Airworthiness Directives; Airbus Helicopters, 3943-3946 [2022-01440]

Download as PDF khammond on DSKJM1Z7X2PROD with PROPOSALS Federal Register / Vol. 87, No. 17 / Wednesday, January 26, 2022 / Proposed Rules (8) A participant may not withdraw funds directly from his or her mutual fund window account. To make a withdrawal, the participant must elect a fund transfer back to the TSP core funds as described in paragraph (b) of this section. Upon completion of such fund transfer, the participant may make a withdrawal in accordance with 5 CFR part 1650. (b) Fund transfers back to TSP core funds. A participant may elect to make a fund transfer to the TSP core funds from amounts invested in his or her mutual fund window account, subject to the following rules: (1) Fund transfers must be made in whole dollar increments (percentages are not permitted); (2) Amounts to be transferred from a participant’s mutual fund window account to the TSP core funds must first be transferred to the sweep money market fund. Subsequently, the participant may direct the investment of the transferred amounts into the TSP core funds; (3) Each fund transfer back to the TSP core funds from the mutual fund window account counts toward the monthly limit set forth in § 1601.32(b); except, however, that a participant may always elect a fund transfer from the mutual fund window account to the G Fund; and (4) Fund transfers are subject to the fees set forth in § 1601.53. (c) Forced transfers. The TSP record keeper will force a transfer from the participant’s mutual fund window account to the TSP core funds in the following situations, and subject to the following rules: (1) A forced transfer may occur if the balance invested in the TSP core funds is insufficient to cover: (i) Amounts necessary to comply with a court order, legal process, or levy described in 5 CFR part 1653; (ii) A beneficiary asset transfer; (iii) A required minimum distribution; (iv) A distribution of an account balance less than $200 described in 5 CFR 1650.23; or (v) Any other payment or transfer that the Board is required by law to make from the participant’s TSP account balance; (2) The amount of the forced transfer shall be equal to the amount of the insufficiency described in paragraph (c)(1) of this section, plus $1,000; except, however, that if the participant’s mutual fund window account balance is less than $25,000, the entire mutual fund window account balance shall be transferred to the TSP core funds; VerDate Sep<11>2014 16:01 Jan 25, 2022 Jkt 256001 (3) Forced transfers shall be liquidated from the participant’s mutual fund window account first from amounts held in the sweep money market fund; and then from amounts invested in mutual funds, beginning with the position with the highest balance; (4) Forced transfers from a participant’s mutual fund window account to the TSP core funds shall be invested according to the participant’s existing contribution allocation; and (5) The participant shall be responsible for any fees incurred as a result of the forced transfer. § 1601.53 Fees. (a) The Board will allocate a portion of the TSP’s administrative expenses to mutual fund users by charging an annual fee of $55.00. The amount of this fee will be redetermined once every three years by multiplying the average mutual fund window account balance by the TSP administrative expense ratio, as of the date of redetermination. (b) The fee described in paragraph (a) of this section is in addition to any mutual fund window account maintenance fees, trading fees, and fees and expenses associated with the specific mutual fund(s) in which the participant chooses to invest. [FR Doc. 2022–01312 Filed 1–25–22; 8:45 am] BILLING CODE 6760–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2022–0015; Project Identifier AD–2021–00832–R] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2020–23–05, which applies to certain Airbus Helicopters Model EC225LP helicopters. AD 2020–23–05 requires inspecting the control rod attachment yokes (yokes) of certain main rotor (M/ R) rotating swashplates (swashplates), establishing a life limit, a one-time inspection of stripped yokes, and applicable corrective actions. Since the FAA issued AD 2020–23–05, the FAA has determined that a revised SUMMARY: PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 3943 compliance time is necessary for swashplates that have accumulated less than seven years since the date of manufacture and that clarification is necessary for the condition that concludes with a dye penetrant inspection of the yoke. This proposed AD would continue to require the actions in AD 2020–23–05, with a revised compliance time for a certain inspection. 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 March 14, 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 Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; phone: (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https://www.airbus.com/helicopters/ technical-services/support.html. You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2022–0015; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the European Union Aviation Safety Agency (EASA) AD, any comments received, and other information. The street address for Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: 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: E:\FR\FM\26JAP1.SGM 26JAP1 3944 Federal Register / Vol. 87, No. 17 / Wednesday, January 26, 2022 / Proposed Rules 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–2022–0015; Project Identifier AD– 2021–00832–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. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this NPRM. Confidential Business Information khammond on DSKJM1Z7X2PROD with PROPOSALS 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 which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background The FAA issued AD 2020–23–05, Amendment 39–21321 (85 FR 73604, November 19, 2020), (AD 2020–23–05), for certain Airbus Helicopters Model EC225LP helicopters. AD 2020–23–05 requires inspecting the yokes of certain swashplates, establishing a life limit, a VerDate Sep<11>2014 16:01 Jan 25, 2022 Jkt 256001 one-time inspection of stripped yokes, and applicable corrective actions. AD 2020–23–05 was prompted by a crack in a swashplate yoke, which could result in failure of the yoke, loss of M/R control, and subsequent loss of control of the helicopter. EASA AD 2019–0074, dated March 28, 2019 (EASA AD 2019–0074), was issued by EASA, which is the Technical Agent for the Member States of the European Union, to supersede EASA AD 2017–0191R2, dated December 15, 2017 (EASA AD 2017–0191R2). EASA AD 2019–0074 followed Airbus Helicopters revising Emergency Alert Service Bulletin (EASB) No. 05A051, Revision 1, dated November 16, 2017, to Revision 2, dated February 26, 2019, to establish a life limit (also called a service life limit) of 12 years for the swashplate and add a reporting requirement if there is a crack or corrosion in a yoke. EASA advises that additional analysis determined that it is necessary to introduce the new life limit for the affected swashplates. Accordingly, EASA AD 2019–0074 retains the requirements of EASA AD 2017–0191R2 and adds a life limit and a reporting requirement. Actions Since AD 2020–23–05 Was Issued Since the FAA issued AD 2020–23– 05, the FAA has determined that a revised compliance time is necessary for swashplates that have accumulated less than seven years since the date of manufacture. This revised compliance time matches the compliance time specified in EASA AD 2019–0074. The FAA has also determined that paragraphs (g)(3)(i) and (g)(4)(iii)(A) of this AD need clarification regarding when it is necessary to do a dye penetrant inspection of the yoke. FAA’s Determination These helicopters have been approved by EASA and are approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with the European Union, EASA has notified the FAA about the unsafe condition described in its AD. The FAA is proposing this AD after evaluating all known relevant information and determining that the unsafe condition described previously is likely to exist or develop on other helicopters of the same type design. Related Service Information Under 1 CFR Part 51 The FAA reviewed one document that co-publishes two Airbus Helicopters EASB identification numbers: EASB No. 05A051 for Model EC225LP helicopters PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 and EASB No. 05A046 for non-FAA type-certificated Model EC725AP helicopters, each Revision 2 and dated February 26, 2019. This service information specifies inspections for swashplate part number (P/N) 332A31– 3074–00 and P/N 332A31–3074–01. This service information specifies procedures for a repetitive inspection of the yokes for a crack and a one-time inspection of the stripped yokes for corrosion and a crack. If in doubt about whether there is a crack, this service information specifies performing a nondestructive inspection. This service information also specifies touching up the swashplate with varnish if there is corrosion, removing any damage within allowable limits, and refinishing the yokes. If there is a crack in a yoke, this service information specifies replacing the swashplate. This service information also specifies a life limit of 12 years since the date of manufacture for the swashplates and reporting requirements if a crack or corrosion is discovered. The Director of the Federal Register approved EASB No. 05A051, Revision 2, dated February 26, 2019, for incorporation by reference as of December 24, 2020 (85 FR 73604, November 19, 2020). EASB No. 05A046, Revision 2, dated February 26, 2019, is not incorporated by reference in this AD. 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. Proposed AD Requirements in This NPRM This proposed AD would retain all of the requirements of AD 2020–23–05. This proposed AD would require inspecting the yokes of certain swashplates, compliance with the established life limit, and a one-time inspection of stripped yokes. This proposed AD would also include a revised compliance time for the initial visual inspection of the yokes on swashplates that have accumulated less than seven years since the date of manufacture; and clarification that dye penetrant inspection of the yoke is required before further flight if no cracks are detected visually during the visual inspection. This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between this Proposed AD and the EASA AD or Service Information.’’ E:\FR\FM\26JAP1.SGM 26JAP1 3945 Federal Register / Vol. 87, No. 17 / Wednesday, January 26, 2022 / Proposed Rules Differences Between This Proposed AD and the EASA AD or Service Information EASB No. 05A051, Revision 2, dated February 26, 2019 requires performing a non-destructive inspection only if there is doubt whether there is a crack. Instead, this proposed AD would require a visual inspection and if no cracks are visually detected, would require a non-destructive inspection. The EASA AD specifies instructions for reporting inspection results; this proposed AD would not. Costs of Compliance 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 proposed AD. The new requirements of this proposed AD add no additional economic burden. The FAA estimates that this AD, if adopted as proposed, would affect 28 ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Determination of the manufacture date of the swashplate. Inspecting the yokes ................................. 0.5 work-hour × $85 per hour = $43 ....... $0 $43 ......................... $1,204. 0.25 work-hour × $85 per hour = $21 per inspection cycle. 8 work-hours × $85 per hour = $680 ...... 0 0 $21 per inspection cycle. $680 ....................... $588 per inspection cycle. $19,040. 1 work-hour × $85 per hour = $85 .......... 0 $85 ......................... $2,380. Removing grease, stripping the yokes, and inspecting the stripped yokes. Creating a life limit record ........................ The FAA estimates the following costs to do any necessary on-condition actions that would be required based on Parts cost Cost on U.S. operators Action the results of any required actions. The FAA has no way of determining the Cost per product number of aircraft that might need these on-condition actions: ESTIMATED COSTS OF ON-CONDITION ACTIONS Labor cost Removing any corrosion or repairing damage within the allowable limit. Replacing the swashplate ............................................ Dye-penetrant inspection .............................................. 3 work-hours × $85 per hour = $255 ........................... $0 $255 6 work-hours × $85 per hour = $510 ........................... 6 work-hours × $85 per hour = $510 ........................... 85,661 50 86,171 560 Authority for This Rulemaking khammond on DSKJM1Z7X2PROD with PROPOSALS Cost per product Action 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 VerDate Sep<11>2014 16:01 Jan 25, 2022 Jkt 256001 have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Would not affect intrastate aviation in Alaska, and (3) Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Parts cost PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive 2020–23–05, Amendment 39–21321 (85 FR 73604, November 19, 2020); and ■ b. Adding the following new airworthiness directive: ■ ■ Airbus Helicopters: Docket No. FAA– 2022–0015; Project Identifier AD–2021– 00832–R. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) action by March 14, 2022. The Proposed Amendment (b) Affected ADs This AD replaces AD 2020–23–05, Amendment 39–21321 (85 FR 73604, November 19, 2020) (AD 2020–23–05). Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: (c) Applicability This AD applies to Airbus Helicopters Model EC225LP helicopters, certificated in any category, with a main rotor (M/R) rotating swashplate (swashplate) part number PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 E:\FR\FM\26JAP1.SGM 26JAP1 3946 Federal Register / Vol. 87, No. 17 / Wednesday, January 26, 2022 / Proposed Rules (P/N) 332A31–3074–00 or P/N 332A31– 3074–01 installed. (d) Subject Joint Aircraft Service Component (JASC) Code: 6230, Main Rotor Mast/Swashplate. (e) Unsafe Condition This AD was prompted by a crack in a swashplate control rod attachment yoke (yoke). The FAA is issuing this AD to detect and correct a crack in a yoke. The unsafe condition, if not addressed, could result in failure of the yoke, loss of M/R control, and subsequent loss of control of the helicopter. khammond on DSKJM1Z7X2PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Before further flight, review Appendix 4.A. of Airbus Helicopters Emergency Alert Service Bulletin No. 05A051, Revision 2, dated February 26, 2019 (EASB 05A051) to determine the date of manufacture of the swashplate. (1) If the swashplate has accumulated 12 or more years since the date of manufacture, remove from service the swashplate. (2) If the swashplate has accumulated less than 12 years since the date of manufacture, create a component history card or equivalent record indicating a life limit of 12 years since the date of manufacture. Thereafter, continue to record the life limit of the swashplate on its component history card or equivalent record and remove from service any swashplate before accumulating 12 years since the date of manufacture. (3) For each swashplate that has accumulated less than 7 years since the date of manufacture, within 15 hours time-inservice (TIS) or 7 days, whichever occurs first after the effective date of this AD, and thereafter at intervals not to exceed 15 hours TIS or 7 days, whichever occurs first, until the swashplate accumulates 7 years since the date of manufacture, visually inspect each yoke for a crack, paying particular attention to the areas shown in Details B, C, and D of Figure 1 of EASB 05A05. (i) If no cracks are visually detected, before further flight, perform a dye penetrant inspection of the yoke for a crack. (ii) If there is a crack on a yoke, before further flight, remove from service the swashplate. (4) For each swashplate that has accumulated 7 or more years, but less than 12 years, since the date of manufacture, within 100 hours TIS: (i) Remove the grease from areas (E), (F), (G), (H), (J), and (K) of each yoke as shown in Details B, C, and D of Figure 1 of EASB 05A051. Using a plastic spatula, strip areas (E), (F), (G), (H), (J), and (K) of each yoke as shown in Details B, C, and D of Figure 1 of EASB 05A051. Do not use a metal tool to strip any area of a yoke. (ii) Inspect areas (E), (F), (G), (H), (J) and (K) of each yoke as shown in Details B, C, and D of Figure 1 of EASB 05A051 for corrosion, pitting, and loss of material. (A) If there is any corrosion less than 0.0078 in. (0.2 mm), before further flight, VerDate Sep<11>2014 16:01 Jan 25, 2022 Jkt 256001 remove the corrosion and apply varnish (Vernelec 43022 or equivalent) to the surface of areas (E), (F), (G), (H), (J) and (K). (B) If there is any pitting or loss of material of less than 0.0078 in. (0.2 mm), before further flight, remove the damage by sanding with sandpaper 200/400 or 330. (C) If there is any corrosion, pitting, or loss of material of 0.0078 in. (0.2 mm) or greater, before further flight, remove from service the swashplate. (iii) Visually inspect each yoke for a crack, paying particular attention to the areas shown in Details B, C, and D of Figure 1 of EASB 05A051. (A) If there are no cracks, before further flight, perform a dye penetrant inspection of the yoke for a crack. (B) If there is a crack on a yoke, before further flight, remove from service the swashplate. (h) Credit for Previous Actions If you performed the actions in paragraph (g)(4) of this AD before the effective date of this AD using Airbus Helicopters Emergency Alert Service Bulletin No. 05A051, Revision 1, dated November 16, 2017, you have met the requirements of paragraph (g)(4) of this AD. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (j)(1) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (j) Related Information (1) For more information about this AD, contact 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) For service information identified in this AD, contact Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; phone: (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https:// www.airbus.com/helicopters/services/ technical-support.html. You may view this referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N– 321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110. (3) The subject of this AD is addressed in European Union Aviation Safety Agency (EASA) AD 2019–0074, dated March 28, 2019 (EASA AD 2019–0074). You may view the EASA AD on the internet at https:// PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 www.regulations.gov in Docket No. FAA– 2022–0015. Issued on January 20, 2022. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–01440 Filed 1–25–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–1169; Project Identifier AD–2021–01011–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 737–800 series airplanes. This proposed AD was prompted by the determination that insufficient sealing may allow water to enter the lower lobe electronic equipment (EE) bay through the main deck floor structure at the rigid cargo barrier (RCB), which could cause damage to EE bay line replacement units (LRUs) in the E5 rack. This proposed AD would require detailed inspections for the presence and condition of sealant at certain locations and applicable on-condition actions. This proposed AD would also require replacing the moisture barrier tape at a certain location, replacing the weather seal at a certain location, and installing seat track fillers. 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 March 14, 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 SUMMARY: E:\FR\FM\26JAP1.SGM 26JAP1

Agencies

[Federal Register Volume 87, Number 17 (Wednesday, January 26, 2022)]
[Proposed Rules]
[Pages 3943-3946]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-01440]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0015; Project Identifier AD-2021-00832-R]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2020-23-05, which applies to certain Airbus Helicopters Model EC225LP 
helicopters. AD 2020-23-05 requires inspecting the control rod 
attachment yokes (yokes) of certain main rotor (M/R) rotating 
swashplates (swashplates), establishing a life limit, a one-time 
inspection of stripped yokes, and applicable corrective actions. Since 
the FAA issued AD 2020-23-05, the FAA has determined that a revised 
compliance time is necessary for swashplates that have accumulated less 
than seven years since the date of manufacture and that clarification 
is necessary for the condition that concludes with a dye penetrant 
inspection of the yoke. This proposed AD would continue to require the 
actions in AD 2020-23-05, with a revised compliance time for a certain 
inspection. 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 March 14, 
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 Airbus 
Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; phone: 
(972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at https://www.airbus.com/helicopters/technical-services/support.html. You may 
view this service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort 
Worth, TX 76177. For information on the availability of this material 
at the FAA, call (817) 222-5110.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2022-0015; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this NPRM, the European 
Union Aviation Safety Agency (EASA) AD, any comments received, and 
other information. The street address for Docket Operations is listed 
above.

FOR FURTHER INFORMATION CONTACT: 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:

[[Page 3944]]

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-2022-0015; Project Identifier 
AD-2021-00832-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.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to 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 which is not specifically designated as CBI will 
be placed in the public docket for this rulemaking.

Background

    The FAA issued AD 2020-23-05, Amendment 39-21321 (85 FR 73604, 
November 19, 2020), (AD 2020-23-05), for certain Airbus Helicopters 
Model EC225LP helicopters. AD 2020-23-05 requires inspecting the yokes 
of certain swashplates, establishing a life limit, a one-time 
inspection of stripped yokes, and applicable corrective actions. AD 
2020-23-05 was prompted by a crack in a swashplate yoke, which could 
result in failure of the yoke, loss of M/R control, and subsequent loss 
of control of the helicopter.
    EASA AD 2019-0074, dated March 28, 2019 (EASA AD 2019-0074), was 
issued by EASA, which is the Technical Agent for the Member States of 
the European Union, to supersede EASA AD 2017-0191R2, dated December 
15, 2017 (EASA AD 2017-0191R2). EASA AD 2019-0074 followed Airbus 
Helicopters revising Emergency Alert Service Bulletin (EASB) No. 
05A051, Revision 1, dated November 16, 2017, to Revision 2, dated 
February 26, 2019, to establish a life limit (also called a service 
life limit) of 12 years for the swashplate and add a reporting 
requirement if there is a crack or corrosion in a yoke. EASA advises 
that additional analysis determined that it is necessary to introduce 
the new life limit for the affected swashplates. Accordingly, EASA AD 
2019-0074 retains the requirements of EASA AD 2017-0191R2 and adds a 
life limit and a reporting requirement.

Actions Since AD 2020-23-05 Was Issued

    Since the FAA issued AD 2020-23-05, the FAA has determined that a 
revised compliance time is necessary for swashplates that have 
accumulated less than seven years since the date of manufacture. This 
revised compliance time matches the compliance time specified in EASA 
AD 2019-0074. The FAA has also determined that paragraphs (g)(3)(i) and 
(g)(4)(iii)(A) of this AD need clarification regarding when it is 
necessary to do a dye penetrant inspection of the yoke.

FAA's Determination

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

Related Service Information Under 1 CFR Part 51

    The FAA reviewed one document that co-publishes two Airbus 
Helicopters EASB identification numbers: EASB No. 05A051 for Model 
EC225LP helicopters and EASB No. 05A046 for non-FAA type-certificated 
Model EC725AP helicopters, each Revision 2 and dated February 26, 2019. 
This service information specifies inspections for swashplate part 
number (P/N) 332A31-3074-00 and P/N 332A31-3074-01. This service 
information specifies procedures for a repetitive inspection of the 
yokes for a crack and a one-time inspection of the stripped yokes for 
corrosion and a crack. If in doubt about whether there is a crack, this 
service information specifies performing a nondestructive inspection. 
This service information also specifies touching up the swashplate with 
varnish if there is corrosion, removing any damage within allowable 
limits, and refinishing the yokes. If there is a crack in a yoke, this 
service information specifies replacing the swashplate. This service 
information also specifies a life limit of 12 years since the date of 
manufacture for the swashplates and reporting requirements if a crack 
or corrosion is discovered. The Director of the Federal Register 
approved EASB No. 05A051, Revision 2, dated February 26, 2019, for 
incorporation by reference as of December 24, 2020 (85 FR 73604, 
November 19, 2020). EASB No. 05A046, Revision 2, dated February 26, 
2019, is not incorporated by reference in this AD.
    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.

Proposed AD Requirements in This NPRM

    This proposed AD would retain all of the requirements of AD 2020-
23-05. This proposed AD would require inspecting the yokes of certain 
swashplates, compliance with the established life limit, and a one-time 
inspection of stripped yokes. This proposed AD would also include a 
revised compliance time for the initial visual inspection of the yokes 
on swashplates that have accumulated less than seven years since the 
date of manufacture; and clarification that dye penetrant inspection of 
the yoke is required before further flight if no cracks are detected 
visually during the visual inspection. This proposed AD would require 
accomplishing the actions specified in the service information 
described previously, except as discussed under ``Differences Between 
this Proposed AD and the EASA AD or Service Information.''

[[Page 3945]]

Differences Between This Proposed AD and the EASA AD or Service 
Information

    EASB No. 05A051, Revision 2, dated February 26, 2019 requires 
performing a non-destructive inspection only if there is doubt whether 
there is a crack. Instead, this proposed AD would require a visual 
inspection and if no cracks are visually detected, would require a non-
destructive inspection.
    The EASA AD specifies instructions for reporting inspection 
results; this proposed AD would not.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 28 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 proposed AD. The new requirements 
of this proposed AD add no additional economic burden.

                                                          Estimated Costs for Required Actions
--------------------------------------------------------------------------------------------------------------------------------------------------------
                Action                            Labor cost            Parts cost           Cost per product                Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Determination of the manufacture date   0.5 work-hour x $85 per hour            $0  $43..............................  $1,204.
 of the swashplate.                      = $43.
Inspecting the yokes..................  0.25 work-hour x $85 per hour            0  $21 per inspection cycle.........  $588 per inspection cycle.
                                         = $21 per inspection cycle.
Removing grease, stripping the yokes,   8 work-hours x $85 per hour =            0  $680.............................  $19,040.
 and inspecting the stripped yokes.      $680.
Creating a life limit record..........  1 work-hour x $85 per hour =             0  $85..............................  $2,380.
                                         $85.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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

                                     Estimated Costs of On-Condition Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Removing any corrosion or repairing damage   3 work-hours x $85 per hour = $255.              $0            $255
 within the allowable limit.
Replacing the swashplate...................  6 work-hours x $85 per hour = $510.          85,661          86,171
Dye-penetrant inspection...................  6 work-hours x $85 per hour = $510.              50             560
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive 2020-23-05, Amendment 39-21321 (85 
FR 73604, November 19, 2020); and
0
b. Adding the following new airworthiness directive:

    Airbus Helicopters: Docket No. FAA-2022-0015; Project Identifier 
AD-2021-00832-R.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) action by March 14, 2022.

(b) Affected ADs

    This AD replaces AD 2020-23-05, Amendment 39-21321 (85 FR 73604, 
November 19, 2020) (AD 2020-23-05).

(c) Applicability

    This AD applies to Airbus Helicopters Model EC225LP helicopters, 
certificated in any category, with a main rotor (M/R) rotating 
swashplate (swashplate) part number

[[Page 3946]]

(P/N) 332A31-3074-00 or P/N 332A31-3074-01 installed.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6230, Main Rotor 
Mast/Swashplate.

(e) Unsafe Condition

    This AD was prompted by a crack in a swashplate control rod 
attachment yoke (yoke). The FAA is issuing this AD to detect and 
correct a crack in a yoke. The unsafe condition, if not addressed, 
could result in failure of the yoke, loss of M/R control, and 
subsequent loss of control of the helicopter.

(f) Compliance

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

(g) Required Actions

    Before further flight, review Appendix 4.A. of Airbus 
Helicopters Emergency Alert Service Bulletin No. 05A051, Revision 2, 
dated February 26, 2019 (EASB 05A051) to determine the date of 
manufacture of the swashplate.
    (1) If the swashplate has accumulated 12 or more years since the 
date of manufacture, remove from service the swashplate.
    (2) If the swashplate has accumulated less than 12 years since 
the date of manufacture, create a component history card or 
equivalent record indicating a life limit of 12 years since the date 
of manufacture. Thereafter, continue to record the life limit of the 
swashplate on its component history card or equivalent record and 
remove from service any swashplate before accumulating 12 years 
since the date of manufacture.
    (3) For each swashplate that has accumulated less than 7 years 
since the date of manufacture, within 15 hours time-in-service (TIS) 
or 7 days, whichever occurs first after the effective date of this 
AD, and thereafter at intervals not to exceed 15 hours TIS or 7 
days, whichever occurs first, until the swashplate accumulates 7 
years since the date of manufacture, visually inspect each yoke for 
a crack, paying particular attention to the areas shown in Details 
B, C, and D of Figure 1 of EASB 05A05.
    (i) If no cracks are visually detected, before further flight, 
perform a dye penetrant inspection of the yoke for a crack.
    (ii) If there is a crack on a yoke, before further flight, 
remove from service the swashplate.
    (4) For each swashplate that has accumulated 7 or more years, 
but less than 12 years, since the date of manufacture, within 100 
hours TIS:
    (i) Remove the grease from areas (E), (F), (G), (H), (J), and 
(K) of each yoke as shown in Details B, C, and D of Figure 1 of EASB 
05A051. Using a plastic spatula, strip areas (E), (F), (G), (H), 
(J), and (K) of each yoke as shown in Details B, C, and D of Figure 
1 of EASB 05A051. Do not use a metal tool to strip any area of a 
yoke.
    (ii) Inspect areas (E), (F), (G), (H), (J) and (K) of each yoke 
as shown in Details B, C, and D of Figure 1 of EASB 05A051 for 
corrosion, pitting, and loss of material.
    (A) If there is any corrosion less than 0.0078 in. (0.2 mm), 
before further flight, remove the corrosion and apply varnish 
(Vernelec 43022 or equivalent) to the surface of areas (E), (F), 
(G), (H), (J) and (K).
    (B) If there is any pitting or loss of material of less than 
0.0078 in. (0.2 mm), before further flight, remove the damage by 
sanding with sandpaper 200/400 or 330.
    (C) If there is any corrosion, pitting, or loss of material of 
0.0078 in. (0.2 mm) or greater, before further flight, remove from 
service the swashplate.
    (iii) Visually inspect each yoke for a crack, paying particular 
attention to the areas shown in Details B, C, and D of Figure 1 of 
EASB 05A051.
    (A) If there are no cracks, before further flight, perform a dye 
penetrant inspection of the yoke for a crack.
    (B) If there is a crack on a yoke, before further flight, remove 
from service the swashplate.

(h) Credit for Previous Actions

    If you performed the actions in paragraph (g)(4) of this AD 
before the effective date of this AD using Airbus Helicopters 
Emergency Alert Service Bulletin No. 05A051, Revision 1, dated 
November 16, 2017, you have met the requirements of paragraph (g)(4) 
of this AD.

(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; phone: (202) 267-9167; email: [email protected].
    (2) For service information identified in this AD, contact 
Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; 
phone: (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at 
https://www.airbus.com/helicopters/services/technical-support.html. 
You may view this referenced service information at the FAA, Office 
of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., 
Room 6N-321, Fort Worth, TX 76177. For information on the 
availability of this material at the FAA, call (817) 222-5110.
    (3) The subject of this AD is addressed in European Union 
Aviation Safety Agency (EASA) AD 2019-0074, dated March 28, 2019 
(EASA AD 2019-0074). You may view the EASA AD on the internet at 
https://www.regulations.gov in Docket No. FAA-2022-0015.

    Issued on January 20, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2022-01440 Filed 1-25-22; 8:45 am]
BILLING CODE 4910-13-P