Airworthiness Directives; Airbus Helicopters, 14238-14241 [2021-05144]

Download as PDF 14238 Federal Register / Vol. 86, No. 48 / Monday, March 15, 2021 / Rules and Regulations airplane, as changed, continues to meet the applicable provisions of the regulations listed in Type Certificate No. T00005NY, or the applicable regulations in effect on the date of application for the change, except for earlier amendments as agreed upon by the FAA. If the Administrator finds that the applicable airworthiness regulations (e.g., 14 CFR part 25) do not contain adequate or appropriate safety standards for the Bombardier Model BD–100– 1A10 airplane because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16. Special conditions are initially applicable to the model for which they are issued. Should the applicant apply for a supplemental type certificate to modify any other model included on the same type certificate to incorporate the same novel or unusual design feature, these special conditions would also apply to the other model under § 21.101. In addition to the applicable airworthiness regulations and special conditions, the Bombardier Model BD– 100–1A10 airplane must comply with the fuel-vent and exhaust-emission requirements of 14 CFR part 34, and the noise-certification requirements of 14 CFR part 36. The FAA issues special conditions, as defined in 14 CFR 11.19, in accordance with § 11.38, and they become part of the type certification basis under § 21.101. khammond on DSKJM1Z7X2PROD with RULES Novel or Unusual Design Features The Bombardier Model BD–100–1A10 airplane, as modified by Rockwell Collins, will incorporate the following novel or unusual design feature: Installation of the Rockwell Collins Pro Line Fusion System, which allows connection to airplane electronic systems and networks, and access from aircraft external sources (e.g., operator networks, wireless devices, internet connectivity, service provider satellite communications, electronic flight bags, etc.) to the previously isolated airplane electronic assets. Discussion The Bombardier Model BD–100–1A10 airplane architecture and network configuration is novel or unusual for commercial transport airplanes because it may allow increased connectivity to and access from external network sources and airline operations and maintenance networks to the airplane control domain and airline information services domain. The airplane control domain and airline information-services domain perform functions required for VerDate Sep<11>2014 15:55 Mar 12, 2021 Jkt 253001 the safe operation and maintenance of the airplane. Previously, these domains had very limited connectivity with external network sources. This data network and design integration creates a potential for unauthorized persons to access the aircraft-control domain and airline information-services domain, and presents security vulnerabilities related to the introduction of computer viruses and worms, user errors, and intentional sabotage of airplane electronic assets (networks, systems, and databases) critical to the safety and maintenance of the airplane. The existing FAA regulations did not anticipate these networked airplane system architectures. Furthermore, these regulations and the current guidance material do not address potential security vulnerabilities, which could be exploited by unauthorized access to airplane networks, data buses, and servers. Therefore, these special conditions ensure that the security (i.e., confidentiality, integrity, and availability) of airplane systems is not compromised by unauthorized wired or wireless electronic connections. This includes ensuring that the security of the airplane’s systems is not compromised during maintenance of the airplane’s electronic systems. These special conditions also require the applicant to provide appropriate instructions to the operator to maintain all electronic-system safeguards that have been implemented as part of the original network design so that this feature does not allow or reintroduce security threats. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards. Applicability List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. Authority Citation The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701, 44702, 44704. The Special Conditions ■ Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for Bombardier Model BD–100–1A10 airplanes, as modified by Rockwell Collins, for airplane electronic-system security protection from unauthorized external access. 1. The applicant must ensure airplane electronic-system security protection from access by unauthorized sources external to the airplane, including those possibly caused by maintenance activity. 2. The applicant must ensure that electronic-system security threats are identified and assessed, and that effective electronic-system securityprotection strategies are implemented to protect the airplane from all adverse impacts on safety, functionality, and continued airworthiness. 3. The applicant must establish appropriate procedures to allow the operator to ensure that continued airworthiness of the airplane is maintained, including all post-typecertification modifications that may have an impact on the approved electronic-system security safeguards. Issued in Des Moines, Washington, on February 9, 2021. Suzanne Masterson, Manager, Transport Airplane Strategic Policy Section, Policy and Innovation Division, Aircraft Certification Service. [FR Doc. 2021–05294 Filed 3–12–21; 8:45 am] As discussed above, these special conditions are applicable to the Bombardier Model BD–100–1A10 airplane. Should Rockwell Collins apply at a later date for a supplemental type certificate to modify any other model included on Type Certificate No. T00005NY to incorporate the same novel or unusual design feature, these special conditions would apply to that model as well. BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0916; Product Identifier 2015–SW–055–AD; Amendment 39–21449; AD 2021–05–06] Conclusion RIN 2120–AA64 This action affects only a certain novel or unusual design feature on one model of airplane, as modified by Rockwell Collins. It is not a rule of general applicability and affects only the applicant. Airworthiness Directives; Airbus Helicopters PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: E:\FR\FM\15MRR1.SGM 15MRR1 Federal Register / Vol. 86, No. 48 / Monday, March 15, 2021 / Rules and Regulations The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, EC 155B, EC155B1, EC225LP, and SA330J helicopters. This AD requires inspecting the snap fasteners on the windows. This AD was prompted by incidents of difficulty unbuttoning the extraction tape on the windows. The actions of this AD are intended to address an unsafe condition on these products. DATES: This AD is effective April 19, 2021. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of April 19, 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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0916. khammond on DSKJM1Z7X2PROD with RULES SUMMARY: 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– 0916; 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 Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) ADs, any service information that is incorporated by reference, 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: David Hatfield, Aerospace Engineer, Aircraft Systems Section, Technical Innovation Policy Branch, Policy & Innovation Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email david.hatfield@faa.gov. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR VerDate Sep<11>2014 15:55 Mar 12, 2021 Jkt 253001 part 39 by adding an AD that would apply to Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, EC 155B, EC155B1, EC225LP, and SA330J helicopters with window extraction tape with snap fasteners installed. The NPRM published in the Federal Register on October 22, 2020 (85 FR 67313). The NPRM proposed to require inspecting each internal and external snap fastener to determine whether they unbutton by hand. For external snap fasteners that do not unbutton by hand, the NPRM proposed to require replacing the male part of the snap fastener and installing selfgripping tape if it still does not unbutton by hand. Thereafter, the NPRM proposed to require a repetitive inspection of the external extraction tape and self-gripping tape and replacing any tape that is cracked, torn, disintegrated, worn, or missing, and replacing the snap fasteners. For internal snap fasteners that do not unbutton by hand, the NPRM proposed to require installing self-gripping tape and replacing the snap fasteners. The proposed requirements were intended to prevent failure of a window to jettison, preventing occupants from exiting the helicopter during an emergency. The NPRM was prompted by EASA AD No. 2015–0149, dated July 23, 2015 (EASA AD 2015–0149), to correct an unsafe condition for Airbus Helicopters Model AS 322 and EC 225 LP helicopters; EASA AD No. 2015–0168, dated August 13, 2015 (EASA AD 2015– 0168), to correct an unsafe condition for Airbus Helicopters Model EC 155 B and EC 155 B1 helicopters; and EASA AD No. 2015–0169, dated August 13, 2015 (EASA AD 2015–0169), to correct an unsafe condition for Airbus Helicopters Model SA330 J helicopters, equipped with an extraction tape fitted with ‘‘press-studs’’ (snap fasteners) on the windows. Each EASA AD was issued by EASA, which is the Technical Agent for the Member States of the European Union. EASA advises of difficulty unbuttoning the extraction tape during the manufacturing of a helicopter. Investigation concluded that the difficulty was caused by a bad male/ female coupling, possibly resulting from miscrimping. This difficulty is known to have occurred on two additional helicopters. EASA states this condition, if not detected and corrected, could prevent the jettisoning of the helicopter window, possibly affecting the evacuation of passengers during an emergency situation. For these reasons, EASA AD 2015–0149, EASA AD 2015– 0168, and EASA AD 2015–0169 require inspecting each press-stud located on PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 14239 the extraction tapes of the window jettisoning system and depending on the findings, installing self-gripping tape and replacing the press-studs. 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. Related Service Information Under 1 CFR Part 51 The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) No. AS332–56.00.10, Revision 0, dated July 16, 2015, for Model AS332-series helicopters; ASB No. EC155–56A006, Revision 0, dated August 10, 2015, for Model EC155-series helicopters; ASB No. EC225–56A008, Revision 0, dated July 16, 2015, for Model EC225LP helicopters; and ASB No. SA330–56.02, Revision 0, dated August 10, 2015, for Model SA330J helicopters. This service information specifies procedures to inspect the internal and external pressstuds and to install self-gripping tape for press-studs that do not unbutton or are difficult to unbutton. This service information also specifies procedures to replace internal press-studs that are difficult to unbutton and a repetitive inspection for affected external pressstuds until they are replaced. 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. Costs of Compliance The FAA estimates that this AD affects 72 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. E:\FR\FM\15MRR1.SGM 15MRR1 14240 Federal Register / Vol. 86, No. 48 / Monday, March 15, 2021 / Rules and Regulations Inspecting the snap fasteners takes about 1 work-hour for a cost of $85 per helicopter and $6,120 for the U.S. fleet. Installing self-gripping tape takes about 0.3 work-hour and parts cost $200 for a cost of $226 per window. Inspecting the tape takes about 0.3 work-hour for a cost of $26 per window per inspection cycle. Replacing the extraction tape or selfgripping tape takes about 1 work-hour and parts cost $200 for a total of $285 per window. Replacing a snap fastener takes about 1 work-hour and parts cost $200 for a total of $285 per snap fastener. 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. khammond on DSKJM1Z7X2PROD with RULES 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. VerDate Sep<11>2014 15:55 Mar 12, 2021 Jkt 253001 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: ■ 2021–05–06 Airbus Helicopters: Amendment 39–21449; Docket No. FAA–2020–0916; Product Identifier 2015–SW–055–AD. (a) Applicability This airworthiness directive (AD) applies to Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, EC 155B, EC155B1, EC225LP, and SA330J helicopters, certificated in any category, with window extraction tape with snap fasteners installed. (b) Unsafe Condition This AD defines the unsafe condition as failure of a snap fastener to unbutton. This condition could result in failure of the window to jettison, preventing occupants from exiting the helicopter during an emergency. (c) Effective Date This AD becomes effective April 19, 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) Required Actions Within 50 hours time-in-service (TIS), inspect each internal and external snap fastener to determine if it can be unbuttoned by hand. Note 1 to the introductory text of paragraph (e): Airbus Helicopters refers to the snap fastener as a ‘‘press-stud.’’ (1) If all internal and external snap fasteners can be unbuttoned by hand, no further action is required by this AD. (2) If an external snap fastener does not unbutton by hand: (i) Before further flight, replace the male part of the snap fastener and determine if the snap fastener can be unbuttoned by hand force. If the snap fastener still does not unbutton by hand, before further flight, install self-gripping tape. (ii) Thereafter, at intervals not to exceed 15 hours TIS, inspect the external extraction tape and self-gripping tape for a crack, a tear, disintegration, or wear. If the extraction tape or self-gripping tape has a crack, a tear, any disintegration, wear, or is missing, before further flight, replace the tape. Replacing the PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 extraction tape or self-gripping tape does not terminate this repetitive inspection. (iii) Within 100 hours TIS, replace each external snap fastener by following the Accomplishment Instructions, paragraph 3.B.4., of Airbus Helicopters Alert Service Bulletin (ASB) No. AS332–56.00.10, Revision 0, dated July 16, 2015 (ASB AS332–56.00.10); ASB No. EC155–56A006, Revision 0, dated August 10, 2015 (ASB EC155–56A006); ASB No. EC225–56A008, Revision 0, dated July 16, 2015 (ASB EC225–56A008); or ASB No. SA330–56.02, Revision 0, dated August 10, 2015 (ASB SA330–56.02), as applicable to your model helicopter. Replacing the external snap fastener terminates the repetitive inspection requirements specified in paragraph (e)(2)(ii) of this AD. (3) If an internal snap fastener does not unbutton by hand: (i) Before further flight, install self-gripping tape by following the Accomplishment Instructions, paragraph 3.B.3., of AS332– 56.00.10, ASB EC155–56A006, ASB EC225– 56A008, or ASB SA330–56.02, as applicable to your model helicopter. (ii) Within 900 hours TIS, replace each internal snap fastener by following the Accomplishment Instructions, paragraph 3.B.5., of ASB AS332–56.00.10, ASB EC155– 56A006, ASB EC225–56A008, or ASB SA330–56.02, as applicable to your model helicopter. (f) 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, send it to the attention of: David Hatfield, Aerospace Engineer, Aircraft Systems Section, Technical Innovation Policy Branch, Policy & Innovation Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD No. 2015–0149, dated July 23, 2015; EASA AD No. 2015–0168, dated August 13, 2015; and EASA AD No. 2015– 0169, dated August 13, 2015. You may view the EASA ADs on the internet at https:// www.regulations.gov in Docket No. FAA– 2020–0916. (h) Subject Joint Aircraft Service Component (JASC) Code: 5600, Window/Windshield System. (i) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of E:\FR\FM\15MRR1.SGM 15MRR1 Federal Register / Vol. 86, No. 48 / Monday, March 15, 2021 / Rules and Regulations 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 the AD specifies otherwise. (i) Airbus Helicopters Alert Service Bulletin (ASB) No. AS332–56.00.10, Revision 0, dated July 16, 2015. (ii) Airbus Helicopters ASB No. EC155– 56A006, Revision 0, dated August 10, 2015. (iii) Airbus Helicopters ASB No. EC225– 56A008, Revision 0, dated July 16, 2015. (iv) Airbus Helicopters ASB No. SA330– 56.02, Revision 0, dated August 10, 2015. (3) 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. (4) You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110. (5) You may view this service information 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/ibrlocations.html. Issued on February 18, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–05144 Filed 3–12–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0903; Project Identifier AD–2020–00957–T; Amendment 39–21454; AD 2021–05–11] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2017–26– 10, which applied to certain The Boeing Company Model 757 airplanes. AD 2017–26–10 required deactivating the spoiler control module (SCM) relays and capping and stowing the associated wiring on certain airplanes. This AD requires repetitive operational tests of the spoiler inhibit function. For certain khammond on DSKJM1Z7X2PROD with RULES SUMMARY: VerDate Sep<11>2014 15:55 Mar 12, 2021 Jkt 253001 airplanes, this AD requires installing a new relay bracket assembly, making changes to the wire bundles for certain SCMs, installing new SCMs, measuring the clearance between a wire bundle and the top of the new relay bracket assembly, and applicable on-condition actions. For a certain other airplane, this AD requires changing certain wire bundles. This AD was prompted by reports of unwanted lateral oscillations during landing operations, and the development of wiring changes for certain SCMs, which will improve the lateral handling qualities of the airplane during approach and landing. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 19, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 19, 2021. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet https://www.myboeingfleet.com. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0903. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0903; 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, 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: Katherine Venegas, Aerospace Engineer, Cabin Safety and Environmental Systems Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5353; fax: 562–627– 5210; email: Katherine.Venegas@ faa.gov. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 14241 Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2017–26–10, Amendment 39–19141 (82 FR 61675, December 29, 2017) (AD 2017–26–10). AD 2017–26–10 applied to certain The Boeing Company Model 757 airplanes. The NPRM published in the Federal Register on October 13, 2020 (85 FR 64419). The NPRM was prompted by reports of unwanted lateral oscillations during landing operations, and the development of wiring changes for certain SCMs, which will improve the lateral handling qualities of the airplane during approach and landing. The NPRM proposed to require repetitive operational tests of the spoiler inhibit function. For certain airplanes, the NPRM proposed to require installing a new relay bracket assembly, making changes to the wire bundles for certain SCMs, installing new SCMs, measuring the clearance between a wire bundle and the top of the new relay bracket assembly, and applicable on-condition actions. For a certain other airplane, the NPRM proposed to require changing certain wire bundles. The FAA is issuing this AD to address unwanted lateral oscillations during landing operations, which could cause overcontrol of the airplane and subsequent lateral pilot induced oscillation, which could affect continued safe flight and landing. Comments The FAA gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Support for the NPRM An anonymous commenter, FedEx Express, and United Airlines (UAL) stated their support for the NPRM. An additional comment from UAL is addressed below. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that the installation of winglets per Supplemental Type Certificate (STC) ST01518SE does not affect the accomplishment of the proposed actions. The FAA agrees with the commenter that STC ST01518SE does not affect the ability to accomplish the actions required by this AD. The FAA has not changed this AD in this regard. E:\FR\FM\15MRR1.SGM 15MRR1

Agencies

[Federal Register Volume 86, Number 48 (Monday, March 15, 2021)]
[Rules and Regulations]
[Pages 14238-14241]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-05144]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0916; Product Identifier 2015-SW-055-AD; Amendment 
39-21449; AD 2021-05-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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[[Page 14239]]

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, EC 
155B, EC155B1, EC225LP, and SA330J helicopters. This AD requires 
inspecting the snap fasteners on the windows. This AD was prompted by 
incidents of difficulty unbuttoning the extraction tape on the windows. 
The actions of this AD are intended to address an unsafe condition on 
these products.

DATES: This AD is effective April 19, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of April 19, 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. It is also available on the 
internet at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2020-0916.

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-
0916; 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 Aviation Safety Agency (now European Union 
Aviation Safety Agency) (EASA) ADs, any service information that is 
incorporated by reference, 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: David Hatfield, Aerospace Engineer, 
Aircraft Systems Section, Technical Innovation Policy Branch, Policy & 
Innovation Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; 
telephone (817) 222-5110; 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 
Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, EC 155B, EC155B1, 
EC225LP, and SA330J helicopters with window extraction tape with snap 
fasteners installed. The NPRM published in the Federal Register on 
October 22, 2020 (85 FR 67313). The NPRM proposed to require inspecting 
each internal and external snap fastener to determine whether they 
unbutton by hand. For external snap fasteners that do not unbutton by 
hand, the NPRM proposed to require replacing the male part of the snap 
fastener and installing self-gripping tape if it still does not 
unbutton by hand. Thereafter, the NPRM proposed to require a repetitive 
inspection of the external extraction tape and self-gripping tape and 
replacing any tape that is cracked, torn, disintegrated, worn, or 
missing, and replacing the snap fasteners. For internal snap fasteners 
that do not unbutton by hand, the NPRM proposed to require installing 
self-gripping tape and replacing the snap fasteners. The proposed 
requirements were intended to prevent failure of a window to jettison, 
preventing occupants from exiting the helicopter during an emergency.
    The NPRM was prompted by EASA AD No. 2015-0149, dated July 23, 2015 
(EASA AD 2015-0149), to correct an unsafe condition for Airbus 
Helicopters Model AS 322 and EC 225 LP helicopters; EASA AD No. 2015-
0168, dated August 13, 2015 (EASA AD 2015-0168), to correct an unsafe 
condition for Airbus Helicopters Model EC 155 B and EC 155 B1 
helicopters; and EASA AD No. 2015-0169, dated August 13, 2015 (EASA AD 
2015-0169), to correct an unsafe condition for Airbus Helicopters Model 
SA330 J helicopters, equipped with an extraction tape fitted with 
``press-studs'' (snap fasteners) on the windows. Each EASA AD was 
issued by EASA, which is the Technical Agent for the Member States of 
the European Union. EASA advises of difficulty unbuttoning the 
extraction tape during the manufacturing of a helicopter. Investigation 
concluded that the difficulty was caused by a bad male/female coupling, 
possibly resulting from miscrimping. This difficulty is known to have 
occurred on two additional helicopters. EASA states this condition, if 
not detected and corrected, could prevent the jettisoning of the 
helicopter window, possibly affecting the evacuation of passengers 
during an emergency situation. For these reasons, EASA AD 2015-0149, 
EASA AD 2015-0168, and EASA AD 2015-0169 require inspecting each press-
stud located on the extraction tapes of the window jettisoning system 
and depending on the findings, installing self-gripping tape and 
replacing the press-studs.

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.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) 
No. AS332-56.00.10, Revision 0, dated July 16, 2015, for Model AS332-
series helicopters; ASB No. EC155-56A006, Revision 0, dated August 10, 
2015, for Model EC155-series helicopters; ASB No. EC225-56A008, 
Revision 0, dated July 16, 2015, for Model EC225LP helicopters; and ASB 
No. SA330-56.02, Revision 0, dated August 10, 2015, for Model SA330J 
helicopters. This service information specifies procedures to inspect 
the internal and external press-studs and to install self-gripping tape 
for press-studs that do not unbutton or are difficult to unbutton. This 
service information also specifies procedures to replace internal 
press-studs that are difficult to unbutton and a repetitive inspection 
for affected external press-studs until they are replaced.
    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.

Costs of Compliance

    The FAA estimates that this AD affects 72 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.

[[Page 14240]]

    Inspecting the snap fasteners takes about 1 work-hour for a cost of 
$85 per helicopter and $6,120 for the U.S. fleet. Installing self-
gripping tape takes about 0.3 work-hour and parts cost $200 for a cost 
of $226 per window. Inspecting the tape takes about 0.3 work-hour for a 
cost of $26 per window per inspection cycle. Replacing the extraction 
tape or self-gripping tape takes about 1 work-hour and parts cost $200 
for a total of $285 per window. Replacing a snap fastener takes about 1 
work-hour and parts cost $200 for a total of $285 per snap fastener.

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:

2021-05-06 Airbus Helicopters: Amendment 39-21449; Docket No. FAA-
2020-0916; Product Identifier 2015-SW-055-AD.

(a) Applicability

    This airworthiness directive (AD) applies to Airbus Helicopters 
Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, EC 155B, EC155B1, 
EC225LP, and SA330J helicopters, certificated in any category, with 
window extraction tape with snap fasteners installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of a snap 
fastener to unbutton. This condition could result in failure of the 
window to jettison, preventing occupants from exiting the helicopter 
during an emergency.

(c) Effective Date

    This AD becomes effective April 19, 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) Required Actions

    Within 50 hours time-in-service (TIS), inspect each internal and 
external snap fastener to determine if it can be unbuttoned by hand.
    Note 1 to the introductory text of paragraph (e): Airbus 
Helicopters refers to the snap fastener as a ``press-stud.''
    (1) If all internal and external snap fasteners can be 
unbuttoned by hand, no further action is required by this AD.
    (2) If an external snap fastener does not unbutton by hand:
    (i) Before further flight, replace the male part of the snap 
fastener and determine if the snap fastener can be unbuttoned by 
hand force. If the snap fastener still does not unbutton by hand, 
before further flight, install self-gripping tape.
    (ii) Thereafter, at intervals not to exceed 15 hours TIS, 
inspect the external extraction tape and self-gripping tape for a 
crack, a tear, disintegration, or wear. If the extraction tape or 
self-gripping tape has a crack, a tear, any disintegration, wear, or 
is missing, before further flight, replace the tape. Replacing the 
extraction tape or self-gripping tape does not terminate this 
repetitive inspection.
    (iii) Within 100 hours TIS, replace each external snap fastener 
by following the Accomplishment Instructions, paragraph 3.B.4., of 
Airbus Helicopters Alert Service Bulletin (ASB) No. AS332-56.00.10, 
Revision 0, dated July 16, 2015 (ASB AS332-56.00.10); ASB No. EC155-
56A006, Revision 0, dated August 10, 2015 (ASB EC155-56A006); ASB 
No. EC225-56A008, Revision 0, dated July 16, 2015 (ASB EC225-
56A008); or ASB No. SA330-56.02, Revision 0, dated August 10, 2015 
(ASB SA330-56.02), as applicable to your model helicopter. Replacing 
the external snap fastener terminates the repetitive inspection 
requirements specified in paragraph (e)(2)(ii) of this AD.
    (3) If an internal snap fastener does not unbutton by hand:
    (i) Before further flight, install self-gripping tape by 
following the Accomplishment Instructions, paragraph 3.B.3., of 
AS332-56.00.10, ASB EC155-56A006, ASB EC225-56A008, or ASB SA330-
56.02, as applicable to your model helicopter.
    (ii) Within 900 hours TIS, replace each internal snap fastener 
by following the Accomplishment Instructions, paragraph 3.B.5., of 
ASB AS332-56.00.10, ASB EC155-56A006, ASB EC225-56A008, or ASB 
SA330-56.02, as applicable to your model helicopter.

(f) 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, send it to the attention of: David 
Hatfield, Aerospace Engineer, Aircraft Systems Section, Technical 
Innovation Policy Branch, Policy & Innovation Division, FAA, 10101 
Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110. 
Information may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(g) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (now European Union Aviation Safety Agency) (EASA) AD No. 
2015-0149, dated July 23, 2015; EASA AD No. 2015-0168, dated August 
13, 2015; and EASA AD No. 2015-0169, dated August 13, 2015. You may 
view the EASA ADs on the internet at https://www.regulations.gov in 
Docket No. FAA-2020-0916.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 5600, Window/
Windshield System.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of

[[Page 14241]]

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 the AD specifies otherwise.
    (i) Airbus Helicopters Alert Service Bulletin (ASB) No. AS332-
56.00.10, Revision 0, dated July 16, 2015.
    (ii) Airbus Helicopters ASB No. EC155-56A006, Revision 0, dated 
August 10, 2015.
    (iii) Airbus Helicopters ASB No. EC225-56A008, Revision 0, dated 
July 16, 2015.
    (iv) Airbus Helicopters ASB No. SA330-56.02, Revision 0, dated 
August 10, 2015.
    (3) 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.
    (4) You may view this service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 
6N-321, Fort Worth, TX 76177. For information on the availability of 
this material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on February 18, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-05144 Filed 3-12-21; 8:45 am]
BILLING CODE 4910-13-P