Airworthiness Directives; Piper Aircraft, Inc. Airplanes, 15439-15443 [2021-05584]

Download as PDF Federal Register / Vol. 86, No. 54 / Tuesday, March 23, 2021 / Proposed Rules seal has between 3,751 and 4,249 cycles, inclusive, since being reconfigured, remove the part from service within 250 cycles after July 5, 2019 (the effective date of AD 2019– 12–05), before accumulating 4,275 cycles since being reconfigured, within 1,500 cycles since the last FPI of the rotating air HPT front seal, or before further flight after the effective date of this AD, whichever occurs later, and replace with a part eligible for installation. (iii) For all remaining CFM CFM56–5C model turbofan engines, remove the rotating air HPT front seal from service before accumulating 4,000 cycles since being reconfigured, or within 50 cycles after the effective date of this AD, whichever occurs later. (3) For CFM56–5B or CFM56–7B model turbofan engines with an affected rotating air HPT front seal that has been operated in a CFM56–5C model turbofan engine since being reconfigured, remove the rotating air HPT front seal from service using the cycle limits in paragraph (g)(2) of this AD. information on the availability of this material at the FAA, call (781) 238–7759. (h) Definition For the purpose of this AD, ‘‘reconfigured’’ occurs when a rotating air HPT front seal has been removed from the original HPT disk and re-assembled to a different HPT disk. AGENCY: (i) Installation Prohibition After the effective date of this AD, do not assemble any rotating air HPT front seal with greater than 0 cycles since new, having a S/ N listed in paragraph (c) of this AD onto a HPT disk unless it is the same S/N HPT disk on which it has previously been assembled. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO 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 certification office, send it to the attention of the person identified in Related Information. You may email your request to: ANE-AD-AMOC@ 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. (k) Related Information (1) For more information about this AD, contact Christopher McGuire, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7120; fax: (781) 238–7199; email: Chris.McGuire@faa.gov. (2) For service information identified in this AD, contact CFM International, S.A., Aviation Operations Center, 1 Neumann Way, M/D Room 285, Cincinnati, OH 45125; phone: (877) 432–3272; email: aviation.fleetsupport@ge.com. You may view this referenced service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For VerDate Sep<11>2014 17:08 Mar 22, 2021 Jkt 253001 Issued on March 12, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–05600 Filed 3–22–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0881; Project Identifier 2018–CE–024–AD] RIN 2120–AA64 Airworthiness Directives; Piper Aircraft, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). The FAA proposes to supersede Airworthiness Directive (AD) 79–01–03, which applies to certain Piper Aircraft, Inc. (Piper) Model PA– 36–285 airplanes, and AD 83–20–03, which applies to Piper Models PA–36– 285, PA–36–300, and PA–36–375 airplanes. AD 79–01–03 requires repetitive inspections of the spar carry through assembly until it is replaced with a different part numbered spar carry through assembly. AD 83–20–03 establishes life limits for the wing spar structural components. Since the FAA issued AD 79–01–03 and AD 83–20–03, the FAA identified inspection and life limit requirements that were inadvertently omitted from those ADs. This proposed AD would retain the requirements in AD 79–01–03 and AD 83–20–03 and require the spar carry through assembly inspection from AD 79–01–03 for additional airplanes and add life limits for certain wing structural components previously omitted from AD 83–20–03 for certain serial numbered airplanes. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by May 7, 2021. 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 https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– SUMMARY: PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 15439 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. For service information identified in this NPRM, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, FL 32960; phone: (772) 567–4361; website: https:// www.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 (816) 329–4148. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0881; 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, any comments received, and other information. The street address for Docket Operations is listed above. Dan McCully, Aviation Safety Engineer, FAA, Atlanta ACO Branch, 1701 Columbia Avenue, College Park, GA 30337; phone: (404) 474–5548; fax: (404) 474–5606; email: william.mccully@ faa.gov. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2020–0881; Project Identifier 2018–CE–024–AD.’’ 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 the 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 https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this proposed AD. E:\FR\FM\23MRP1.SGM 23MRP1 15440 Federal Register / Vol. 86, No. 54 / Tuesday, March 23, 2021 / Proposed Rules 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 Dan McCully, Aviation Safety Engineer, FAA, Atlanta ACO Branch, 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 issued AD 79–01–03, Amendment 39–3383 (44 FR 36, January 2, 1979), Docket No. 78–EA–69 (AD 79– 01–03), for certain Piper Model PA–36– 285 airplanes. AD 79–01–03 requires repetitive inspections of spar carry through assembly part number (P/N) 97370–00, with repair as necessary, until the spar carry through assembly is replaced with P/N 76824–02. AD 79– 01–03 was prompted by reports of cumulative damage to the wing spar carry through assembly, which resulted from fatigue testing and other field evidence of movement between the leg of the spar cap and the spar web. The FAA issued AD 79–01–03 to prevent hazards in flight associated with damage of the wing spar carry through assembly. The FAA also issued AD 83–20–03, Amendment 39–4739 (48 FR 45535, October 6, 1983), Docket No. 83–CE–23– AD (AD 83–20–03), for Piper Models PA–36–285, PA–36–300, and PA–36– 375 airplanes. AD 83–20–03 establishes life limits for certain wing structural components. AD 83–20–03 was prompted by manufacturer laboratory fatigue tests of the wing structure that identified the need to establish a service life limit for the wing structural components. The FAA issued AD 83– 20–03 to prevent failure of the wing structural components because of fatigue damage. Actions Since AD 79–01–03 and AD 83– 20–03 Were Issued Since the FAA issued AD 79–01–03 and AD 83–20–03, the FAA identified inconsistencies between the two ADs and the airplanes’ type certificate. The FAA determined that the life limits for the spar carry through assembly, P/N 97370–00 or 76824–02, were inadvertently omitted from AD 83–20– 03 for certain airplanes. The FAA is issuing this NPRM to add the life limit for the spar carry through assembly for Models PA–36–285 and PA–36–300 airplanes, serial numbers 36–7660123 through 36–8160023, and Model PA– 36–375 airplanes, serial numbers 36– 7802001 through 36–8302025. The FAA also determined the repetitive inspections of the spar carry through assembly required by AD 79–01–03 should apply to both Model PA–36–285 and Model PA–36–300 airplanes until the life limit replacement of the spar carry through assembly with P/N 76824–02. After the initial life limit replacement of the wing spar carry through assembly required by AD 83– 20–03 (P/N 97370–00 with P/N 76824– 02), the inspections required by AD 79– 01–03 are no longer be required. In this NPRM, the FAA proposes to supersede both of those ADs. FAA’s Determination The FAA is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design. Related Service Information Under 1 CFR Part 51 The FAA reviewed Piper Aircraft, Inc., Service Bulletin No. 552A, dated August 3, 2018 (Piper SB No. 552A); Piper Aircraft PA–36, Pawnee Brave Kit 764–394, Right Wing Main Spar Caps Replacement, dated June 9, 2012 (Piper Kit 764–394); and Piper Aircraft PA–36, Pawnee Brave Kit 764–393, Left Wing Main Spar Caps Replacement, dated June 9, 2012 (Piper Kit 764–393). Piper SB No. 552A applies to Models PA–36– 285 and PA–36–300 airplanes and contains procedures for repetitively inspecting wing spar carry through assembly P/N 97370–00. Piper Kit 764– 394 identifies the applicable parts and specifies procedures for replacing the right wing main spar caps, which includes the attachment bolts and wing carry through spar fittings and assembly. Piper Kit 764–393 identifies the applicable parts and specifies procedures for replacing the left wing main spar caps, which includes the attachment bolts and wing carry through spar fittings and assembly. 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 the ADDRESSES section. Other Related Service Information The FAA also reviewed Piper Aircraft Corporation Service Bulletin No. 552, dated February 3, 1978 (Piper SB No. 552). Piper SB No. 552 contains the same procedures as Piper SB No. 552A, but Piper SB No. 552 only applies to Model PA–36–285 airplanes. Proposed AD Requirements in This NPRM This proposed AD would retain all of the requirements of AD 79–01–03 and AD 83–20–03 but would apply some of the requirements to additional serialnumbered airplanes. Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 123 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: ESTIMATED COSTS Cost per product Cost on U.S. operators Action Labor cost Parts cost Inspection of P/N 97370–00 wing spar carry through assembly. Replacement of the wing attachment upper bolt and lower bolt. * Replacement of wing carry through spar assembly. 8 work-hours × $85 per hour = $680. 10 work-hours × $85 per hour = $850. 30 work-hours × $85 per hour = $2,550. Not applicable ................................ $680 $83,640 $1,310 (both bolts) ......................... 2,160 265,680 $23,467 .......................................... 26,017 3,200,091 VerDate Sep<11>2014 17:08 Mar 22, 2021 Jkt 253001 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 E:\FR\FM\23MRP1.SGM 23MRP1 Federal Register / Vol. 86, No. 54 / Tuesday, March 23, 2021 / Proposed Rules 15441 ESTIMATED COSTS—Continued Cost per product Action Labor cost Parts cost ** Replacement of Piper Kit 764– 393 (Left) and Piper Kit 764-394 (Right). 20 work-hours × $85 per hour = $1,700. $26,867 (both kits) ......................... 28,567 Cost on U.S. operators 3,513,741 * The wing carry through spar fitting, P/N 97713–03, is included in the wing carry through spar assembly, P/N 76824–02. ** The replacement for the wing spar fitting P/N 97712–00 and the replacement for spar assembly P/Ns 97701–00 and 97701–01 are included in Piper Kit 764–393 and Piper Kit 764–394. 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 has 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 that the proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Would not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, 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. VerDate Sep<11>2014 17:08 Mar 22, 2021 Jkt 253001 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 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: a. Removing Airworthiness Directive 79–01–03, Amendment 39–3383 (44 FR 36, January 2, 1979), Docket No. 78–EA– 69; and Airworthiness Directive 83–20– 03, Amendment 39–4739 (48 FR 45535, October 6, 1983), Docket No. 83–CE–23– AD; and ■ b. Adding the following new airworthiness directive: ■ ■ Piper Aircraft, Inc.: Docket No. FAA–2020– 0881; Project Identifier 2018–CE–024– AD. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) action by May 7, 2021. (b) Affected ADs This AD replaces AD 79–01–03, Amendment 39–3383 (44 FR 36, January 2, 1979), Docket No. 78–EA–69 (AD 79–01–03); and AD 83–20–03, Amendment 39–4739 (48 FR 45535, October 6, 1983), Docket No. 83– CE–23–AD (83–20–03). (c) Applicability This AD applies to Piper Aircraft, Inc. Models PA–36–285, PA–36–300, and PA–36– 375 airplanes, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 5700, Wings. (e) Unsafe Condition This AD was prompted by a review of AD 83–20–03 and AD 79–01–03 and the determination that the requirements of those ADs did not address all of the affected airplanes. The FAA is issuing this AD to prevent fatigue damage to the wing structural components. The unsafe condition, if not addressed, could result in failure of the wing structure with consequent loss of control. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection of the Wing Spar Carry Through Assembly (1) For Models PA–36–285 and PA–36–300 airplanes, serial numbers 36–7360001 through 36–7560003, with a wing spar carry through assembly part number (P/N) 97370– 00 installed, before the airplane accumulates a total of 2,000 hours time-in-service (TIS) or within 25 hours TIS after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 100 hours TIS, inspect the wing spar carry through assembly by following the Instructions, section 1, of Piper Aircraft, Inc., Service Bulletin No. 552A, dated August 3, 2018, (Piper SB No. 552A). (2) If any damage is found during any inspection required by paragraph (g)(1) of this AD, before further flight, repair or replace the wing spar carry through assembly by following the Instructions, section 2, of Piper SB No. 552A. (3) Replacing wing spar carry through assembly P/N 97370–00 with wing spar carry through assembly P/N 76824–02 terminates the repetitive inspections required by paragraph (g)(1) of this AD. (h) Life Limit Replacement of Wing Structural Components Remove from service the wing structural components specified in paragraphs (h)(1) through (8) of this AD before the part accumulates the life limit hours TIS set forth in table 1 to paragraph (h) of this AD. If, on the effective date of this AD, the component will reach its life limit within 100 hours TIS or has already reached its life limit, remove the part from service within 100 hours TIS after the effective date of this AD. (1) Remove from service wing attachment upper bolt P/N 77245–00 and replace with an unused (zero hours TIS) wing attachment upper bolt P/N 77245–00. (2) Remove from service any wing carry through spar fitting P/Ns 97713–00, 97713– 02, or 97713–03 and replace with an unused (zero hours TIS) wing carry through spar fitting P/N 97713–03. Note 1 to paragraph (h)(2): Wing carry through spar fitting P/N 97713–03 is included as part of spar carry through assembly P/N 76824–02. (3) Remove from service wing spar fitting P/N 97712–00 and replace with an unused (zero hours TIS) wing spar fitting P/N 97712– 00 by following steps D(1)(a) through D(1)(c) E:\FR\FM\23MRP1.SGM 23MRP1 15442 Federal Register / Vol. 86, No. 54 / Tuesday, March 23, 2021 / Proposed Rules or section D(2), in Piper Aircraft, PA–36, Pawnee Brave Kit 764–393, Left Wing Main Spar Caps Replacement, dated June 9, 2012 (Piper Kit 764–393), or Piper Aircraft, PA–36, Pawnee Brave Kit 764–394, Right Wing Main Spar Caps Replacement, dated June 9, 2012 (Piper Kit 764–394), as applicable. Note 2 to paragraph (h)(3): This note applies to paragraphs (h)(3) and (7) of this AD. Replacement parts for the left and right wing spar fittings P/N 97712–00 and the right, left, top, and bottom spar assemblies P/ Ns 97701–00 and 97701–01 are included with Piper Kit 764–393 and Piper Kit 764– 394. (4) Remove from service spar carry through assembly P/N 97370–00 or 76824–02, as applicable, and replace with an unused (zero hours TIS) spar carry through assembly P/N 76824–02. (5) Remove from service spar assembly P/ Ns 97701–00 and 97701–01, Revision P or later revision, and replace with an unused (zero hours TIS) spar assembly by following the Instructions, sections B. and C., in Piper Kit 764–393 or Piper Kit 764–394, as applicable. (6) Remove from service any spar carry through assembly P/N 76767–00 or P/N 76824–02 and replace with an unused (zero hours TIS) spar carry through assembly P/N 76824–02. (7) Remove from service spar assemblies P/ Ns 97701–00 and 97701–01, Revision N or earlier revision, and replace with an unused (zero hours TIS) left spar cap replacement kit P/N 764–393 and right spar cap replacement kit P/N 764–394 by following the Instructions, sections B. and C., in Piper Kit 764–393 or Piper Kit 764–394, as applicable. (8) Remove from service wing attachment lower bolt P/N 77245–00 and replace with an unused (zero hours TIS) P/N 77245–00 bolt. BILLING CODE 4910–13–P Table 1 to paragraph (h)-Compliance Times for Life Limit Replacement of Wing Com onents Airplanes Type of Replacement Paragraph of this AD (h)(l) (h)(2) (h)(3) Models PA-36-285 and PA-36-300 (h)(5) (h)(6) (h)(7) (h)(8) Life Limit Hours Time-in-Service on the Component Serial Numbers (S/Ns) 36-7360001 throu h 36-7560003 S/Ns 36-7560004 through 36-7560055 Initial Repetitive 4,100 4,100 4,100 4,100 NIA NIA NIA NIA 3,100 4,100 2,000 2,000 Initial Repetitive 4,100 4,100 NIA NIA 4,000 4,100 3,100 4,100 2,000 2,000 S/Ns 36-7560056 through 36-7660122 Initial Repetitive 4,100 4,100 NIA NIA NIA NIA 4,100 4,100 4,000 4,100 2,000 2,000 S/Ns 36-7660123 through 36-8160023 Initial Repetitive 4,100 4,100 4,100 4,100 4,100 4,100 NIA NIA NIA NIA NIA NIA Initial Repetitive (i) 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 Piper Aircraft Corporation Service Bulletin No. 552, dated February 3, 1978. Jkt 253001 (h)(l) (h)(2) (h)(3) (h)(4) (h)(5) (h)(6) (h)(7) (h)(8) 4,100 4,100 4,100 4,100 4,100 4,100 NIA NIA NIA NIA 2,000 2,000 (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta ACO 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 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 information directly to the manager of the certification office, send it to the attention of the person identified in Related Information. (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. E:\FR\FM\23MRP1.SGM 23MRP1 EP23MR21.000</GPH> S/Ns 36-7802001 through 36-8302025 17:08 Mar 22, 2021 2,000 2,000 Life Limit Hours Time-in-Service on the Component Model PA-36-375 VerDate Sep<11>2014 (h)(4) Federal Register / Vol. 86, No. 54 / Tuesday, March 23, 2021 / Proposed Rules (3) AMOCs approved for AD 79–01–03 and AD 83–20–03 are approved as AMOCs for the corresponding provisions of this AD. (k) Related Information (1) For more information about this AD, contact Dan McCully, Aviation Safety Engineer, FAA, Atlanta ACO Branch, 1701 Columbia Avenue, College Park, GA 30337; phone: (404) 474–5548; fax: (404) 474–5606; email: william.mccully@faa.gov. (2) For service information identified in this AD, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, FL 32960; phone: (772) 567–4361; website: www.piper.com. You may view this service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Issued on March 12, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–05584 Filed 3–22–21; 8:45 am] BILLING CODE 4910–13–C • Federal eRulemaking Portal: Go to https://www.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. For service information identified in this NPRM, contact CFM International, S.A., Aviation Operations Center, 1 Neumann Way, M/D Room 285, Cincinnati, OH 45125; phone: (877) 432–3272; email: aviation.fleetsupport@ ge.com. You may view this service information at the 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 (781) 238–7759. DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0187; 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, any comments received, and other information. The street address for Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: Chris McGuire, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7120; fax: (781) 238– 7199; email: Chris.McGuire@faa.gov. SUPPLEMENTARY INFORMATION: 14 CFR Part 39 [Docket No. FAA–2021–0187; Project Identifier AD–2020–01664–E] RIN 2120–AA64 Airworthiness Directives; CFM International, S.A. Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain CFM International, S.A. (CFM) LEAP–1A23, LEAP–1A24, LEAP– 1A24E1, LEAP–1A26, LEAP–1A26CJ, LEAP–1A26E1, LEAP–1A29, LEAP– 1A29CJ, LEAP–1A30, LEAP–1A32, LEAP–1A33, LEAP–1A33B2, and LEAP–1A35A model turbofan engines. This proposed AD was prompted by a report of a manufacturing quality escape found during an inspection of a highpressure turbine (HPT) case. This proposed AD would require the removal from service of the affected HPT case. The FAA is proposing this AD to address the unsafe condition on these products. SUMMARY: The FAA must receive comments on this proposed AD by May 7, 2021. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: DATES: VerDate Sep<11>2014 17:08 Mar 22, 2021 Jkt 253001 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–2021–0187; Project Identifier AD– 2020–01664–E’’ 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 https:// PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 15443 www.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 Chris McGuire, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington MA 01803. 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 received a report of a manufacturing quality escape that identified certain HPT cases did not meet their approved type design. CFM determined the nonconforming parts could lead to over-temperature of the HPT mid-seal and uncontained rotor failure. A review of several x-rays of the bleed ports of the HPT case showed 148 parts with nonconforming indications, 8 of which were significant enough to impact the life of the HPT case. This condition, if not addressed, could result in failure of the HPT case, uncontained rotor release, damage to the engine, and damage to the airplane. FAA’s Determination The FAA is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design. Related Service Information Under 1 CFR Part 51 The FAA reviewed CFM Service Bulletin (SB) LEAP–1A–72–00–0421– 01A–930A–D, Issue 001, dated October 22, 2020. This SB specifies procedures for replacing the affected HPT cases. This service information is reasonably available because the interested parties E:\FR\FM\23MRP1.SGM 23MRP1

Agencies

[Federal Register Volume 86, Number 54 (Tuesday, March 23, 2021)]
[Proposed Rules]
[Pages 15439-15443]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-05584]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0881; Project Identifier 2018-CE-024-AD]
RIN 2120-AA64


Airworthiness Directives; Piper Aircraft, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 79-
01-03, which applies to certain Piper Aircraft, Inc. (Piper) Model PA-
36-285 airplanes, and AD 83-20-03, which applies to Piper Models PA-36-
285, PA-36-300, and PA-36-375 airplanes. AD 79-01-03 requires 
repetitive inspections of the spar carry through assembly until it is 
replaced with a different part numbered spar carry through assembly. AD 
83-20-03 establishes life limits for the wing spar structural 
components. Since the FAA issued AD 79-01-03 and AD 83-20-03, the FAA 
identified inspection and life limit requirements that were 
inadvertently omitted from those ADs. This proposed AD would retain the 
requirements in AD 79-01-03 and AD 83-20-03 and require the spar carry 
through assembly inspection from AD 79-01-03 for additional airplanes 
and add life limits for certain wing structural components previously 
omitted from AD 83-20-03 for certain serial numbered airplanes. The FAA 
is proposing this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by May 7, 
2021.

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 https://www.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.
    For service information identified in this NPRM, contact Piper 
Aircraft, Inc., 2926 Piper Drive, Vero Beach, FL 32960; phone: (772) 
567-4361; website: https://www.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 (816) 329-4148.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-0881; 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, any comments 
received, and other information. The street address for Docket 
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Dan McCully, Aviation Safety Engineer, 
FAA, Atlanta ACO Branch, 1701 Columbia Avenue, College Park, GA 30337; 
phone: (404) 474-5548; fax: (404) 474-5606; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2020-0881; 
Project Identifier 2018-CE-024-AD.'' 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 the 
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 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this proposed AD.

[[Page 15440]]

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 Dan 
McCully, Aviation Safety Engineer, FAA, Atlanta ACO Branch, 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 issued AD 79-01-03, Amendment 39-3383 (44 FR 36, January 2, 
1979), Docket No. 78-EA-69 (AD 79-01-03), for certain Piper Model PA-
36-285 airplanes. AD 79-01-03 requires repetitive inspections of spar 
carry through assembly part number (P/N) 97370-00, with repair as 
necessary, until the spar carry through assembly is replaced with P/N 
76824-02. AD 79-01-03 was prompted by reports of cumulative damage to 
the wing spar carry through assembly, which resulted from fatigue 
testing and other field evidence of movement between the leg of the 
spar cap and the spar web. The FAA issued AD 79-01-03 to prevent 
hazards in flight associated with damage of the wing spar carry through 
assembly.
    The FAA also issued AD 83-20-03, Amendment 39-4739 (48 FR 45535, 
October 6, 1983), Docket No. 83-CE-23-AD (AD 83-20-03), for Piper 
Models PA-36-285, PA-36-300, and PA-36-375 airplanes. AD 83-20-03 
establishes life limits for certain wing structural components. AD 83-
20-03 was prompted by manufacturer laboratory fatigue tests of the wing 
structure that identified the need to establish a service life limit 
for the wing structural components. The FAA issued AD 83-20-03 to 
prevent failure of the wing structural components because of fatigue 
damage.

Actions Since AD 79-01-03 and AD 83-20-03 Were Issued

    Since the FAA issued AD 79-01-03 and AD 83-20-03, the FAA 
identified inconsistencies between the two ADs and the airplanes' type 
certificate. The FAA determined that the life limits for the spar carry 
through assembly, P/N 97370-00 or 76824-02, were inadvertently omitted 
from AD 83-20-03 for certain airplanes. The FAA is issuing this NPRM to 
add the life limit for the spar carry through assembly for Models PA-
36-285 and PA-36-300 airplanes, serial numbers 36-7660123 through 36-
8160023, and Model PA-36-375 airplanes, serial numbers 36-7802001 
through 36-8302025. The FAA also determined the repetitive inspections 
of the spar carry through assembly required by AD 79-01-03 should apply 
to both Model PA-36-285 and Model PA-36-300 airplanes until the life 
limit replacement of the spar carry through assembly with P/N 76824-02. 
After the initial life limit replacement of the wing spar carry through 
assembly required by AD 83-20-03 (P/N 97370-00 with P/N 76824-02), the 
inspections required by AD 79-01-03 are no longer be required. In this 
NPRM, the FAA proposes to supersede both of those ADs.

FAA's Determination

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

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Piper Aircraft, Inc., Service Bulletin No. 552A, 
dated August 3, 2018 (Piper SB No. 552A); Piper Aircraft PA-36, Pawnee 
Brave Kit 764-394, Right Wing Main Spar Caps Replacement, dated June 9, 
2012 (Piper Kit 764-394); and Piper Aircraft PA-36, Pawnee Brave Kit 
764-393, Left Wing Main Spar Caps Replacement, dated June 9, 2012 
(Piper Kit 764-393). Piper SB No. 552A applies to Models PA-36-285 and 
PA-36-300 airplanes and contains procedures for repetitively inspecting 
wing spar carry through assembly P/N 97370-00. Piper Kit 764-394 
identifies the applicable parts and specifies procedures for replacing 
the right wing main spar caps, which includes the attachment bolts and 
wing carry through spar fittings and assembly. Piper Kit 764-393 
identifies the applicable parts and specifies procedures for replacing 
the left wing main spar caps, which includes the attachment bolts and 
wing carry through spar fittings and assembly. 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 the ADDRESSES section.

Other Related Service Information

    The FAA also reviewed Piper Aircraft Corporation Service Bulletin 
No. 552, dated February 3, 1978 (Piper SB No. 552). Piper SB No. 552 
contains the same procedures as Piper SB No. 552A, but Piper SB No. 552 
only applies to Model PA-36-285 airplanes.

Proposed AD Requirements in This NPRM

    This proposed AD would retain all of the requirements of AD 79-01-
03 and AD 83-20-03 but would apply some of the requirements to 
additional serial-numbered airplanes.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 123 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
----------------------------------------------------------------------------------------------------------------
Inspection of P/N 97370-00 wing     8 work-hours x $85     Not applicable.......            $680         $83,640
 spar carry through assembly.        per hour = $680.
Replacement of the wing attachment  10 work-hours x $85    $1,310 (both bolts)..           2,160         265,680
 upper bolt and lower bolt.          per hour = $850.
* Replacement of wing carry         30 work-hours x $85    $23,467..............          26,017       3,200,091
 through spar assembly.              per hour = $2,550.

[[Page 15441]]

 
** Replacement of Piper Kit 764-    20 work-hours x $85    $26,867 (both kits)..          28,567       3,513,741
 393 (Left) and Piper Kit            per hour = $1,700.
 764[dash]394 (Right).
----------------------------------------------------------------------------------------------------------------
* The wing carry through spar fitting, P/N 97713-03, is included in the wing carry through spar assembly, P/N
  76824-02.
** The replacement for the wing spar fitting P/N 97712-00 and the replacement for spar assembly P/Ns 97701-00
  and 97701-01 are included in Piper Kit 764-393 and Piper Kit 764-394.

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 has 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 that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction, 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:
0
a. Removing Airworthiness Directive 79-01-03, Amendment 39-3383 (44 FR 
36, January 2, 1979), Docket No. 78-EA-69; and Airworthiness Directive 
83-20-03, Amendment 39-4739 (48 FR 45535, October 6, 1983), Docket No. 
83-CE-23-AD; and
0
b. Adding the following new airworthiness directive:

Piper Aircraft, Inc.: Docket No. FAA-2020-0881; Project Identifier 
2018-CE-024-AD.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) action by May 7, 2021.

(b) Affected ADs

    This AD replaces AD 79-01-03, Amendment 39-3383 (44 FR 36, 
January 2, 1979), Docket No. 78-EA-69 (AD 79-01-03); and AD 83-20-
03, Amendment 39-4739 (48 FR 45535, October 6, 1983), Docket No. 83-
CE-23-AD (83-20-03).

(c) Applicability

    This AD applies to Piper Aircraft, Inc. Models PA-36-285, PA-36-
300, and PA-36-375 airplanes, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC) Code 5700, Wings.

(e) Unsafe Condition

    This AD was prompted by a review of AD 83-20-03 and AD 79-01-03 
and the determination that the requirements of those ADs did not 
address all of the affected airplanes. The FAA is issuing this AD to 
prevent fatigue damage to the wing structural components. The unsafe 
condition, if not addressed, could result in failure of the wing 
structure with consequent loss of control.

(f) Compliance

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

(g) Inspection of the Wing Spar Carry Through Assembly

    (1) For Models PA-36-285 and PA-36-300 airplanes, serial numbers 
36-7360001 through 36-7560003, with a wing spar carry through 
assembly part number (P/N) 97370-00 installed, before the airplane 
accumulates a total of 2,000 hours time-in-service (TIS) or within 
25 hours TIS after the effective date of this AD, whichever occurs 
later, and thereafter at intervals not to exceed 100 hours TIS, 
inspect the wing spar carry through assembly by following the 
Instructions, section 1, of Piper Aircraft, Inc., Service Bulletin 
No. 552A, dated August 3, 2018, (Piper SB No. 552A).
    (2) If any damage is found during any inspection required by 
paragraph (g)(1) of this AD, before further flight, repair or 
replace the wing spar carry through assembly by following the 
Instructions, section 2, of Piper SB No. 552A.
    (3) Replacing wing spar carry through assembly P/N 97370-00 with 
wing spar carry through assembly P/N 76824-02 terminates the 
repetitive inspections required by paragraph (g)(1) of this AD.

(h) Life Limit Replacement of Wing Structural Components

    Remove from service the wing structural components specified in 
paragraphs (h)(1) through (8) of this AD before the part accumulates 
the life limit hours TIS set forth in table 1 to paragraph (h) of 
this AD. If, on the effective date of this AD, the component will 
reach its life limit within 100 hours TIS or has already reached its 
life limit, remove the part from service within 100 hours TIS after 
the effective date of this AD.
    (1) Remove from service wing attachment upper bolt P/N 77245-00 
and replace with an unused (zero hours TIS) wing attachment upper 
bolt P/N 77245-00.
    (2) Remove from service any wing carry through spar fitting P/Ns 
97713-00, 97713-02, or 97713-03 and replace with an unused (zero 
hours TIS) wing carry through spar fitting P/N 97713-03.

    Note 1 to paragraph (h)(2): Wing carry through spar fitting P/N 
97713-03 is included as part of spar carry through assembly P/N 
76824-02.

    (3) Remove from service wing spar fitting P/N 97712-00 and 
replace with an unused (zero hours TIS) wing spar fitting P/N 97712-
00 by following steps D(1)(a) through D(1)(c)

[[Page 15442]]

or section D(2), in Piper Aircraft, PA-36, Pawnee Brave Kit 764-393, 
Left Wing Main Spar Caps Replacement, dated June 9, 2012 (Piper Kit 
764-393), or Piper Aircraft, PA-36, Pawnee Brave Kit 764-394, Right 
Wing Main Spar Caps Replacement, dated June 9, 2012 (Piper Kit 764-
394), as applicable.

    Note 2 to paragraph (h)(3): This note applies to paragraphs 
(h)(3) and (7) of this AD. Replacement parts for the left and right 
wing spar fittings P/N 97712-00 and the right, left, top, and bottom 
spar assemblies P/Ns 97701-00 and 97701-01 are included with Piper 
Kit 764-393 and Piper Kit 764-394.

    (4) Remove from service spar carry through assembly P/N 97370-00 
or 76824-02, as applicable, and replace with an unused (zero hours 
TIS) spar carry through assembly P/N 76824-02.
    (5) Remove from service spar assembly P/Ns 97701-00 and 97701-
01, Revision P or later revision, and replace with an unused (zero 
hours TIS) spar assembly by following the Instructions, sections B. 
and C., in Piper Kit 764-393 or Piper Kit 764-394, as applicable.
    (6) Remove from service any spar carry through assembly P/N 
76767-00 or P/N 76824-02 and replace with an unused (zero hours TIS) 
spar carry through assembly P/N 76824-02.
    (7) Remove from service spar assemblies P/Ns 97701-00 and 97701-
01, Revision N or earlier revision, and replace with an unused (zero 
hours TIS) left spar cap replacement kit P/N 764-393 and right spar 
cap replacement kit P/N 764-394 by following the Instructions, 
sections B. and C., in Piper Kit 764-393 or Piper Kit 764-394, as 
applicable.
    (8) Remove from service wing attachment lower bolt P/N 77245-00 
and replace with an unused (zero hours TIS) P/N 77245-00 bolt.
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(i) 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 Piper Aircraft Corporation Service Bulletin No. 552, 
dated February 3, 1978.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta ACO 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 certification office, send it to the attention of the 
person identified in Related Information.
    (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.

[[Page 15443]]

    (3) AMOCs approved for AD 79-01-03 and AD 83-20-03 are approved 
as AMOCs for the corresponding provisions of this AD.

(k) Related Information

    (1) For more information about this AD, contact Dan McCully, 
Aviation Safety Engineer, FAA, Atlanta ACO Branch, 1701 Columbia 
Avenue, College Park, GA 30337; phone: (404) 474-5548; fax: (404) 
474-5606; email: [email protected].
    (2) For service information identified in this AD, contact Piper 
Aircraft, Inc., 2926 Piper Drive, Vero Beach, FL 32960; phone: (772) 
567-4361; website: www.piper.com. You may view this service 
information at the FAA, Policy and Innovation Division, 901 Locust, 
Kansas City, MO 64106. For information on the availability of this 
material at the FAA, call (816) 329-4148.

    Issued on March 12, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-05584 Filed 3-22-21; 8:45 am]
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