Airworthiness Directives; Bombardier, Inc., Airplanes, 95095-95098 [2024-28125]

Download as PDF Federal Register / Vol. 89, No. 231 / Monday, December 2, 2024 / Rules and Regulations (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. ddrumheller on DSK120RN23PROD with RULES1 (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 VerDate Sep<11>2014 16:22 Nov 29, 2024 Jkt 265001 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 Federal Aviation Administration (FAA), DOT. AGENCY: PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 ACTION: 95095 Final rule. 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 Côte-Vertu Road West, Dorval, Québec 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. SUMMARY: 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 E:\FR\FM\02DER1.SGM 02DER1 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. ddrumheller on DSK120RN23PROD with RULES1 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 VerDate Sep<11>2014 16:22 Nov 29, 2024 Jkt 265001 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 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 (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. E:\FR\FM\02DER1.SGM 02DER1 Federal Register / Vol. 89, No. 231 / Monday, December 2, 2024 / Rules and Regulations § 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. 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. missing inboard flap seal plate could lead to excessive buffeting and vibration, and consequent damage to the airplane. (d) Subject 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. Air Transport Association (ATA) of America Code 57, Wings. (b) Affected ADs None. (e) Unsafe Condition (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, 95097 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 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Detailed Inspection 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 ........................................................................ More than 750 .......................................................................................... (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. ddrumheller on DSK120RN23PROD with RULES1 (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. VerDate Sep<11>2014 16:22 Nov 29, 2024 Jkt 265001 Within 250 flight hours. Within 100 flight hours. (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 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 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 CôteVertu Road West, Dorval, Québec 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 E:\FR\FM\02DER1.SGM 02DER1 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 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. ddrumheller on DSK120RN23PROD with RULES1 SUMMARY: VerDate Sep<11>2014 16:22 Nov 29, 2024 Jkt 265001 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. PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 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. E:\FR\FM\02DER1.SGM 02DER1

Agencies

[Federal Register Volume 89, Number 231 (Monday, December 2, 2024)]
[Rules and Regulations]
[Pages 95095-95098]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-28125]


-----------------------------------------------------------------------

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 C[ocirc]te-
Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, Canada; telephone 514-
855-2999; email bombardier.com">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 [email protected].

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

[[Page 95096]]

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
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
24 work-hours x $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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

[[Page 95097]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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     Compliance time after the
            date of this AD                 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: 
[email protected]. 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 [email protected].
    (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 
C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, Canada; 
telephone 514-855-2999; email bombardier.com">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

[[Page 95098]]

Administration (NARA). For information on the availability of this 
material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    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

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