Airworthiness Directives; Airbus Helicopters Deutschland GmbH (AHD) Helicopters, 20341-20344 [2021-07800]

Download as PDF jbell on DSKJLSW7X2PROD with PROPOSALS Federal Register / Vol. 86, No. 73 / Monday, April 19, 2021 / Proposed Rules safety cable, the correct installation of lock wire 0.20 CRES NAS 33540 P/N MS20995C20 (double-twist lock wire), and any missing double-twist lock wire for each set of upper (connecter) end and lower (pigtail or standpipe) end fasteners of the M/ R slip ring as depicted in Figures 1 and 2 of Annex A to Leonardo Helicopters Alert Service Bulletin (ASB) No. 139–472, dated May 9, 2017 (ASB 139–472), or Leonardo Helicopters ASB No. 189–138, dated May 12, 2017 (ASB 189–138), as applicable to your model helicopter. Figures 2 and 3 of Annex A to ASB 139–472 and ASB 189–138 also show examples of a ferrule ended safety cable installed that are not approved. Note 1 to paragraph (g)(1)(i): Annex A to ASB 139–472 and ASB 189–138 is Moog Service Bulletin No. SB 16–01, Revision 5, undated. (ii) If all of the screws are present, there is not any ferrule ended safety cable installed, the double-twist lock wire is correctly installed, and none of the double-twist lock wire is missing on each set of upper end and lower end fasteners of the M/R slip ring, before further flight, mark the letter ‘‘L’’ following the S/N on the identification label by following the Compliance Instructions, paragraph 3) of Annex A to ASB 139–472 or ASB 189–138, as applicable to your model helicopter. (iii) If a screw is missing from the inner diameter (the connector flange) of the upper end of the M/R slip ring, before further flight, remove the M/R slip ring from service. (iv) If a screw is missing from the outer diameter of the upper end, from the inner diameter of the lower end (shaft extension attachment area), or from the outer diameter of the lower end, before further flight, install a new screw and washer, apply a torque to 1–1.25 Nm, and install double-twist lock wire by following the Compliance Instructions, paragraphs 9)a) through g) of Annex A to ASB 139–472 or ASB 189–138, as applicable to your model helicopter. (v) If any double-twist lock wire is not correctly installed, is missing, or if there is a ferrule ended safety cable installed on any set of upper end or lower end fasters of the M/R slip ring, before further flight, remove the incorrectly installed lock wire or ferrule ended safety cable from service, as applicable, and inspect the fastener torque by applying 1–1.25 Nm of torque. (A) If the torque of a screw installed in the inner diameter (the connector flange) of the upper end of the M/R slip ring is below 1 Nm of torque, do not remove or replace the screw, before further flight, apply a torque of 1–1.25 Nm. (B) If the torque of a screw installed in the outer diameter of the upper end, in the inner diameter of the lower end (shaft extension attachment area), or in the outer diameter of the lower end is below 1 Nm of torque, before further flight, remove the affected screw and washer from service, install a new screw and washer, and apply a torque of 1–1.25 Nm. (C) Install double-twist lock wire by following the Compliance Instructions, paragraphs 9)a) through g) of Annex A to ASB 139–472 or ASB 189–138, as applicable to your model helicopter. (vi) Mark the letter ‘‘L’’ following the S/N on the identification label by following the VerDate Sep<11>2014 16:42 Apr 16, 2021 Jkt 253001 20341 Compliance Instructions, paragraph 3) of Annex A to ASB 139–472 or ASB 189–138, as applicable to your model helicopter. (2) As of the effective date of this AD, do not install an M/R slip ring identified in paragraph (c) of this AD unless the requirements of paragraph (g)(1) have been accomplished. DEPARTMENT OF TRANSPORTATION (h) Special Flight Permits RIN 2120–AA64 Special flight permits are prohibited. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (j)(1) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (j) Related Information (1) For more information about this AD, contact Steven Warwick, Aerospace Engineer, Certification Section, Fort Worth ACO Branch, Compliance & Airworthiness Division, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5225; email steven.r.warwick@faa.gov. (2) Moog Service Bulletin No. SB 16–01, Revision 5, undated, is attached as Annex A to both ASB 139–472 and ASB 189–138. For Leonardo Helicopters and Moog service information identified in this AD, contact Leonardo S.p.A. Helicopters, Emanuele Bufano, Head of Airworthiness, Viale G.Agusta 520, 21017 C.Costa di Samarate (Va) Italy; telephone +39–0331–225074; fax +39–0331–229046; or at https:// www.leonardocompany.com/en/home. 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. For information on the availability of this material at the FAA, call (817) 222–5110. (3) The subject of this AD is addressed in European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 2017–0083, dated May 10, 2017, and EASA AD 2017–0087, dated May 12, 2017. You may view the EASA ADs on the internet at https://www.regulations.gov in the AD Docket. Issued on April 8, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–07666 Filed 4–16–21; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0308; Project Identifier MCAI–2020–00594–R] Airworthiness Directives; Airbus Helicopters Deutschland GmbH (AHD) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH (AHD) Model BO–105A, BO– 105C, BO–105S, and BO–105LS A–3 helicopters equipped with a certain hoist system. This AD was prompted by an uncommanded activation of the hoist cable cutter function on an MBB–BK117 C–1 helicopter, which prompted a design review of the BO105 hoist control grip with coiled cable. This proposed AD would require inspections of the hoist control grip with coiled cable and deactivation of the hoist cuter function, as specified in a European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, which is proposed for incorporation by reference (IBR). 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 June 3, 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 is proposed for IBR in this AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this material on the EASA website at https:// ad.easa.europa.eu. You may view this material at the FAA, Office of the SUMMARY: E:\FR\FM\19APP1.SGM 19APP1 20342 Federal Register / Vol. 86, No. 73 / Monday, April 19, 2021 / Proposed Rules 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. It is also available in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0308. 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–2021– 0308; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, 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 FURTHER INFORMATION CONTACT: Blaine Williams, Aerospace Engineer, Cabin Safety & Environmental Systems Section, Los Angeles ACO Branch, Compliance & Airworthiness Division, 3960 Paramount Blvd., Lakewood, CA 90712; telephone (562) 627–5371; email blaine.williams@faa.gov. SUPPLEMENTARY INFORMATION: jbell on DSKJLSW7X2PROD with PROPOSALS Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2021–0308; Project Identifier MCAI–2020–00594–R’’ at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this proposal because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this 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 VerDate Sep<11>2014 16:42 Apr 16, 2021 Jkt 253001 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 Blaine Williams, Aerospace Engineer, Cabin Safety & Environmental Systems Section, Los Angeles ACO Branch, Compliance & Airworthiness Division, 3960 Paramount Blvd., Lakewood, CA 90712; telephone (562) 627–5371; email blaine.williams@faa.gov. Any commentary that the FAA receives that is not specifically designated as CBI will be placed in the public docket for this rulemaking. Discussion The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2015–0017, dated February 4, 2015 (EASA AD 2015–0017) to correct an unsafe condition for all Airbus Helicopters Deutschland GmbH Model BO105 A, BO105 C, BO105 D, BO105 S and BO105 LS A–3 helicopters. This proposed AD was prompted by uncommanded activation of the hoist cable cutter function on an MBB–BK117 C–1 helicopter which prompted a design review of the BO105 hoist control grip with coiled cable. It was determined that mechanical damage in the harness of the control grip could cause an uncommanded deployment of the cable cutter function. The FAA is proposing this AD to prevent uncommanded cutting of the hoist cable and subsequent injury to persons being lifted by the hoist and injury to persons on the ground. See the EASA AD for additional background information. Related Service Information Under 1 CFR Part 51 For Model BO105 C, BO105 D, BO105 S and BO105 LS A–3 helicopters, EASA AD 2015–0017 specifies to perform an initial and recurring inspections of the hoist control grip with coiled cable of the hoist and depending on the results, replacing the hoist control grip with coiled cable with a serviceable part. EASA also specifies to replace any hoist control grip with coiled cable that has exceeded 10 years since first installation or since last overhaul and to deactivate PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 the cable cutter function in accordance with referenced service information. EASA AD 2015–0017 also specifies to not operate the hoist on any of the model BO105 A, BO105 D, variant BO105 D, and BO105 DS helicopters. For most BO105 model helicopters, except for BO105 D, variant BO105 D, and BO105 DS model helicopters, EASA specifies to amend the helicopter flight manual (FM) to incorporate the temporary revision as specified in Table 1 of the EASA AD. This material is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination and Requirements of This Proposed AD These products have been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to the bilateral agreement with the State of Design Authority, the FAA has been notified of the unsafe condition described in the EASA AD referenced above. The FAA is proposing this AD after evaluating all the relevant information and determining the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in EASA AD 2015–0017, described previously, as incorporated by reference, except for any differences identified as exceptions in the regulatory text of this proposed AD and except as discussed under ‘‘Differences Between this Proposed AD and the EASA AD.’’ Additionally, the owner/ operator (pilot) may perform the required visual checks but must enter compliance with the applicable paragraph of this AD in the helicopter maintenance records in accordance with 14 CFR 43.9(a)(1) through (4) and 91.417(a)(2)(v). A pilot may perform these checks because they only involve visually checking affected control grips with coiled cable. This action can be performed equally well by a pilot or a mechanic. This check is an exception to the FAA’s standard maintenance regulations. Explanation of Required Compliance Information In the FAA’s ongoing efforts to improve the efficiency of the AD process, the FAA initially worked with Airbus and EASA to develop a process to use certain EASA ADs as the primary E:\FR\FM\19APP1.SGM 19APP1 Federal Register / Vol. 86, No. 73 / Monday, April 19, 2021 / Proposed Rules source of information for compliance with requirements for corresponding FAA ADs. The FAA has since coordinated with other manufacturers and civil aviation authorities (CAAs) to use this process. As a result, EASA AD 2015–0017 will be incorporated by reference in the FAA final rule. This proposed AD would, therefore, require compliance with EASA AD 2015–0017 in its entirety, through that incorporation, except for any differences identified as exceptions in the regulatory text of this proposed AD. Using common terms that are the same as the heading of a particular section in the EASA AD does not mean that operators need comply only with that section. For example, where the AD requirement refers to ‘‘all required actions and compliance times,’’ compliance with this AD requirement is not limited to the section titled ‘‘Required Action(s) and Compliance Time(s)’’ in the EASA AD. Service information specified in EASA AD 2015–0017 that is required for compliance with EASA AD 2015–0017 will be available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0308 after the FAA final rule is published. jbell on DSKJLSW7X2PROD with PROPOSALS Differences Between This Proposed AD and the EASA AD Where EASA AD 2015–0017 refers to its effective date, this proposed AD requires using the effective date of the FAA AD. Where EASA AD 2015–0017 specifies this unsafe condition for Airbus Helicopters Deutschland GmbH Model BO105 A, BO105 C, BO105 D, BO105 S and BO105 LS A–3 helicopters, this proposed AD will not include Model BO–105 D helicopters, because this model is not FAA typecertificated. Where EASA AD 2015– 0017 specifies replacing an affected part, this proposed AD requires removing the part from service. Where the service information referenced in the EASA AD refers to calendar time for certain actions, this proposed AD uses hours time-in-service instead. The EASA AD allows a tolerance to certain compliance times, whereas this proposed AD does not. The EASA AD requires using service information to accomplish the preflight checks of the control grip with coil cable, whereas this proposed AD would require visually checking the condition of the control grip and coiled cable for mechanical damage including deformed or damaged switches, damaged housing, abrasion, cracks, and cuts instead. VerDate Sep<11>2014 16:42 Apr 16, 2021 Jkt 253001 Interim Action The FAA considers this proposed AD interim action. If final action is later identified, the FAA might consider further rulemaking then. Costs of Compliance The FAA estimates that this AD affects 20 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 proposed AD. Inspecting the hoist control grip with coiled cable would take up to one quarter work-hour(s) for an estimated cost of $21 per helicopter and $420 for the U.S. fleet, per inspection cycle. Replacing the hoist control grip would take about 1 work-hour and parts cost $1,956 for an estimated cost of $2,041 per helicopter. Replacing the coiled cable would take about 2 work-hours and parts cost $1,858 for an estimated cost of $2,028 per helicopter. Deactivation of the cable cutter function would take about 1 work hour and parts would cost about $26 for an estimated cost $111 per hoist control grip. 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. PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 20343 For the reasons discussed above, 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: ■ 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: ■ Airbus Helicopters Deutschland GmbH (AHD): Docket No. FAA–2021–0308; Project Identifier MCAI–2020–00594–R. (a) Comments Due Date The FAA must receive comments by June 3, 2021. (b) Affected Airworthiness Directives (ADs) None. (c) Applicability This AD applies to Airbus Helicopters Deutschland GmbH (AHD) Model BO–105A, BO–105C, BO–105S, and BO–105LS A–3 helicopters, certificated in any category, as identified in European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 2015–0017 dated February 4, 2015 (EASA AD 2015–0017). (d) Subject Joint Aircraft System Component (JASC) Code: 2500, Cabin Equipment/Furnishings. (e) Reason This AD was prompted by uncommanded activation of the hoist cable cutter function on an MBB–BK117 C–1 helicopter which prompted a design review of the BO105 hoist control grip with coiled cable. The FAA is issuing this AD to prevent uncommanded cutting of the hoist cable and subsequent injury to persons being lifted by the hoist and injury to persons on the ground. (f) Compliance Comply with this AD within the compliance times specified, unless already done. E:\FR\FM\19APP1.SGM 19APP1 jbell on DSKJLSW7X2PROD with PROPOSALS 20344 Federal Register / Vol. 86, No. 73 / Monday, April 19, 2021 / Proposed Rules (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2015–0017. (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. (h) Exceptions to EASA AD 2015–0017 (1) Where EASA AD 2015–0017 refers to its effective date, this AD requires using the effective date of this AD. (2) Where Note 1 of EASA AD 2015–0017 specifies a non-cumulative compliance time tolerance of 10% for certain required compliance times, this AD does not allow this tolerance. (3) Where paragraph (1) of EASA AD 2015– 0017 specifies a compliance time of ‘‘not to exceed 30 days’’, this AD requires a compliance time of within 13 hours time-inservice. (4) Where paragraph (4) of EASA AD 2015– 0017 specifies a compliance time of ‘‘within 9 months’’, this AD requires a compliance time of within 108 hours time-in-service. (5) Where paragraph (5) of EASA AD 2015– 0017 specifies a compliance time of ‘‘within 3 months’’, this AD requires a compliance time of within 36 hours time-in-service. (6) Where paragraph (3) of EASA AD 2015– 0017 specifies replacing a part with a serviceable part, this AD requires removing the part from service. (7) Where the service information referenced in EASA AD 2015–0017 specifies to use tooling, equivalent tooling may be used. (8) Where the service information referenced in paragraph (2) of EASA AD 2015–0017 specifies a visual check of the control grip coiled cable, this AD requires, before next flight after the effective date of this AD involving a hoist operation, visually checking the control grip with coiled cable for mechanical damage including deformed or damaged switches, damaged housing, abrasion, cracks, and cuts. These visual checks may be performed by the owner/ operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9(a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. (9) Where EASA AD 2015–0017 refers to November 10, 2014, the effective date of EASA AD 2014–0235, this AD requires using the effective date of this AD. (10) The ‘‘Remarks’’ section of EASA AD 2015–0017 does not apply to this AD. (j) Related Information (1) For EASA AD 2015–0017, 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–2021–0308. (2) For more information about this AD, contact Blaine Williams, Aerospace Engineer, Cabin Safety & Environmental Systems Section, Los Angeles ACO Branch, Compliance & Airworthiness Division, 3960 Paramount Blvd., Lakewood, CA 90712; telephone (562) 627–5371; email blaine.williams@faa.gov. Issued on April 12, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (j)(2) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. VerDate Sep<11>2014 16:42 Apr 16, 2021 Jkt 253001 [FR Doc. 2021–07800 Filed 4–16–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Coast Guard 33 CFR Part 117 [Docket No. USCG–2019–0824] RIN 1625–AA09 Drawbridge Operation Regulation; Milwaukee, Menomonee, and Kinnickinnic Rivers and Burnham Canals, Milwaukee, WI Coast Guard, DHS. Notice of proposed rulemaking. AGENCY: ACTION: The Coast Guard proposes to change the operating schedules of the bridges over the Milwaukee, Menomonee, and Kinnickinnic Rivers and South Menomonee and Burnham Canals. The City of Milwaukee requested the regulations to be reviewed and updated to allow for a more balanced flow of maritime and land based transportation. DATES: Comments and relate material must reach the Coast Guard on or before June 18, 2021. ADDRESSES: You may submit comments identified by docket number USCG– SUMMARY: PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 2019–0824 using Federal e-Rulemaking Portal at https://www.regulations.gov. See the ‘‘Public Participation and Request for Comments’’ portion of the SUPPLEMENTARY INFORMATION section below for instructions on submitting comments. If you have questions on this proposed rule, call or email Mr. Lee D. Soule, Bridge Management Specialist, Ninth Coast Guard District; telephone 216– 902–6085, email Lee.D.Soule@uscg.mil. SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT: I. Table of Abbreviations CFR Code of Federal Regulations DHS Department of Homeland Security FR Federal Register IGLD85 International Great Lakes Datum of 1985 LWD Low Water Datum based on IGLD85 OMB Office of Management and Budget NPRM Notice of Proposed Rulemaking (Advance, Supplemental) § Section U.S.C. United States Code II. Background, Purpose and Legal Basis The Milwaukee River is approximately 104 miles long. Beginning in Fond du Lac County the river flows easterly to a low head dam just above the Humboldt Avenue Bridge at mile 3.22 in downtown Milwaukee, WI. From here the river flows south to Lake Michigan. This southerly course of the Milwaukee River divides the lakefront area from the rest of the city. The Menomonee River joins the Milwaukee River at Mile 1.01 with the Kinnickinnic River joining the Milwaukee River at Mile 0.39. 21 bridges cross the Milwaukee River from mile 0.19 to mile 3.22. In the early 20th Century, the Milwaukee River was heavily used to support the industries in and around the Great Lakes. Today, the river has been redeveloped as a tourist and recreational destination. From its confluence with the Milwaukee River the Menomonee River flows west for 33 miles. The lower three miles of the Menomonee River is passable by vessels over 600 feet in length. Seven bridges cross the navigable portion of the Menomonee River. The South Menomonee Canal and the Burnham Canal were both excavated during a waterways improvement project in 1864. Both man-made canals are tributaries of the Menomonee River branching just above its mouth. The South Menomonee Canal is crossed by two bridges and the Burnham Canal is crossed by three bridges. The Kinnickinnic River flows north through the southern portion of the City of E:\FR\FM\19APP1.SGM 19APP1

Agencies

[Federal Register Volume 86, Number 73 (Monday, April 19, 2021)]
[Proposed Rules]
[Pages 20341-20344]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-07800]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0308; Project Identifier MCAI-2020-00594-R]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
(AHD) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Airbus Helicopters Deutschland GmbH (AHD) Model BO-105A, 
BO-105C, BO-105S, and BO-105LS A-3 helicopters equipped with a certain 
hoist system. This AD was prompted by an uncommanded activation of the 
hoist cable cutter function on an MBB-BK117 C-1 helicopter, which 
prompted a design review of the BO105 hoist control grip with coiled 
cable. This proposed AD would require inspections of the hoist control 
grip with coiled cable and deactivation of the hoist cuter function, as 
specified in a European Aviation Safety Agency (now European Union 
Aviation Safety Agency) (EASA) AD, which is proposed for incorporation 
by reference (IBR). 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 June 3, 
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 is proposed for IBR in this AD, contact the EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 
000; email [email protected]; internet www.easa.europa.eu. You may 
find this material on the EASA website at https://ad.easa.europa.eu. 
You may view this material at the FAA, Office of the

[[Page 20342]]

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. It is also available in the AD 
docket on the internet at https://www.regulations.gov by searching for 
and locating Docket No. FAA-2021-0308.

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-2021-
0308; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this NPRM, 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 FURTHER INFORMATION CONTACT: Blaine Williams, Aerospace Engineer, 
Cabin Safety & Environmental Systems Section, Los Angeles ACO Branch, 
Compliance & Airworthiness Division, 3960 Paramount Blvd., Lakewood, CA 
90712; telephone (562) 627-5371; 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-2021-0308; Project Identifier 
MCAI-2020-00594-R'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this 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 
Blaine Williams, Aerospace Engineer, Cabin Safety & Environmental 
Systems Section, Los Angeles ACO Branch, Compliance & Airworthiness 
Division, 3960 Paramount Blvd., Lakewood, CA 90712; telephone (562) 
627-5371; email [email protected]. Any commentary that the FAA 
receives that is not specifically designated as CBI will be placed in 
the public docket for this rulemaking.

Discussion

    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2015-0017, dated February 4, 2015 
(EASA AD 2015-0017) to correct an unsafe condition for all Airbus 
Helicopters Deutschland GmbH Model BO105 A, BO105 C, BO105 D, BO105 S 
and BO105 LS A-3 helicopters.
    This proposed AD was prompted by uncommanded activation of the 
hoist cable cutter function on an MBB-BK117 C-1 helicopter which 
prompted a design review of the BO105 hoist control grip with coiled 
cable. It was determined that mechanical damage in the harness of the 
control grip could cause an uncommanded deployment of the cable cutter 
function. The FAA is proposing this AD to prevent uncommanded cutting 
of the hoist cable and subsequent injury to persons being lifted by the 
hoist and injury to persons on the ground. See the EASA AD for 
additional background information.

Related Service Information Under 1 CFR Part 51

    For Model BO105 C, BO105 D, BO105 S and BO105 LS A-3 helicopters, 
EASA AD 2015-0017 specifies to perform an initial and recurring 
inspections of the hoist control grip with coiled cable of the hoist 
and depending on the results, replacing the hoist control grip with 
coiled cable with a serviceable part. EASA also specifies to replace 
any hoist control grip with coiled cable that has exceeded 10 years 
since first installation or since last overhaul and to deactivate the 
cable cutter function in accordance with referenced service 
information.
    EASA AD 2015-0017 also specifies to not operate the hoist on any of 
the model BO105 A, BO105 D, variant BO105 D, and BO105 DS helicopters. 
For most BO105 model helicopters, except for BO105 D, variant BO105 D, 
and BO105 DS model helicopters, EASA specifies to amend the helicopter 
flight manual (FM) to incorporate the temporary revision as specified 
in Table 1 of the EASA AD.
    This material is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

    These products have been approved by the aviation authority of 
another country, and is approved for operation in the United States. 
Pursuant to the bilateral agreement with the State of Design Authority, 
the FAA has been notified of the unsafe condition described in the EASA 
AD referenced above. The FAA is proposing this AD after evaluating all 
the relevant information and determining the unsafe condition described 
previously is likely to exist or develop in other products of these 
same type designs.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in EASA AD 2015-0017, described previously, as incorporated by 
reference, except for any differences identified as exceptions in the 
regulatory text of this proposed AD and except as discussed under 
``Differences Between this Proposed AD and the EASA AD.'' Additionally, 
the owner/operator (pilot) may perform the required visual checks but 
must enter compliance with the applicable paragraph of this AD in the 
helicopter maintenance records in accordance with 14 CFR 43.9(a)(1) 
through (4) and 91.417(a)(2)(v). A pilot may perform these checks 
because they only involve visually checking affected control grips with 
coiled cable. This action can be performed equally well by a pilot or a 
mechanic. This check is an exception to the FAA's standard maintenance 
regulations.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA initially worked with Airbus and EASA to develop a 
process to use certain EASA ADs as the primary

[[Page 20343]]

source of information for compliance with requirements for 
corresponding FAA ADs. The FAA has since coordinated with other 
manufacturers and civil aviation authorities (CAAs) to use this 
process. As a result, EASA AD 2015-0017 will be incorporated by 
reference in the FAA final rule. This proposed AD would, therefore, 
require compliance with EASA AD 2015-0017 in its entirety, through that 
incorporation, except for any differences identified as exceptions in 
the regulatory text of this proposed AD. Using common terms that are 
the same as the heading of a particular section in the EASA AD does not 
mean that operators need comply only with that section. For example, 
where the AD requirement refers to ``all required actions and 
compliance times,'' compliance with this AD requirement is not limited 
to the section titled ``Required Action(s) and Compliance Time(s)'' in 
the EASA AD. Service information specified in EASA AD 2015-0017 that is 
required for compliance with EASA AD 2015-0017 will be available on the 
internet at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2021-0308 after the FAA final rule is published.

Differences Between This Proposed AD and the EASA AD

    Where EASA AD 2015-0017 refers to its effective date, this proposed 
AD requires using the effective date of the FAA AD. Where EASA AD 2015-
0017 specifies this unsafe condition for Airbus Helicopters Deutschland 
GmbH Model BO105 A, BO105 C, BO105 D, BO105 S and BO105 LS A-3 
helicopters, this proposed AD will not include Model BO-105 D 
helicopters, because this model is not FAA type-certificated. Where 
EASA AD 2015-0017 specifies replacing an affected part, this proposed 
AD requires removing the part from service. Where the service 
information referenced in the EASA AD refers to calendar time for 
certain actions, this proposed AD uses hours time-in-service instead. 
The EASA AD allows a tolerance to certain compliance times, whereas 
this proposed AD does not. The EASA AD requires using service 
information to accomplish the preflight checks of the control grip with 
coil cable, whereas this proposed AD would require visually checking 
the condition of the control grip and coiled cable for mechanical 
damage including deformed or damaged switches, damaged housing, 
abrasion, cracks, and cuts instead.

Interim Action

    The FAA considers this proposed AD interim action. If final action 
is later identified, the FAA might consider further rulemaking then.

Costs of Compliance

    The FAA estimates that this AD affects 20 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 proposed AD.
    Inspecting the hoist control grip with coiled cable would take up 
to one quarter work-hour(s) for an estimated cost of $21 per helicopter 
and $420 for the U.S. fleet, per inspection cycle.
    Replacing the hoist control grip would take about 1 work-hour and 
parts cost $1,956 for an estimated cost of $2,041 per helicopter.
    Replacing the coiled cable would take about 2 work-hours and parts 
cost $1,858 for an estimated cost of $2,028 per helicopter.
    Deactivation of the cable cutter function would take about 1 work 
hour and parts would cost about $26 for an estimated cost $111 per 
hoist control grip.

Authority for This Rulemaking

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

Regulatory Findings

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

    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:

Airbus Helicopters Deutschland GmbH (AHD): Docket No. FAA-2021-0308; 
Project Identifier MCAI-2020-00594-R.

(a) Comments Due Date

    The FAA must receive comments by June 3, 2021.

(b) Affected Airworthiness Directives (ADs)

    None.

(c) Applicability

    This AD applies to Airbus Helicopters Deutschland GmbH (AHD) 
Model BO-105A, BO-105C, BO-105S, and BO-105LS A-3 helicopters, 
certificated in any category, as identified in European Aviation 
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 
2015-0017 dated February 4, 2015 (EASA AD 2015-0017).

(d) Subject

    Joint Aircraft System Component (JASC) Code: 2500, Cabin 
Equipment/Furnishings.

(e) Reason

    This AD was prompted by uncommanded activation of the hoist 
cable cutter function on an MBB-BK117 C-1 helicopter which prompted 
a design review of the BO105 hoist control grip with coiled cable. 
The FAA is issuing this AD to prevent uncommanded cutting of the 
hoist cable and subsequent injury to persons being lifted by the 
hoist and injury to persons on the ground.

(f) Compliance

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

[[Page 20344]]

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, EASA AD 2015-0017.

(h) Exceptions to EASA AD 2015-0017

    (1) Where EASA AD 2015-0017 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where Note 1 of EASA AD 2015-0017 specifies a non-cumulative 
compliance time tolerance of 10% for certain required compliance 
times, this AD does not allow this tolerance.
    (3) Where paragraph (1) of EASA AD 2015-0017 specifies a 
compliance time of ``not to exceed 30 days'', this AD requires a 
compliance time of within 13 hours time-in-service.
    (4) Where paragraph (4) of EASA AD 2015-0017 specifies a 
compliance time of ``within 9 months'', this AD requires a 
compliance time of within 108 hours time-in-service.
    (5) Where paragraph (5) of EASA AD 2015-0017 specifies a 
compliance time of ``within 3 months'', this AD requires a 
compliance time of within 36 hours time-in-service.
    (6) Where paragraph (3) of EASA AD 2015-0017 specifies replacing 
a part with a serviceable part, this AD requires removing the part 
from service.
    (7) Where the service information referenced in EASA AD 2015-
0017 specifies to use tooling, equivalent tooling may be used.
    (8) Where the service information referenced in paragraph (2) of 
EASA AD 2015-0017 specifies a visual check of the control grip 
coiled cable, this AD requires, before next flight after the 
effective date of this AD involving a hoist operation, visually 
checking the control grip with coiled cable for mechanical damage 
including deformed or damaged switches, damaged housing, abrasion, 
cracks, and cuts. These visual checks may be performed by the owner/
operator (pilot) holding at least a private pilot certificate and 
must be entered into the aircraft records showing compliance with 
this AD in accordance with 14 CFR 43.9(a)(1) through (4) and 14 CFR 
91.417(a)(2)(v). The record must be maintained as required by 14 CFR 
91.417, 121.380, or 135.439.
    (9) Where EASA AD 2015-0017 refers to November 10, 2014, the 
effective date of EASA AD 2014-0235, this AD requires using the 
effective date of this AD.
    (10) The ``Remarks'' section of EASA AD 2015-0017 does not apply 
to this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Validation Branch, send 
it to the attention of the person identified in paragraph (j)(2) of 
this AD. Information may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(j) Related Information

    (1) For EASA AD 2015-0017, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email 
[email protected]; 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-2021-0308.
    (2) For more information about this AD, contact Blaine Williams, 
Aerospace Engineer, Cabin Safety & Environmental Systems Section, 
Los Angeles ACO Branch, Compliance & Airworthiness Division, 3960 
Paramount Blvd., Lakewood, CA 90712; telephone (562) 627-5371; email 
[email protected].

    Issued on April 12, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.

[FR Doc. 2021-07800 Filed 4-16-21; 8:45 am]
BILLING CODE 4910-13-P