Federal Register / Vol. 89, No. 231 / Monday, December 2, 2024 / Rules and Regulations 95095 

(e) Unsafe Condition 

This AD was prompted by a report of a 

non-conforming installation of spoiler wire 

bundles that led to unintended spoiler 

motion, including one instance of a flight 

spoiler hardover. Further investigation 

identified the potential for a time-limited 

hardover of more than one flight spoiler on 

the same wing, which can exceed full lateral 

control capability leading to loss of control 

of the airplane. The FAA is issuing this AD 

to address improper clearance between the 

spoiler control wire bundles and the adjacent 

structure, which can lead to damage to the 

wire bundle, causing unintentional spoiler 

motion. The unsafe condition, if not 

addressed, could result in loss of control 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 737–27A1325 RB, 

dated July 14, 2023, do all applicable actions 

identified in, and in accordance with, the 

Accomplishment Instructions of Boeing Alert 

Requirements Bulletin 737–27A1325 RB, 

dated July 14, 2023. 

Note 1 to paragraph (g): Guidance for 

accomplishing the actions required by this 

AD can be found in Boeing Alert Service 

Bulletin 737–27A1325, dated July 14, 2023, 

which is referred to in Boeing Alert 

Requirements Bulletin 737–27A1325 RB, 

dated July 14, 2023. 

(h) Exception to Service Information 

Specifications 

Where the Compliance Time columns of 

the tables in the ‘‘Compliance’’ paragraph of 

Boeing Alert Requirements Bulletin 737– 

27A1325 RB, dated July 14, 2023, use the 

phrase ‘‘the original issue date of 

Requirements Bulletin 737–27A1325 RB,’’ 

this AD requires using 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, 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 Michael Closson, Aviation Safety 

Engineer, FAA, 2200 South 216th St., Des 

Moines, WA 98198; phone: 206–231–3973; 

email: Michael.P.Closson@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 

(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 the AD specifies otherwise. 

(i) Boeing Alert Requirements Bulletin 

737–27A1325 RB, dated July 14, 2023. 

(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 14, 2024. 

John P. Piccola, Jr., 

Director, Integrated Certificate Management 

Division, Aircraft Certification Service. 

[FR Doc. 2024–28120 Filed 11–29–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2015; Project 

Identifier MCAI–2023–00769–T; Amendment 

39–22887; AD 2024–23–08] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc., Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc., Model BD–700–1A10 

and BD–700–1A11 airplanes. This AD 

was prompted by reports of missing or 

damaged inboard flap seal plate 

assemblies. This AD requires repetitive 

inspections for cracks of the attaching 

angles of the inboard flap seal plates 

and replacement. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective January 6, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 6, 2025. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–2015; 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 Bombardier material identified 

in this AD, contact Bombardier Business 

Aircraft Customer Response Center, 400 

Coˆte-Vertu Road West, Dorval, Que ́bec 

H4S 1Y9, Canada; telephone 514–855– 

2999; email ac.yul@

aero.bombardier.com; website 

bombardier.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–2024–2015. 

FOR FURTHER INFORMATION CONTACT: 

Yaser Osman, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 516– 

228–7300; email 9-avs-nyaco-cos@

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 Bombardier, Inc., Model 

BD–700–1A10 and BD–700–1A11 

airplanes. The NPRM published in the 


ddrumheller on DSK120RN23PROD with RULES1
95096 Federal Register / Vol. 89, No. 231 / Monday, December 2, 2024 / Rules and Regulations 

Federal Register on August 9, 2024 (89 

FR 65264). The NPRM was prompted by 

AD CF–2023–42, dated June 19, 2023, 

issued by Transport Canada, which is 

the aviation authority for Canada 

(referred to after this as the MCAI). The 

MCAI states that there have been 

multiple reports in service of missing or 

damaged inboard flap seal plates. An 

investigation revealed a premature 

fatigue failure mode of the inboard flap 

seal plates. Left uncorrected, an inboard 

flap seal plate may partially or totally 

detach. Under certain flight conditions, 

a missing inboard flap seal plate could 

lead to excessive buffeting and 

vibration, and consequent damage to the 

airplane. 

In the NPRM, the FAA proposed to 

require repetitive inspections for cracks 

of the attaching angles of the inboard 

flap seal plates and replacement. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2024–2015. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the cost to the public. 

Conclusion 

This product has been approved by 

the aviation authority of another 

country and is approved for operation in 

the United States. Pursuant to the FAA’s 

bilateral agreement with this State of 

Design Authority, it has notified the 

FAA of the unsafe condition described 

in the MCAI referenced above. The FAA 

reviewed the relevant data and 

determined that air safety requires 

adopting this AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on this 

product. 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. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

The FAA reviewed Bombardier 

Service Bulletins 700–27–5509 and 

700–27–6509, both Revision 01, both 

dated May 5, 2023. This material 

specifies procedures for repetitive 

detailed inspections for cracks of the 

attaching angles of the inboard flap seal 

plates and replacing the inboard flap 

seal plates if any crack is detected. This 

material also specifies procedures for 

replacing both existing inboard flap seal 

plates with structurally more robust 

redesigned components. The 

replacement actions include a detailed 

visual inspection for damage (including 

signs of failure, cracking, and 

deformation) of the flap inboard closing 

ribs and trailing edges, an eddy current 

or liquid penetrant inspection for cracks 

running out of the flap inboard closing 

rib holes common to the outboard 

stiffener and angle, and repair for cracks 

and other damage. The replacement 

would eliminate the need for the 

repetitive detailed inspections. These 

documents are distinct since they apply 

to different airplane models. 

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 43 airplanes of U.S. registry. The 

FAA estimates the following costs to 

comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

24 work-hours × $85 per hour = $2,040 ..................................................................................... $37,919 $39,959 $1,718,237 

The FAA has received no definitive 

data on which to base the cost estimates 

for the repairs specified in this AD. 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some or all 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected operators. 

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. 


ddrumheller on DSK120RN23PROD with RULES1
Federal Register / Vol. 89, No. 231 / Monday, December 2, 2024 / Rules and Regulations 95097 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2024–23–08 Bombardier, Inc.: Amendment 

39–22887; Docket No. FAA–2024–2015; 

Project Identifier MCAI–2023–00769–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 6, 2025. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc., 

Model BD–700–1A10 and BD–700–1A11 

airplanes, certificated in any category, serial 

numbers 9861, 9872, 60001 through 60004 

inclusive, 60006 through 60023 inclusive, 

60025 through 60029 inclusive, 60031, 60033 

through 60036 inclusive, 60038 through 

60042 inclusive, 60044, 60046 through 60048 

inclusive, 60050 through 60055 inclusive, 

60058 through 60060 inclusive, 60062 

through 60067 inclusive, 60069 through 

60071 inclusive, 60073 through 60086 

inclusive, and 60088 through 60101 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

missing or damaged inboard flap seal plates. 

The FAA is issuing this AD to address the 

unsafe condition, which could result in the 

partial or total detachment of the flap seal 

plate. Under certain flight conditions, a 

missing inboard flap seal plate could lead to 

excessive buffeting and vibration, and 

consequent damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Detailed Inspection 

At the applicable time specified in figure 

1 to paragraph (g) of this AD, perform a 

detailed inspection for cracks of the attaching 

angles of the inboard flap seal plates, in 

accordance with Section 2.B. (Part A) of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 700–27–5509 or 700–27– 

6509, both Revision 01, both dated May 5, 

2023, as applicable, except do corrective 

actions as specified in paragraph (h) of this 

AD. 

FIGURE 1 TO PARAGRAPH (g)—COMPLIANCE REQUIREMENTS

Total flight hours as of the effective date of this AD Compliance time after the effective date of this AD 

Less than or equal to 750 ........................................................................ Within 250 flight hours. 

More than 750 .......................................................................................... Within 100 flight hours.

(h) Corrective Actions for Inboard Flap Seal 

Plates 

(1) If no crack is found during any 

inspection required by paragraph (g) of this 

AD, repeat the inspection thereafter at 

intervals not to exceed 250 flight hours, 

except as specified in paragraph (i) of this 

AD. 

(2) If any crack is found during any 

inspection required by paragraph (g) of this 

AD, do the actions specified in paragraph (i) 

of this AD before further flight. 

(i) Replacement of Inboard Flap Seal Plates 

Unless already done as specified in 

paragraph (h)(2) of this AD: Within 12 

months after the effective date of this AD, do 

the actions specified in paragraphs (i)(1) 

through (3) of this AD, in accordance with 

Section 2.C. (Part B) of the Accomplishment 

Instructions of Bombardier Service Bulletin 

700–27–5509 or 700–27–6509, both Revision 

01, both dated May 5, 2023, as applicable. 

(1) Replace the inboard flap seal plates 

with redesigned plates. 

(2) Do a detailed visual inspection for 

damage of the flap inboard closing ribs and 

trailing edges. 

(3) Do an eddy current or liquid penetrant 

inspection for cracks running out of the flap 

inboard closing rib holes common to the 

outboard stiffener and angle. 

(j) Repair for Flap Inboard Closing Ribs and 

Trailing Edges 

If any crack or other damage is found 

during any inspection required by paragraph 

(i)(2) or (3) of this AD, repair before further 

flight using a method approved by the 

Manager, International Validation Branch, 

FAA; or Transport Canada; or Bombardier, 

Inc.’s Transport Canada Design Approval 

Organization (DAO). If the method is 

approved by the DAO, the approval must 

include the DAO-authorized signature. 

(k) Terminating Action for Repetitive 

Inspections 

Accomplishment of the actions required by 

paragraph (i) of this AD terminates the 

requirements of paragraph (h)(1) of this AD. 

(l) Credit for Previous Actions 

This paragraph provides credit for actions 

required by this AD, if those actions were 

performed before the effective date of this AD 

using Bombardier Service Bulletin 700–27– 

5509 or 700–27–6509, both dated October 4, 

2022. 

(m) No Reporting Requirement 

Although Bombardier Service Bulletins 

700–27–5509 and 700–27–6509, both 

Revision 01, both dated May 5, 2023, specify 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(n) 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 (o)(1) 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 Transport Canada; or 

Bombardier, Inc.’s Transport Canada Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(o) Additional Information 

(1) For more information about this AD, 

contact Yaser Osman, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 516– 

228–7300; email 9-avs-nyaco-cos@faa.gov. 

(2) Material identified in this AD that is not 

incorporated by reference is available at the 

address specified in paragraph (p)(3) of this 

AD. 

(p) 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 this AD specifies otherwise. 

(i) Bombardier Service Bulletin 700–27– 

5509, Revision 01, dated May 5, 2023. 

(ii) Bombardier Service Bulletin 700–27– 

6509, Revision 01, dated May 5, 2023. 

(3) For Bombardier material identified in 

this AD, contact Bombardier Business 

Aircraft Customer Response Center, 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–2999; email 

ac.yul@aero.bombardier.com; website 

bombardier.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 


ddrumheller on DSK120RN23PROD with RULES1
95098 Federal Register / Vol. 89, No. 231 / Monday, December 2, 2024 / Rules and Regulations 

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 12, 2024. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–28125 Filed 11–29–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–1474; Project 

Identifier MCAI–2023–01014–T; Amendment 

39–22884; AD 2024–23–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Canada Limited Partnership (Type 

Certificate Previously Held by C Series 

Aircraft Limited Partnership (CSALP)) 

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 reports that the pylon-to-wing area 

motive flow flexible fuel line assemblies 

may have been installed incorrectly. 

This AD requires inspecting the motive 

flow fuel line assemblies and 

performing corrective actions 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 6, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 6, 2025. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–1474; 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; 

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–2024–1474. 

FOR FURTHER INFORMATION CONTACT: 

Joseph Catanzaro, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; email 

joseph.catanzaro@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 Canada Limited 

Partnership Model BD–500–1A10 and 

BD–500–1A11 airplanes. The NPRM 

published in the Federal Register on 

May 23, 2024 (89 FR 45610). The NPRM 

was prompted by AD CF–2023–64, 

dated September 18, 2023, issued by 

Transport Canada, which is the aviation 

authority for Canada (referred to after 

this as the MCAI). The MCAI states that 

reports have been received indicating 

that the pylon-to-wing area motive flow 

flexible fuel line assemblies may have 

been installed incorrectly, potentially 

resulting in a twist to the motive flow 

fuel line. 

In the NPRM, the FAA proposed to 

require inspecting the motive flow fuel 

line assemblies and corrective actions, 

as specified in Transport Canada AD 

CF–2023–64. The FAA is issuing this 

AD to address a possible abrasion of the 

fuel line causing a fuel leak; if not 

addressed, the electrical harness 

connectors in the wing area could be a 

potential ignition source and pose a risk 

of fire. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2024–1474. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received a comment from 

Air Line Pilots Association, 

International (ALPA), who supported 

the NPRM without change. 

The FAA received an additional 

comment from Delta Airlines. The 

following presents the comment 

received on the NPRM and the FAA’s 

response to the comment. 

Request for Change to Exceptions 

Paragraph 

Delta requested revising paragraph 

(h)(3) by removing the word ‘‘flexible’’ 

and revising certain punctuation. Delta 

stated the term ‘‘flexible’’ is used only 

when referring to the flexible-hose 

assembly installed in the shroud 

assembly. Therefore, the flexible-hose 

assembly and the shroud assembly are 

subassemblies of the fuel motive-flow 

tube assembly. 

The FAA agrees that the term 

‘‘flexible’’ should be removed in 

reference to the entire motive flow fuel 

line assemblies since the service 

information referenced in Transport 

Canada AD CF–2023–64 requires 

replacement of the fuel motive-flow 

tube assembly if damage is found on 

either the flexible-hose assembly or the 

shroud assembly. 

Conclusion 

This product has been approved by 

the aviation authority of another 

country and is approved for operation in 

the United States. Pursuant to the FAA’s 

bilateral agreement with this State of 

Design Authority, it has notified the 

FAA of the unsafe condition described 

in the MCAI referenced above. The FAA 

reviewed the relevant data, considered 

the 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 this product. 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. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

The FAA reviewed AD CF–2023–64, 

dated September 18, 2023. This material 

specifies procedures for a general visual 

inspection of the left and right motive 

flow flexible fuel line assemblies for 

twisted or damaged fuel lines or 

damaged shrouds, and replacement of 

motive flow fuel line assemblies with 

twisted or damaged fuel lines or 

damaged shrouds. 

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. 


ddrumheller on DSK120RN23PROD with RULES1