Airworthiness Directives; Hélicoptères Guimbal Helicopters, 70000-70003 [2021-26543]

Download as PDF 70000 Federal Register / Vol. 86, No. 234 / Thursday, December 9, 2021 / Rules and Regulations into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9(a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. 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: ■ 2021–24–04 Bell Textron Canada Limited (Type Certificate Previously Held by Bell Helicopter Textron Canada Limited): Amendment 39–21825; Docket No. FAA–2021–0783; Project Identifier 2019–SW–009–AD. (a) Effective Date This airworthiness directive (AD) is effective January 13, 2022. (b) Affected ADs None. (c) Applicability This AD applies to Bell Helicopter Textron Canada Limited (type certificate previously held by Bell Helicopter Textron Canada Limited) Model 505 helicopters having serial number 65011 and subsequent, certificated in any category. (d) Subject Joint Aircraft Service Component (JASC) Code: 7300, Engine fuel and control. (e) Unsafe Condition This AD was prompted by the determination that reducing the pressure altitude limitations for certain fuel types is necessary. The FAA is issuing this AD to address unsatisfactory flight performance of the engine above pressure altitude limitations for Jet B and JP–4 fuels. The unsafe condition, if not addressed, could result in low fuel pressure, engine flame-out, or engine power interruption. khammond on DSKJM1Z7X2PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Within 30 calendar days after the effective date of this AD, revise the Limitations Section of the existing Rotorcraft Flight Manual (RFM) for your helicopter by replacing Figure 1–6. with Figure 1–6. Fuel Operating Envelope (Sheet 1 of 1) of Bell 505 Rotorcraft Flight Manual BHT–505–FM–1, Revision 3, dated July 25, 2018 (BHT–505– FM–1 Revision 3). Using a different document with information identical to that in Figure 1–6. Fuel Operating Envelope (Sheet 1 of 1) of BHT–505–FM–1 Revision 3 is acceptable for compliance with the requirements of this AD. The action required by this paragraph may be performed by the owner/operator (pilot) holding at least a private pilot certificate and must be entered VerDate Sep<11>2014 16:33 Dec 08, 2021 Jkt 256001 (h) 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 (i)(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. (i) Related Information (1) For more information about this AD, contact Rao Edupuganti, Aerospace Engineer, Dynamic Systems Section, Technical Innovation Policy Branch, Policy & Innovation Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email rao.edupuganti@ faa.gov. (2) The subject of this AD is addressed in Transport Canada AD CF–2019–08, dated March 5, 2019. You may view the Transport Canada AD at https://www.regulations.gov in Docket No. FAA–2021–0783. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Figure 1–6. Fuel Operating Envelope (Sheet 1 of 1) of Bell 505 Rotorcraft Flight Manual BHT–505–FM–1, Revision 3, dated July 25, 2018. (ii) [Reserved] (3) For service information identified in this AD, contact Bell Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J 1R4, Canada; telephone 1–450– 437–2862 or 1–800–363–8023; fax 1–450– 433–0272; email productsupport@ bellflight.com; or at https:// www.bellflight.com/support/contact-support. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: fr.inspection@nara.gov, or go to: PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on November 12, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–26605 Filed 12–8–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0688; Project Identifier 2019–SW–025–AD; Amendment 39–21781; AD 2021–22–08] RIN 2120–AA64 Airworthiness Directives; He´licopte`res Guimbal Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for He´licopte`res Guimbal (HG) Model Cabri G2 helicopters. This AD was prompted by the determination that certain parts need life limits and certification maintenance requirement (CMR) tasks. This AD requires 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 AD requires corrective action. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 13, 2022. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of January 13, 2022. ADDRESSES: For service information identified in this final rule, contact He´licopte`res Guimbal, 1070, rue du Lieutenant Parayre, Ae´rodrome d’Aixen-Provence, 13290 Les Milles, France; telephone 33–04–42–39–10–88; email support@guimbal.com; or at https:// www.guimbal.com. You may view the 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. It is also available at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0688. SUMMARY: E:\FR\FM\09DER1.SGM 09DER1 Federal Register / Vol. 86, No. 234 / Thursday, December 9, 2021 / Rules and Regulations khammond on DSKJM1Z7X2PROD with 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 final rule, 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 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: 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: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to He´licopte`res Guimbal (HG) Model Cabri G2 helicopters. The NPRM published in the Federal Register on August 23, 2021 (86 FR 47038). In the NPRM, the FAA proposed to require before further flight, removing from service certain part-numbered cooling fan front flanges and engine pulley ball bearings that have accumulated or exceeded their life limit. The NPRM also proposed to require establishing recurring CMR tasks for certain partnumbered cooling fan front flanges. Depending on the results of the CMR tasks, the NPRM proposed to require corrective action. Additionally, the NPRM proposed to require painting certain part-numbered tail booms with glossy white paint. The NPRM was prompted by a series of EASA ADs beginning with EASA AD 2016–0032, dated February 24, 2016 (EASA AD 2016–0032), issued by EASA, which is the Technical Agent for the Member States of the European Union, 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 VerDate Sep<11>2014 16:33 Dec 08, 2021 Jkt 256001 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) No. J70–002 Issue 06, dated December 6, 2018, Section C, Airworthiness Limitations (the ALS). In addition to the new life limits, EASA advises of new and more restrictive inspection intervals identified in the ALS 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 that the ALS revised the tail structure paint to include certain partnumbered 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 the ALS, 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 the ALS. PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 70001 Comments The FAA received no comments on the NPRM or on the determination of the costs. Conclusion 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 reviewed the relevant data 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 helicopters. Except for minor editorial changes, this AD is adopted as proposed in the NPRM. Changes include clarifying the name of and the specific portions of Guimbal France He´licopte`res Guimbal Cabri G2 Maintenance Manual and Instructions for Continued Airworthiness, J70–002— Issue 06, dated December 6, 2018 (MM J70–002 Issue 06) that are required to accomplish this final rule. MM J70–002 Issue 06 also refers to a flashlight as a torchlight; accordingly, changes have been made in this final rule to clarify that where MM J70–002 Issue 06 specifies to use a torchlight, to use a flashlight instead. This final rule also removes the requirements of accomplishing sub section 52–A–10 Cooling Fan Inspection, paragraph d), of MM J70–002 Issue 06 because it is unnecessary, this final rule already provides requirements pertaining to what to do if there is a crack. Related Service Information Under 1 CFR Part 51 The FAA reviewed page C–6 of Section C, Airworthiness Limitations, and page E–5–53 of Section E, Maintenance Instructions, of MM J70– 002 Issue 06. This service information specifies airworthiness life limits, inspection intervals, and CMR requirements for parts installed on Cabri G2 helicopters. MM J70–002 Issue 06 also 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. Differences Between This AD and EASA 2019–0025 EASA AD 2019–0025 requires contacting He´licopte`res Guimbal for corrective actions when a discrepancy is E:\FR\FM\09DER1.SGM 09DER1 70002 Federal Register / Vol. 86, No. 234 / Thursday, December 9, 2021 / Rules and Regulations found, whereas this AD requires removing the part from service. EASA AD 2019–0025 requires accomplishing the actions specified in the ALS, whereas this AD requires 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 the ALS, whereas this AD does not. Costs of Compliance The FAA estimates that this AD affects 32 helicopters of U.S. Registry. Labor rates are estimated at $85 per work-hour. Based on these numbers, the FAA estimates the following costs to comply with this AD. Replacing a cooling fan front flange takes about 16 work-hours and parts 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 takes about 12 work-hours and parts 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 takes about 16 work-hours and parts 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 AD may be covered under warranty, thereby reducing the cost impact on affected operators. khammond on DSKJM1Z7X2PROD with RULES 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 VerDate Sep<11>2014 16:33 Dec 08, 2021 Jkt 256001 develop on helicopters identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (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: ■ 2021–22–08 He´licopte`res Guimbal: Amendment 39–21781; Docket No. FAA–2021–0688; Project Identifier 2019–SW–025–AD. (a) Effective Date This airworthiness directive (AD) is effective January 13, 2022. (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 PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 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 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 Section E, Maintenance Instructions, sub section 52– A–10 Cooling Fan Inspection, paragraph c), on page E–5–53, of Guimbal France He´licopte`res Guimbal Cabri G2 Maintenance Manual (MM) and Instructions for Continued Airworthiness, J70–002—Issue 06, dated December 6, 2018 (MM J70–002 Issue 06), except where MM J70–002 Issue 06 specifies to use a torchlight, use a flashlight. 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 E:\FR\FM\09DER1.SGM 09DER1 Federal Register / Vol. 86, No. 234 / Thursday, December 9, 2021 / Rules and Regulations 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 Section E, Maintenance Instructions, sub section 52–A–10 Cooling Fan Inspection, paragraph c), on page E–5–53, of MM J70– 002 Issue 06, except where MM J70–002 Issue 06 specifies to use a torchlight, use a flashlight. 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 Section E, Maintenance Instructions, sub section 52–A–10 Cooling Fan Inspection, paragraph c), on page E–5–53, of MM J70– 002 Issue 06, except where MM J70–002 Issue 06 specifies to use a torchlight, use a flashlight. 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 Section C, Airworthiness Limitations, sub section C–23 Tail Structure Paint, on page C–6, of MM J70–002 Issue 06, as applicable to your helicopter. khammond on DSKJM1Z7X2PROD with RULES (h) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraphs (g)(2)(i) through (iii) of this AD, if those actions were performed before the effective date of this AD using Section E, Maintenance Instructions, sub section 52–A–10 Cooling Fan Inspection, paragraphs (c) and (d), of Guimbal France He´licopte`res Guimbal Cabri G2 MM and Instructions for Continued Airworthiness, J70–002 Issue—05.1, dated October 30, 2015. (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. 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) Service information identified in this AD that is not incorporated by reference is available at the contact information specified in paragraphs (k)(3) and (4) of this AD. (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. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Page C–6 of Section C, Airworthiness Limitations, of Guimbal France He´licopte`res Guimbal Cabri G2 Maintenance Manual and Instructions for Continued Airworthiness, J70–002—Issue 06, dated December 6, 2018. (ii) Page E–5–53 of Section E, Maintenance Instructions, of Guimbal France He´licopte`res Guimbal Cabri G2 Maintenance Manual and Instructions for Continued Airworthiness, J70–002—Issue 06, dated December 6, 2018. (3) For service information identified in this AD, contact He´licopte`res Guimbal, 1070, rue du Lieutenant Parayre, Ae´rodrome d’Aixen-Provence, 13290 Les Milles, France; telephone 33–04–42–39–10–88; email support@guimbal.com; or at https:// www.guimbal.com. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: fr.inspection@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on October 14, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–26543 Filed 12–8–21; 8:45 am] BILLING CODE 4910–13–P (j) Related Information (1) For more information about this AD, contact Andrea Jimenez, Aerospace Engineer, VerDate Sep<11>2014 16:33 Dec 08, 2021 Jkt 256001 PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 70003 DEPARTMENT OF COMMERCE Bureau of Industry and Security 15 CFR Part 705 [Docket No. 211115–0229] RIN 0694–AH55 Removal of Certain General Approved Exclusions (GAEs) Under the Section 232 Steel and Aluminum Tariff Exclusions Process Bureau of Industry and Security, U.S. Department of Commerce. AGENCY: ACTION: Interim final rule. On December 14, 2020, the Department of Commerce published an interim final rule (the ‘‘December 14 rule’’) that revised aspects of the process for requesting exclusions from the duties and quantitative limitations on imports of aluminum and steel discussed in three previous Department of Commerce (‘‘Commerce’’) interim final rules implementing the exclusion process authorized by the President under Section 232 of the Trade Expansion Act of 1962, as amended, as well as a May 26, 2020 notice of inquiry. The December 14 rule included adding 123 General Approved Exclusions (GAEs) to the regulations. Subsequently, based on Commerce’s review of the public comments received in response to the December 14 rule and additional analysis conducted by Commerce on the Section 232 exclusion request submissions, Commerce determined that a subset of the GAEs added in the December 14 rule no longer meets the criteria for inclusion as a GAE and should therefore be removed. Commerce is removing these GAEs in this interim final rule to ensure only those GAEs that meet the stated criteria from the December 14 rule will continue to be included as eligible GAEs. This interim final rule removes thirty of the GAEs that were added to the regulations in the December 14 rule, consisting of twentysix GAEs for steel and four GAEs for aluminum. As a conforming change to a recent U.S. International Trade Commission (ITC) decision, this rule also removes one additional steel GAE. Lastly, this interim final rule adds a note to both GAE supplements to address future changes to the Harmonized Tariff Schedule of the United States (HTSUS). SUMMARY: E:\FR\FM\09DER1.SGM 09DER1

Agencies

[Federal Register Volume 86, Number 234 (Thursday, December 9, 2021)]
[Rules and Regulations]
[Pages 70000-70003]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-26543]


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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; Amendment 
39-21781; AD 2021-22-08]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
H[eacute]licopt[egrave]res Guimbal (HG) Model Cabri G2 helicopters. 
This AD was prompted by the determination that certain parts need life 
limits and certification maintenance requirement (CMR) tasks. This AD 
requires 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 AD 
requires corrective action. The FAA is issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective January 13, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of January 13, 
2022.

ADDRESSES: For service information identified in this final rule, 
contact H[eacute]licopt[egrave]res Guimbal, 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]; or at https://www.guimbal.com. You may view the 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. It is 
also available at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2021-0688.

[[Page 70001]]

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 final rule, 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 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: 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:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to 
H[eacute]licopt[egrave]res Guimbal (HG) Model Cabri G2 helicopters. The 
NPRM published in the Federal Register on August 23, 2021 (86 FR 
47038). In the NPRM, the FAA proposed to require before further flight, 
removing from service certain part-numbered cooling fan front flanges 
and engine pulley ball bearings that have accumulated or exceeded their 
life limit. The NPRM also proposed to require establishing recurring 
CMR tasks for certain part-numbered cooling fan front flanges. 
Depending on the results of the CMR tasks, the NPRM proposed to require 
corrective action. Additionally, the NPRM proposed to require painting 
certain part-numbered tail booms with glossy white paint.
    The NPRM was prompted by a series of EASA ADs beginning with EASA 
AD 2016-0032, dated February 24, 2016 (EASA AD 2016-0032), issued by 
EASA, which is the Technical Agent for the Member States of the 
European Union, 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) No. J70-002 Issue 06, dated 
December 6, 2018, Section C, Airworthiness Limitations (the ALS). In 
addition to the new life limits, EASA advises of new and more 
restrictive inspection intervals identified in the ALS 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 that the ALS 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 the ALS, 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 the ALS.

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs.

Conclusion

    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 reviewed the relevant 
data 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 helicopters. Except for minor editorial changes, 
this AD is adopted as proposed in the NPRM. Changes include clarifying 
the name of and the specific portions of Guimbal France 
H[eacute]licopt[egrave]res Guimbal Cabri G2 Maintenance Manual and 
Instructions for Continued Airworthiness, J70-002--Issue 06, dated 
December 6, 2018 (MM J70-002 Issue 06) that are required to accomplish 
this final rule. MM J70-002 Issue 06 also refers to a flashlight as a 
torchlight; accordingly, changes have been made in this final rule to 
clarify that where MM J70-002 Issue 06 specifies to use a torchlight, 
to use a flashlight instead. This final rule also removes the 
requirements of accomplishing sub section 52-A-10 Cooling Fan 
Inspection, paragraph d), of MM J70-002 Issue 06 because it is 
unnecessary, this final rule already provides requirements pertaining 
to what to do if there is a crack.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed page C-6 of Section C, Airworthiness Limitations, 
and page E-5-53 of Section E, Maintenance Instructions, of MM J70-002 
Issue 06. This service information specifies airworthiness life limits, 
inspection intervals, and CMR requirements for parts installed on Cabri 
G2 helicopters. MM J70-002 Issue 06 also 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.

Differences Between This AD and EASA 2019-0025

    EASA AD 2019-0025 requires contacting H[eacute]licopt[egrave]res 
Guimbal for corrective actions when a discrepancy is

[[Page 70002]]

found, whereas this AD requires removing the part from service. EASA AD 
2019-0025 requires accomplishing the actions specified in the ALS, 
whereas this AD requires 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 the ALS, whereas this AD does not.

Costs of Compliance

    The FAA estimates that this AD affects 32 helicopters of U.S. 
Registry. Labor rates are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates the following costs to comply with 
this AD.
    Replacing a cooling fan front flange takes about 16 work-hours and 
parts 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 takes about 12 work-hours 
and parts 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 takes about 16 work-hours 
and parts 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 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 helicopters identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (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:

2021-22-08 H[eacute]licopt[egrave]res Guimbal: Amendment 39-21781; 
Docket No. FAA-2021-0688; Project Identifier 2019-SW-025-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective January 13, 2022.

(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 
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 Section 
E, Maintenance Instructions, sub section 52-A-10 Cooling Fan 
Inspection, paragraph c), on page E-5-53, of Guimbal France 
H[eacute]licopt[egrave]res Guimbal Cabri G2 Maintenance Manual (MM) 
and Instructions for Continued Airworthiness, J70-002--Issue 06, 
dated December 6, 2018 (MM J70-002 Issue 06), except where MM J70-
002 Issue 06 specifies to use a torchlight, use a flashlight. 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

[[Page 70003]]

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 Section E, Maintenance Instructions, 
sub section 52-A-10 Cooling Fan Inspection, paragraph c), on page E-
5-53, of MM J70-002 Issue 06, except where MM J70-002 Issue 06 
specifies to use a torchlight, use a flashlight. 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 Section E, 
Maintenance Instructions, sub section 52-A-10 Cooling Fan 
Inspection, paragraph c), on page E-5-53, of MM J70-002 Issue 06, 
except where MM J70-002 Issue 06 specifies to use a torchlight, use 
a flashlight. 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 Section C, Airworthiness Limitations, sub 
section C-23 Tail Structure Paint, on page C-6, of MM J70-002 Issue 
06, as applicable to your helicopter.

(h) Credit for Previous Actions

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

(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) Service information identified in this AD that is not 
incorporated by reference is available at the contact information 
specified in paragraphs (k)(3) and (4) of this AD.
    (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.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Page C-6 of Section C, Airworthiness Limitations, of Guimbal 
France H[eacute]licopt[egrave]res Guimbal Cabri G2 Maintenance 
Manual and Instructions for Continued Airworthiness, J70-002--Issue 
06, dated December 6, 2018.
    (ii) Page E-5-53 of Section E, Maintenance Instructions, of 
Guimbal France H[eacute]licopt[egrave]res Guimbal Cabri G2 
Maintenance Manual and Instructions for Continued Airworthiness, 
J70-002--Issue 06, dated December 6, 2018.
    (3) For service information identified in this AD, contact 
H[eacute]licopt[egrave]res Guimbal, 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]; or at 
https://www.guimbal.com.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on October 14, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-26543 Filed 12-8-21; 8:45 am]
BILLING CODE 4910-13-P