Airworthiness Directives; Honda Aircraft Company LLC, 15926-15930 [2020-05891]

Download as PDF 15926 Federal Register / Vol. 85, No. 55 / Friday, March 20, 2020 / Rules and Regulations 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 (AD): ■ 2020–05–20 Airbus Helicopters: Amendment 39–19870; Docket No. FAA–2019–0970; Product Identifier 2018–SW–089–AD. (a) Applicability This AD applies to Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, and AS332L2 helicopters, certificated in any category, except those with modification 0726383 installed. (b) Unsafe Condition This AD defines the unsafe condition as closure of fuel tank drains. This condition could result in fuel accumulating in an area containing electrical equipment and ignition of fuel vapors. This condition could result in a fire and subsequent damage to the helicopter or injury to the occupants. (c) Effective Date This AD becomes effective April 24, 2020. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. jbell on DSKJLSW7X2PROD with RULES (e) Required Actions Within 110 hours time-in-service or during the next scheduled maintenance, whichever occurs first: (1) For Model AS332C and AS332C1 helicopters, remove the 6 fuel tank drain plugs by following the Accomplishment Instructions, paragraph 3.B.2. of Airbus Helicopters Alert Service Bulletin No. AS332–53.01.62, Revision 1, dated May 28, 2019 (ASB AS332–53.01.62), except you are not required to place the drain plugs in stock. (2) For Model AS332L, AS332L1, and AS332L2 helicopters, remove the 7 fuel tank drain plugs by following the Accomplishment Instructions, paragraph 3.B.2. of ASB AS332–53.01.62, except you are not required to place the drain plugs in stock. (f) Credit for Previous Actions Actions accomplished before the effective date of this AD in accordance with the procedures specified in Airbus Helicopters Alert Service Bulletin No. AS332–53.01.62, Revision 0, dated June 7, 2018, are considered acceptable for compliance with the corresponding actions specified in paragraph (e) of this AD. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, VerDate Sep<11>2014 17:04 Mar 19, 2020 Jkt 250001 may approve AMOCs for this AD. Send your proposal to: James Blyn, Aviation Safety Engineer, Regulations and Policy Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email 9-ASW-FTWAMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, the FAA suggests that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. email fedreg.legal@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. (h) Additional Information (1) Airbus Helicopters Alert Service Bulletin No. AS332–53.01.62, Revision 0, dated June 7, 2018, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone 972–641– 0000 or 800–232–0323; fax 972–641–3775; or at https://www.airbus.com/helicopters/ services/technical-support.html. You may view the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Union Aviation Safety Agency (previously European Aviation Safety Agency) (EASA) AD No. 2018–0209, dated September 21, 2018. You may view the EASA AD on the internet at https:// www.regulations.gov in Docket No. FAA– 2019–0970. 14 CFR Part 39 (i) Subject Joint Aircraft Service Component (JASC) Code: 2810, Fuel Storage. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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) Airbus Helicopters Alert Service Bulletin No. AS332–53.01.62, Revision 1, dated May 28, 2019. (ii) [Reserved] (3) For service information identified in this AD, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone 972–641–0000 or 800–232–0323; fax 972–641–3775; or at https:// www.airbus.com/helicopters/services/ technical-support.html. (4) You may view this service information at 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, PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Issued on March 11, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–05667 Filed 3–19–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration [Docket No. FAA–2020–0195; Product Identifier 2019–CE–052–AD; Amendment 39–21031; AD 2020–04–14] RIN 2120–AA64 Airworthiness Directives; Honda Aircraft Company LLC Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Honda Aircraft Company LLC (Honda) Model HA–420 airplanes. This AD requires inspecting the wheel speed transducer (WST) wiring harness, replacing the wiring harness if necessary, installing wiring hardware, and rerouting the WST wiring harness on both the left and right brake assemblies. This AD also requires revising the Abnormal Procedures section of the airplane flight manual (AFM) and quick reference handbook (QRH). This AD was prompted by reports of damage to the wiring harness due to excessive slack in the wiring harness assembly that allows contact with the main landing gear tire and by the determination that the AFMs and QRHs contain incorrect procedures for anti-skid braking system failures. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 6, 2020. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 6, 2020. The FAA must receive comments on this AD by May 4, 2020. 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. E:\FR\FM\20MRR1.SGM 20MRR1 Federal Register / Vol. 85, No. 55 / Friday, March 20, 2020 / Rules and Regulations • 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this final rule, contact Honda Aircraft Company LLC, 6430 Ballinger Road, Greensboro, North Carolina 27410; telephone (336) 662–0246; internet: https://www.hondajet.com. You may view this service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0195. 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– 0195; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, 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: Samuel Kovitch, Aerospace Engineer, Atlanta ACO Branch, FAA, 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474–5570; fax: (404) 474–5605; email: samuel.kovitch@ faa.gov. SUPPLEMENTARY INFORMATION: jbell on DSKJLSW7X2PROD with RULES Discussion The FAA received a report of a Honda Model HA–420 airplane losing normal braking during ground operations. Inspections revealed damage to a brake wiring harness for the WST, which was most likely caused by contact with the main landing gear tire. A review of manufacturer type design data and production line assembly instructions revealed that the wiring harness is installed with excessive slack that allows contact with the tire when pulled. Thus, the damage found may VerDate Sep<11>2014 17:04 Mar 19, 2020 Jkt 250001 occur on all in service Honda Model HA–420 airplanes. Further investigation revealed that damage to the wiring harness results in loss of the WST signal, which is interpreted by the digital antiskid control unit (DACU) as either a WST failure or locked wheel condition. The DACU provides locked wheel protection, which commands a full release of normal brakes at speeds greater than 25 knots until the right and left wheel speeds are within 70 percent of each other. Thus, when a WST signal is lost, the DACU commands a full normal brake release until the airplane speed falls below 25 knots. In this scenario, unavailability of the normal brakes is not annunciated to the pilot, because WST signal loss does not trigger the NORMAL BRAKE FAIL red crew alerting system (CAS) message. The pilot is notified via an ANTI–SKID FAIL amber CAS message. Existing AFM procedures for ANTI–SKID FAIL instruct the pilot to apply normal brakes gradually to stop the airplane when the anti-skid system has failed. The current AFM procedures are incorrect and do not caution the pilot that normal braking may be unavailable when the ANTI–SKID FAIL amber CAS message posts or instruct the pilot to use emergency braking. This condition, if not addressed, could result in unannunciated loss of normal brakes, reduced directional control during landing deceleration and ground operations, and loss of control of the airplane when applying the brakes. The FAA is issuing this AD to address the unsafe condition on these products. Related Service Information Under 1 CFR Part 51 The FAA reviewed Pages 3A–178 through 3A–180 from Section 3A— Abnormal Procedures in Honda Aircraft Company Airplane Flight Manual, HondaJet, Effectivity: 42000012 through 42000125, Model HA–420, Part No.: HJ1–29000–003–001, Revision D, dated December 12, 2019; and Pages 3A–178 through 3A–180 from Section 3A— Abnormal Procedures in Honda Aircraft Company Airplane Flight Manual, HondaJet ELITE, Effectivity: 42000011, 42000126 and after, HondaJet APMG, Effectivity: 42000012 through 42000125 with SB–420–55–001, Model HA–420, Part No.: HJ1–29001–003–001, Revision B1, dated December 12, 2019. For the specific airplane serial numbers specified on each document, these pages are revised pages to the AFMs that provide procedures for the flight crew when the braking anti-skid system fails. The FAA also reviewed Page A–126 and Page A–127 from HondaJet, Model PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 15927 HA–420, HJ1–29000–007–001, Volume 1 of 2, Effectivity 42000012 through 42000125, Quick Reference Handbook, Normal Procedures, Revision D, dated December 12, 2019; Page A–124 and Page A–125 from HondaJet, Model HA– 420, HJ1–29001–007–001, HondaJet ELITE, Effectivity: 42000011, 42000126 and after, HondaJet APMG, Effectivity: 42000012 through 42000125 with SB– 420–55–001, Quick Reference Handbook, Revision B, dated December 12, 2019. For the specific airplane serial numbers specified on each document, these pages are revised pages to the QRHs that provide procedures for the flight crew when the braking anti-skid system fails. The FAA also reviewed Honda Aircraft Company Service Bulletin Alert SB–420–32–008, Revision B, dated November 16, 2019 (Honda SB–420–32– 008, Revision B). This service document contains procedures for inspecting the condition of the WST wiring harness, replacing the wiring harness if necessary, installing wiring hardware, and rerouting the WST wiring harness on both the left and right brake assemblies. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination The FAA is issuing this AD because the FAA evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires replacing the revised pages in the AFMs and QRHs applicable to your airplane. This AD also requires accomplishing the actions specified in Honda SB–420–32–008, Revision B described previously. Interim Action The FAA considers this AD, which addresses anti-skid braking system failures, an interim action. Honda is developing software changes to revise the WST logic from the ANTI–SKID FAIL CAS to the NORMAL BRAKES FAIL CAS. Once this action is developed, approved, and available, the FAA may consider additional rulemaking. FAA’s Justification and Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD without providing an opportunity E:\FR\FM\20MRR1.SGM 20MRR1 15928 Federal Register / Vol. 85, No. 55 / Friday, March 20, 2020 / Rules and Regulations for public comments prior to adoption. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because the damage to WST wiring harness is possible on all affected airplanes due to slack in the harness by type design and may worsen rapidly after each landing cycle and result in loss of normal braking if left uncorrected. Additionally, incorrect AFM and QRH procedures instruct the pilot to use normal braking when it is unavailable instead of using emergency braking. The FAA has determined that certain corrective action is necessary before further flight to address the wiring harness damage that results in loss of normal braking and to provide pilot notification and guidance on what to expect and how to react to the ANTI– SKID FAIL CAS message coupled with the loss of normal brakes. Therefore, the FAA finds good cause that notice and opportunity for prior public comment are impracticable. In addition, for the reasons stated above, the FAA finds that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, the FAA invites you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under the ADDRESSES section. Include the Docket Number FAA–2020–0195 and Product Identifier 2019–CE–052–AD at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this final rule. The FAA will consider all comments received by the closing date and may amend this final rule because of those comments. The FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The FAA will also post a report summarizing each substantive verbal contact the FAA receives about this final rule. Costs of Compliance The FAA estimates that this AD affects 116 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Cost per product Cost on U.S. operators Action Labor cost Parts cost Revise the Abnormal Procedures section of the AFM. Revise the QRH ..................................... Inspect WST wiring harness, install hardware and reroute the WST wiring harness. 1 work-hour × $85 per hour = $85 ....... Not applicable .................. $85 $9,860 1 work-hour × $85 per hour = $85 ....... 7.5 work-hours × $85 per hour = $637.50. Not applicable .................. Not applicable .................. 85 637.50 9,860 73,950 The FAA estimates the following costs to do any necessary replacements that would be required based on the results of the inspection. The FAA has no way of determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Parts cost Replace the WST wiring harness ................................. *See note below ........................................................... $389 Cost per product $389 * Note: Since all operators are required to install wiring hardware and reroute the WST wiring harness, there is no additional labor cost associated with replacing the WST wiring harness. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. jbell on DSKJLSW7X2PROD with RULES 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 VerDate Sep<11>2014 17:04 Mar 19, 2020 Jkt 250001 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to small airplanes, gliders, balloons, airships, domestic business jet transport airplanes, and associated appliances to the Director of the Policy and Innovation Division. Regulatory Flexibility Act The requirements of the Regulatory Flexibility Act (RFA) do not apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and comment. Because FAA has determined that it has good cause to adopt this rule without notice and comment, RFA analysis is not required. E:\FR\FM\20MRR1.SGM 20MRR1 Federal Register / Vol. 85, No. 55 / Friday, March 20, 2020 / Rules and Regulations 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, and (2) Will not affect intrastate aviation in Alaska. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2020–04–14 Honda Aircraft Company LLC: Amendment 39–21031; Docket No. FAA–2020–0195; Product Identifier 2019–CE–052–AD. (a) Effective Date This AD is effective April 6, 2020. (b) Affected ADs None. (c) Applicability This AD applies to Honda Aircraft Company LLC Model HA–420 airplanes, serial numbers (S/Ns) 42000011 through 42000184, certificated in any category. jbell on DSKJLSW7X2PROD with RULES (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Unsafe Condition This AD was prompted by reports of damage to the wheel speed transducer wiring harness due to excessive slack in the wiring harness assembly that allows contact with the main landing gear tire and the determination that the airplane flight manuals (AFMs) and quick reference handbooks (QRHs) contain incorrect procedures for anti-skid braking system VerDate Sep<11>2014 17:04 Mar 19, 2020 Jkt 250001 failures. The FAA is issuing this AD to prevent un-annunciated loss of normal brakes and reduced directional control during landing deceleration and ground operations, which could lead to a runway excursion. (f) Compliance Comply with this AD within the compliance time specified, unless already done. (g) Revise the Airplane Flight Manuals and Quick Reference Handbooks Before further flight after April 6, 2020 (the effective date of this AD), revise your AFM and your QRH as specified below. (1) For airplanes with S/Ns 42000012 through 42000125 without SB–420–55–001: Remove the Abnormal Procedure pages for ANTI–SKID Fail and replace with Pages 3A– 178 through 3A–180 from Section 3A— Abnormal Procedures in Honda Aircraft Company Airplane Flight Manual, Model HA–420, Part No.: HJ1–29000–003–001, Revision D, dated December 12, 2019. (2) For airplanes with S/Ns 42000012 through 42000125 without SB–420–55–001: Remove the Abnormal Procedure pages for ANTI–SKID FAIL and replace with Page A– 126 and Page A–127 from Model HA–420, HJ1–29000–007–001, Volume 1 of 2, Quick Reference Handbook, Normal Procedures, Revision D, dated December 12, 2019. (3) For airplanes with S/Ns 42000011, 42000012 through 42000125 with SB–420– 55–001, and 42000126 through 42000184: Remove the Abnormal Procedure pages for ANTI–SKID FAIL and replace with Pages 3A–178 through 3A–180 from Section 3A— Abnormal Procedures in Honda Aircraft Company Airplane Flight Manual, Model HA–420, Part No.: HJ1–29001–003–001, Revision B1, dated December 12, 2019. (4) For airplanes with S/Ns 42000011, 42000012 through 42000125 with SB–420– 55–001, and 42000126 through 42000184: Remove the Abnormal Procedure pages for ANTI–SKID FAIL and replace with Page A– 124 and Page A–125 from Model HA–420, HJ1–29001–007–001, Quick Reference Handbook, Revision B, dated December 12, 2019. (h) Corrective Actions for the Wheel Speed Transducer Wiring Harness Within 90 days after April 6, 2020 (the effective date of this AD), do the actions specified in steps 1 through 7 of the Accomplishment Instructions in Honda Aircraft Company Service Bulletin Alert SB– 420–32–008, Revision B, dated November 16, 2019. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta ACO 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 certification office, send it to the attention of the person identified in paragraph (j) of this AD. PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 15929 (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. (3) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (i)(3)(i) and (ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with this AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (j) Related Information For more information about this AD, contact Samuel Kovitch, Aerospace Engineer, Atlanta ACO Branch, FAA, 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474–5570; fax: (404) 474–5605; email: samuel.kovitch@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 the AD specifies otherwise. (i) Pages 3A–178 through 3A–180 from Section 3A—Abnormal Procedures in Honda Aircraft Company Airplane Flight Manual, HondaJet, Effectivity: 42000012 through 42000125, Model HA–420, Part No.: HJ1– 29000–003–001, Revision D, dated December 12, 2019. (ii) Page A–126 and Page A–127 from HondaJet, Model HA–420, HJ1–29000–007– 001, Volume 1 of 2, Effectivity 42000012 through 42000125, Quick Reference Handbook, Normal Procedures, Revision D, dated December 12, 2019. (iii) Pages 3A–178 through 3A–180 from Section 3A—Abnormal Procedures in Honda Aircraft Company Airplane Flight Manual, HondaJet ELITE, Effectivity: 42000011, 42000126 and after, HondaJet APMG, Effectivity: 42000012 through 42000125 with SB–420–55–001, Model HA–420, Part No.: HJ1–29001–003–001, Revision B1, dated December 12, 2019. (iv) Page A–124 and Page A–125 from HondaJet, Model HA–420, HJ1–29001–007– 001, HondaJet ELITE, Effectivity: 42000011, 42000126 and after, HondaJet APMG, Effectivity: 42000012 through 42000125 with SB–420–55–001, Quick Reference Handbook, Revision B, dated December 12, 2019. (v) Honda Aircraft Company Service Bulletin Alert SB–420–32–008, Revision B, dated November 16, 2019. (3) For service information identified in this AD, contact Honda Aircraft Company LLC, 6430 Ballinger Road, Greensboro, North E:\FR\FM\20MRR1.SGM 20MRR1 15930 Federal Register / Vol. 85, No. 55 / Friday, March 20, 2020 / Rules and Regulations Carolina 27410; telephone (336) 662–0246; internet: https://www.hondajet.com. (4) You may view this service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. (5) You may view the 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 in Kansas City, Missouri, on March 16, 2020. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–05891 Filed 3–19–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0602; Product Identifier 2019–NM–016–AD; Amendment 39–19874; AD 2020–05–24] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. jbell on DSKJLSW7X2PROD with RULES AGENCY: SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2010–26– 01, which applied to certain The Boeing Company Model 777–200 series airplanes. AD 2010–26–01 required installing a new insulation blanket on the latch beam firewall of each thrust reverser (T/R) half. This AD requires retaining the requirements of 2010–26– 01. This AD also adds airplanes to the applicability. For those airplanes, this AD requires an inspection to determine if the installed T/R has an affected part number and, if an affected part number is found, installation of a new insulation blanket. This AD was prompted by a report of an in-flight shutdown due to an engine fire indication and a determination that additional airplanes are affected. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 24, 2020. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 24, 2020. VerDate Sep<11>2014 17:04 Mar 19, 2020 Jkt 250001 The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of January 20, 2011 (75 FR 78594, December 16, 2010). ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet https://www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards 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–2019–0602. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.govby searching for and locating Docket No. FAA–2019– 0602; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, 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: James Laubaugh, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206– 231–3622; email: james.laubaugh@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2010–26–01, Amendment 39–16540 (75 FR 78594, December 16, 2010) (‘‘AD 2010–26– 01’’). AD 2010–26–01 applied to certain Model 777–200 series airplanes. The NPRM published in the Federal Register on August 9, 2019 (84 FR 39241). The NPRM was prompted by a report of an in-flight shutdown due to an engine fire indication; an under-cowl engine fire was extinguished after landing. The NPRM was also prompted by a determination that additional airplanes are affected. The NPRM proposed to continue to require installing a new insulation blanket on PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 the latch beam firewall of each T/R half. The NPRM also proposed to add airplanes to the applicability. For those airplanes, the NPRM proposed to require an inspection to determine if the installed T/R has an affected part number and, if an affected part number is found, installation of a new insulation blanket. The FAA is issuing this AD to address the potential for a fire from entering the cowl or strut area, which could weaken T/R parts and result in reduced structural integrity of the T/R, possible separation of T/R parts during flight, and consequent damage to the airplane, injury to people, and damage to property on the ground. Comments The FAA gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Support for the NPRM The Air Line Pilots Association, International (ALPA) and United Airlines stated their support for the NPRM. Request To Revise the Cost of Compliance Boeing requested that the FAA revise the Cost of Compliance paragraph in the NPRM. Boeing stated that the proposed AD would affect 4 additional airplanes for a total of 29 airplanes of U.S. registry. Boeing stated that the 4 additional airplanes are equipped with Model GE 90–90B engines with line numbers greater than 413 and are therefore not identified in Boeing Alert Service Bulletin 777–78A0066, Revision 2, dated April 8, 2010, and not affected by AD 2010–26–01. The FAA concurs with the request and has revised the Cost of Compliance paragraph of this final rule to include 29 airplanes of U.S. registry. The four additional airplanes are Model 777–200 series with the specified engines already included in the applicability of the proposed AD. Although the effectivity of Boeing Alert Service Bulletin 777– 78A0066, Revision 2, dated April 8, 2010, does not include those four additional airplanes, the FAA determined that the actions in that service information are applicable to the additional airplanes. Request To Revise the Applicability Boeing requested that the applicability paragraph in the proposed AD also include Model 777–200 series airplanes equipped with General Electric Company (GE) GE90–92B engines. Boeing stated that there are two E:\FR\FM\20MRR1.SGM 20MRR1

Agencies

[Federal Register Volume 85, Number 55 (Friday, March 20, 2020)]
[Rules and Regulations]
[Pages 15926-15930]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-05891]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0195; Product Identifier 2019-CE-052-AD; Amendment 
39-21031; AD 2020-04-14]
RIN 2120-AA64


Airworthiness Directives; Honda Aircraft Company LLC

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Honda Aircraft Company LLC (Honda) Model HA-420 airplanes. This 
AD requires inspecting the wheel speed transducer (WST) wiring harness, 
replacing the wiring harness if necessary, installing wiring hardware, 
and rerouting the WST wiring harness on both the left and right brake 
assemblies. This AD also requires revising the Abnormal Procedures 
section of the airplane flight manual (AFM) and quick reference 
handbook (QRH). This AD was prompted by reports of damage to the wiring 
harness due to excessive slack in the wiring harness assembly that 
allows contact with the main landing gear tire and by the determination 
that the AFMs and QRHs contain incorrect procedures for anti-skid 
braking system failures. The FAA is issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective April 6, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 6, 
2020.
    The FAA must receive comments on this AD by May 4, 2020.

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.

[[Page 15927]]

     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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this final rule, contact 
Honda Aircraft Company LLC, 6430 Ballinger Road, Greensboro, North 
Carolina 27410; telephone (336) 662-0246; internet: https://www.hondajet.com. You may view this service information at the FAA, 
Policy and Innovation Division, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the FAA, 
call (816) 329-4148. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0195.

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-
0195; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, 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: Samuel Kovitch, Aerospace Engineer, 
Atlanta ACO Branch, FAA, 1701 Columbia Avenue, College Park, Georgia 
30337; phone: (404) 474-5570; fax: (404) 474-5605; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA received a report of a Honda Model HA-420 airplane losing 
normal braking during ground operations. Inspections revealed damage to 
a brake wiring harness for the WST, which was most likely caused by 
contact with the main landing gear tire. A review of manufacturer type 
design data and production line assembly instructions revealed that the 
wiring harness is installed with excessive slack that allows contact 
with the tire when pulled. Thus, the damage found may occur on all in 
service Honda Model HA-420 airplanes.
    Further investigation revealed that damage to the wiring harness 
results in loss of the WST signal, which is interpreted by the digital 
antiskid control unit (DACU) as either a WST failure or locked wheel 
condition. The DACU provides locked wheel protection, which commands a 
full release of normal brakes at speeds greater than 25 knots until the 
right and left wheel speeds are within 70 percent of each other. Thus, 
when a WST signal is lost, the DACU commands a full normal brake 
release until the airplane speed falls below 25 knots. In this 
scenario, unavailability of the normal brakes is not annunciated to the 
pilot, because WST signal loss does not trigger the NORMAL BRAKE FAIL 
red crew alerting system (CAS) message. The pilot is notified via an 
ANTI-SKID FAIL amber CAS message. Existing AFM procedures for ANTI-SKID 
FAIL instruct the pilot to apply normal brakes gradually to stop the 
airplane when the anti-skid system has failed. The current AFM 
procedures are incorrect and do not caution the pilot that normal 
braking may be unavailable when the ANTI-SKID FAIL amber CAS message 
posts or instruct the pilot to use emergency braking.
    This condition, if not addressed, could result in unannunciated 
loss of normal brakes, reduced directional control during landing 
deceleration and ground operations, and loss of control of the airplane 
when applying the brakes. The FAA is issuing this AD to address the 
unsafe condition on these products.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Pages 3A-178 through 3A-180 from Section 3A--
Abnormal Procedures in Honda Aircraft Company Airplane Flight Manual, 
HondaJet, Effectivity: 42000012 through 42000125, Model HA-420, Part 
No.: HJ1-29000-003-001, Revision D, dated December 12, 2019; and Pages 
3A-178 through 3A-180 from Section 3A--Abnormal Procedures in Honda 
Aircraft Company Airplane Flight Manual, HondaJet ELITE, Effectivity: 
42000011, 42000126 and after, HondaJet APMG, Effectivity: 42000012 
through 42000125 with SB-420-55-001, Model HA-420, Part No.: HJ1-29001-
003-001, Revision B1, dated December 12, 2019. For the specific 
airplane serial numbers specified on each document, these pages are 
revised pages to the AFMs that provide procedures for the flight crew 
when the braking anti-skid system fails.
    The FAA also reviewed Page A-126 and Page A-127 from HondaJet, 
Model HA-420, HJ1-29000-007-001, Volume 1 of 2, Effectivity 42000012 
through 42000125, Quick Reference Handbook, Normal Procedures, Revision 
D, dated December 12, 2019; Page A-124 and Page A-125 from HondaJet, 
Model HA-420, HJ1-29001-007-001, HondaJet ELITE, Effectivity: 42000011, 
42000126 and after, HondaJet APMG, Effectivity: 42000012 through 
42000125 with SB-420-55-001, Quick Reference Handbook, Revision B, 
dated December 12, 2019. For the specific airplane serial numbers 
specified on each document, these pages are revised pages to the QRHs 
that provide procedures for the flight crew when the braking anti-skid 
system fails.
    The FAA also reviewed Honda Aircraft Company Service Bulletin Alert 
SB-420-32-008, Revision B, dated November 16, 2019 (Honda SB-420-32-
008, Revision B). This service document contains procedures for 
inspecting the condition of the WST wiring harness, replacing the 
wiring harness if necessary, installing wiring hardware, and rerouting 
the WST wiring harness on both the left and right brake assemblies.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination

    The FAA is issuing this AD because the FAA evaluated all the 
relevant information and determined the unsafe condition described 
previously is likely to exist or develop in other products of the same 
type design.

AD Requirements

    This AD requires replacing the revised pages in the AFMs and QRHs 
applicable to your airplane. This AD also requires accomplishing the 
actions specified in Honda SB-420-32-008, Revision B described 
previously.

Interim Action

    The FAA considers this AD, which addresses anti-skid braking system 
failures, an interim action. Honda is developing software changes to 
revise the WST logic from the ANTI-SKID FAIL CAS to the NORMAL BRAKES 
FAIL CAS. Once this action is developed, approved, and available, the 
FAA may consider additional rulemaking.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity

[[Page 15928]]

for public comments prior to adoption. The FAA has found that the risk 
to the flying public justifies waiving notice and comment prior to 
adoption of this rule because the damage to WST wiring harness is 
possible on all affected airplanes due to slack in the harness by type 
design and may worsen rapidly after each landing cycle and result in 
loss of normal braking if left uncorrected. Additionally, incorrect AFM 
and QRH procedures instruct the pilot to use normal braking when it is 
unavailable instead of using emergency braking. The FAA has determined 
that certain corrective action is necessary before further flight to 
address the wiring harness damage that results in loss of normal 
braking and to provide pilot notification and guidance on what to 
expect and how to react to the ANTI-SKID FAIL CAS message coupled with 
the loss of normal brakes. Therefore, the FAA finds good cause that 
notice and opportunity for prior public comment are impracticable. In 
addition, for the reasons stated above, the FAA finds that good cause 
exists for making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, the FAA invites you to send any written data, views, 
or arguments about this final rule. Send your comments to an address 
listed under the ADDRESSES section. Include the Docket Number FAA-2020-
0195 and Product Identifier 2019-CE-052-AD at the beginning of your 
comments. The FAA specifically invites comments on the overall 
regulatory, economic, environmental, and energy aspects of this final 
rule. The FAA will consider all comments received by the closing date 
and may amend this final rule because of those comments.
    The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact the FAA receives about this final rule.

Costs of Compliance

    The FAA estimates that this AD affects 116 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
              Action                      Labor cost             Parts cost           product        operators
----------------------------------------------------------------------------------------------------------------
Revise the Abnormal Procedures      1 work-hour x $85 per  Not applicable.......             $85          $9,860
 section of the AFM.                 hour = $85.
Revise the QRH....................  1 work-hour x $85 per  Not applicable.......              85           9,860
                                     hour = $85.
Inspect WST wiring harness,         7.5 work-hours x $85   Not applicable.......          637.50          73,950
 install hardware and reroute the    per hour = $637.50.
 WST wiring harness.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace the WST wiring harness................  *See note below.................            $389            $389
----------------------------------------------------------------------------------------------------------------
* Note: Since all operators are required to install wiring hardware and reroute the WST wiring harness, there is
  no additional labor cost associated with replacing the WST wiring harness.

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our 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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to small airplanes, gliders, 
balloons, airships, domestic business jet transport airplanes, and 
associated appliances to the Director of the Policy and Innovation 
Division.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because FAA has determined 
that it has good cause to adopt this rule without notice and comment, 
RFA analysis is not required.

[[Page 15929]]

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, and
    (2) Will not affect intrastate aviation in Alaska.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

2020-04-14 Honda Aircraft Company LLC: Amendment 39-21031; Docket 
No. FAA-2020-0195; Product Identifier 2019-CE-052-AD.

(a) Effective Date

    This AD is effective April 6, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Honda Aircraft Company LLC Model HA-420 
airplanes, serial numbers (S/Ns) 42000011 through 42000184, 
certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 32, Landing Gear.

(e) Unsafe Condition

    This AD was prompted by reports of damage to the wheel speed 
transducer wiring harness due to excessive slack in the wiring 
harness assembly that allows contact with the main landing gear tire 
and the determination that the airplane flight manuals (AFMs) and 
quick reference handbooks (QRHs) contain incorrect procedures for 
anti-skid braking system failures. The FAA is issuing this AD to 
prevent un-annunciated loss of normal brakes and reduced directional 
control during landing deceleration and ground operations, which 
could lead to a runway excursion.

(f) Compliance

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

(g) Revise the Airplane Flight Manuals and Quick Reference Handbooks

    Before further flight after April 6, 2020 (the effective date of 
this AD), revise your AFM and your QRH as specified below.
    (1) For airplanes with S/Ns 42000012 through 42000125 without 
SB-420-55-001: Remove the Abnormal Procedure pages for ANTI-SKID 
Fail and replace with Pages 3A-178 through 3A-180 from Section 3A--
Abnormal Procedures in Honda Aircraft Company Airplane Flight 
Manual, Model HA-420, Part No.: HJ1-29000-003-001, Revision D, dated 
December 12, 2019.
    (2) For airplanes with S/Ns 42000012 through 42000125 without 
SB-420-55-001: Remove the Abnormal Procedure pages for ANTI-SKID 
FAIL and replace with Page A-126 and Page A-127 from Model HA-420, 
HJ1-29000-007-001, Volume 1 of 2, Quick Reference Handbook, Normal 
Procedures, Revision D, dated December 12, 2019.
    (3) For airplanes with S/Ns 42000011, 42000012 through 42000125 
with SB-420-55-001, and 42000126 through 42000184: Remove the 
Abnormal Procedure pages for ANTI-SKID FAIL and replace with Pages 
3A-178 through 3A-180 from Section 3A--Abnormal Procedures in Honda 
Aircraft Company Airplane Flight Manual, Model HA-420, Part No.: 
HJ1-29001-003-001, Revision B1, dated December 12, 2019.
    (4) For airplanes with S/Ns 42000011, 42000012 through 42000125 
with SB-420-55-001, and 42000126 through 42000184: Remove the 
Abnormal Procedure pages for ANTI-SKID FAIL and replace with Page A-
124 and Page A-125 from Model HA-420, HJ1-29001-007-001, Quick 
Reference Handbook, Revision B, dated December 12, 2019.

(h) Corrective Actions for the Wheel Speed Transducer Wiring Harness

    Within 90 days after April 6, 2020 (the effective date of this 
AD), do the actions specified in steps 1 through 7 of the 
Accomplishment Instructions in Honda Aircraft Company Service 
Bulletin Alert SB-420-32-008, Revision B, dated November 16, 2019.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta ACO 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 certification office, send it to the attention of the 
person identified in paragraph (j) of this AD.
    (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.
    (3) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(i)(3)(i) and (ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with this AD. An AMOC is required for any deviations to RC steps, 
including substeps and identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

 (j) Related Information

    For more information about this AD, contact Samuel Kovitch, 
Aerospace Engineer, Atlanta ACO Branch, FAA, 1701 Columbia Avenue, 
College Park, Georgia 30337; phone: (404) 474-5570; fax: (404) 474-
5605; 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 the AD specifies otherwise.
    (i) Pages 3A-178 through 3A-180 from Section 3A--Abnormal 
Procedures in Honda Aircraft Company Airplane Flight Manual, 
HondaJet, Effectivity: 42000012 through 42000125, Model HA-420, Part 
No.: HJ1-29000-003-001, Revision D, dated December 12, 2019.
    (ii) Page A-126 and Page A-127 from HondaJet, Model HA-420, HJ1-
29000-007-001, Volume 1 of 2, Effectivity 42000012 through 42000125, 
Quick Reference Handbook, Normal Procedures, Revision D, dated 
December 12, 2019.
    (iii) Pages 3A-178 through 3A-180 from Section 3A--Abnormal 
Procedures in Honda Aircraft Company Airplane Flight Manual, 
HondaJet ELITE, Effectivity: 42000011, 42000126 and after, HondaJet 
APMG, Effectivity: 42000012 through 42000125 with SB-420-55-001, 
Model HA-420, Part No.: HJ1-29001-003-001, Revision B1, dated 
December 12, 2019.
    (iv) Page A-124 and Page A-125 from HondaJet, Model HA-420, HJ1-
29001-007-001, HondaJet ELITE, Effectivity: 42000011, 42000126 and 
after, HondaJet APMG, Effectivity: 42000012 through 42000125 with 
SB-420-55-001, Quick Reference Handbook, Revision B, dated December 
12, 2019.
    (v) Honda Aircraft Company Service Bulletin Alert SB-420-32-008, 
Revision B, dated November 16, 2019.
    (3) For service information identified in this AD, contact Honda 
Aircraft Company LLC, 6430 Ballinger Road, Greensboro, North

[[Page 15930]]

Carolina 27410; telephone (336) 662-0246; internet: https://www.hondajet.com.
    (4) You may view this service information at the FAA, Policy and 
Innovation Division, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
(816) 329-4148.
    (5) You may view the service information that is incorporated by 
reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on March 16, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2020-05891 Filed 3-19-20; 8:45 am]
 BILLING CODE 4910-13-P
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