40710 Federal Register / Vol. 87, No. 130 / Friday, July 8, 2022 / Rules and Regulations 

Virginia, Washington, and West 

Virginia. If an existing borrower in a 

pilot state qualifies for a subsequent 

loan or grant, the pilot conditions can 

apply to the subsequent request as 

appropriate. Non-pilot states may 

request case-by-case administrative 

waivers (if justified) that mirror the 

allowances in the pilot. 

Paperwork Reduction Act 

The regulatory waivers for this pilot 

contains no new reporting or 

recordkeeping burdens under Office of 

Management and Budget (OMB) control 

number 0575–0179 that would require 

approval under the Paperwork 

Reduction Act of 1995 (44 U.S.C. 

Chapter 35). 

Non-Discrimination Statement 

In accordance with Federal civil 

rights laws and USDA civil rights 

regulations and policies, the USDA, its 

Mission Areas, agencies, staff offices, 

employees, and institutions 

participating in or administering USDA 

programs are prohibited from 

discriminating based on race, color, 

national origin, religion, sex, gender 

identity (including gender expression), 

sexual orientation, disability, age, 

marital status, family/parental status, 

income derived from a public assistance 

program, political beliefs, or reprisal or 

retaliation for prior civil rights activity, 

in any program or activity conducted or 

funded by USDA (not all bases apply to 

all programs). Remedies and complaint 

filing deadlines vary by program or 

incident. 

Program information may be made 

available in languages other than 

English. Persons with disabilities who 

require alternative means of 

communication to obtain program 

information (e.g., Braille, large print, 

audiotape, American Sign Language) 

should contact the responsible Mission 

Area, agency, or staff office; the USDA 

TARGET Center at (202) 720–2600 

(voice and TTY); or the Federal Relay 

Service at (800) 877–8339. 

To file a program discrimination 

complaint, a complainant should 

complete a Form AD–3027, USDA 

Program Discrimination Complaint 

Form, which can be obtained online at 

https://www.ascr.usda.gov/complaint_

filing_cust.html, from any USDA office, 

by calling (866) 632–9992, or by writing 

a letter addressed to USDA. The letter 

must contain the complainant’s name, 

address, telephone number, and a 

written description of the alleged 

discriminatory action in sufficient detail 

to inform the Assistant Secretary for 

Civil Rights (ASCR) about the nature 

and date of an alleged civil rights 

violation. The completed AD–3027 form 

or letter must be submitted to USDA by: 

(1) Mail: U.S. Department of 

Agriculture, Office of the Assistant 

Secretary for Civil Rights, 1400 

Independence Avenue SW, Washington, 

DC 20250–9410; or 

(2) Fax: (833) 256–1665 or (202) 690– 

7442; or 

(3) Email: Program.Intake@usda.gov. 

Joaquin Altoro, 

Administrator, Rural Housing Service. 

[FR Doc. 2022–14523 Filed 7–7–22; 8:45 am] 

BILLING CODE 3410–XV–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1073; Project 

Identifier AD–2021–01252–T; Amendment 

39–22090; AD 2022–13–04] 

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) 2017–24– 

10, which applied to certain The Boeing 

Company Model 757–200, –200PF, and 

–300 series airplanes. AD 2017–24–10 

required repetitive inspections for any 

cracking of a certain fuselage frame 

inner chord; identification of the 

material of a certain fuselage frame 

inner chord for certain airplanes; and 

applicable corrective actions. This AD 

was prompted by reports of cracking 

found at a certain fuselage frame inner 

chord. This AD retains the requirements 

of AD 2017–24–10, adds airplanes, and 

requires new inspection types in certain 

areas, an expanded inspection area, 

additional inspections, and applicable 

corrective actions. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective August 12, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 12, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of January 9, 2018 (82 FR 

57343, December 5, 2017). 

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– 

1073. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–1073; 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: 

Peter Jarzomb, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5234; email: 

peter.jarzomb@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2017–24–10, 

Amendment 39–19114 (82 FR 57343, 

December 5, 2017) (AD 2017–24–10). 

AD 2017–24–10 applied to certain The 

Boeing Company Model 757–200, 

–200PF, and –300 series airplanes. The 

NPRM published in the Federal 

Register on January 21, 2022 (87 FR 

3246). The NPRM was prompted by 

reports of cracking found at the fuselage 

station (STA) 1380 frame inner chord 

and by reports of new crack findings 

outside of the AD 2017–24–10 

inspection area, which the existing 

inspections will not detect. In the 

NPRM, the FAA proposed to continue to 

require repetitive inspections for any 

cracking of a certain fuselage frame 

inner chord; identification of the 

material of a certain fuselage frame 

inner chord for certain airplanes; and 

applicable corrective actions. The 

NPRM also proposed to add airplanes 

and require new inspection types in 


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certain areas, an expanded inspection 

area, additional inspections, and 

applicable corrective actions. The FAA 

is issuing this AD to detect and correct 

such cracks, which could result in rapid 

decompression of the airplane and the 

inability to sustain loads required for 

continued safe flight and landing. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

seven commenters. The Airline Pilots 

Association, International (ALPA), 

United Airlines, and two additional 

commenters supported the NPRM 

without change. 

The FAA received additional 

comments from Aviation Partners 

Boeing (APB), Delta Airlines (DAL), and 

FedEx Express (FedEx). 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 the installation of 

winglets per Supplemental Type 

Certificate (STC) ST01518SE does not 

affect compliance with the mandated 

actions in the proposed rule. 

The FAA agrees with the commenter. 

A review of the STC holders determined 

that airplanes with their winglets 

installed do not affect compliance with 

the proposed actions. Paragraph (c) of 

the proposed AD has been redesignated 

as paragraph (c)(1) of this AD, and 

paragraph (c)(2) has been added 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 for an Exception for a Certain 

STC 

FedEx noted that its fleet of Boeing 

Model 757–200 series airplanes was 

converted to a configuration similar to 

the Boeing Model 757–200SF per VT 

Mobile Aerospace Engineering (VT 

MAE) STC ST03562AT, and those 

airplanes are no longer configured as 

passenger airplanes. Per the VT MAE 

STC ST03562AT, certain areas of the 

airplane are not altered, but are subject 

to Boeing Model 757–200SF loads. The 

FAA infers that the certain areas the 

commenter referred to is the fuselage 

STA 1380 frame inner chord. As a 

result, FedEx requested the VT MAE 

STC ST03562AT be included as a new 

exception in paragraph (k) of this AD to 

the requirements of paragraph (j) of this 

AD, similar to Model 757–200 Special 

Freighter STC ST00916WI–D, as 

specified in Boeing Alert Requirements 

Bulletin 757–53A0118 RB, dated 

October 22, 2021. 

The FAA agrees with the commenter 

for the reasons provided. Paragraph 

(k)(3) has been added to this AD to state 

that where Boeing Alert Requirements 

Bulletin 757–53A0118 RB, dated 

October 22, 2021, allows an approved 

web repair accomplished in accordance 

with 757–200 SRM 53–00–07 Repair 4 

for ‘‘757–200 Special Freighter STC 

ST00916WI–D only,’’ this AD also 

approves those repairs for VT MAE STC 

ST03562AT. 

Request To Change Compliance Time 

FedEx requested that paragraphs (g), 

(h), and (i) of the proposed AD (retained 

from AD 2017–24–10) be retained only 

until the effective date of this final rule, 

at which point the new requirements of 

this AD, as specified in paragraphs (j), 

(k), and (l) of this AD would be the only 

requirements of this AD. FedEx pointed 

to the unsafe condition statement in 

paragraph (e) of the proposed AD as 

justification, emphasizing the phrase 

‘‘. . . new crack findings outside of the 

AD 2017–24–10 inspection area, which 

the existing inspections will not detect.’’ 

FedEx noted that the exception 

specified in paragraph (k)(1) of this AD 

would remain unchanged. 

The FAA does not agree with the 

commenter. This AD is issued to 

address new cracking that has been 

found outside of the inspection area of 

AD 2017–24–10, and that AD’s 

inspections will not detect the new 

cracking. Operators that have performed 

the initial eddy current inspections 

required by AD 2017–24–10 need to 

continue to inspect affected airplanes at 

the applicable repetitive interval in 

order to maintain the damage tolerance 

capability of the affected structure. If the 

FAA were to not retain the requirements 

of AD 2017–24–10 until the terminating 

action required by paragraph (l) of this 

AD is performed, that would allow the 

affected airplanes to continue flying 

beyond the repetitive inspection 

interval. If those repetitive eddy current 

inspections are not performed, an 

undetected crack could result in the 

inability of a principal structural 

element to sustain limit loads, which 

could adversely affect the structural 

integrity of the airplane. No change has 

been made to this final rule. 

Request for an Additional AMOC 

FedEx requested that paragraph (m)(4) 

of the proposed AD be updated to reflect 

the language in Notes (a) and (b) of 

Tables 1 and 2 of Boeing Alert 

Requirements Bulletin 757–53A0118 

RB, dated October 22, 2021, which 

FedEx believes should allow additional 

AMOCs. FedEx observed that paragraph 

(m)(4) of the proposed AD states that 

AMOCs approved previously for AD 

2017–24–10 are not approved as 

AMOCs for this AD. In expressing its 

disagreement with that statement, 

FedEx observed that those Notes state 

that if any existing repair is found and 

meets either one of the conditions stated 

in the Notes, the repair is still approved 

and meets the requirements for 

accomplishing the action specified in 

Boeing Alert Requirements Bulletin 

757–53A0118 RB, dated October 22, 

2021. FedEx asserts that the referenced 

notes are governed by paragraph (j) of 

the proposed AD, and paragraph (k) of 

the proposed AD does not provide any 

exceptions for the referenced notes. In 

conclusion, FedEx asserted that 

paragraph (m)(4) of the proposed AD is 

in conflict with Notes (a) and (b) of 

Tables 1 and 2 of Boeing Alert 

Requirements Bulletin 757–53A0118 

RB, dated October 22, 2021. As a result, 

FedEx requests that paragraph (m)(4) of 

the final rule be updated to reflect the 

language in the referenced notes. 

The FAA does not agree with the 

commenter. FedEx asserted that a repair 

that meets either one of the conditions 

stated in Notes (a) and (b) of Tables 1 

and 2 of Boeing Alert Requirements 

Bulletin 757–53A0118 RB, dated 

October 22, 2021, is approved and meets 

the requirements for accomplishing the 

actions specified in that service 

information. FedEx further asserts that 

such a repair is therefore in conflict 

with paragraph (m)(4) of the proposed 

AD. These assertions are incorrect. For 

airplanes with repairs that meet either 

one of the conditions stated in Notes (a) 

and (b) of Tables 1 and 2 of Boeing Alert 

Requirements Bulletin 757–53A0118 

RB, dated October 22, 2021, the 

inspections specified in that service 

information are still required, but at a 

different inspection threshold than the 

threshold for airplanes that do not have 

an approved repair installed in the 

inspection area. Therefore, Notes (a) and 

(b) of Tables 1 and 2 of Boeing Alert 

Requirements Bulletin 757–53A0118 

RB, dated October 22, 2021, are not in 

conflict with paragraph (m)(4) of this 

AD. AMOCs previously approved for 

AD 2017–24–10 do not address the 

unsafe condition identified in this final 

rule (cracks initiating in the STA 1380 

frame web), and therefore cannot be 

approved as AMOCs for this final rule. 

If the existing AMOCs were to be 


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approved as AMOCs for this final rule, 

then the inspections specified in Boeing 

Alert Requirements Bulletin 757– 

53A0118 RB, dated October 22, 2021, 

would not be required on airplanes with 

a previously approved AMOC. If these 

inspections are not accomplished, 

cracks initiating in the frame web could 

grow undetected, which could result in 

the inability of a principal structural 

element to sustain limit loads, which 

could adversely affect the structural 

integrity of the airplane. No change has 

been made to this final rule. 

Request for a New Exception To Omit 

Reinstallation of the Guide Track 

Fitting as a Required for Compliance 

Action 

Delta requested that the FAA modify 

paragraph (k) of the proposed AD to 

include a new exception that omits 

Figure 6 from Boeing Alert 

Requirements Bulletin 757–53A0118 

RB, dated October 22, 2021. Delta 

recognized that the proposed AD seeks 

to mitigate cracking at the fuselage STA 

1380 frame inner chord by detecting and 

repairing such cracks as described in 

paragraph (e) of the proposed AD. 

However, Delta contends that 

reinstallation of the guide track fitting in 

accordance with Figure 6 of Boeing 

Alert Requirements Bulletin 757– 

53A0118 RB, dated October 22, 2021, 

does nothing to mitigate the unsafe 

condition and is a close access step. 

Open access steps in accordance with 

Boeing Alert Requirements Bulletin 

757–53A0118 RB, dated October 22, 

2021, including removal of the guide 

track fitting in Figure 2, and other close 

access steps in accordance with Part 2, 

are not contained in Boeing Alert 

Requirements Bulletin 757–53A0118 

RB, dated October 22, 2021. 

The FAA does not agree with the 

commenter. The root cause for the 

cracking in the STA 1380 frame inner 

chord and web under the roller guide 

track fitting is attributed to the out-ofplane bending stress induced from a 

mis-rigging condition of the No. 2 cargo 

door, which allows the roller pin on the 

lower cargo door to contact the roller 

guide track fitting. Figure 6 provides 

instructions on how to properly re-rig 

the roller guide track fitting and the No. 

2 cargo door to prevent the contact 

between the roller pin and the roller 

guide track fitting, eliminating the outof-plane bending loads on the STA 1380 

frame. No change has been made to this 

final rule. 

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 757–53A0118 

RB, dated October 22, 2021. This service 

information specifies procedures for a 

general visual inspection or a 

maintenance records check of the STA 

1380 frame for any repair, and repetitive 

surface high frequency eddy current 

(HFEC) inspections of the STA 1380 

frame inner chord and frame web for 

any cracking, repetitive sub-surface low 

frequency eddy current (LFEC) 

inspections of the STA 1380 frame inner 

chord for any cracking, and applicable 

corrective actions. Corrective actions 

include repair. 

This AD also requires Boeing Alert 

Service Bulletin 757–53A0101, dated 

November 8, 2016, which the Director of 

the Federal Register approved for 

incorporation by reference as of January 

9, 2018 (82 FR 57343, December 5, 

2017). 

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 affect 

477 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 

Surface HFEC inspection (retained 

actions from AD 2017–24–10).

5 work-hours × $85 per hour = 

$425 per inspection cycle.

$0 $425 per inspection cycle $202,725 per inspection 

cycle. 

Identify the material (retained actions 

from AD 2017–24–10).

Up to 2 work-hours × $85 per hour 

= $170.

0 Up to $170 ...................... Up to $81,090. 

General visual inspection (new proposed action).6 work-hours × $85 per hour = 

$510.

0 $510 ................................ $243,270. 

Surface frame inner chord HFEC inspection (new proposed action).Up to 10 work-hours × $85 per hour 

= $850 per inspection cycle.

0 Up to $850 per inspection cycle.Up to $405,450 per inspection cycle. 

Sub-surface frame inner chord LFEC 

inspection (new proposed action).

Up to 6 work-hours × $85 per hour 

= $510 per inspection cycle.

0 Up to $510 per inspection cycle.Up to $243,270 per inspection cycle. 

Surface HFEC frame web inspection 

(new proposed action).

Up to 6 work-hours × $85 per hour 

= $510 per inspection cycle.

0 Up to $510 per inspection cycle.Up to $243,270 per inspection cycle. 

The FAA has received no definitive 

data on which to base the cost estimates 

for the on-condition 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 


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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) 2017–24–10, Amendment 39– 

19114 (82 FR 57343, December 5, 2017); 

and 

■ b. Adding the following new AD: 

2022–13–04 The Boeing Company: 

Amendment 39–22090; Docket No. FAA– 

2021–1073; Project Identifier AD–2021– 

01252–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 12, 2022. 

(b) Affected ADs 

This AD replaces AD 2017–24–10, 

Amendment 39–19114 (82 FR 57343, 

December 5, 2017) (AD 2017–24–10). 

(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 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking found at the fuselage station (STA) 

1380 frame inner chord and by reports of 

new crack findings outside of the AD 2017– 

24–10 inspection area, which the existing 

inspections will not detect. The FAA is 

issuing this AD to detect and correct such 

cracks, which could result in rapid 

decompression of the airplane and the 

inability to sustain loads required for 

continued safe flight and landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection for Group 1 

Airplanes, With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2017–24–10, with no 

changes. For Group 1 airplanes as identified 

in Boeing Alert Service Bulletin 757– 

53A0101, dated November 8, 2016: At the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 757–53A0101, dated November 8, 

2016; except as specified in paragraph (i)(1) 

of this AD, do a surface high frequency eddy 

current (HFEC) inspection for any cracking of 

the fuselage STA 1380 frame inner chord, 

and do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–53A0101, dated November 8, 2016; 

except as specified in paragraph (i)(2) of this 

AD. Do all applicable corrective actions 

before further flight. Repeat the surface HFEC 

inspection, thereafter, at the times specified 

in paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 757–53A0101, dated 

November 8, 2016. 

(h) Retained Inspection for Group 2 

Airplanes, With No Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2017–24–10, with no 

changes. For Group 2 airplanes as identified 

in Boeing Alert Service Bulletin 757– 

53A0101, dated November 8, 2016: At the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 757–53A0101, dated November 8, 

2016, except as specified in paragraph (i)(1) 

of this AD, identify the material of the 

fuselage STA 1380 frame inner chord, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–53A0101, dated November 8, 2016. 

(1) If the fuselage STA 1380 frame inner 

chord material 2024–T42 aluminum alloy is 

found during any identification required by 

paragraph (h) of this AD: No further action 

is required by this paragraph for that 

airplane. 

(2) If the fuselage STA 1380 frame inner 

chord material 7075–T73 aluminum alloy is 

found during any identification required by 

the introductory text of paragraph (h) of this 

AD: Before further flight, do a surface HFEC 

inspection for any cracking of the fuselage 

STA 1380 frame inner chord, and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 757–53A0101, 

dated November 8, 2016; except as specified 

in paragraph (i)(2) of this AD. Do all 

applicable corrective actions before further 

flight. Repeat the surface HFEC inspection 

thereafter at the times specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 757–53A0101, dated November 8, 

2016. 

(i) Retained Exceptions to the Service 

Information, With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2017–24–10, with no 

changes. 

(1) Where Boeing Alert Service Bulletin 

757–53A0101, dated November 8, 2016, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after January 9, 

2018 (the effective date of AD 2017–24–10). 

(2) Where Boeing Alert Service Bulletin 

757–53A0101, dated November 8, 2016, 

specifies to contact Boeing for appropriate 

action and identifies that action as ‘‘RC’’ 

(Required for Compliance): Before further 

flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (m) of this AD. 

(j) New Required Actions 

Except as specified by paragraph (k) of this 

AD: At the applicable times specified in the 

‘‘Compliance’’ paragraph of Boeing Alert 

Requirements Bulletin 757–53A0118 RB, 

dated October 22, 2021, do all applicable 

actions identified in, and in accordance with, 

the Accomplishment Instructions of Boeing 

Alert Requirements Bulletin 757–53A0118 

RB, dated October 22, 2021. 

Note 1 to paragraph (j): Guidance for 

accomplishing the actions required by this 

AD can be found in Boeing Alert Service 

Bulletin 757–53A0118, dated October 22, 

2021, which is referred to in Boeing Alert 

Requirements Bulletin 757–53A0118 RB, 

dated October 22, 2021. 

(k) New Exceptions to Service Information 

Specifications 

(1) Where the Compliance Time column of 

the tables in the ‘‘Compliance’’ paragraph of 

Boeing Alert Requirements Bulletin 757– 

53A0118 RB, dated October 22, 2021, uses 

the phrase ‘‘the original issue date of the 

Requirements Bulletin 757–53A0118 RB,’’ 

this AD requires using ‘‘the effective date of 

this AD.’’ 

(2) Where Boeing Alert Requirements 

Bulletin 757–53A0118 RB, dated October 22, 

2021, specifies contacting Boeing for repair 

instructions or for alternative inspections: 

This AD requires doing the repair, or doing 

the alternative inspections and applicable oncondition actions using a method approved 

in accordance with the procedures specified 

in paragraph (m) of this AD. 

(3) Where Boeing Alert Requirements 

Bulletin 757–53A0118 RB, dated October 22, 

2021, states that 757–200 SRM 53–00–07 

Repair 4 is for ‘‘757–200 Special Freighter 

STC ST00916WI–D only,’’ for this AD, 757– 

200 SRM 53–00–07 Repair 4 is for ‘‘757–200 

Special Freighter STC ST00916WI–D and VT 

Mobile Aerospace Engineering (VT MAE) 

Supplemental Type Certificate (STC) 

ST03562AT only.’’ 


jspears on DSK121TN23PROD with RULES1
40714 Federal Register / Vol. 87, No. 130 / Friday, July 8, 2022 / Rules and Regulations 

(l) Terminating Action for Certain 

Inspections 

Accomplishment of the applicable initial 

inspections and corrective actions specified 

in the Accomplishment Instructions of 

Boeing Alert Requirements Bulletin 757– 

53A0118 RB, dated October 22, 2021, 

terminates the inspections required by 

paragraphs (g) and (h) of this AD. 

(m) 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 paragraph (n) of this 

AD. 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 previously for AD 

2017–24–10 are not approved as AMOCs 

with this AD. 

(5) Except as specified by paragraph (i) of 

this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (m)(5)(i) and (ii) of this AD apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled 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 RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(n) Related Information 

For more information about this AD, 

contact Peter Jarzomb, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

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

5234; email: peter.jarzomb@faa.gov. 

(o) 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 August 12, 2022. 

(i) Boeing Alert Requirements Bulletin 

757–53A0118 RB, dated October 22, 2021. 

(ii) [Reserved] 

(4) The following service information was 

approved for IBR on January 9, 2018 (82 FR 

57343, December 5, 2017). 

(i) Boeing Alert Service Bulletin 757– 

53A0101, dated November 8, 2016. 

(ii) [Reserved] 

(5) 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. 

(6) 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. 

(7) 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 June 13, 2022. 

Christina Underwood, 

Acting Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–14490 Filed 7–7–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0296; Project 

Identifier MCAI–2021–01064–E; Amendment 

39–22103; AD 2022–13–17] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG (Type 

Certificate Previously Held by RollsRoyce plc) Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2021–15– 

01 for all Rolls-Royce Deutschland Ltd 

& Co KG (RRD) Trent XWB–75, Trent 

XWB–79, Trent XWB–79B, Trent XWB– 

84, and Trent XWB–97 model turbofan 

engines. AD 2021–15–01 required 

revisions to the airworthiness 

limitations section (ALS) of the RollsRoyce (RR) Trent XWB time limits 

manual (TLM) and the operator’s 

existing approved aircraft maintenance 

program (AMP). Since the FAA issued 

AD 2021–15–01, the manufacturer has 

revised the TLM life limits and updated 

mandatory inspection intervals of 

certain critical rotating parts. This AD 

requires revisions to the ALS of the RR 

Trent XWB TLM and the operator’s 

existing approved AMP, as specified in 

a European Union Aviation Safety 

Agency (EASA) AD, which is 

incorporated by reference. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective August 12, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 12, 2022. 

ADDRESSES: For material incorporated 

by reference in this AD, contact EASA, 

Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; phone: +49 221 8999 

000; email: ADs@easa.europa.eu. You 

may find this material on the EASA 

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

You may view this material at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 1200 District 

Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call (817) 222– 

5110. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2022– 

0296. For the material identified in this 

AD that is not incorporated by 

reference, contact Rolls-Royce plc, 

Corporate Communications, P.O. Box 

31, Derby, DE24 8BJ, United Kingdom; 

phone: +44 (0)1332 242424; fax: +44 

(0)1332 249936; website: https://

www.rolls-royce.com/contact-us.aspx. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0296; 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 

AD, the EASA AD, 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: 

Sungmo Cho, Aviation Safety Engineer, 

ECO Branch, FAA, 1200 District 


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