Airworthiness Directives; Piper Aircraft, Inc. Airplanes, 44914-44917 [2024-11143]

Download as PDF 44914 Federal Register / Vol. 89, No. 100 / Wednesday, May 22, 2024 / Rules and Regulations If the Administrator finds that the applicable airworthiness regulations (e.g., 14 CFR part 25) do not contain adequate or appropriate safety standards for the Textron Model 550 (Bravo), 560 (Ultra Encore), and 560XL (Excel) airplane because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16. Special conditions are initially applicable to the model for which they are issued. Should the applicant apply for a supplemental type certificate to modify any other model included on the same type certificate to incorporate the same novel or unusual design feature, these special conditions would also apply to the other model under § 21.101. In addition to the applicable airworthiness regulations and special conditions, the Textron Aviation Inc. Model 550 (Bravo), 560 (Ultra Encore), and 560XL (Excel) airplane must comply with the exhaust-emission requirements of 14 CFR part 34, and the noise-certification requirements of 14 CFR part 36. The FAA issues special conditions, as defined in 14 CFR 11.19, in accordance with § 11.38, and they become part of the type certification basis under § 21.101. khammond on DSKJM1Z7X2PROD with RULES Novel or Unusual Design Features The STC requested by ADC for the Textron Model 550 (Bravo), 560 (Ultra Encore), and 560XL (Excel) series airplane will incorporate the following novel or unusual design feature: the installation of a digital system that contains a wireless and hardwired network with hosted application functionality that allows access, from sources internal to the airplane, to the airplane’s internal electronic components. Discussion The Textron Model 550 (Bravo), 560 (Ultra Encore), and 560XL (Excel) series airplane system architecture and network configuration change proposed by ADC is novel or unusual for transport category airplanes because it is composed of several connected wireless and hardwired networks. This system and network architecture is used for a diverse set of airplane functions including: • Flight safety related control and navigation systems; • Airline business and administrative support; and • Passenger entertainment. The airplane’s control domain and airline information-services domain of these networks perform functions required for the safe operation and VerDate Sep<11>2014 15:39 May 21, 2024 Jkt 262001 maintenance of the airplane. Previously, these domains had very limited connectivity with other network sources. This network architecture creates a potential for unauthorized persons to access the airplane-control domain and airline information-services domain from sources internal to the airplane and presents security vulnerabilities related to the introduction of computer viruses and worms, user errors, and intentional sabotage of airplane electronic assets (networks, systems, and databases) critical to the safety and maintenance of the airplane. The applicable FAA regulations did not anticipate these networked airplane system architectures. Furthermore, these regulations and the current guidance material do not address potential security vulnerabilities, which could be exploited by unauthorized access to airplane networks, data buses, and servers. Therefore, these special conditions ensure that the security (i.e., confidentiality, integrity, and availability) of airplane systems will not be compromised by unauthorized hardwired or wireless electronic connections from within the airplane. These special conditions also require the applicant to provide appropriate instructions to the operator to maintain all electronic-system safeguards that have been implemented as part of the original network design so that this feature does not allow or reintroduce security threats. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards. Applicability As discussed above, these special conditions are applicable to the Textron Model 550 (Bravo), 560 (Ultra Encore), and 560XL (Excel) series airplane, as proposed to be modified by ADC. Should ADC apply at a later date for a supplemental type certificate to modify any other model included on Type Certificate No. A22CE to incorporate the same novel or unusual design feature, these special conditions would apply to that model as well. Conclusion This action affects only a certain novel or unusual design feature of ADC’s proposed STC for the Textron Model 550 (Bravo), 560 (Ultra Encore), and 560XL (Excel) series of airplane. It is not a rule of general applicability and affects only the applicant who applied PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 to the FAA for approval of that feature on the airplane. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. Authority Citation The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701, 44702, and 44704. The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for Textron Model 550 (Bravo), 560 (Ultra Encore), and 560XL (Excel) series airplanes, as modified by ADC, for airplane electronic-system internal access: 1. The applicant must ensure that the design provides isolation from, or airplane electronic network system security protection against, access by unauthorized sources internal to the airplane. The design must prevent inadvertent and malicious changes to, and all adverse impacts upon, airplane equipment, systems, networks, or other assets required for safe flight and operations. 2. The applicant must establish appropriate procedures to allow the operator to ensure that continued airworthiness of the airplane is maintained, including all post type certification modifications that may have an impact on the approved electronic network system security safeguards. Issued in Kansas City, Missouri, on May 9, 2024. Patrick R. Mullen, Manager, Technical Policy Branch, Policy and Standards Division, Aircraft Certification Service. [FR Doc. 2024–10500 Filed 5–21–24; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–1302; Project Identifier AD–2024–00213–A; Amendment 39–22749; AD 2024–10–04] RIN 2120–AA64 Airworthiness Directives; Piper Aircraft, Inc. Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: E:\FR\FM\22MYR1.SGM 22MYR1 Federal Register / Vol. 89, No. 100 / Wednesday, May 22, 2024 / Rules and Regulations Final rule; request for comments. ACTION: The FAA is adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Model PA– 28–181, PA–28R–201, PA–34–220T, and PA–44–180 airplanes. This AD was prompted by a report of a double-drilled bolt hole of the rear wing spar attachment fitting found during an unscheduled inspection of an airplane due to a ground collision with an automobile. This AD requires inspecting the rear wing spar attachment fitting and, if discrepancies are found, inspecting the forward wing spar attachment fitting, accomplishing corrective actions as required, and reporting to the FAA when corrective actions are required. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 6, 2024. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 6, 2024. The FAA must receive comments on this AD by July 8, 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–2024–1302; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, any comments received, and other information. The street address for Docket Operations is listed above. Material Incorporated by Reference: • For service information, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, FL 32960; phone: (772) 567–4361; email: customerservice@ piper.com; website: piper.com. • You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, khammond on DSKJM1Z7X2PROD with RULES SUMMARY: VerDate Sep<11>2014 15:39 May 21, 2024 Jkt 262001 call (817) 222–5110. It is also available at regulations.gov under Docket No. FAA–2024–1302. Fred Caplan, Aviation Safety Engineer, FAA, East Certification Branch, FAA, 1701 Columbia Avenue, College Park, GA 30337; phone: (404) 474–5507; email: 9ASO-ATLACO-ADs@faa.gov. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2024–1302; Project Identifier AD–2024–00213–A’’ at the beginning of your comments. The most helpful comments reference a specific portion of the final rule, 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 final rule 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 final rule. 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 AD 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 AD, 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 AD. Submissions containing CBI should be sent to Fred Caplan, Aviation Safety Engineer, FAA, East Certification Branch, FAA, 1701 Columbia Avenue, College Park, GA 30337. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 44915 Background The FAA is issuing this AD to correct an unsafe condition on certain serialnumbered Piper Model PA–28–181, PA– 28R–201, PA–34–220T, and PA–44–180 airplanes. The FAA received a report that a double-drilled bolt hole of the rear wing spar attachment fitting was found during an unscheduled inspection of an airplane due to a ground collision with an automobile. This was the result of an error made during manufacturing. A double-drilled bolt hole of the rear wing spar attachment fitting reduces its strength below its limit load with possible failure of the fitting, which can lead to load redistribution and result in possible failure of the primary wing structure. This condition, if not addressed, could result in separation of the wing and loss of control of the airplane. The FAA is issuing this AD to address the unsafe condition on these products. FAA’s Determination The FAA is issuing this AD because the agency has determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Related Service Information Under 1 CFR Part 51 The FAA reviewed Piper Service Bulletin No. 1413, dated April 9, 2024 (Piper Service Bulletin No. 1413). This service information specifies procedures for inspecting the front and rear wing spar attachment fittings for correctly drilled holes and corrosion and accomplishing corrective actions if needed. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in ADDRESSES. AD Requirements This AD requires accomplishing the actions specified in the service information already described, except as discussed under ‘‘Differences Between the AD and the Service Information.’’ This AD also requires sending the inspection results to the FAA when corrective actions are required. Differences Between the AD and the Service Information Piper Service Bulletin No. 1413 includes a corrosion inspection and corrosion corrective actions. However, these are not directly related to the current unsafe condition of this AD and are not part of the required actions of this AD. E:\FR\FM\22MYR1.SGM 22MYR1 44916 Federal Register / Vol. 89, No. 100 / Wednesday, May 22, 2024 / Rules and Regulations Justification for Immediate Adoption and Determination of the Effective Date Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 U.S.C. 551 et seq.) authorizes agencies to dispense with notice and comment procedures for rules when the agency, for ‘‘good cause,’’ finds that those procedures are ‘‘impracticable, unnecessary, or contrary to the public interest.’’ Under this section, an agency, upon finding good cause, may issue a final rule without providing notice and seeking comment prior to issuance. Further, section 553(d) of the APA authorizes agencies to make rules effective in less than thirty days, upon a finding of good cause. An unsafe condition exists that requires the immediate adoption of this AD without providing an opportunity for public comments prior to adoption. The FAA has found that the risk to the flying public justifies forgoing notice and comment prior to adoption of this rule because a double-drilled bolt hole of the rear wing spar attachment fitting reduces the strength of the fitting below its limit load, and, if not addressed, could result in separation of the wing and loss of control of the airplane. Because these airplanes are used heavily in training operations and accumulate a large number of flight hours in a short period of time, inspection for this condition is necessary before further flight. Accordingly, notice and opportunity for prior public comment are impracticable and contrary to the public interest pursuant to 5 U.S.C. 553(b)(3)(B). In addition, the FAA finds that good cause exists pursuant to 5 U.S.C. 553(d) for making this amendment effective in less than 30 days, for the same reasons the FAA found good cause to forgo notice and comment. Regulatory Flexibility Act The requirements of the Regulatory Flexibility Act (RFA) do not apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and comment. Because the FAA has determined that it has good cause to adopt this rule without prior notice and comment, RFA analysis is not required. Costs of Compliance The FAA estimates that this AD affects 499 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Inspect the aft wing spar attachment fitting ....... 1 work-hour × $85 per hour = $85 ............. The FAA estimates the following costs to do any necessary repairs that Cost per product Parts cost would be required based on the results of the inspection. The agency has no $0 Cost on U.S. operators $85 $42,415 way of determining the number of airplanes that might need these repairs: ON-CONDITION COSTS Action Labor cost Parts cost Report discrepant condition ......................................... Inspect the forward wing spar attachment fitting ........ Perform corrective actions if condition discovered ..... 1 work-hour × $85 per hour = $85 ..................... 1 work-hour × $85 per hour = $85 ..................... 10 work-hours × $85 per hour = $850 ............... $0 ........................ $0 ........................ Up to $2,808 ....... khammond on DSKJM1Z7X2PROD with RULES Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a currently valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. All responses to this collection of information are mandatory. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to: VerDate Sep<11>2014 15:39 May 21, 2024 Jkt 262001 Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177–1524. 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 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Cost per product $85. $85. Up to $3,658. 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, and (2) Will not affect intrastate aviation in Alaska. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. E:\FR\FM\22MYR1.SGM 22MYR1 Federal Register / Vol. 89, No. 100 / Wednesday, May 22, 2024 / Rules and Regulations The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2024–10–04 Piper Aircraft, Inc.: Amendment 39–22749; Docket No. FAA–2024–1302; Project Identifier AD– 2024–00213–A. (a) Effective Date This airworthiness directive (AD) is effective June 6, 2024. (b) Affected ADs None. (c) Applicability This AD applies to Piper Aircraft, Inc. Model PA–28–181, PA–28R–201, PA–34– 220T, and PA–44–180 airplanes, certificated in any category, serial numbers as identified in Piper Service Bulletin No. 1413, dated April 9, 2024 (Piper Service Bulletin No. 1413). (d) Subject Joint Aircraft System Component (JASC) Code 5740, Wing, Attach Fittings. (e) Unsafe Condition This AD was prompted by a report of a double-drilled bolt hole of the rear wing spar attachment fitting found during an unscheduled inspection of an airplane due to a ground collision with an automobile. The FAA is issuing this AD to address the reduction of strength of the part to below its limit load. The unsafe condition, if not addressed, could result in separation of the wing and loss of control of the airplane. khammond on DSKJM1Z7X2PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Before further flight after the effective date of this AD, remove the wing fastening hardware securing the aft spar attachment and do the inspection and applicable corrective actions in accordance with Part II, paragraphs 2, 3, 4b, 4c, 5, and 6, of the Instructions in Piper Service Bulletin No. 1413, except the corrosion inspection and corrosion corrective actions are not required by this AD. (2) If, during the inspection specified in Part II, paragraph 3, of the Instructions in Piper Service Bulletin No. 1413, as required by paragraph (g)(1) of this AD, any VerDate Sep<11>2014 15:39 May 21, 2024 Jkt 262001 discrepancy is found, before further flight, do an inspection of the bolt holes common to the forward spar attachment for wear that exceeds the specified limits, and before further flight replace any component that has a bolt hole that exceeds the specified limits, in accordance with Part II, paragraph 7, of the Instructions in Piper Service Bulletin No. 1413. (3) If it is determined that the corrective actions required by paragraph (g)(1) or the replacement required by paragraph (g)(2) of this AD are necessary, submit a report to the FAA at the address referenced in paragraph (j) of this AD. The report must include the airplane registration and serial number, airplane hours time-in-service, a description of the condition discovered, the wing or wings affected, and a description of the replacement or corrective action performed. Submit the report at the applicable time specified in paragraph (g)(3)(i) or (ii) of this AD. (i) If the action was done on or after the effective date of this AD, submit the report within 10 days after the action was done. (ii) If the action was done before the effective date of this AD, submit the report within 10 days after the effective date of this AD. (h) Special Flight Permits A special flight permit may be issued in accordance with 14 CFR 21.197 and 21.199 provided the following limitations identified in paragraphs (h)(1) and (2) are adhered to: (1) Minimum Crew Only (no passengers); (2) Do not exceed the design maneuvering speed as defined in the applicable existing pilot’s operating handbook (POH). (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, East Certification 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 local Flight Standards District Office, as appropriate. If sending information directly to the manager of the East Certification Branch, mail it to the address identified in paragraph (j) of this. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (j) Additional Information Fred Caplan, Aviation Safety Engineer, East Certification Branch, FAA, 1701 Columbia Avenue, College Park, GA 30337; phone: (404) 474–5507; email: 9-ASOATLACO-ADs@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 the AD specifies otherwise. (i) Piper Service Bulletin No. 1413, dated April 9, 2024. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 44917 (ii) [Reserved] (3) For service information, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, FL 32960; phone: (772) 567–4361; email: customerservice@piper.com; website: piper.com. (4) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (817) 222–5110. (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 May 16, 2024. James D. Foltz, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024–11143 Filed 5–16–24; 4:15 pm] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–1298; Project Identifier MCAI–2024–00216–T; Amendment 39–22745; AD 2024–09–03] RIN 2120–AA64 Airworthiness Directives; ATR—GIE Avions de Transport Régional Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all ATR—GIE Avions de Transport Régional Model ATR42–500 and Model ATR72 airplanes. This AD was prompted by reports of heavy corrosion on one of the two lugs of the travel limiting unit (TLU) lever assembly. This AD requires repetitive inspections of the TLU lever assembly for corrosion and, depending on findings, a conductivity test and applicable corrective actions, and prohibits the installation of affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 6, 2024. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 6, 2024. The FAA must receive comments on this AD by July 8, 2024. SUMMARY: E:\FR\FM\22MYR1.SGM 22MYR1

Agencies

[Federal Register Volume 89, Number 100 (Wednesday, May 22, 2024)]
[Rules and Regulations]
[Pages 44914-44917]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-11143]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-1302; Project Identifier AD-2024-00213-A; 
Amendment 39-22749; AD 2024-10-04]
RIN 2120-AA64


Airworthiness Directives; Piper Aircraft, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 44915]]


ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Piper Aircraft, Inc. (Piper) Model PA-28-181, PA-28R-201, PA-
34-220T, and PA-44-180 airplanes. This AD was prompted by a report of a 
double-drilled bolt hole of the rear wing spar attachment fitting found 
during an unscheduled inspection of an airplane due to a ground 
collision with an automobile. This AD requires inspecting the rear wing 
spar attachment fitting and, if discrepancies are found, inspecting the 
forward wing spar attachment fitting, accomplishing corrective actions 
as required, and reporting to the FAA when corrective actions are 
required. The FAA is issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective June 6, 2024.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 6, 
2024.
    The FAA must receive comments on this AD by July 8, 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-2024-1302; or in person at Docket Operations between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this final rule, any comments received, and other 
information. The street address for Docket Operations is listed above.
    Material Incorporated by Reference:
     For service information, contact Piper Aircraft, Inc., 
2926 Piper Drive, Vero Beach, FL 32960; phone: (772) 567-4361; email: 
piper.com">customerservice@piper.com; website: piper.com.
     You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 901 Locust, 
Kansas City, MO 64106. For information on the availability of this 
material at the FAA, call (817) 222-5110. It is also available at 
regulations.gov under Docket No. FAA-2024-1302.

FOR FURTHER INFORMATION CONTACT: Fred Caplan, Aviation Safety Engineer, 
FAA, East Certification Branch, FAA, 1701 Columbia Avenue, College 
Park, GA 30337; phone: (404) 474-5507; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments to an address listed under 
ADDRESSES. Include ``Docket No. FAA-2024-1302; Project Identifier AD-
2024-00213-A'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the final rule, 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 final rule 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 final rule.

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 AD 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 AD, 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 AD. Submissions containing CBI should be sent to Fred 
Caplan, Aviation Safety Engineer, FAA, East Certification Branch, FAA, 
1701 Columbia Avenue, College Park, GA 30337. Any commentary that the 
FAA receives which is not specifically designated as CBI will be placed 
in the public docket for this rulemaking.

Background

    The FAA is issuing this AD to correct an unsafe condition on 
certain serial-numbered Piper Model PA-28-181, PA-28R-201, PA-34-220T, 
and PA-44-180 airplanes. The FAA received a report that a double-
drilled bolt hole of the rear wing spar attachment fitting was found 
during an unscheduled inspection of an airplane due to a ground 
collision with an automobile. This was the result of an error made 
during manufacturing. A double-drilled bolt hole of the rear wing spar 
attachment fitting reduces its strength below its limit load with 
possible failure of the fitting, which can lead to load redistribution 
and result in possible failure of the primary wing structure. This 
condition, if not addressed, could result in separation of the wing and 
loss of control of the airplane. The FAA is issuing this AD to address 
the unsafe condition on these products.

FAA's Determination

    The FAA is issuing this AD because the agency has determined the 
unsafe condition described previously is likely to exist or develop in 
other products of the same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Piper Service Bulletin No. 1413, dated April 9, 
2024 (Piper Service Bulletin No. 1413). This service information 
specifies procedures for inspecting the front and rear wing spar 
attachment fittings for correctly drilled holes and corrosion and 
accomplishing corrective actions if needed. This service information is 
reasonably available because the interested parties have access to it 
through their normal course of business or by the means identified in 
ADDRESSES.

AD Requirements

    This AD requires accomplishing the actions specified in the service 
information already described, except as discussed under ``Differences 
Between the AD and the Service Information.'' This AD also requires 
sending the inspection results to the FAA when corrective actions are 
required.

Differences Between the AD and the Service Information

    Piper Service Bulletin No. 1413 includes a corrosion inspection and 
corrosion corrective actions. However, these are not directly related 
to the current unsafe condition of this AD and are not part of the 
required actions of this AD.

[[Page 44916]]

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and 
comment procedures for rules when the agency, for ``good cause,'' finds 
that those procedures are ``impracticable, unnecessary, or contrary to 
the public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than thirty days, 
upon a finding of good cause.
    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies forgoing notice and comment prior to adoption of this rule 
because a double-drilled bolt hole of the rear wing spar attachment 
fitting reduces the strength of the fitting below its limit load, and, 
if not addressed, could result in separation of the wing and loss of 
control of the airplane. Because these airplanes are used heavily in 
training operations and accumulate a large number of flight hours in a 
short period of time, inspection for this condition is necessary before 
further flight. Accordingly, notice and opportunity for prior public 
comment are impracticable and contrary to the public interest pursuant 
to 5 U.S.C. 553(b)(3)(B).
    In addition, the FAA finds that good cause exists pursuant to 5 
U.S.C. 553(d) for making this amendment effective in less than 30 days, 
for the same reasons the FAA found good cause to forgo notice and 
comment.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without prior notice and 
comment, RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 499 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspect the aft wing spar attachment    1 work-hour x $85 per                 $0             $85         $42,415
 fitting.                                hour = $85.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary repairs 
that would be required based on the results of the inspection. The 
agency has no way of determining the number of airplanes that might 
need these repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
              Action                    Labor cost                Parts cost               Cost per product
----------------------------------------------------------------------------------------------------------------
Report discrepant condition......  1 work-hour x $85     $0.........................  $85.
                                    per hour = $85.
Inspect the forward wing spar      1 work-hour x $85     $0.........................  $85.
 attachment fitting.                per hour = $85.
Perform corrective actions if      10 work-hours x $85   Up to $2,808...............  Up to $3,658.
 condition discovered.              per hour = $850.
----------------------------------------------------------------------------------------------------------------

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a currently valid OMB Control Number. The OMB 
Control Number for this information collection is 2120-0056. Public 
reporting for this collection of information is estimated to be 
approximately 1 hour per response, including the time for reviewing 
instructions, searching existing data sources, gathering and 
maintaining the data needed, and completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Send comments regarding this burden estimate 
or any other aspect of this collection of information, including 
suggestions for reducing this burden to: Information Collection 
Clearance Officer, Federal Aviation Administration, 10101 Hillwood 
Parkway, Fort Worth, TX 76177-1524.

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, and
    (2) Will not affect intrastate aviation in Alaska.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 44917]]

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.


Sec.  39.13  [Amended]

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

2024-10-04 Piper Aircraft, Inc.: Amendment 39-22749; Docket No. FAA-
2024-1302; Project Identifier AD-2024-00213-A.

(a) Effective Date

    This airworthiness directive (AD) is effective June 6, 2024.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Piper Aircraft, Inc. Model PA-28-181, PA-28R-
201, PA-34-220T, and PA-44-180 airplanes, certificated in any 
category, serial numbers as identified in Piper Service Bulletin No. 
1413, dated April 9, 2024 (Piper Service Bulletin No. 1413).

(d) Subject

    Joint Aircraft System Component (JASC) Code 5740, Wing, Attach 
Fittings.

(e) Unsafe Condition

    This AD was prompted by a report of a double-drilled bolt hole 
of the rear wing spar attachment fitting found during an unscheduled 
inspection of an airplane due to a ground collision with an 
automobile. The FAA is issuing this AD to address the reduction of 
strength of the part to below its limit load. The unsafe condition, 
if not addressed, could result in separation of the wing and loss of 
control of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) Before further flight after the effective date of this AD, 
remove the wing fastening hardware securing the aft spar attachment 
and do the inspection and applicable corrective actions in 
accordance with Part II, paragraphs 2, 3, 4b, 4c, 5, and 6, of the 
Instructions in Piper Service Bulletin No. 1413, except the 
corrosion inspection and corrosion corrective actions are not 
required by this AD.
    (2) If, during the inspection specified in Part II, paragraph 3, 
of the Instructions in Piper Service Bulletin No. 1413, as required 
by paragraph (g)(1) of this AD, any discrepancy is found, before 
further flight, do an inspection of the bolt holes common to the 
forward spar attachment for wear that exceeds the specified limits, 
and before further flight replace any component that has a bolt hole 
that exceeds the specified limits, in accordance with Part II, 
paragraph 7, of the Instructions in Piper Service Bulletin No. 1413.
    (3) If it is determined that the corrective actions required by 
paragraph (g)(1) or the replacement required by paragraph (g)(2) of 
this AD are necessary, submit a report to the FAA at the address 
referenced in paragraph (j) of this AD. The report must include the 
airplane registration and serial number, airplane hours time-in-
service, a description of the condition discovered, the wing or 
wings affected, and a description of the replacement or corrective 
action performed. Submit the report at the applicable time specified 
in paragraph (g)(3)(i) or (ii) of this AD.
    (i) If the action was done on or after the effective date of 
this AD, submit the report within 10 days after the action was done.
    (ii) If the action was done before the effective date of this 
AD, submit the report within 10 days after the effective date of 
this AD.

(h) Special Flight Permits

    A special flight permit may be issued in accordance with 14 CFR 
21.197 and 21.199 provided the following limitations identified in 
paragraphs (h)(1) and (2) are adhered to:
    (1) Minimum Crew Only (no passengers);
    (2) Do not exceed the design maneuvering speed as defined in the 
applicable existing pilot's operating handbook (POH).

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, East Certification 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 local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the East Certification Branch, mail it to 
the address identified in paragraph (j) of this. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.

(j) Additional Information

    Fred Caplan, Aviation Safety Engineer, East Certification 
Branch, FAA, 1701 Columbia Avenue, College Park, GA 30337; phone: 
(404) 474-5507; email: [email protected].

(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 the AD specifies otherwise.
    (i) Piper Service Bulletin No. 1413, dated April 9, 2024.
    (ii) [Reserved]
    (3) For service information, contact Piper Aircraft, Inc., 2926 
Piper Drive, Vero Beach, FL 32960; phone: (772) 567-4361; email: 
piper.com">customerservice@piper.com; website: piper.com.
    (4) You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 901 
Locust, Kansas City, MO 64106. For information on the availability 
of this material at the FAA, call (817) 222-5110.
    (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 May 16, 2024.
James D. Foltz,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2024-11143 Filed 5-16-24; 4:15 pm]
BILLING CODE 4910-13-P
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