Airworthiness Directives; B-N Group Ltd. Airplanes, 33576-33579 [2021-13463]

Download as PDF 33576 Federal Register / Vol. 86, No. 120 / Friday, June 25, 2021 / Proposed Rules (c) Applicability This AD applies to The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 777–25–0649, Revision 2, dated October 8, 2020. (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/furnishings. (e) Unsafe Condition This AD was prompted by a report that showed a non-compliance exists on some inservice galley attendant seat fitting installations, and a determination that additional airplanes are subject to the unsafe condition. The FAA is issuing this AD to address non-compliant flight attendant seats, which could fail in a high-G crash and result in potential injury to flight attendants and consequent inability of the flight attendants to assist with passenger evacuation in a timely manner. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Except as specified by paragraph (h) of this AD: At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–25– 0649, Revision 2, dated October 8, 2020, do all applicable actions identified as ‘‘RC’’ (required for compliance) in, and in accordance with, the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–25–0649, Revision 2, dated October 8, 2020. (h) Exception to Service Information Specifications Where Boeing Special Attention Service Bulletin 777–25–0649, Revision 2, dated October 8, 2020, uses the phrase ‘‘the Revision 2 date of this service bulletin,’’ this AD requires using ‘‘the effective date of this AD.’’ lotter on DSK11XQN23PROD with PROPOSALS1 (i) No Reporting Requirement Although the service information referenced in Boeing Special Attention Service Bulletin 777–25–0649, Revision 2, dated October 8, 2020, specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 777–25–0649, Revision 1, dated October 6, 2017 (which is incorporated by reference in AD 2019–01– 08). (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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 VerDate Sep<11>2014 16:54 Jun 24, 2021 Jkt 253001 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in Related Information. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by The Boeing Company Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2019–01–08 are approved as AMOCs for the corresponding provisions of Boeing Special Attention Service Bulletin 777–25–0649, Revision 2, dated October 8, 2020, that are required by paragraph (g) of this AD. (5) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(5)(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 the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. 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. (l) Related Information (1) For more information about this AD, contact Brandon Lucero, Aerospace Engineer, Cabin Safety and Environmental Systems Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3569; email: brandon.lucero@faa.gov. (2) For service information identified in this AD, 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 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. PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 Issued on May 28, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–13407 Filed 6–24–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0502; Project Identifier 2018–CE–043–AD] RIN 2120–AA64 Airworthiness Directives; B–N Group Ltd. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain B–N Group Ltd. Models BN–2, BN–2A, BN–2A–2, BN–2A–3, BN–2A–6, BN–2A–8, BN–2A–9, BN–2A–20, BN– 2A–21, BN–2A–26, BN–2A–27, BN–2B– 20, BN–2B–21, BN–2B–26, BN–2B–27, BN–2T, and BN–2T–4R airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as failure of the rudder final drive rod because of cracks in the region of the taper pins. This proposed AD would require repetitively inspecting the rudder final drive rod assembly and replacing the rudder final drive assembly, if necessary. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by August 9, 2021. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. SUMMARY: E:\FR\FM\25JNP1.SGM 25JNP1 Federal Register / Vol. 86, No. 120 / Friday, June 25, 2021 / Proposed Rules For service information identified in this NPRM, contact Britten-Norman Aircraft Limited, Commodore House, Mountbatten Business Centre, Millbrook Road East, Southampton SO15 1HY, United Kingdom; phone: +44 20 3371 4000; fax: +44 20 3371 4001; email: info@bnaircraft.com; website: https:// britten-norman.com/approvalstechnical-publications/. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (816) 329–4148. lotter on DSK11XQN23PROD with PROPOSALS1 Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0502; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, any comments received, and other information. The street address for Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: Penelope Trease, Aviation Safety Engineer, General Aviation & Rotorcraft Section, International Validation Branch, FAA, 26805 E 68th Avenue, Denver, CO 80249; phone: (303) 342– 1094; email: penelope.trease@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2021–0502; Project Identifier 2018–CE–043–AD’’ at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this proposal because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this NPRM. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. VerDate Sep<11>2014 16:54 Jun 24, 2021 Jkt 253001 Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Penelope Trease, Aviation Safety Engineer, General Aviation & Rotorcraft Section, International Validation Branch, FAA, 26805 E 68th Avenue, Denver, CO 80249. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018–0153, dated July 19, 2018 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for B–N Group Ltd. (BrittenNorman Aircraft Ltd., or ‘‘BNA’’) Models BN–2, BN–2A, BN–2B, BN–2T, BN–2T–2, BN–2T–2R, and BN–2T–4R airplanes. The MCAI states: Occurrences have been reported of failures of the rudder final drive rod, [part number] P/N NB–45–0991. Cracks were found in the region of the taper pins. There is evidence that replacing the taper pins could be a significant factor contributing to the failure of this rod. This condition, if not detected and corrected, could lead to failure of the affected part, possibly resulting in reduced control of the aeroplane. To address this potential unsafe condition, BNA issued the applicable SB [service bulletin], providing inspection instructions. Prompted by operator comments, BNA revised the applicable SB (issue 3) to introduce repetitive inspections. For the reason described above, this [EASA] AD requires repetitive inspections of the affected part and, depending on findings, replacement. This AD also prohibits replacement of taper pins on an affected part. BNA will amend the applicable Maintenance Manuals accordingly. You may examine the MCAI in the AD docket at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 0502. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 33577 Related Service Information Under 1 CFR Part 51 The FAA reviewed Britten-Norman Aircraft Limited Service Bulletin Number SB 363, Issue 3, dated May 23, 2018, and Service Bulletin Number SB 364, Issue 3, dated May 23, 2018. For the applicable airplane models identified on each document, this service information contains procedures for repetitively inspecting the rudder final drive rod assembly and replacing the rudder final drive assembly, if necessary. 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 ADDRESSES. FAA’s Determination This product has been approved by the aviation authority of another country and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, it has notified the FAA of the unsafe condition described in the MCAI and service information referenced above. The FAA is issuing this NPRM after determining the unsafe condition described previously is likely to exist or develop on other products of the same type design. Proposed AD Requirements in This NPRM This AD requires accomplishing the actions specified in the service information already described. Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 76 airplanes of U.S. registry. The FAA also estimates that inspecting the rudder final drive assembly would take about 1 work-hour at the average labor rate of $85 per work-hour. Based on these figures, the FAA estimates the cost of this proposed AD on U.S. operators to be $6,460, or $85 per product, each inspection cycle. In addition, the FAA estimates that any necessary follow-on actions to replace the rudder final drive assembly would take about 5 work-hours and require parts costing $1,200, for a cost of $1,625 per product. The FAA has no way of determining the number of airplanes that may need these actions. 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 E:\FR\FM\25JNP1.SGM 25JNP1 33578 Federal Register / Vol. 86, No. 120 / Friday, June 25, 2021 / Proposed Rules detail the scope of the Agency’s authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Would not affect intrastate aviation in Alaska, and (3) Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ lotter on DSK11XQN23PROD with PROPOSALS1 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: ■ B–N Group Ltd.: Docket No. FAA–2021– 0502; Project Identifier 2018–CE–043– AD. VerDate Sep<11>2014 16:54 Jun 24, 2021 Jkt 253001 (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by August 9, 2021. (b) Affected ADs None. (c) Applicability This AD applies to B–N Group Ltd. Models BN–2, BN–2A, BN–2A–2, BN–2A–3, BN–2A– 6, BN–2A–8, BN–2A–9, BN–2A–20, BN–2A– 21, BN–2A–26, BN–2A–27, BN–2B–20, BN– 2B–21, BN–2B–26, BN–2B–27, BN–2T, and BN–2T–4R airplanes, all serial numbers, certificated in any category, with a rudder final drive rod part number (P/N) NB–45– 0991 installed. (d) Subject Joint Aircraft System Component (JASC) Code 2720, Rudder Control System. (e) Unsafe Condition This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as failure of the rudder final drive rod because of cracks in the region of the taper pins. The FAA is issuing this AD to detect and correct defects on the rudder final drive rod assembly to prevent failure of the assembly. The unsafe condition, if not addressed, could result in loss of rudder control and reduced airplane control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Corrective Action (1) Inspect the rudder final drive rod assembly for loose taper pins, loose end connections, bending, and cracks within the applicable compliance times for your airplane specified in paragraph (g)(1)(i) or (ii) of this AD. (i) For Models BN–2, BN–2A, BN–2A–2, BN–2A–3, BN–2A–6, BN–2A–8, BN–2A–9, BN–2A–20, BN–2A–21, BN–2A–26, BN–2A– 27, BN–2B–20, BN–2B–21, BN–2B–26, and BN–2B–27 airplanes, within 100 hours timein-service (TIS) after the effective date of this AD and thereafter at intervals not to exceed 1,000 hours TIS. (ii) For Models BN–2T and BN–2T–4R airplanes, within 200 hours TIS after the effective date of this AD and thereafter at intervals not to exceed 1,000 hours TIS. (2) If a loose taper pin, a loose end connection, any bending, or a crack is found during any inspection required by paragraph (g)(1) of this AD, before further flight, replace the rudder final drive rod assembly by following section 7, Removal and Installation Instructions for Unserviceable Units, of Britten-Norman Service Bulletin Number SB 363, Issue 3, dated May 23, 2018 (SB 363, Issue 3) or Britten-Norman Service Bulletin Number SB 364, Issue 3, dated May 23, 2018 (SB 364, Issue 3), as applicable to your model airplane. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 (3) If no loose taper pins, no loose end connections, no bending, and no cracks are found during the initial inspection required by paragraph (g)(1) of this AD, review the airplane maintenance records to determine whether any taper pins have been replaced or reworked on the rudder final drive rod assembly. (4) If a taper pin has ever been replaced or reworked, without exceeding the initial compliance time in paragraph (g)(1)(i) or (ii) of this AD, replace the rudder final drive rod assembly by following section 7, Removal and Installation Instructions for Unserviceable Units, of SB 363, Issue 3 or SB 364, Issue 3, as applicable to your model airplane. (5) As of the effective date of this AD, do not install a rudder final drive rod assembly P/N NB–45–0991 on any airplane unless: (i) The rudder final drive rod assembly is unused (zero hours TIS); or (ii) The taper pins in the rudder final drive rod assembly have never been replaced. (6) As of the effective date of this AD, do not replace any taper pin on a rudder final drive rod assembly P/N NB–45–0991 installed on any airplane. (h) 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 certification office, send it to the attention of the person identified in Related Information or email: 9AVS-AIR-730-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. (i) Related Information (1) For more information about this AD, contact Penelope Trease, Aviation Safety Engineer, General Aviation & Rotorcraft Section, International Validation Branch, FAA, 26805 E 68th Avenue, Denver, CO 80249; phone: (303) 342–1094; email: penelope.trease@faa.gov. (2) Refer to European Aviation Safety Agency (EASA) AD 2018–0153, dated July 19, 2018, for more information. You may examine the EASA AD in the AD docket at https://www.regulations.gov by searching for and locating it in Docket No. FAA–2021– 0502. (3) For service information identified in this AD, contact Britten-Norman Aircraft Limited, Commodore House, Mountbatten Business Centre, Millbrook Road East, Southampton SO15 1HY, United Kingdom; phone: +44 20 3371 4000; fax: +44 20 3371 4001; email: info@bnaircraft.com; website: https://britten-norman.com/approvalstechnical-publications/. You may review this referenced service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO E:\FR\FM\25JNP1.SGM 25JNP1 Federal Register / Vol. 86, No. 120 / Friday, June 25, 2021 / Proposed Rules 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Issued on June 11, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–13463 Filed 6–24–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0511; Project Identifier AD–2020–01229–E] RIN 2120–AA64 Airworthiness Directives; Williams International Co., L.L.C. Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Williams International Co., L.L.C. (Williams) FJ44–2A, FJ44–2C, FJ44–3A, and FJ44–3A–24 model turbofan engines. This proposed AD was prompted by a report of cracks in highpressure turbine (HPT) disk posts and failure of an HPT disk post. This proposed AD would require the removal and replacement of the affected HPT disk before reaching its new life limit. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by August 9, 2021. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Williams International Co., L.L.C., Product Support, 2000 Centerpoint Pkwy., Pontiac, MI 48341; phone: (800) 859– 3544; website: http://www.williams- lotter on DSK11XQN23PROD with PROPOSALS1 SUMMARY: VerDate Sep<11>2014 16:54 Jun 24, 2021 Jkt 253001 int.com/product-support. You may view this service information at the Chicago ACO Branch, 2300 East Devon Avenue, Des Plaines, IL 60018. For information on the availability of this material at the FAA, call (781) 238–7759. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0511; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, any comments received, and other information. The street address for Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: Kyle Bush, Aviation Safety Engineer, Chicago ACO Branch, FAA, 2300 East Devon Avenue, Des Plaines, IL 60018; phone: (847) 294–7870; fax: (847) 294–7834; email: kyle.bush@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2021–0511; Project Identifier AD– 2020–01229–E’’ at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this proposal because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this NPRM. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 33579 page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Kyle Bush, Aviation Safety Engineer, Chicago ACO Branch, FAA, 2300 East Devon Avenue, Des Plaines, IL 60018. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background The FAA received a report that Williams discovered cracks in one HPT disk post during a scheduled inspection of an FJ44–2A model turbofan engine. An operator also discovered that one HPT disk post failed, while the engine was in service, resulting in the release of an HPT blade. Williams initiated an investigation to understand the root cause of the cracks and to determine the necessary corrective action. Williams found that, between August 2018 and July 2019, nine FJ44–2A HPT disks were rejected during inspection after discovery of cracks in the HPT disk post. As part of its investigation, Williams conducted several tests and analysis to determine the failure mechanism. Engine tests confirmed that FJ44–2A and FJ44–2C model turbofan engines operate at a higher temperature than most recently certified engines. Metallurgical evaluation showed cracking is intergranular with oxidation attack near and around the crack, with no fatigue striations. Metallurgical evaluation and comparison of HPT disk, part number (P/N) 67093, installed on both FJ44–2A and FJ44–3A model turbofan engines, showed cracking of the HPT disk. As a result of this investigation, Williams determined the root cause of this cracking was due to higher temperatures and a difference in manufacturing processes (electrical discharge machining vs. broaching). Williams determined that these cracks have only occurred on HPT disks with P/N 67093. Williams subsequently issued service information to instruct operators to remove the HPT disk, P/N 67093. This condition, if not addressed, could result in failure of the engine, inflight shutdown of the engine, and loss of control of the aircraft. FAA’s Determination The FAA is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design. E:\FR\FM\25JNP1.SGM 25JNP1

Agencies

[Federal Register Volume 86, Number 120 (Friday, June 25, 2021)]
[Proposed Rules]
[Pages 33576-33579]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-13463]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0502; Project Identifier 2018-CE-043-AD]
RIN 2120-AA64


Airworthiness Directives; B-N Group Ltd. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain B-N Group Ltd. Models BN-2, BN-2A, BN-2A-2, BN-2A-3, BN-2A-
6, BN-2A-8, BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26, BN-2A-27, BN-2B-20, 
BN-2B-21, BN-2B-26, BN-2B-27, BN-2T, and BN-2T-4R airplanes. This 
proposed AD results from mandatory continuing airworthiness information 
(MCAI) originated by an aviation authority of another country to 
identify and correct an unsafe condition on an aviation product. The 
MCAI identifies the unsafe condition as failure of the rudder final 
drive rod because of cracks in the region of the taper pins. This 
proposed AD would require repetitively inspecting the rudder final 
drive rod assembly and replacing the rudder final drive assembly, if 
necessary. The FAA is proposing this AD to address the unsafe condition 
on these products.

DATES: The FAA must receive comments on this proposed AD by August 9, 
2021.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

[[Page 33577]]

    For service information identified in this NPRM, contact Britten-
Norman Aircraft Limited, Commodore House, Mountbatten Business Centre, 
Millbrook Road East, Southampton SO15 1HY, United Kingdom; phone: +44 
20 3371 4000; fax: +44 20 3371 4001; email: [email protected]; 
website: https://britten-norman.com/approvals-technical-publications/. 
You may view this service information at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 901 Locust, Kansas City, 
MO 64106. For information on the availability of this material at the 
FAA, call (816) 329-4148.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0502; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this NPRM, any comments 
received, and other information. The street address for Docket 
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Penelope Trease, Aviation Safety 
Engineer, General Aviation & Rotorcraft Section, International 
Validation Branch, FAA, 26805 E 68th Avenue, Denver, CO 80249; phone: 
(303) 342-1094; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2021-0502; Project Identifier 
2018-CE-043-AD'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to 
Penelope Trease, Aviation Safety Engineer, General Aviation & 
Rotorcraft Section, International Validation Branch, FAA, 26805 E 68th 
Avenue, Denver, CO 80249. Any commentary that the FAA receives which is 
not specifically designated as CBI will be placed in the public docket 
for this rulemaking.

Background

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0153, dated July 19, 2018 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for B-N Group Ltd. (Britten-
Norman Aircraft Ltd., or ``BNA'') Models BN-2, BN-2A, BN-2B, BN-2T, BN-
2T-2, BN-2T-2R, and BN-2T-4R airplanes. The MCAI states:

    Occurrences have been reported of failures of the rudder final 
drive rod, [part number] P/N NB-45-0991. Cracks were found in the 
region of the taper pins. There is evidence that replacing the taper 
pins could be a significant factor contributing to the failure of 
this rod.
    This condition, if not detected and corrected, could lead to 
failure of the affected part, possibly resulting in reduced control 
of the aeroplane.
    To address this potential unsafe condition, BNA issued the 
applicable SB [service bulletin], providing inspection instructions. 
Prompted by operator comments, BNA revised the applicable SB (issue 
3) to introduce repetitive inspections.
    For the reason described above, this [EASA] AD requires 
repetitive inspections of the affected part and, depending on 
findings, replacement. This AD also prohibits replacement of taper 
pins on an affected part. BNA will amend the applicable Maintenance 
Manuals accordingly.

    You may examine the MCAI in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0502.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Britten-Norman Aircraft Limited Service Bulletin 
Number SB 363, Issue 3, dated May 23, 2018, and Service Bulletin Number 
SB 364, Issue 3, dated May 23, 2018. For the applicable airplane models 
identified on each document, this service information contains 
procedures for repetitively inspecting the rudder final drive rod 
assembly and replacing the rudder final drive assembly, if necessary. 
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 ADDRESSES.

FAA's Determination

    This product has been approved by the aviation authority of another 
country and is approved for operation in the United States. Pursuant to 
our bilateral agreement with this State of Design Authority, it has 
notified the FAA of the unsafe condition described in the MCAI and 
service information referenced above. The FAA is issuing this NPRM 
after determining the unsafe condition described previously is likely 
to exist or develop on other products of the same type design.

Proposed AD Requirements in This NPRM

    This AD requires accomplishing the actions specified in the service 
information already described.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 76 airplanes of U.S. registry. The FAA also estimates that 
inspecting the rudder final drive assembly would take about 1 work-hour 
at the average labor rate of $85 per work-hour.
    Based on these figures, the FAA estimates the cost of this proposed 
AD on U.S. operators to be $6,460, or $85 per product, each inspection 
cycle.
    In addition, the FAA estimates that any necessary follow-on actions 
to replace the rudder final drive assembly would take about 5 work-
hours and require parts costing $1,200, for a cost of $1,625 per 
product. The FAA has no way of determining the number of airplanes that 
may need these actions.

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

[[Page 33578]]

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

Regulatory Findings

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

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

B-N Group Ltd.: Docket No. FAA-2021-0502; Project Identifier 2018-
CE-043-AD.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by August 9, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to B-N Group Ltd. Models BN-2, BN-2A, BN-2A-2, 
BN-2A-3, BN-2A-6, BN-2A-8, BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26, 
BN-2A-27, BN-2B-20, BN-2B-21, BN-2B-26, BN-2B-27, BN-2T, and BN-2T-
4R airplanes, all serial numbers, certificated in any category, with 
a rudder final drive rod part number (P/N) NB-45-0991 installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 2720, Rudder Control 
System.

(e) Unsafe Condition

    This AD was prompted by mandatory continuing airworthiness 
information (MCAI) originated by an aviation authority of another 
country to identify and correct an unsafe condition on an aviation 
product. The MCAI describes the unsafe condition as failure of the 
rudder final drive rod because of cracks in the region of the taper 
pins. The FAA is issuing this AD to detect and correct defects on 
the rudder final drive rod assembly to prevent failure of the 
assembly. The unsafe condition, if not addressed, could result in 
loss of rudder control and reduced airplane control.

(f) Compliance

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

(g) Inspection and Corrective Action

    (1) Inspect the rudder final drive rod assembly for loose taper 
pins, loose end connections, bending, and cracks within the 
applicable compliance times for your airplane specified in paragraph 
(g)(1)(i) or (ii) of this AD.
    (i) For Models BN-2, BN-2A, BN-2A-2, BN-2A-3, BN-2A-6, BN-2A-8, 
BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26, BN-2A-27, BN-2B-20, BN-2B-21, 
BN-2B-26, and BN-2B-27 airplanes, within 100 hours time-in-service 
(TIS) after the effective date of this AD and thereafter at 
intervals not to exceed 1,000 hours TIS.
    (ii) For Models BN-2T and BN-2T-4R airplanes, within 200 hours 
TIS after the effective date of this AD and thereafter at intervals 
not to exceed 1,000 hours TIS.
    (2) If a loose taper pin, a loose end connection, any bending, 
or a crack is found during any inspection required by paragraph 
(g)(1) of this AD, before further flight, replace the rudder final 
drive rod assembly by following section 7, Removal and Installation 
Instructions for Unserviceable Units, of Britten-Norman Service 
Bulletin Number SB 363, Issue 3, dated May 23, 2018 (SB 363, Issue 
3) or Britten-Norman Service Bulletin Number SB 364, Issue 3, dated 
May 23, 2018 (SB 364, Issue 3), as applicable to your model 
airplane.
    (3) If no loose taper pins, no loose end connections, no 
bending, and no cracks are found during the initial inspection 
required by paragraph (g)(1) of this AD, review the airplane 
maintenance records to determine whether any taper pins have been 
replaced or reworked on the rudder final drive rod assembly.
    (4) If a taper pin has ever been replaced or reworked, without 
exceeding the initial compliance time in paragraph (g)(1)(i) or (ii) 
of this AD, replace the rudder final drive rod assembly by following 
section 7, Removal and Installation Instructions for Unserviceable 
Units, of SB 363, Issue 3 or SB 364, Issue 3, as applicable to your 
model airplane.
    (5) As of the effective date of this AD, do not install a rudder 
final drive rod assembly P/N NB-45-0991 on any airplane unless:
    (i) The rudder final drive rod assembly is unused (zero hours 
TIS); or
    (ii) The taper pins in the rudder final drive rod assembly have 
never been replaced.
    (6) As of the effective date of this AD, do not replace any 
taper pin on a rudder final drive rod assembly P/N NB-45-0991 
installed on any airplane.

(h) 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 certification office, send it to the 
attention of the person identified in Related Information or email: 
[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.

(i) Related Information

    (1) For more information about this AD, contact Penelope Trease, 
Aviation Safety Engineer, General Aviation & Rotorcraft Section, 
International Validation Branch, FAA, 26805 E 68th Avenue, Denver, 
CO 80249; phone: (303) 342-1094; email: [email protected].
    (2) Refer to European Aviation Safety Agency (EASA) AD 2018-
0153, dated July 19, 2018, for more information. You may examine the 
EASA AD in the AD docket at https://www.regulations.gov by searching 
for and locating it in Docket No. FAA-2021-0502.
    (3) For service information identified in this AD, contact 
Britten-Norman Aircraft Limited, Commodore House, Mountbatten 
Business Centre, Millbrook Road East, Southampton SO15 1HY, United 
Kingdom; phone: +44 20 3371 4000; fax: +44 20 3371 4001; email: 
[email protected]; website: https://britten-norman.com/approvals-technical-publications/. You may review this referenced service 
information at the FAA, Airworthiness Products Section, Operational 
Safety Branch, 901 Locust, Kansas City, MO

[[Page 33579]]

64106. For information on the availability of this material at the 
FAA, call (816) 329-4148.

    Issued on June 11, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-13463 Filed 6-24-21; 8:45 am]
BILLING CODE 4910-13-P