Airworthiness Directives; Airbus Airplanes, 11304-11307 [2017-03260]

Download as PDF 11304 Federal Register / Vol. 82, No. 34 / Wednesday, February 22, 2017 / Rules and Regulations Issued in Renton, Washington, on February 8, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–03261 Filed 2–21–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9305; Directorate Identifier 2016–NM–073–AD; Amendment 39–18804; AD 2017–04–09] Examining the AD Docket RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2012–22– 12 for all Airbus Model A330–243, –243F, –341, –342, and –343 airplanes. AD 2012–22–12 required inspecting piccolo tubes and mount links, the aft side of the forward bulkhead, and outer boundary angles (OBAs); and doing corrective actions if necessary. This new AD retains certain requirements of AD 2012–22–12, and adds inspections of certain areas of the forward bulkhead, and related investigative and corrective actions if necessary. This AD was prompted by reports of cracking of air intake cowls, worn and detached attachment links, fractured thermal antiice (TAI) piccolo tubes, and loose or missing attachment rivets of the inner boundary angles (IBAs) and OBAs of the forward bulkhead. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 29, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 29, 2017. ADDRESSES: For Airbus service information identified in this final rule, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330A340@airbus.com; Internet https:// www.airbus.com. For Rolls-Royce service information identified in this final rule, contact Rolls-Royce Plc, Technical Publications, sradovich on DSK3GMQ082PROD with RULES SUMMARY: VerDate Sep<11>2014 18:04 Feb 21, 2017 Jkt 241001 P.O. Box 31, Derby, DE24 8BJ, United Kingdom; telephone 44 (0) 1332 245882; fax 44 (0) 1332 249936; Internet https:// www.Rolls-Royce.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9305. You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9305; 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2012–22–12, Amendment 39–17248 (77 FR 67263, November 9, 2012) (‘‘AD 2012–22–12’’). AD 2012–22–12 applied to all Airbus Model A330–243, –243F, –341, –342, and –343 airplanes. The NPRM published in the Federal Register on November 7, 2016 (81 FR 78085). The NPRM was prompted by reports of cracking of air intake cowls on RollsRoyce Trent engines, worn and detached attachment links, fractured TAI piccolo tubes, and loose or missing attachment rivets of the IBAs and the OBAs of the forward bulkhead. The NPRM proposed to retain certain requirements of AD 2012–22–12, and add repetitive inspections for pulled, loose, and missing attachment rivets of the IBAs and OBAs of the forward bulkhead, and related investigative and corrective actions if necessary. We are PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 issuing this AD to detect and correct degraded structural integrity of the engine nose cowl, which in the case of forward bulkhead damage in conjunction with a broken piccolo tube, could lead to damage to the engine and operation in icing conditions with reduced TAI performance. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive, 2016–0086R1, dated May 13, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model 330–243, –243F, –341, –342, and –343 airplanes. The MCAI states: During shop visit, cracks were found in several primary structural parts of Rolls Royce (RR) Trent 700 engine air intake cowls, specifically in the forward bulkhead web, web stiffeners and outer boundary angles (OBA). In addition, several attachment links were found severely worn, and some became detached. In two cases, the thermal anti-ice (TAI) piccolo tube was found fractured. Investigation results show that the cracks are most likely due to acoustic excitation and vibration. A broken piccolo tube, if not detected and corrected, in conjunction with forward air intake cowl bulkhead damage, could lead to in-flight detachment of the outer barrel, possibly resulting in damage to the engine or reduced control of the aeroplane. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A330– 71–3025, making reference to RR SB RB.211– 71–AG416, to provide inspection instructions, and, depending on findings, accomplishment of applicable corrective action(s). Consequently, EASA issued AD 2011–0062 [which corresponds to FAA AD 2012–22–12] to require repetitive special detailed inspections (SDI) [borescope] of the piccolo tube and affected mount links, the aft side of forward bulkhead, inner boundary angles (IBA) and OBA of the RR Trent 700 air intake cowl assemblies, and, depending on findings, accomplishment of applicable corrective action(s). Since EASA AD 2011–0062 was issued, some occurrences were reported of finding attachment rivets of the IBA and OBA either pulled, loose, or missing during inspection. It was determined that the affected IBA and OBA rivets may not have been previously inspected if operators accomplished the required inspection in accordance with the instructions of RR SB RB.211–71–AG416 at original issue. To address this potentially missed inspection, Airbus published SB A330–71– 3033, providing instructions for a one-time detailed inspection of the IBA and OBA attachment rivets, to be accomplished if the previous inspection was accomplished using the instructions of RR SB RB.211–71–AG416 at original issue. Airbus also published SB A330–71–3025 Revision 2, adding an inspection of the IBA and OBA attachment E:\FR\FM\22FER1.SGM 22FER1 11305 Federal Register / Vol. 82, No. 34 / Wednesday, February 22, 2017 / Rules and Regulations rivets, to be used if the previous inspection was accomplished using RR SB RB.211–71– AG416 at issue 1 or later. Airbus also published SB A330–71–3032 to introduce a modification (mod) that would eliminate the need for repetitive inspections. For the reasons described above, this [EASA] AD partially retains the requirements of EASA AD 2011–0062, which is superseded, and requires an additional [special] detailed inspection [borescope] of IBA and OBA forward bulkhead attachment rivets. This [EASA] AD also introduces an optional terminating action (Airbus mod 204615, embodied in production, which can be embodied in service with Airbus SB A330–71–3032) for the repetitive inspections required by this [EASA] AD. This [EASA] AD is revised to improve clarity, including Airbus and RR SB references and inserting Notes to identify the Part Numbers (P/N) of the affected engine air intake nose cowl assemblies. Related investigative actions include inspecting for cracked or fractured piccolo tubes and for broken piccolo tube links. Corrective actions include replacing the engine air intake cowl assembly and repair of pulled, loose, or missing rivets. The compliance times for the related investigative and corrective actions range from before further flight to within 100 flight cycles, depending on the findings of the inspections. The repetitive inspection interval for the IBAs, OBAs, and forward bulkhead varies depending on inspection findings, and ranges between 200 and 5,000 flight cycles. The repetitive inspection interval for the piccolo tubes and links is 2,500 flight cycles. 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–2016– 9305. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A330–71–3025, Revision 02, dated December 9, 2015. This service information describes procedures for inspections of the piccolo tube and mount links, the aft side of the forward bulkhead, the IBAs, OBAs, and the forward bulkhead on the engine air intake cowl assemblies; and related investigative and corrective actions. Airbus also has issued Service Bulletin A330–71–3032, dated December 10, 2014. This service information describes procedures for a modification that improves the air intake primary structure and adds a new piccolo tube supporting structure on the engine air intake cowl assemblies. In addition, Airbus has issued Service Bulletin A330–71–3033, dated December 14, 2015. This service information describes procedures for an inspection for pulled, loose, and missing attachment rivets of the IBAs and OBAs of the forward bulkhead, and corrective actions. Rolls-Royce has issued Service Bulletin RB.211–71–H205, dated July 7, 2014. This service information describes procedures for modifying the nose cowl assembly acoustic panels. Rolls-Royce also has issued Service Bulletin RB.211–71–H847, dated December 2, 2014. This service information describes procedures for modifying the air intake nose cowl assembly, forward bulkhead assembly, TAI spray ring, and the TAI spray ring supporting hardware. 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. Costs of Compliance We estimate that this AD affects 47 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Inspections (new action) 12 work-hours × $85 per hour = $1,020 per inspection cycle. $0 Cost per product Cost on U.S. operators $1,020 per inspection cycle. $47,940 per inspection cycle. ESTIMATED COSTS FOR OPTIONAL ACTIONS Action Labor cost Modification ............................. Up to 142 work-hours × $85 per hour = $12,070 .................... [1] We Cost per product Parts cost [1] Up to $12,070. have received no definitive data that will enable us to provide material cost estimates for the optional actions specified in this AD. We estimate the following costs to do any necessary repairs that will be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these repairs: sradovich on DSK3GMQ082PROD with RULES ON-CONDITION COSTS Action Labor cost Repairs ............................................. 16 work-hours × $85 per hour = $1,360 ................................................... [2] We Cost per product Parts cost [2] $1,360 have received no definitive data that will enable us to provide material cost estimates for the on-condition actions specified in this AD. VerDate Sep<11>2014 18:04 Feb 21, 2017 Jkt 241001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\22FER1.SGM 22FER1 11306 Federal Register / Vol. 82, No. 34 / Wednesday, February 22, 2017 / Rules and Regulations Authority for This Rulemaking § 39.13 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. ■ Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. 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. sradovich on DSK3GMQ082PROD with RULES Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. VerDate Sep<11>2014 18:04 Feb 21, 2017 Jkt 241001 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2012–22–12, Amendment 39–17248 (77 FR 67263, November 9, 2012), and adding the following new AD: 2017–04–09 Airbus: Amendment 39–18804; Docket No. FAA–2016–9305; Directorate Identifier 2016–NM–073–AD. (a) Effective Date This AD is effective March 29, 2017. (b) Affected ADs This AD replaces AD 2012–22–12, Amendment 39–17248 (77 FR 67263, November 9, 2012) (‘‘AD 2012–22–12’’). (c) Applicability This AD applies to Airbus Model A330– 243, –243F, –341, –342, and –343 airplanes, certificated in any category, all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by reports of cracking of air intake cowls on Rolls-Royce Trent engines, worn and detached attachment links, and fractured thermal antiice (TAI) piccolo tubes, and loose, or missing attachment rivets of the inner boundary angles (IBAs) and the outer boundary angles (OBAs) of the forward bulkhead. We are issuing this AD to detect and correct degraded structural integrity of the engine nose cowl, which in the case of forward bulkhead damage in conjunction with a broken piccolo tube, could lead to damage to the engine and operation in icing conditions with reduced TAI performance. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Affected Engine Air Intake Nose Cowl Assemblies The engine air intake nose cowl assemblies affected by this AD have part numbers (P/N) SJ30020, P/N SJ30361, P/N SJ30687, P/N SJ30810, and P/N SJ30811, as specified in Rolls-Royce Service Bulletin RB.211–71– H205, dated July 7, 2014. (1) The engine air intake nose cowl assemblies having P/N SJ30020, P/N SJ30361, and P/N SJ30687 can be modified (reworked and re-identified as P/N SJ30810 (for P/N SJ30020 and P/N SJ30361) and P/N SJ30811 (for P/N SJ30687)), as specified in RollsRoyce Service Bulletin RB.211–71–H205, dated July 7, 2014. (2) The engine air intake nose cowl assemblies having P/N SJ30810 and P/N SJ30811 can be modified (reworked and reidentified as P/N SJ30820 and P/N SJ30821, respectively), as specified in Rolls-Royce Service Bulletin RB.211–71–H847, dated December 2, 2014. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 (h) Inspections, Related Investigative Actions, and Corrective Actions For airplanes in pre-Airbus Modification 204615 and pre-Airbus Service Bulletin A330–71–3032 configuration: At the applicable times specified in paragraph (h)(1) or (h)(2) of this AD, do a special detailed inspection of the piccolo tube and affected mount links, the aft side of the forward bulkhead, and the IBAs and OBAs of the affected engine air intake cowl assemblies specified in paragraph (g) of this AD; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–71–3025, Revision 02, dated December 9, 2015, except as required by paragraph (i) of this AD. Do all applicable related investigative and corrective actions at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A330–71–3025, Revision 02, dated December 9, 2015. Repeat the inspections of the piccolo tube and affected mount links, the aft side of the forward bulkhead, and the IBAs and OBAs of the engine air intake cowl assemblies thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A330–71–3025, Revision 02, dated December 9, 2015. Accomplishment of corrective actions does not constitute terminating action for the repetitive inspections required by this paragraph. (1) For any engine air intake cowl assembly that has accumulated fewer than 5,000 flight cycles since its first installation on an airplane as of the effective date of this AD: Inspect within 24 months after the engine air intake cowl assembly has accumulated 5,000 total flight cycles. (2) For any engine air intake cowl assembly that has accumulated 5,000 or more flight cycles since its first installation on an airplane as of the effective date of this AD: Inspect within 24 months after the effective date of this AD. (i) Service Information Exception Where Airbus Service Bulletin A330–71– 3025, Revision 02, dated December 9, 2015, specifies to contact Bombardier Aerospace— Shorts for instructions, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). (j) Optional Terminating Action Modification of an airplane in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–71–3032, dated December 10, 2014, constitutes terminating action for the repetitive inspections required by paragraph (h) of this AD for the modified airplane only. (k) Parts Installation Limitation As of the effective date of this AD, any preAirbus Modification 204615 part may be installed on any airplane provided that, at the earlier of the applicable times specified in paragraphs (h)(1) and (h)(2) of this AD following installation, the actions required by E:\FR\FM\22FER1.SGM 22FER1 Federal Register / Vol. 82, No. 34 / Wednesday, February 22, 2017 / Rules and Regulations paragraph (h) of this AD have been accomplished on the pre-Airbus Modification 204615 part. sradovich on DSK3GMQ082PROD with RULES (l) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A330–71–3025, dated January 10, 2011, which was incorporated by reference in AD 2012–22–12; or Airbus Service Bulletin A330–71–3025, Revision 01, dated October 24, 2012, which is not incorporated by reference in this AD; provided that, within 1,050 flight cycles after the effective date of this AD, a special detailed inspection for pulled, loose, and missing attachment rivets of the IBAs and OBAs of the forward bulkhead is accomplished; and all applicable corrective actions are done; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–71–3033, dated December 14, 2015. Do all applicable corrective actions before further flight. Accomplishment of corrective actions does not constitute terminating action for the repetitive inspections required by paragraph (h) of this AD. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. (i) 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. (ii) AMOCs approved previously for AD 2012–22–12 are not approved as AMOCs with this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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 Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): 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 VerDate Sep<11>2014 18:04 Feb 21, 2017 Jkt 241001 11307 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. DEPARTMENT OF TRANSPORTATION (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0086R1, dated May 13, 2016, 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–2016–9305. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(5) of this AD. RIN 2120–AA64 (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A330–71–3025, Revision 02, dated December 9, 2015. (ii) Airbus Service Bulletin A330–71–3032, dated December 10, 2014. (iii) Airbus Service Bulletin A330–71– 3033, dated December 14, 2015. (iv) Rolls-Royce Service Bulletin RB.211– 71–H205, dated July 7, 2014. (v) Rolls-Royce Service Bulletin RB.211– 71–H847, dated December 2, 2014. (3) For Airbus service information identified in this AD, contact Airbus SAS— Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330A340@airbus.com; Internet https:// www.airbus.com. (4) For Rolls-Royce service information identified in this AD, contact Rolls-Royce Plc, Technical Publications, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; telephone 44 (0) 1332 245882; fax 44 (0) 1332 249936; Internet https://www.Rolls-Royce.com. (5) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (6) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. SUMMARY: Issued in Renton, Washington, on February 3, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–03260 Filed 2–21–17; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0122; Directorate Identifier 2017–NM–010–AD; Amendment 39–18809; AD 2017–04–14] Airworthiness Directives; Textron Aviation Inc. (Type Certificate Previously Held by Cessna Aircraft Company) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain Textron Aviation Inc. Model 560XL airplanes. This AD requires inspections of the fuel tube and right alternating current (AC) generator wires. This AD was prompted by reports of inadequate separation between the electrical wire bundle and fuel tube. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 9, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 9, 2017. We must receive comments on this AD by April 10, 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 final rule, contact Textron Aviation Inc., P.O. Box 7706, Wichita, KS 67277; telephone 316–517–6215; fax 316–517– 5802; email citationpubs@txtav.com; Internet https://support.cessna.com/ custsupt/csupport/newlogin.jsp. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the E:\FR\FM\22FER1.SGM 22FER1

Agencies

[Federal Register Volume 82, Number 34 (Wednesday, February 22, 2017)]
[Rules and Regulations]
[Pages 11304-11307]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03260]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9305; Directorate Identifier 2016-NM-073-AD; 
Amendment 39-18804; AD 2017-04-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2012-22-12 for 
all Airbus Model A330-243, -243F, -341, -342, and -343 airplanes. AD 
2012-22-12 required inspecting piccolo tubes and mount links, the aft 
side of the forward bulkhead, and outer boundary angles (OBAs); and 
doing corrective actions if necessary. This new AD retains certain 
requirements of AD 2012-22-12, and adds inspections of certain areas of 
the forward bulkhead, and related investigative and corrective actions 
if necessary. This AD was prompted by reports of cracking of air intake 
cowls, worn and detached attachment links, fractured thermal anti-ice 
(TAI) piccolo tubes, and loose or missing attachment rivets of the 
inner boundary angles (IBAs) and OBAs of the forward bulkhead. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective March 29, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 29, 
2017.

ADDRESSES: For Airbus service information identified in this final 
rule, contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 
96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet https://www.airbus.com.
    For Rolls-Royce service information identified in this final rule, 
contact Rolls-Royce Plc, Technical Publications, P.O. Box 31, Derby, 
DE24 8BJ, United Kingdom; telephone 44 (0) 1332 245882; fax 44 (0) 1332 
249936; Internet https://www.Rolls-Royce.com.
    You may view this referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 425-
227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9305.

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-2016-
9305; 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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2012-22-12, Amendment 39-17248 (77 FR 67263, 
November 9, 2012) (``AD 2012-22-12''). AD 2012-22-12 applied to all 
Airbus Model A330-243, -243F, -341, -342, and -343 airplanes. The NPRM 
published in the Federal Register on November 7, 2016 (81 FR 78085). 
The NPRM was prompted by reports of cracking of air intake cowls on 
Rolls-Royce Trent engines, worn and detached attachment links, 
fractured TAI piccolo tubes, and loose or missing attachment rivets of 
the IBAs and the OBAs of the forward bulkhead. The NPRM proposed to 
retain certain requirements of AD 2012-22-12, and add repetitive 
inspections for pulled, loose, and missing attachment rivets of the 
IBAs and OBAs of the forward bulkhead, and related investigative and 
corrective actions if necessary. We are issuing this AD to detect and 
correct degraded structural integrity of the engine nose cowl, which in 
the case of forward bulkhead damage in conjunction with a broken 
piccolo tube, could lead to damage to the engine and operation in icing 
conditions with reduced TAI performance.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive, 2016-0086R1, dated May 13, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 330-
243, -243F, -341, -342, and -343 airplanes. The MCAI states:

    During shop visit, cracks were found in several primary 
structural parts of Rolls Royce (RR) Trent 700 engine air intake 
cowls, specifically in the forward bulkhead web, web stiffeners and 
outer boundary angles (OBA). In addition, several attachment links 
were found severely worn, and some became detached. In two cases, 
the thermal anti-ice (TAI) piccolo tube was found fractured. 
Investigation results show that the cracks are most likely due to 
acoustic excitation and vibration.
    A broken piccolo tube, if not detected and corrected, in 
conjunction with forward air intake cowl bulkhead damage, could lead 
to in-flight detachment of the outer barrel, possibly resulting in 
damage to the engine or reduced control of the aeroplane.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A330-71-3025, making reference to RR SB 
RB.211-71-AG416, to provide inspection instructions, and, depending 
on findings, accomplishment of applicable corrective action(s).
    Consequently, EASA issued AD 2011-0062 [which corresponds to FAA 
AD 2012-22-12] to require repetitive special detailed inspections 
(SDI) [borescope] of the piccolo tube and affected mount links, the 
aft side of forward bulkhead, inner boundary angles (IBA) and OBA of 
the RR Trent 700 air intake cowl assemblies, and, depending on 
findings, accomplishment of applicable corrective action(s).
    Since EASA AD 2011-0062 was issued, some occurrences were 
reported of finding attachment rivets of the IBA and OBA either 
pulled, loose, or missing during inspection. It was determined that 
the affected IBA and OBA rivets may not have been previously 
inspected if operators accomplished the required inspection in 
accordance with the instructions of RR SB RB.211-71-AG416 at 
original issue.
    To address this potentially missed inspection, Airbus published 
SB A330-71-3033, providing instructions for a one-time detailed 
inspection of the IBA and OBA attachment rivets, to be accomplished 
if the previous inspection was accomplished using the instructions 
of RR SB RB.211-71-AG416 at original issue. Airbus also published SB 
A330-71-3025 Revision 2, adding an inspection of the IBA and OBA 
attachment

[[Page 11305]]

rivets, to be used if the previous inspection was accomplished using 
RR SB RB.211-71-AG416 at issue 1 or later. Airbus also published SB 
A330-71-3032 to introduce a modification (mod) that would eliminate 
the need for repetitive inspections.
    For the reasons described above, this [EASA] AD partially 
retains the requirements of EASA AD 2011-0062, which is superseded, 
and requires an additional [special] detailed inspection [borescope] 
of IBA and OBA forward bulkhead attachment rivets. This [EASA] AD 
also introduces an optional terminating action (Airbus mod 204615, 
embodied in production, which can be embodied in service with Airbus 
SB A330-71-3032) for the repetitive inspections required by this 
[EASA] AD.
    This [EASA] AD is revised to improve clarity, including Airbus 
and RR SB references and inserting Notes to identify the Part 
Numbers (P/N) of the affected engine air intake nose cowl 
assemblies.

    Related investigative actions include inspecting for cracked or 
fractured piccolo tubes and for broken piccolo tube links. Corrective 
actions include replacing the engine air intake cowl assembly and 
repair of pulled, loose, or missing rivets.
    The compliance times for the related investigative and corrective 
actions range from before further flight to within 100 flight cycles, 
depending on the findings of the inspections.
    The repetitive inspection interval for the IBAs, OBAs, and forward 
bulkhead varies depending on inspection findings, and ranges between 
200 and 5,000 flight cycles. The repetitive inspection interval for the 
piccolo tubes and links is 2,500 flight cycles.
    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-2016-
9305.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A330-71-3025, Revision 02, dated 
December 9, 2015. This service information describes procedures for 
inspections of the piccolo tube and mount links, the aft side of the 
forward bulkhead, the IBAs, OBAs, and the forward bulkhead on the 
engine air intake cowl assemblies; and related investigative and 
corrective actions.
    Airbus also has issued Service Bulletin A330-71-3032, dated 
December 10, 2014. This service information describes procedures for a 
modification that improves the air intake primary structure and adds a 
new piccolo tube supporting structure on the engine air intake cowl 
assemblies.
    In addition, Airbus has issued Service Bulletin A330-71-3033, dated 
December 14, 2015. This service information describes procedures for an 
inspection for pulled, loose, and missing attachment rivets of the IBAs 
and OBAs of the forward bulkhead, and corrective actions.
    Rolls-Royce has issued Service Bulletin RB.211-71-H205, dated July 
7, 2014. This service information describes procedures for modifying 
the nose cowl assembly acoustic panels.
    Rolls-Royce also has issued Service Bulletin RB.211-71-H847, dated 
December 2, 2014. This service information describes procedures for 
modifying the air intake nose cowl assembly, forward bulkhead assembly, 
TAI spray ring, and the TAI spray ring supporting hardware.
    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.

Costs of Compliance

    We estimate that this AD affects 47 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
             Action                     Labor cost           Parts cost     Cost per product       operators
----------------------------------------------------------------------------------------------------------------
Inspections (new action).......  12 work-hours x $85 per              $0   $1,020 per          $47,940 per
                                  hour = $1,020 per                         inspection cycle.   inspection
                                  inspection cycle.                                             cycle.
----------------------------------------------------------------------------------------------------------------


                                      Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
                Action                            Labor cost              Parts cost        Cost per  product
----------------------------------------------------------------------------------------------------------------
Modification..........................  Up to 142 work-hours x $85 per           \[1]\  Up to $12,070.
                                         hour = $12,070.
----------------------------------------------------------------------------------------------------------------
\[1]\ We have received no definitive data that will enable us to provide material cost estimates for the
  optional actions specified in this AD.

    We estimate the following costs to do any necessary repairs that 
will be required based on the results of the inspection. We have no way 
of determining the number of aircraft that might need these repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repairs....................................  16 work-hours x $85 per hour =               \[2]\          $1,360
                                              $1,360.
----------------------------------------------------------------------------------------------------------------
\[2]\ We have received no definitive data that will enable us to provide material cost estimates for the on-
  condition actions specified in this AD.


[[Page 11306]]

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.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. 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.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2012-22-12, Amendment 39-17248 (77 FR 67263, November 9, 2012), and 
adding the following new AD:

2017-04-09 Airbus: Amendment 39-18804; Docket No. FAA-2016-9305; 
Directorate Identifier 2016-NM-073-AD.

(a) Effective Date

    This AD is effective March 29, 2017.

(b) Affected ADs

    This AD replaces AD 2012-22-12, Amendment 39-17248 (77 FR 67263, 
November 9, 2012) (``AD 2012-22-12'').

(c) Applicability

    This AD applies to Airbus Model A330-243, -243F, -341, -342, and 
-343 airplanes, certificated in any category, all serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracking of air intake cowls 
on Rolls-Royce Trent engines, worn and detached attachment links, 
and fractured thermal anti-ice (TAI) piccolo tubes, and loose, or 
missing attachment rivets of the inner boundary angles (IBAs) and 
the outer boundary angles (OBAs) of the forward bulkhead. We are 
issuing this AD to detect and correct degraded structural integrity 
of the engine nose cowl, which in the case of forward bulkhead 
damage in conjunction with a broken piccolo tube, could lead to 
damage to the engine and operation in icing conditions with reduced 
TAI performance.

(f) Compliance

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

(g) Affected Engine Air Intake Nose Cowl Assemblies

    The engine air intake nose cowl assemblies affected by this AD 
have part numbers (P/N) SJ30020, P/N SJ30361, P/N SJ30687, P/N 
SJ30810, and P/N SJ30811, as specified in Rolls-Royce Service 
Bulletin RB.211-71-H205, dated July 7, 2014.
    (1) The engine air intake nose cowl assemblies having P/N 
SJ30020, P/N SJ30361, and P/N SJ30687 can be modified (reworked and 
re-identified as P/N SJ30810 (for P/N SJ30020 and P/N SJ30361) and 
P/N SJ30811 (for P/N SJ30687)), as specified in Rolls-Royce Service 
Bulletin RB.211-71-H205, dated July 7, 2014.
    (2) The engine air intake nose cowl assemblies having P/N 
SJ30810 and P/N SJ30811 can be modified (reworked and re-identified 
as P/N SJ30820 and P/N SJ30821, respectively), as specified in 
Rolls-Royce Service Bulletin RB.211-71-H847, dated December 2, 2014.

(h) Inspections, Related Investigative Actions, and Corrective Actions

    For airplanes in pre-Airbus Modification 204615 and pre-Airbus 
Service Bulletin A330-71-3032 configuration: At the applicable times 
specified in paragraph (h)(1) or (h)(2) of this AD, do a special 
detailed inspection of the piccolo tube and affected mount links, 
the aft side of the forward bulkhead, and the IBAs and OBAs of the 
affected engine air intake cowl assemblies specified in paragraph 
(g) of this AD; and do all applicable related investigative and 
corrective actions; in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-71-3025, Revision 02, 
dated December 9, 2015, except as required by paragraph (i) of this 
AD. Do all applicable related investigative and corrective actions 
at the applicable time specified in paragraph 1.E., ``Compliance,'' 
of Airbus Service Bulletin A330-71-3025, Revision 02, dated December 
9, 2015. Repeat the inspections of the piccolo tube and affected 
mount links, the aft side of the forward bulkhead, and the IBAs and 
OBAs of the engine air intake cowl assemblies thereafter at the 
applicable intervals specified in paragraph 1.E., ``Compliance,'' of 
Airbus Service Bulletin A330-71-3025, Revision 02, dated December 9, 
2015. Accomplishment of corrective actions does not constitute 
terminating action for the repetitive inspections required by this 
paragraph.
    (1) For any engine air intake cowl assembly that has accumulated 
fewer than 5,000 flight cycles since its first installation on an 
airplane as of the effective date of this AD: Inspect within 24 
months after the engine air intake cowl assembly has accumulated 
5,000 total flight cycles.
    (2) For any engine air intake cowl assembly that has accumulated 
5,000 or more flight cycles since its first installation on an 
airplane as of the effective date of this AD: Inspect within 24 
months after the effective date of this AD.

(i) Service Information Exception

    Where Airbus Service Bulletin A330-71-3025, Revision 02, dated 
December 9, 2015, specifies to contact Bombardier Aerospace--Shorts 
for instructions, before further flight, repair using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA).

(j) Optional Terminating Action

    Modification of an airplane in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-71-3032, 
dated December 10, 2014, constitutes terminating action for the 
repetitive inspections required by paragraph (h) of this AD for the 
modified airplane only.

(k) Parts Installation Limitation

    As of the effective date of this AD, any pre-Airbus Modification 
204615 part may be installed on any airplane provided that, at the 
earlier of the applicable times specified in paragraphs (h)(1) and 
(h)(2) of this AD following installation, the actions required by

[[Page 11307]]

paragraph (h) of this AD have been accomplished on the pre-Airbus 
Modification 204615 part.

(l) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(h) of this AD, if those actions were performed before the effective 
date of this AD using Airbus Service Bulletin A330-71-3025, dated 
January 10, 2011, which was incorporated by reference in AD 2012-22-
12; or Airbus Service Bulletin A330-71-3025, Revision 01, dated 
October 24, 2012, which is not incorporated by reference in this AD; 
provided that, within 1,050 flight cycles after the effective date 
of this AD, a special detailed inspection for pulled, loose, and 
missing attachment rivets of the IBAs and OBAs of the forward 
bulkhead is accomplished; and all applicable corrective actions are 
done; in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A330-71-3033, dated December 14, 2015. Do all 
applicable corrective actions before further flight. Accomplishment 
of corrective actions does not constitute terminating action for the 
repetitive inspections required by paragraph (h) of this AD.

(m) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (i) 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.
    (ii) AMOCs approved previously for AD 2012-22-12 are not 
approved as AMOCs with this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, 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 Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (3) Required for Compliance (RC): 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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0086R1, dated May 13, 2016, 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-2016-9305.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(3) and (o)(5) of this AD.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A330-71-3025, Revision 02, dated 
December 9, 2015.
    (ii) Airbus Service Bulletin A330-71-3032, dated December 10, 
2014.
    (iii) Airbus Service Bulletin A330-71-3033, dated December 14, 
2015.
    (iv) Rolls-Royce Service Bulletin RB.211-71-H205, dated July 7, 
2014.
    (v) Rolls-Royce Service Bulletin RB.211-71-H847, dated December 
2, 2014.
    (3) For Airbus service information identified in this AD, 
contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet https://www.airbus.com.
    (4) For Rolls-Royce service information identified in this AD, 
contact Rolls-Royce Plc, Technical Publications, P.O. Box 31, Derby, 
DE24 8BJ, United Kingdom; telephone 44 (0) 1332 245882; fax 44 (0) 
1332 249936; Internet https://www.Rolls-Royce.com.
    (5) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (6) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 3, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-03260 Filed 2-21-17; 8:45 am]
 BILLING CODE 4910-13-P
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