Airworthiness Directives; Piaggio Aviation S.p.A. Airplanes, 61482-61485 [2023-19092]

Download as PDF 61482 Federal Register / Vol. 88, No. 172 / Thursday, September 7, 2023 / Proposed Rules (h) Installation Prohibition After the effective date of this AD, do not install an auxiliary motor and pump having P/N 782655–3 (Aerocontrolex P/N 4122– 006009) on any propeller. (i) No Return of Parts Where the service information referenced in the Accomplishment Instructions, paragraph 3.B. of Hamilton Sundstrand SB 14SF–61–168, Revision 1, specifies returning certain parts to the manufacturer for modification, this AD does not include that requirement. (j) Credit for Previous Actions You may take credit for the actions required by paragraph (g) of this AD if you performed those actions before the effective date of this AD using Hamilton Sundstrand SB 14SF–61–168, Original Issue, dated December 14, 2016. (k) 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 branch office, send it to the attention of the person identified in paragraph (l)(1) of this AD. Information may be emailed to: 9-AVSAIR-BACO-COS@faa.gov. (2) 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. ddrumheller on DSK120RN23PROD with PROPOSALS1 (l) Related Information (1) For more information about this AD, contact Isabel Saltzman, Aviation Safety Engineer, FAA, 1701 Columbia Avenue, College Park, GA 30337; phone: (781) 238– 7649; email: 9-AVS-AIR-BACO-COS@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (4) of this AD. (m) 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) Hamilton Sundstrand Corporation Service Bulletin 14SF–61–168, Revision 1, dated December 21, 2016. Note 2 to paragraph (m)(2)(i): Hamilton Sundstrand Corporation is a UTC Aerospace Systems Company. This service information is identified as both Hamilton Sundstrand Corporation and UTC Aerospace Systems. (ii) [Reserved] (3) For service information identified in this AD, contact Hamilton Sundstrand, One Hamilton Road, Windsor Locks, CT 06096– 1010, phone: (877) 808–7575; email: CRC@ collins.com. VerDate Sep<11>2014 16:52 Sep 06, 2023 Jkt 259001 (4) You may view this service information at FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (817) 222–5110. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: fr.inspection@nara.gov, or go to: www.archives.gov/federal-register/cfr/ibrlocations.html. Issued on August 30, 2023. Victor Wicklund, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2023–19085 Filed 9–6–23; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–1819; Project Identifier MCAI–2023–00052–A] RIN 2120–AA64 Airworthiness Directives; Piaggio Aviation S.p.A. 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 Piaggio Aviation S.p.A. (Piaggio) Model P–180 airplanes. This proposed AD was prompted by a report of corrosion on the various aluminum alloy reinforcements in the horizontal stabilizer (HS) central box caused by a humid environment inside the box from water ingress and/or condensation. This proposed AD would require a one-time detailed inspection of the HS central box for corrosion; an assessment of the corrosion level; and depending on the determination, repetitive detailed inspections of the HS central box for corrosion and the internal composite structure for surface cracks, distortion, and damage; and repair or replacement of the HS assembly. Repair or replacement of the HS assembly would be terminating action for the repetitive inspections. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this NPRM by October 23, 2023. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: SUMMARY: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 • 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–2023–1819; 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 NPRM, the mandatory continuing airworthiness information (MCAI), any comments received, and other information. The street address for Docket Operations is listed above. Material Incorporated by Reference: • For service information identified in this NPRM, contact Piaggio Aviation S.p.A., P180 Customer Support, via Pionieri e Aviatori d’Italia, snc—16154 Genoa, Italy; phone: +39 331 679 74 93; email: technicalsupport@ piaggioaerospace.it. • 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. FOR FURTHER INFORMATION CONTACT: Sungmo Cho, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (781) 238– 7241; email: sungmo.d.cho@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 ADDRESSES. Include ‘‘Docket No. FAA–2023–1819; Project Identifier MCAI–2023–00052–A’’ 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 E:\FR\FM\07SEP1.SGM 07SEP1 Federal Register / Vol. 88, No. 172 / Thursday, September 7, 2023 / Proposed Rules 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 Sungmo Cho, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590. 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 European Union Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2023–0007, dated January 13, 2023 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition on certain serial-numbered Piaggio Model P–180 airplanes. The MCAI states that an occurrence of corrosion was found inside the HS central box of a Piaggio Model P–180 airplane during scheduled maintenance. A subsequent investigation and inspection of 16 other Piaggio Model P– 180 airplanes of various configurations and ages revealed that corrosion of differing levels of severity was found on various aluminum alloy reinforcements in the HS central box of all the inspected airplanes. The MCAI also states that this corrosion was caused by the formation of a humid environment inside the HS central box, from water ingress and/or condensation. Further investigation revealed that airplanes left in prolonged inactivity or parked outside are more prone to develop corrosion damage. To address the unsafe condition, the MCAI requires a one-time detailed inspection of the HS central box for corrosion, contacting Piaggio for a determination of the corrosion level, and depending on that determination, repetitive detailed inspections of the HS central box for corrosion and the internal composite structure for surface cracks, distortion, and damage; and depending on the results, repair or replacement of the HS assembly. The MCAI states that repair or replacement of the HS assembly is terminating action for the repetitive inspections. This condition, if not addressed, could result in reduced structural integrity of the HS, and loss of control of the airplane. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2023–1819. Related Service Information Under 1 CFR Part 51 The FAA reviewed Piaggio Aerospace Service Bulletin 80–0489, Revision 2, dated November 30, 2022 (Piaggio SB 80–0489, Revision 2). This service information specifies procedures for a one-time detailed inspection of the HS central box for corrosion, a report of the inspection results to Piaggio for a determination of the corrosion level, repetitive inspections of the HS central box as needed, and applicable corrective actions. The corrective actions include installation of a serviceable HS assembly, which is terminating action for the repetitive inspections. 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. 61483 FAA’s Determination These products have been approved by the aviation authority of another country and are 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 and service information described above. 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. Proposed AD Requirements in This NPRM This proposed AD would require accomplishing the actions specified in the MCAI, except as discussed under ‘‘Differences Between this Proposed AD and the MCAI.’’ Differences Between This Proposed AD and the MCAI The MCAI requires contacting the manufacturer for a determination of the corrosion level if any corrosion is found during the initial inspection of the HS central box, and if it is determined that level 2 or 3 corrosion is present, having the manufacturer provide the threshold and intervals for doing repetitive inspections of the HS central box. This proposed AD would require contacting either the FAA, EASA, or Piaggio’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. Although Piaggio SB 80–0489, Revision 2, specifies to record the image of the location of corroded areas, this proposed AD would not require that action. Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 102 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: ddrumheller on DSK120RN23PROD with PROPOSALS1 ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Initial inspection of HS central box for corrosion. 6 work-hours × $85 per hour = $510 ............. $0 $510 $52,020 VerDate Sep<11>2014 16:52 Sep 06, 2023 Jkt 259001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\07SEP1.SGM 07SEP1 61484 Federal Register / Vol. 88, No. 172 / Thursday, September 7, 2023 / Proposed Rules ON-CONDITION COSTS Cost per product Action Labor cost Repetitive inspections of HS central box for corrosion. Repetitive inspections for surface cracks, distortion, and damage. Replace HS assembly .............................................. 6 work-hours × $85 per hour = $510, per inspection cycle. 6 work-hours × $85 per hour = $510 ....................... $0 10 work-hours × $85 per hour = $850 ..................... 150,000 The repair of the HS assembly that may be required as a result of any inspection could vary significantly from airplane to airplane. The FAA has no data to determine the costs to accomplish the repair or the number of airplanes that may require the repair. 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 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 Parts cost 0 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. (b) Affected ADs List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (e) Unsafe Condition 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 None. (c) Applicability This AD applies to Piaggio Aviation S.p.A. Model P–180 airplanes, serial numbers (S/ Ns) 1002, 1004 through 1234 inclusive, 3001 through 3012 inclusive, and 3016, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 5510, Horizontal Stabilizer Structure. This AD was prompted by a report of corrosion on the various aluminum alloy reinforcements in the horizontal stabilizer (HS) central box caused by a humid environment inside the box from water ingress and/or condensation. The FAA is issuing this AD to address this condition. The unsafe condition, if not addressed, could result in reduced structural integrity of the HS and loss of control of the airplane. (f) Compliance 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 $510, per inspection cycle. $510, per inspection cycle. $150,850. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ Piaggio Aviation S.p.A: Docket No. FAA– 2023–1819; Project Identifier MCAI– 2023–00052–A. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by October 23, 2023. Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Within the applicable compliance time specified in Table 1 to paragraph (g)(1) of this AD, do a detailed inspection of the HS central box for corrosion, in accordance with step (8), of Part A, of the Accomplishment Instructions in Piaggio Aerospace Service Bulletin 80–0489, Revision 2, dated November 30, 2022 (Piaggio SB 80–0489, Revision 2), except you are not required to record any images. TABLE 1 TO PARAGRAPH (g)(1)—HS CENTRAL BOX ONE TIME INSPECTION Compliance time (hours time-in-service (TIS) or calendar time, whichever occurs first after the effective date of this AD) ddrumheller on DSK120RN23PROD with PROPOSALS1 P–180 serial No. 1002; and 1034 through 3016 inclusive ................................................... 1004 through 1033 inclusive .................................................................... (2) If, during the inspection required by paragraph (g)(1) of this AD, any corrosion is detected, before next flight, contact either the Manager, International Validation Branch, FAA; European Union Aviation Safety VerDate Sep<11>2014 16:52 Sep 06, 2023 Jkt 259001 Within 220 hours TIS or 13 months. Within 320 hours TIS or 13 months. Agency (EASA); or Piaggio’s EASA Design Organization Approval (DOA), for an assessment of the corrosion level (level 1, 2, or 3). PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Note 1 to paragraph (g)(2): Appendix 1, Inspection Results Form, in Piaggio SB 80– 0489, Revision 2, may be used when contacting the FAA, EASA, or Piaggio’s EASA DOA. E:\FR\FM\07SEP1.SGM 07SEP1 ddrumheller on DSK120RN23PROD with PROPOSALS1 Federal Register / Vol. 88, No. 172 / Thursday, September 7, 2023 / Proposed Rules (3) If level 1 corrosion is found during the inspection required by paragraph (g)(1) of this AD, no further action is required by this AD. (4) If level 2 corrosion is found during the inspection required by paragraph (g)(1) of this AD, do the action in either paragraph (g)(4)(i) or (ii) of this AD. (i) Before further flight replace the HS assembly or repair the HS assembly in accordance with instructions from either the Manager, International Validation Branch, FAA; EASA; or Piaggio’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (ii) Within 400 hours TIS or 12 months, whichever occurs first after the inspection required by paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 400 hours TIS or 12 months, whichever occurs first after the most recent inspection, repeat the inspection required by paragraph (g)(1) of this AD. In addition, inspect the internal composite structure of the HS central box for surface cracks, distortion, and damage. After each repetitive inspection, before further flight, assess the inspection findings as required by paragraph (g)(2) of this AD. If it is determined that the level 2 corrosion has worsened since the last inspection; or if any surface cracks, distortion, or damage is found during any inspection; before further flight, replace the HS assembly or repair the HS assembly in accordance with instructions from either the Manager, International Validation Branch, FAA; EASA; or Piaggio’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. These inspections must be repeated at intervals not to exceed 400 hours TIS or 12 months, whichever occurs first after the most recent inspection, until a maximum of 660 hours TIS or 13 months, whichever occurs first after the inspection required by paragraph (g)(1) of this AD has been reached, at which time the HS assembly must be repaired or replaced. (5) If level 3 corrosion is found during the inspection required by paragraph (g)(1) of this AD, do the actions required by paragraph (g)(5)(i) or (ii) of this AD. (i) Before further flight after the inspection required by paragraph (g)(1) of this AD, replace the HS assembly or repair the HS assembly in accordance with instructions from either the Manager, International Validation Branch, FAA; EASA; or Piaggio’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (ii) Within 200 hours TIS or 6 months, whichever occurs first after the inspection required by paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 200 hours TIS or 6 months, whichever occurs first after the most recent inspection, repeat the inspection required by paragraph (g)(1) of this AD. In addition, inspect the internal composite structure of the HS central box for surface cracks, distortion, and damage. After each repetitive inspection, before further flight, assess the inspection findings as required by paragraph (g)(2) of this AD. If it is determined that the level 3 corrosion has worsened since the last inspection; or if any surface cracks, distortion, or damage is VerDate Sep<11>2014 16:52 Sep 06, 2023 Jkt 259001 found; before further flight, replace the HS assembly or repair the HS assembly in accordance with instructions from either the Manager, International Validation Branch, FAA; EASA; or Piaggio’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. These inspections must be repeated at intervals not to exceed 200 hours TIS or 6 months, whichever occurs first after the most recent inspection, until a maximum of 660 hours TIS or 13 months, whichever occurs first after the inspection required by paragraph (g)(1) of this AD, at which time the HS assembly must be repaired or replaced. (6) Repair or replacement of the HS assembly is terminating action for the repetitive inspections required by paragraphs (g)(4)(ii) and (g)(5)(ii) of this AD. (h) Credit for Previous Actions You may take credit for the actions required by paragraphs (g)(1) through (5) of this AD if you performed those actions before the effective date of this AD using Piaggio Aerospace Service Bulletin 80–0489, Revision 1, dated May 13, 2022. 61485 (3) For service information identified in this AD, contact Piaggio Aviation S.p.A., P180 Customer Support, via Pionieri e Aviatori d’Italia, snc—16154 Genoa, Italy; phone: +39 331 679 74 93; email: technicalsupport@piaggioaerospace.it. (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 service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: fr.inspection@nara.gov, or go to: www.archives.gov/federal-register/cfr/ibrlocations.html. Issued on August 30, 2023. Victor Wicklund, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2023–19092 Filed 9–6–23; 8:45 am] BILLING CODE 4910–13–P (i) 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 local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, mail it to the address identified in paragraph (j)(2) of this AD or email to: 9AVS-AIR-730-AMOC@faa.gov. If mailing information, also submit information by email. 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 (1) Refer to EASA AD 2023–0007, dated January 13, 2023, for related information. This EASA AD may be found in the AD docket at regulations.gov under Docket No. FAA–2023–1819. (2) For more information about this AD, contact Sungmo Cho, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (781) 238– 7241; email: sungmo.d.cho@faa.gov. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k)(3) and (4) of this AD. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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) Piaggio Aerospace Service Bulletin 80– 0489, Revision 2, dated November 30, 2022. (ii) [Reserved] PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–1816; Project Identifier MCAI–2021–01460–R] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH (AHD) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH (AHD) Model MBB–BK 117 D–3 helicopters. This proposed AD was prompted by recalculations of the inspection intervals for certain parts. This proposed AD would require revising the airworthiness limitations section (ALS) of the existing helicopter maintenance manual or instructions for continued airworthiness for your helicopter and the existing approved maintenance or inspection program for your helicopter, as applicable, to reduce the inspection interval of certain parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference (IBR). The FAA is proposing this AD to address the unsafe condition on these products. SUMMARY: E:\FR\FM\07SEP1.SGM 07SEP1

Agencies

[Federal Register Volume 88, Number 172 (Thursday, September 7, 2023)]
[Proposed Rules]
[Pages 61482-61485]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-19092]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-1819; Project Identifier MCAI-2023-00052-A]
RIN 2120-AA64


Airworthiness Directives; Piaggio Aviation S.p.A. 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 Piaggio Aviation S.p.A. (Piaggio) Model P-180 airplanes. 
This proposed AD was prompted by a report of corrosion on the various 
aluminum alloy reinforcements in the horizontal stabilizer (HS) central 
box caused by a humid environment inside the box from water ingress 
and/or condensation. This proposed AD would require a one-time detailed 
inspection of the HS central box for corrosion; an assessment of the 
corrosion level; and depending on the determination, repetitive 
detailed inspections of the HS central box for corrosion and the 
internal composite structure for surface cracks, distortion, and 
damage; and repair or replacement of the HS assembly. Repair or 
replacement of the HS assembly would be terminating action for the 
repetitive inspections. The FAA is proposing this AD to address the 
unsafe condition on these products.

DATES: The FAA must receive comments on this NPRM by October 23, 2023.

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-2023-1819; 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 NPRM, the mandatory continuing airworthiness 
information (MCAI), any comments received, and other information. The 
street address for Docket Operations is listed above.
    Material Incorporated by Reference:
     For service information identified in this NPRM, contact 
Piaggio Aviation S.p.A., P180 Customer Support, via Pionieri e Aviatori 
d'Italia, snc--16154 Genoa, Italy; phone: +39 331 679 74 93; email: 
[email protected].
     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.

FOR FURTHER INFORMATION CONTACT: Sungmo Cho, Aviation Safety Engineer, 
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (781) 
238-7241; 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 ADDRESSES. Include ``Docket No. FAA-2023-1819; Project Identifier 
MCAI-2023-00052-A'' 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

[[Page 61483]]

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 
Sungmo Cho, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 
410, Westbury, NY 11590. 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 European Union Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Union, has issued 
EASA AD 2023-0007, dated January 13, 2023 (referred to after this as 
``the MCAI''), to correct an unsafe condition on certain serial-
numbered Piaggio Model P-180 airplanes.
    The MCAI states that an occurrence of corrosion was found inside 
the HS central box of a Piaggio Model P-180 airplane during scheduled 
maintenance. A subsequent investigation and inspection of 16 other 
Piaggio Model P-180 airplanes of various configurations and ages 
revealed that corrosion of differing levels of severity was found on 
various aluminum alloy reinforcements in the HS central box of all the 
inspected airplanes. The MCAI also states that this corrosion was 
caused by the formation of a humid environment inside the HS central 
box, from water ingress and/or condensation. Further investigation 
revealed that airplanes left in prolonged inactivity or parked outside 
are more prone to develop corrosion damage.
    To address the unsafe condition, the MCAI requires a one-time 
detailed inspection of the HS central box for corrosion, contacting 
Piaggio for a determination of the corrosion level, and depending on 
that determination, repetitive detailed inspections of the HS central 
box for corrosion and the internal composite structure for surface 
cracks, distortion, and damage; and depending on the results, repair or 
replacement of the HS assembly. The MCAI states that repair or 
replacement of the HS assembly is terminating action for the repetitive 
inspections.
    This condition, if not addressed, could result in reduced 
structural integrity of the HS, and loss of control of the airplane.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2023-1819.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Piaggio Aerospace Service Bulletin 80-0489, 
Revision 2, dated November 30, 2022 (Piaggio SB 80-0489, Revision 2). 
This service information specifies procedures for a one-time detailed 
inspection of the HS central box for corrosion, a report of the 
inspection results to Piaggio for a determination of the corrosion 
level, repetitive inspections of the HS central box as needed, and 
applicable corrective actions. The corrective actions include 
installation of a serviceable HS assembly, which is terminating action 
for the repetitive inspections.
    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.

FAA's Determination

    These products have been approved by the aviation authority of 
another country and are 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 and service information described above. 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.

Proposed AD Requirements in This NPRM

    This proposed AD would require accomplishing the actions specified 
in the MCAI, except as discussed under ``Differences Between this 
Proposed AD and the MCAI.''

Differences Between This Proposed AD and the MCAI

    The MCAI requires contacting the manufacturer for a determination 
of the corrosion level if any corrosion is found during the initial 
inspection of the HS central box, and if it is determined that level 2 
or 3 corrosion is present, having the manufacturer provide the 
threshold and intervals for doing repetitive inspections of the HS 
central box. This proposed AD would require contacting either the FAA, 
EASA, or Piaggio's EASA Design Organization Approval (DOA). If approved 
by the DOA, the approval must include the DOA-authorized signature.
    Although Piaggio SB 80-0489, Revision 2, specifies to record the 
image of the location of corroded areas, this proposed AD would not 
require that action.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 102 airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Initial inspection of HS central box  6 work-hours x $85 per               $0             $510          $52,020
 for corrosion.                        hour = $510.
----------------------------------------------------------------------------------------------------------------


[[Page 61484]]


                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost          Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Repetitive inspections of HS central   6 work-hours x $85 per               $0  $510, per inspection cycle.
 box for corrosion.                     hour = $510, per
                                        inspection cycle.
Repetitive inspections for surface     6 work-hours x $85 per                0  $510, per inspection cycle.
 cracks, distortion, and damage.        hour = $510.
Replace HS assembly..................  10 work-hours x $85 per         150,000  $150,850.
                                        hour = $850.
----------------------------------------------------------------------------------------------------------------

    The repair of the HS assembly that may be required as a result of 
any inspection could vary significantly from airplane to airplane. The 
FAA has no data to determine the costs to accomplish the repair or the 
number of airplanes that may require the repair.

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

    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:

Piaggio Aviation S.p.A: Docket No. FAA-2023-1819; Project Identifier 
MCAI-2023-00052-A.

 (a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by October 23, 2023.

 (b) Affected ADs

    None.

 (c) Applicability

    This AD applies to Piaggio Aviation S.p.A. Model P-180 
airplanes, serial numbers (S/Ns) 1002, 1004 through 1234 inclusive, 
3001 through 3012 inclusive, and 3016, certificated in any category.

 (d) Subject

    Joint Aircraft System Component (JASC) Code 5510, Horizontal 
Stabilizer Structure.

 (e) Unsafe Condition

    This AD was prompted by a report of corrosion on the various 
aluminum alloy reinforcements in the horizontal stabilizer (HS) 
central box caused by a humid environment inside the box from water 
ingress and/or condensation. The FAA is issuing this AD to address 
this condition. The unsafe condition, if not addressed, could result 
in reduced structural integrity of the HS 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) Within the applicable compliance time specified in Table 1 
to paragraph (g)(1) of this AD, do a detailed inspection of the HS 
central box for corrosion, in accordance with step (8), of Part A, 
of the Accomplishment Instructions in Piaggio Aerospace Service 
Bulletin 80-0489, Revision 2, dated November 30, 2022 (Piaggio SB 
80-0489, Revision 2), except you are not required to record any 
images.

     Table 1 to Paragraph (g)(1)--HS Central Box One Time Inspection
------------------------------------------------------------------------
                                         Compliance time  (hours time-in-
                                         service (TIS) or calendar time,
            P-180 serial No.               whichever occurs first after
                                          the effective date of this AD)
------------------------------------------------------------------------
1002; and 1034 through 3016 inclusive..  Within 220 hours TIS or 13
                                          months.
1004 through 1033 inclusive............  Within 320 hours TIS or 13
                                          months.
------------------------------------------------------------------------

    (2) If, during the inspection required by paragraph (g)(1) of 
this AD, any corrosion is detected, before next flight, contact 
either the Manager, International Validation Branch, FAA; European 
Union Aviation Safety Agency (EASA); or Piaggio's EASA Design 
Organization Approval (DOA), for an assessment of the corrosion 
level (level 1, 2, or 3).
    Note 1 to paragraph (g)(2): Appendix 1, Inspection Results Form, 
in Piaggio SB 80-0489, Revision 2, may be used when contacting the 
FAA, EASA, or Piaggio's EASA DOA.

[[Page 61485]]

    (3) If level 1 corrosion is found during the inspection required 
by paragraph (g)(1) of this AD, no further action is required by 
this AD.
    (4) If level 2 corrosion is found during the inspection required 
by paragraph (g)(1) of this AD, do the action in either paragraph 
(g)(4)(i) or (ii) of this AD.
    (i) Before further flight replace the HS assembly or repair the 
HS assembly in accordance with instructions from either the Manager, 
International Validation Branch, FAA; EASA; or Piaggio's EASA DOA. 
If approved by the DOA, the approval must include the DOA-authorized 
signature.
    (ii) Within 400 hours TIS or 12 months, whichever occurs first 
after the inspection required by paragraph (g)(1) of this AD, and 
thereafter at intervals not to exceed 400 hours TIS or 12 months, 
whichever occurs first after the most recent inspection, repeat the 
inspection required by paragraph (g)(1) of this AD. In addition, 
inspect the internal composite structure of the HS central box for 
surface cracks, distortion, and damage. After each repetitive 
inspection, before further flight, assess the inspection findings as 
required by paragraph (g)(2) of this AD. If it is determined that 
the level 2 corrosion has worsened since the last inspection; or if 
any surface cracks, distortion, or damage is found during any 
inspection; before further flight, replace the HS assembly or repair 
the HS assembly in accordance with instructions from either the 
Manager, International Validation Branch, FAA; EASA; or Piaggio's 
EASA DOA. If approved by the DOA, the approval must include the DOA-
authorized signature. These inspections must be repeated at 
intervals not to exceed 400 hours TIS or 12 months, whichever occurs 
first after the most recent inspection, until a maximum of 660 hours 
TIS or 13 months, whichever occurs first after the inspection 
required by paragraph (g)(1) of this AD has been reached, at which 
time the HS assembly must be repaired or replaced.
    (5) If level 3 corrosion is found during the inspection required 
by paragraph (g)(1) of this AD, do the actions required by paragraph 
(g)(5)(i) or (ii) of this AD.
    (i) Before further flight after the inspection required by 
paragraph (g)(1) of this AD, replace the HS assembly or repair the 
HS assembly in accordance with instructions from either the Manager, 
International Validation Branch, FAA; EASA; or Piaggio's EASA DOA. 
If approved by the DOA, the approval must include the DOA-authorized 
signature.
    (ii) Within 200 hours TIS or 6 months, whichever occurs first 
after the inspection required by paragraph (g)(1) of this AD, and 
thereafter at intervals not to exceed 200 hours TIS or 6 months, 
whichever occurs first after the most recent inspection, repeat the 
inspection required by paragraph (g)(1) of this AD. In addition, 
inspect the internal composite structure of the HS central box for 
surface cracks, distortion, and damage. After each repetitive 
inspection, before further flight, assess the inspection findings as 
required by paragraph (g)(2) of this AD. If it is determined that 
the level 3 corrosion has worsened since the last inspection; or if 
any surface cracks, distortion, or damage is found; before further 
flight, replace the HS assembly or repair the HS assembly in 
accordance with instructions from either the Manager, International 
Validation Branch, FAA; EASA; or Piaggio's EASA DOA. If approved by 
the DOA, the approval must include the DOA-authorized signature. 
These inspections must be repeated at intervals not to exceed 200 
hours TIS or 6 months, whichever occurs first after the most recent 
inspection, until a maximum of 660 hours TIS or 13 months, whichever 
occurs first after the inspection required by paragraph (g)(1) of 
this AD, at which time the HS assembly must be repaired or replaced.
    (6) Repair or replacement of the HS assembly is terminating 
action for the repetitive inspections required by paragraphs 
(g)(4)(ii) and (g)(5)(ii) of this AD.

 (h) Credit for Previous Actions

    You may take credit for the actions required by paragraphs 
(g)(1) through (5) of this AD if you performed those actions before 
the effective date of this AD using Piaggio Aerospace Service 
Bulletin 80-0489, Revision 1, dated May 13, 2022.

 (i) 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 local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Validation Branch, mail 
it to the address identified in paragraph (j)(2) of this AD or email 
to: [email protected]. If mailing information, also submit 
information by email. 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

    (1) Refer to EASA AD 2023-0007, dated January 13, 2023, for 
related information. This EASA AD may be found in the AD docket at 
regulations.gov under Docket No. FAA-2023-1819.
    (2) For more information about this AD, contact Sungmo Cho, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: (781) 238-7241; email: 
[email protected].
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (k)(3) and (4) of this AD.

 (k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference 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) Piaggio Aerospace Service Bulletin 80-0489, Revision 2, 
dated November 30, 2022.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Piaggio Aviation S.p.A., P180 Customer Support, via Pionieri e 
Aviatori d'Italia, snc--16154 Genoa, Italy; phone: +39 331 679 74 
93; email: [email protected].
    (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 service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on August 30, 2023.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2023-19092 Filed 9-6-23; 8:45 am]
BILLING CODE 4910-13-P
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