022 / Rules and Regulations 

FAA–2021–0685; Project Identifier AD– 

2021–00432–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective June 10, 2022. 

(b) Affected ADs 

This AD replaces AD 2020–21–17, 

Amendment 39–21290 (85 FR 79418, 

December 10, 2020) (AD 2020–21–17). 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 757–200, –200PF, –200CB, 

and –300 series airplanes, certificated in any 

category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01518SE does not affect 

the ability to accomplish the actions required 

by this AD. Therefore, for airplanes on which 

STC ST01518SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of bolt 

rotation in the engine drag fitting joint and 

fastener heads and cracks found in the skin 

of the fastener holes, and the need to reduce 

the compliance time for certain groups. The 

FAA is issuing this AD to address cracking 

in the wing upper skin and forward drag 

fittings, which could lead to a compromised 

upper link and reduced structural integrity of 

the engine strut, and possible separation of 

a strut and engine from the airplane during 

flight. 

(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 757–57A0073 RB, 

Revision 2, dated March 1, 2021, do all 

applicable actions identified in, and in 

accordance with, the Accomplishment 

Instructions of Boeing Alert Requirements 

Bulletin 757–57A0073 RB, Revision 2, dated 

March 1, 2021. 

Note 1 to paragraph (g): Guidance for 

accomplishing the actions required by this 

AD can be found in Boeing Alert Service 

Bulletin 757–57A0073, Revision 2, dated 

March 1, 2021, which is referred to in Boeing 

Alert Requirements Bulletin 757–57A0073 

RB, Revision 2, dated March 1, 2021. 

(h) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Requirements 

Bulletin 757–57A0073 RB, Revision 2, dated 

March 1, 2021, uses the phrase ‘‘the Original 

Issue date of Requirements Bulletin 757– 

57A0073 RB,’’ this AD requires using 

September 10, 2018 (the effective date of AD 

2018–16–05, Amendment 39–19345 (83 FR 

38250, August 6, 2018)). 

(2) Where the Compliance Time columns 

of the tables in the ‘‘Compliance’’ paragraph 

of Boeing Alert Requirements Bulletin 757– 

57A0073 RB, Revision 2, dated March 1, 

2021, uses the phrase ‘‘the Revision 1 date of 

Requirements Bulletin 757–57A0073 RB date 

of this service bulletin,’’ this AD requires 

using January 14, 2021 (the effective date of 

AD 2020–21–17). 

(3) Where the Condition and Compliance 

Time columns of the tables in the 

‘‘Compliance’’ paragraph of Boeing Alert 

Requirements Bulletin 757–57A0073 RB, 

Revision 2, dated March 1, 2021, uses the 

phrase ‘‘the Revision 2 date of Requirements 

Bulletin 757–57A0073 RB,’’ this AD requires 

using the effective date of this AD. 

(4) Where Boeing Alert Requirements 

Bulletin 757–57A0073 RB, Revision 2, dated 

March 1, 2021, specifies contacting Boeing 

for repair instructions: This AD requires 

doing the repair using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions specified in paragraph (g) of this AD, 

except for the open-hole high frequency eddy 

current inspections at fastener locations 11– 

18, if those actions were performed before the 

effective date of this AD using Boeing Alert 

Requirements Bulletin 757–57A0073 RB, 

dated July 14, 2017. 

(2) This paragraph provides credit for the 

actions specified in paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Requirements Bulletin 757–57A0073 RB, 

Revision 1, dated August 1, 2019. This 

service information is not incorporated by 

reference in this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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-ANMLAACO-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, Los Angeles 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. 

(4) AMOCs approved for AD 2020–21–17 

are approved as AMOCs for the 

corresponding provisions of Boeing Alert 

Requirements Bulletin 757–57A0073 RB, 

Revision 2, dated March 1, 2021, that are 

required by paragraph (g) of this AD. 

(5) AMOCs approved for AD 2018–16–05, 

Amendment 39–19345 (83 FR 38250, August 

6, 2018) are approved as AMOCs for the 

corresponding provisions of Boeing Alert 

Requirements Bulletin 757–57A0073 RB, 

Revision 2, dated March 1, 2021, that are 

required by paragraph (g) of this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact David Truong, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5224; email: david.truong@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(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 the AD specifies otherwise. 

(i) Boeing Alert Requirements Bulletin 

757–57A0073 RB, Revision 2, dated March 1, 

2021. 

(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, 

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

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on April 7, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–09663 Filed 5–5–22; 8:45 am] 

BILLING CODE 4910–13–P 


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