Airworthiness Directives; Bell Textron Canada Limited Helicopters, 66158-66162 [2021-25489]

Download as PDF 66158 Federal Register / Vol. 86, No. 222 / Monday, November 22, 2021 / Rules and Regulations responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, and (2) Will not affect intrastate aviation in Alaska. (f) Compliance Comply with this AD within the compliance times specified, unless already done. List of Subjects in 14 CFR Part 39 (h) Exceptions to EASA AD 2021–0237–E (1) Where EASA AD 2021–0237–E refers to its effective date, this AD requires using the effective date of this AD. (2) The ‘‘Remarks’’ section of EASA AD 2021–0237–E does not apply to this AD. (3) For this AD, the safety seal installation only may be deferred up to 750 flight hours or 6 months, whichever occurs first, after the effective date of this AD, if the safety seal is not available at the time of the snap wire installation. 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: ■ 2021–24–07 ATR—GIE Avions de Transport Re´gional: Amendment 39– 21828; Docket No. FAA–2021–1008; Project Identifier MCAI–2021–01210–T. (a) Effective Date This airworthiness directive (AD) is effective November 22, 2021. (b) Affected ADs None. (c) Applicability This AD applies to the ATR—GIE Avions de Transport Re´gional airplanes specified in paragraphs (c)(1) and (2) of this AD, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) Emergency AD 2021–0237–E, dated November 4, 2021 (EASA AD 2021–0237–E). (1) Model ATR42–200, –300, –320, and –500 airplanes. (2) Model ATR72–101, –102, –201, –202, –211, –212, and –212A airplanes. jspears on DSK121TN23PROD with RULES1 (d) Subject Air Transport Association (ATA) of America Code 26, Fire protection. (e) Unsafe Condition This AD was prompted by a report of a certain procedure in the aircraft maintenance manual (AMM) that incorrectly described a visual inspection of the fire handle. The FAA is issuing this AD to address snap wires made of incorrect material, which, if not detected and corrected, and combined with an engine fire, could lead to a failure of the engine fire handle to operate, possibly resulting in an uncontrolled engine fire and reduced control of the airplane. VerDate Sep<11>2014 17:19 Nov 19, 2021 Jkt 256001 (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, EASA AD 2021–0237–E. (i) No Reporting Requirement Although the service information referenced in EASA AD 2021–0237–E specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or ATR—GIE Avions de Transport Re´gional’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (k) Related Information For more information about this AD, contact Shahram Daneshmandi, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3220; email Shahram.Daneshmandi@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 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) European Union Aviation Safety Agency (EASA) Emergency AD 2021–0237–E, dated November 4, 2021. (ii) [Reserved] (3) For EASA AD 2021–0237–E, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 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. (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. Issued on November 12, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–25494 Filed 11–18–21; 11:15 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–1011; Project Identifier MCAI–2021–00867–R; Amendment 39–21830; AD 2021–24–09] RIN 2120–AA64 Airworthiness Directives; Bell Textron Canada Limited Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 430 helicopters. This AD was prompted by an in-flight failure of the main rotor (M/ R) pitch link clevis (clevis) due to fatigue damage and excessive wear. This AD requires a visual inspection of the M/R clevis, rod end, and a certain partnumbered universal bearing, performing a purge grease, and performing a magnetic particle inspection of each M/ R clevis. Depending on the visual SUMMARY: E:\FR\FM\22NOR1.SGM 22NOR1 Federal Register / Vol. 86, No. 222 / Monday, November 22, 2021 / Rules and Regulations inspection and magnetic particle inspection results, this AD requires removing certain parts from service, replacing certain parts, and performing additional actions. This AD also requires recurring inspections of each M/R clevis and each universal bearing. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective December 7, 2021. The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of December 7, 2021. The FAA must receive comments on this AD by January 6, 2022. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this 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. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 1011. jspears on DSK121TN23PROD 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–2021–1011; 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 street address for Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: Hal Jensen, Aerospace Engineer, Operational VerDate Sep<11>2014 17:19 Nov 19, 2021 Jkt 256001 Safety Branch, Compliance & Airworthiness Division, FAA, 950 L’Enfant Plaza N SW, Washington, DC 20024; telephone (202) 267–9167; email hal.jensen@faa.gov. SUPPLEMENTARY INFORMATION: Background Transport Canada, which is the aviation authority for Canada, has issued Transport Canada AD CF–2021– 26, dated July 26, 2021 (Transport Canada AD CF–2021–26), to correct an unsafe condition for Bell Textron Canada Limited Model 430 helicopters, serial numbers 49001 through 49129. Transport Canada advises of an in-flight failure of an M/R clevis which resulted in loss of control of the helicopter and fatal injuries to occupants. Transport Canada further advises that the M/R clevis part number (P/N) 430–010–432– 101 fractured at the exposed thread area above the nut, which was consistent with fatigue damage. Transport Canada also advises an inspection of the failed part determined universal bearing P/N 212–010–412–001 of the M/R pitch link assembly had excessive wear and increased resistance to rotation. Transport Canada states a similar accident previously occurred on the same model helicopter in which the M/ R clevis was found to have fractured at the neck area due to fatigue damage. Transport Canada states the restriction in freedom of movement of the universal bearing can cause increased loads on the M/R pitch link assembly and subsequent fatigue failure of the M/ R clevis prior to its life limit. Finally, Transport Canada advises the accident investigation is still ongoing. This condition, if not addressed, could result in crack initiation at the M/R clevis neck or threaded area and failure of the M/R pitch link, resulting in loss of control of the helicopter. Accordingly, Transport Canada AD CF–2021–26 requires visually inspecting the M/R clevis and rod end for wear and damage and performing corrective actions. Transport Canada AD CF–2021–26 also requires for certain part-numbered M/R rotor pitch link assemblies that have accumulated 5000 hours air time or less and have a universal bearing P/N 212–010–412–001 that is unserviceable, replacing the universal bearing. Transport Canada AD CF–2021–26 requires for certain partnumbered M/R pitch link assemblies that have accumulated more than 5,000 hours air time and have a universal bearing P/N 212–010–412–001 with signs of binding or stiffness, replacing both the universal bearing and the M/R clevis or if the universal bearing is PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 66159 unserviceable but there are no signs of binding or stiffness, replacing only the universal bearing. Transport Canada AD CF–2021–26 requires performing a purge grease of each universal bearing and performing a magnetic particle inspection of the M/R clevis to detect cracks, replacing any M/ R clevis with cracks, or if the M/R clevis does not have any cracks, replacing any missing cadmium plating. Additionally, Transport Canada AD CF–2021–26 requires after the initial visual and magnetic particle inspections, performing recurring visual inspections of the M/R clevis for corrosion and mechanical damage and performing corrective actions as needed. Transport Canada AD CF–2021–26 also requires performing recurring visual inspections of the universal bearing for binding, stiffness, wear, damage looseness, excess axial and radial play, and performing corrective actions as needed. Transport Canada AD CF– 2021–26 requires reporting any cracks or M/R clevises that are beyond published limits to Bell Product Support Engineering. Transport Canada considers its AD an interim action and states that further AD action may follow. FAA’s Determination 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 is issuing this AD after evaluating all known relevant information and determining that the unsafe condition described previously is likely to exist or develop on other helicopters of these same type designs. Related Service Information Under 1 CFR Part 51 The FAA reviewed Bell Alert Service Bulletin 430–21–60, dated July 13, 2021. This service information specifies procedures to visually inspect the M/R clevis and rod ends for wear or damage, the M/R clevis for corrosion or mechanical damage and the universal bearings for binding, stiffness, wear, looseness, excess axial and radial play, and damage. This service information also specifies procedures to perform a magnetic particle inspection, and recurring inspections of each M/R clevis and each universal bearing. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. E:\FR\FM\22NOR1.SGM 22NOR1 jspears on DSK121TN23PROD with RULES1 66160 Federal Register / Vol. 86, No. 222 / Monday, November 22, 2021 / Rules and Regulations AD Requirements This AD requires within 25 hours time-in-service (TIS) or 30 days, whichever occurs first after the effective date of this AD, removing and dissembling a certain part-numbered M/ R pitch link assembly and visually inspecting a certain part-numbered M/R clevis and rod end for wear, corrosion, and damage, which may be indicated by distortion, bending, a crack, or damaged M/R clevis threads, and removing any affected parts from service before further flight. This AD also requires visually inspecting a certain part-numbered universal bearing for binding, stiffness, wear, looseness, excess axial and radial play, and damage, which may be indicated by distortion, bending, or a crack. If certain discrepancies are found, and a certain part-numbered M/R pitch link assembly that has accumulated 5,000 or less total hours TIS is installed, this AD requires before further flight, removing a certain part-numbered universal bearing from service. If certain discrepancies are found, and a certain part-numbered M/R pitch link assembly that has accumulated more than 5,000 total hours TIS is installed, this AD requires before further flight and depending on the discrepancies, removing a certain part-numbered universal bearing and the M/R clevis from service or removing only the universal bearing from service. This AD also requires performing a purge grease of each universal bearing and performing a magnetic particle inspection of each M/R clevis for a crack in accordance with the applicable service information. Following the magnetic particle inspection, if there is a crack, this AD requires before further flight, removing each affected M/R clevis from service. If there is no crack, this AD requires performing a selective brush cadmium plating and applying a chromate conversion coating. This AD requires within 50 hours TIS after completion of the initial inspections required by this AD, and thereafter at intervals not to exceed 50 hours TIS, using a 10X magnifying glass, visually inspecting the neck and threaded area of each M/R clevis for wear, corrosion, and damage, which may be indicated by distortion, bending, a crack, or damaged M/R clevis threads, and depending on the inspection results before further flight, removing the affected part from service and replacing with an airworthy part, and repeating the magnetic particle inspection of each M/R clevis. Finally, AD requires within 150 hours TIS after the completion of the initial inspections required by this AD, and VerDate Sep<11>2014 17:19 Nov 19, 2021 Jkt 256001 thereafter at intervals not to exceed 150 hours TIS, repeating the visual inspection of each universal bearing for binding, stiffness, wear, looseness, excess axial and radial play, and damage, and performing a purge grease of each universal bearing. Differences Between This AD and Transport Canada AD CF–2021–26 Transport Canada AD CF–2021–26 specifies compliance times in terms of air time, whereas this AD requires using hours TIS. Where the service information required by Transport Canada AD CF–2021–26 specifies to report any signs of cracking to Bell Product Support Engineering, this AD does not require reporting any information. Transport Canada AD CF– 2021–26 specifies replacing any affected part, whereas this AD requires removing the affected part from service and then replacing with an airworthy part. Interim Action The FAA considers this AD to be an interim action. Once final action has been identified, the FAA might consider further rulemaking. Justification for Immediate Adoption and Determination of the Effective Date Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 U.S.C. 551 et seq.) authorizes agencies to dispense with notice and comment procedures for rules when the agency, for ‘‘good cause,’’ finds that those procedures are ‘‘impracticable, unnecessary, or contrary to the public interest.’’ Under this section, an agency, upon finding good cause, may issue a final rule without providing notice and seeking comment prior to issuance. Further, section 553(d) of the APA authorizes agencies to make rules effective in less than thirty days, upon a finding of good cause. An unsafe condition exists that requires the immediate adoption of this AD without providing an opportunity for public comments prior to adoption. The FAA has found that the risk to the flying public justifies foregoing notice and comment prior to adoption of this rule because if not corrected, the unsafe condition could lead to crack initiation at the M/R clevis neck or threaded area and consequent failure of the M/R pitch link, resulting in loss of control of the helicopter. In addition, the compliance time for the required actions is within 25 hours TIS or 30 days, whichever occurs first after the effective date of this AD, a shorter time period than the time necessary for the public to comment and for publication of the final rule. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Therefore, notice and opportunity for prior public comment are impracticable and contrary to public interest pursuant to 5 U.S.C. 553(b)(3)(B). In addition, the FAA finds that good cause exists pursuant to 5 U.S.C. 553(d) for making this amendment effective in less than 30 days, for the same reasons the FAA found good cause to forgo notice and comment. Comments Invited The FAA invites you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2021–1011; Project Identifier MCAI–2020–00867–R’’ at the beginning of your comments. The most helpful comments reference a specific portion of the final rule, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this final rule because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this final rule. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this AD contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this AD, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this AD. Submissions containing CBI should be sent to Hal Jensen, Aerospace Engineer, Operational Safety Branch, Compliance & Airworthiness Division, FAA, 950 L’Enfant Plaza N SW, Washington, DC 20024; telephone (202) 267–9167; email hal.jensen@faa.gov. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. E:\FR\FM\22NOR1.SGM 22NOR1 Federal Register / Vol. 86, No. 222 / Monday, November 22, 2021 / Rules and Regulations Regulatory Flexibility Act The requirements of the Regulatory Flexibility Act (RFA) do not apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and comment. Because the FAA has determined that it has good cause to adopt this rule without prior notice and comment, RFA analysis is not required. Costs of Compliance The FAA estimates that this AD affects 29 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. Removing and disassembling each M/ R pitch link assembly and inspecting each M/R clevis and rod end takes about 4 work-hours for an estimated cost of $340 per inspection and $9,860 for the U.S. fleet. Inspecting each universal bearing takes about 4 work-hours for an estimated cost of $340 per inspection and $9,860 for the U.S. fleet. If required, replacing each universal bearing takes about 4 work-hours for an estimated cost of $340 and parts cost about $1,000 for an estimated cost of $1,340 per replacement. If required, replacing each universal bearing and each M/R clevis takes about 8 work-hours for an estimated cost of $680 and parts cost about $3,000 for an estimated cost of $3,680 per replacement of both parts. Performing a purge grease on each universal bearing takes about 0.25 workhours for an estimated cost of $22 per purge. Performing a magnetic particle inspection of each M/R clevis takes about 2 work-hours for an estimated cost of $170 per inspection. Performing a selective brush cadmium plating takes about 4 work-hours for an estimated cost of $340 per helicopter. jspears on DSK121TN23PROD with RULES1 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 VerDate Sep<11>2014 17:19 Nov 19, 2021 Jkt 256001 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, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, and (2) Will not affect intrastate aviation in Alaska. 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: ■ 2021–24–09 Bell Textron Canada Limited: Amendment 39–21830; Docket No. FAA–2021–1011; Project Identifier MCAI–2021–00867–R. (a) Effective Date This airworthiness directive (AD) is effective December 7, 2021. (b) Affected ADs None. (c) Applicability This AD applies to Bell Textron Canada Limited Model 430 helicopters, having serial number 49001 through 49129, inclusive, certificated in any category. (d) Subject Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor Head. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 66161 (e) Unsafe Condition This AD was prompted by an in-flight failure of the main rotor (M/R) pitch link clevis (clevis) due to fatigue damage and excessive wear. The FAA is issuing this AD to detect and address any wear and damage of the M/R clevis neck or threaded area. The unsafe condition, if not addressed, could result in crack initiation at the M/R clevis neck and failure of the M/R pitch link, resulting 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) Within 25 hours time-in-service (TIS) or 30 days, whichever occurs first, after the effective date of this AD: (i) Remove and disassemble each M/R pitch link assembly part number (P/N) 430– 010–411–105, or P/N 430–010–411–107, but do not remove the inserts from the tube. Visually inspect the M/R clevis P/N 430– 010–432–101 and rod end for wear, corrosion, and damage, which for the purposes of this inspection may be indicated by distortion, bending, a crack, or damaged M/R clevis threads. If there is any wear, corrosion or damage, before further flight, remove the affected M/R clevis or the affected rod end from service. (ii) Visually inspect each universal bearing P/N 212–010–412–001 for binding, stiffness, wear, looseness, excess axial and radial play, and damage, which for the purposes of this inspection may be indicated by distortion, bending, or a crack. (A) If there is any wear, looseness, excess axial and radial play, or damage and the M/ R pitch link assembly is P/N 430–010–411– 105 or P/N 430–010–411–107 and has accumulated 5,000 or less total hours TIS, before further flight, remove the universal bearing P/N 212–010–412–001 from service and replace with an airworthy part. (B) If there is any binding or stiffness and the M/R pitch link assembly is P/N 430–010– 411–105 or P/N 430–010–411–107 and has accumulated more than 5,000 total hours TIS, before further flight, remove the universal bearing P/N 212–010–412–001 and M/R clevis from service and replace with airworthy parts. (C) If there is any wear, looseness, excess axial and radial play, or damage and the M/ R pitch link assembly is P/N 430–010–411– 105 or P/N 430–010–411–107 and has accumulated more than 5,000 total hours TIS, before further flight, remove the universal bearing P/N 212–010–412–001 from service and replace with an airworthy part. (iii) Purge grease the bearings of each universal bearing. (iv) Perform a magnetic particle inspection for any crack on each M/R clevis by following the Accomplishment Instructions, Part I, paragraphs 8. through 8.d., of Bell Alert Service Bulletin 430–21–60, dated July 13, 2021 (ASB 430–21–60). If there is any crack, before further flight, remove each affected M/R clevis from service. If there is no crack, before further flight, perform a selective brush cadmium plating to replace E:\FR\FM\22NOR1.SGM 22NOR1 66162 Federal Register / Vol. 86, No. 222 / Monday, November 22, 2021 / Rules and Regulations any missing cadmium plating and apply a chromate conversion coating. (2) Within 50 hours TIS after completion of paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 50 hours TIS: (i) Using a 10X magnifying glass, visually inspect the neck and threaded area of each M/R clevis for wear, corrosion, and damage, which for the purposes of this inspection may be indicated by distortion, bending, a crack, or damaged M/R clevis threads. Refer to Figure 3 of ASB 430–21–60 for a depiction of the area to inspect on each M/R clevis. If there is any wear, corrosion, or damage, before further flight, remove the affected M/ R clevis from service and replace with an airworthy part. (ii) Perform the actions required in paragraph (g)(1)(iv) of this AD for each M/R clevis. (3) Within 150 hours TIS after the completion of paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 150 hours TIS, visually inspect and purge grease each universal bearing, by performing the actions as required in paragraphs (g)(1)(ii) and (iii) of this AD. (h) Special Flight Permits A special flight permit may be permitted provided that there are no passengers onboard. jspears on DSK121TN23PROD with RULES1 (j) Related Information (1) For more information about this AD, contact Hal Jensen, Aerospace Engineer, Operational Safety Branch, Compliance & Airworthiness Division, FAA, 950 L’Enfant Plaza N SW, Washington, DC 20024; telephone (202) 267–9167; email hal.jensen@ faa.gov. (2) The subject of this AD is addressed in Transport Canada CF–2021–26 AD, dated July 26, 2021. You may view the Transport Canada AD at https://www.regulations.gov in Docket No. FAA–2021–1011. (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. 17:19 Nov 19, 2021 Jkt 256001 Issued on November 16, 2021. Ross Landes, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–25489 Filed 11–18–21; 11:15 am] (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. VerDate Sep<11>2014 (i) Bell Alert Service Bulletin 430–21–60, dated July 13, 2021. (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: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 89 [Docket No.: FAA–2019–1100] Policy Statement for the Reported Geometric Altitude of the Control Station of a Standard Remote Identification Unmanned Aircraft Federal Aviation Administration (FAA), U.S. Department of Transportation (DOT). ACTION: Statement of policy. AGENCY: This action clarifies FAA policy regarding the existing accuracy requirements for the reported geometric altitude of the control station of a standard remote identification unmanned aircraft. The FAA describes one acceptable way producers of unmanned aircraft can meet the minimum performance requirement for the accuracy of the control station’s reported geometric altitude. The FAA determined that this action is necessary to inform developers of means of compliance of one potential pathway to meet the performance requirement for the control station’s reported geometric altitude. DATES: The effective date of this policy is November 22, 2021. SUMMARY: PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 For information on where to obtain copies of this statement of policy and other information related to this statement, see ‘‘Additional Information’’ in the SUPPLEMENTARY INFORMATION section of this document. FOR FURTHER INFORMATION CONTACT: Paul Siegmund, Policy and Innovation Division, Federal Aviation Administration, 800 Independence Ave. SW, Washington, DC 20591; telephone 1–844–FLY–MY–UA (1–844–359–6981); email: UAShelp@faa.gov. SUPPLEMENTARY INFORMATION: ADDRESSES: I. Overview A. Background On January 15, 2021, the FAA published a final rule titled ‘‘Remote Identification of Unmanned Aircraft’’ (Remote ID final rule) with an original effective date of March 16, 2021.1 2 The Remote ID final rule requires the remote identification of unmanned aircraft in the airspace of the United States. Remote identification is the capability of an unmanned aircraft, in flight, to provide certain identification, location, and performance information that people on the ground and other airspace users can receive. In addition to the operating requirements, the Remote ID final rule provides the design and production requirements for the production of remote identification unmanned aircraft or broadcast modules. These requirements describe the performance standards for remote identification without establishing a specific means or process for regulated entities to follow.3 A person designing or producing a standard remote identification unmanned aircraft or remote identification broadcast module must show that the unmanned aircraft or broadcast module meets the performance requirements of the rule by following an FAA-accepted means of compliance. A means of compliance submitted to the FAA for acceptance 1 Remote Identification of Unmanned Aircraft final rule, 86 FR 4390 (Jan. 15, 2021). 2 On March 10, 2021, the FAA published a correction to the Remote ID final rule in accordance with the memorandum titled Regulatory Freeze Pending Review (86 FR 7424, Jan 28, 2021), delaying the final rule’s effective date to April 21, 2021 (86 FR 13629). 3 A standard remote identification unmanned aircraft broadcasts identification, location, and performance information of the unmanned aircraft and control station. This unmanned aircraft broadcasts the remote identification message elements directly from the unmanned aircraft from takeoff to shutdown. A remote identification broadcast module broadcasts identification, location, and take-off information; the broadcast module may be a separate device that is attached to an unmanned aircraft, or a feature built into the aircraft. 86 FR 4391 (Jan. 15, 2021). E:\FR\FM\22NOR1.SGM 22NOR1

Agencies

[Federal Register Volume 86, Number 222 (Monday, November 22, 2021)]
[Rules and Regulations]
[Pages 66158-66162]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-25489]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-1011; Project Identifier MCAI-2021-00867-R; 
Amendment 39-21830; AD 2021-24-09]
RIN 2120-AA64


Airworthiness Directives; Bell Textron Canada Limited Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Bell Textron Canada Limited Model 430 helicopters. This AD was 
prompted by an in-flight failure of the main rotor (M/R) pitch link 
clevis (clevis) due to fatigue damage and excessive wear. This AD 
requires a visual inspection of the M/R clevis, rod end, and a certain 
part-numbered universal bearing, performing a purge grease, and 
performing a magnetic particle inspection of each M/R clevis. Depending 
on the visual

[[Page 66159]]

inspection and magnetic particle inspection results, this AD requires 
removing certain parts from service, replacing certain parts, and 
performing additional actions. This AD also requires recurring 
inspections of each M/R clevis and each universal bearing. The FAA is 
issuing this AD to address the unsafe condition on these products.

DATES: This AD becomes effective December 7, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of December 7, 
2021.
    The FAA must receive comments on this AD by January 6, 2022.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this 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. It is also available at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-1011.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-1011; 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 
street address for Docket Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Hal Jensen, Aerospace Engineer, 
Operational Safety Branch, Compliance & Airworthiness Division, FAA, 
950 L'Enfant Plaza N SW, Washington, DC 20024; telephone (202) 267-
9167; email hal.[email protected].

SUPPLEMENTARY INFORMATION:

Background

    Transport Canada, which is the aviation authority for Canada, has 
issued Transport Canada AD CF-2021-26, dated July 26, 2021 (Transport 
Canada AD CF-2021-26), to correct an unsafe condition for Bell Textron 
Canada Limited Model 430 helicopters, serial numbers 49001 through 
49129. Transport Canada advises of an in-flight failure of an M/R 
clevis which resulted in loss of control of the helicopter and fatal 
injuries to occupants. Transport Canada further advises that the M/R 
clevis part number (P/N) 430-010-432-101 fractured at the exposed 
thread area above the nut, which was consistent with fatigue damage. 
Transport Canada also advises an inspection of the failed part 
determined universal bearing P/N 212-010-412-001 of the M/R pitch link 
assembly had excessive wear and increased resistance to rotation. 
Transport Canada states a similar accident previously occurred on the 
same model helicopter in which the M/R clevis was found to have 
fractured at the neck area due to fatigue damage. Transport Canada 
states the restriction in freedom of movement of the universal bearing 
can cause increased loads on the M/R pitch link assembly and subsequent 
fatigue failure of the M/R clevis prior to its life limit. Finally, 
Transport Canada advises the accident investigation is still ongoing. 
This condition, if not addressed, could result in crack initiation at 
the M/R clevis neck or threaded area and failure of the M/R pitch link, 
resulting in loss of control of the helicopter.
    Accordingly, Transport Canada AD CF-2021-26 requires visually 
inspecting the M/R clevis and rod end for wear and damage and 
performing corrective actions. Transport Canada AD CF-2021-26 also 
requires for certain part-numbered M/R rotor pitch link assemblies that 
have accumulated 5000 hours air time or less and have a universal 
bearing P/N 212-010-412-001 that is unserviceable, replacing the 
universal bearing. Transport Canada AD CF-2021-26 requires for certain 
part-numbered M/R pitch link assemblies that have accumulated more than 
5,000 hours air time and have a universal bearing P/N 212-010-412-001 
with signs of binding or stiffness, replacing both the universal 
bearing and the M/R clevis or if the universal bearing is unserviceable 
but there are no signs of binding or stiffness, replacing only the 
universal bearing.
    Transport Canada AD CF-2021-26 requires performing a purge grease 
of each universal bearing and performing a magnetic particle inspection 
of the M/R clevis to detect cracks, replacing any M/R clevis with 
cracks, or if the M/R clevis does not have any cracks, replacing any 
missing cadmium plating.
    Additionally, Transport Canada AD CF-2021-26 requires after the 
initial visual and magnetic particle inspections, performing recurring 
visual inspections of the M/R clevis for corrosion and mechanical 
damage and performing corrective actions as needed. Transport Canada AD 
CF-2021-26 also requires performing recurring visual inspections of the 
universal bearing for binding, stiffness, wear, damage looseness, 
excess axial and radial play, and performing corrective actions as 
needed. Transport Canada AD CF-2021-26 requires reporting any cracks or 
M/R clevises that are beyond published limits to Bell Product Support 
Engineering. Transport Canada considers its AD an interim action and 
states that further AD action may follow.

FAA's Determination

    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 is issuing this AD after evaluating all 
known relevant information and determining that the unsafe condition 
described previously is likely to exist or develop on other helicopters 
of these same type designs.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Bell Alert Service Bulletin 430-21-60, dated July 
13, 2021. This service information specifies procedures to visually 
inspect the M/R clevis and rod ends for wear or damage, the M/R clevis 
for corrosion or mechanical damage and the universal bearings for 
binding, stiffness, wear, looseness, excess axial and radial play, and 
damage. This service information also specifies procedures to perform a 
magnetic particle inspection, and recurring inspections of each M/R 
clevis and each universal bearing.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

[[Page 66160]]

AD Requirements

    This AD requires within 25 hours time-in-service (TIS) or 30 days, 
whichever occurs first after the effective date of this AD, removing 
and dissembling a certain part-numbered M/R pitch link assembly and 
visually inspecting a certain part-numbered M/R clevis and rod end for 
wear, corrosion, and damage, which may be indicated by distortion, 
bending, a crack, or damaged M/R clevis threads, and removing any 
affected parts from service before further flight. This AD also 
requires visually inspecting a certain part-numbered universal bearing 
for binding, stiffness, wear, looseness, excess axial and radial play, 
and damage, which may be indicated by distortion, bending, or a crack. 
If certain discrepancies are found, and a certain part-numbered M/R 
pitch link assembly that has accumulated 5,000 or less total hours TIS 
is installed, this AD requires before further flight, removing a 
certain part-numbered universal bearing from service. If certain 
discrepancies are found, and a certain part-numbered M/R pitch link 
assembly that has accumulated more than 5,000 total hours TIS is 
installed, this AD requires before further flight and depending on the 
discrepancies, removing a certain part-numbered universal bearing and 
the M/R clevis from service or removing only the universal bearing from 
service.
    This AD also requires performing a purge grease of each universal 
bearing and performing a magnetic particle inspection of each M/R 
clevis for a crack in accordance with the applicable service 
information. Following the magnetic particle inspection, if there is a 
crack, this AD requires before further flight, removing each affected 
M/R clevis from service. If there is no crack, this AD requires 
performing a selective brush cadmium plating and applying a chromate 
conversion coating.
    This AD requires within 50 hours TIS after completion of the 
initial inspections required by this AD, and thereafter at intervals 
not to exceed 50 hours TIS, using a 10X magnifying glass, visually 
inspecting the neck and threaded area of each M/R clevis for wear, 
corrosion, and damage, which may be indicated by distortion, bending, a 
crack, or damaged M/R clevis threads, and depending on the inspection 
results before further flight, removing the affected part from service 
and replacing with an airworthy part, and repeating the magnetic 
particle inspection of each M/R clevis.
    Finally, AD requires within 150 hours TIS after the completion of 
the initial inspections required by this AD, and thereafter at 
intervals not to exceed 150 hours TIS, repeating the visual inspection 
of each universal bearing for binding, stiffness, wear, looseness, 
excess axial and radial play, and damage, and performing a purge grease 
of each universal bearing.

Differences Between This AD and Transport Canada AD CF-2021-26

    Transport Canada AD CF-2021-26 specifies compliance times in terms 
of air time, whereas this AD requires using hours TIS. Where the 
service information required by Transport Canada AD CF-2021-26 
specifies to report any signs of cracking to Bell Product Support 
Engineering, this AD does not require reporting any information. 
Transport Canada AD CF-2021-26 specifies replacing any affected part, 
whereas this AD requires removing the affected part from service and 
then replacing with an airworthy part.

Interim Action

    The FAA considers this AD to be an interim action. Once final 
action has been identified, the FAA might consider further rulemaking.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and 
comment procedures for rules when the agency, for ``good cause,'' finds 
that those procedures are ``impracticable, unnecessary, or contrary to 
the public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than thirty days, 
upon a finding of good cause.
    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies foregoing notice and comment prior to adoption of this rule 
because if not corrected, the unsafe condition could lead to crack 
initiation at the M/R clevis neck or threaded area and consequent 
failure of the M/R pitch link, resulting in loss of control of the 
helicopter.
    In addition, the compliance time for the required actions is within 
25 hours TIS or 30 days, whichever occurs first after the effective 
date of this AD, a shorter time period than the time necessary for the 
public to comment and for publication of the final rule.
    Therefore, notice and opportunity for prior public comment are 
impracticable and contrary to public interest pursuant to 5 U.S.C. 
553(b)(3)(B). In addition, the FAA finds that good cause exists 
pursuant to 5 U.S.C. 553(d) for making this amendment effective in less 
than 30 days, for the same reasons the FAA found good cause to forgo 
notice and comment.

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments to an address listed under 
ADDRESSES. Include ``Docket No. FAA-2021-1011; Project Identifier MCAI-
2020-00867-R'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the final rule, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this final rule because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this final rule.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this AD contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this AD, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this AD. Submissions containing CBI should be sent to Hal 
Jensen, Aerospace Engineer, Operational Safety Branch, Compliance & 
Airworthiness Division, FAA, 950 L'Enfant Plaza N SW, Washington, DC 
20024; telephone (202) 267-9167; email [email protected]. Any 
commentary that the FAA receives which is not specifically designated 
as CBI will be placed in the public docket for this rulemaking.

[[Page 66161]]

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without prior notice and 
comment, RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 29 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.
    Removing and disassembling each M/R pitch link assembly and 
inspecting each M/R clevis and rod end takes about 4 work-hours for an 
estimated cost of $340 per inspection and $9,860 for the U.S. fleet.
    Inspecting each universal bearing takes about 4 work-hours for an 
estimated cost of $340 per inspection and $9,860 for the U.S. fleet.
    If required, replacing each universal bearing takes about 4 work-
hours for an estimated cost of $340 and parts cost about $1,000 for an 
estimated cost of $1,340 per replacement.
    If required, replacing each universal bearing and each M/R clevis 
takes about 8 work-hours for an estimated cost of $680 and parts cost 
about $3,000 for an estimated cost of $3,680 per replacement of both 
parts.
    Performing a purge grease on each universal bearing takes about 
0.25 work-hours for an estimated cost of $22 per purge.
    Performing a magnetic particle inspection of each M/R clevis takes 
about 2 work-hours for an estimated cost of $170 per inspection.
    Performing a selective brush cadmium plating takes about 4 work-
hours for an estimated cost of $340 per helicopter.

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, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866, and
    (2) Will not affect intrastate aviation in Alaska.

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:

2021-24-09 Bell Textron Canada Limited: Amendment 39-21830; Docket 
No. FAA-2021-1011; Project Identifier MCAI-2021-00867-R.

(a) Effective Date

    This airworthiness directive (AD) is effective December 7, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bell Textron Canada Limited Model 430 
helicopters, having serial number 49001 through 49129, inclusive, 
certificated in any category.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor 
Head.

(e) Unsafe Condition

    This AD was prompted by an in-flight failure of the main rotor 
(M/R) pitch link clevis (clevis) due to fatigue damage and excessive 
wear. The FAA is issuing this AD to detect and address any wear and 
damage of the M/R clevis neck or threaded area. The unsafe 
condition, if not addressed, could result in crack initiation at the 
M/R clevis neck and failure of the M/R pitch link, resulting 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) Within 25 hours time-in-service (TIS) or 30 days, whichever 
occurs first, after the effective date of this AD:
    (i) Remove and disassemble each M/R pitch link assembly part 
number (P/N) 430-010-411-105, or P/N 430-010-411-107, but do not 
remove the inserts from the tube. Visually inspect the M/R clevis P/
N 430-010-432-101 and rod end for wear, corrosion, and damage, which 
for the purposes of this inspection may be indicated by distortion, 
bending, a crack, or damaged M/R clevis threads. If there is any 
wear, corrosion or damage, before further flight, remove the 
affected M/R clevis or the affected rod end from service.
    (ii) Visually inspect each universal bearing P/N 212-010-412-001 
for binding, stiffness, wear, looseness, excess axial and radial 
play, and damage, which for the purposes of this inspection may be 
indicated by distortion, bending, or a crack.
    (A) If there is any wear, looseness, excess axial and radial 
play, or damage and the M/R pitch link assembly is P/N 430-010-411-
105 or P/N 430-010-411-107 and has accumulated 5,000 or less total 
hours TIS, before further flight, remove the universal bearing P/N 
212-010-412-001 from service and replace with an airworthy part.
    (B) If there is any binding or stiffness and the M/R pitch link 
assembly is P/N 430-010-411-105 or P/N 430-010-411-107 and has 
accumulated more than 5,000 total hours TIS, before further flight, 
remove the universal bearing P/N 212-010-412-001 and M/R clevis from 
service and replace with airworthy parts.
    (C) If there is any wear, looseness, excess axial and radial 
play, or damage and the M/R pitch link assembly is P/N 430-010-411-
105 or P/N 430-010-411-107 and has accumulated more than 5,000 total 
hours TIS, before further flight, remove the universal bearing P/N 
212-010-412-001 from service and replace with an airworthy part.
    (iii) Purge grease the bearings of each universal bearing.
    (iv) Perform a magnetic particle inspection for any crack on 
each M/R clevis by following the Accomplishment Instructions, Part 
I, paragraphs 8. through 8.d., of Bell Alert Service Bulletin 430-
21-60, dated July 13, 2021 (ASB 430-21-60). If there is any crack, 
before further flight, remove each affected M/R clevis from service. 
If there is no crack, before further flight, perform a selective 
brush cadmium plating to replace

[[Page 66162]]

any missing cadmium plating and apply a chromate conversion coating.
    (2) Within 50 hours TIS after completion of paragraph (g)(1) of 
this AD, and thereafter at intervals not to exceed 50 hours TIS:
    (i) Using a 10X magnifying glass, visually inspect the neck and 
threaded area of each M/R clevis for wear, corrosion, and damage, 
which for the purposes of this inspection may be indicated by 
distortion, bending, a crack, or damaged M/R clevis threads. Refer 
to Figure 3 of ASB 430-21-60 for a depiction of the area to inspect 
on each M/R clevis. If there is any wear, corrosion, or damage, 
before further flight, remove the affected M/R clevis from service 
and replace with an airworthy part.
    (ii) Perform the actions required in paragraph (g)(1)(iv) of 
this AD for each M/R clevis.
    (3) Within 150 hours TIS after the completion of paragraph 
(g)(1) of this AD, and thereafter at intervals not to exceed 150 
hours TIS, visually inspect and purge grease each universal bearing, 
by performing the actions as required in paragraphs (g)(1)(ii) and 
(iii) of this AD.

(h) Special Flight Permits

    A special flight permit may be permitted provided that there are 
no passengers onboard.

(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 Hal Jensen, 
Aerospace Engineer, Operational Safety Branch, Compliance & 
Airworthiness Division, FAA, 950 L'Enfant Plaza N SW, Washington, DC 
20024; telephone (202) 267-9167; email [email protected].
    (2) The subject of this AD is addressed in Transport Canada CF-
2021-26 AD, dated July 26, 2021. You may view the Transport Canada 
AD at https://www.regulations.gov in Docket No. FAA-2021-1011.

(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) Bell Alert Service Bulletin 430-21-60, dated July 13, 2021.
    (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 [email protected]; 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: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on November 16, 2021.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-25489 Filed 11-18-21; 11:15 am]
BILLING CODE 4910-13-P