Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France), 94623-94626 [2024-27814]

Download as PDF Federal Register / Vol. 89, No. 230 / Friday, November 29, 2024 / Proposed Rules khammond on DSK9W7S144PROD with PROPOSALS Requirements Specific to the Stairway (h) The stairway must have essentially straight route segments with a landing at each significant change in segment direction. (i) The stairway must have essentially rectangular treads. (j) The stairway must accommodate the carriage of an incapacitated occupant from the lower deck to the main deck. The crewmember procedures for such carriage must be established and included in the AFM. (k) In normal operation, the general illumination level must not be less than 0.05 foot-candles when measured along the center lines of each tread and landing. (l) The stairway must have a handrail on at least one side to allow occupants to steady themselves during moderate turbulence in flight. The handrail(s) must be constructed so there is no obstruction on them that will cause the user to release his/her grip or hinder the continuous movement of the hands along the handrail. The design must accommodate the stature of a 5th percentile female and a 95th percentile male. (m) The public address system must be intelligible in the stairway during all flight phases. (n) ‘‘Return to seat’’ signs must be installed and visible in the stairway both going up and down and at the stairway entrances. (o) Appropriate placards must be located outside each main deck entrance to the lower lobe access stairs to indicate: (1) The maximum number of occupants allowed in flight. (2) Occupancy during flight is restricted to crewmembers that are trained in the procedures for the lower lobe compartments. (3) Occupancy is prohibited during taxi, take-off, and landing. (4) The stowage of cargo or passenger baggage is not allowed in the stair enclosure. This placard is also required at each stair landing. (p) Passengers must be prevented from entering the stairway in the event of an emergency or when no flight attendant is present. (q) The means required by condition (p) must be capable of being quickly opened from inside the stairway, even when crowding occurs at the passenger cabin side of the stair entrance. (r) A means must be in place to preclude anyone from being trapped inside the stairway. If a locking mechanism is installed, it must be capable of being unlocked from either side without the aid of tools. VerDate Sep<11>2014 16:47 Nov 27, 2024 Jkt 265001 (s) There must be appropriate placards conspicuously located as follows: (1) Inside the stairs on or near each exit to the main deck defining the operating instructions for the door. (2) On the cabin side, when the door is closed, no higher than 4 feet from the floor, indicating that the door is not an emergency exit. For the placards required by condition (s) the following applies: (3) Placards must be readable from a distance of 30 inches under emergency lighting conditions. (4) Placards must be illuminated to at least 160 micro-lamberts under emergency lighting conditions. (t) There shall be a means (visible and audible) to notify an occupant of the stairway of the need to don supplemental oxygen equipment in the event of a decompression. The aural and visual alerts must activate before the cabin pressure altitude exceeds 15,000 feet. (u) A means must be available, in the event of failure of the airplane’s main power system, or of the normal stairway lighting system, for emergency illumination to be automatically provided in the stairway. (1) This emergency illumination must be independent of the main lighting system. (2) The sources of general illumination may be common to both the emergency and the main lighting systems if the power supply to the emergency lighting system is independent of the power supply to the main lighting system. (3) Emergency illumination must be provided so that, when measured along the centerlines of each tread and landing, the illumination is not less than 0.05 foot-candles. Issued in Kansas City, Missouri, on signature November 18, 2024. Patrick R. Mullen, Manager, Technical Policy Branch, Policy and Standards Division, Aircraft Certification Service. [FR Doc. 2024–27786 Filed 11–27–24; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 94623 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–2542; Project Identifier MCAI–2023–00611–R] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2008–10–01 and AD 2010–05–51, which apply to certain Eurocopter France (now Airbus Helicopters) Model EC120B helicopters. AD 2008–10–01 requires replacing certain part-numbered and serial-numbered spherical thrust bearings. AD 2010–05–51 requires repetitively inspecting the main rotor (M/R) head rotor hub (rotor hub) and, depending on the results, taking corrective action. Since the FAA issued those ADs, the manufacturer revised the airworthiness limitations section (ALS) to incorporate various airworthiness limitations, tasks, and associated thresholds and intervals that were previously contained in service bulletins, as well as incorporate a new task. This proposed AD would require revising the ALS of the existing maintenance manual (MM) or instructions for continued airworthiness (ICAs) and the existing approved maintenance or inspection program, as applicable, as specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this NPRM by January 13, 2025. 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 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. SUMMARY: E:\FR\FM\29NOP1.SGM 29NOP1 94624 Federal Register / Vol. 89, No. 230 / Friday, November 29, 2024 / Proposed Rules AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2024–2542; 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 EASA AD, any comments received, and other information. The street address for Docket Operations is listed above. Material Incorporated by Reference: • For EASA material identified in this proposed AD, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email: ADs@easa.europa.eu; website: easa.europa.eu. You may find the EASA material on the EASA website at ad.easa.europa.eu. • You may view this material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110. The EASA material is also available at regulations.gov under Docket No. FAA–2024–2542. FOR FURTHER INFORMATION CONTACT: Hye Yoon Jang, Aviation Safety Engineer, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (206) 231– 3758; email: hye.yoon.jang@faa.gov. SUPPLEMENTARY INFORMATION: khammond on DSK9W7S144PROD with PROPOSALS 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–2024–2542; Project Identifier MCAI–2023–00611–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 the 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 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 VerDate Sep<11>2014 16:47 Nov 27, 2024 Jkt 265001 (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 Hye Yoon Jang, Aviation Safety Engineer, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (206) 231–3758; email: hye.yoon.jang@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 2008–10–01, Amendment 39–15507 (73 FR 24856, May 6, 2008) (AD 2008–10–01), for Eurocopter France (now Airbus Helicopters) Model EC120B helicopters with spherical thrust bearings part number (P/N) 7050A3622036 having serial number LK0130, LK0142, LK0155, or LK0158, installed. AD 2008–10–01 was prompted by Direction generale de l’aviation civile France (DGAC), which was the aviation authority for France before the European Aviation Safety Agency, AD F–2006–040, dated February 15, 2006 (DGAC France AD F– 2006–040), to address a batch of nonconforming spherical thrust bearings. AD 2008–10–01 requires removing any identified spherical thrust bearing and installing an airworthy spherical thrust bearing. The FAA issued AD 2008–10– 01 to prevent failure of a spherical thrust bearing during flight, which, if not addressed, could cause the M/R system to separate from the helicopter, which would be catastrophic. The FAA issued AD 2010–05–51, Amendment 39–16265 (75 FR 22510, April 29, 2010) (AD 2010–05–51), for Eurocopter France (now Airbus Helicopters) Model EC120B helicopters with a rotor hub P/N C622A1002103, C622A1002104, or C622A1002105, installed. AD 2010–05–51 was prompted by European Aviation Safety Agency, which was the aviation authority for France after the DGAC and before the European Union Aviation Safety Agency, Emergency AD 2010– 0026–E, dated February 19, 2010 (European Aviation Safety Agency Emergency AD 2010–0026–E), to PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 address failure of a rotor hub attachment area in one of the three drag damper fittings. AD 2010–05–51 requires repetitively inspecting the rotor hub, and depending on the results, sanding the area to inspect for cracks, and replacing the rotor hub if cracks are found. The FAA issued AD 2010–05–51 to prevent failure of a rotor hub, excessive vibrations, loss of an M/R blade, and subsequent loss of control of the helicopter. Actions Since AD 2008–10–01 and AD 2010–05–51 Were Issued Since the FAA issued AD 2008–10–01 and AD 2010–05–51, EASA, which is the Technical Agent for the Member States of the European Union (including France), has issued EASA AD 2023– 0083, dated April 19, 2023 (EASA AD 2023–0083), to supersede DGAC France AD F–2006–040 and European Aviation Safety Agency Emergency AD 2010– 0026–E. EASA advises that airworthiness limitations instructions are identified as mandatory for continued airworthiness and that Revision 3 of AH [Airbus Helicopters] EC 120 B Chapter 4 ALS, dated July 18, 2022, was issued to introduce new, or more restrictive tasks, or both, including incorporation of the requirements of DGAC France AD F–2006–040 and EASA Emergency AD 2010–0026–E. Consequently, EASA AD 2023–0083 retains the requirements of DGAC France AD F–2006–040 and European Aviation Safety Agency Emergency AD 2010–0026–E and requires accomplishing the actions specified in, and the incorporation into the Aircraft Maintenance Programme (AMP) of, AH [Airbus Helicopters] EC 120 B Chapter 4 ALS, Revision 3, dated July 18, 2022. According to EASA, failure to accomplish these instructions could result in an unsafe condition. You may examine EASA AD 2023–0083 in the AD docket at regulations.gov under Docket No. FAA–2024–2542. Lastly, since the FAA issued AD 2008–10–01 and AD 2010–05–51, Eurocopter France changed its name to Airbus Helicopters; this NPRM reflects that change. Material Incorporated by Reference Under 1 CFR Part 51 The FAA reviewed EASA AD 2023– 0083, which requires replacing components before exceeding their life limits and accomplishing all applicable maintenance tasks within thresholds and intervals specified in the ALS as defined within. Depending on the results of the maintenance tasks, EASA AD 2023–0083 requires accomplishing corrective action(s) or contacting AH E:\FR\FM\29NOP1.SGM 29NOP1 Federal Register / Vol. 89, No. 230 / Friday, November 29, 2024 / Proposed Rules [Airbus Helicopters] for approved instructions and accomplishing those instructions. Additionally, EASA AD 2023–0083 requires revising the AMP by incorporating the limitations, tasks, and associated thresholds and intervals described in the specified ALS, as applicable. Revising the AMP constitutes terminating action for the requirement to record accomplishment of the actions of replacing components before exceeding their life limits and accomplishing maintenance tasks within thresholds and intervals specified in the applicable ALS as required by EASA AD 2023–0083 for demonstration of AD compliance on a continued basis. 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. FAA’s Determination These products have been approved by the aviation authority of another country and are approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with this State of Design Authority, it has notified the FAA of the unsafe condition described in its AD referenced above. The FAA is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design. khammond on DSK9W7S144PROD with PROPOSALS Proposed AD Requirements in This NPRM This proposed AD would require revising the ALS of the existing MM or ICAs and the existing approved maintenance or inspection program, as applicable, by incorporating new or more restrictive actions and associated thresholds and intervals, including any life limits, specified in EASA AD 2023– 0083, described previously, as incorporated by reference, except for any differences identified as exceptions in the regulatory text of this proposed AD and except as discussed under ‘‘Differences Between this Proposed AD and the EASA AD.’’ Explanation of Required Compliance Information In the FAA’s ongoing efforts to improve the efficiency of the AD process, the FAA developed a process to use some civil aviation authority (CAA) ADs as the primary source of information for compliance with requirements for corresponding FAA ADs. The FAA has been coordinating this process with manufacturers and VerDate Sep<11>2014 16:47 Nov 27, 2024 Jkt 265001 CAAs. As a result, the FAA proposes to incorporate EASA AD 2023–0083 by reference in the FAA final rule. Using common terms that are the same as the heading of a particular section in EASA AD 2023–0083 does not mean that operators need comply only with that section. For example, where the AD requirement refers to ‘‘all required actions and compliance times,’’ compliance with this AD requirement is not limited to the section titled ‘‘Required Action(s) and Compliance Time(s)’’ in EASA AD 2023–0083. Material referenced in EASA AD 2023– 0083 for compliance will be available at regulations.gov under Docket No. FAA– 2024–2542 after the FAA final rule is published. Differences Between This Proposed AD and the EASA AD EASA AD 2023–0083 requires, as individual tasks, replacing certain components before exceeding applicable life limits, accomplishing certain maintenance tasks within thresholds and intervals as specified in the ALS, as defined within, and depending on the results, accomplishing corrective action(s), whereas this proposed AD would not. EASA AD 2023–0083 also requires revising the approved AMP to incorporate the limitations, tasks, and associated thresholds and intervals described in that ALS within 12 months, whereas this proposed AD would require revising the ALS of the existing MM or ICAs and the existing approved maintenance or inspection program, as applicable, by incorporating the limitations, tasks, and associated thresholds and intervals described in that ALS within 30 days, and clarifies that if the initial instance of an incorporated limitation or threshold therein is reached before 30 days after the effective date of the final rule of this proposed AD, you still have up to 30 days after the effective date of the final rule of this proposed AD to accomplish the corresponding task. Lastly, the material referenced in ‘‘the ALS,’’ as defined in EASA AD 2023– 0083, specifies contacting Airbus [Helicopters] if there is a crack in the rotor hub, whereas this proposed AD would not require contacting Airbus Helicopters. Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 65 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. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 94625 Revising the ALS of the existing MM or ICAs and the existing approved maintenance or inspection program, as applicable, would take 1 work-hour, at an estimated cost of $85 per helicopter and $5,525 for the U.S. fleet. 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 that the 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: E:\FR\FM\29NOP1.SGM 29NOP1 94626 Federal Register / Vol. 89, No. 230 / Friday, November 29, 2024 / Proposed Rules 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 2008–10–01, Amendment 39–15507 (73 FR 24856, May 6, 2008), and AD 2010– 05–51, Amendment 39–16265 (75 FR 22510, April 29, 2010); and ■ b. Adding the following new airworthiness directive: ■ ■ Airbus Helicopters (Type Certificate previously held by Eurocopter France): Docket No. FAA–2024–2542; Project Identifier MCAI–2023–00611–R. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by January 13, 2025. (b) Affected ADs This AD replaces AD 2008–10–01, Amendment 39–15507 (73 FR 24856, May 6, 2008), and AD 2010–05–51, Amendment 39– 16265 (75 FR 22510, April 29, 2010). (c) Applicability This AD applies to Airbus Helicopters (type certificate previously held by Eurocopter France) Model EC120B helicopters, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code: 6220, Main Rotor Head. (e) Unsafe Condition This AD was prompted by new and more restrictive airworthiness limitations. The FAA is issuing this AD to prevent failure of certain parts, which if not addressed, could result in subsequent loss of control of the helicopter. khammond on DSK9W7S144PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Except as specified in paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency AD 2023–0083, dated April 19, 2023 (EASA AD 2023–0083). (h) Exceptions to EASA AD 2023–0083 (1) Where EASA AD 2023–0083 refers to its effective date, this AD requires using the effective date of this AD. (2) This AD does not adopt paragraphs (1), (2), (4), and (5) of EASA AD 2023–0083. (3) Where paragraph (3) of EASA AD 2023– 0083 specifies ‘‘Within 12 months after the effective date of this AD, revise the approved AMP,’’ this AD requires replacing that text with ‘‘Within 30 days after the effective date of this AD, revise the airworthiness limitations section of the existing VerDate Sep<11>2014 16:47 Nov 27, 2024 Jkt 265001 maintenance manual or instructions for continued airworthiness and the existing approved maintenance or inspection program, as applicable.’’ (4) Regarding ‘‘the ALS’’ as defined in EASA AD 2023–0083; where the material referenced in ‘‘the ALS’’ in paragraph (3) of EASA AD 2023–0083 specifies contacting Airbus [Helicopters] if there is a crack in the (main rotor head rotor) hub body, this AD does not require contacting Airbus Helicopters. (5) The initial compliance time for doing the tasks specified in paragraph (3) of EASA AD 2023–0083 is on or before the applicable ‘‘limitations’’ and ‘‘associated thresholds’’ as incorporated by the requirements of paragraph (3) of EASA AD 2023–0083 or within 30 days after the effective date of this AD, whichever occurs later. (6) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2023–0083. (i) Provisions for Alternative Actions and Intervals After the action required by paragraph (g) of this AD has been done, no alternative actions and associated thresholds and intervals, including life limits, are allowed unless they are approved as specified in the provisions of the ‘‘Ref. Publications’’ section of EASA AD 2023–0083. (j) 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 (k) of this AD. If sending information directly to the manager of the International Validation Branch, mail it to the address identified in paragraph (k) of this AD or email to: AMOC@faa.gov. If mailing information, also submit information by email. (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. (k) Additional Information For more information about this AD, contact Hye Yoon Jang, Aviation Safety Engineer, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (206) 231–3758; email: hye.yoon.jang@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2023–0083, dated April 19, 2023. (ii) [Reserved] PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 (3) For EASA material identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email: ADs@easa.europa.eu; website: easa.europa.eu. You may find the EASA material on the EASA website at ad.easa.europa.eu. (4) 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. (5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ ibr-locations or email fr.inspection@nara.gov. Issued on November 21, 2024. Victor Wicklund, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024–27814 Filed 11–27–24; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–2541; Project Identifier MCAI–2023–00006–R] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Helicopters Model SA341G and SA342J helicopters. This proposed AD was prompted by a report of a pilot collective pitch stick handle grip that broke when pulled. This proposed AD would require replacing certain pilot collective pitch stick handle grips and prohibit installing those pilot collective pitch stick handle grips. These actions are specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this NPRM by January 13, 2025. 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 regulations.gov. Follow the instructions for submitting comments. SUMMARY: E:\FR\FM\29NOP1.SGM 29NOP1

Agencies

[Federal Register Volume 89, Number 230 (Friday, November 29, 2024)]
[Proposed Rules]
[Pages 94623-94626]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-27814]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-2542; Project Identifier MCAI-2023-00611-R]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Type Certificate 
Previously Held by Eurocopter France)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2008-10-01 and AD 2010-05-51, which apply to certain Eurocopter France 
(now Airbus Helicopters) Model EC120B helicopters. AD 2008-10-01 
requires replacing certain part-numbered and serial-numbered spherical 
thrust bearings. AD 2010-05-51 requires repetitively inspecting the 
main rotor (M/R) head rotor hub (rotor hub) and, depending on the 
results, taking corrective action. Since the FAA issued those ADs, the 
manufacturer revised the airworthiness limitations section (ALS) to 
incorporate various airworthiness limitations, tasks, and associated 
thresholds and intervals that were previously contained in service 
bulletins, as well as incorporate a new task. This proposed AD would 
require revising the ALS of the existing maintenance manual (MM) or 
instructions for continued airworthiness (ICAs) and the existing 
approved maintenance or inspection program, as applicable, as specified 
in a European Union Aviation Safety Agency (EASA) AD, which is proposed 
for incorporation by reference. The FAA is proposing this AD to address 
the unsafe condition on these products.

DATES: The FAA must receive comments on this NPRM by January 13, 2025.

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 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.

[[Page 94624]]

    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2024-2542; 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 EASA AD, any comments received, and 
other information. The street address for Docket Operations is listed 
above.
    Material Incorporated by Reference:
     For EASA material identified in this proposed AD, contact 
EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 
8999 000; email: [email protected]; website: easa.europa.eu. You may 
find the EASA material on the EASA website at ad.easa.europa.eu.
     You may view this material at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N-
321, Fort Worth, TX 76177. For information on the availability of this 
material at the FAA, call (817) 222-5110. The EASA material is also 
available at regulations.gov under Docket No. FAA-2024-2542.

FOR FURTHER INFORMATION CONTACT: Hye Yoon Jang, Aviation Safety 
Engineer, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: 
(206) 231-3758; 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-2024-2542; Project Identifier 
MCAI-2023-00611-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 
the 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 
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 Hye 
Yoon Jang, Aviation Safety Engineer, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: (206) 231-3758; 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 2008-10-01, Amendment 39-15507 (73 FR 24856, May 
6, 2008) (AD 2008-10-01), for Eurocopter France (now Airbus 
Helicopters) Model EC120B helicopters with spherical thrust bearings 
part number (P/N) 7050A3622036 having serial number LK0130, LK0142, 
LK0155, or LK0158, installed. AD 2008-10-01 was prompted by Direction 
generale de l'aviation civile France (DGAC), which was the aviation 
authority for France before the European Aviation Safety Agency, AD F-
2006-040, dated February 15, 2006 (DGAC France AD F-2006-040), to 
address a batch of non-conforming spherical thrust bearings. AD 2008-
10-01 requires removing any identified spherical thrust bearing and 
installing an airworthy spherical thrust bearing. The FAA issued AD 
2008-10-01 to prevent failure of a spherical thrust bearing during 
flight, which, if not addressed, could cause the M/R system to separate 
from the helicopter, which would be catastrophic.
    The FAA issued AD 2010-05-51, Amendment 39-16265 (75 FR 22510, 
April 29, 2010) (AD 2010-05-51), for Eurocopter France (now Airbus 
Helicopters) Model EC120B helicopters with a rotor hub P/N 
C622A1002103, C622A1002104, or C622A1002105, installed. AD 2010-05-51 
was prompted by European Aviation Safety Agency, which was the aviation 
authority for France after the DGAC and before the European Union 
Aviation Safety Agency, Emergency AD 2010-0026-E, dated February 19, 
2010 (European Aviation Safety Agency Emergency AD 2010-0026-E), to 
address failure of a rotor hub attachment area in one of the three drag 
damper fittings. AD 2010-05-51 requires repetitively inspecting the 
rotor hub, and depending on the results, sanding the area to inspect 
for cracks, and replacing the rotor hub if cracks are found. The FAA 
issued AD 2010-05-51 to prevent failure of a rotor hub, excessive 
vibrations, loss of an M/R blade, and subsequent loss of control of the 
helicopter.

Actions Since AD 2008-10-01 and AD 2010-05-51 Were Issued

    Since the FAA issued AD 2008-10-01 and AD 2010-05-51, EASA, which 
is the Technical Agent for the Member States of the European Union 
(including France), has issued EASA AD 2023-0083, dated April 19, 2023 
(EASA AD 2023-0083), to supersede DGAC France AD F-2006-040 and 
European Aviation Safety Agency Emergency AD 2010-0026-E. EASA advises 
that airworthiness limitations instructions are identified as mandatory 
for continued airworthiness and that Revision 3 of AH [Airbus 
Helicopters] EC 120 B Chapter 4 ALS, dated July 18, 2022, was issued to 
introduce new, or more restrictive tasks, or both, including 
incorporation of the requirements of DGAC France AD F-2006-040 and EASA 
Emergency AD 2010-0026-E. Consequently, EASA AD 2023-0083 retains the 
requirements of DGAC France AD F-2006-040 and European Aviation Safety 
Agency Emergency AD 2010-0026-E and requires accomplishing the actions 
specified in, and the incorporation into the Aircraft Maintenance 
Programme (AMP) of, AH [Airbus Helicopters] EC 120 B Chapter 4 ALS, 
Revision 3, dated July 18, 2022. According to EASA, failure to 
accomplish these instructions could result in an unsafe condition. You 
may examine EASA AD 2023-0083 in the AD docket at regulations.gov under 
Docket No. FAA-2024-2542.
    Lastly, since the FAA issued AD 2008-10-01 and AD 2010-05-51, 
Eurocopter France changed its name to Airbus Helicopters; this NPRM 
reflects that change.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed EASA AD 2023-0083, which requires replacing 
components before exceeding their life limits and accomplishing all 
applicable maintenance tasks within thresholds and intervals specified 
in the ALS as defined within. Depending on the results of the 
maintenance tasks, EASA AD 2023-0083 requires accomplishing corrective 
action(s) or contacting AH

[[Page 94625]]

[Airbus Helicopters] for approved instructions and accomplishing those 
instructions.
    Additionally, EASA AD 2023-0083 requires revising the AMP by 
incorporating the limitations, tasks, and associated thresholds and 
intervals described in the specified ALS, as applicable. Revising the 
AMP constitutes terminating action for the requirement to record 
accomplishment of the actions of replacing components before exceeding 
their life limits and accomplishing maintenance tasks within thresholds 
and intervals specified in the applicable ALS as required by EASA AD 
2023-0083 for demonstration of AD compliance on a continued basis.
    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.

FAA's Determination

    These products have been approved by the aviation authority of 
another country and are approved for operation in the United States. 
Pursuant to the FAA's bilateral agreement with this State of Design 
Authority, it has notified the FAA of the unsafe condition described in 
its AD referenced above. The FAA is issuing this NPRM after determining 
that the unsafe condition described previously is likely to exist or 
develop on other products of the same type design.

Proposed AD Requirements in This NPRM

    This proposed AD would require revising the ALS of the existing MM 
or ICAs and the existing approved maintenance or inspection program, as 
applicable, by incorporating new or more restrictive actions and 
associated thresholds and intervals, including any life limits, 
specified in EASA AD 2023-0083, described previously, as incorporated 
by reference, except for any differences identified as exceptions in 
the regulatory text of this proposed AD and except as discussed under 
``Differences Between this Proposed AD and the EASA AD.''

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA developed a process to use some civil aviation 
authority (CAA) ADs as the primary source of information for compliance 
with requirements for corresponding FAA ADs. The FAA has been 
coordinating this process with manufacturers and CAAs. As a result, the 
FAA proposes to incorporate EASA AD 2023-0083 by reference in the FAA 
final rule. Using common terms that are the same as the heading of a 
particular section in EASA AD 2023-0083 does not mean that operators 
need comply only with that section. For example, where the AD 
requirement refers to ``all required actions and compliance times,'' 
compliance with this AD requirement is not limited to the section 
titled ``Required Action(s) and Compliance Time(s)'' in EASA AD 2023-
0083. Material referenced in EASA AD 2023-0083 for compliance will be 
available at regulations.gov under Docket No. FAA-2024-2542 after the 
FAA final rule is published.

Differences Between This Proposed AD and the EASA AD

    EASA AD 2023-0083 requires, as individual tasks, replacing certain 
components before exceeding applicable life limits, accomplishing 
certain maintenance tasks within thresholds and intervals as specified 
in the ALS, as defined within, and depending on the results, 
accomplishing corrective action(s), whereas this proposed AD would not. 
EASA AD 2023-0083 also requires revising the approved AMP to 
incorporate the limitations, tasks, and associated thresholds and 
intervals described in that ALS within 12 months, whereas this proposed 
AD would require revising the ALS of the existing MM or ICAs and the 
existing approved maintenance or inspection program, as applicable, by 
incorporating the limitations, tasks, and associated thresholds and 
intervals described in that ALS within 30 days, and clarifies that if 
the initial instance of an incorporated limitation or threshold therein 
is reached before 30 days after the effective date of the final rule of 
this proposed AD, you still have up to 30 days after the effective date 
of the final rule of this proposed AD to accomplish the corresponding 
task.
    Lastly, the material referenced in ``the ALS,'' as defined in EASA 
AD 2023-0083, specifies contacting Airbus [Helicopters] if there is a 
crack in the rotor hub, whereas this proposed AD would not require 
contacting Airbus Helicopters.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 65 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.
    Revising the ALS of the existing MM or ICAs and the existing 
approved maintenance or inspection program, as applicable, would take 1 
work-hour, at an estimated cost of $85 per helicopter and $5,525 for 
the U.S. fleet.

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 that the 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:

[[Page 94626]]

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 2008-10-01, Amendment 39-15507 (73 
FR 24856, May 6, 2008), and AD 2010-05-51, Amendment 39-16265 (75 FR 
22510, April 29, 2010); and
0
b. Adding the following new airworthiness directive:

Airbus Helicopters (Type Certificate previously held by Eurocopter 
France): Docket No. FAA-2024-2542; Project Identifier MCAI-2023-
00611-R.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by January 13, 2025.

(b) Affected ADs

    This AD replaces AD 2008-10-01, Amendment 39-15507 (73 FR 24856, 
May 6, 2008), and AD 2010-05-51, Amendment 39-16265 (75 FR 22510, 
April 29, 2010).

(c) Applicability

    This AD applies to Airbus Helicopters (type certificate 
previously held by Eurocopter France) Model EC120B helicopters, 
certificated in any category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by new and more restrictive airworthiness 
limitations. The FAA is issuing this AD to prevent failure of 
certain parts, which if not addressed, could result in subsequent 
loss of control of the helicopter.

(f) Compliance

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

(g) Required Actions

    Except as specified in paragraphs (h) and (i) of this AD: Comply 
with all required actions and compliance times specified in, and in 
accordance with, European Union Aviation Safety Agency AD 2023-0083, 
dated April 19, 2023 (EASA AD 2023-0083).
    (h) Exceptions to EASA AD 2023-0083
    (1) Where EASA AD 2023-0083 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) This AD does not adopt paragraphs (1), (2), (4), and (5) of 
EASA AD 2023-0083.
    (3) Where paragraph (3) of EASA AD 2023-0083 specifies ``Within 
12 months after the effective date of this AD, revise the approved 
AMP,'' this AD requires replacing that text with ``Within 30 days 
after the effective date of this AD, revise the airworthiness 
limitations section of the existing maintenance manual or 
instructions for continued airworthiness and the existing approved 
maintenance or inspection program, as applicable.''
    (4) Regarding ``the ALS'' as defined in EASA AD 2023-0083; where 
the material referenced in ``the ALS'' in paragraph (3) of EASA AD 
2023-0083 specifies contacting Airbus [Helicopters] if there is a 
crack in the (main rotor head rotor) hub body, this AD does not 
require contacting Airbus Helicopters.
    (5) The initial compliance time for doing the tasks specified in 
paragraph (3) of EASA AD 2023-0083 is on or before the applicable 
``limitations'' and ``associated thresholds'' as incorporated by the 
requirements of paragraph (3) of EASA AD 2023-0083 or within 30 days 
after the effective date of this AD, whichever occurs later.
    (6) This AD does not adopt the ``Remarks'' section of EASA AD 
2023-0083.

(i) Provisions for Alternative Actions and Intervals

    After the action required by paragraph (g) of this AD has been 
done, no alternative actions and associated thresholds and 
intervals, including life limits, are allowed unless they are 
approved as specified in the provisions of the ``Ref. Publications'' 
section of EASA AD 2023-0083.

(j) 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 (k) of 
this AD. If sending information directly to the manager of the 
International Validation Branch, mail it to the address identified 
in paragraph (k) of this AD or email to: [email protected]. If mailing 
information, also submit information by email.
    (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.

(k) Additional Information

    For more information about this AD, contact Hye Yoon Jang, 
Aviation Safety Engineer, 1600 Stewart Avenue, Suite 410, Westbury, 
NY 11590; phone: (206) 231-3758; email: [email protected].

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the material listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this material as applicable to do the actions 
required by this AD, unless the AD specifies otherwise.
    (i) European Union Aviation Safety Agency (EASA) AD 2023-0083, 
dated April 19, 2023.
    (ii) [Reserved]
    (3) For EASA material identified in this AD, contact EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 
000; email: [email protected]; website: easa.europa.eu. You may 
find the EASA material on the EASA website at ad.easa.europa.eu.
    (4) 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.
    (5) You may view this material at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    Issued on November 21, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2024-27814 Filed 11-27-24; 8:45 am]
BILLING CODE 4910-13-P
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