Airworthiness Directives; Anjou Aeronautique Torso Restraint Systems, 72257-72260 [2019-27939]

Download as PDF Federal Register / Vol. 84, No. 250 / Tuesday, December 31, 2019 / Proposed Rules khammond on DSKJM1Z7X2PROD with PROPOSALS No. 05.00.51, Revision 1, dated July 29, 2015 (ASB 05.00.51 Rev 1). (i) Record the outside air temperature (OAT) and rotor speed (NR RPM) and plot the point at which they intersect using the graph in Figure 1 or 2 of ASB 05.00.51 Rev 0 or ASB 05.00.51 Rev 1. (ii) If the point on the graph at the intersection of the recorded OAT and the NR RPM falls within: (A) Zone 3—Before further flight, replace the MGB and pump with an airworthy MGB and pump. (B) Zone 2—At intervals not to exceed 25 hours TIS, repeat the inspection procedures by following the Accomplishment Instructions, paragraph 2.B.2, steps 1. through 6., of ASB 05.00.51 Rev 0 or ASB 05.00.51 Rev 1. After being classified in ‘‘Zone 2,’’ you must obtain two successive inspections separated by at least 24 hours TIS that fall within Zone 1 before you can begin to inspect at intervals not to exceed 110 hours TIS by following paragraph (f)(2)(ii)(C) of this AD for Zone 1. (C) Zone 1—At intervals not to exceed 110 hours TIS, repeat the inspection procedures by following the Accomplishment Instructions, paragraph 2.B.2., steps 1. through 6., of ASB 05.00.51 Rev 0 or ASB 05.00.51 Rev 1. (iii) Compliance with paragraphs (f)(2)(i) and (ii) of this AD constitutes terminating action for the checks and inspections required by paragraph (f)(1) of this AD. (3) As an optional terminating action for the requirements in this AD, alter the lubrication system for the MGB in accordance with the Accomplishment Instructions, paragraphs 3.B.2.a. through 3.B.3 of Airbus Helicopters Service Bulletin No. AS355–63.00.25, Revision 1, dated July 29, 2015, or Revision 2, dated June 22, 2017. Mineral oil 0–155 is required after compliance with this alteration. Note 1 to paragraph (f)(3) of this AD: Airbus Helicopters identifies alteration of the lubrication system as MOD 077222. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Jignesh Patel, Aerospace Engineer, Safety Management 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. (h) Additional Information (1) Airbus Helicopters Service Bulletin No. AS355–63.00.25, Revision 1, dated July 29, 2015, and Revision 2, dated June 22, 2017, and Eurocopter Emergency Alert Service Bulletin No. 05.00.40, Revision 3, dated July VerDate Sep<11>2014 16:29 Dec 30, 2019 Jkt 250001 9, 2007, which are not incorporated by reference, pertain to 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 a copy of the 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 Aviation Safety Agency (EASA) AD No. 2007–0209R1, dated September 11, 2015. You may view the EASA AD on the internet at https://www.regulations.gov in the AD Docket. (i) Subject Joint Aircraft Service Component (JASC) Code: 6320, Main Rotor Gearbox. Issued in Fort Worth, Texas, on December 20, 2019. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2019–27978 Filed 12–30–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0537; Product Identifier 2019–NE–16–AD] RIN 2120–AA64 Airworthiness Directives; Anjou Aeronautique Torso Restraint Systems Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede airworthiness directive (AD) 2017–16–04 which applies to certain Anjou Aeronautique (formerly Romtex Anjou Aeronautique) Model 358 torso restraint systems (restraint systems). AD 2017–16–04 required inspection of the restraint system, placarding if it is found to be inoperative, and replacement of the affected restraint system with a part eligible for installation. Since the FAA issued AD 2017–16–04, the European Union Aviation Safety Agency (EASA) received reports of additional serial numbered restraint systems rotary buckle knobs (buckle knobs) breaking on a batch of parts outside of the previous population. This proposed AD would require the removal from service of this expanded population of affected restraint systems and modifies the compliance schedule for their removal. SUMMARY: PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 72257 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 February 14, 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. • 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 Anjou Aeronautique, Strada Livezii nr. 98, 550042, Sibiu, Romania; telephone: +40 269 243 918; fax: +40 269 243 921; email: seatbelts@anjouaero.com. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. 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 on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0537; 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, the mandatory continuing airworthiness information (MCAI), 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: Dorie Resnik, Aerospace Engineer, Boston ACO Branch, FAA, 1200 District Avenue, Burlington, MA, 01803; phone: 781–238–7693; fax: 781–238–7199; email: dorie.resnik@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2019–0537; Product Identifier 2019–NE–16–AD’’ at E:\FR\FM\31DEP1.SGM 31DEP1 72258 Federal Register / Vol. 84, No. 250 / Tuesday, December 31, 2019 / Proposed Rules the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. The FAA will consider all comments received by the closing date and may amend this NPRM 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 received about this proposed AD. Discussion The FAA issued AD 2017–16–04, Amendment 39–18981 (82 FR 39355, August 18, 2017), (‘‘AD 2017–16–04’’), for Anjou Aeronautique restraint systems installed on, but not limited to, Airbus Helicopters Model AS350B2, AS350B3, EC130B4, EC130T2, and AS355NP helicopters. AD 2017–16–04 requires inspection of the restraint system, placarding if it is found to be inoperative, and replacement of the affected restraint system with a part eligible for installation. AD 2017–16–04 resulted from reports of a population of buckle knobs breaking due to the alteration of rotary buckle sub-assembly by a supplier of Anjou Aeronautique to a specification different from the approved design data. The FAA issued AD 2017–16–04 to prevent a restraint system from failing to release due to the buckle knobs breaking off, preventing occupants from exiting the helicopter during an emergency. Actions Since AD 2017–16–04 Was Issued Since the FAA issued AD 2017–16– 04, EASA received reports of additional Anjou Aeronautique Model 358 buckle knobs breaking on a batch of parts affected by the same unsafe condition due to an unknown root cause. As a result, EASA issued AD 2018–0195, dated September 4, 2018, which identifies a population of the restraint systems to be removed from service. Revision to Cost Estimate The FAA determined the need to clarify the estimated cost in AD 2017– 16–04. The cost reflected in AD 2017– 16–04 is the total cost per helicopter ($6,000 per restraint system multiplied by 7 seats per helicopter totaling $42,000). In this AD, the FAA is providing the cost estimate per restraint system. Related Service Information Under 1 CFR Part 51 The FAA reviewed Anjou Aero Service Bulletin (SB) No. 358SB–14– 101, Revision 1, dated December 12, 2014. The SB describes procedures for removing from service and replacing the rotary buckle sub-assembly on certain part-numbered and serial-numbered buckle assemblies, consisting of the rotary buckle, belt, and attachment. 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 proposing this AD because it 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. Proposed AD Requirements This proposed AD would retain certain requirements of AD 2017–16–04. This proposed AD expands the populations of affected restrains systems and modifies the compliance schedule for their removal. Differences Between the Proposed AD and MCAI EASA AD 2018–0195, dated September 4, 2018, requires replacement of the affected restraint system within six months after the effective date of the EASA AD. This proposed AD would require inspection of each restraint system within 30 hours time in service (TIS) after the effective date of the AD and replacement of the rotary buckle sub-assembly within 180 hours TIS after the effective date of this AD. Additionally, the EASA AD applies to restraint systems installed on, but not limited to, Airbus Helicopter AS350B2, AS350B3, and EC130T2 helicopters. This proposed AD would apply to restraint systems installed on, but not limited to, Airbus Helicopters AS350B2, AS350B3, EC130B4, EC130T2, and AS355NP helicopters. Costs of Compliance The FAA estimates that this proposed AD affects an unknown number of restraint systems installed on, but not limited to, Airbus Helicopters AS350B2, AS350B3, EC130B4, EC130T2, and AS355NP helicopters of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspect restraint system ............................................... Remove and replace restraint system ......................... 0.5 work-hours × $85 per hour = $42.50 ..................... 0.5 work-hours × $85 per hour = $42.50 ..................... The FAA estimates the following costs to do any necessary placarding that would be required based on the results of the proposed inspection. The FAA has no way of determining the Cost per product Parts cost $0 6,000 $42.50 6,042.50 number of aircraft that might need this placarding: khammond on DSKJM1Z7X2PROD with PROPOSALS ON-CONDITION COSTS Action Labor cost Placard seat as inoperable ........................................... 0.1 work-hour × $85 per hour = $8.50 ......................... According to the manufacturer, some of the costs of this proposed AD may be VerDate Sep<11>2014 16:29 Dec 30, 2019 Jkt 250001 covered under warranty, thereby reducing the cost impact on affected PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Cost per product Parts cost $0 $8.50 individuals. The FAA does not control warranty coverage for affected E:\FR\FM\31DEP1.SGM 31DEP1 Federal Register / Vol. 84, No. 250 / Tuesday, December 31, 2019 / Proposed Rules individuals. As a result, the FAA has included all costs in its cost estimate. khammond on DSKJM1Z7X2PROD with PROPOSALS 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 engines, propellers, and associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. 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 that the proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. VerDate Sep<11>2014 16:29 Dec 30, 2019 Jkt 250001 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2017–16–04, Amendment 39–18981 (82 FR 39355, August 18, 2017), and adding the following new AD: ■ Anjou Aeronautique (formerly Romtex Anjou Aeronautique): Docket No. FAA– 2019–0537; Product Identifier 2019–NE– 16–AD. (a) Comments Due Date The FAA must receive comments on this AD action by February 14, 2020. (b) Affected ADs This AD replaces AD 2017–16–04, Amendment 39–18981 (82 FR 39355, August 18, 2017). (c) Applicability (1) This AD applies to Anjou Aeronautique Model 358 torso restraint systems (restraint systems), part number (P/N) 358XX–XXX– YY–ZZZ (where 358XX–XXX–YY–ZZZ can be any combination of numbers and/or letters), with serial numbers (S/Ns) listed in Effectivity, paragraph 1.2, of Anjou Aero Service Bulletin (SB) No. 358SB–14–101, Revision 1, dated December 12, 2014, and with S/Ns listed in Figure 1 to Paragraph (c)(1) of this AD. FIGURE 1 TO PARAGRAPH (c)(1)— APPLICABILITY S/N (From . . . inclusive) S/N (To . . . inclusive) 738 1049 1056 1074 1037 1049 1061 1619 (2) These restraint systems are installed on, but not limited to, Airbus Helicopters AS350B2, AS350B3, EC130B4, EC130T2, and AS355NP helicopters, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 2500, Cabin Equipment/Furnishings. (e) Unsafe Condition This AD was prompted by reports to the European Union Aviation Safety Agency (EASA) of additional restraint system buckle knobs, since the publication of AD 2017–16– 04, breaking on a batch of parts outside of the PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 72259 population identified in AD 2017–16–04. The FAA is issuing this AD to prevent a restraint system strap from failing to release from the buckle, causing occupants to be unable to exit the aircraft during an emergency. The unsafe condition, if not addressed, could result in a restraint system strap failing to release from the buckle, resulting in injury or death of the occupant. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For the restraint systems listed in the Effectivity, paragraph 1.2, of Anjou Aero SB No. 358SB–14–101, Revision 1, dated December 12, 2014, except for S/Ns 1038– 1048 (inclusive), 1050–1055 (inclusive), and 1062–1073 (inclusive), within 30 hours timein-service (TIS) after the effective date of this AD, inspect each restraint system for proper release of the straps from the restraint system. (i) If the straps do not release from the restraint system, before further flight, placard the seat as inoperative. Within 180 hours TIS after the effective date of this AD, remove the rotary buckle sub-assembly and replace it with a part eligible for installation. (ii) If the straps release from the restraint system, within 180 hours TIS after the effective date of this AD, remove the rotary buckle sub-assembly and replace it with a part eligible for installation. (2) For restraint systems, P/N 358XX– XXX–YY–ZZZ (where 358XX–XXX–YY–ZZZ can be any combination of numbers and/or letters), having S/Ns 738–1619 (inclusive), within 30 hours TIS after the effective date of this AD, inspect the restraint system for proper release of the straps from the restraint system. (i) If the straps do not release from the restraint system, before further flight, placard the seat as inoperative and within 180 hours TIS after the effective date of this AD, remove the restraint system from service and replace it with a part eligible for installation. (ii) If the straps release from the restraint system, within 180 hours TIS or six months after the effective date of this AD, whichever occurs first, remove the restraint system from service and replace it with a part eligible for installation. (h) Installation Prohibition After the effective date of this AD, do not install on any aircraft an Anjou Aeronautique restraint system, P/N 358XX–XXX–YY–ZZZ, having S/Ns 738–1619 (inclusive), even if the restraint system is labeled in compliance with Anjou Aero SB No. 358SB–14–101, Revision 1, dated December 12, 2014. (i) Definition For the purpose of this AD, a ‘‘part eligible for installation’’ is an Anjou Aeronautique restraint system, excluding P/N 358XX– XXX–YY–ZZZ, having S/Ns 738–1619 (inclusive), that had the rotary buckle subsystem repaired and a label attached indicating compliance with Anjou Aero SB No. 358SB–14–101, Revision 1, dated December 12, 2014, or later revisions. E:\FR\FM\31DEP1.SGM 31DEP1 72260 Federal Register / Vol. 84, No. 250 / Tuesday, December 31, 2019 / Proposed Rules (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Boston 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 (k)(1) 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. (k) Related Information (1) For more information about this AD, contact Dorie Resnik, Aerospace Engineer, Boston ACO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781– 238–7693; fax: 781–238–7199; email: dorie.resnik@faa.gov. (2) Refer to EASA AD 2018–0195, dated September 4, 2018, for more information. You may examine the EASA AD in the AD docket on the internet at https:// www.regulations.gov by searching for and locating it in Docket No. FAA–2019–0537. (3) For service information identified in this AD, contact Anjou Aeronautique, Strada Livezii nr. 98, 550042, Sibiu, Romania; telephone: +40 269 243 918; fax: +40 269 243 921; email: seatbelts@anjouaero.com. You may view this referenced service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7759. Federal Aviation Administration 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 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, 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–2019–0990. 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2019–0990; Product Identifier 2019–NM–122–AD] You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0990; 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, 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. Issued in Burlington, Massachusetts, on December 20, 2019. Karen M. Grant, Acting Manager, Engine & Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2019–27939 Filed 12–30–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION RIN 2120–AA64 khammond on DSKJM1Z7X2PROD with PROPOSALS The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747– 400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. This proposed AD was prompted by reports of cracks of the upper splice fittings. This proposed AD would require repetitive detailed inspections and open hole high frequency eddy current (HFEC) inspections of the upper splice fittings for cracks and applicable on-condition actions. 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 February 14, 2020. Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for all SUMMARY: VerDate Sep<11>2014 16:29 Dec 30, 2019 Jkt 250001 ADDRESSES: PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 Bill Ashforth, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3520; email: bill.ashforth@faa.gov. SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT: 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 the ADDRESSES section. Include ‘‘Docket No. FAA–2019–0990; Product Identifier 2019–NM–122–AD’’ at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. The FAA will consider all comments received by the closing date and may amend this NPRM 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 received about this proposed AD. Discussion The FAA has received reports of cracks of the upper splice fittings at station (STA) 2598. There have been a total of seven cracks reported on the upper splice fittings on six different airplanes. During accomplishment of Boeing Service Bulletin 747–53A2473, an operator reported a crack approximately 0.30 inches long at a fastener hole in the splice fitting at STA 2598. The crack was in the outboard flange at a location which is outside of the area inspected in accordance with Boeing Service Bulletin 747–53A2473. The airplane had accumulated 112,500 flight hours and 18,784 flight cycles when the crack was found. Ground spoiler buffet loading contributes significantly to maximum fatigue damage in the area. This condition, if not addressed, could result in undetected fatigue cracks of the bulkhead splice fitting, which could lead to failure in the critical attach structure and loss of the horizontal stabilizer, and adversely affect the structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 The FAA reviewed Boeing Alert Requirements Bulletin 747–53A2899 RB, dated April 5, 2019. The service information describes procedures for repetitive detailed inspections and open E:\FR\FM\31DEP1.SGM 31DEP1

Agencies

[Federal Register Volume 84, Number 250 (Tuesday, December 31, 2019)]
[Proposed Rules]
[Pages 72257-72260]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-27939]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0537; Product Identifier 2019-NE-16-AD]
RIN 2120-AA64


Airworthiness Directives; Anjou Aeronautique Torso Restraint 
Systems

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede airworthiness directive (AD) 
2017-16-04 which applies to certain Anjou Aeronautique (formerly Romtex 
Anjou Aeronautique) Model 358 torso restraint systems (restraint 
systems). AD 2017-16-04 required inspection of the restraint system, 
placarding if it is found to be inoperative, and replacement of the 
affected restraint system with a part eligible for installation. Since 
the FAA issued AD 2017-16-04, the European Union Aviation Safety Agency 
(EASA) received reports of additional serial numbered restraint systems 
rotary buckle knobs (buckle knobs) breaking on a batch of parts outside 
of the previous population. This proposed AD would require the removal 
from service of this expanded population of affected restraint systems 
and modifies the compliance schedule for their removal. 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 February 
14, 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.
     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 Anjou 
Aeronautique, Strada Livezii nr. 98, 550042, Sibiu, Romania; telephone: 
+40 269 243 918; fax: +40 269 243 921; email: [email protected]. 
You may view this service information at the FAA, Engine and Propeller 
Standards Branch, 1200 District Avenue, Burlington, MA 01803. 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 on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0537; 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, the mandatory continuing airworthiness information (MCAI), 
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: Dorie Resnik, Aerospace Engineer, 
Boston ACO Branch, FAA, 1200 District Avenue, Burlington, MA, 01803; 
phone: 781-238-7693; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2019-0537; 
Product Identifier 2019-NE-16-AD'' at

[[Page 72258]]

the beginning of your comments. The FAA specifically invites comments 
on the overall regulatory, economic, environmental, and energy aspects 
of this NPRM. The FAA will consider all comments received by the 
closing date and may amend this NPRM 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 received about this proposed AD.

Discussion

    The FAA issued AD 2017-16-04, Amendment 39-18981 (82 FR 39355, 
August 18, 2017), (``AD 2017-16-04''), for Anjou Aeronautique restraint 
systems installed on, but not limited to, Airbus Helicopters Model 
AS350B2, AS350B3, EC130B4, EC130T2, and AS355NP helicopters. AD 2017-
16-04 requires inspection of the restraint system, placarding if it is 
found to be inoperative, and replacement of the affected restraint 
system with a part eligible for installation. AD 2017-16-04 resulted 
from reports of a population of buckle knobs breaking due to the 
alteration of rotary buckle sub-assembly by a supplier of Anjou 
Aeronautique to a specification different from the approved design 
data. The FAA issued AD 2017-16-04 to prevent a restraint system from 
failing to release due to the buckle knobs breaking off, preventing 
occupants from exiting the helicopter during an emergency.

Actions Since AD 2017-16-04 Was Issued

    Since the FAA issued AD 2017-16-04, EASA received reports of 
additional Anjou Aeronautique Model 358 buckle knobs breaking on a 
batch of parts affected by the same unsafe condition due to an unknown 
root cause. As a result, EASA issued AD 2018-0195, dated September 4, 
2018, which identifies a population of the restraint systems to be 
removed from service.

Revision to Cost Estimate

    The FAA determined the need to clarify the estimated cost in AD 
2017-16-04. The cost reflected in AD 2017-16-04 is the total cost per 
helicopter ($6,000 per restraint system multiplied by 7 seats per 
helicopter totaling $42,000). In this AD, the FAA is providing the cost 
estimate per restraint system.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Anjou Aero Service Bulletin (SB) No. 358SB-14-101, 
Revision 1, dated December 12, 2014. The SB describes procedures for 
removing from service and replacing the rotary buckle sub-assembly on 
certain part-numbered and serial-numbered buckle assemblies, consisting 
of the rotary buckle, belt, and attachment. 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 proposing this AD because it 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.

Proposed AD Requirements

    This proposed AD would retain certain requirements of AD 2017-16-
04. This proposed AD expands the populations of affected restrains 
systems and modifies the compliance schedule for their removal.

Differences Between the Proposed AD and MCAI

    EASA AD 2018-0195, dated September 4, 2018, requires replacement of 
the affected restraint system within six months after the effective 
date of the EASA AD. This proposed AD would require inspection of each 
restraint system within 30 hours time in service (TIS) after the 
effective date of the AD and replacement of the rotary buckle sub-
assembly within 180 hours TIS after the effective date of this AD. 
Additionally, the EASA AD applies to restraint systems installed on, 
but not limited to, Airbus Helicopter AS350B2, AS350B3, and EC130T2 
helicopters. This proposed AD would apply to restraint systems 
installed on, but not limited to, Airbus Helicopters AS350B2, AS350B3, 
EC130B4, EC130T2, and AS355NP helicopters.

Costs of Compliance

    The FAA estimates that this proposed AD affects an unknown number 
of restraint systems installed on, but not limited to, Airbus 
Helicopters AS350B2, AS350B3, EC130B4, EC130T2, and AS355NP helicopters 
of U.S. registry.
    The FAA estimates the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Inspect restraint system......................  0.5 work-hours x $85 per hour =               $0          $42.50
                                                 $42.50.
Remove and replace restraint system...........  0.5 work-hours x $85 per hour =            6,000        6,042.50
                                                 $42.50.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Placard seat as inoperable....................  0.1 work-hour x $85 per hour =                $0           $8.50
                                                 $8.50.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. The FAA does not control warranty coverage for 
affected

[[Page 72259]]

individuals. As a result, the FAA has included all costs in its 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 engines, propellers, and 
associated appliances to the Manager, Engine and Propeller Standards 
Branch, Policy and Innovation Division.

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 that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2017-16-04, Amendment 39-18981 (82 FR 39355, August 18, 2017), and 
adding the following new AD:

Anjou Aeronautique (formerly Romtex Anjou Aeronautique): Docket No. 
FAA-2019-0537; Product Identifier 2019-NE-16-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by February 14, 
2020.

(b) Affected ADs

    This AD replaces AD 2017-16-04, Amendment 39-18981 (82 FR 39355, 
August 18, 2017).

(c) Applicability

    (1) This AD applies to Anjou Aeronautique Model 358 torso 
restraint systems (restraint systems), part number (P/N) 358XX-XXX-
YY-ZZZ (where 358XX-XXX-YY-ZZZ can be any combination of numbers 
and/or letters), with serial numbers (S/Ns) listed in Effectivity, 
paragraph 1.2, of Anjou Aero Service Bulletin (SB) No. 358SB-14-101, 
Revision 1, dated December 12, 2014, and with S/Ns listed in Figure 
1 to Paragraph (c)(1) of this AD.

               Figure 1 to Paragraph (c)(1)--Applicability
------------------------------------------------------------------------
     S/N (From . . . inclusive)           S/N (To . . .  inclusive)
------------------------------------------------------------------------
                     738                                 1037
                    1049                                 1049
                    1056                                 1061
                    1074                                 1619
------------------------------------------------------------------------

    (2) These restraint systems are installed on, but not limited 
to, Airbus Helicopters AS350B2, AS350B3, EC130B4, EC130T2, and 
AS355NP helicopters, certificated in any category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports to the European Union Aviation 
Safety Agency (EASA) of additional restraint system buckle knobs, 
since the publication of AD 2017-16-04, breaking on a batch of parts 
outside of the population identified in AD 2017-16-04. The FAA is 
issuing this AD to prevent a restraint system strap from failing to 
release from the buckle, causing occupants to be unable to exit the 
aircraft during an emergency. The unsafe condition, if not 
addressed, could result in a restraint system strap failing to 
release from the buckle, resulting in injury or death of the 
occupant.

(f) Compliance

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

(g) Required Actions

    (1) For the restraint systems listed in the Effectivity, 
paragraph 1.2, of Anjou Aero SB No. 358SB-14-101, Revision 1, dated 
December 12, 2014, except for S/Ns 1038-1048 (inclusive), 1050-1055 
(inclusive), and 1062-1073 (inclusive), within 30 hours time-in-
service (TIS) after the effective date of this AD, inspect each 
restraint system for proper release of the straps from the restraint 
system.
    (i) If the straps do not release from the restraint system, 
before further flight, placard the seat as inoperative. Within 180 
hours TIS after the effective date of this AD, remove the rotary 
buckle sub-assembly and replace it with a part eligible for 
installation.
    (ii) If the straps release from the restraint system, within 180 
hours TIS after the effective date of this AD, remove the rotary 
buckle sub-assembly and replace it with a part eligible for 
installation.
    (2) For restraint systems, P/N 358XX-XXX-YY-ZZZ (where 358XX-
XXX-YY-ZZZ can be any combination of numbers and/or letters), having 
S/Ns 738-1619 (inclusive), within 30 hours TIS after the effective 
date of this AD, inspect the restraint system for proper release of 
the straps from the restraint system.
    (i) If the straps do not release from the restraint system, 
before further flight, placard the seat as inoperative and within 
180 hours TIS after the effective date of this AD, remove the 
restraint system from service and replace it with a part eligible 
for installation.
    (ii) If the straps release from the restraint system, within 180 
hours TIS or six months after the effective date of this AD, 
whichever occurs first, remove the restraint system from service and 
replace it with a part eligible for installation.

(h) Installation Prohibition

    After the effective date of this AD, do not install on any 
aircraft an Anjou Aeronautique restraint system, P/N 358XX-XXX-YY-
ZZZ, having S/Ns 738-1619 (inclusive), even if the restraint system 
is labeled in compliance with Anjou Aero SB No. 358SB-14-101, 
Revision 1, dated December 12, 2014.

(i) Definition

    For the purpose of this AD, a ``part eligible for installation'' 
is an Anjou Aeronautique restraint system, excluding P/N 358XX-XXX-
YY-ZZZ, having S/Ns 738-1619 (inclusive), that had the rotary buckle 
sub-system repaired and a label attached indicating compliance with 
Anjou Aero SB No. 358SB-14-101, Revision 1, dated December 12, 2014, 
or later revisions.

[[Page 72260]]

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Boston 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 (k)(1) 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.

(k) Related Information

    (1) For more information about this AD, contact Dorie Resnik, 
Aerospace Engineer, Boston ACO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7693; fax: 781-238-7199; email: 
[email protected].
    (2) Refer to EASA AD 2018-0195, dated September 4, 2018, for 
more information. You may examine the EASA AD in the AD docket on 
the internet at https://www.regulations.gov by searching for and 
locating it in Docket No. FAA-2019-0537.
    (3) For service information identified in this AD, contact Anjou 
Aeronautique, Strada Livezii nr. 98, 550042, Sibiu, Romania; 
telephone: +40 269 243 918; fax: +40 269 243 921; email: 
[email protected]. You may view this referenced service 
information at the FAA, Engine and Propeller Standards Branch, 1200 
District Avenue, Burlington, MA 01803. For information on the 
availability of this material at the FAA, call 781-238-7759.

    Issued in Burlington, Massachusetts, on December 20, 2019.
Karen M. Grant,
Acting Manager, Engine & Propeller Standards Branch, Aircraft 
Certification Service.
[FR Doc. 2019-27939 Filed 12-30-19; 8:45 am]
 BILLING CODE 4910-13-P