Airworthiness Directives; Pratt & Whitney Turbofan Engines, 52600-52603 [2021-20365]

Download as PDF 52600 Federal Register / Vol. 86, No. 181 / Wednesday, September 22, 2021 / Rules and Regulations determined that notice and public procedures are unnecessary. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Correction Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: (i) No Reporting Requirement Although the service information referenced in CAAI AD ISR–I–57–2020–06– 01 specifies to submit certain information to the manufacturer, this AD does not include that requirement. 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 [Corrected] 2. The FAA corrects § 39.13 by correcting the airworthiness directive published at (86 FR 50451) (October 14, 2021) to read: ■ 2021–17–14 Gulfstream Aerospace LP: Amendment 39–21697; Docket No. FAA–2021–0459; Project Identifier MCAI–2021–00129–T. (a) Effective Date This airworthiness directive (AD) is effective October 14, 2021. (b) Affected ADs None. (c) Applicability This AD applies to Gulfstream Aerospace LP Model Gulfstream G280 airplanes, certificated in any category, as identified in The Civil Aviation Authority of Israel (CAAI) AD ISR–I–57–2020–06–01, dated January 27, 2021 (CAAI AD ISR–I–57–2020–06–01). (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a report that during full-scale fatigue testing, a crack was found in the area of the attachment of the wing rib 0 to the front spar. The FAA is issuing this AD to address any cracking at the area of the wing rib 0 to the front spar, which could affect the structural integrity of the wing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, CAAI AD ISR–I–57–2020– 06–01. VerDate Sep<11>2014 16:04 Sep 21, 2021 Jkt 253001 (h) Exception to CAAI AD ISR–I–57–2020– 06–01 Where CAAI AD ISR–I–57–2020–06–01 requires compliance ‘‘not later than 5,000 flight cycles,’’ this AD requires compliance before the accumulation of 5,000 total flight cycles since the date of issuance of the original Israeli airworthiness certificate or the date of issuance of the original Israeli export certificate of airworthiness. (j) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or CAAI; or CAAI’s authorized Designee. If approved by the CAAI Designee, the approval must include the Designee’s authorized signature. (k) Related Information For more information about this AD, contact Tom Rodriguez, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3226; email Tom.Rodriguez@ faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on October 14, 2021 (86 FR 50451, September 9, 2021). (i) Civil Aviation Authority of Israel (CAAI) AD ISR–I–57–2020–06–01, dated January 27, 2021. (ii) [Reserved] PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 (4) For CAAI AD ISR–I–57–2020–06–01, contact CAAI, P.O. Box 1101, Golan Street, Airport City, 70100, Israel; telephone 972–3– 9774665; fax 972–3–9774592; email aip@ mot.gov.il. You may find this CAAI AD on the CAAI website at https://www.caa.gov.il. (5) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (6) 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: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on September 16, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–20404 Filed 9–21–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0515; Project Identifier AD–2021–00191–E; Amendment 39–21739; AD 2021–20–01] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney PW1500G and PW1900G series turbofan engines with a certain high-pressure turbine (HPT) 1st-stage hub or HPT rotor 1st-stage blade retaining plate installed. This AD was prompted by a report from the manufacturer who determined that the HPT 1st-stage hub and HPT rotor 1ststage blade retaining plate fail to meet the published life-cycle limits for each part. This AD requires removal and replacement of the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate prior to reaching certain cycle limits. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 27, 2021. ADDRESSES: For service information identified in this final rule, contact Pratt & Whitney, 400 Main Street, East Hartford, CT 06118; phone: (800) 565– SUMMARY: E:\FR\FM\22SER1.SGM 22SER1 Federal Register / Vol. 86, No. 181 / Wednesday, September 22, 2021 / Rules and Regulations 0140; fax: (860) 565–5442; email: help24@prattwhitney.com; website: https://fleetcare.prattwhitney.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. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 0515. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0515; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Mark Taylor, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7229; fax: (781) 238–7199; email: Mark.Taylor@faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Pratt & Whitney PW1500G and PW1900G series turbofan engines with a certain HPT 1st-stage hub or HPT rotor 1st-stage blade retaining plate installed. The NPRM published in the Federal Register on June 29, 2021 (86 FR 34166). The NPRM was prompted by a report from the manufacturer who determined that the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate fail to meet the published lifecycle limits for each part. In the NPRM, the FAA proposed to require removal and replacement of the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate prior to reaching certain cycle limits. The FAA is issuing this AD to address the unsafe condition on these products. Discussion of Final Airworthiness Directive Comments The FAA received comments from two commenters. The commenters were Delta Air Lines, Inc. (DAL) and the Air Line Pilots Association, International (ALPA). The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Correct Required Actions DAL requested that the FAA change paragraph (g)(1)(ii) of this AD from removing the affected part and replacing with a part eligible for installation ‘‘at the next engine shop visit after accumulating 4,700 CSN. . .’’ to ‘‘at the next engine shop visit after accumulating 4,960 CSN. . .’’ to mirror the 4,960 CSN listed earlier in the paragraph. DAL suggested that ‘‘4,700 CSN’’ is a typographical error. The FAA disagrees that ‘‘4,700 CSN’’ is a typographical error. It is the cyclic value at which point certain HPT parts are to be removed from service. In contrast, ‘‘4,960 CSN on the effective date of this AD’’ is a calculated point at which HPT-part removal requirements transition from the requirements of 52601 paragraph (g)(1)(ii) of this AD to the requirements of paragraph (g)(1)(iii) of this AD. ‘‘4,960 CSN’’ and ‘‘4,700 CSN’’ are different in their function and how they are calculated. The FAA did not change this AD. Support for the AD ALPA expressed support for the NPRM as written. Conclusion The FAA reviewed the relevant data, considered any comments received, and determined that air safety requires adopting this AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. This AD is adopted as proposed in the NPRM. Related Service Information The FAA reviewed Pratt & Whitney Service Bulletin (SB) PW1000G–A–72– 00–0115–00B–930A–D, Issue No. 001, dated April 26, 2021, and Pratt & Whitney SB PW1000G–A–72–00–0168– 00A–930A–D, Issue No. 001, dated April 26, 2021. These SBs describe procedures for removing and replacing the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate. Costs of Compliance The FAA estimates that this AD affects 88 engines installed on airplanes of U.S. registry. The FAA estimates that in most cases the affected HPT 1st-stage hub and the affected HPT 1st-stage blade retaining plate will both be replaced during the same disassembly of the engine. This cost estimate therefore reflects the cost of replacing both parts during the same engine disassembly. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Replace HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate (pro-rated part cost). 300 work-hours × $85 per hour = $25,500 .... 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 VerDate Sep<11>2014 16:04 Sep 21, 2021 Jkt 253001 Parts cost 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 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 $86,252 Cost per product $111,752 Cost on U.S. operators $9,834,176 develop on products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and E:\FR\FM\22SER1.SGM 22SER1 52602 Federal Register / Vol. 86, No. 181 / Wednesday, September 22, 2021 / Rules and Regulations responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2021–20–01 Pratt & Whitney: Amendment 39–21739; Docket No. FAA–2021–0515; Project Identifier AD–2021–00191–E. (a) Effective Date This airworthiness directive (AD) is effective October 27, 2021. (b) Affected ADs None. (c) Applicability This AD applies to Pratt & Whitney PW1519G, PW1521G, PW1521G–3, PW1521GA, PW1524G, PW1524G–3, PW1525G, PW1525G–3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G–A model turbofan engines with a high-pressure turbine (HPT) 1st-stage hub, part number (P/N) 30G5701, or an HPT rotor 1st-stage blade retaining plate, P/N 30G1692, installed. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by a report from the manufacturer who determined that the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate fail to meet the published life-cycle limits for each part. The FAA is issuing this AD to prevent failure of the HPT 1st-stage hub or HPT rotor 1st-stage blade retaining plate. The unsafe condition, if not addressed, could result in the release VerDate Sep<11>2014 16:04 Sep 21, 2021 Jkt 253001 of the HPT 1st-stage hub or HPT rotor 1ststage blade retaining plate, damage to the engine, and damage to the aircraft. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For PW1519G, PW1521G, PW1521G–3, PW1521GA, PW1524G, and PW1524G–3 model turbofan engines: (i) For an affected HPT 1st-stage hub and an affected HPT rotor 1st-stage blade retaining plate with 3,000 cycles since new (CSN) or fewer on the effective date of this AD, before the affected part exceeds 4,700 CSN, remove the affected part, as applicable, and replace with a part eligible for installation. (ii) For an affected HPT 1st-stage hub and an affected HPT rotor 1st-stage blade retaining plate with greater than 3,000 CSN but fewer than 4,960 CSN on the effective date of the AD, at the next engine shop visit after accumulating 4,700 CSN or before the affected part exceeds 5,260 CSN, whichever occurs first, remove the affected part, as applicable, and replace with a part eligible for installation. (iii) For an affected HPT 1st-stage hub and an affected HPT rotor 1st-stage blade retaining plate with 4,960 CSN or greater on the effective date of the AD, at the next engine shop visit or within 300 cycles after the effective date of this AD, whichever occurs first, remove the affected part, as applicable, and replace with a part eligible for installation. (2) For PW1919G and PW1921G model turbofan engines: (i) For an affected HPT 1st-stage hub and an affected HPT rotor 1st-stage blade retaining plate with 3,000 CSN or fewer on the effective date of this AD, before the affected part exceeds 4,700 CSN, remove the affected part, as applicable, and replace with a part eligible for installation. (ii) For an affected HPT 1st-stage hub and an affected HPT rotor 1st-stage blade retaining plate with greater than 3,000 CSN but fewer than 4,700 CSN on the effective date of the AD, at the next engine shop visit after the affected part accumulates 4,700 CSN or before the affected part exceeds 5,000 CSN, whichever occurs first, remove the affected part, as applicable, and replace with a part eligible for installation. (iii) For an affected HPT 1st-stage hub and an affected HPT rotor 1st-stage blade retaining plate with 4,700 CSN or greater on the effective date of the AD, at the next engine shop visit or within 300 cycles after the effective date of this AD, whichever occurs first, remove the affected part, as applicable, and replace with a part eligible for installation. (3) For PW1525G and PW1525G–3 model turbofan engines: (i) Before the affected HPT 1st-stage hub and affected HPT rotor 1st-stage blade retaining plate exceeds 2,800 CSN, respectively, or within 300 cycles after the effective date of this AD, whichever occurs later, remove the affected part, as applicable, PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 and replace with a part eligible for installation. (ii) [Reserved] (4) For PW1922G, PW1923G, and PW1923G–A model turbofan engines: (i) Before the affected HPT 1st-stage hub and affected HPT rotor 1st-stage blade retaining plate exceeds 3,000 CSN, respectively, or within 300 cycles after the effective date of this AD, whichever occurs later, remove the affected part, as applicable, and replace with a part eligible for installation. (ii) [Reserved] (h) Definitions (1) For the purpose of this AD, an ‘‘engine shop visit’’ is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine case flanges, except for the following, which do not constitute an engine shop visit: (i) Separation of engine flanges solely for the purposes of transportation without subsequent maintenance does not constitute an engine shop visit. (ii) Separation of engine flanges solely for the purpose of replacing the fan without subsequent maintenance does not constitute an engine shop visit. (2) For the purpose of this AD, a ‘‘part eligible for installation’’ is: (i) For PW1519G, PW1521G, PW1521G–3, PW1521GA, PW1524G, PW1524G–3, PW1919G, and PW1921G model turbofan engines: (A) Any HPT 1st-stage hub with P/N 30G5701 with 4,700 CSN or fewer, or with a P/N not listed in this AD. (B) Any HPT rotor 1st-stage blade retaining plate with P/N 30G1692 with 4,700 CSN or fewer, or with a P/N not listed in this AD. (ii) For PW1525G and PW1525G–3 model turbofan engines: (A) Any HPT 1st-stage hub with P/N 30G5701 with 2,800 CSN or fewer, or with a P/N not listed in this AD. (B) Any HPT rotor 1st-stage blade retaining plate with P/N 30G1692 with 2,800 CSN or fewer, or with a P/N not listed in this AD. (iii) For PW1922G, PW1923G, and PW1923G–A model turbofan engines: (A) Any HPT 1st-stage hub with P/N 30G5701 with 3,000 CSN or fewer, or with a P/N not listed in this AD. (B) Any HPT rotor 1st-stage blade retaining plate with P/N 30G1692 with 3,000 CSN or fewer, or with a P/N not listed in this AD. (i) 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 paragraph (j) of this AD. 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 E:\FR\FM\22SER1.SGM 22SER1 Federal Register / Vol. 86, No. 181 / Wednesday, September 22, 2021 / Rules and Regulations of the local flight standards district office/ certificate holding district office. FOR FURTHER INFORMATION CONTACT: (j) Related Information For more information about this AD, contact Mark Taylor, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7229; fax: (781) 238–7199; email: Mark.Taylor@faa.gov. (k) Material Incorporated by Reference None. Issued on September 14, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–20365 Filed 9–21–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2021–0518; Airspace Docket No. 21–ASW–12] RIN 2120–AA66 Amendment of Class E Airspace; Oklahoma City, OK This action amends the Class E airspace at Sundance Airport, Oklahoma City, OK. This action is the result of an airspace review due to the decommissioning of the Sundance Localizer (LOC). DATES: Effective 0901 UTC, December 2, 2021. The Director of the Federal Register approves this incorporation by reference action under 1 CFR part 51, subject to the annual revision of FAA Order JO 7400.11 and publication of conforming amendments. ADDRESSES: FAA Order JO 7400.11F, Airspace Designations and Reporting Points, and subsequent amendments can be viewed online at https:// www.faa.gov/air_traffic/publications/. For further information, you can contact the Airspace Policy Group, Federal Aviation Administration, 800 Independence Avenue SW, Washington, DC 20591; telephone: (202) 267–8783. The Order is also available for inspection at the National Archives and Records Administration (NARA). For information on the availability of FAA Order JO 7400.11F at NARA, email: fr.inspection@nara.gov or go to https:// www.archives.gov/federal-register/cfr/ ibr-locations.html. SUMMARY: 16:04 Sep 21, 2021 SUPPLEMENTARY INFORMATION: Authority for This Rulemaking The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. 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. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart I, Section 40103. Under that section, the FAA is charged with prescribing regulations to assign the use of airspace necessary to ensure the safety of aircraft and the efficient use of airspace. This regulation is within the scope of that authority as it amends the Class E airspace extending upward from 700 feet above the surface at Sundance Airport, Oklahoma City, OK, to support instrument flight rule operations at these airports. History Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: VerDate Sep<11>2014 Jeffrey Claypool, Federal Aviation Administration, Operations Support Group, Central Service Center, 10101 Hillwood Parkway, Fort Worth, TX 76177; telephone (817) 222–5711. Jkt 253001 The FAA published a notice of proposed rulemaking in the Federal Register (86 FR 34168; June 29, 2021) for Docket No. FAA–2021–0518 to amend the Class E airspace at Sundance Airport, Oklahoma City, OK. Interested parties were invited to participate in this rulemaking effort by submitting written comments on the proposal to the FAA. No comments were received. Class E airspace designations are published in paragraph 6005 of FAA Order JO 7400.11F, dated August 10, 2021, and effective September 15, 2021, which is incorporated by reference in 14 CFR 71.1. The Class E airspace designations listed in this document will be published subsequently in the Order. Availability and Summary of Documents for Incorporation by Reference This document amends FAA Order JO 7400.11F, Airspace Designations and Reporting Points, dated August 10, 2021, and effective September 15, 2021. FAA Order JO 7400.11F is publicly available as listed in the ADDRESSES section of this document. FAA Order JO 7400.11F lists Class A, B, C, D, and E airspace areas, air traffic service routes, and reporting points. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 52603 The Rule This amendment to 14 CFR part 71 amends the Class E airspace extending upward from 700 feet above the surface to within a 6.5-mile (decreased from a 6.8-mile) radius of Sundance Airport, Oklahoma City, OK. This action is the result of an airspace review caused by the decommissioning of the Sundance LOC which provided guidance to instrument procedures at this airport. FAA Order JO 7400.11, Airspace Designations and Reporting Points, is published yearly and effective on September 15. Regulatory Notices and Analyses The FAA has determined that this regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current, is non-controversial and unlikely to result in adverse or negative comments. It, therefore: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034; February 26, 1979); and (3) does not warrant preparation of a regulatory evaluation as the anticipated impact is so minimal. Since this is a routine matter that only affects air traffic procedures and air navigation, it is certified that this rule, when promulgated, does not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Environmental Review The FAA has determined that this action qualifies for categorical exclusion under the National Environmental Policy Act in accordance with FAA Order 1050.1F, ‘‘Environmental Impacts: Policies and Procedures,’’ paragraph 5–6.5.a. This airspace action is not expected to cause any potentially significant environmental impacts, and no extraordinary circumstances exist that warrant preparation of an environmental assessment. Lists of Subjects in 14 CFR Part 71 Airspace, Incorporation by reference, Navigation (air). Adoption of the Amendment In consideration of the foregoing, the Federal Aviation Administration amends 14 CFR part 71 as follows: E:\FR\FM\22SER1.SGM 22SER1

Agencies

[Federal Register Volume 86, Number 181 (Wednesday, September 22, 2021)]
[Rules and Regulations]
[Pages 52600-52603]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-20365]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0515; Project Identifier AD-2021-00191-E; 
Amendment 39-21739; AD 2021-20-01]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Pratt & Whitney PW1500G and PW1900G series turbofan engines with a 
certain high-pressure turbine (HPT) 1st-stage hub or HPT rotor 1st-
stage blade retaining plate installed. This AD was prompted by a report 
from the manufacturer who determined that the HPT 1st-stage hub and HPT 
rotor 1st-stage blade retaining plate fail to meet the published life-
cycle limits for each part. This AD requires removal and replacement of 
the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate 
prior to reaching certain cycle limits. The FAA is issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective October 27, 2021.

ADDRESSES: For service information identified in this final rule, 
contact Pratt & Whitney, 400 Main Street, East Hartford, CT 06118; 
phone: (800) 565-

[[Page 52601]]

0140; fax: (860) 565-5442; email: [email protected]; website: 
https://fleetcare.prattwhitney.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. It is also available at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0515.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0515; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this final rule, any 
comments received, and other information. The address for Docket 
Operations is U.S. Department of Transportation, Docket Operations, M-
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue 
SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Mark Taylor, Aviation Safety Engineer, 
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 
(781) 238-7229; fax: (781) 238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to all Pratt & Whitney 
PW1500G and PW1900G series turbofan engines with a certain HPT 1st-
stage hub or HPT rotor 1st-stage blade retaining plate installed. The 
NPRM published in the Federal Register on June 29, 2021 (86 FR 34166). 
The NPRM was prompted by a report from the manufacturer who determined 
that the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining 
plate fail to meet the published life-cycle limits for each part. In 
the NPRM, the FAA proposed to require removal and replacement of the 
HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate prior 
to reaching certain cycle limits. The FAA is issuing this AD to address 
the unsafe condition on these products.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from two commenters. The commenters were 
Delta Air Lines, Inc. (DAL) and the Air Line Pilots Association, 
International (ALPA). The following presents the comments received on 
the NPRM and the FAA's response to each comment.

Request To Correct Required Actions

    DAL requested that the FAA change paragraph (g)(1)(ii) of this AD 
from removing the affected part and replacing with a part eligible for 
installation ``at the next engine shop visit after accumulating 4,700 
CSN. . .'' to ``at the next engine shop visit after accumulating 4,960 
CSN. . .'' to mirror the 4,960 CSN listed earlier in the paragraph. DAL 
suggested that ``4,700 CSN'' is a typographical error.
    The FAA disagrees that ``4,700 CSN'' is a typographical error. It 
is the cyclic value at which point certain HPT parts are to be removed 
from service. In contrast, ``4,960 CSN on the effective date of this 
AD'' is a calculated point at which HPT-part removal requirements 
transition from the requirements of paragraph (g)(1)(ii) of this AD to 
the requirements of paragraph (g)(1)(iii) of this AD. ``4,960 CSN'' and 
``4,700 CSN'' are different in their function and how they are 
calculated. The FAA did not change this AD.

Support for the AD

    ALPA expressed support for the NPRM as written.

Conclusion

    The FAA reviewed the relevant data, considered any comments 
received, and determined that air safety requires adopting this AD as 
proposed. Accordingly, the FAA is issuing this AD to address the unsafe 
condition on these products. This AD is adopted as proposed in the 
NPRM.

Related Service Information

    The FAA reviewed Pratt & Whitney Service Bulletin (SB) PW1000G-A-
72-00-0115-00B-930A-D, Issue No. 001, dated April 26, 2021, and Pratt & 
Whitney SB PW1000G-A-72-00-0168-00A-930A-D, Issue No. 001, dated April 
26, 2021. These SBs describe procedures for removing and replacing the 
HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate.

Costs of Compliance

    The FAA estimates that this AD affects 88 engines installed on 
airplanes of U.S. registry. The FAA estimates that in most cases the 
affected HPT 1st-stage hub and the affected HPT 1st-stage blade 
retaining plate will both be replaced during the same disassembly of 
the engine. This cost estimate therefore reflects the cost of replacing 
both parts during the same engine disassembly.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Replace HPT 1st-stage hub and HPT       300 work-hours x $85 per         $86,252        $111,752      $9,834,176
 rotor 1st-stage blade retaining plate   hour = $25,500.
 (pro-rated part cost).
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and

[[Page 52602]]

responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

2021-20-01 Pratt & Whitney: Amendment 39-21739; Docket No. FAA-2021-
0515; Project Identifier AD-2021-00191-E.

(a) Effective Date

    This airworthiness directive (AD) is effective October 27, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Pratt & Whitney PW1519G, PW1521G, PW1521G-3, 
PW1521GA, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G, 
PW1922G, PW1923G, and PW1923G-A model turbofan engines with a high-
pressure turbine (HPT) 1st-stage hub, part number (P/N) 30G5701, or 
an HPT rotor 1st-stage blade retaining plate, P/N 30G1692, 
installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
Section.

(e) Unsafe Condition

    This AD was prompted by a report from the manufacturer who 
determined that the HPT 1st-stage hub and HPT rotor 1st-stage blade 
retaining plate fail to meet the published life-cycle limits for 
each part. The FAA is issuing this AD to prevent failure of the HPT 
1st-stage hub or HPT rotor 1st-stage blade retaining plate. The 
unsafe condition, if not addressed, could result in the release of 
the HPT 1st-stage hub or HPT rotor 1st-stage blade retaining plate, 
damage to the engine, and damage to the aircraft.

(f) Compliance

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

(g) Required Actions

    (1) For PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, and 
PW1524G-3 model turbofan engines:
    (i) For an affected HPT 1st-stage hub and an affected HPT rotor 
1st-stage blade retaining plate with 3,000 cycles since new (CSN) or 
fewer on the effective date of this AD, before the affected part 
exceeds 4,700 CSN, remove the affected part, as applicable, and 
replace with a part eligible for installation.
    (ii) For an affected HPT 1st-stage hub and an affected HPT rotor 
1st-stage blade retaining plate with greater than 3,000 CSN but 
fewer than 4,960 CSN on the effective date of the AD, at the next 
engine shop visit after accumulating 4,700 CSN or before the 
affected part exceeds 5,260 CSN, whichever occurs first, remove the 
affected part, as applicable, and replace with a part eligible for 
installation.
    (iii) For an affected HPT 1st-stage hub and an affected HPT 
rotor 1st-stage blade retaining plate with 4,960 CSN or greater on 
the effective date of the AD, at the next engine shop visit or 
within 300 cycles after the effective date of this AD, whichever 
occurs first, remove the affected part, as applicable, and replace 
with a part eligible for installation.
    (2) For PW1919G and PW1921G model turbofan engines:
    (i) For an affected HPT 1st-stage hub and an affected HPT rotor 
1st-stage blade retaining plate with 3,000 CSN or fewer on the 
effective date of this AD, before the affected part exceeds 4,700 
CSN, remove the affected part, as applicable, and replace with a 
part eligible for installation.
    (ii) For an affected HPT 1st-stage hub and an affected HPT rotor 
1st-stage blade retaining plate with greater than 3,000 CSN but 
fewer than 4,700 CSN on the effective date of the AD, at the next 
engine shop visit after the affected part accumulates 4,700 CSN or 
before the affected part exceeds 5,000 CSN, whichever occurs first, 
remove the affected part, as applicable, and replace with a part 
eligible for installation.
    (iii) For an affected HPT 1st-stage hub and an affected HPT 
rotor 1st-stage blade retaining plate with 4,700 CSN or greater on 
the effective date of the AD, at the next engine shop visit or 
within 300 cycles after the effective date of this AD, whichever 
occurs first, remove the affected part, as applicable, and replace 
with a part eligible for installation.
    (3) For PW1525G and PW1525G-3 model turbofan engines:
    (i) Before the affected HPT 1st-stage hub and affected HPT rotor 
1st-stage blade retaining plate exceeds 2,800 CSN, respectively, or 
within 300 cycles after the effective date of this AD, whichever 
occurs later, remove the affected part, as applicable, and replace 
with a part eligible for installation.
    (ii) [Reserved]
    (4) For PW1922G, PW1923G, and PW1923G-A model turbofan engines:
    (i) Before the affected HPT 1st-stage hub and affected HPT rotor 
1st-stage blade retaining plate exceeds 3,000 CSN, respectively, or 
within 300 cycles after the effective date of this AD, whichever 
occurs later, remove the affected part, as applicable, and replace 
with a part eligible for installation.
    (ii) [Reserved]

(h) Definitions

    (1) For the purpose of this AD, an ``engine shop visit'' is the 
induction of an engine into the shop for maintenance involving the 
separation of pairs of major mating engine case flanges, except for 
the following, which do not constitute an engine shop visit:
    (i) Separation of engine flanges solely for the purposes of 
transportation without subsequent maintenance does not constitute an 
engine shop visit.
    (ii) Separation of engine flanges solely for the purpose of 
replacing the fan without subsequent maintenance does not constitute 
an engine shop visit.
    (2) For the purpose of this AD, a ``part eligible for 
installation'' is:
    (i) For PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, PW1524G-
3, PW1919G, and PW1921G model turbofan engines:
    (A) Any HPT 1st-stage hub with P/N 30G5701 with 4,700 CSN or 
fewer, or with a P/N not listed in this AD.
    (B) Any HPT rotor 1st-stage blade retaining plate with P/N 
30G1692 with 4,700 CSN or fewer, or with a P/N not listed in this 
AD.
    (ii) For PW1525G and PW1525G-3 model turbofan engines:
    (A) Any HPT 1st-stage hub with P/N 30G5701 with 2,800 CSN or 
fewer, or with a P/N not listed in this AD.
    (B) Any HPT rotor 1st-stage blade retaining plate with P/N 
30G1692 with 2,800 CSN or fewer, or with a P/N not listed in this 
AD.
    (iii) For PW1922G, PW1923G, and PW1923G-A model turbofan 
engines:
    (A) Any HPT 1st-stage hub with P/N 30G5701 with 3,000 CSN or 
fewer, or with a P/N not listed in this AD.
    (B) Any HPT rotor 1st-stage blade retaining plate with P/N 
30G1692 with 3,000 CSN or fewer, or with a P/N not listed in this 
AD.

(i) 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 paragraph (j) of this AD. You may email your request 
to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager

[[Page 52603]]

of the local flight standards district office/certificate holding 
district office.

(j) Related Information

    For more information about this AD, contact Mark Taylor, 
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: (781) 238-7229; fax: (781) 238-7199; 
email: [email protected].

(k) Material Incorporated by Reference

    None.

    Issued on September 14, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-20365 Filed 9-21-21; 8:45 am]
BILLING CODE 4910-13-P