Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters, 28476-28479 [2021-11080]

Download as PDF 28476 Federal Register / Vol. 86, No. 101 / Thursday, May 27, 2021 / Rules and Regulations cycles per hour TIS, the IFWU assembly is an REL IFWU assembly. (ii) If any calculation specified in paragraph (h)(2) of this AD results in 6 or less lift cycles per hour TIS, the IFWU assembly is a Non-REL IFWU assembly. Note 1 to paragraph (h)(2): Sikorsky Aircraft Corporation All Operators Letter (AOL) CCS–61–AOL–04–0005, dated May 18, 2004, provides an example and additional information about tracking cycles and the moving average procedure. jbell on DSKJLSW7X2PROD with RULES Note 2 to paragraph (h)(2): The following is a sample calculation for subsequent 50 hour TIS intervals. Assume the total number of lift cycles for the first 50 hour TIS interval used in the previous moving average calculation = 450 lift cycles and the total number of lift cycles for the previous 300 hours TIS = 2,700 lift cycles. The subsequent moving average of lift cycles per hour TIS = (2,700¥450) divided by 250 = 9 lift cycles per hour TIS. (3) Once an IFWU assembly is determined to be an REL IFWU assembly, it remains an REL IFWU assembly for the rest of its service life and is subject to the inspection for REL IFWU assemblies required by paragraph (i) of this AD. (4) Once an IFWU assembly is determined to be an REL IFWU assembly, you no longer need to perform the 250-hour TIS moving average calculation required by paragraph (h)(2) of this AD, but you must continue to count and record the lift cycles as required by paragraph (g)(2) of this AD. (i) Repetitive Inspections of REL IFWU Assemblies and Replacement For each REL IFWU assembly, as determined by paragraph (h)(1) or (2) of this AD: (1) Within 500 hours TIS or 7,500 lift cycles, whichever occurs first since the assembly was determined to be a REL IFWU assembly, and thereafter at intervals not to exceed 500 hours TIS or 7,500 lift cycles, whichever occurs first, inspect for wear, surface distress, and endplay by following paragraphs B.(1) through B.(6) of the Accomplishment Instructions of Sikorsky Aircraft Corporation Alert Service Bulletin 61B35–67B, Revision B, dated August 11, 2003. Record all the information specified in Figures 1 through 3 of the Sikorsky Aircraft Corporation Alert Service Bulletin 61B35– 67B, Revision B, dated August 11, 2003. You may record this information on any suitable maintenance record, or you may use the Sikorsky evaluation forms provided in Sikorsky Aircraft Corporation Alert Service Bulletin 61B35–67B, Revision B, dated August 11, 2003. This AD does not require you to contact Sikorsky or provide information to Sikorsky. (2) If during any inspection required by paragraph (i)(1) of this AD, any IFWU assembly part is found whose average wear, wear marks, surface distress, or endplay exceeds the limits specified in paragraphs B.(1) through B.(6) of the Accomplishment Instructions of Sikorsky Aircraft Corporation Alert Service Bulletin 61B35–67B, Revision B, dated August 11, 2003, before further flight, replace the affected part with an airworthy IFWU assembly part. VerDate Sep<11>2014 16:14 May 26, 2021 Jkt 253001 Note 3 to paragraph (i)(2): Sikorsky Aircraft S–61L/N Overhaul Manual, SA4045– 83, Revision 20, dated August 15, 2003, as revised by Temporary Revisions 65–193, –194, –195, and –196, contains the overhaul procedures for the IFWU assembly. (j) Part Marking For each REL IFWU assembly, as determined by paragraph (h)(1) or (2) of this AD: Before further flight after the assembly was determined to be an REL IFWU assembly, permanently mark IFWU camshafts, P/N 61350–24052, 61350–24072, S6135–20611, S6135–20614 and S6137– 23075, and IFWU gear housings, P/N 61350– 24051, 61350–24068, S6135–20695, and S6137–23057, with the letters ‘‘REL’’. Mark the camshafts by applying etching ink on the surface of the part that is 0.5-inch square with the depth of the letters not to exceed 0.001 inch. Before further flight and after etching, neutralize the etched surface and oil to prevent corrosion. (k) 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 (l)(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. (l) Related Information (1) For more information about this AD, contact Isabel Saltzman, Aviation Safety Engineer, Boston ACO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; telephone 781–238–7649; email Isabel.L.Saltzman@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (4) of this AD. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Sikorsky Aircraft Corporation Alert Service Bulletin 61B35–67B, Revision B, dated August 11, 2003. (ii) [Reserved] (3) For service information identified in this AD, contact your local Sikorsky Field Representative or Sikorsky’s Service Engineering Group at Sikorsky Aircraft Corporation, 124 Quarry Road, Trumbull, CT PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 06611; telephone 1–800-Winged-S; email wcs_cust_service_eng.gr-sik@lmco.com. Operators may also log on to the Sikorsky 360 website at https://www.sikorsky360.com. (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/ ibr-locations.html. Issued on May 4, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–11081 Filed 5–26–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–1171; Product Identifier 2017–SW–124–AD; Amendment 39–21548; AD 2021–10–15] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH Model MBB–BK 117 C–2 and Model MBB–BK 117 D–2 helicopters. This AD was prompted by a determination that a life limit for the adapter forward (FWD) of the outboard load system, repetitive inspections of other components of that system, and for certain helicopters, a modification of the outboard load system, are necessary to address the unsafe condition. This AD requires a modification of the outboard load system for certain helicopters, repetitive inspections of the outboard load system and its components for any defect (including cracking, damage, corrosion, and incorrect installation) and applicable corrective actions, and implementation of a new life limit for the FWD adapter, as specified in a European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, which is SUMMARY: E:\FR\FM\27MYR1.SGM 27MYR1 Federal Register / Vol. 86, No. 101 / Thursday, May 27, 2021 / Rules and Regulations incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 1, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 1, 2021. ADDRESSES: For material incorporated by reference (IBR) in this AD, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@ easa.europa.eu; internet www.easa.europa.eu. You may find this material 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. It is also available in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–1171. 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– 1171; 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: Kathleen Arrigotti, Program Manager, Large Aircraft Section, International Validation Branch, Compliance & Airworthiness Division, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3218; email kathleen.arrigotti@faa.gov. SUPPLEMENTARY INFORMATION: Background jbell on DSKJLSW7X2PROD with RULES The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017–0177, dated September 14, 2017 (EASA AD 2017–0177) (also referred to as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for all Airbus Helicopters Deutschland GmbH Model MBB–BK 117 C–2 helicopters, except the Model C–2e variant, and all Model MBB–BK 117 D–2 helicopters. EASA’s Model MBB–BK 117 C–2e variant helicopters are not a unique model on the U.S. type certificate but are considered a configuration of the Model MBB–BK117 C–2. The U.S. type certificate data sheet explains that the FAA determined that the type design changes involved did not rise to the level that required an FAA amended type certificate. However, the FAA does recognize that helicopters with these type design changes exist, therefore the designation Model MBB–BK117 C–2(e) is used, starting from Serial Number 9601. The Model MBB–BK117 C–2(e) is a visual flight rules only configuration of the Model MBB–BK117 C–2 utilizing a Garmin 500H flight display system. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Helicopters Deutschland GmbH Model MBB–BK 117 C–2 and Model MBB–BK 117 D–2 helicopters, except the Model MBB– BK117 C–2(e) configuration. The NPRM published in the Federal Register on March 11, 2021 (86 FR 13830). The NPRM was prompted by a determination that a life limit for the adapter FWD of the outboard load system, repetitive inspections of other components of that system, and for certain helicopters, a modification of the outboard load system, are necessary to address the unsafe condition. The NPRM proposed to require a modification of the outboard load system for certain helicopters, repetitive inspections of the outboard load system and its components for any defect (including cracking, damage, corrosion, and incorrect installation) and applicable corrective actions, and implementation of a new life limit for the FWD adapter, as specified in an EASA AD. The FAA is issuing this AD to address detachment of an external load or person from the helicopter hoist, resulting in personal injury, or injury to persons on the ground. See the MCAI for additional background information. 28477 Discussion of Final Airworthiness Directive Comments The FAA gave the public the opportunity to participate in developing this final rule. The FAA received no comments on the NPRM or on the determination of the cost to the public. Costs of Compliance Update The NPRM had specified no definitive data was available for the costs of the modification and certain parts. The FAA has received data on the costs of the modification and parts and has updated the costs of compliance accordingly. Conclusion The FAA reviewed the relevant data and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes and a change to paragraph (i)(1) of this AD. The FAA has determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 EASA AD 2017–0177 describes procedures for modification of the outboard load system for certain Model MBB–BK 117 C–2 helicopters, repetitive inspections of the outboard load system and its components for any defect (including cracking, damage, corrosion, and incorrect installation) and corrective actions, and implementation of a new life limit for the FWD adapter (i.e., repetitive replacements). The corrective actions include replacement of any defective component with a serviceable part. 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. Costs of Compliance The FAA estimates that this AD affects 175 helicopters of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Parts cost Cost per product Cost on U.S. operators 4 work-hours × $85 per hour = $340 .......................................................................................... $2,276 $2,616 $457,800 VerDate Sep<11>2014 16:14 May 26, 2021 Jkt 253001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\27MYR1.SGM 27MYR1 28478 Federal Register / Vol. 86, No. 101 / Thursday, May 27, 2021 / Rules and Regulations The FAA estimates the following costs to do any necessary on-condition actions that would be required based on the results of any required actions. The FAA has no way of determining the number of helicopters that might need these on-condition actions: ESTIMATED COSTS OF ON-CONDITION ACTION Labor cost Parts cost 2 work-hours × $85 per hour = $170 ...................................................................................................................... Up to $970 ..... According to the manufacturer, some or all of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected operators. The FAA does not control warranty coverage for affected operators. As a result, the FAA has included all known costs in the cost estimate. 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. jbell on DSKJLSW7X2PROD 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. VerDate Sep<11>2014 16:14 May 26, 2021 Jkt 253001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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: ■ 2021–10–15 Airbus Helicopters Deutschland GmbH: Amendment 39– 21548; Docket No. FAA–2020–1171; Product Identifier 2017–SW–124–AD. (a) Effective Date This airworthiness directive (AD) is effective July 1, 2021. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Helicopters Deutschland GmbH Model MBB–BK 117 C–2 and Model MBB–BK 117 D–2 helicopters, certificated in any category, all manufacturer serial numbers, except the Model MBB–BK117 C–2(e) configuration. Note 1 to paragraph (c): Model MBB– BK117 C–2 helicopters utilizing a Garmin 500H flight display system are designated by EASA as Model MBB–BK117 C–2e variants of the Model BK 117 C–2 helicopters, and by the FAA as a Model MBB–BK117 C–2(e) configuration. (d) Subject Joint Aircraft System Component (JASC) Code 2500, Cabin Equipment/Furnishings. (e) Reason This AD was prompted by a determination that a life limit for the adapter forward of the outboard load system, repetitive inspections of other components of that system, and for certain helicopters, a modification of the outboard load system, are necessary to PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Cost per product Up to $1,140. address the unsafe condition. The FAA is issuing this AD to address detachment of an external load or person from the helicopter hoist, which could result in personal injury, or injury to persons on the ground. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (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, European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 2017–0177, dated September 14, 2017 (EASA AD 2017–0177). (h) Exceptions to EASA AD 2017–0177 (1) Where EASA AD 2017–0177 refers to its effective date, this AD requires using the effective date of this AD. (2) The ‘‘Remarks’’ section of EASA AD 2017–0177 does not apply to this AD. (3) Where the service information referenced in EASA AD 2017–0177 specifies contacting the applicable manufacturer of the dedicated equipment for a definition of a cycle and recalculation to hoist cycles, this AD does not require contacting the manufacturer for a definition of a cycle and recalculation to hoist cycles. (4) Where paragraph (3) of EASA AD 2017– 0177 specifies to do ‘‘applicable corrective actions,’’ for this AD, if there are any defective components, replace all defective components with serviceable components in accordance with FAA-approved procedures. For the purposes of this AD, a defect may be indicated by cracking, damage, corrosion, or incorrect installation. (5) Although the service information referenced in EASA AD 2017–0177 specifies to discard certain parts, this AD requires removing those parts from service instead. (6) Where the service information referenced in EASA AD 2017–0177 refers to flight hours (FH), this AD requires using hours time-in-service. (7) Paragraph (9) of EASA AD 2017–0177 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 E:\FR\FM\27MYR1.SGM 27MYR1 Federal Register / Vol. 86, No. 101 / Thursday, May 27, 2021 / Rules and Regulations to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (j) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. (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. DEPARTMENT OF TRANSPORTATION (j) Related Information Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes For more information about this AD, contact Kathleen Arrigotti, Program Manager, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3218; email: kathleen.arrigotti@ faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) European Aviation Safety Agency (EASA) AD 2017–0177, dated September 14, 2017. (ii) [Reserved] (3) For EASA AD 2017–0177, 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. (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. This material may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–1171. (5) You may view this material that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@ nara.gov, or go to https://www.archives.gov/ federal-register/cfr/ibr-locations.html. Issued on May 3, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. jbell on DSKJLSW7X2PROD with RULES [FR Doc. 2021–11080 Filed 5–26–21; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:14 May 26, 2021 Jkt 253001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0018; Project Identifier MCAI–2020–01214–T; Amendment 39–21546; AD 2021–10–13] RIN 2120–AA64 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: 28479 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: Siddeeq Bacchus, Aerospace Engineer, Mechanical Systems and Administrative Services Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7362; fax 516–794–5531; email 9-avs-nyaco-cos@faa.gov. SUPPLEMENTARY INFORMATION: The FAA is superseding Airworthiness Directive (AD) 2015–17– 08, which applied to certain Bombardier, Inc. Model DHC–8–400 series airplanes. AD 2015–17–08 required installing new cable assemblies with a pull-down resistor. This AD requires modifications to the nose wheel steering (NWS) system. This AD was prompted by a report indicating that several failure modes of the NWS system may cause the loss of feedback from both rotary variable differential transformers to the steering control unit. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 1, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 1, 2021. ADDRESSES: For service information identified in this final rule, contact De Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375– 4000; fax 416–375–4539; email thd@ dehavilland.com; internet https:// dehavilland.com. You may view this referenced 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 on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0018. Discussion Examining the AD Docket Comments You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 0018; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday The FAA gave the public the opportunity to participate in developing this final rule. The FAA has considered the comment received. The Air Line Pilots Association, International (ALPA) indicated its support for the NPRM. SUMMARY: PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued TCCA AD CF– 2020–28, dated August 14, 2020 (also referred to as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for certain De Havilland Aircraft of Canada Limited Model DHC–8–401 and –402 airplanes. You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0018. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2015–17–08, Amendment 39–18241 (80 FR 51459, August 25, 2015) (AD 2015–17–08). AD 2015–17–08 applied to certain Bombardier, Inc. Model DHC–8–400 series airplanes. The NPRM published in the Federal Register on February 24, 2021 (86 FR 11175). The NPRM was prompted by a report indicating that several failure modes of the NWS system may cause the loss of feedback from both rotary variable differential transformers to the steering control unit. The NPRM proposed to require modifications to the NWS system. The FAA is issuing this AD to address failure modes of the NWS system, which could lead to NWS runaway, loss of directional control of the airplane, and possible consequent runway excursion. See the MCAI for additional background information. E:\FR\FM\27MYR1.SGM 27MYR1

Agencies

[Federal Register Volume 86, Number 101 (Thursday, May 27, 2021)]
[Rules and Regulations]
[Pages 28476-28479]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-11080]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-1171; Product Identifier 2017-SW-124-AD; Amendment 
39-21548; AD 2021-10-15]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus Helicopters Deutschland GmbH Model MBB-BK 117 C-2 and Model MBB-
BK 117 D-2 helicopters. This AD was prompted by a determination that a 
life limit for the adapter forward (FWD) of the outboard load system, 
repetitive inspections of other components of that system, and for 
certain helicopters, a modification of the outboard load system, are 
necessary to address the unsafe condition. This AD requires a 
modification of the outboard load system for certain helicopters, 
repetitive inspections of the outboard load system and its components 
for any defect (including cracking, damage, corrosion, and incorrect 
installation) and applicable corrective actions, and implementation of 
a new life limit for the FWD adapter, as specified in a European 
Aviation Safety Agency (now European Union Aviation Safety Agency) 
(EASA) AD, which is

[[Page 28477]]

incorporated by reference. The FAA is issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective July 1, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 1, 
2021.

ADDRESSES: For material incorporated by reference (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 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-2020-1171.

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-
1171; 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: Kathleen Arrigotti, Program Manager, 
Large Aircraft Section, International Validation Branch, Compliance & 
Airworthiness Division, FAA, 2200 South 216th St., Des Moines, WA 
98198; telephone and fax 206-231-3218; email 
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2017-0177, dated September 14, 2017 
(EASA AD 2017-0177) (also referred to as the Mandatory Continuing 
Airworthiness Information, or the MCAI), to correct an unsafe condition 
for all Airbus Helicopters Deutschland GmbH Model MBB-BK 117 C-2 
helicopters, except the Model C-2e variant, and all Model MBB-BK 117 D-
2 helicopters.
    EASA's Model MBB-BK 117 C-2e variant helicopters are not a unique 
model on the U.S. type certificate but are considered a configuration 
of the Model MBB-BK117 C-2. The U.S. type certificate data sheet 
explains that the FAA determined that the type design changes involved 
did not rise to the level that required an FAA amended type 
certificate. However, the FAA does recognize that helicopters with 
these type design changes exist, therefore the designation Model MBB-
BK117 C-2(e) is used, starting from Serial Number 9601. The Model MBB-
BK117 C-2(e) is a visual flight rules only configuration of the Model 
MBB-BK117 C-2 utilizing a Garmin 500H flight display system.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to all Airbus Helicopters 
Deutschland GmbH Model MBB-BK 117 C-2 and Model MBB-BK 117 D-2 
helicopters, except the Model MBB-BK117 C-2(e) configuration. The NPRM 
published in the Federal Register on March 11, 2021 (86 FR 13830). The 
NPRM was prompted by a determination that a life limit for the adapter 
FWD of the outboard load system, repetitive inspections of other 
components of that system, and for certain helicopters, a modification 
of the outboard load system, are necessary to address the unsafe 
condition. The NPRM proposed to require a modification of the outboard 
load system for certain helicopters, repetitive inspections of the 
outboard load system and its components for any defect (including 
cracking, damage, corrosion, and incorrect installation) and applicable 
corrective actions, and implementation of a new life limit for the FWD 
adapter, as specified in an EASA AD.
    The FAA is issuing this AD to address detachment of an external 
load or person from the helicopter hoist, resulting in personal injury, 
or injury to persons on the ground. See the MCAI for additional 
background information.

Discussion of Final Airworthiness Directive

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA received no comments on the NPRM or 
on the determination of the cost to the public.

Costs of Compliance Update

    The NPRM had specified no definitive data was available for the 
costs of the modification and certain parts. The FAA has received data 
on the costs of the modification and parts and has updated the costs of 
compliance accordingly.

Conclusion

    The FAA reviewed the relevant data and determined that air safety 
and the public interest require adopting this final rule as proposed, 
except for minor editorial changes and a change to paragraph (i)(1) of 
this AD. The FAA has determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    EASA AD 2017-0177 describes procedures for modification of the 
outboard load system for certain Model MBB-BK 117 C-2 helicopters, 
repetitive inspections of the outboard load system and its components 
for any defect (including cracking, damage, corrosion, and incorrect 
installation) and corrective actions, and implementation of a new life 
limit for the FWD adapter (i.e., repetitive replacements). The 
corrective actions include replacement of any defective component with 
a serviceable part.
    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.

Costs of Compliance

    The FAA estimates that this AD affects 175 helicopters of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
4 work-hours x $85 per hour = $340...........................          $2,276           $2,616         $457,800
----------------------------------------------------------------------------------------------------------------


[[Page 28478]]

    The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any 
required actions. The FAA has no way of determining the number of 
helicopters that might need these on-condition actions:

                 Estimated Costs of On-Condition Action
------------------------------------------------------------------------
          Labor cost                 Parts cost        Cost per product
------------------------------------------------------------------------
2 work-hours x $85 per hour =   Up to $970.........  Up to $1,140.
 $170.
------------------------------------------------------------------------

    According to the manufacturer, some or all of the costs of this AD 
may be covered under warranty, thereby reducing the cost impact on 
affected operators. The FAA does not control warranty coverage for 
affected operators. As a result, the FAA has included all known costs 
in the cost estimate.

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

    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.

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:

2021-10-15 Airbus Helicopters Deutschland GmbH: Amendment 39-21548; 
Docket No. FAA-2020-1171; Product Identifier 2017-SW-124-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective July 1, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Helicopters Deutschland GmbH Model 
MBB-BK 117 C-2 and Model MBB-BK 117 D-2 helicopters, certificated in 
any category, all manufacturer serial numbers, except the Model MBB-
BK117 C-2(e) configuration.

    Note 1 to paragraph (c): Model MBB-BK117 C-2 helicopters 
utilizing a Garmin 500H flight display system are designated by EASA 
as Model MBB-BK117 C-2e variants of the Model BK 117 C-2 
helicopters, and by the FAA as a Model MBB-BK117 C-2(e) 
configuration.

(d) Subject

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

(e) Reason

    This AD was prompted by a determination that a life limit for 
the adapter forward of the outboard load system, repetitive 
inspections of other components of that system, and for certain 
helicopters, a modification of the outboard load system, are 
necessary to address the unsafe condition. The FAA is issuing this 
AD to address detachment of an external load or person from the 
helicopter hoist, which could result in personal injury, or injury 
to persons on the ground.

(f) Compliance

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

(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, European Aviation Safety Agency (now European Union 
Aviation Safety Agency) (EASA) AD 2017-0177, dated September 14, 
2017 (EASA AD 2017-0177).

(h) Exceptions to EASA AD 2017-0177

    (1) Where EASA AD 2017-0177 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2017-0177 does not apply 
to this AD.
    (3) Where the service information referenced in EASA AD 2017-
0177 specifies contacting the applicable manufacturer of the 
dedicated equipment for a definition of a cycle and recalculation to 
hoist cycles, this AD does not require contacting the manufacturer 
for a definition of a cycle and recalculation to hoist cycles.
    (4) Where paragraph (3) of EASA AD 2017-0177 specifies to do 
``applicable corrective actions,'' for this AD, if there are any 
defective components, replace all defective components with 
serviceable components in accordance with FAA-approved procedures. 
For the purposes of this AD, a defect may be indicated by cracking, 
damage, corrosion, or incorrect installation.
    (5) Although the service information referenced in EASA AD 2017-
0177 specifies to discard certain parts, this AD requires removing 
those parts from service instead.
    (6) Where the service information referenced in EASA AD 2017-
0177 refers to flight hours (FH), this AD requires using hours time-
in-service.
    (7) Paragraph (9) of EASA AD 2017-0177 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

[[Page 28479]]

to the manager of the International Validation Branch, send it to 
the attention of the person identified in paragraph (j) 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

    For more information about this AD, contact Kathleen Arrigotti, 
Program Manager, Large Aircraft Section, International Validation 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and 
fax: 206-231-3218; email: [email protected].

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) European Aviation Safety Agency (EASA) AD 2017-0177, dated 
September 14, 2017.
    (ii) [Reserved]
    (3) For EASA AD 2017-0177, 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.
    (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. This material may be 
found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2020-1171.
    (5) You may view this material that is incorporated by reference 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, email 
[email protected], or go to https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on May 3, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-11080 Filed 5-26-21; 8:45 am]
BILLING CODE 4910-13-P