Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters, 13237-13239 [2021-03991]

Download as PDF Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules Rotorcraft Section, send it to: Manager, Strategic Policy Rotorcraft Section, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110. Information may be emailed to: 9-ASW-FTW-AMOCRequests@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. (k) Related Information (1) For EASA AD 2020–0084, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https:// ad.easa.europa.eu. 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. This material may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0104. (2) For more information about this AD, contact Hal Jensen, Aerospace Engineer, Operational Safety Branch, FAA, 470 L’Enfant Plaza SW, Washington, DC 20024; telephone 202–267–9167; email hal.jensen@ faa.gov. Issued on February 19, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–04185 Filed 3–5–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0113; Product Identifier 2017–SW–140–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2016–11–21 for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters. AD 2016–11–21 requires revising the life limit of certain parts and removing each part that has reached its life limit. Since the FAA issued AD 2016–11–21, new models were certified. jbell on DSKJLSW7X2PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:28 Mar 05, 2021 Jkt 253001 This proposed AD would expand the applicability to include Model EC135P3 and EC135T3 helicopters. This proposed AD would also revise the life limits for certain parts and propose to remove each part that has reached or exceeded its life limit. The actions of this proposed AD are intended to address an unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by April 22, 2021. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0113; 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 proposed AD, the European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, any comments received and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. For service information identified in this proposed rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone 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 FURTHER INFORMATION CONTACT: Matt Fuller, AD Program Manager, Operational Safety Branch, Airworthiness Products Section, General Aviation & Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222– 5110; email matthew.fuller@faa.gov. PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 13237 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–2019–0113; Product Identifier 2017–SW–140–AD’’ 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.regualtions.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this proposal. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Matt Fuller, AD Program Manager, Operational Safety Branch, Airworthiness Products Section, General Aviation & Rotorcraft Unit, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222– 5110; email Matthew.Fuller@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. Discussion The FAA issued AD 2016–11–21, Amendment 39–18548 (81 FR 36137, June 6, 2016) (AD 2016–11–21) for Airbus Helicopters Model EC135P1, EC135P2, EC135P2+, EC135T1, E:\FR\FM\08MRP1.SGM 08MRP1 13238 Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules EC135T2, and EC135T2+ helicopters. AD 2016–11–21 requires reducing the life limit of certain parts and removing each part that has reached its life limit. AD 2016–11–21 was prompted by Airbus Helicopters revising the airworthiness limitations for the Model EC135 and EC635 helicopters’ type design as published in the Master Servicing Manual (MSM) EC135 Chapter 04—ALS documents. Revision 14 of the MSM contains these new airworthiness limitations. EASA, which is the Technical Agent for the Member States of the European Union, issued EASA AD No. 2013–0178, dated August 7, 2013 (EASA AD 2013– 0178), to correct an unsafe condition for Eurocopter Deutschland GmbH (ECD) (now Airbus Helicopters) Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, EC135T2+, EC635T1, EC635P2+, and EC635T2+ helicopters. EASA advises that ECD has revised the airworthiness limitations for the EC135 and EC635 type design as published in the MSM. Revision 14 of the MSM contains these new airworthiness limitations. EASA states that failure to comply with these limitations could result in failure of a critical part, which could result in loss of control of the helicopter. Accordingly, EASA AD 2013–0178 requires revising the airworthiness limitations section (ALS) to include the new life limits and replacing each part that has reached its life limit. Actions Since AD 2016–11–21 Was Issued Since the FAA issued AD 2016–11– 21, EASA issued EASA AD No. 2017– 0243, dated December 6, 2017 (EASA AD 2017–0243), which supersedes EASA AD No. 2013–0178 and expands the applicability to include Models EC135P3, EC135T3, EC635P3, and EC635T3 helicopters. New life limits also were added for some parts. Model EC635P3 and EC635T3 helicopters are not included in the applicability of this proposed AD as these model helicopters are not FAA type-certificated. jbell on DSKJLSW7X2PROD with PROPOSALS 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 of the unsafe condition described in its AD. The FAA is proposing this AD after evaluating all known relevant information and determining that an unsafe condition is likely to exist or develop on other helicopters of the same type design. VerDate Sep<11>2014 16:28 Mar 05, 2021 Jkt 253001 Related Service Information Under 1 CFR Part 51 The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) EC135– 04A–012, Revision 0, dated September 11, 2017, which specifies incorporating life limits for the tail rotor hub body into the tail rotor hub log card and into the list of life-limited parts. Airbus Helicopters reports the addition of the tail rotor hub body into the tail rotor hub log card was prompted by a new, recently manufactured, serial-numbered hub. 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 This proposed AD would require, before further flight, establishing a life limit for the tail rotor hub body of 27,400 hours time-in-service (TIS) or using the service information if the history of the tail rotor hub body is not known or cannot be identified. This proposed AD would also require establishing life limits for certain swashplate and mixing lever gear unit parts in the ALS, and recording the revised life limit on the component history card or equivalent record. Additionally, this proposed AD would require continuing to record the life limit of certain parts that have not reached their life limit. This proposed AD would require removing from service any part that reached or exceeded its life limit. Differences Between This Proposed AD and the EASA AD The EASA AD applies to Model EC635P2+, EC635P3, EC635T2+, and EC635T3 helicopters, whereas this proposed AD would not because these model helicopters are not FAA typecertificated. The EASA AD would require revising the Aircraft Maintenance Program with new or revised life limitations within 12 months after the EASA AD’s effective date. This proposed AD would require revising the life limit for certain parts in the ALS of the existing maintenance manual for your helicopter before further flight. Costs of Compliance The FAA estimates that this proposed AD would affect 272 helicopters of U.S. Registry. The FAA estimates that operators may incur the following costs in order to comply with this proposed AD. Labor costs are estimated at $85 per work-hour. PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 Revising the component history card or equivalent record would take about 2 work-hours, for an estimated cost of $170 per helicopter and $46,240 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, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866, 2. Will not affect intrastate aviation in Alaska, and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The 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 1. The authority citation for part 39 continues to read as follows: ■ E:\FR\FM\08MRP1.SGM 08MRP1 Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive (AD) 2016–11–21, Amendment 39– 18548 (81 FR 36137); and ■ b. Adding the following new AD: ■ ■ Airbus Helicopters Deutschland GmbH: Docket No. FAA–2019–0113; Product Identifier 2017–SW–140–AD. (a) Applicability This airworthiness directive (AD) applies to Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters, certificated in any category. (b) Unsafe Condition The FAA is issuing this AD to prevent certain parts from remaining in service beyond their fatigue life, resulting in failure of the part and subsequent loss of control of the helicopter. (c) Affected ADs This AD replaces AD 2016–11–21, Amendment 39–18548 (81 FR 36137, June 6, 2016). (d) Comments Due Date The FAA must receive comments by April 22, 2021. jbell on DSKJLSW7X2PROD with PROPOSALS (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (f) Required Actions (1) Before further flight, establish a life limit for the tail rotor hub body (hub body), part number (P/N) L642A2003102, of 27,400 hours time-in-service (TIS). If you cannot determine the hub body’s TIS, follow the instructions in Table 1, Examples and Calculations, Effectivity: The history of the hub body is not known or can’t be identified, in Airbus Helicopters Alert Service Bulletin (ASB) EC135–04A–012, Revision 0, dated September 11, 2017, except where the service information specifies that you contact the manufacturer, you are required to remove the part from service instead. (2) Before further flight, revise the life limit for each part listed in paragraphs (f)(2)(i) and (ii) of this AD in the Airworthiness Limitations Section (ALS) of the existing maintenance manual for your helicopter and record the revised life limit on the component history card or equivalent record as follows: (i) For swashplate parts: (A) The life limit for the ring (control ring), P/N L623M2001213, is 10,700 hours TIS. (B) The life limit for the cardan ring (twopart), P/N L623M2005205, is 14,300 hours TIS. (C) The life limit for the bolt (control ring), P/N L671M7001215, is 14,300 hours TIS. (D) The life limit for the bolt (sliding sleeve), P/N L623M2006206 and P/N L623M2006213, is 14,300 hours TIS. VerDate Sep<11>2014 16:28 Mar 05, 2021 Jkt 253001 (ii) For mixing lever gear unit parts: (A) The life limit for the forked lever assembly, P/N L671M3012102, is 10,400 hours TIS. (B) The life limit for the hinged support, P/N L671M7003210, is 8,400 hours TIS. (C) The life limit for the bolt, P/N L671M7001220, is 8,400 hours TIS. (3) Before further flight, remove from service any part listed in paragraphs (f)(1) and (2) of this AD that has reached or exceeded its revised life limit. (4) Thereafter, for any part listed in paragraphs (f)(1) and (2) of this AD that has not reached or exceeded its life limit, continue to record the life limit of the part on its component history card or equivalent record and remove any part listed in paragraph (f)(1) and (2) of this AD from service before the part has reached or exceeded its revised life limit. (g) Special Flight Permits Special flight permits are limited to a onetime flight to a maintenance facility to replace a part that has reached its life limit. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Strategic Policy Rotorcraft Section, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. If sending information directly to the manager of the Strategic Policy Rotorcraft Section, send it to: Manager, Strategic Policy Rotorcraft Section, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110. Information may be emailed to: 9-ASW-FTW-AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, the FAA suggests that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (i) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD No. 2017–0243, dated December 6, 2017. You may view the EASA AD on the internet at https://www.regulations.gov in the AD Docket. (j) Subject Joint Aircraft Service Component (JASC) Code: 6400, Tail Rotor System. Issued on February 17, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–03991 Filed 3–5–21; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 13239 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0131; Project Identifier MCAI–2020–01628–T] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for all Airbus SAS Model A330–200, –300, –800, and –900 series airplanes; and Model A340–200, –300, –500, and –600 series airplanes. This proposed AD was prompted by reports that certain oxygen supply solenoid valves are a potential source of increased flow resistance within the flightcrew oxygen system. This proposed AD would require a special detailed inspection (flow test) of certain solenoid valves, and replacement if necessary, 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 proposed AD by April 22, 2021. 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 material that will be incorporated by reference (IBR) in this AD, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@ easa.europa.eu; internet www.easa.europa.eu. You may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may view this IBR material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For SUMMARY: E:\FR\FM\08MRP1.SGM 08MRP1

Agencies

[Federal Register Volume 86, Number 43 (Monday, March 8, 2021)]
[Proposed Rules]
[Pages 13237-13239]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-03991]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0113; Product Identifier 2017-SW-140-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2016-11-21 for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) 
Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ 
helicopters. AD 2016-11-21 requires revising the life limit of certain 
parts and removing each part that has reached its life limit. Since the 
FAA issued AD 2016-11-21, new models were certified. This proposed AD 
would expand the applicability to include Model EC135P3 and EC135T3 
helicopters. This proposed AD would also revise the life limits for 
certain parts and propose to remove each part that has reached or 
exceeded its life limit. The actions of this proposed AD are intended 
to address an unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by April 22, 
2021.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0113; 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 proposed AD, the European Aviation Safety Agency (now European 
Union Aviation Safety Agency) (EASA) AD, any comments received and 
other information. The street address for Docket Operations is listed 
above. Comments will be available in the AD docket shortly after 
receipt.
    For service information identified in this proposed rule, contact 
Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; 
telephone 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 FURTHER INFORMATION CONTACT: Matt Fuller, AD Program Manager, 
Operational Safety Branch, Airworthiness Products Section, General 
Aviation & Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 
76177; telephone 817-222-5110; 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-2019-0113; Product Identifier 
2017-SW-140-AD'' 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.regualtions.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this proposal.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to Matt 
Fuller, AD Program Manager, Operational Safety Branch, Airworthiness 
Products Section, General Aviation & Rotorcraft Unit, 10101 Hillwood 
Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; 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.

Discussion

    The FAA issued AD 2016-11-21, Amendment 39-18548 (81 FR 36137, June 
6, 2016) (AD 2016-11-21) for Airbus Helicopters Model EC135P1, EC135P2, 
EC135P2+, EC135T1,

[[Page 13238]]

EC135T2, and EC135T2+ helicopters. AD 2016-11-21 requires reducing the 
life limit of certain parts and removing each part that has reached its 
life limit. AD 2016-11-21 was prompted by Airbus Helicopters revising 
the airworthiness limitations for the Model EC135 and EC635 
helicopters' type design as published in the Master Servicing Manual 
(MSM) EC135 Chapter 04--ALS documents. Revision 14 of the MSM contains 
these new airworthiness limitations.
    EASA, which is the Technical Agent for the Member States of the 
European Union, issued EASA AD No. 2013-0178, dated August 7, 2013 
(EASA AD 2013-0178), to correct an unsafe condition for Eurocopter 
Deutschland GmbH (ECD) (now Airbus Helicopters) Model EC135P1, EC135P2, 
EC135P2+, EC135T1, EC135T2, EC135T2+, EC635T1, EC635P2+, and EC635T2+ 
helicopters. EASA advises that ECD has revised the airworthiness 
limitations for the EC135 and EC635 type design as published in the 
MSM. Revision 14 of the MSM contains these new airworthiness 
limitations. EASA states that failure to comply with these limitations 
could result in failure of a critical part, which could result in loss 
of control of the helicopter. Accordingly, EASA AD 2013-0178 requires 
revising the airworthiness limitations section (ALS) to include the new 
life limits and replacing each part that has reached its life limit.

Actions Since AD 2016-11-21 Was Issued

    Since the FAA issued AD 2016-11-21, EASA issued EASA AD No. 2017-
0243, dated December 6, 2017 (EASA AD 2017-0243), which supersedes EASA 
AD No. 2013-0178 and expands the applicability to include Models 
EC135P3, EC135T3, EC635P3, and EC635T3 helicopters. New life limits 
also were added for some parts. Model EC635P3 and EC635T3 helicopters 
are not included in the applicability of this proposed AD as these 
model helicopters are not FAA type-certificated.

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 of the 
unsafe condition described in its AD. The FAA is proposing this AD 
after evaluating all known relevant information and determining that an 
unsafe condition 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 Airbus Helicopters Alert Service Bulletin (ASB) 
EC135-04A-012, Revision 0, dated September 11, 2017, which specifies 
incorporating life limits for the tail rotor hub body into the tail 
rotor hub log card and into the list of life-limited parts. Airbus 
Helicopters reports the addition of the tail rotor hub body into the 
tail rotor hub log card was prompted by a new, recently manufactured, 
serial-numbered hub.
    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

    This proposed AD would require, before further flight, establishing 
a life limit for the tail rotor hub body of 27,400 hours time-in-
service (TIS) or using the service information if the history of the 
tail rotor hub body is not known or cannot be identified. This proposed 
AD would also require establishing life limits for certain swashplate 
and mixing lever gear unit parts in the ALS, and recording the revised 
life limit on the component history card or equivalent record. 
Additionally, this proposed AD would require continuing to record the 
life limit of certain parts that have not reached their life limit. 
This proposed AD would require removing from service any part that 
reached or exceeded its life limit.

Differences Between This Proposed AD and the EASA AD

    The EASA AD applies to Model EC635P2+, EC635P3, EC635T2+, and 
EC635T3 helicopters, whereas this proposed AD would not because these 
model helicopters are not FAA type-certificated. The EASA AD would 
require revising the Aircraft Maintenance Program with new or revised 
life limitations within 12 months after the EASA AD's effective date. 
This proposed AD would require revising the life limit for certain 
parts in the ALS of the existing maintenance manual for your helicopter 
before further flight.

Costs of Compliance

    The FAA estimates that this proposed AD would affect 272 
helicopters of U.S. Registry. The FAA estimates that operators may 
incur the following costs in order to comply with this proposed AD. 
Labor costs are estimated at $85 per work-hour.
    Revising the component history card or equivalent record would take 
about 2 work-hours, for an estimated cost of $170 per helicopter and 
$46,240 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, I certify this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866,
    2. Will not affect intrastate aviation in Alaska, and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The 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:


[[Page 13239]]


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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2016-11-21, Amendment 39-18548 
(81 FR 36137); and
0
b. Adding the following new AD:

Airbus Helicopters Deutschland GmbH: Docket No. FAA-2019-0113; 
Product Identifier 2017-SW-140-AD.

(a) Applicability

    This airworthiness directive (AD) applies to Airbus Helicopters 
Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, 
EC135T2, EC135T2+, and EC135T3 helicopters, certificated in any 
category.

(b) Unsafe Condition

    The FAA is issuing this AD to prevent certain parts from 
remaining in service beyond their fatigue life, resulting in failure 
of the part and subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD replaces AD 2016-11-21, Amendment 39-18548 (81 FR 36137, 
June 6, 2016).

(d) Comments Due Date

    The FAA must receive comments by April 22, 2021.

(e) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(f) Required Actions

    (1) Before further flight, establish a life limit for the tail 
rotor hub body (hub body), part number (P/N) L642A2003102, of 27,400 
hours time-in-service (TIS). If you cannot determine the hub body's 
TIS, follow the instructions in Table 1, Examples and Calculations, 
Effectivity: The history of the hub body is not known or can't be 
identified, in Airbus Helicopters Alert Service Bulletin (ASB) 
EC135-04A-012, Revision 0, dated September 11, 2017, except where 
the service information specifies that you contact the manufacturer, 
you are required to remove the part from service instead.
    (2) Before further flight, revise the life limit for each part 
listed in paragraphs (f)(2)(i) and (ii) of this AD in the 
Airworthiness Limitations Section (ALS) of the existing maintenance 
manual for your helicopter and record the revised life limit on the 
component history card or equivalent record as follows:
    (i) For swashplate parts:
    (A) The life limit for the ring (control ring), P/N 
L623M2001213, is 10,700 hours TIS.
    (B) The life limit for the cardan ring (two-part), P/N 
L623M2005205, is 14,300 hours TIS.
    (C) The life limit for the bolt (control ring), P/N 
L671M7001215, is 14,300 hours TIS.
    (D) The life limit for the bolt (sliding sleeve), P/N 
L623M2006206 and P/N L623M2006213, is 14,300 hours TIS.
    (ii) For mixing lever gear unit parts:
    (A) The life limit for the forked lever assembly, P/N 
L671M3012102, is 10,400 hours TIS.
    (B) The life limit for the hinged support, P/N L671M7003210, is 
8,400 hours TIS.
    (C) The life limit for the bolt, P/N L671M7001220, is 8,400 
hours TIS.
    (3) Before further flight, remove from service any part listed 
in paragraphs (f)(1) and (2) of this AD that has reached or exceeded 
its revised life limit.
    (4) Thereafter, for any part listed in paragraphs (f)(1) and (2) 
of this AD that has not reached or exceeded its life limit, continue 
to record the life limit of the part on its component history card 
or equivalent record and remove any part listed in paragraph (f)(1) 
and (2) of this AD from service before the part has reached or 
exceeded its revised life limit.

 (g) Special Flight Permits

    Special flight permits are limited to a onetime flight to a 
maintenance facility to replace a part that has reached its life 
limit.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Strategic Policy Rotorcraft Section, FAA, has 
the authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. If sending information directly to 
the manager of the Strategic Policy Rotorcraft Section, send it to: 
Manager, Strategic Policy Rotorcraft Section, FAA, 10101 Hillwood 
Pkwy., Fort Worth, TX 76177; telephone 817-222-5110. Information may 
be emailed to: [email protected].
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, the FAA suggests 
that you notify your principal inspector, or lacking a principal 
inspector, the manager of the local flight standards district office 
or certificate holding district office before operating any aircraft 
complying with this AD through an AMOC.

(i) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (now European Union Aviation Safety Agency) (EASA) AD No. 
2017-0243, dated December 6, 2017. You may view the EASA AD on the 
internet at https://www.regulations.gov in the AD Docket.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 6400, Tail Rotor 
System.

    Issued on February 17, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-03991 Filed 3-5-21; 8:45 am]
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