Airworthiness Directives; Hélicoptères Guimbal Helicopters, 47038-47041 [2021-17944]

Download as PDF 47038 Federal Register / Vol. 86, No. 160 / Monday, August 23, 2021 / Proposed Rules (d) Subject Air Transport Association (ATA) of America Code 24, Electrical power. (e) Unsafe Condition This AD was prompted by reports of erratic electrical system status on the push button annunciators (PBAs) and the engine instrument and crew alerting system (EICAS), while on-ground and during flight. The FAA is issuing this AD to address erroneous indications that could mislead pilots, causing them to turn off active electrical power sources, leading to partial or complete loss of electrical power. Loss of electrical power could result in the loss of flight displays and reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. jbell on DSKJLSW7X2PROD with PROPOSALS (g) Revision of the Airplane Flight Manual (AFM) Within 60 days after the effective date of this AD: Revise the Emergency Procedures and Non-Normal Procedures sections of the existing AFM and applicable corresponding operational procedures to include the information in Section 03–19, Electrical, of Chapter 03, Emergency Procedures, and Section 05–19, Electrical, of Chapter 05, NonNormal Procedures, of the Bombardier Challenger 300 (Imperial Version) Airplane Flight Manual, Publication No. CSP 100–1, Revision 63, dated April 1, 2021 (for airplanes having serial numbers 20003 through 20500 inclusive); or Bombardier Challenger 350 Airplane Flight Manual, Publication No. CH 350 AFM, Revision 29, dated April 1, 2021 (for airplanes having serial numbers 20501 through 20999 inclusive); as applicable. Note 1 to paragraph (g): For obtaining the sections for Bombardier Challenger 300 (Imperial Version) Airplane Flight Manual, Publication No. CSP 100–1, use Document Identification No. CH 300 AFM–I. (h) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Section 03–19, Electrical, of Chapter 03, Emergency Procedures, and Section 05–19, Electrical, of Chapter 05, Non-Normal Procedures, of the Bombardier Challenger 300 (Imperial Version) Airplane Flight Manual, Publication No. CSP 100–1, Revision 62, dated December 22, 2020; or Bombardier Challenger 350 Airplane Flight Manual, Publication No. CH 350 AFM, Revision 28, dated December 22, 2020; as applicable. Note 2 to paragraph (h): For obtaining the sections for Bombardier Challenger 300 (Imperial Version) Airplane Flight Manual, Publication No. CSP 100–1, use Document Identification No. CH 300 AFM–I. Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. 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, New York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) TCCA AD CF–2020–46, dated November 17, 2020, for related information. This MCAI may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0691. (2) For more information about this AD, contact Steven Dzierzynski, Aerospace Engineer, Avionics and Electrical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7367; fax 516– 794–5531; email 9-avs-nyaco-cos@faa.gov. (3) For service information identified in this AD, contact Bombardier, Inc., 200 CoˆteVertu Road West, Dorval, Que´bec H4S 2A3, Canada; North America toll-free telephone 1– 866–538–1247 or direct-dial telephone 1– 514–855–2999; email ac.yul@ aero.bombardier.com; internet https:// www.bombardier.com. 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. Issued on August 17, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–17943 Filed 8–20–21; 8:45 am] BILLING CODE 4910–13–P (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO VerDate Sep<11>2014 16:56 Aug 20, 2021 Jkt 253001 PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0688; Project Identifier 2019–SW–025–AD] RIN 2120–AA64 Airworthiness Directives; He´licopte`res Guimbal Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for He´licopte`res Guimbal (HG) Model Cabri G2 helicopters. This proposed AD was prompted by the determination that certain parts need life limits and certification maintenance requirement (CMR) tasks. This proposed AD would require establishing life limits and CMR tasks for various parts and removing any parts from service that have reached or exceeded their life limits. Depending on the results of the CMR tasks, this proposed AD would require corrective action. 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 October 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 between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact He´licopte`res Guimbal, Basile Ginel, 1070, rue du Lieutenant Parayre, Ae´rodrome d’Aixen-Provence, 13290 Les Milles, France; telephone 33–04–42–39–10–88; email basile.ginel@guimbal.com; web https:// www.guimbal.com. You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222– 5110. DATES: E:\FR\FM\23AUP1.SGM 23AUP1 Federal Register / Vol. 86, No. 160 / Monday, August 23, 2021 / Proposed Rules Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0688; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the European Aviation Safety Agency (now European Union Aviation Safety Agency (EASA) AD, any comments received, and other information. The street address for Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer, COS Program Management Section, Operational Safety Branch, Compliance & Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228–7330; email andrea.jimenez@faa.gov. SUPPLEMENTARY INFORMATION: jbell on DSKJLSW7X2PROD with PROPOSALS 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–2021–0688; Project Identifier 2019–SW–025–AD’’ 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:// 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 VerDate Sep<11>2014 16:56 Aug 20, 2021 Jkt 253001 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 Andrea Jimenez, Aerospace Engineer, COS Program Management Section, Operational Safety Branch, Compliance & Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228–7330; email andrea.jimenez@faa.gov. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background EASA, which is the Technical Agent for the Member States of the European Union, issued EASA AD 2016–0032, dated February 24, 2016 (EASA AD 2016–0032), to correct an unsafe condition for HG Model Cabri G2 helicopters. EASA AD 2016–0032 states HG has revised the airworthiness limitations and maintenance tasks specified in the existing maintenance manual. EASA further advised the revisions include new and more restrictive applicable life limits and compliance times for applicable tasks. Accordingly, EASA 2016–0032 required replacing each affected part before exceeding its life limit, accomplishing all applicable maintenance tasks within the defined intervals as described in revised maintenance manual and if discrepancies were found accomplishing the corrective actions in accordance with the applicable maintenance instructions or contacting HG. EASA AD 2016–0032 also required revising the existing Aircraft Maintenance Program (AMP) for your helicopter by incorporating the actions specified in the revised maintenance. After EASA issued EASA AD 2016– 0032, HG again revised the airworthiness limitations and maintenance tasks. Accordingly, EASA superseded EASA AD 2016–0032 with EASA AD 2019– 0025, dated February 4, 2019 (EASA AD 2019–0025). EASA advises new and more restrictive life limits have been established for cooling fan part number (P/N) G52–00–001, and P/N G52–00– 002, which have been identified as mandatory for continued airworthiness in He´licopte`res Guimbal Cabri G2 Maintenance Manual (MM) and Instructions for Continued Airworthiness J70–002 Issue 06, Section C, Airworthiness Limitations, dated December 6, 2018 (MM J70–002 Issue 06). In addition to the new life limits, EASA further advises of new and more PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 47039 restrictive inspection intervals identified in MM J70–002–Issue 06 for cooling fan P/N G52–00–001 with a certain mounted cooling fan front flange P/N G52–02–200, or P/N G52–02–201. EASA further advises MM J70–002 Issue 06, revised the tail structure paint to include certain part-numbered tail booms and an additional figure. This condition, if not addressed, could result in parts remaining in service beyond their fatigue life and failure of a part, which could result in loss of control of the helicopter. Accordingly, EASA AD 2019–0025 retains the requirements of EASA AD 2016–0032 and requires replacing each affected part before exceeding its life limit, accomplishing all applicable maintenance tasks within the defined intervals as described in MM J70–002 Issue 6, and if discrepancies are found accomplishing the corrective actions in accordance with the applicable maintenance instructions or contacting HG. EASA AD 2019–0025 also requires revising the tail structure paint scheme to include certain part-numbered tail booms and an additional figure. EASA AD 2019–0025 requires revising the existing AMP for your helicopter by incorporating the actions specified in MM J70–002 Issue 6. FAA’s Determination These helicopters have been approved by EASA and are approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with the European Union, EASA has notified the FAA about the unsafe condition described in its AD. The FAA is proposing this AD after evaluating all known relevant information and determining that the unsafe condition described previously is likely to exist or develop on other helicopters of the same type designs. Related Service Information Under 1 CFR Part 51 The FAA reviewed He´licopte`res Guimbal Cabri G2 MM J70–002 Issue 06. This service information specifies airworthiness life limits, inspection intervals, and CMR requirements for parts installed on Cabri G2 helicopters. Issue 06 establishes life limits for certain part-numbered cooling fan front flanges, and engine pulley ball bearings and CMR requirements for certain cooling fan front flanges. 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. E:\FR\FM\23AUP1.SGM 23AUP1 47040 Federal Register / Vol. 86, No. 160 / Monday, August 23, 2021 / Proposed Rules Proposed AD Requirements in This NPRM This proposed AD would require, before further flight after the effective date of this AD, removing from service certain part-numbered cooling fan front flanges and engine pulley ball bearings that have accumulated or exceeded their life limit. This proposed AD would also require establishing recurring CMR tasks for certain part-numbered cooling fan front flanges. Depending on the results of the CMR tasks, this proposed AD would also require corrective action. Additionally, this proposed AD would require painting certain part-numbered tail booms with glossy white paint. jbell on DSKJLSW7X2PROD with PROPOSALS Differences Between This Proposed AD and EASA AD 2019–0025 EASA AD 2019–0025 requires contacting He´licopte`res Guimbal for corrective actions when a discrepancy is found, whereas this proposed AD would require removing the part from service. EASA AD 2019–0025 requires accomplishing the actions specified in MM J70–002 Issue 06, whereas this proposed AD would require establishing a life limit for certain part-numbered cooling fan front flanges and certain part-numbered engine pulley ball bearings and removing any part from service accordingly instead. EASA AD 2019–0025 requires revising the AMP with the actions specified in MM J70– 002 Issue 06, whereas the proposed AD would not. Costs of Compliance The FAA estimates that this proposed AD would affect 32 helicopters of U.S. Registry. The FAA estimates that operators may incur the following costs in order to comply with this proposed AD. Labor costs are estimated at $85 per work-hour. Replacing a cooling fan front flange would take about 16 work-hours and parts would cost about $4,500 for an estimated cost of $5,860 per helicopter and $187,520 for the U.S. fleet, per replacement cycle. Replacing an engine pulley ball bearing would take about 12 work-hours and parts would cost about $250 for an estimated cost of $1,270 per helicopter and $40,640 for the U.S. fleet, per replacement cycle. The FAA has no way of determining the estimated costs to do allowable repairs based on the results of the CMR tasks. If required, replacing a cracked cooling fan front flange would take about 16 work-hours and parts would cost about $4,500 for an estimated cost of $5,860. The FAA has included all known costs in its cost estimate. According to VerDate Sep<11>2014 16:56 Aug 20, 2021 Jkt 253001 the manufacturer, however, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected operators. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Would not affect intrastate aviation in Alaska, and (3) Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 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: ■ He´licopte`res Guimbal: Docket No. FAA– 2021–0688; Project Identifier 2019–SW– 025–AD. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by October 7, 2021. (b) Affected ADs None. (c) Applicability This AD applies to He´licopte`res Guimbal (HG) Model Cabri G2 helicopters, certificated in any category. (d) Subject Joint Aircraft Service Component (JASC) Code: 7100, Powerplant System. (e) Unsafe Condition This AD was prompted by a notification of certain parts remaining in service beyond their fatigue life or beyond maintenance intervals required by the certification maintenance requirements (CMRs) of the Instructions for Continued Airworthiness. The FAA is issuing this AD to prevent failure of a part, which could result in loss of control of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Before further flight after the effective date of this AD, remove from service any part that has reached or exceeded its life limit, as specified in paragraphs (g)(1)(i) through (iii) of this AD, and thereafter remove from service any part on or before each part reaches its life limit: (i) The life limit for cooling fan front flange part number (P/N) G52–02–200 mounted on pulley (12 screws) P/N G52–10–100 or G52– 10–101; and cooling fan front flange P/N G52–02–201 mounted or having been mounted on pulley (12 screws) P/N G52–10– 100 or G52–10–101, installed on cooling fan P/N G52–00–001 or G52–00–002; is 2,200 total hours time-in-service (TIS). (ii) The life limit for cooling fan front flange P/N G52–02–201 mounted on pulley (24 screws) P/N G52–10–102 and having never been mounted on pulley (12 screws) P/ N G52–10–100 or G52–10–101, installed on cooling fan P/N G52–00–001 or G52–00–002, is 4,400 total hours TIS. (iii) The life limit for engine pulley ball bearing P/N HG61–0790 and HG61–1944, installed on engine pulley assembly P/N G51–14–1XX, is 2,200 total hours TIS. (2) Perform the following CMR tasks as follows: (i) Cooling fan front flange P/N G52–02– 200 mounted on pulley (12 screws) P/N G52– 10–100 or G52–10–101; and cooling fan front E:\FR\FM\23AUP1.SGM 23AUP1 Federal Register / Vol. 86, No. 160 / Monday, August 23, 2021 / Proposed Rules flange P/N G52–02–201 mounted or having been mounted on pulley (12 screws) P/N G52–10–100 or G52–10–101, installed on cooling fan P/N G52–00–001, and with 500 or more total hours TIS since new as of the effective date of this AD: Within 5 hours TIS after the effective date of this AD and thereafter at intervals not to exceed 50 hours TIS, or 70 engine start-stop cycles, whichever occurs first, inspect the cooling fan front flange for a crack in accordance with He´licopte`res Guimbal Cabri G2 Maintenance Manual (MM) and Instructions for Continued Airworthiness J70–002 Issue 06, Section C, Airworthiness Limitations, dated December 6, 2018 (MM J70–002 Issue 06), sub section 52–A–10 Cooling Fan Inspection, paragraphs (c) through (d). If any crack is found, before further flight, remove the cooling fan front flange from service. (ii) Cooling fan front flange P/N G52–02– 200 mounted on pulley (12 screws) P/N G52– 10–100 or G52–10–101; and cooling fan front flange P/N G52–02–201 mounted or having been mounted on pulley (12 screws) P/N G52–10–100 or G52–10–101, installed on cooling fan P/N G52–00–001, and with less than 500 total hours TIS since new as of the effective date of this AD: Before accumulating 500 total hours TIS since new and thereafter at intervals not to exceed 50 hours TIS, or 70 engine start-stop cycles, whichever occurs first, inspect the cooling fan front flange for a crack in accordance with MM J70–002 Issue 06, sub section 52– A–10 Cooling Fan Inspection, paragraphs (c) through (d). If any crack is found, before further flight, remove the cooling fan front flange from service. (iii) Cooling fan front flange P/N G52–02– 201 mounted on pulley (24 screws) P/N G52– 10–102 and having never been mounted on pulley (12 screws) P/N G52–10–100 or G52– 10–101, installed on cooling fan P/N G52– 00–002: Before accumulating 500 total hours TIS since new and thereafter at intervals not to exceed 100 hours TIS, inspect the cooling fan front flange for a crack in accordance with MM J70–002, Issue 06, sub section 52– A–10 Cooling Fan Inspection, paragraphs (c) through (d). If any crack is found, before further flight, remove the cooling fan front flange from service. (iv) For helicopters with tail boom P/N G65–00–101, G65–00–102 or G65–00–103 and subsequent installed: Before further flight after the effective date of this AD, paint or verify the tail boom upper surface in accordance with MM J70–002, Issue 06, sub section C–23 Tail Structure Paint, as applicable to your helicopter. jbell on DSKJLSW7X2PROD with PROPOSALS (h) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraph (g)(2)(i), (ii) and (iii) of this AD, if those actions were performed before the effective date of this AD using He´licopte`res Guimbal Cabri G2 MM and Instructions for Continued Airworthiness J70–002 Issue 05.1, Section C, Airworthiness Limitations, dated October 30, 2015, sub section 52–A–10 Cooling Fan Inspection, paragraphs (c) through (d). VerDate Sep<11>2014 16:56 Aug 20, 2021 Jkt 253001 (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (j)(1) of this AD. Information may be emailed to: 9-AVS-AIR730-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. (j) Related Information (1) For more information about this AD, contact Andrea Jimenez, Aerospace Engineer, COS Program Management Section, Operational Safety Branch, Compliance & Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228–7330; email andrea.jimenez@faa.gov. (2) For service information identified in this AD, contact He´licopte`res Guimbal, Basile Ginel, 1070, rue du Lieutenant Parayre, Ae´rodrome d’Aix-en-Provence, 13290 Les Milles, France; telephone 33–04–42–39–10– 88; email basile.ginel@guimbal.com; web https://www.guimbal.com. You may view this referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110. (3) The subject of this AD is addressed in European Aviation Safety Agency (now European Union Aviation Safety Agency (EASA) AD 2019–0025, dated February 4, 2019. You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA–2021–0688. Issued on August 16, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–17944 Filed 8–20–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0689; Project Identifier AD–2020–01589–R] RIN 2120–AA64 Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters Federal Aviation Administration (FAA), DOT. AGENCY: PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 47041 Notice of proposed rulemaking (NPRM). ACTION: The FAA proposes to adopt a new airworthiness directive (AD) for certain Sikorsky Aircraft Corporation (Sikorsky) Model S–92A helicopters. This proposed AD was prompted by a cracked main rotor stationary swashplate assembly (swashplate assembly). This proposed AD would require visually inspecting the swashplate assembly at specified intervals and depending on the results, removing the swashplate assembly from service. 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 October 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 your local Sikorsky Field Representative or Sikorsky’s Service Engineering Group at Sikorsky Aircraft Corporation, 124 Quarry Road, Trumbull, CT 06611; telephone 1–800– 946–4337 (1–800–Winged–S); email wcs_cust_service_eng.gr-sik@lmco.com. Operators may also log on to the Sikorsky 360 website at https:// www.sikorsky360.com. You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110. SUMMARY: Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0689; 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: Jared Hyman, Aerospace Engineer, E:\FR\FM\23AUP1.SGM 23AUP1

Agencies

[Federal Register Volume 86, Number 160 (Monday, August 23, 2021)]
[Proposed Rules]
[Pages 47038-47041]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-17944]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0688; Project Identifier 2019-SW-025-AD]
RIN 2120-AA64


Airworthiness Directives; H[eacute]licopt[egrave]res Guimbal 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for H[eacute]licopt[egrave]res Guimbal (HG) Model Cabri G2 helicopters. 
This proposed AD was prompted by the determination that certain parts 
need life limits and certification maintenance requirement (CMR) tasks. 
This proposed AD would require establishing life limits and CMR tasks 
for various parts and removing any parts from service that have reached 
or exceeded their life limits. Depending on the results of the CMR 
tasks, this proposed AD would require corrective action. 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 October 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 between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact 
H[eacute]licopt[egrave]res Guimbal, Basile Ginel, 1070, rue du 
Lieutenant Parayre, A[eacute]rodrome d'Aix-en-Provence, 13290 Les 
Milles, France; telephone 33-04-42-39-10-88; email 
[email protected]; web https://www.guimbal.com. You may view 
this service information at the FAA, Office of the Regional Counsel, 
Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 
76177. For information on the availability of this material at the FAA, 
call (817) 222-5110.

[[Page 47039]]

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0688; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this NPRM, the European 
Aviation Safety Agency (now European Union Aviation Safety Agency 
(EASA) AD, any comments received, and other information. The street 
address for Docket Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer, 
COS Program Management Section, Operational Safety Branch, Compliance & 
Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 
11590; telephone (516) 228-7330; email [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2021-0688; Project Identifier 
2019-SW-025-AD'' 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://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 
Andrea Jimenez, Aerospace Engineer, COS Program Management Section, 
Operational Safety Branch, Compliance & Airworthiness Division, FAA, 
1600 Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228-
7330; email [email protected]. Any commentary that the FAA 
receives which is not specifically designated as CBI will be placed in 
the public docket for this rulemaking.

Background

    EASA, which is the Technical Agent for the Member States of the 
European Union, issued EASA AD 2016-0032, dated February 24, 2016 (EASA 
AD 2016-0032), to correct an unsafe condition for HG Model Cabri G2 
helicopters. EASA AD 2016-0032 states HG has revised the airworthiness 
limitations and maintenance tasks specified in the existing maintenance 
manual. EASA further advised the revisions include new and more 
restrictive applicable life limits and compliance times for applicable 
tasks. Accordingly, EASA 2016-0032 required replacing each affected 
part before exceeding its life limit, accomplishing all applicable 
maintenance tasks within the defined intervals as described in revised 
maintenance manual and if discrepancies were found accomplishing the 
corrective actions in accordance with the applicable maintenance 
instructions or contacting HG. EASA AD 2016-0032 also required revising 
the existing Aircraft Maintenance Program (AMP) for your helicopter by 
incorporating the actions specified in the revised maintenance. After 
EASA issued EASA AD 2016-0032, HG again revised the airworthiness 
limitations and maintenance tasks.
    Accordingly, EASA superseded EASA AD 2016-0032 with EASA AD 2019-
0025, dated February 4, 2019 (EASA AD 2019-0025). EASA advises new and 
more restrictive life limits have been established for cooling fan part 
number (P/N) G52-00-001, and P/N G52-00-002, which have been identified 
as mandatory for continued airworthiness in H[eacute]licopt[egrave]res 
Guimbal Cabri G2 Maintenance Manual (MM) and Instructions for Continued 
Airworthiness J70-002 Issue 06, Section C, Airworthiness Limitations, 
dated December 6, 2018 (MM J70-002 Issue 06). In addition to the new 
life limits, EASA further advises of new and more restrictive 
inspection intervals identified in MM J70-002-Issue 06 for cooling fan 
P/N G52-00-001 with a certain mounted cooling fan front flange P/N G52-
02-200, or P/N G52-02-201. EASA further advises MM J70-002 Issue 06, 
revised the tail structure paint to include certain part-numbered tail 
booms and an additional figure. This condition, if not addressed, could 
result in parts remaining in service beyond their fatigue life and 
failure of a part, which could result in loss of control of the 
helicopter.
    Accordingly, EASA AD 2019-0025 retains the requirements of EASA AD 
2016-0032 and requires replacing each affected part before exceeding 
its life limit, accomplishing all applicable maintenance tasks within 
the defined intervals as described in MM J70-002 Issue 6, and if 
discrepancies are found accomplishing the corrective actions in 
accordance with the applicable maintenance instructions or contacting 
HG. EASA AD 2019-0025 also requires revising the tail structure paint 
scheme to include certain part-numbered tail booms and an additional 
figure. EASA AD 2019-0025 requires revising the existing AMP for your 
helicopter by incorporating the actions specified in MM J70-002 Issue 
6.

FAA's Determination

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Union, EASA has notified the FAA about the 
unsafe condition described in its AD. The FAA is proposing this AD 
after evaluating all known relevant information and determining that 
the unsafe condition described previously is likely to exist or develop 
on other helicopters of the same type designs.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed H[eacute]licopt[egrave]res Guimbal Cabri G2 MM 
J70-002 Issue 06. This service information specifies airworthiness life 
limits, inspection intervals, and CMR requirements for parts installed 
on Cabri G2 helicopters. Issue 06 establishes life limits for certain 
part-numbered cooling fan front flanges, and engine pulley ball 
bearings and CMR requirements for certain cooling fan front flanges.
    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.

[[Page 47040]]

Proposed AD Requirements in This NPRM

    This proposed AD would require, before further flight after the 
effective date of this AD, removing from service certain part-numbered 
cooling fan front flanges and engine pulley ball bearings that have 
accumulated or exceeded their life limit. This proposed AD would also 
require establishing recurring CMR tasks for certain part-numbered 
cooling fan front flanges. Depending on the results of the CMR tasks, 
this proposed AD would also require corrective action. Additionally, 
this proposed AD would require painting certain part-numbered tail 
booms with glossy white paint.

Differences Between This Proposed AD and EASA AD 2019-0025

    EASA AD 2019-0025 requires contacting H[eacute]licopt[egrave]res 
Guimbal for corrective actions when a discrepancy is found, whereas 
this proposed AD would require removing the part from service. EASA AD 
2019-0025 requires accomplishing the actions specified in MM J70-002 
Issue 06, whereas this proposed AD would require establishing a life 
limit for certain part-numbered cooling fan front flanges and certain 
part-numbered engine pulley ball bearings and removing any part from 
service accordingly instead. EASA AD 2019-0025 requires revising the 
AMP with the actions specified in MM J70-002 Issue 06, whereas the 
proposed AD would not.

Costs of Compliance

    The FAA estimates that this proposed AD would affect 32 helicopters 
of U.S. Registry. The FAA estimates that operators may incur the 
following costs in order to comply with this proposed AD. Labor costs 
are estimated at $85 per work-hour.
    Replacing a cooling fan front flange would take about 16 work-hours 
and parts would cost about $4,500 for an estimated cost of $5,860 per 
helicopter and $187,520 for the U.S. fleet, per replacement cycle.
    Replacing an engine pulley ball bearing would take about 12 work-
hours and parts would cost about $250 for an estimated cost of $1,270 
per helicopter and $40,640 for the U.S. fleet, per replacement cycle.
    The FAA has no way of determining the estimated costs to do 
allowable repairs based on the results of the CMR tasks. If required, 
replacing a cracked cooling fan front flange would take about 16 work-
hours and parts would cost about $4,500 for an estimated cost of 
$5,860.
    The FAA has included all known costs in its cost estimate. 
According to the manufacturer, however, some of the costs of this 
proposed AD may be covered under warranty, thereby reducing the cost 
impact on affected operators.

Authority for This Rulemaking

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

Regulatory Findings

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed, I certify this proposed regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

H[eacute]licopt[egrave]res Guimbal: Docket No. FAA-2021-0688; 
Project Identifier 2019-SW-025-AD.

(a) Comments Due Date

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

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to H[eacute]licopt[egrave]res Guimbal (HG) Model 
Cabri G2 helicopters, certificated in any category.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 7100, Powerplant 
System.

(e) Unsafe Condition

    This AD was prompted by a notification of certain parts 
remaining in service beyond their fatigue life or beyond maintenance 
intervals required by the certification maintenance requirements 
(CMRs) of the Instructions for Continued Airworthiness. The FAA is 
issuing this AD to prevent failure of a part, which could result in 
loss of control of the helicopter.

(f) Compliance

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

(g) Required Actions

    (1) Before further flight after the effective date of this AD, 
remove from service any part that has reached or exceeded its life 
limit, as specified in paragraphs (g)(1)(i) through (iii) of this 
AD, and thereafter remove from service any part on or before each 
part reaches its life limit:
    (i) The life limit for cooling fan front flange part number (P/
N) G52-02-200 mounted on pulley (12 screws) P/N G52-10-100 or G52-
10-101; and cooling fan front flange P/N G52-02-201 mounted or 
having been mounted on pulley (12 screws) P/N G52-10-100 or G52-10-
101, installed on cooling fan P/N G52-00-001 or G52-00-002; is 2,200 
total hours time-in-service (TIS).
    (ii) The life limit for cooling fan front flange P/N G52-02-201 
mounted on pulley (24 screws) P/N G52-10-102 and having never been 
mounted on pulley (12 screws) P/N G52-10-100 or G52-10-101, 
installed on cooling fan P/N G52-00-001 or G52-00-002, is 4,400 
total hours TIS.
    (iii) The life limit for engine pulley ball bearing P/N HG61-
0790 and HG61-1944, installed on engine pulley assembly P/N G51-14-
1XX, is 2,200 total hours TIS.
    (2) Perform the following CMR tasks as follows:
    (i) Cooling fan front flange P/N G52-02-200 mounted on pulley 
(12 screws) P/N G52-10-100 or G52-10-101; and cooling fan front

[[Page 47041]]

flange P/N G52-02-201 mounted or having been mounted on pulley (12 
screws) P/N G52-10-100 or G52-10-101, installed on cooling fan P/N 
G52-00-001, and with 500 or more total hours TIS since new as of the 
effective date of this AD: Within 5 hours TIS after the effective 
date of this AD and thereafter at intervals not to exceed 50 hours 
TIS, or 70 engine start-stop cycles, whichever occurs first, inspect 
the cooling fan front flange for a crack in accordance with 
H[eacute]licopt[egrave]res Guimbal Cabri G2 Maintenance Manual (MM) 
and Instructions for Continued Airworthiness J70-002 Issue 06, 
Section C, Airworthiness Limitations, dated December 6, 2018 (MM 
J70-002 Issue 06), sub section 52-A-10 Cooling Fan Inspection, 
paragraphs (c) through (d). If any crack is found, before further 
flight, remove the cooling fan front flange from service.
    (ii) Cooling fan front flange P/N G52-02-200 mounted on pulley 
(12 screws) P/N G52-10-100 or G52-10-101; and cooling fan front 
flange P/N G52-02-201 mounted or having been mounted on pulley (12 
screws) P/N G52-10-100 or G52-10-101, installed on cooling fan P/N 
G52-00-001, and with less than 500 total hours TIS since new as of 
the effective date of this AD: Before accumulating 500 total hours 
TIS since new and thereafter at intervals not to exceed 50 hours 
TIS, or 70 engine start-stop cycles, whichever occurs first, inspect 
the cooling fan front flange for a crack in accordance with MM J70-
002 Issue 06, sub section 52-A-10 Cooling Fan Inspection, paragraphs 
(c) through (d). If any crack is found, before further flight, 
remove the cooling fan front flange from service.
    (iii) Cooling fan front flange P/N G52-02-201 mounted on pulley 
(24 screws) P/N G52-10-102 and having never been mounted on pulley 
(12 screws) P/N G52-10-100 or G52-10-101, installed on cooling fan 
P/N G52-00-002: Before accumulating 500 total hours TIS since new 
and thereafter at intervals not to exceed 100 hours TIS, inspect the 
cooling fan front flange for a crack in accordance with MM J70-002, 
Issue 06, sub section 52-A-10 Cooling Fan Inspection, paragraphs (c) 
through (d). If any crack is found, before further flight, remove 
the cooling fan front flange from service.
    (iv) For helicopters with tail boom P/N G65-00-101, G65-00-102 
or G65-00-103 and subsequent installed: Before further flight after 
the effective date of this AD, paint or verify the tail boom upper 
surface in accordance with MM J70-002, Issue 06, sub section C-23 
Tail Structure Paint, as applicable to your helicopter.

(h) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (g)(2)(i), (ii) and (iii) of this AD, if those actions 
were performed before the effective date of this AD using 
H[eacute]licopt[egrave]res Guimbal Cabri G2 MM and Instructions for 
Continued Airworthiness J70-002 Issue 05.1, Section C, Airworthiness 
Limitations, dated October 30, 2015, sub section 52-A-10 Cooling Fan 
Inspection, paragraphs (c) through (d).

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Validation Branch, send 
it to the attention of the person identified in paragraph (j)(1) of 
this AD. Information may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(j) Related Information

    (1) For more information about this AD, contact Andrea Jimenez, 
Aerospace Engineer, COS Program Management Section, Operational 
Safety Branch, Compliance & Airworthiness Division, FAA, 1600 
Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228-
7330; email [email protected].
    (2) For service information identified in this AD, contact 
H[eacute]licopt[egrave]res Guimbal, Basile Ginel, 1070, rue du 
Lieutenant Parayre, A[eacute]rodrome d'Aix-en-Provence, 13290 Les 
Milles, France; telephone 33-04-42-39-10-88; email 
[email protected]; web https://www.guimbal.com. You may view 
this referenced service information at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. For information on the availability of 
this material at the FAA, call (817) 222-5110.
    (3) The subject of this AD is addressed in European Aviation 
Safety Agency (now European Union Aviation Safety Agency (EASA) AD 
2019-0025, dated February 4, 2019. You may view the EASA AD on the 
internet at https://www.regulations.gov in Docket No. FAA-2021-0688.

    Issued on August 16, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-17944 Filed 8-20-21; 8:45 am]
BILLING CODE 4910-13-P
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