97494 Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Rules and Regulations 

(i) No Reporting Requirement 

Although the material referenced in EASA 

AD 2024–0049 specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

(j) Additional AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, 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 manager of the International Validation 

Branch, mail it to the address identified in 

paragraph (k) of this AD. Information may be 

emailed to: 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, International Validation 

Branch, FAA; or EASA; or Airbus Defense 

and Space S.A.’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(k) Additional Information 

For more information about this AD, 

contact Shahram Daneshmandi, Aviation 

Safety Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

206–231–3220; email 

shahram.daneshmandi@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the material listed in this paragraph 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use this material as 

applicable to do the actions required by this 

AD, unless this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2024–0049, dated February 20, 

2024. 

(ii) [Reserved] 

(3) For EASA AD 2024–0049, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

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

easa.europa.eu. You may find this EASA AD 

on the EASA website at 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. 

(5) You may view this material at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

visit www.archives.gov/federal-register/cfr/ 

ibr-locationsoremailfr.inspection@nara.gov. 

Issued on November 21, 2024. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–28787 Filed 12–6–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1053; Project 

Identifier AD–2023–00164–T; Amendment 

39–22891; AD 2024–24–01] 

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 certain 

The Boeing Company Model 757–200, 

–200CB, and –200PF series airplanes. 

This AD was prompted by a crack 

growth analysis, which indicated that 

current inspections are not adequate to 

detect cracks in certain sections of the 

upper frame at the frame splice between 

certain stringers before a single frame 

fails. This AD requires an inspection or 

records review for existing repairs, 

repetitive inspections for cracks of the 

upper frame at the frame splices 

between certain stringers in certain 

sections, and applicable on-condition 

actions. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective January 13, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 13, 2025. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2023–1053, 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. 

Material Incorporated by Reference: 

• For Boeing material 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; 

website myboeingfleet.com. 

• 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. 

It is also available at regulations.gov 

under Docket No. FAA–2023–1053. 

FOR FURTHER INFORMATION CONTACT: 

Wayne Ha, Aviation Safety Engineer, 

FAA, 2200 South 216th Street, Des 

Moines, WA 98198; phone: 562–627– 

5238; email: wayne.ha@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 certain The Boeing Company 

Model 757–200, –200CB, and –200PF 

series airplanes. The NPRM published 

in the Federal Register on July 24, 2023 

(88 FR 47402). The NPRM was 

prompted by a crack growth analysis, 

which indicated that current 

inspections are not adequate to detect 

cracks in certain sections of the upper 

frame at the frame splice between 

certain stringers before a single frame 

fails. In the NPRM, the FAA proposed 

to require an inspection or records 

review for existing repairs, repetitive 

inspections for cracks of the upper 

frame at the frame splices between 

certain stringers in certain sections, and 

applicable on-condition actions. 

The FAA issued a supplemental 

notice of proposed rulemaking (SNPRM) 

to amend 14 CFR part 39 by adding an 

AD that would apply to certain The 

Boeing Company Model 757–200, 

–200CB, and –200PF series airplanes. 

The SNPRM published in the Federal 

Register on April 22, 2024 (89 FR 

29274). The SNPRM was prompted by a 

determination that the repetitive 

inspection intervals for airplanes that 

were modified by Aviation Partners 

Boeing (APB) supplemental type 

certificate (STC) ST01518SE needed to 

be revised. The SNPRM proposed to 

require the actions specified in the 

NPRM, with certain revised compliance 

times. 

The FAA is issuing this AD to address 

cracking at the upper frames common to 

the splice at stringers S–13 to S–14, 

which could interact with fuselage skin 

cracking at the stringer S–14 lap splice. 

This unsafe condition, if not addressed, 

could result in the inability of a 

principal structural element to sustain 


ddrumheller on DSK120RN23PROD with RULES1
Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Rules and Regulations 97495 

limit loads, and 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 SNPRM 

without change. 

The FAA received additional 

comments from FedEx Express, United 

Airlines (United), and European Air 

Transport Leipzig GmbH (EATL). The 

following presents the comments 

received on the SNPRM and the FAA’s 

response to each comment. 

Request To Use Different Figures 

FedEx Express noted that its 757 fleet 

has been modified by VT MAE STC 

ST03562AT, passenger-to-freighter 

modification for Model 757–200 series 

airplanes, which adds a main deck cargo 

door to the airplane. After consultation 

with the STC holder, FedEx Express 

requested modifications for Groups 1, 2, 

and 3 of Boeing Alert Requirements 

Bulletin 757–53A0115, dated January 

25, 2022, for airplanes modified by VT 

MAE STC ST03562AT. FedEx Express 

requested using the different figures 

from the requirements bulletin for the 

factory freighter airplanes along with 

shorter repeat intervals associated with 

those figures. FedEx Express stated that 

all other figures along with the method 

of inspections called out in the 

requirements bulletin will be complied 

with according to their respective 

effectivity. 

The FAA finds no justification for 

airplanes modified by VT MAE STC 

ST03562AT to utilize the inspections, 

methods, and intervals in Groups 1, 2, 

and 3 of Boeing Alert Requirements 

Bulletin 757–53A0115, dated January 

25, 2022. FedEx did not provide 

sufficient justification and data for 

airplanes modified by VT MAE STC 

ST03562AT to support a revision to this 

AD. Operators must request approval of 

an alternative method of compliance 

(AMOC) for airplanes modified by VT 

MAE STC ST03562AT to address the 

unsafe condition of this AD and comply 

with its requirements. For those 

airplanes, the FAA has added paragraph 

(h)(4) of this AD to provide an exception 

to the actions specified in Boeing Alert 

Requirements Bulletin 757–53A0115, 

dated January 25, 2022. 

Comment Regarding Compliance Time 

United stated that the proposed 

requirement to divide the applicable 

compliance times and repeat intervals 

specified in Boeing Alert Requirements 

Bulletin 757–53A0115, dated January 

25, 2022, by a factor of two is excessive 

and could create an undue burden on 

the operators. United added that the 

FAA did not provide details regarding 

how it determined requiring a reduction 

in compliance by a factor of two. United 

understood that a reduction is necessary 

because APB does not yet have an 

approved service bulletin to provide its 

compliance requirements. However, 

United believed the reduction required 

by APB will likely show a factor of two 

is not an accurate determination. 

EATL stated the proposed exception 

in paragraph (h)(3) of the proposed AD 

includes strong penalties for airplanes 

equipped with winglets, as modified by 

APB STC ST01518SE. EATL noted 

Boeing and APB usually work closely 

together to align impacts generated by 

installation of winglets, which is then 

included in the compliance tables of the 

requirements bulletin. EATL added that 

Boeing Alert Requirements Bulletin 

757–53A0115, dated January 25, 2022, 

does not include such penalties or any 

indication that installation of winglets 

affects the compliance times. 

EATL stated the proposed exception 

in paragraph (h)(3) of the proposed AD 

would prevent airplanes equipped with 

winglets, as modified by APB STC 

ST01518SE, from scheduling the 

inspections required by this AD during 

base maintenance events. EATL 

requested that the FAA re-evaluate 

halving the applicable compliance times 

and repeat intervals specified in Boeing 

Alert Requirements Bulletin 757– 

53A0115, dated January 25, 2022. 

The FAA stated the reduction in 

compliance by a factor of two is to allow 

for APB to complete its evaluation of 

airplanes with APB STC ST01518SE 

installed. The FAA determined this is a 

conservative and appropriate 

compliance time for this AD. No 

changes have been made to this AD in 

this regard. 

Conclusion 

The FAA reviewed the relevant data, 

considered any comments received, and 

determined that air safety requires 

adopting this AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. Except for minor editorial 

changes, and any other changes 

described previously, this AD is 

adopted as proposed in the SNPRM. 

None of the changes will increase the 

economic burden on any operator. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

The FAA reviewed Boeing Alert 

Requirements Bulletin 757–53A0115 

RB, dated January 25, 2022. This 

material specifies procedures for a 

general visual inspection (GVI) or 

records review between stringers S–13 

and S–14 in Sections 43 and 46 for 

existing repairs. This material also 

describes procedures, depending on the 

configuration, for repetitive high 

frequency eddy current (HFEC) and low 

frequency eddy current (LFEC) 

inspections for cracking of the upper 

frames and splice doublers at the frame 

splices between stringers S–13 and S– 

14, left- and right-hand sides, in 

Sections 43 and 46; and applicable oncondition actions. On-condition actions 

include repair. 

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 456 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 

GVI .............................................. 2 work-hours × $85 per hour = 

$170 per inspection cycle.

$0 $170 per inspection cycle ......... $77,520 per inspection cycle. 

Repetitive Inspections ................. Up to 267 work-hours × $85 per 

hour = Up to $22,695 per inspection cycle.

0 Up to $22,695 per inspection 

cycle.

Up to $10,348,920 per inspection cycle. 


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97496 Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Rules and Regulations 

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 

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: 

2024–24–01 The Boeing Company: 

Amendment 39–22891; Docket No. 

FAA–2023–1053; Project Identifier AD– 

2023–00164–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 13, 2025. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 757–200, –200CB, and –200PF series 

airplanes, certificated in any category, as 

identified in Boeing Alert Requirements 

Bulletin 757–53A0115 RB, dated January 25, 

2022. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a crack growth 

analysis, which indicated that current 

inspections are not adequate to detect cracks 

in the Sections 43 and 46 upper frame at the 

frame splice between stringers S–13 and S– 

14 before a single frame fails. The FAA is 

issuing this AD to address cracking at the 

upper frames common to the splice at 

stringers S–13 to S–14, which could interact 

with fuselage skin cracking at the stringer S– 

14 lap splice. The unsafe condition, if not 

addressed, could result in the inability of a 

principal structural element to sustain limit 

loads, and 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 757–53A0115 RB, 

dated January 25, 2022, do all applicable 

actions identified in, and in accordance with, 

the Accomplishment Instructions of Boeing 

Alert Requirements Bulletin 757–53A0115 

RB, dated January 25, 2022. 

Note 1 to paragraph (g): Guidance for 

accomplishing the actions required by this 

AD can be found in Boeing Alert Service 

Bulletin 757–53A0115, dated January 25, 

2022, which is referred to in Boeing Alert 

Requirements Bulletin 757–53A0115 RB, 

dated January 25, 2022. 

(h) Exceptions to Service Information 

Specifications 

(1) Where the Compliance Time columns 

of the tables in the ‘‘Compliance’’ paragraph 

of Boeing Alert Requirements Bulletin 757– 

53A0115 RB, dated January 25, 2022, use the 

phrase ‘‘the original issue date of 

Requirements Bulletin 757–53A0115 RB,’’ 

this AD requires using the effective date of 

this AD. 

(2) Where Boeing Alert Requirements 

Bulletin 757–53A0115 RB, dated January 25, 

2022, specifies contacting Boeing for repair 

instructions or for alternative inspections: 

This AD requires doing the repair and doing 

the alternative inspections and applicable oncondition actions using a method approved 

in accordance with the procedures specified 

in paragraph (i) of this AD. 

(3) For airplanes on which winglet 

structural provisions (original equipment 

manufacturer (OEM) wingtips) or Aviation 

Partners Boeing (APB) winglets have been 

installed in accordance with APB 

Supplemental Type Certificate (STC) 

ST01518SE: This AD requires dividing the 

applicable compliance times and repeat 

intervals specified in the ‘‘Compliance’’ 

paragraph of Boeing Requirements Bulletin 

757–53A0115 RB, dated January 25, 2022, by 

a factor of two. 

(4) For airplanes modified by VT MAE STC 

ST03562AT: Where paragraph (g) of this AD 

requires doing ‘‘all applicable actions 

identified in, and in accordance with, the 

Accomplishment Instructions of Boeing Alert 

Requirements Bulletin 757–53A0115 RB, 

dated January 25, 2022,’’ this AD requires 

obtaining inspection instructions and 

applicable repair instructions in accordance 

with the procedures specified in paragraph 

(i) of this AD at the later of the compliance 

times specified in paragraphs (h)(4)(i) and (ii) 

of this AD. Comply with all applicable 

instructions at the time specified in the 

instructions. 

(i) Before 50,000 total flight cycles. 

(ii) Within 2,500 flight cycles after the 

effective date of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, AIR–520, Continued 

Operational Safety 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 (j)(1) of this AD. 

Information may be emailed to: AMOC@

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, AIR–520, Continued Operational 

Safety Branch, 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 Wayne Ha, Aviation Safety Engineer, 


ddrumheller on DSK120RN23PROD with RULES1
Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Rules and Regulations 97497 

Continued Operational Safety Branch, FAA, 

2200 South 216th Street, Des Moines, WA 

98198; phone: 562–627–5238; email: 

wayne.ha@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the address specified in 

paragraph (k)(3) of this AD. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the material listed in this paragraph under 5 

U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use this material as 

applicable to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Boeing Alert Requirements Bulletin 

757–53A0115 RB, dated January 25, 2022. 

(ii) [Reserved] 

(3) For Boeing material 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; website myboeingfleet.com. 

(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. 

(5) You may view this material at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

visit www.archives.gov/federal-register/cfr/ 

ibr-locations or email fr.inspection@nara.gov. 

Issued on November 19, 2024. 

Peter A. White, 

Deputy Director, Integrated Certificate 

Management Division, Aircraft Certification 

Service. 

[FR Doc. 2024–28782 Filed 12–6–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–0468; Project 

Identifier MCAI–2023–00762–T; Amendment 

39–22898; AD 2024–24–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Canada Limited Partnership (Type 

Certificate Previously Held by C Series 

Aircraft Limited Partnership (CSALP); 

Bombardier, Inc.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Canada Limited Partnership 

Model BD–500–1A10 and BD–500– 

1A11 airplanes. This AD was prompted 

by multiple occurrences of pilot and copilot seats locking in a fore-aft position 

due to the seat fore-aft adjustment 

mechanism disconnecting, caused by a 

broken cotter pin in the seat base egress 

linkage. This AD requires modifying the 

pilot and co-pilot seats by replacing the 

hardware of the seat base egress linkage, 

as specified in a Transport Canada 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 January 13, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 13, 2025. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–0468; 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, the mandatory 

continuing airworthiness information 

(MCAI), 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. 

Material Incorporated by Reference: 

• For Transport Canada material 

identified in this AD, contact Transport 

Canada, Transport Canada National 

Aircraft Certification, 159 Cleopatra 

Drive, Nepean, Ontario K1A 0N5, 

Canada; telephone 888–663–3639; email 

TC.AirworthinessDirectivesConsignesdenavigabilite.TC@tc.gc.ca. 

You may find this material on the 

Transport Canada website at 

tc.canada.ca/en/aviation. 

• 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. 

It is also available at regulations.gov 

under Docket No. FAA–2024–0468. 

FOR FURTHER INFORMATION CONTACT: 

Fatin Saumik, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone 516–228– 

7300; email fatin.r.saumik@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 certain Airbus Limited 

Partnership Model BD–500–1A10 and 

BD–500–1A11 airplanes. The NPRM 

published in the Federal Register on 

March 21, 2024 (89 FR 20144). The 

NPRM was prompted by AD CF–2023– 

40, dated June 13, 2023, issued by 

Transport Canada, which is the aviation 

authority for Canada (Transport Canada 

AD CF–2023–40) (also referred to as the 

MCAI). The MCAI states that there have 

been in-service occurrences of pilot and 

co-pilot seats becoming locked in a foreaft position due to disconnection of the 

seat fore-aft adjustment mechanism 

caused by a broken cotter pin in the seat 

base egress linkage. 

In the NPRM, the FAA proposed to 

require modifying the pilot and co-pilot 

seats by replacing the hardware of the 

seat base egress, as specified in 

Transport Canada AD CF–2023–40. The 

FAA is issuing this AD to address the 

disconnection of the seat fore-aft 

adjustment mechanism caused by a 

broken cotter pin in the seat base egress 

linkage. The unsafe condition, if not 

addressed, could result in a significant 

increase in crew workload for continued 

safe flight and landing. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2024–0468. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

two commenters, including Collins 

Aerospace and Delta Airlines (Delta). 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request for Later-Approved Service 

Information 

Collins Aerospace and Delta 

requested that the FAA edit paragraph 

(h)(3) of the proposed AD so that it 

would allow the use of later service 

information. Paragraph (h)(3) of the 

proposed AD would mandate Goodrich 

Interiors Service Bulletin 1430–25–003, 

Revision C, dated November 22, 2022. 

The FAA disagrees with the request. 

Transport Canada AD CF–2023–40, 

dated June 13, 2023, refers to ‘‘Airbus 

Canada Service Bulletin (SB) BD500– 

251006, Issue 001, dated 05 April 2023, 

or later revisions approved by the Chief, 

Continuing Airworthiness, Transport 

Canada,’’ but does not specifically allow 

later-approved revisions of any service 

information cited in that Airbus Canada 

service bulletin. The FAA has not 

changed this AD as a result of this 

comment. 

Request for Clarification of Paragraph 

(h)(3) of Proposed AD 

Delta requested clarification of the 

wording in (h)(3) of the proposed AD 


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