Airworthiness Directives; Bell Textron Canada Limited (Type Certificate Previously Held by Bell Helicopter Textron Canada Limited) Helicopters, 16097-16100 [2022-05664]

Download as PDF Federal Register / Vol. 87, No. 55 / Tuesday, March 22, 2022 / Rules and Regulations (c) Applicability This AD applies to all Airbus SAS airplanes, certificated in any category, identified in paragraphs (c)(1) through (4) of this AD. (1) Model A318–111 and –112 airplanes. (2) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes. (4) Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/furnishings. (e) Reason This AD was prompted by reports of damaged lower lateral fittings of the 80VU rack, and reports of new damage on airplanes on which certain optional service information had been accomplished. The FAA is issuing this AD to address damage or cracking of the 80VU fittings and supports, which could lead to possible disconnection of the cable harnesses to one or more computers, and if occurring during a critical phase of flight, could result in reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2021–0172, dated July 20, 2021 (EASA AD 2021–0172). lotter on DSK11XQN23PROD with RULES1 (h) Exceptions to EASA AD 2021–0172 (1) Where EASA AD 2021–0172 refers to its effective date, this AD requires using the effective date of this AD. (2) The remarks section of EASA AD 2021– 0172 does not apply to this AD. (3) Where paragraph (3) of EASA AD 2021– 0172 specifies ‘‘any discrepancy,’’ for this AD ‘‘any discrepancy’’ includes broken fittings, missing bolts, an electronics rack FIN 80VU that is in contact with structure, any bush that has migrated, burred material, and cracks. (i) Method of Compliance for Paragraphs (1), (2), and (3) of EASA AD 2021–0172 Accomplishing inspections and correctives actions in accordance with the Accomplishment Instruction of Airbus Service Bulletin A320–25–1BKJ, Revision 02, dated April 9, 2020, with corrections referenced in the Airbus Technical Adaptation 80827186/024/2020, Issue 1, dated September 18, 2020, is an acceptable method of compliance for the inspections and corrective actions specified in paragraphs (1), (2), and (3) of EASA AD 2021–0172. (j) Additional AD Provisions The following provisions also apply to this AD: VerDate Sep<11>2014 16:08 Mar 21, 2022 Jkt 256001 16097 (1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (j)(2) of this AD, if any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. 000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https:// ad.easa.europa.eu. For Airbus service information identified in this AD, contact Airbus SAS, Airworthiness Office—EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; internet https://www.airbus.com. (4) You may view this material 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. (5) You may view this material 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/ibrlocations.html. (k) Related Information For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223; email sanjay.ralhan@ faa.gov. Airworthiness Directives; Bell Textron Canada Limited (Type Certificate Previously Held by Bell Helicopter Textron Canada Limited) Helicopters (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A320–25–1BKJ, Revision 02, dated April 9, 2020. (ii) Airbus Technical Adaptation 80827186/024/2020, Issue 1, dated September 18, 2020. (iii) European Union Aviation Safety Agency (EASA) AD 2021–0172, dated July 20, 2021. (3) For EASA AD 2021–0172, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 Issued on March 8, 2022. Ross Landes, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–05617 Filed 3–21–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–1178; Project Identifier MCAI–2021–00986–R; Amendment 39–21986; AD 2022–06–20] RIN 2120–AA64 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2020–20– 06, which applied to certain Bell Helicopter Textron Canada Limited (now Bell Textron Canada Limited) Model 429 helicopters. AD 2020–20–06 required repetitive inspections of certain cyclic and collective assembly bearings. This AD was prompted by new bellcrank assemblies, which have been upgraded with corrosion resistant steel bearings. This AD retains certain requirements of AD 2020–20–06, and depending on the inspection results, requires removing certain parts from service and installing the upgraded cyclic and collective bellcrank SUMMARY: E:\FR\FM\22MRR1.SGM 22MRR1 16098 Federal Register / Vol. 87, No. 55 / Tuesday, March 22, 2022 / Rules and Regulations assemblies. This AD also requires installing the upgraded collective and cyclic bellcrank assemblies on certain helicopters if not already installed, and prohibits installing certain bellcrank assemblies. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 26, 2022. ADDRESSES: For service information identified in this final rule, 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. 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. lotter on DSK11XQN23PROD with RULES1 Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–1178; 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 Transport Canada AD, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: 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 to supersede AD 2020–20–06, Amendment 39–21262 (85 FR 60356, September 25, 2020) (AD 2020–20–06). AD 2020–20–06 applied to Bell Helicopter Textron Canada Limited Model 429 helicopters with a bellcrank assembly part number (P/N) 429–001– 523–101, 429–001–523–103, 429–001– 532–101, or 429–001–532–103 installed. The NPRM published in the Federal Register on January 14, 2022 (87 FR 2362). In the NPRM, the FAA proposed VerDate Sep<11>2014 16:08 Mar 21, 2022 Jkt 256001 to retain some of the requirements of AD 2020–20–06, and proposed to require, for certain serial-numbered helicopters, within 12 months after the helicopter was manufactured or 30 days, whichever occurs later, and thereafter at intervals not to exceed 6 months, disconnecting certain parts, stowing certain parts to prevent binding, and moving the cyclic stick and the collective stick to inspect for roughness in the flight control system and binding in the collective, lateral, and longitudinal arm assemblies. If any of these conditions exist, the NPRM proposed to require, before further flight, removing certain parts from service and installing upgraded bellcrank assemblies. Additionally, the NPRM proposed to require, for certain serial-numbered helicopters that do not have the upgraded bellcrank assemblies installed, within 24 months, installing the upgraded bellcrank assemblies, which would provide a terminating action for the recurring inspections. Finally, the NPRM proposed to prohibit installing any affected bellcrank assembly on any helicopter. The NPRM was prompted by Transport Canada AD CF–2016–11R3, dated August 30, 2021 (Transport Canada AD CF–2016–11R3), issued by Transport Canada, which is the aviation authority for Canada, to correct an unsafe condition for Bell Textron Canada Limited Model 429 helicopters, all serial numbers. Transport Canada advises of new collective and cyclic bellcrank assemblies which have been upgraded with corrosion resistant steel bearings. This condition, if not addressed, could result in restrictions in the collective, directional, or pitch control systems, and subsequent loss of helicopter control. Accordingly, Transport Canada AD CF–2016–11R3 requires for certain serial-numbered helicopters, within 12 months from the helicopter manufacture date, or for helicopters that have exceeded the age threshold of 12 months from the helicopter manufacturer date, within 30 days, and thereafter at intervals not to exceed 6 months, performing a functional check of the flight controls to detect roughness in the pivot bearings and binding of the collective, lateral, or longitudinal arm end bearings of the bellcrank assemblies. If any roughness or binding is detected, Transport Canada AD CF– 2016–11R3 requires replacement of each affected bellcrank assembly before further flight. Transport Canada AD CF– 2016–11R3 also requires, within 24 months, installing the upgraded collective and cyclic bellcrank PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 assemblies and considers this action a terminating action to the recurring inspections. Finally, Transport Canada AD CF–2016–11R3 prohibits an affected bellcrank assembly from being installed on any helicopter. Discussion of Final Airworthiness Directive Comments The FAA received no comments on the NPRM or on the determination of the costs. Conclusion These helicopters have been approved by the aviation authority of Canada and are approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with Canada, Transport Canada, its technical representative, has notified the FAA of 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. This AD is adopted as proposed in the NPRM. Related Service Information The FAA reviewed Bell Technical Bulletin 429–18–58, Revision B, dated August 23, 2021 (TB 429–18–58 Rev B), which specifies procedures to upgrade certain part-numbered bellcrank assemblies to the bellcrank assemblies that utilize the corrosion resistant steel bearings. The FAA also reviewed Bell Helicopter Alert Service Bulletin 429– 15–21, Revision C, dated August 23, 2021 (ASB 429–15–21 Rev C), which specifies moving the cyclic stick fore, aft, and laterally, and the collective stick up and down from stop to stop to detect deteriorated pivot bearings. ASB 429– 15–21 Rev C also specifies inspecting to determine whether the bearings in the collective, lateral, and longitudinal arm assemblies rotate freely. If discrepant arm bearings are found, ASB 429–15–21 Rev C specifies contacting Bell Product Support Engineering to report the findings and replacing the discrepant parts with serviceable parts. Differences Between This AD and Transport Canada AD CF–2016–11R3 Transport Canada AD CF–2016–11R3 provides requirements if the most recent functional check was performed using a hydraulic test stand as an alternate procedure. This AD provides no such alternate procedure. Transport Canada AD CF–2016–11R3 provides requirements for helicopters that have exceeded the age threshold of 12 months from the helicopter E:\FR\FM\22MRR1.SGM 22MRR1 Federal Register / Vol. 87, No. 55 / Tuesday, March 22, 2022 / Rules and Regulations manufacturer date to complete the initial functional check within 30 days from the effective date of its AD. This AD requires the initial inspection within 12 months after the helicopter was manufactured or 30 days after the effective date of this AD, whichever occurs later. Transport Canada AD CF– 2016–11R3 allows credit for the corrective actions of Part I if the initial functional check was accomplished prior to the effective date of Transport Canada AD CF–2016–11R3, whereas this AD does not. lotter on DSK11XQN23PROD with RULES1 Costs of Compliance The FAA estimates that this AD affects 64 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. Inspecting the cyclic and the collective bellcrank assemblies for roughness in the pivot bearings and binding in the collective, lateral, and longitudinal arm end bearings takes about 3 work-hours for an estimated cost of $255 per inspection cycle. Installing the upgraded collective and cyclic bellcrank assemblies takes about 18 work-hours and parts cost about $1,750 for an estimated cost of $3,280 per upgrade installation. 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 products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order VerDate Sep<11>2014 16:08 Mar 21, 2022 Jkt 256001 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: a. Removing Airworthiness Directive 2020–20–06, Amendment 39–21262 (85 FR 60356, September 25, 2020); and ■ b. Adding the following new airworthiness directive: ■ ■ AD 2022–06–20 Bell Textron Canada Limited (Type Certificate Previously Held by Bell Helicopter Textron Canada Limited): Amendment 39–21986; Docket No. FAA–2021–1178; Project Identifier MCAI–2021–00986–R. (a) Effective Date This airworthiness directive (AD) is effective April 26, 2022. (b) Affected ADs This AD replaces AD 2020–20–06, Amendment 39–21262 (85 FR 60356, September 25, 2020) (AD 2020–20–06). (c) Applicability This AD applies to Bell Textron Canada Limited (type certificate previously held by Bell Helicopter Textron Canada Limited) Model 429 helicopters, certificated in any category, with a bellcrank assembly part number (P/N) 429–001–523–101, 429–001– 523–103, 429–001–532–101, or 429–001– 532–103 installed. (d) Subject Joint Aircraft Service Component (JASC) Code: 2700, Flight Control System. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 16099 (e) Unsafe Condition This AD was prompted by new bellcrank assemblies, which have been upgraded with corrosion resistant steel bearings. The FAA is issuing this AD to prevent corrosion of the bearings due to pooling at the bellcrank assembly from precipitation in the forward portion of the roof structure. The unsafe condition, if not addressed, could result in restrictions in the collective, directional, or pitch control systems, and subsequent loss of helicopter control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For Model 429 helicopters serial number (S/N) 57001 through 57296 inclusive, within 12 months after the helicopter was manufactured or 30 days after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 6 months: (i) Disconnect the forward ends of the collective control tube, longitudinal stability and control augmentation system (SCAS) actuator, and lateral SCAS actuator. Stow the collective control tube and each SCAS actuator to prevent binding. (ii) Move the cyclic stick fore, aft, and laterally, and the collective stick up and down from stop to stop to determine if there is any roughness. If there is any roughness in the flight control system, before further flight, remove each pivot bearing P/N MS27646–41, each arm assembly bearing P/N MS27643–4, and each sleeve P/N 120–13–4A from service and install bellcrank assemblies P/N 429– 001–523–101FM and 429–001–532–101FM; or 429–001–523–107FM and 429–001–532– 107FM; or 429–001–523–107 and 429–001– 532–107. (iii) Inspect the collective arm assembly P/ N 429–001–525–101, the lateral arm assembly P/N 429–001–527–101, and the longitudinal arm assembly P/N 429–001– 530–101, by rotating each bearing and determining whether each bearing rotates freely. If there is any binding in any arm end bearing or on the longitudinal bellcrank assembly, before further flight, remove each pivot bearing P/N MS27646–41, each arm assembly bearing P/N MS27643–4, and each sleeve P/N 120–13–4A from service and install bellcrank assemblies P/N 429–001– 523–101FM and 429–001–532–101FM; or 429–001–523–107FM and 429–001–532– 107FM; or 429–001–523–107 and 429–001– 532–107. (2) For Model 429 helicopters S/N 57001 through 57296 inclusive, unless already accomplished by following paragraphs (g)(1)(ii) or (iii) of this AD, within 24 months after the effective date of this AD, install bellcrank assemblies P/N 429–001–523– 101FM and 429–001–532–101FM; or 429– 001–523–107FM and 429–001–532–107FM; or 429–001–523–107 and 429–001–532–107. (3) As of the effective date of this AD, installing bellcrank assemblies P/N 429–001– 523–101FM and 429–001–532–101FM; or 429–001–523–107FM and 429–001–532– 107FM; or 429–001–523–107 and 429–001– E:\FR\FM\22MRR1.SGM 22MRR1 16100 Federal Register / Vol. 87, No. 55 / Tuesday, March 22, 2022 / Rules and Regulations 532–107, constitutes a terminating action for the recurring inspections required by paragraph (g)(1) of this AD. (4) As of the effective date of this AD, do not install any bellcrank assembly P/N 429– 001–523–101, 429–001–523–103, 429–001– 532–101, or 429–001–532–103 on any helicopter. DEPARTMENT OF TRANSPORTATION (h) Special Flight Permits RIN 2120–AA66 Special flight permits are prohibited. (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 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. 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 Transport Canada AD CF–2016–11R3, dated August 30, 2021. You may view the Transport Canada AD on the internet at https://www.regulations.gov in Docket No. FAA–2021–1178. (k) Material Incorporated by Reference lotter on DSK11XQN23PROD with RULES1 None. Issued on March 10, 2022. Ross Landes, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–05664 Filed 3–21–22; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:08 Mar 21, 2022 Jkt 256001 Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2021–0816; Airspace Docket No. 21–ANM–27] Modification of Class D and Class E Airspace, and Establishment of Class E Airspace; Southwest Oregon Regional Airport, OR; Correction Federal Aviation Administration (FAA), DOT. ACTION: Final rule; correction. AGENCY: The FAA is correcting a final rule that appeared in the Federal Register on March 3, 2022. The rule modified the Class D and Class E surface airspace, established Class E airspace designated as an extension to Class D & E surface areas, Class E airspace beginning at 700 feet above the surface, removed navigational aids (NAVAIDs) from text headers, and made administrative changes to the legal descriptions at Southwest Oregon Regional Airport, North Bend, OR. The Final Rule did not explain the purposeful removal of Class E airspace beginning at 1,200 feet above the surface, nor did it properly exclude the Sunnyhill Airport cut-out. This action adds verbiage explaining the removal of Class E airspace beginning at 1,200 feet above the surface, and corrects the legal description for the newly established Class E airspace designated as an extension to Class D & E surface areas to properly exclude Sunnyhill Airport, OR. DATES: Effective 0901 UTC, May 19, 2022. The Director of the Federal Register approves this incorporation by reference action under 1 CFR part 51, subject to the annual revision of FAA Order 7400.11 and publication of conforming amendments. FOR FURTHER INFORMATION CONTACT: Nathan A. Chaffman, Federal Aviation Administration, Western Service Center, Operations Support Group, 2200 S 216th Street, Des Moines, WA 98198; telephone (206) 231–3460. SUPPLEMENTARY INFORMATION: SUMMARY: History The FAA published a final rule in the Federal Register (87 FR 11955; March 3, 2022) for Docket FAA–2021–0816, which modified the Class D and Class E surface airspace, established Class E airspace designated as an extension to Class D & E surface areas, modified the Class E airspace beginning at 700 feet PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 above the surface, removed navigational aids (NAVAIDs) from text headers, and made administrative changes to the legal descriptions at Southwest Oregon Regional Airport, North Bend, OR. Subsequent to publication, the FAA identified that the removal of Class E airspace beginning at 1,200 feet above the surface at the airport was not disclosed. This airspace was removed as it is not needed at Southwest Oregon Regional Airport. The Bend E6 en route domestic airspace area beginning at 1,200 feet above the surface provides sufficient containment to accommodate arriving instrument flight rules (IFR) operations at 1,500 feet and higher above the surface and departing IFR operations from the point they reach 1,200 feet above the surface. Additionally, it was discovered after publication of the Final Rule that the legal description for the Class E airspace designated as an extension to Class D & E surface areas did not properly exclude the Sunnyhill Airport, OR cut-out. This action corrects those errors. Class D, Class E2, Class E4, and Class E5 airspace designations are published in paragraphs 5000, 6002, 6004, and 6005, respectively, of FAA Order JO 7400.11F, dated August 10, 2021, and effective September 15, 2021, which is incorporated by reference in 14 CFR 71.1. The Class D and Class E airspace designations listed in this document will be published subsequently in FAA Order JO 7400.11. Correction to Final Rule Accordingly, pursuant to the authority delegated to me, Amendment of Class D and Class E airspace, and Establishment of Class E airspace; Southwest Oregon Regional Airport, North Bend, OR, published in the Federal Register of March 3, 2022 (87 FR 11955), FR Doc. 2022–04326, is corrected as follows: § 71.1 [Corrected] 1. On page 11957, in the first column, beginning on line 8, the legal description for ANM OR E4 is corrected to read: ■ ANM OR E4 North Bend, OR [New] Southwest Oregon Regional Airport, OR (Lat. 43°25′01″ N, long. 124°14′49″ W) Sunnyhill Airport, OR (Lat. 43°28′59″ N, long. 124°12′10″ W) That airspace extending upward from the surface within 3.6 miles north and 3.5 miles south of the 092° bearing from the airport, extending from the Southwest Oregon Regional Airport Class D 4.2-mile radius to 11.7 miles east of the airport, excluding that airspace within a 0.9-mile radius of Sunnyhill Airport, and within 2.0 miles southeast and 2.1 miles northwest of the 242° E:\FR\FM\22MRR1.SGM 22MRR1

Agencies

[Federal Register Volume 87, Number 55 (Tuesday, March 22, 2022)]
[Rules and Regulations]
[Pages 16097-16100]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-05664]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-1178; Project Identifier MCAI-2021-00986-R; 
Amendment 39-21986; AD 2022-06-20]
RIN 2120-AA64


Airworthiness Directives; Bell Textron Canada Limited (Type 
Certificate Previously Held by Bell Helicopter Textron Canada Limited) 
Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2020-20-
06, which applied to certain Bell Helicopter Textron Canada Limited 
(now Bell Textron Canada Limited) Model 429 helicopters. AD 2020-20-06 
required repetitive inspections of certain cyclic and collective 
assembly bearings. This AD was prompted by new bellcrank assemblies, 
which have been upgraded with corrosion resistant steel bearings. This 
AD retains certain requirements of AD 2020-20-06, and depending on the 
inspection results, requires removing certain parts from service and 
installing the upgraded cyclic and collective bellcrank

[[Page 16098]]

assemblies. This AD also requires installing the upgraded collective 
and cyclic bellcrank assemblies on certain helicopters if not already 
installed, and prohibits installing certain bellcrank assemblies. The 
FAA is issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective April 26, 2022.

ADDRESSES: For service information identified in this final rule, 
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 [email protected]; or at https://www.bellflight.com/support/contact-support. 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.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-1178; 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 
Transport Canada AD, any comments received, and other information. The 
address for Docket Operations is U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: 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 to supersede AD 2020-20-06, Amendment 39-21262 (85 FR 
60356, September 25, 2020) (AD 2020-20-06). AD 2020-20-06 applied to 
Bell Helicopter Textron Canada Limited Model 429 helicopters with a 
bellcrank assembly part number (P/N) 429-001-523-101, 429-001-523-103, 
429-001-532-101, or 429-001-532-103 installed. The NPRM published in 
the Federal Register on January 14, 2022 (87 FR 2362). In the NPRM, the 
FAA proposed to retain some of the requirements of AD 2020-20-06, and 
proposed to require, for certain serial-numbered helicopters, within 12 
months after the helicopter was manufactured or 30 days, whichever 
occurs later, and thereafter at intervals not to exceed 6 months, 
disconnecting certain parts, stowing certain parts to prevent binding, 
and moving the cyclic stick and the collective stick to inspect for 
roughness in the flight control system and binding in the collective, 
lateral, and longitudinal arm assemblies. If any of these conditions 
exist, the NPRM proposed to require, before further flight, removing 
certain parts from service and installing upgraded bellcrank 
assemblies.
    Additionally, the NPRM proposed to require, for certain serial-
numbered helicopters that do not have the upgraded bellcrank assemblies 
installed, within 24 months, installing the upgraded bellcrank 
assemblies, which would provide a terminating action for the recurring 
inspections. Finally, the NPRM proposed to prohibit installing any 
affected bellcrank assembly on any helicopter.
    The NPRM was prompted by Transport Canada AD CF-2016-11R3, dated 
August 30, 2021 (Transport Canada AD CF-2016-11R3), issued by Transport 
Canada, which is the aviation authority for Canada, to correct an 
unsafe condition for Bell Textron Canada Limited Model 429 helicopters, 
all serial numbers. Transport Canada advises of new collective and 
cyclic bellcrank assemblies which have been upgraded with corrosion 
resistant steel bearings. This condition, if not addressed, could 
result in restrictions in the collective, directional, or pitch control 
systems, and subsequent loss of helicopter control.
    Accordingly, Transport Canada AD CF-2016-11R3 requires for certain 
serial-numbered helicopters, within 12 months from the helicopter 
manufacture date, or for helicopters that have exceeded the age 
threshold of 12 months from the helicopter manufacturer date, within 30 
days, and thereafter at intervals not to exceed 6 months, performing a 
functional check of the flight controls to detect roughness in the 
pivot bearings and binding of the collective, lateral, or longitudinal 
arm end bearings of the bellcrank assemblies. If any roughness or 
binding is detected, Transport Canada AD CF-2016-11R3 requires 
replacement of each affected bellcrank assembly before further flight. 
Transport Canada AD CF-2016-11R3 also requires, within 24 months, 
installing the upgraded collective and cyclic bellcrank assemblies and 
considers this action a terminating action to the recurring 
inspections. Finally, Transport Canada AD CF-2016-11R3 prohibits an 
affected bellcrank assembly from being installed on any helicopter.

Discussion of Final Airworthiness Directive

Comments

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

Conclusion

    These helicopters have been approved by the aviation authority of 
Canada and are approved for operation in the United States. Pursuant to 
the FAA's bilateral agreement with Canada, Transport Canada, its 
technical representative, has notified the FAA of 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. This AD is adopted as proposed in the NPRM.

Related Service Information

    The FAA reviewed Bell Technical Bulletin 429-18-58, Revision B, 
dated August 23, 2021 (TB 429-18-58 Rev B), which specifies procedures 
to upgrade certain part-numbered bellcrank assemblies to the bellcrank 
assemblies that utilize the corrosion resistant steel bearings.
    The FAA also reviewed Bell Helicopter Alert Service Bulletin 429-
15-21, Revision C, dated August 23, 2021 (ASB 429-15-21 Rev C), which 
specifies moving the cyclic stick fore, aft, and laterally, and the 
collective stick up and down from stop to stop to detect deteriorated 
pivot bearings. ASB 429-15-21 Rev C also specifies inspecting to 
determine whether the bearings in the collective, lateral, and 
longitudinal arm assemblies rotate freely. If discrepant arm bearings 
are found, ASB 429-15-21 Rev C specifies contacting Bell Product 
Support Engineering to report the findings and replacing the discrepant 
parts with serviceable parts.

Differences Between This AD and Transport Canada AD CF-2016-11R3

    Transport Canada AD CF-2016-11R3 provides requirements if the most 
recent functional check was performed using a hydraulic test stand as 
an alternate procedure. This AD provides no such alternate procedure. 
Transport Canada AD CF-2016-11R3 provides requirements for helicopters 
that have exceeded the age threshold of 12 months from the helicopter

[[Page 16099]]

manufacturer date to complete the initial functional check within 30 
days from the effective date of its AD. This AD requires the initial 
inspection within 12 months after the helicopter was manufactured or 30 
days after the effective date of this AD, whichever occurs later. 
Transport Canada AD CF-2016-11R3 allows credit for the corrective 
actions of Part I if the initial functional check was accomplished 
prior to the effective date of Transport Canada AD CF-2016-11R3, 
whereas this AD does not.

Costs of Compliance

    The FAA estimates that this AD affects 64 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.
    Inspecting the cyclic and the collective bellcrank assemblies for 
roughness in the pivot bearings and binding in the collective, lateral, 
and longitudinal arm end bearings takes about 3 work-hours for an 
estimated cost of $255 per inspection cycle.
    Installing the upgraded collective and cyclic bellcrank assemblies 
takes about 18 work-hours and parts cost about $1,750 for an estimated 
cost of $3,280 per upgrade installation.
    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 products identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and 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:
0
a. Removing Airworthiness Directive 2020-20-06, Amendment 39-21262 (85 
FR 60356, September 25, 2020); and
0
b. Adding the following new airworthiness directive:

AD 2022-06-20 Bell Textron Canada Limited (Type Certificate 
Previously Held by Bell Helicopter Textron Canada Limited): 
Amendment 39-21986; Docket No. FAA-2021-1178; Project Identifier 
MCAI-2021-00986-R.

(a) Effective Date

    This airworthiness directive (AD) is effective April 26, 2022.

(b) Affected ADs

    This AD replaces AD 2020-20-06, Amendment 39-21262 (85 FR 60356, 
September 25, 2020) (AD 2020-20-06).

(c) Applicability

    This AD applies to Bell Textron Canada Limited (type certificate 
previously held by Bell Helicopter Textron Canada Limited) Model 429 
helicopters, certificated in any category, with a bellcrank assembly 
part number (P/N) 429-001-523-101, 429-001-523-103, 429-001-532-101, 
or 429-001-532-103 installed.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 2700, Flight 
Control System.

(e) Unsafe Condition

    This AD was prompted by new bellcrank assemblies, which have 
been upgraded with corrosion resistant steel bearings. The FAA is 
issuing this AD to prevent corrosion of the bearings due to pooling 
at the bellcrank assembly from precipitation in the forward portion 
of the roof structure. The unsafe condition, if not addressed, could 
result in restrictions in the collective, directional, or pitch 
control systems, and subsequent loss of helicopter control.

(f) Compliance

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

(g) Required Actions

    (1) For Model 429 helicopters serial number (S/N) 57001 through 
57296 inclusive, within 12 months after the helicopter was 
manufactured or 30 days after the effective date of this AD, 
whichever occurs later, and thereafter at intervals not to exceed 6 
months:
    (i) Disconnect the forward ends of the collective control tube, 
longitudinal stability and control augmentation system (SCAS) 
actuator, and lateral SCAS actuator. Stow the collective control 
tube and each SCAS actuator to prevent binding.
    (ii) Move the cyclic stick fore, aft, and laterally, and the 
collective stick up and down from stop to stop to determine if there 
is any roughness. If there is any roughness in the flight control 
system, before further flight, remove each pivot bearing P/N 
MS27646-41, each arm assembly bearing P/N MS27643-4, and each sleeve 
P/N 120-13-4A from service and install bellcrank assemblies P/N 429-
001-523-101FM and 429-001-532-101FM; or 429-001-523-107FM and 429-
001-532-107FM; or 429-001-523-107 and 429-001-532-107.
    (iii) Inspect the collective arm assembly P/N 429-001-525-101, 
the lateral arm assembly P/N 429-001-527-101, and the longitudinal 
arm assembly P/N 429-001-530-101, by rotating each bearing and 
determining whether each bearing rotates freely. If there is any 
binding in any arm end bearing or on the longitudinal bellcrank 
assembly, before further flight, remove each pivot bearing P/N 
MS27646-41, each arm assembly bearing P/N MS27643-4, and each sleeve 
P/N 120-13-4A from service and install bellcrank assemblies P/N 429-
001-523-101FM and 429-001-532-101FM; or 429-001-523-107FM and 429-
001-532-107FM; or 429-001-523-107 and 429-001-532-107.
    (2) For Model 429 helicopters S/N 57001 through 57296 inclusive, 
unless already accomplished by following paragraphs (g)(1)(ii) or 
(iii) of this AD, within 24 months after the effective date of this 
AD, install bellcrank assemblies P/N 429-001-523-101FM and 429-001-
532-101FM; or 429-001-523-107FM and 429-001-532-107FM; or 429-001-
523-107 and 429-001-532-107.
    (3) As of the effective date of this AD, installing bellcrank 
assemblies P/N 429-001-523-101FM and 429-001-532-101FM; or 429-001-
523-107FM and 429-001-532-107FM; or 429-001-523-107 and 429-001-

[[Page 16100]]

532-107, constitutes a terminating action for the recurring 
inspections required by paragraph (g)(1) of this AD.
    (4) As of the effective date of this AD, do not install any 
bellcrank assembly P/N 429-001-523-101, 429-001-523-103, 429-001-
532-101, or 429-001-532-103 on any helicopter.

(h) Special Flight Permits

    Special flight permits are prohibited.

(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 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 [email protected]; or at https://www.bellflight.com/support/contact-support. 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 Transport Canada AD 
CF-2016-11R3, dated August 30, 2021. You may view the Transport 
Canada AD on the internet at https://www.regulations.gov in Docket 
No. FAA-2021-1178.

(k) Material Incorporated by Reference

    None.

    Issued on March 10, 2022.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2022-05664 Filed 3-21-22; 8:45 am]
BILLING CODE 4910-13-P
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