Airworthiness Directives; Bell Textron Canada Limited (Type Certificate Previously Held by Bell Helicopter Textron Canada Limited) Helicopters, 10107-10110 [2022-03770]

Download as PDF Federal Register / Vol. 87, No. 36 / Wednesday, February 23, 2022 / Proposed Rules 10107 5 There are no existing NRC licenses in these fee categories. If NRC issues a license for these categories, the Commission will consider establishing an annual fee for this type of license. 6 Standardized spent fuel facilities, 10 CFR parts 71 and 72 Certificates of Compliance and related Quality Assurance program approvals, and special reviews, such as topical reports, are not assessed an annual fee because the generic costs of regulating these activities are primarily attributable to users of the designs, certificates, and topical reports. 7 Licensees in this category are not assessed an annual fee because they are charged an annual fee in other categories while they are licensed to operate. 8 No annual fee is charged because it is not practical to administer due to the relatively short life or temporary nature of the license. 9 Separate annual fees will not be assessed for pacemaker licenses issued to medical institutions that also hold nuclear medicine licenses under fee categories 7.A, 7.A.1, 7.A.2, 7.B., 7.B.1, 7.B.2, 7.C, 7.C.1, or 7.C.2. 10 This includes Certificates of Compliance issued to the U.S. Department of Energy that are not funded from the Nuclear Waste Fund. 11 See § 171.15(c). 12 See § 171.15(c). 13 No annual fee is charged for this category because the cost of the general license registration program applicable to licenses in this category will be recovered through 10 CFR part 170 fees. 14 Persons who possess radium sources that are used for operational purposes in another fee category are not also subject to the fees in this category. (This exception does not apply if the radium sources are possessed for storage only.) 15 Licensees subject to fees under categories 1.A., 1.B., 1.E., 2.A., and licensees paying fees under fee category 17 must pay the largest applicable fee and are not subject to additional fees listed in this table. 16 Licensees paying fees under 3.C. are not subject to fees under 2.B. for possession and shielding authorized on the same license. 17 Licensees paying fees under 7.C. are not subject to fees under 2.B. for possession and shielding authorized on the same license. 18 Licensees paying fees under 3.N. are not subject to paying fees under 3.P., 3.P.1, or 3.P.2 for calibration or leak testing services authorized on the same license. 19 Licensees paying fees under 7.B., 7.B.1, or 7.B.2 are not subject to paying fees under 7.C., 7.C.1, or 7.C.2 for broad scope license licenses issued under parts 30, 35, 40, and 70 of this chapter for human use of byproduct material, source material, and/or special nuclear material, except licenses for byproduct material, source material, or special nuclear material in sealed sources contained in teletherapy devices authorized on the same license. 20 No annual fee is charged for a materials license (or part of a materials license) that has transitioned to this fee category because the decommissioning costs will be recovered through 10 CFR part 170 fees, but annual fees may be charged for other activities authorized under the license that are not in decommissioning status. 21 Licensees paying fees under 4.A., 4.B. or 4.C. are not subject to paying fees under 3.N. licenses that authorize services for other licensees authorized on the same license. Dated: February 15, 2022. For the Nuclear Regulatory Commission. Cherish K. Johnson, Chief Financial Officer. [FR Doc. 2022–03715 Filed 2–18–22; 4:15 pm] BILLING CODE 7590–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2022–0145; Project Identifier MCAI–2021–00522–R] RIN 2120–AA64 Airworthiness Directives; Bell Textron Canada Limited (Type Certificate Previously Held by Bell Helicopter Textron Canada Limited) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2019–11–05, which applies to Bell Helicopter Textron Canada Limited (now Bell Textron Canada Limited) Model 429 helicopters having certain tail rotor (TR) pitch link assemblies. AD 2019–11–05 requires inspecting the TR pitch link assemblies, and replacing certain pitch link bearings. Since the FAA issued AD 2019–11–05, the FAA has determined that all TR pitch link assemblies are affected by the unsafe khammond on DSKJM1Z7X2PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 17:39 Feb 22, 2022 Jkt 256001 condition. This proposed AD would continue to require the actions specified in AD 2019–11–05, and would revise the applicability and require inspections of certain other TR pitch link assemblies. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by April 11, 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 NPRM, 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 material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information PO 00000 Frm 00027 Fmt 4702 Sfmt 4702 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–2022–0145; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the Transport Canada Civil Aviation (TCCA) 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; phone: (202) 267–9167; email: hal.jensen@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2022–0145; Project Identifier MCAI–2021–00522–R’’ at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this proposal because of those comments. E:\FR\FM\23FEP1.SGM 23FEP1 10108 Federal Register / Vol. 87, No. 36 / Wednesday, February 23, 2022 / Proposed Rules 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 proposal. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Hal Jensen, Aerospace Engineer, Operational Safety Branch, Compliance & Airworthiness Division, FAA, 950 L’Enfant Plaza N SW, Washington, DC 20024; phone: (202) 267–9167; email: hal.jensen@faa.gov. Any commentary that the FAA receives that is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background The FAA issued AD 2019–11–05, Amendment 39–19651 (84 FR 26546, June 7, 2019) (AD 2019–11–05), which applies to certain Bell Helicopter Textron Canada Limited Model 429 helicopters. AD 2019–11–05 requires inspecting the TR pitch link assemblies, and replacing certain pitch link bearings. The FAA issued AD 2019–11– 05 to address a worn pitch link, which if not corrected, could result in pitch link failure and subsequent loss of control of the helicopter. Actions Since AD 2019–11–05 Was Issued Since the FAA issued AD 2019–11– 05, the FAA has determined that additional TR pitch link assemblies are affected by the unsafe condition. AD 2019–11–05 applies to helicopters with a pitch link assembly part number (P/N) 429–012–112–101, 429–012–112–103, 429–012–112–101FM, or 429–012–112– 103FM installed. However, as specified in the corresponding TCCA AD, CF– 2015–16R2, dated April 3, 2017 (TCCA AD CF–2015–16R2), all pitch link assemblies are part of the repetitive inspections. The TCCA, which is the aviation authority for Canada, has issued TCCA AD CF–2015–16R3, dated April 30, 2021 (TCCA AD CF–2015–16R3) (also referred to as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for certain Bell Helicopter Textron Canada Limited Model 429 helicopters. TCCA AD CF–2015–16R3 retains the requirements of TCCA AD CF–2015– 16R2 and revises the applicability by specifying certain helicopter serial numbers to account for new production helicopters which have already incorporated the new pitch link assemblies and corrected the unsafe condition. TCCA AD CF–2015–16R3 also specifies that installing a new pitch link assembly terminates the repetitive inspections. This proposed AD was prompted by a report of a worn pitch link, and the FAA’s determination that that all TR pitch link assemblies are affected by the unsafe condition. The FAA is proposing this AD to address a worn pitch link, which if not corrected, could result in pitch link failure and subsequent loss of control of the helicopter. See the MCAI for additional background information. FAA’s Determination These products have been approved by the aviation authority of Canada, and are approved for operation in the United States. Pursuant to the bilateral agreement with Canada, TCCA, its technical representative, has notified the FAA of the unsafe condition described in its AD. The FAA is proposing this AD after evaluating all known relevant information and determining the unsafe condition described previously is likely to exist or develop in other products of the same type design. Related Service Information Under 1 CFR Part 51 The FAA reviewed Bell Alert Service Bulletin No. 429–15–16, Revision C, dated October 16, 2020. This service information contains procedures for inspecting the TR pitch link assemblies, replacing certain pitch link bearings, and replacement of the pitch link assemblies. This material 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. Proposed AD Requirements in this NPRM This proposed AD would retain all of the requirements of AD 2019–11–05. This proposed AD would revise the applicability and require inspections of all TR pitch link assemblies. Costs of Compliance The FAA estimates that this proposed AD affects 120 helicopters of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: khammond on DSKJM1Z7X2PROD with PROPOSALS ESTIMATED COSTS FOR REQUIRED ACTIONS Action Labor cost Retained inspections from AD 2019-11-05. New inspections ..................... 2 work-hours × $85 per hour = $170 per inspection cycle. 2 work-hours × $85 per hour = $170 per inspection cycle. The FAA estimates the following costs to do any necessary on-condition replacements that would be required VerDate Sep<11>2014 17:39 Feb 22, 2022 Jkt 256001 Cost per product Cost on U.S. operators $0 $170 per inspection cycle ...... $20,400 per inspection cycle. 0 170 per inspection cycle ........ 20,400 per inspection cycle. Parts cost based on the results of any required actions. The FAA has no way of determining the number of helicopters PO 00000 Frm 00028 Fmt 4702 Sfmt 4702 that might need these on-condition actions: E:\FR\FM\23FEP1.SGM 23FEP1 Federal Register / Vol. 87, No. 36 / Wednesday, February 23, 2022 / Proposed Rules 10109 ESTIMATED COSTS OF ON-CONDITION ACTIONS Action Labor cost Parts cost Cost per product Cost on U.S. operators Bearing replacements ..................................... 3 work-hours × $85 per hour = $255 ............. $3,340 $3,343 $401,160 According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected operators. The FAA does not control warranty coverage for affected operators. As a result, the FAA has included all known costs in the cost estimate. Authority for This Rulemaking PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ 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 khammond on DSKJM1Z7X2PROD with PROPOSALS The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Would not affect intrastate aviation in Alaska, and (3) Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive (AD) 2019–11–05, Amendment 39– 19651 (84 FR 26546, June 7, 2019); and ■ b. Adding the following new AD: ■ ■ Bell Textron Canada Limited (Type Certificate Previously Held by Bell Helicopter Textron Canada Limited): Docket No. FAA–2022–0145; Project Identifier MCAI–2021–00522–R. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) action by April 11, 2022. (b) Affected ADs (1) This AD replaces AD 2019–11–05, Amendment 39–19651 (84 FR 26546, June 7, 2019) (AD 2019–11–05). (2) This AD affects AD 2020–17–10, Amendment 39–21215 (85 FR 49941, August 17, 2020) (AD 2020–17–10). (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, serial numbers 57001 through 57401 inclusive. (d) Subject Joint Aircraft System Component (JASC) Code 6720, Tail Rotor Control System. (e) Unsafe Condition This AD was prompted by a report of a worn pitch link. The FAA is issuing this AD to address a worn pitch link, which if not corrected, could result in pitch link failure and subsequent loss of control of the helicopter. List of Subjects in 14 CFR Part 39 (f) Compliance Comply with this AD within the compliance times specified, unless already done. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (g) Retained Requirements (1) For pitch link assembly part number (P/ N) 429–012–112–101, 429–012–112–103, VerDate Sep<11>2014 17:39 Feb 22, 2022 Jkt 256001 PO 00000 Frm 00029 Fmt 4702 Sfmt 4702 429–012–112–101FM, and 429–012–112– 103FM: Within 50 hours time-in-service (TIS) after July 12, 2019 (the effective date of AD 2019–11–05) and thereafter at intervals not to exceed 50 hours TIS: (i) Perform a dimensional inspection of each inboard and outboard pitch link assembly for axial and radial bearing play. With a 10X or higher power magnifying glass, inspect the bearing liner for a crack, deterioration of the liner, and extrusion of the liner from the plane. If there is axial or radial play that exceeds allowable limits, or if there is a crack, deterioration of the liner, or extrusion of the liner, before further flight, replace the bearing. (ii) Inspect the pitch link assembly sealant for pin holes and voids and to determine if the sealant thickness is 0.025 inch (0.64 mm) or less, extends over the roll staked lip by 0.030 inch (0.76 mm) or more, and is clear of the bearing ball. If there is a pin hole or void, or if the sealant exceeds 0.026 inch (0.66 mm), does not extend over the roll staked lip by 0.030 inch (0.76 mm) or more, or is not clear of the bearing ball, before further flight, replace the bearing. (2) For pitch link assembly part number (P/ N) 429–012–112–101, 429–012–112–103, 429–012–112–101FM, and 429–012–112– 103FM, within 200 hours TIS following the initial inspection required by paragraph (g)(1) of this AD, or if the hours TIS of a pitch link assembly exceed 250 hours TIS or are unknown, at the next 50-hour-TIS inspection required by paragraph (g)(1) of this AD: (i) Replace each bearing P/N 429–312–107– 103 with a date of manufacture before January 13, 2015, with a bearing P/N 429– 312–107–103 that was manufactured on or after January 13, 2015. (ii) Using a white permanent fine point marker or equivalent, re-identify the pitch link assembly: (A) Re-identify P/N 429–012–112–101 and 429–012–112–101FM as 429–012–112– 111FM. (B) Re-identify P/N 429–012–112–103 and 429–012–112–103FM as 429–012–112– 113FM. (iii) Apply a coating of DEVCON 2–TON (C–298) or equivalent over the new P/N. (h) New Requirements For pitch link assemblies other than P/N 429–012–112–101, 429–012–112–103, 429– 012–112–101FM, and 429–012–112–103FM: Within 50 hours TIS after the effective date of this AD and thereafter at intervals not to exceed 50 hours TIS: (1) Perform a dimensional inspection of each inboard and outboard pitch link assembly for axial and radial bearing play. With a 10X or higher power magnifying glass, inspect the bearing liner for a crack, deterioration of the liner, and extrusion of the liner from the plane. If there is axial or radial play that exceeds allowable limits, or E:\FR\FM\23FEP1.SGM 23FEP1 10110 Federal Register / Vol. 87, No. 36 / Wednesday, February 23, 2022 / Proposed Rules if there is a crack, deterioration of the liner, or extrusion of the liner, before further flight, replace the bearing. (2) Inspect the pitch link assembly sealant for pin holes and voids and to determine if the sealant thickness is 0.025 inch (0.64 mm) or less, extends over the roll staked lip by 0.030 inch (0.76 mm) or more, and is clear of the bearing ball. If there is a pin hole or void, or if the sealant exceeds 0.026 inch (0.66 mm), does not extend over the roll staked lip by 0.030 inch (0.76 mm) or more, or is not clear of the bearing ball, before further flight, replace the bearing. (i) Terminating Action for Certain Actions in AD 2020–17–10 Accomplishing the initial inspection required by paragraph (g)(1) or (h) of this AD constitutes terminating action for the inspections required by paragraph (f)(2) of AD 2020–17–10 for that pitch link assembly only. (j) Optional Terminating Action The repetitive inspections required by paragraph (h) of this AD are no longer required for helicopters that incorporate pitch link assemblies, P/N 429–012–212–105 or 429–012–212–107, in accordance with Part III of the Accomplishment Instructions of Bell Alert Service Bulletin No. 429–15–16, Revision C, dated October 16, 2020. khammond on DSKJM1Z7X2PROD with PROPOSALS (k) 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 (l)(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. (l) 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; phone: (202) 267–9167; email: hal.jensen@faa.gov. (2) Bell Alert Service Bulletin No. 429–15– 16, Revision C, dated October 16, 2020, which is not incorporated by reference, contains additional information about the subject of this AD. 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 VerDate Sep<11>2014 17:39 Feb 22, 2022 Jkt 256001 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 Civil Aviation (TCCA) AD CF–2015–16R3, dated April 30, 2021 (TCCA AD CF–2015–16R3). You may view the Transport Canada AD on the internet at https://www.regulations.gov in Docket No. FAA–2022–0145. Issued on February 15, 2022. Ross Landes, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–03770 Filed 2–22–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–1168; Project Identifier AD–2021–00825–T] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737–8 airplanes. This proposed AD was prompted by a report that, during production, a small number of fasteners in certain locations of the center fuel tank were cap sealed on top of a black stripe of ink with a clear overcoat. This clear overcoat is not an approved surface for sealing and can potentially compromise sealant adhesion. Compromised sealant adhesion can, over time, affect the lightning-protection properties of the airplane. This proposed AD would require preparation of the affected surface areas to ensure that there is adequate sealant adhesion, and complete encapsulation of the discrepant fastener locations with the approved production sealant. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by April 11, 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. SUMMARY: PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, ;M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231– 3195. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 1168. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–1168; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, any comments received, and other information. The street address for Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: Chris Baker, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206– 231–3552; email: christopher.r.baker@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2021–1168; Project Identifier AD– 2021–00825–T’’ at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this proposal because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other E:\FR\FM\23FEP1.SGM 23FEP1

Agencies

[Federal Register Volume 87, Number 36 (Wednesday, February 23, 2022)]
[Proposed Rules]
[Pages 10107-10110]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-03770]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0145; Project Identifier MCAI-2021-00522-R]
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), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2019-11-05, which applies to Bell Helicopter Textron Canada Limited 
(now Bell Textron Canada Limited) Model 429 helicopters having certain 
tail rotor (TR) pitch link assemblies. AD 2019-11-05 requires 
inspecting the TR pitch link assemblies, and replacing certain pitch 
link bearings. Since the FAA issued AD 2019-11-05, the FAA has 
determined that all TR pitch link assemblies are affected by the unsafe 
condition. This proposed AD would continue to require the actions 
specified in AD 2019-11-05, and would revise the applicability and 
require inspections of certain other TR pitch link assemblies. The FAA 
is proposing this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by April 11, 
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 NPRM, 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 material 
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-2022-0145; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this NPRM, the 
Transport Canada Civil Aviation (TCCA) 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; phone: (202) 267-9167; 
email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2022-0145; Project Identifier 
MCAI-2021-00522-R'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this proposal because of those comments.

[[Page 10108]]

    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 proposal.

Confidential Business Information

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

Background

    The FAA issued AD 2019-11-05, Amendment 39-19651 (84 FR 26546, June 
7, 2019) (AD 2019-11-05), which applies to certain Bell Helicopter 
Textron Canada Limited Model 429 helicopters. AD 2019-11-05 requires 
inspecting the TR pitch link assemblies, and replacing certain pitch 
link bearings. The FAA issued AD 2019-11-05 to address a worn pitch 
link, which if not corrected, could result in pitch link failure and 
subsequent loss of control of the helicopter.

Actions Since AD 2019-11-05 Was Issued

    Since the FAA issued AD 2019-11-05, the FAA has determined that 
additional TR pitch link assemblies are affected by the unsafe 
condition. AD 2019-11-05 applies to helicopters with a pitch link 
assembly part number (P/N) 429-012-112-101, 429-012-112-103, 429-012-
112-101FM, or 429-012-112-103FM installed. However, as specified in the 
corresponding TCCA AD, CF-2015-16R2, dated April 3, 2017 (TCCA AD CF-
2015-16R2), all pitch link assemblies are part of the repetitive 
inspections.
    The TCCA, which is the aviation authority for Canada, has issued 
TCCA AD CF-2015-16R3, dated April 30, 2021 (TCCA AD CF-2015-16R3) (also 
referred to as the Mandatory Continuing Airworthiness Information, or 
the MCAI), to correct an unsafe condition for certain Bell Helicopter 
Textron Canada Limited Model 429 helicopters. TCCA AD CF-2015-16R3 
retains the requirements of TCCA AD CF-2015-16R2 and revises the 
applicability by specifying certain helicopter serial numbers to 
account for new production helicopters which have already incorporated 
the new pitch link assemblies and corrected the unsafe condition. TCCA 
AD CF-2015-16R3 also specifies that installing a new pitch link 
assembly terminates the repetitive inspections.
    This proposed AD was prompted by a report of a worn pitch link, and 
the FAA's determination that that all TR pitch link assemblies are 
affected by the unsafe condition. The FAA is proposing this AD to 
address a worn pitch link, which if not corrected, could result in 
pitch link failure and subsequent loss of control of the helicopter. 
See the MCAI for additional background information.

FAA's Determination

    These products have been approved by the aviation authority of 
Canada, and are approved for operation in the United States. Pursuant 
to the bilateral agreement with Canada, TCCA, its technical 
representative, has notified the FAA of the unsafe condition described 
in its AD. The FAA is proposing this AD after evaluating all known 
relevant information and determining the unsafe condition described 
previously is likely to exist or develop in other products of the same 
type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Bell Alert Service Bulletin No. 429-15-16, 
Revision C, dated October 16, 2020. This service information contains 
procedures for inspecting the TR pitch link assemblies, replacing 
certain pitch link bearings, and replacement of the pitch link 
assemblies. This material 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.

Proposed AD Requirements in this NPRM

    This proposed AD would retain all of the requirements of AD 2019-
11-05. This proposed AD would revise the applicability and require 
inspections of all TR pitch link assemblies.

Costs of Compliance

    The FAA estimates that this proposed AD affects 120 helicopters of 
U.S. registry. The FAA estimates the following costs to comply with 
this proposed AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Retained inspections from AD       2 work-hours x $85               $0  $170 per inspection  $20,400 per
 2019[dash]11[dash]05.              per hour = $170                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
New inspections..................  2 work-hours x $85                0  170 per inspection   20,400 per
                                    per hour = $170                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary on-
condition replacements that would be required based on the results of 
any required actions. The FAA has no way of determining the number of 
helicopters that might need these on-condition actions:

[[Page 10109]]



                                     Estimated Costs of On-Condition Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Bearing replacements................  3 work-hours x $85 per           $3,340           $3,343         $401,160
                                       hour = $255.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected operators. The FAA does not control warranty coverage for 
affected operators. As a result, the FAA has included all known costs 
in the cost estimate.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2019-11-05, Amendment 39-19651 
(84 FR 26546, June 7, 2019); and
0
b. Adding the following new AD:

Bell Textron Canada Limited (Type Certificate Previously Held by 
Bell Helicopter Textron Canada Limited): Docket No. FAA-2022-0145; 
Project Identifier MCAI-2021-00522-R.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) action by April 11, 2022.

(b) Affected ADs

    (1) This AD replaces AD 2019-11-05, Amendment 39-19651 (84 FR 
26546, June 7, 2019) (AD 2019-11-05).
    (2) This AD affects AD 2020-17-10, Amendment 39-21215 (85 FR 
49941, August 17, 2020) (AD 2020-17-10).

(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, serial numbers 57001 
through 57401 inclusive.

(d) Subject

    Joint Aircraft System Component (JASC) Code 6720, Tail Rotor 
Control System.

(e) Unsafe Condition

    This AD was prompted by a report of a worn pitch link. The FAA 
is issuing this AD to address a worn pitch link, which if not 
corrected, could result in pitch link failure and subsequent loss of 
control of the helicopter.

(f) Compliance

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

(g) Retained Requirements

    (1) For pitch link assembly part number (P/N) 429-012-112-101, 
429-012-112-103, 429-012-112-101FM, and 429-012-112-103FM: Within 50 
hours time-in-service (TIS) after July 12, 2019 (the effective date 
of AD 2019-11-05) and thereafter at intervals not to exceed 50 hours 
TIS:
    (i) Perform a dimensional inspection of each inboard and 
outboard pitch link assembly for axial and radial bearing play. With 
a 10X or higher power magnifying glass, inspect the bearing liner 
for a crack, deterioration of the liner, and extrusion of the liner 
from the plane. If there is axial or radial play that exceeds 
allowable limits, or if there is a crack, deterioration of the 
liner, or extrusion of the liner, before further flight, replace the 
bearing.
    (ii) Inspect the pitch link assembly sealant for pin holes and 
voids and to determine if the sealant thickness is 0.025 inch (0.64 
mm) or less, extends over the roll staked lip by 0.030 inch (0.76 
mm) or more, and is clear of the bearing ball. If there is a pin 
hole or void, or if the sealant exceeds 0.026 inch (0.66 mm), does 
not extend over the roll staked lip by 0.030 inch (0.76 mm) or more, 
or is not clear of the bearing ball, before further flight, replace 
the bearing.
    (2) For pitch link assembly part number (P/N) 429-012-112-101, 
429-012-112-103, 429-012-112-101FM, and 429-012-112-103FM, within 
200 hours TIS following the initial inspection required by paragraph 
(g)(1) of this AD, or if the hours TIS of a pitch link assembly 
exceed 250 hours TIS or are unknown, at the next 50-hour-TIS 
inspection required by paragraph (g)(1) of this AD:
    (i) Replace each bearing P/N 429-312-107-103 with a date of 
manufacture before January 13, 2015, with a bearing P/N 429-312-107-
103 that was manufactured on or after January 13, 2015.
    (ii) Using a white permanent fine point marker or equivalent, 
re-identify the pitch link assembly:
    (A) Re-identify P/N 429-012-112-101 and 429-012-112-101FM as 
429-012-112-111FM.
    (B) Re-identify P/N 429-012-112-103 and 429-012-112-103FM as 
429-012-112-113FM.
    (iii) Apply a coating of DEVCON 2-TON (C-298) or equivalent over 
the new P/N.

(h) New Requirements

    For pitch link assemblies other than P/N 429-012-112-101, 429-
012-112-103, 429-012-112-101FM, and 429-012-112-103FM: Within 50 
hours TIS after the effective date of this AD and thereafter at 
intervals not to exceed 50 hours TIS:
    (1) Perform a dimensional inspection of each inboard and 
outboard pitch link assembly for axial and radial bearing play. With 
a 10X or higher power magnifying glass, inspect the bearing liner 
for a crack, deterioration of the liner, and extrusion of the liner 
from the plane. If there is axial or radial play that exceeds 
allowable limits, or

[[Page 10110]]

if there is a crack, deterioration of the liner, or extrusion of the 
liner, before further flight, replace the bearing.
    (2) Inspect the pitch link assembly sealant for pin holes and 
voids and to determine if the sealant thickness is 0.025 inch (0.64 
mm) or less, extends over the roll staked lip by 0.030 inch (0.76 
mm) or more, and is clear of the bearing ball. If there is a pin 
hole or void, or if the sealant exceeds 0.026 inch (0.66 mm), does 
not extend over the roll staked lip by 0.030 inch (0.76 mm) or more, 
or is not clear of the bearing ball, before further flight, replace 
the bearing.

(i) Terminating Action for Certain Actions in AD 2020-17-10

    Accomplishing the initial inspection required by paragraph 
(g)(1) or (h) of this AD constitutes terminating action for the 
inspections required by paragraph (f)(2) of AD 2020-17-10 for that 
pitch link assembly only.

(j) Optional Terminating Action

    The repetitive inspections required by paragraph (h) of this AD 
are no longer required for helicopters that incorporate pitch link 
assemblies, P/N 429-012-212-105 or 429-012-212-107, in accordance 
with Part III of the Accomplishment Instructions of Bell Alert 
Service Bulletin No. 429-15-16, Revision C, dated October 16, 2020.

(k) 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 (l)(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.

(l) 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; phone: (202) 267-9167; email: [email protected].
    (2) Bell Alert Service Bulletin No. 429-15-16, Revision C, dated 
October 16, 2020, which is not incorporated by reference, contains 
additional information about the subject of this AD. 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 
Civil Aviation (TCCA) AD CF-2015-16R3, dated April 30, 2021 (TCCA AD 
CF-2015-16R3). You may view the Transport Canada AD on the internet 
at https://www.regulations.gov in Docket No. FAA-2022-0145.

    Issued on February 15, 2022.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2022-03770 Filed 2-22-22; 8:45 am]
BILLING CODE 4910-13-P

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