Airworthiness Directives; Airbus Airplanes, 49146-49149 [2017-23014]

Download as PDF 49146 Federal Register / Vol. 82, No. 204 / Tuesday, October 24, 2017 / Proposed Rules Bulletin 32–JA981042 Rev 9, dated July 11, 2017. (3) For all affected airplane models: Before further flight after the effective date of this AD, revise the FAA-approved maintenance program (instructions for continued airworthiness) on the basis of which the operator or the owner ensures the continuing airworthiness of each operated airplane, as applicable to the airplane model, by incorporating the limitations described in BAE Systems British Aerospace Jetstream Series 3100 and 3200 Service Bulletin 32– JA981042 Rev 9, dated July 11, 2017, as applicable to the airplane model and depending on the airplane configuration. (4) For all airplanes: The compliance times in paragraphs (f)(1) and (2) of this AD are presented in flight cycles (landings). If the total flight cycles have not been kept, multiply the total number of airplane hours time-in-service (TIS) by 0.75 to calculate the cycles. For the purposes of this AD: (i) 100 hours TIS × .75 = 75 cycles; and (ii) 1,000 hours TIS × .75 = 750 cycles. ethrower on DSK3G9T082PROD with PROPOSALS (g) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Small Airplane Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; fax: (816) 329–4090; email: doug.rudolph@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, Small Airplane Standards Branch, FAA; or the European Aviation Safety Agency (EASA). (h) Related Information (1) Refer to MCAI EASA AD 2017–0157, dated August 25, 2017, and BAE Systems British Aerospace Jetstream Series 3100 and 3200 Service Bulletin 32–JA981042 Rev 9, dated July 11, 2017, for related information. You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2017–0993. For service information related to this AD, contact BAE Systems (Operations) Limited, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; telephone: +44 1292 675207; fax: +44 1292 675704; email: RApublications@baesystems.com; Internet: https://www.baesystems.com/Businesses/ RegionalAircraft/. You may review copies of the referenced service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. VerDate Sep<11>2014 18:07 Oct 23, 2017 Jkt 244001 Issued in Kansas City, Missouri, on October 12, 2017. Melvin J. Johnson, Acting Deputy Director, Policy & Innovation Division, Aircraft Certification Service. [FR Doc. 2017–22708 Filed 10–23–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–1020; Product Identifier 2017–NM–114–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318–111 and –112 airplanes; Model A319–111, –112, –113, –114, and –115 airplanes; Model A320– 211, –212, –214, and –216 airplanes; and Model A321–111, –112, –211, –212, and –213 airplanes. This proposed AD was prompted by a review of maintenance instructions for a blend repair of the snout diameter of the main beam assembly of the forward engine mount that would create an excessive gap between the bearing mono-ball and the snout. This proposed AD would require modifying the main beam assembly of the forward engine mount. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by December 8, 2017. 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 Airbus, Airworthiness Office–EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac SUMMARY: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; Internet: https://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. 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–2017– 1020; or in person at the Docket Management Facility 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 the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227– 1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite 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– 2017–1020; Product Identifier 2017– NM–114–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017–0132, dated July 27, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318–111 and –112 airplanes; Model A319–111, –112, E:\FR\FM\24OCP1.SGM 24OCP1 Federal Register / Vol. 82, No. 204 / Tuesday, October 24, 2017 / Proposed Rules affected forward engine mount main beam assemblies. As the same main beam assemblies are certified for CFM56–5A engine installation, this [EASA] AD also applies to aeroplanes with that engine. –113, –114, and –115 airplanes; Model A320–211, –212, –214, and –216 airplanes; and Model A321–111, –112, –211, –212, and –213 airplanes. The MCAI states: A review of maintenance instructions revealed that the Goodrich Aerospace CFM56–5B, Forward Engine Mount Component Maintenance Manual (CMM) 71– 21–08, revision (rev.) 1 up to 46 (inclusive), repair 10 (Blend Repair-Beam Assembly Snout Diameter), provides instructions to blend the wear on the forward engine mount assembly, Part Number (P/N) 642–2000–9, 642–2000–13, or 642–2000–25, creating an excessive gap between the bearing mono-ball and the snout of the forward engine mount main beam assembly, P/N 642–2006–501, or P/N 642–2006–503. This condition, if not detected and corrected, could lead to in-flight failure of a forward engine mount and consequent detachment of an engine, possibly resulting in reduced control of the aeroplane and injury to persons on the ground. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320– 71–1065 and SB A320–71–1066, and Goodrich Aerospace issued SB RA32071– 159, providing instructions for an in-shop inspection(s) for the main beam snout and, depending on findings, applicable corrective action(s) and re-identification. For the reason described above, this [EASA] AD requires replacement of the Required actions include modifying the main beam assembly of the forward engine mount. The modification includes repairing, replacing, or reworking the main beam assembly. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 1020. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–71–1065, Revision 01, dated July 28, 2017. This service information describes procedures for modifying the main beam assembly of the forward engine mount. The modification includes, among other things, repair or replacement of the main beam assembly. Airbus has also issued Service Bulletin A320–71–1066, dated December 1, 2016. This service information describes procedures for modifying the main beam assembly of the forward engine mount. The 49147 modification includes, among other things, rework of the main beam assembly. 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 and Requirements of This Proposed AD 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 the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Costs of Compliance We estimate that this proposed AD affects 500 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Modification .................. Up to 76 work-hours × $85 per hour = $6,460 ... ethrower on DSK3G9T082PROD 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. We are 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 proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by VerDate Sep<11>2014 18:07 Oct 23, 2017 Jkt 244001 Parts cost $778 Cost per product Up to $7,238 ................ Cost on U.S. operators Up to $3,619,000. 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 transport category airplanes to the Director of the System Oversight Division. 3. Will not affect intrastate aviation in Alaska; and 4. 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. Regulatory Findings Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. We 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. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 List of Subjects in 14 CFR Part 39 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. E:\FR\FM\24OCP1.SGM 24OCP1 49148 § 39.13 Federal Register / Vol. 82, No. 204 / Tuesday, October 24, 2017 / Proposed Rules (h) Definition of Qualifying Inspection [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2017–1020; Product Identifier 2017–NM–114–AD. (a) Comments Due Date We must receive comments by December 8, 2017. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Model A318– 111 and –112 airplanes; Model A319–111, –112, –113, –114, and –115 airplanes; Model A320–211, –212, –214, and –216 airplanes; and Model A321–111, –112, –211, –212, and –213 airplanes; certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by a review of maintenance instructions for a blend repair of the diameter of the snout of the main beam assembly of the forward engine mount that would create an excessive gap between the bearing mono-ball and the snout. We are issuing this AD to prevent in-flight failure of a forward engine mount, and consequent detachment of an engine, which could result in reduced controllability of the airplane. ethrower on DSK3G9T082PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of Affected Parts For the purposes of this AD: An ‘‘affected main beam’’ is any main beam assembly of the forward engine mount, part number (P/ N) 642–2006–501 or P/N 642–2006–503, identified in paragraph (g)(1) or (g)(2) of this AD. (1) Any part for which no maintenance records are available to confirm the part has never been repaired. (2) Any part that was repaired as specified in the instructions of Goodrich Aerospace component maintenance manual (CMM) 71– 21–08, Revision 1 through 46, repair 10, except for parts identified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. (i) Any part on which a qualifying inspection identified in paragraph (h) of this AD has been done and there were no findings (the inspection was passed). (ii) Any part on which a qualifying inspection identified in paragraph (h) of this AD has been done and that part has been repaired as specified in the instructions of Goodrich Aerospace Service Bulletin RA32071–159. (iii) Any part that has been repaired in accordance with other instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). VerDate Sep<11>2014 18:07 Oct 23, 2017 Jkt 244001 (n) Other FAA AD Provisions For the purposes of this AD: ‘‘A qualifying inspection’’ is an inspection done as specified in the instructions of Goodrich Aerospace Service Bulletin RA32071–159; or for CFM56–5B engines, an inspection done as specified in the instructions of Goodrich Aerospace CMM 71–21–08, Revision 47, repair 10; or for CFM56–5A engines, an inspection done as specified in the instructions of Goodrich Aerospace CMM 71–21–06, Revision 59, repair 21. The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Section, send it to the attention of the person identified in paragraph (o)(2) of this AD. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): Except as required by paragraph (k) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified 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 procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (i) Definition of Airplane Groups For the purposes of this AD: ‘‘Group 1 airplanes’’ are airplanes on which an affected main beam has been installed as of the effective date of this AD. ‘‘Group 2 airplanes’’ are airplanes on which an affected main beam has not been installed as of the effective date of this AD; this includes airplanes with an original certificate of airworthiness or original export certificate of airworthiness that was issued after the effective date of this AD. (j) Modification of Affected Main Beam Assemblies For Group 1 airplanes as identified in paragraph (i) of this AD: At the earliest of the compliance times specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD, modify each affected main beam identified in paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–71–1065, Revision 01, dated July 28, 2017; and Airbus Service Bulletin A320–71–1066, dated December 1, 2016; as applicable, except as required by paragraph (k) of this AD. (1) Within 48 months after the effective date of this AD. (2) Within 10,000 flight cycles after the effective date of this AD. (3) Within 15,000 flight hours after the effective date of this AD. (k) Exception to Service Information Where Airbus Service Bulletin A320–71– 1065, Revision 01, dated July 28, 2017, specifies to contact a manufacturer for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (n)(2) of this AD. (l) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (j) of this AD involving Airbus Service Bulletin A320–71– 1065, Revision 01, dated July 28, 2017, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–71–1065, dated December 1, 2016. (m) Parts Installation Prohibition As of the effective date of this AD, no person may install an affected main beam identified in paragraph (g) of this AD or a forward engine mount assembly equipped with an affected main beam identified in paragraph (g) of this AD, on any airplane. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0132, dated July 27, 2017, for related information. This MCAI may be found in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017–1020. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425– 227–1405; fax 425–227–1149. (3) For service information identified in this AD, contact Airbus, Airworthiness Office–EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; Internet: https://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. E:\FR\FM\24OCP1.SGM 24OCP1 Federal Register / Vol. 82, No. 204 / Tuesday, October 24, 2017 / Proposed Rules Issued in Renton, Washington, on October 17, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–23014 Filed 10–23–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0909; Product Identifier 2017–NM–081–AD] RIN 2120–AA64 Airworthiness Directives; Dassault Aviation Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Dassault Aviation Model MYSTERE– FALCON 900, FALCON 900EX, FALCON 2000, and FALCON 2000EX airplanes. This proposed AD was prompted by reports of a loose screw on certain slat mechanical stop assemblies, and punctures in certain fuel caps. This proposed AD would require a one-time inspection, and corrective action if necessary. We are proposing this AD to address the unsafe condition on these products. SUMMARY: We must receive comments on this proposed AD by December 8, 2017. 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 Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201–440–6700; Internet https://www.dassaultfalcon.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue ethrower on DSK3G9T082PROD with PROPOSALS DATES: VerDate Sep<11>2014 18:07 Oct 23, 2017 Jkt 244001 SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. 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–2017– 0909; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425–227– 1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite 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– 2017–0909; Product Identifier 2017– NM–081–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2017–0106, dated June 19, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Dassault Aviation Model MYSTERE–FALCON 900, FALCON 900EX, FALCON 2000, and FALCON 2000EX airplanes. The MCAI states: On some aeroplanes in-service, the screw of the slat mechanical stop assembly on slat PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 49149 tracks #6, #7 and #8 was found loose. In some cases, a puncture was found in the fuel cap. The results of the technical investigations concluded that the most probable reason for these events was improper installation of the lock washers on the screws during production or maintenance. This condition, if not detected and corrected, could lead to structural damage to the wing front spar, and consequent fuel leakage, possibly resulting in an uncontrolled fire. To address this potential unsafe condition, Dassault issued [Service Bulletin] SB F900– 460 Revision 1, SB F900EX–508 Revision 3, SB F2000–433 Revision 1, and SB F2000EX– 386 Revision 3 (hereafter collectively referred as ‘the applicable SB’ in this [EASA] AD), as applicable to aeroplane type/model, to provide inspection instructions. For the reasons described above, this [EASA] AD requires a one-time [general visual] inspection of the slat tracks #6, #7 and #8 to verify the tightening torque of the screw and proper lock washer installation and, depending on findings, accomplishment of applicable corrective action(s). Applicable corrective actions include replacement, if necessary. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0909. Related Service Information Under 1 CFR Part 51 Dassault Aviation has issued the following service information. • Dassault Service Bulletin F900–460, Revision 1, dated February 10, 2017 • Dassault Service Bulletin F900EX– 508, Revision 3, dated February 10, 2017 • Dassault Service Bulletin F2000–433, Revision 1, dated February 10, 2017 • Dassault Service Bulletin F2000EX– 386, Revision 3, dated February 10, 2017 This service information describes procedures for doing a one-time general visual inspection of the screw on the affected slat tracks, and replacement if necessary. These documents are distinct since they apply to different airplane models. The 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 and Requirements of This Proposed AD 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 the State of Design Authority, we have been notified E:\FR\FM\24OCP1.SGM 24OCP1

Agencies

[Federal Register Volume 82, Number 204 (Tuesday, October 24, 2017)]
[Proposed Rules]
[Pages 49146-49149]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-23014]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1020; Product Identifier 2017-NM-114-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -
114, and -115 airplanes; Model A320-211, -212, -214, and -216 
airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. 
This proposed AD was prompted by a review of maintenance instructions 
for a blend repair of the snout diameter of the main beam assembly of 
the forward engine mount that would create an excessive gap between the 
bearing mono-ball and the snout. This proposed AD would require 
modifying the main beam assembly of the forward engine mount. We are 
proposing this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by December 8, 
2017.

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 Airbus, 
Airworthiness Office-EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; 
email: [email protected]; Internet: https://www.airbus.com. You may view this service information at the FAA, 
Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 425-
227-1221.

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-2017-
1020; or in person at the Docket Management Facility 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 the Docket Operations 
office (telephone 800-647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-
1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite 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-2017-1020; 
Product Identifier 2017-NM-114-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM based on 
those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0132, dated July 27, 2017 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for all Airbus Model A318-111 and -112 airplanes; 
Model A319-111, -112,

[[Page 49147]]

-113, -114, and -115 airplanes; Model A320-211, -212, -214, and -216 
airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. 
The MCAI states:

    A review of maintenance instructions revealed that the Goodrich 
Aerospace CFM56-5B, Forward Engine Mount Component Maintenance 
Manual (CMM) 71-21-08, revision (rev.) 1 up to 46 (inclusive), 
repair 10 (Blend Repair-Beam Assembly Snout Diameter), provides 
instructions to blend the wear on the forward engine mount assembly, 
Part Number (P/N) 642-2000-9, 642-2000-13, or 642-2000-25, creating 
an excessive gap between the bearing mono-ball and the snout of the 
forward engine mount main beam assembly, P/N 642-2006-501, or P/N 
642-2006-503.
    This condition, if not detected and corrected, could lead to in-
flight failure of a forward engine mount and consequent detachment 
of an engine, possibly resulting in reduced control of the aeroplane 
and injury to persons on the ground.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A320-71-1065 and SB A320-71-1066, and Goodrich 
Aerospace issued SB RA32071-159, providing instructions for an in-
shop inspection(s) for the main beam snout and, depending on 
findings, applicable corrective action(s) and re-identification.
    For the reason described above, this [EASA] AD requires 
replacement of the affected forward engine mount main beam 
assemblies. As the same main beam assemblies are certified for 
CFM56-5A engine installation, this [EASA] AD also applies to 
aeroplanes with that engine.

    Required actions include modifying the main beam assembly of the 
forward engine mount. The modification includes repairing, replacing, 
or reworking the main beam assembly. You may examine the MCAI in the AD 
docket on the Internet at https://www.regulations.gov by searching for 
and locating Docket No. FAA-2017-1020.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-71-1065, Revision 01, dated 
July 28, 2017. This service information describes procedures for 
modifying the main beam assembly of the forward engine mount. The 
modification includes, among other things, repair or replacement of the 
main beam assembly.
    Airbus has also issued Service Bulletin A320-71-1066, dated 
December 1, 2016. This service information describes procedures for 
modifying the main beam assembly of the forward engine mount. The 
modification includes, among other things, rework of the main beam 
assembly.
    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 and Requirements of This Proposed AD

    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 the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 500 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Modification.....................  Up to 76 work-hours            $778  Up to $7,238.......  Up to $3,619,000.
                                    x $85 per hour =
                                    $6,460.
----------------------------------------------------------------------------------------------------------------

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.
    We are 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 proposed 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 transport category airplanes to the Director of the System Oversight 
Division.

Regulatory Findings

    We 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. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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.

[[Page 49148]]

Sec.  39.13  [Amended]

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

Airbus: Docket No. FAA-2017-1020; Product Identifier 2017-NM-114-AD.

(a) Comments Due Date

    We must receive comments by December 8, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Model A318-111 and -112 airplanes; 
Model A319-111, -112, -113, -114, and -115 airplanes; Model A320-
211, -212, -214, and -216 airplanes; and Model A321-111, -112, -211, 
-212, and -213 airplanes; certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by a review of maintenance instructions for 
a blend repair of the diameter of the snout of the main beam 
assembly of the forward engine mount that would create an excessive 
gap between the bearing mono-ball and the snout. We are issuing this 
AD to prevent in-flight failure of a forward engine mount, and 
consequent detachment of an engine, which could result in reduced 
controllability of the airplane.

(f) Compliance

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

(g) Definition of Affected Parts

    For the purposes of this AD: An ``affected main beam'' is any 
main beam assembly of the forward engine mount, part number (P/N) 
642-2006-501 or P/N 642-2006-503, identified in paragraph (g)(1) or 
(g)(2) of this AD.
    (1) Any part for which no maintenance records are available to 
confirm the part has never been repaired.
    (2) Any part that was repaired as specified in the instructions 
of Goodrich Aerospace component maintenance manual (CMM) 71-21-08, 
Revision 1 through 46, repair 10, except for parts identified in 
paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD.
    (i) Any part on which a qualifying inspection identified in 
paragraph (h) of this AD has been done and there were no findings 
(the inspection was passed).
    (ii) Any part on which a qualifying inspection identified in 
paragraph (h) of this AD has been done and that part has been 
repaired as specified in the instructions of Goodrich Aerospace 
Service Bulletin RA32071-159.
    (iii) Any part that has been repaired in accordance with other 
instructions approved by the Manager, International Section, 
Transport Standards Branch, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).

(h) Definition of Qualifying Inspection

    For the purposes of this AD: ``A qualifying inspection'' is an 
inspection done as specified in the instructions of Goodrich 
Aerospace Service Bulletin RA32071-159; or for CFM56-5B engines, an 
inspection done as specified in the instructions of Goodrich 
Aerospace CMM 71-21-08, Revision 47, repair 10; or for CFM56-5A 
engines, an inspection done as specified in the instructions of 
Goodrich Aerospace CMM 71-21-06, Revision 59, repair 21.

(i) Definition of Airplane Groups

    For the purposes of this AD: ``Group 1 airplanes'' are airplanes 
on which an affected main beam has been installed as of the 
effective date of this AD. ``Group 2 airplanes'' are airplanes on 
which an affected main beam has not been installed as of the 
effective date of this AD; this includes airplanes with an original 
certificate of airworthiness or original export certificate of 
airworthiness that was issued after the effective date of this AD.

(j) Modification of Affected Main Beam Assemblies

    For Group 1 airplanes as identified in paragraph (i) of this AD: 
At the earliest of the compliance times specified in paragraphs 
(j)(1), (j)(2), and (j)(3) of this AD, modify each affected main 
beam identified in paragraph (g) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-71-1065, 
Revision 01, dated July 28, 2017; and Airbus Service Bulletin A320-
71-1066, dated December 1, 2016; as applicable, except as required 
by paragraph (k) of this AD.
    (1) Within 48 months after the effective date of this AD.
    (2) Within 10,000 flight cycles after the effective date of this 
AD.
    (3) Within 15,000 flight hours after the effective date of this 
AD.

(k) Exception to Service Information

    Where Airbus Service Bulletin A320-71-1065, Revision 01, dated 
July 28, 2017, specifies to contact a manufacturer for appropriate 
action, and specifies that action as ``RC'' (Required for 
Compliance): Before further flight, accomplish corrective actions in 
accordance with the procedures specified in paragraph (n)(2) of this 
AD.

(l) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (j) of this AD involving Airbus Service Bulletin A320-71-
1065, Revision 01, dated July 28, 2017, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A320-71-1065, dated December 1, 2016.

(m) Parts Installation Prohibition

    As of the effective date of this AD, no person may install an 
affected main beam identified in paragraph (g) of this AD or a 
forward engine mount assembly equipped with an affected main beam 
identified in paragraph (g) of this AD, on any airplane.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Section, send it to the 
attention of the person identified in paragraph (o)(2) of this AD. 
Information may be emailed to: [email protected]. 
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.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA 
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (k) of this AD: If any service information contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified 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 procedures and tests identified as RC can be done and the 
airplane can be put back in an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0132, dated July 27, 2017, for related 
information. This MCAI may be found in the AD docket on the Internet 
at https://www.regulations.gov by searching for and locating Docket 
No. FAA-2017-1020.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 
425-227-1405; fax 425-227-1149.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office-EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 
5 61 93 44 51; email: [email protected]; Internet: 
https://www.airbus.com. You may view this service information at the 
FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.


[[Page 49149]]


    Issued in Renton, Washington, on October 17, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-23014 Filed 10-23-17; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.