Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters, 10449-10451 [2021-01848]

Download as PDF Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Rules and Regulations (1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (j) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Saab AB, Support and Services’ EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (j) Related Information For more information about this AD, contact Shahram Daneshmandi, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3220; email: shahram.daneshmandi@faa.gov. tkelley on DSKBCP9HB2PROD with RULES (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2020–0137, dated June 18, 2020. (ii) [Reserved] (3) For EASA AD 2020–0137, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email: ADs@easa.europa.eu; internet: www.easa.europa.eu. You may find this EASA AD on the EASA website at https:// ad.easa.europa.eu. (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. 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–2020–0855. (5) You may view this material that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@ nara.gov, or go to: https://www.archives.gov/ federal-register/cfr/ibr-locations.html. VerDate Sep<11>2014 16:23 Feb 19, 2021 Jkt 253001 Issued on January 4, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–01824 Filed 2–19–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–1037; Project Identifier 2019–SW–077–AD; Amendment 39–21407; AD 2021–03–04] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. This AD requires removing certain Titanium (Ti) bolts from service and prohibits installing these Ti-bolts in a critical area. This AD was prompted by a report of a broken Ti-bolt. The actions of this AD are intended to address an unsafe condition on these products. DATES: This AD is effective March 29, 2021. SUMMARY: For service information identified in this final 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 the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. ADDRESSES: 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–2020– 1037; 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 AD, the European Union Aviation Safety Agency (EASA) AD, any comments received, and other information. The street address for Docket Operations is U.S. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 10449 Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Katherine Venegas, Aviation Safety Engineer, Los Angeles ACO, FAA, 3960 Paramount Blvd., Lakewood, CA 90712; telephone 562–627–5353; email katherine.venegas@faa.gov. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters with a Ti-bolt part number (P/N) L535M2001203 marked with manufacturer monogram ‘‘D’’ or with an illegible manufacturer monogram installed on the forward tail rotor (T/R) drive shaft. The NPRM published in the Federal Register on November 30, 2020 (85 FR 76490). The NPRM proposed to require removing any affected Ti-bolt installed on the forward T/R drive shaft from service and prohibit installing an affected Tibolt on the forward T/R drive shaft of any helicopter. The proposed requirements were intended to prevent failure of an affected Ti-bolt installed in a critical location, possibly resulting in reduced control of the helicopter. The NPRM was prompted by EASA AD No. 2019–0199, dated August 16, 2019, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Airbus Helicopters Deutschland GmbH (AHD), formerly Eurocopter Deutschland GmbH, Eurocopter Espan˜a S.A., Model EC135 P1, EC135 P2, EC135 P2+, EC135 P3, EC135 T1, EC135 T2, EC135 T2+, EC135 T3, EC635 P2+, EC635 P3, EC635 T1, EC635 T2+, and EC635 T3 helicopters. EASA advises of a report of a broken Tibolt. Subsequent investigation revealed that an improper heat treatment process was accomplished on a batch of Tibolts, which can lead to hydrogen embrittlement. The investigation also identified the critical location where these Ti-bolts are installed on helicopters. According to EASA, this condition, if not detected and corrected, could lead to failure of an affected Tibolt installed in a critical location, possibly resulting in reduced control of the helicopter. Accordingly, the EASA AD requires a one-time inspection of Tibolt P/N L535M2001203 marked with E:\FR\FM\22FER1.SGM 22FER1 10450 Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Rules and Regulations manufacturer monogram ‘‘D’’ or with an illegible manufacturer monogram installed on the forward T/R drive shaft and, depending on the inspection results, replacing the Ti-bolt. The EASA AD also prohibits the (re)installation of these Ti-bolts. Comments The FAA gave the public the opportunity to participate in developing this final rule, but the FAA did not receive any comments on the NPRM or on the determination of the cost to the public. 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 issuing this AD after evaluating all of the information provided by EASA and determining the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed. tkelley on DSKBCP9HB2PROD with RULES Differences Between This AD and the EASA AD The EASA AD applies to Model EC135 P1, EC135 P2, EC135 P2+, EC135 P3, EC135 T1, EC135 T2, EC135 T2+, EC135 T3, EC635 P2+, EC635 P3, EC635 T1, EC635 T2+, and EC635 T3 helicopters and requires inspecting Tibolt P/N L535M2001203 marked with manufacturer monogram ‘‘D’’ or with an illegible manufacturer monogram installed on the forward T/R drive shaft. This AD applies to Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters with a Ti-bolt P/N L535M2001203 marked with manufacturer monogram ‘‘D’’ or with an illegible manufacturer monogram installed on the forward T/R drive shaft instead. This AD does not apply to Model EC635 P2+, EC635 P3, EC635 T1, EC635 T2+, or EC635 T3 helicopters because these models are not FAA typecertificated. The EASA AD requires discarding the affected Ti-bolts, whereas this AD requires removing the affected Ti-bolts from service instead. Related Service Information The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) No. EC135– 00A–001, Revision 1, dated September 2, 2019, for Airbus Helicopters Deutschland GmbH Model EC135 T1, T2, T2+, T3, P1, P2, P2+, P3, 635 T1, VerDate Sep<11>2014 16:23 Feb 19, 2021 Jkt 253001 635 T2+, 635 T3, 635 P2+, and 635 P3 helicopters, and Airbus Helicopters ASB No. EC135H–00A–001, Revision 1, dated September 2, 2019, for Airbus Helicopters Deutschland GmbH Model EC135, T3H, P3H, 635 T3H, and 635 P3H helicopters. This service information specifies inspecting the forward T/R drive shaft, distance plate of the 5B–0.50–2.50P–XN–1 antenna, main rotor controls, FWD connection of ball bearing control, and AFT connection of ball bearing control and yaw actuator for the installation of Tibolt P/N L535M2001203, EN3308– 040020F, L221M1040201, EN3740– 060020F, and EN3308–060020F, marked with manufacturer monogram ‘‘D’’ or an illegible manufacturer monogram. If a specified Ti-bolt is installed, the service information specifies replacing the Tibolt and discarding the removed Ti-bolt. Costs of Compliance The FAA estimates that this AD affects 326 helicopters of U.S. Registry. Labor rates are estimated at $85 per work-hour. Based on these numbers, the FAA estimates that operators may incur the following costs in order to comply with this AD. Replacing a Ti-bolt takes about four work-hours and parts cost about $82 for an estimated cost of $422 per Ti-bolt. 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 helicopters identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2021–03–04 Airbus Helicopters Deutschland GmbH: Amendment 39– 21407; Docket No. FAA–2020–1037; Project Identifier 2019–SW–077–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, with a Titanium (Ti) bolt part number L535M2001203 marked with manufacturer monogram ‘‘D’’ or with an illegible manufacturer monogram installed on the forward tail rotor drive shaft. Note 1 to paragraph (a): Helicopters with an EC135P3H designation are Model EC135P3 helicopters. Helicopters with an EC135T3H designation are Model EC135T3 helicopters. (b) Unsafe Condition This AD defines the unsafe condition as failure of an affected Ti-bolt installed in a critical location, possibly resulting in reduced control of the helicopter. (c) Effective Date This AD becomes effective March 29, 2021. (d) 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. E:\FR\FM\22FER1.SGM 22FER1 Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Rules and Regulations (e) Required Actions DEPARTMENT OF TRANSPORTATION (1) Within 50 hours time-in-service or 3 months, whichever occurs first, remove any Ti-bolt identified in paragraph (a) of this AD, located on the forward tail rotor drive shaft, from service. (2) As of the effective date of this AD, do not install a Ti-bolt identified in paragraph (a) of this AD on the forward tail rotor drive shaft of any helicopter. 14 CFR Part 39 [Docket No. FAA–2020–0849; Project Identifier MCAI–2020–01036–A; Amendment 39–21374; AD 2020–26–19] RIN 2120–AA64 (f) Alternative Methods of Compliance (AMOCs) Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes (1) The Manager, Strategic Policy Rotorcraft Section, FAA, may approve AMOCs for this AD. Send your proposal to: Manager, Strategic Policy Rotorcraft Section, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email 9ASW-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. AGENCY: (g) Additional Information (1) Airbus Helicopters Alert Service Bulletin (ASB) No. EC135–00A–001 and ASB No. EC135H–00A–001, each Revision 1 and dated September 2, 2019, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, 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 a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Union Aviation Safety Agency (EASA) AD No. 2019–0199, dated August 16, 2019. You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA–2020–1037. (h) Subject Joint Aircraft Service Component (JASC) Code: 1430, Fasteners; and 6510, Tail Rotor Drive Shaft. tkelley on DSKBCP9HB2PROD with RULES Federal Aviation Administration Issued on January 22, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–01848 Filed 2–19–21; 8:45 am] BILLING CODE 4910–13–P Federal Aviation Administration (FAA), DOT. ACTION: Final rule. The FAA is adopting a new airworthiness directive (AD) for all Pilatus Aircraft Ltd. Model PC–7 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. This AD requires revising the Airworthiness Limitations section (ALS) of the existing aircraft maintenance manual (AMM) to introduce new mandatory repetitive inspections for the flap pivot arm assemblies and for certain wing angle brackets, and to implement a change to the Oxygen cylinder and pressure reducer task item. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 29, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 29, 2021. ADDRESSES: For service information identified in this final rule, contact Pilatus Aircraft Ltd., CH–6371, Customer Technical Support (MCC), P.O. Box 992, CH–6371, Stans, Switzerland; phone: +41 (0)41 619 67 74; fax: +41 (0)41 619 67; email: techsupport@pilatus-aircraft.com; website: https://www.pilatusaircraft.comen/. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329– 4148. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0849. SUMMARY: Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. VerDate Sep<11>2014 16:23 Feb 19, 2021 Jkt 253001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 10451 FAA–2020–0849; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the MCAI, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, General Aviation & Rotorcraft Section, International Validation Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; phone: (816) 329– 4059; fax: (816) 329–4090; email: doug.rudolph@faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Pilatus Aircraft Ltd. Model PC–7 airplanes. The NPRM published in the Federal Register on September 24, 2020 (85 FR 60097). The NPRM was prompted by MCAI originated by the Federal Office for Civil Aviation (FOCA), which is the aviation authority for Switzerland. FOCA has issued FOCA AD HB–2020–007, dated July 23, 2020 (referred to after this as the MCAI), to correct an unsafe condition with new mandatory instructions for continued airworthiness for all Pilatus Aircraft Ltd. Model PC–7 airplanes. The MCAI states: The airworthiness limitations and certification maintenance instructions for Pilatus PC–7 aeroplanes, which are approved by FOCA, are currently defined and published in the Pilatus PC–7 AMM Chapter 5. These instructions have been identified as mandatory for continued airworthiness. Failure to accomplish these instructions could result in an unsafe condition [discrepancies of life-limited and overhauled components, which could result in reduced structural integrity and system reliability of the airplane]. Previously, FOCA issued AD HB–2019–004 (later corrected) to require implementation of the maintenance tasks and airworthiness limitations as specified in Pilatus PC–7 AMM Document Number 01715, or Document Number 02416, both at issue 44, as applicable. [These tasks included the added wing angle bracket at rib 23 repetitive inspections.] Since that AD was issued, Pilatus amended the ALS, as defined in this AD, to introduce new mandatory repetitive inspection for the flap pivot arm assemblies and a change to the Oxygen cylinder and pressure reducer task (Chapter 35—Oxygen) to remove the reference to the part numbers. For the reason described above, this [Swiss] AD retains the requirements of FOCA E:\FR\FM\22FER1.SGM 22FER1

Agencies

[Federal Register Volume 86, Number 33 (Monday, February 22, 2021)]
[Rules and Regulations]
[Pages 10449-10451]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-01848]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-1037; Project Identifier 2019-SW-077-AD; Amendment 
39-21407; AD 2021-03-04]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, 
EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. 
This AD requires removing certain Titanium (Ti) bolts from service and 
prohibits installing these Ti-bolts in a critical area. This AD was 
prompted by a report of a broken Ti-bolt. The actions of this AD are 
intended to address an unsafe condition on these products.

DATES: This AD is effective March 29, 2021.

ADDRESSES: For service information identified in this final 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 the referenced service information at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, 
Fort Worth, TX 76177.

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-2020-
1037; 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 AD, the European Union Aviation Safety Agency (EASA) AD, any 
comments received, and other information. The street address for Docket 
Operations is U.S. Department of Transportation, Docket Operations, M-
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue 
SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Katherine Venegas, Aviation Safety 
Engineer, Los Angeles ACO, FAA, 3960 Paramount Blvd., Lakewood, CA 
90712; telephone 562-627-5353; email [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to Airbus Helicopters 
Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, 
EC135T2, EC135T2+, and EC135T3 helicopters with a Ti-bolt part number 
(P/N) L535M2001203 marked with manufacturer monogram ``D'' or with an 
illegible manufacturer monogram installed on the forward tail rotor (T/
R) drive shaft. The NPRM published in the Federal Register on November 
30, 2020 (85 FR 76490). The NPRM proposed to require removing any 
affected Ti-bolt installed on the forward T/R drive shaft from service 
and prohibit installing an affected Ti-bolt on the forward T/R drive 
shaft of any helicopter. The proposed requirements were intended to 
prevent failure of an affected Ti-bolt installed in a critical 
location, possibly resulting in reduced control of the helicopter.
    The NPRM was prompted by EASA AD No. 2019-0199, dated August 16, 
2019, issued by EASA, which is the Technical Agent for the Member 
States of the European Union, to correct an unsafe condition for Airbus 
Helicopters Deutschland GmbH (AHD), formerly Eurocopter Deutschland 
GmbH, Eurocopter Espa[ntilde]a S.A., Model EC135 P1, EC135 P2, EC135 
P2+, EC135 P3, EC135 T1, EC135 T2, EC135 T2+, EC135 T3, EC635 P2+, 
EC635 P3, EC635 T1, EC635 T2+, and EC635 T3 helicopters. EASA advises 
of a report of a broken Ti-bolt. Subsequent investigation revealed that 
an improper heat treatment process was accomplished on a batch of Ti-
bolts, which can lead to hydrogen embrittlement. The investigation also 
identified the critical location where these Ti-bolts are installed on 
helicopters. According to EASA, this condition, if not detected and 
corrected, could lead to failure of an affected Ti-bolt installed in a 
critical location, possibly resulting in reduced control of the 
helicopter. Accordingly, the EASA AD requires a one-time inspection of 
Ti-bolt P/N L535M2001203 marked with

[[Page 10450]]

manufacturer monogram ``D'' or with an illegible manufacturer monogram 
installed on the forward T/R drive shaft and, depending on the 
inspection results, replacing the Ti-bolt. The EASA AD also prohibits 
the (re)installation of these Ti-bolts.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule, but the FAA did not receive any comments on 
the NPRM or on the determination of the cost to the public.

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 issuing this AD after 
evaluating all of the information provided by EASA and determining the 
unsafe condition exists and is likely to exist or develop on other 
helicopters of these same type designs and that air safety and the 
public interest require adopting the AD requirements as proposed.

Differences Between This AD and the EASA AD

    The EASA AD applies to Model EC135 P1, EC135 P2, EC135 P2+, EC135 
P3, EC135 T1, EC135 T2, EC135 T2+, EC135 T3, EC635 P2+, EC635 P3, EC635 
T1, EC635 T2+, and EC635 T3 helicopters and requires inspecting Ti-bolt 
P/N L535M2001203 marked with manufacturer monogram ``D'' or with an 
illegible manufacturer monogram installed on the forward T/R drive 
shaft. This AD applies to Model EC135P1, EC135P2, EC135P2+, EC135P3, 
EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters with a Ti-bolt P/N 
L535M2001203 marked with manufacturer monogram ``D'' or with an 
illegible manufacturer monogram installed on the forward T/R drive 
shaft instead. This AD does not apply to Model EC635 P2+, EC635 P3, 
EC635 T1, EC635 T2+, or EC635 T3 helicopters because these models are 
not FAA type-certificated. The EASA AD requires discarding the affected 
Ti-bolts, whereas this AD requires removing the affected Ti-bolts from 
service instead.

 Related Service Information

    The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) 
No. EC135-00A-001, Revision 1, dated September 2, 2019, for Airbus 
Helicopters Deutschland GmbH Model EC135 T1, T2, T2+, T3, P1, P2, P2+, 
P3, 635 T1, 635 T2+, 635 T3, 635 P2+, and 635 P3 helicopters, and 
Airbus Helicopters ASB No. EC135H-00A-001, Revision 1, dated September 
2, 2019, for Airbus Helicopters Deutschland GmbH Model EC135, T3H, P3H, 
635 T3H, and 635 P3H helicopters. This service information specifies 
inspecting the forward T/R drive shaft, distance plate of the 5B-0.50-
2.50P-XN-1 antenna, main rotor controls, FWD connection of ball bearing 
control, and AFT connection of ball bearing control and yaw actuator 
for the installation of Ti-bolt P/N L535M2001203, EN3308-040020F, 
L221M1040201, EN3740-060020F, and EN3308-060020F, marked with 
manufacturer monogram ``D'' or an illegible manufacturer monogram. If a 
specified Ti-bolt is installed, the service information specifies 
replacing the Ti-bolt and discarding the removed Ti-bolt.

Costs of Compliance

    The FAA estimates that this AD affects 326 helicopters of U.S. 
Registry. Labor rates are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates that operators may incur the following 
costs in order to comply with this AD.
    Replacing a Ti-bolt takes about four work-hours and parts cost 
about $82 for an estimated cost of $422 per Ti-bolt.

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 helicopters identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (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.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2021-03-04 Airbus Helicopters Deutschland GmbH: Amendment 39-21407; 
Docket No. FAA-2020-1037; Project Identifier 2019-SW-077-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, with a Titanium (Ti) bolt part number L535M2001203 marked 
with manufacturer monogram ``D'' or with an illegible manufacturer 
monogram installed on the forward tail rotor drive shaft.
    Note 1 to paragraph (a): Helicopters with an EC135P3H 
designation are Model EC135P3 helicopters. Helicopters with an 
EC135T3H designation are Model EC135T3 helicopters.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of an affected 
Ti-bolt installed in a critical location, possibly resulting in 
reduced control of the helicopter.

(c) Effective Date

    This AD becomes effective March 29, 2021.

(d) 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.

[[Page 10451]]

(e) Required Actions

    (1) Within 50 hours time-in-service or 3 months, whichever 
occurs first, remove any Ti-bolt identified in paragraph (a) of this 
AD, located on the forward tail rotor drive shaft, from service.
    (2) As of the effective date of this AD, do not install a Ti-
bolt identified in paragraph (a) of this AD on the forward tail 
rotor drive shaft of any helicopter.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Strategic Policy Rotorcraft Section, FAA, may 
approve AMOCs for this AD. Send your proposal to: Manager, Strategic 
Policy Rotorcraft Section, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 
76177; telephone 817-222-5110; email [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.

(g) Additional Information

    (1) Airbus Helicopters Alert Service Bulletin (ASB) No. EC135-
00A-001 and ASB No. EC135H-00A-001, each Revision 1 and dated 
September 2, 2019, which are not incorporated by reference, contain 
additional information about the subject of this AD. For service 
information identified in this AD, 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 a copy of 
the service information at the FAA, Office of the Regional Counsel, 
Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX 
76177.
    (2) The subject of this AD is addressed in European Union 
Aviation Safety Agency (EASA) AD No. 2019-0199, dated August 16, 
2019. You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA-2020-1037.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 1430, Fasteners; 
and 6510, Tail Rotor Drive Shaft.

    Issued on January 22, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-01848 Filed 2-19-21; 8:45 am]
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