Airworthiness Directives; The Boeing Company Airplanes, 55128-55130 [2024-14608]

Download as PDF 55128 Federal Register / Vol. 89, No. 128 / Wednesday, July 3, 2024 / Proposed Rules (i) Additional AD Provisions Bombardier, Inc.): Docket No. FAA– 2024–1703; Project Identifier MCAI– 2023–01054–T. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by August 19, 2024. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Canada Limited Partnership (Type Certificate previously held by C Series Aircraft Limited Partnership (CSALP); Bombardier, Inc.) Model BD–500–1A11 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 51, Standard practices/ structures. (e) Unsafe Condition This AD was prompted by a design review of aircraft structural and stress reports that resulted in a revision of operational loads for some aircraft flight phases, affecting certain aircraft sections. The FAA is issuing this AD to address in-service repairs in some structural areas that require verification, and possibly further repair. The unsafe condition, if not addressed, could result in negative margins for the load envelopes. (f) Compliance Comply with this AD within the compliance times specified, unless already done. khammond on DSKJM1Z7X2PROD with PROPOSALS (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, Transport Canada AD CF– 2023–70, dated October 5, 2023 (Transport Canada AD CF–2023–70). (h) Exception to Transport Canada AD CF– 2023–70 (1) Where Transport Canada AD CF–2023– 70 refers to its effective date, this AD requires using the effective date of this AD. (2) Where paragraph B. of Part I of Transport Canada AD CF–2023–70 specifies operators may use Airbus Canada source data, for this AD, any repair using Airbus Canada source data must be accomplished using a method approved by the Manager, International Validation Branch, FAA; or Transport Canada; or Airbus Canada Limited Partnership’s Transport Canada Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (3) Where the definition of ‘‘Affected Structure’’ in Transport Canada AD CF– 2023–70 specifies ‘‘as identified in Service Bulletin (SB) BD500–530012, Issue 001, dated 13 September 2023 or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada,’’ this AD requires replacing that text with ‘‘as identified in Airbus Canada Service Bulletin (SB) BD500–530012, Issue 001, dated September 13, 2023.’’ VerDate Sep<11>2014 19:24 Jul 02, 2024 Jkt 262001 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 (j) of this AD. Information may be emailed to: 9-AVS-NYACO-COS@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 Airbus Canada Limited Partnership’s Transport Canada DAO. If approved by the DAO, the approval must include the DAO-authorized signature. (j) Additional Information For more information about this AD, contact Deep Gaurav, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7300; email 9-avs-nyaco-cos@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Transport Canada AD CF–2023–70, dated October 5, 2023. (ii) [Reserved] (3) For Transport Canada AD CF–2023–70, 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 Transport Canada AD on the Transport Canada website at tc.canada.ca/ en/aviation. (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. PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 Issued on June 26, 2024. Suzanne Masterson, Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2024–14522 Filed 7–2–24; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–1882; Project Identifier AD–2024–00227–T] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747– 300, 747–400, 747–400D, 747–400F, 747SP, and 747SR series airplanes. This proposed AD was prompted by a report indicating cracks at eight fastener hole locations in the fuselage skin lap splice between certain stations (STAs) at certain stringers. This proposed AD would require repetitive inspections of the upper fastener row of the fuselage skin lap splice in a certain area for any crack, and applicable on-condition actions. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by August 19, 2024. SUMMARY: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2024–1882; or in person at ADDRESSES: E:\FR\FM\03JYP1.SGM 03JYP1 Federal Register / Vol. 89, No. 128 / Wednesday, July 3, 2024 / Proposed Rules Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, any comments received, and other information. The street address for Docket Operations is listed above. Material Incorporated by Reference: • For the material, 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–2024–1882. FOR FURTHER INFORMATION CONTACT: Stefanie Roesli, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206– 231–3964; email: Stefanie.N.Roesli@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2024–1882; Project Identifier AD–2024–00227–T’’ at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this proposal because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this NPRM. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Stefanie Roesli, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206–231–3964; email: Stefanie.N.Roesli@faa.gov. Any commentary that the FAA receives that is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background The FAA has received a report that cracking was found at eight fastener hole locations in the fuselage skin lap splice between STAs 1450 and 1470 at stringers S–23L and S–23R on a Boeing Model 747–400 series airplane that had completed 128,792 flight hours and 25,581 flight cycles when the cracks were discovered. The maximum crack length discovered was 0.946 inch. After this report was received, the Boeing Company did a high frequency eddy current inspection on the Boeing Model 747–100 fatigue test airplane and found cracks on the countersink area of the fastener holes on the lap splice between STAs 1416 and 1480 at stringers S–23L and S–23R. The maximum crack length 55129 discovered was 0.10 inch. The Boeing Model 747–100 fatigue test airplane had completed the equivalent of 45,000 flight cycles. Cracking in the fuselage skin lap splice, if not addressed, could result in an in-flight rapid decompression and a loss of structural integrity of the fuselage. FAA’s Determination The FAA is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design. Related Material Under 1 CFR Part 51 The FAA reviewed Boeing Alert Requirements Bulletin 747–53A2912 RB, dated April 5, 2024. This material specifies procedures for repetitive external surface high frequency eddy current inspections of the upper fastener row of the fuselage skin lap splice between STAs 1350 and 1480 at stringers S–23L and S–23R for any crack, and applicable on-condition actions. On-condition actions include obtaining and following repair instructions. 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. Proposed AD Requirements in This NPRM This proposed AD would require accomplishing the actions specified in the material already described, except for any differences identified as exceptions in the regulatory text of this proposed AD. For information on the procedures and compliance times, see this material at regulations.gov under Docket No. FAA–2024–1882. Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 170 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: khammond on DSKJM1Z7X2PROD with PROPOSALS ESTIMATED COSTS Action Labor cost Inspections ............................. 8 work-hours × $85 per hour = $680 per inspection cycle. The FAA has received no definitive data on which to base the cost estimates for the on-condition actions specified in this proposed AD. VerDate Sep<11>2014 19:24 Jul 02, 2024 Jkt 262001 Parts cost $0 Cost per product Cost on U.S. operators $680 per inspection cycle ...... $115,600 per inspection cycle Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. E:\FR\FM\03JYP1.SGM 03JYP1 55130 Federal Register / Vol. 89, No. 128 / Wednesday, July 3, 2024 / Proposed Rules 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 The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Would not affect intrastate aviation in Alaska, and (3) Would 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 Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: (c) Applicability This AD applies to The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SP, and 747SR series airplanes, certificated in any category, as identified in Boeing Alert Requirements Bulletin 747–53A2912 RB, dated April 5, 2024. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a report indicating cracks at eight fastener hole locations in the fuselage skin lap splice between stations (STAs) 1450 and 1470 at stringers S–23L and S–23R. The FAA is issuing this AD to detect and correct cracking of the upper fastener row of the fuselage skin lap splice between STAs 1350 and 1480 at stringers S–23L and S–23R. The unsafe condition, if not addressed, could result in an in-flight rapid decompression and a loss of structural integrity of the fuselage. (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 747–53A2912 RB, dated April 5, 2024, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 747–53A2912 RB, dated April 5, 2024. Note 1 to paragraph (g): Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin 747–53A2912, dated April 5, 2024, which is referred to in Boeing Alert Requirements Bulletin 747–53A2912 RB, dated April 5, 2024. The Boeing Company: Docket No. FAA– 2024–1882; Project Identifier AD–2024– 00227–T. (h) Exceptions to Service Information Specifications (1) Where the Condition and Boeing Recommended Compliance Time columns of the tables in the ‘‘Compliance’’ paragraph of Boeing Alert Requirements Bulletin 747– 53A2912 RB, dated April 5, 2024, refer to ‘‘the Original Issue date of the Requirements Bulletin 747–53A2912 RB,’’ this AD requires using the effective date of this AD. (2) Where Boeing Alert Requirements Bulletin 747–53A2912 RB, dated April 5, 2024, specifies contacting Boeing for repair instructions: This AD requires doing the repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by August 19, 2024. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, AIR–520, Continued Operational Safety Branch, FAA, has the 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: ■ khammond on DSKJM1Z7X2PROD with PROPOSALS (b) Affected ADs None. VerDate Sep<11>2014 19:24 Jul 02, 2024 Jkt 262001 PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 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 Stefanie Roesli, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206–231–3964; email: Stefanie.N.Roesli@faa.gov. (2) Material identified in this AD that is not incorporated by reference is available at the address specified in paragraph (k)(3) 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 747–53A2912 RB, dated April 5, 2024. (ii) [Reserved] (3) For Boeing material, 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 June 27, 2024. Suzanne Masterson, Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2024–14608 Filed 7–2–24; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\03JYP1.SGM 03JYP1

Agencies

[Federal Register Volume 89, Number 128 (Wednesday, July 3, 2024)]
[Proposed Rules]
[Pages 55128-55130]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-14608]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-1882; Project Identifier AD-2024-00227-T]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 
747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 
747SP, and 747SR series airplanes. This proposed AD was prompted by a 
report indicating cracks at eight fastener hole locations in the 
fuselage skin lap splice between certain stations (STAs) at certain 
stringers. This proposed AD would require repetitive inspections of the 
upper fastener row of the fuselage skin lap splice in a certain area 
for any crack, and applicable on-condition actions. The FAA is 
proposing this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by August 19, 
2024.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to regulations.gov. Follow 
the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2024-1882; or in person at

[[Page 55129]]

Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this NPRM, any comments 
received, and other information. The street address for Docket 
Operations is listed above.
    Material Incorporated by Reference:
     For the material, 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-2024-1882.

FOR FURTHER INFORMATION CONTACT: Stefanie Roesli, Aviation Safety 
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-
231-3964; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2024-1882; 
Project Identifier AD-2024-00227-T'' at the beginning of your comments. 
The most helpful comments reference a specific portion of the proposal, 
explain the reason for any recommended change, and include supporting 
data. The FAA will consider all comments received by the closing date 
and may amend this proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
regulations.gov, including any personal information you provide. The 
agency will also post a report summarizing each substantive verbal 
contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to 
Stefanie Roesli, Aviation Safety Engineer, FAA, 2200 South 216th St., 
Des Moines, WA 98198; phone: 206-231-3964; email: 
[email protected]. Any commentary that the FAA receives that is 
not specifically designated as CBI will be placed in the public docket 
for this rulemaking.

Background

    The FAA has received a report that cracking was found at eight 
fastener hole locations in the fuselage skin lap splice between STAs 
1450 and 1470 at stringers S-23L and S-23R on a Boeing Model 747-400 
series airplane that had completed 128,792 flight hours and 25,581 
flight cycles when the cracks were discovered. The maximum crack length 
discovered was 0.946 inch. After this report was received, the Boeing 
Company did a high frequency eddy current inspection on the Boeing 
Model 747-100 fatigue test airplane and found cracks on the countersink 
area of the fastener holes on the lap splice between STAs 1416 and 1480 
at stringers S-23L and S-23R. The maximum crack length discovered was 
0.10 inch. The Boeing Model 747-100 fatigue test airplane had completed 
the equivalent of 45,000 flight cycles. Cracking in the fuselage skin 
lap splice, if not addressed, could result in an in-flight rapid 
decompression and a loss of structural integrity of the fuselage.

FAA's Determination

    The FAA is issuing this NPRM after determining that the unsafe 
condition described previously is likely to exist or develop on other 
products of the same type design.

Related Material Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Requirements Bulletin 747-53A2912 RB, 
dated April 5, 2024. This material specifies procedures for repetitive 
external surface high frequency eddy current inspections of the upper 
fastener row of the fuselage skin lap splice between STAs 1350 and 1480 
at stringers S-23L and S-23R for any crack, and applicable on-condition 
actions. On-condition actions include obtaining and following repair 
instructions.
    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.

Proposed AD Requirements in This NPRM

    This proposed AD would require accomplishing the actions specified 
in the material already described, except for any differences 
identified as exceptions in the regulatory text of this proposed AD. 
For information on the procedures and compliance times, see this 
material at regulations.gov under Docket No. FAA-2024-1882.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 170 airplanes of U.S. registry. The FAA estimates the following 
costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections......................  8 work-hours x $85               $0  $680 per inspection  $115,600 per
                                    per hour = $680                      cycle.               inspection cycle
                                    per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition actions specified in this proposed 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.

[[Page 55130]]

    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

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would 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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

The Boeing Company: Docket No. FAA-2024-1882; Project Identifier AD-
2024-00227-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by August 19, 2024.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, 747SP, and 747SR series airplanes, certificated in 
any category, as identified in Boeing Alert Requirements Bulletin 
747-53A2912 RB, dated April 5, 2024.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by a report indicating cracks at eight 
fastener hole locations in the fuselage skin lap splice between 
stations (STAs) 1450 and 1470 at stringers S-23L and S-23R. The FAA 
is issuing this AD to detect and correct cracking of the upper 
fastener row of the fuselage skin lap splice between STAs 1350 and 
1480 at stringers S-23L and S-23R. The unsafe condition, if not 
addressed, could result in an in-flight rapid decompression and a 
loss of structural integrity of the fuselage.

(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 747-53A2912 RB, dated April 5, 2024, do 
all applicable actions identified in, and in accordance with, the 
Accomplishment Instructions of Boeing Alert Requirements Bulletin 
747-53A2912 RB, dated April 5, 2024.

    Note 1 to paragraph (g):  Guidance for accomplishing the actions 
required by this AD can be found in Boeing Alert Service Bulletin 
747-53A2912, dated April 5, 2024, which is referred to in Boeing 
Alert Requirements Bulletin 747-53A2912 RB, dated April 5, 2024.

(h) Exceptions to Service Information Specifications

    (1) Where the Condition and Boeing Recommended Compliance Time 
columns of the tables in the ``Compliance'' paragraph of Boeing 
Alert Requirements Bulletin 747-53A2912 RB, dated April 5, 2024, 
refer to ``the Original Issue date of the Requirements Bulletin 747-
53A2912 RB,'' this AD requires using the effective date of this AD.
    (2) Where Boeing Alert Requirements Bulletin 747-53A2912 RB, 
dated April 5, 2024, specifies contacting Boeing for repair 
instructions: This AD requires doing the repair using a method 
approved in accordance with the procedures specified in paragraph 
(i) 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: [email protected].
    (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 Stefanie Roesli, 
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 
98198; phone: 206-231-3964; email: [email protected].
    (2) Material identified in this AD that is not incorporated by 
reference is available at the address specified in paragraph (k)(3) 
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 747-53A2912 RB, dated 
April 5, 2024.
    (ii) [Reserved]
    (3) For Boeing material, 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 [email protected].

    Issued on June 27, 2024.
Suzanne Masterson,
Deputy Director, Integrated Certificate Management Division, Aircraft 
Certification Service.
[FR Doc. 2024-14608 Filed 7-2-24; 8:45 am]
BILLING CODE 4910-13-P
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