Airworthiness Directives; Airbus Airplanes, 34251-34257 [2017-14923]

Download as PDF 34251 Rules and Regulations Federal Register Vol. 82, No. 140 Monday, July 24, 2017 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9393; Directorate Identifier 2014–NM–199–AD; Amendment 39–18935; AD 2017–13–05] 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) 2013–13– 16 for all Airbus Model A330–200, A330–200 Freighter, A330–300 series airplanes; and all Airbus Model A340– 200, –300, –500, and –600 series airplanes. AD 2013–13–16 required repetitive inspections for discrepancies of the ball-screw assembly of the trimmable horizontal stabilizer actuator (THSA), repetitive greasing of the THSA ball-nut, and replacement of the THSA if necessary; and modification or replacement (as applicable) of the ballnut assembly, which ends certain repetitive inspections. This new AD requires an inspection, corrective actions if necessary, lubrication of the ball-nut, modification of the THSA, and removal of certain airplanes from the applicability. This AD was prompted by a determination that a modification that automatically detects failure of the ballscrew assembly is necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 28, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 28, 2017. ADDRESSES: For service information identified in this final rule, contact srobinson on DSKBC5CHB2PROD with RULES SUMMARY: VerDate Sep<11>2014 16:26 Jul 21, 2017 Jkt 241001 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 http://www.airbus.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 http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9393. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9393; 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 street 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 2013–13–16, Amendment 39–17504 (78 FR 47537, August 6, 2013) (‘‘AD 2013–13–16’’). AD 2013–13–16 applied to all Airbus Model A330–200, A330–200 Freighter, A330– 300 series airplanes, and all Airbus Model A340–200, –300, –500, and –600 series airplanes. The NPRM published in the Federal Register on December 19, 2016 (81 FR 91882) (‘‘the NPRM’’). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 Directive 2014–0219, dated September 29, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on all Airbus Model A330 and Model A340 series airplanes. The MCAI states: Several cases of transfer tube disconnection from the ball-nut of the trimmable horizontal stabilizer actuator (THSA) part number (P/N) 47172 and 47147– 400 were detected on the ground during greasing and maintenance. Investigation results showed that this was caused by water ingress into the ball-nut, resulting in the jamming of the ball transfer circuit when the water froze. If the three (independent) ball circuits fail, then the THSA operates on a fail-safe nut (which operates without balls), which jams after several movements on the ballscrew of the THSA. This condition, if not detected and corrected, could damage the ball screw and the fail-safe nut, possibly resulting in jamming of the THSA and consequent reduced control of the aeroplane. To detect at an early stage any distortion or initiation of disconnection, [Directorate General for Civil Aviation] DGAC France issued AD 2001–356 and AD 2001–357 to require repetitive inspections of the transfer tubes and their collars and, depending on findings, corrective action(s). Prompted by another case of transfer tube disconnection, DGAC France issued AD 2001–356R2 and AD 2001–357R2 to require additional repetitive greasing and reinforcement of the ball-nut maintenance greasing instructions. Subsequently, DGAC France issued AD 2002–037 and AD 2002–038 to require a modification that was also terminating action for the repetitive inspections and greasing tasks required by DGAC France AD 2001– 356R2 and AD 2001–357R2 for the THSA P/ N 47172 by application of Service Bulletin (SB) A330–27–3085 or SB A340–27–4089 (equivalent to Airbus production modification 49590), as applicable, changing the THSA P/N from 47172 to 47172–300. Later on, DGAC France issued AD 2002– 414 (later revised to R3) and AD 2002–415 (later revised to R2), which superseded the DGAC France AD 2001–356R2, AD 2001– 357R2, AD 2002–037, and AD 2002–038, requiring: —Repetitive inspections of all THSA P/N in service, —repetitive lubrication of some THSA P/N, and —replacement of THSA P/N 47172, 47147– 400 and 47147–2XX/–3XX. In addition, the electrical flight control computers monitor the operation of the THSA and the jamming of this actuator could be detected and indicated by messages on the maintenance system and on the [electronic centralized aircraft monitor] ECAM. For that E:\FR\FM\24JYR1.SGM 24JYR1 34252 Federal Register / Vol. 82, No. 140 / Monday, July 24, 2017 / Rules and Regulations srobinson on DSKBC5CHB2PROD with RULES reason, DGAC France AD 2002–414 and AD 2002–415 also required inspection of the THSA after display of such message(s). After those [DGAC France] ADs were issued, Airbus introduced 4 new THSA, P/N 47172–500, P/N 47172–510, P/N 47172–520 and P/N 47172–530. As these new THSA also needed to be inspected/lubricated, EASA issued AD 2010– 0192 and [EASA] AD 2010–0193 [which correspond to FAA AD 2013–13–16], which retained the requirements of DGAC France AD F–2002–414R3 and AD F–2002–415R2 respectively, which were superseded, to add required repetitive inspections and lubrications of the new THSA P/N. Since those [EASA] ADs were issued, all requirements of EASA AD 2010–0192 and [EASA] AD 2010–0193 were transferred into Airbus Airworthiness Limitations Section (ALS) Part 4, except the requirement of paragraph (2.3) of those [EASA] ADs. At this time, compliance with ALS Part 4 tasks is required by EASA AD 2013–0268 (A330 aeroplanes) and [EASA] AD 2013–0269 (A340 aeroplanes), respectively [which correspond to FAA AD 2015–16–02, Amendment 39–18227 (80 FR 48019, August 11, 2015) (A330 airplanes); and AD 2014–23– 17, Amendment 39–18033 (79 FR 71304, December 2, 2014) (A340 airplanes); respectively.] In addition, Airbus developed a Checkable Shear Pin (CSP) for the THSA and an associated additional electrical harness, which consists of installation of two Electrical Detection Devices (EDD) on the lower attachment secondary load path, which gives an indication to the Flight Control Primary Computers of secondary load path engagement. After embodiment of these modifications on an aeroplane, the repetitive inspections of the ballscrew assembly for integrity of the primary and secondary load paths is no longer required, because the failure is detected automatically by this new device. For the reasons described above, this [EASA] AD retains only the requirement of paragraph (2.3) of EASA AD 2010–0192 and 2010–0193 [actions following ECAM fault messages], which are superseded, and requires the installation of CSP and associated additional electrical harness on the THSA of the aeroplane. This [EASA] AD also requires, for A340–500/–600 aeroplanes that are post-SB A340–92–5008 (at Revision 06 or earlier), accomplishment of A340 ALS Part 3 task 274000–B0002–1–C, providing a grace period of 3 months for aeroplanes that have exceeded the applicable threshold or interval. The unsafe condition is the degraded operation of the THSA, which could result in reduced control of the airplane. Model A330–223F and A330–243F airplanes have been removed from the applicability of this AD to correspond with the MCAI. Required actions include a detailed inspection and corrective actions if an ECAM fault message is displayed, repetitive lubrication of the THSA ballnut, and a modification of the THSA by VerDate Sep<11>2014 16:26 Jul 21, 2017 Jkt 241001 installing a CSP and associated electrical harness. Required actions also include certain ‘‘Additional Work’’ that is described in the following service information. • ‘‘Additional Work’’ in Airbus Service Bulletin A330–27–3143, Revision 01, dated July 10, 2012, is described as removing the closing plug from the electrical harness 4515VB and connecting the electrical harness 4515VB to the THSA. • ‘‘Additional Work’’ in Airbus Service Bulletin A330–92–3046, Revision 07, dated January 13, 2017; and in Airbus Service Bulletin A340– 92–4056, Revision 04, dated December 5, 2013; is described as replacement of a certain harness item, installation of placards and cable support, modification of a certain bracket, and installation of a certain spacer. • ‘‘Additional Work’’ in Airbus Service Bulletin A340–92–5008, Revision 07, dated February 8, 2013, is described as replacing a certain wiring harness, replacing a certain THSA harness, installing additional placards, and modifying a certain wire harness installation order. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9393. 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. New Service Information Since we issued the NPRM, we have reviewed Airbus Service Bulletin A330– 92–3046, Revision 07, dated January 13, 2017 (we referred to Airbus Service Bulletin A330–92–3046, Revision 06, dated November 15, 2013, as one of the appropriate sources of service information for installing an electrical harness). Airbus Service Bulletin A330– 92–3046, Revision 07, dated January 13, 2017, includes minor updates to the procedures and illustrations. We have revised figure 2 to paragraphs (h) and (i) of this AD and figure 3 to paragraph (j) of this AD to refer to Airbus Service Bulletin A330–92–3046, Revision 07, dated January 13, 2017. We have also added paragraph (r)(2) to this AD to give credit for actions done in accordance with Airbus Service Bulletin A330–92– 3046, Revision 06, dated November 15, 2013. PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Costs of Compliance Change The costs of compliance information in the NPRM included a parts cost of $14,198. We have revised the costs of compliance information in this AD based on receiving updated cost information from the manufacturer to include a parts cost of $17,481. Conclusion We reviewed the relevant data, and determined that air safety and the public interest require adopting this AD with the changes described previously and 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. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. The service bulletins having the same document number are distinct because each revision contains unique editorial changes. The following service information describes procedures for doing repetitive inspections for integrity of the primary and secondary load paths of the ball-screw assembly of the THSA. These service bulletins are distinct because they apply to different airplane models. • Airbus Service Bulletin A330–27– 3102, Revision 09, dated March 29, 2016. • Airbus Service Bulletin A340–27– 4107, Revision 09, dated March 29, 2016. The following service information describes procedures for installing two electrical detection devices, also called CSPs, on the lower attachment secondary load path of the THSA, and modifying the THSA. These service bulletins are distinct because they apply to different airplane models equipped with THSAs having different part numbers. • Airbus Service Bulletin A330–27– 3137, including Appendix 01, dated March 20, 2007. • Airbus Service Bulletin A330–27– 3137, Revision 01, including Appendix 1, dated December 6, 2007. • Airbus Service Bulletin A330–27– 3137, Revision 02, dated January 18, 2010. • Airbus Service Bulletin A330–27– 3143, Revision 01, dated July 10, 2012. E:\FR\FM\24JYR1.SGM 24JYR1 srobinson on DSKBC5CHB2PROD with RULES Federal Register / Vol. 82, No. 140 / Monday, July 24, 2017 / Rules and Regulations • Airbus Service Bulletin A340–27– 4136, including Appendix 01, dated March 20, 2007. • Airbus Service Bulletin A340–27– 4136, Revision 01, including Appendix 1, dated December 6, 2007. • Airbus Service Bulletin A340–27– 4136, Revision 02, including Appendix 1, dated February 24, 2010. • Airbus Service Bulletin A340–27– 4143, dated February 21, 2012. • Airbus Service Bulletin A340–27– 5030, Revision 01, including Appendix 1, dated November 20, 2009. The following service information describes procedures for installing electrical wiring harnesses and brackets to connect the secondary nut detection device to the monitoring systems. These service bulletins are distinct because they apply to different airplane models. • Airbus Service Bulletin A330–92– 3046, Revision 04, dated July 16, 2010. • Airbus Service Bulletin A330–92– 3046, Revision 05, dated November 7, 2011. • Airbus Service Bulletin A330–92– 3046, Revision 07, dated January 13, 2017. • Airbus Service Bulletin A340–92– 4056, Revision 03, dated July 16, 2010. • Airbus Service Bulletin A340–92– 4056, Revision 04, dated December 5, 2013. • Airbus Service Bulletin A340–92– 5008, Revision 07, dated February 8, 2013. The following service information describes system equipment maintenance requirements (SEMRs) that refer to preventative maintenance requirements found necessary to comply with safety objectives. These documents are distinct because they apply to different airplane models. • Airbus A330 Airworthiness Limitations Section (ALS) Part 4— System Equipment Maintenance Requirements (SEMR), Revision 05, dated October 19, 2015. • Airbus A340 Airworthiness Limitations Section (ALS) Part 4— System Equipment Maintenance Requirements (SEMR), Revision 04, dated October 19, 2015. Airbus A340 Airworthiness Limitations Section (ALS) Part 3— Certification Maintenance Requirements (CMR), Revision 03, dated October 19, 2015, describes CMRs that are systemrelated periodic tasks established during type certification. 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. VerDate Sep<11>2014 16:26 Jul 21, 2017 Jkt 241001 Costs of Compliance We estimate that this AD affects 33 airplanes of U.S. registry. The actions required by AD 2013–13– 16, and retained in this AD take about 1 work-hour per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2013–13–16 is $85 per product. We also estimate that it takes about 67 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts would cost about $17,481 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $764,808, or $23,176 per product. 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. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 34253 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2013–13–16, Amendment 39–17504 (78 FR 47537, August 6, 2013), and adding the following new AD: ■ 2017–13–05 Airbus: Amendment 39–18935; Docket No. FAA–2016–9393; Directorate Identifier 2014–NM–199–AD. (a) Effective Date This AD is effective August 28, 2017. (b) Affected ADs This AD replaces AD 2013–13–16, Amendment 39–17504 (78 FR 47537, August 6, 2013) (‘‘AD 2013–13–16’’). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Airbus Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes, all manufacturer serial numbers. (2) Airbus Model A340–211, –212, –213, –311, –312, –313, –541, and –642 airplanes, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Reason This AD was prompted by the determination that a modification that automatically detects failure of the ball-screw assembly is necessary. We are issuing this AD to detect and correct wear on the trimmable horizontal stabilizer actuator (THSA), possibly resulting in damage to the ball-screw and fail-safe nut, which could jam the THSA and result in reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Actions for Electronic Centralized Aircraft Monitor (ECAM) Fault Messages For airplanes other than those identified in figure 1 to paragraphs (g), (h), and (q) of this AD: If, during any flight, one of the ‘‘PRIM E:\FR\FM\24JYR1.SGM 24JYR1 34254 Federal Register / Vol. 82, No. 140 / Monday, July 24, 2017 / Rules and Regulations X PITCH FAULT’’ or ‘‘STAB CTL FAULT’’ messages is displayed on the ECAM associated with the ‘‘PITCH TRIM ACTR (1CS)’’ maintenance message, before further flight after each time the message is displayed on the ECAM, do the actions specified in paragraphs (g)(1) and (g)(2) of this AD. (1) Do the applicable detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path; check the checkable shear pins (CSP), if installed; and do all applicable corrective actions; as specified in paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of this AD. Do all applicable corrective actions before further flight. (i) For Model A330 series airplanes: Do the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–27–3102, Revision 09, dated March 29, 2016, except as required by paragraph (n)(1) of this AD. (ii) For Model A340–200 and –300 series airplanes: Do the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340–27–4107, Revision 09, dated March 29, 2016, except as required by paragraph (n)(1) of this AD. (iii) For Model A340–500 and –600 series airplanes: Do the actions 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). Note 1 to paragraph (g)(1)(iii) of this AD: Guidance for the inspection of the ball-screw assembly can be found in Task 274000– B0002–1–C, Inspection of the ball-screw assembly for integrity of the primary and secondary load paths, of the Airbus A340 Airworthiness Limitations Section (ALS) Part 3—Certification Maintenance Requirements (CMR), Revision 03, dated October 19, 2015. (2) Lubricate the THSA ball-nut in accordance with the applicable service information specified in paragraph (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of this AD. (i) Task 274400–00002–1–E, Lubrication of the THSA ball-nut, of Airbus A330 ALS Part 4—System Equipment Maintenance Requirements (SEMR), Revision 05, dated October 19, 2015 (for Model A330 series airplanes). (ii) Task 274400–00002–1–E, Lubrication of the THSA ball-nut, of Airbus A340 ALS Part 4—System Equipment Maintenance Requirements (SEMR), Revision 04, dated October 19, 2015 (for Model A340–200 and –300 series airplanes). (iii) Task 274000–B0003–1–C, Lubrication of THS Actuator ball-screw nut, of Airbus A340 ALS Part 3—Certification Maintenance Requirements (CMR), Revision 03, dated October 19, 2015 (for Model A340–500 and –600 series airplanes). FIGURE 1 TO PARAGRAPHS (g), (h), AND (q) OF THIS AD—DEFINITION OF AIRPLANE GROUPS Group Airplane models On which the following actions or modifications have been done Group 1 airplanes ... Airbus Model A330–200 and –300 series airplanes. On which the actions specified in Airbus Service Bulletin A330–27–3137, dated March 20, 2007; or Revision 01, dated December 6, 2007; and Airbus Service Bulletin A330–92–3046, Revision 04, dated July 16, 2010; or Revision 05, dated November 7, 2011; or Revision 06, dated November 15, 2013; have been embodied in service. On which the actions specified in Airbus Service Bulletin A340–27–4136, including Appendix 1, dated March 20, 2007; or Revision 01, including Appendix 1, dated December 6, 2007; and Airbus Service Bulletin A340–92–4056, Revision 03, dated July 16, 2010; have been embodied in service. On which Airbus Modifications 55780, 52269, and 56056 have been embodied in production. Airbus Model A340–200 and –300 series airplanes. Group 2 airplanes ... Group 3 airplanes ... Airbus Model A330–200 and –300 series airplanes and Model A340–200 and –300 series airplanes. Airbus Model A340–500 and –600 series airplanes. Airbus Model A330–200 and –300 series airplanes. Airbus Model A330–200 and –300 series airplanes. Airbus Model A340–200 and –300 series airplanes. Airbus Model A340–200 and –300 series airplanes. (h) Installation of CSP and Electrical Harness For all airplanes, except Group 2 airplanes specified in figure 1 to paragraphs (g), (h), and (q) of this AD, and except for airplanes On which Airbus Modifications 54882, 52191, and 56058 have been embodied in production. On which Airbus Service Bulletin A330–27–3137, dated March 20, 2007; or Revision 01, dated December 6, 2007; has been embodied in service and Airbus Modifications 52269 and 56056 have been embodied in production. On which Airbus Modification 55780 has been embodied in production and Airbus Service Bulletin A330–92–3046 Revision 04, dated July 16, 2010; or Revision 05, dated November 07, 2011; or Revision 06, dated November 15, 2013; has been embodied in service. On which Airbus Service Bulletin A340–27–4136, including Appendix 1, dated March 20, 2007; or Revision 01, including Appendix 1, dated December 6, 2007; has been embodied in service and Airbus Modifications 52269 and 56056 have been embodied in production. On which Airbus Modification 55780 has been embodied in production and Airbus Service Bulletin A340–92–4056, Revision 03, dated July 16, 2010, has been embodied in service. identified in paragraphs (i), (j), and (n)(2) of this AD: Within 12 months after the effective date of this AD, modify the airplane by installing a CSP on the THSA and an additional electrical harness, in accordance with the Accomplishment Instructions of the Airbus service information specified in figure 2 to paragraphs (h) and (i) of this AD, as applicable to the part number of the THSA installed on the airplane, except as provided by paragraph (n)(2) of this AD. srobinson on DSKBC5CHB2PROD with RULES FIGURE 2 TO PARAGRAPHS (h) AND (i) OF THIS AD—APPLICABLE SERVICE INFORMATION FOR MODIFICATION THSA Part No. (P/N) Service bulletin for CSP installation Service bulletin for electrical harness installation 47172–300 ....... Airbus Service Bulletin A330–27–3137, Revision 02, dated January 18, 2010, for Airbus Model A330–200 and –300 series airplanes; and Airbus Service Bulletin A340–27–4136, Revision 02, including Appendix 1, dated February 24, 2010, for Airbus Model A340–200 and –300 series airplanes. Airbus Service Bulletin A330–92–3046, Revision 07, dated January 13, 2017, for Airbus Model A330–200 and –300 series airplanes; and VerDate Sep<11>2014 16:26 Jul 21, 2017 Jkt 241001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\24JYR1.SGM 24JYR1 Federal Register / Vol. 82, No. 140 / Monday, July 24, 2017 / Rules and Regulations 34255 FIGURE 2 TO PARAGRAPHS (h) AND (i) OF THIS AD—APPLICABLE SERVICE INFORMATION FOR MODIFICATION—Continued THSA Part No. (P/N) Service bulletin for CSP installation Service bulletin for electrical harness installation 47147–500 ....... Airbus Service Bulletin A330–27–3143, Revision 01, dated July 10, 2012, for Airbus Model A330–200 and –300 series airplanes; and Airbus Service Bulletin A340–27–4143, dated February 21, 2012, for Airbus Model A340–200 and –300 series airplanes. Airbus Service Bulletin A340–27–5030, Revision 01, including Appendix 1, dated November 20, 2009, for Airbus Model A340–541 and –642 airplanes. Airbus Service Bulletin A340–92–4056, Revision 04, dated December 5, 2013, for Airbus Model A340–200 and –300 series airplanes. 47175–200, 47175–300. (i) ‘‘Additional Work’’ on Previously Modified Airplanes For airplanes that have already been modified (installation of CSP on the THSA and electrical harness) before the effective date of this AD in accordance with the Accomplishment Instructions of any previous revision of an Airbus service bulletin specified in figure 2 to paragraphs (h) and (i) of this AD, as applicable: Within 12 months after the effective date of this AD, do the ‘‘Additional Work’’ specified in, and in accordance with, the Accomplishment Instructions of the applicable Airbus service Airbus Service Bulletin A340–92–5008, Revision 07, dated February 8, 2013, for Airbus Model A340–541 and –642 airplanes. information specified in figure 2 to paragraphs (h) and (i) of this AD. (j) Installation of Electrical Harness on Airplanes Equipped With a CSP For airplanes having one of the THSAs installed with a part number listed in figure 3 to paragraph (j) of this AD, and which have been modified by installing a CSP on the THSA as required by paragraph (h) of this AD: Within 12 months after the effective date of this AD, inspect to determine if the electrical harness identified in the applicable Airbus service information specified in figure 3 to paragraph (j) of this AD is installed on the airplane, and if found not to be installed, modify the airplane by installing an electrical harness, in accordance with the Accomplishment Instructions of the Airbus service information specified in figure 3 to paragraph (j) of this AD, as applicable to the part number of the THSA installed on the airplane. Airplanes having one of the THSAs installed with a part number listed in figure 3 to paragraph (j) of this AD already have the CSP installed on the THSA, and only the electrical harness must be installed on the airplane. FIGURE 3 TO PARAGRAPH (j) OF THIS AD—ELECTRICAL HARNESS INSTALLATION THSA P/N Service information for electrical harness installation 47172–500, 47172–510, 47172–520, 47172–530, 47147–700, 47147– 710. Airbus Service Bulletin A330–92–3046, Revision 07, dated January 13, 2017, for Airbus Model A330–200 and –300 series airplanes. Airbus Service Bulletin A340–92–4056, Revision 04, dated December 5, 2013, for Airbus Model A340–200 and –300 series airplanes. Airbus Service Bulletin A340–92–5008, Revision 07, dated February 8, 2013, for Airbus Model A340–541 and –642 airplanes. 47175–500, 47175–520, 47175–530 ....................................................... srobinson on DSKBC5CHB2PROD with RULES (k) Terminating Action for Repetitive Inspections of Airbus Model A330–200 and –300 Series Airplanes Accomplishment of a modification before the effective date of this AD, using the Accomplishment Instructions of Airbus Service Bulletin A330–27–3137, dated March 20, 2007; or Revision 01, dated December 6, 2007; and Airbus Service Bulletin A330–92– 3046, Revision 04, dated July 15, 2010; or Revision 05, dated November 7, 2011; or Revision 06, dated November 15, 2013; terminates the repetitive inspections specified in paragraphs (k)(1) through (k)(4) of this AD. Modification of an airplane as required by this paragraph does not constitute terminating action for the actions specified in paragraph (g)(2) of this AD or the additional work specified in paragraph (i) of this AD. (1) Task 274400–00001–1–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and check the gap at the secondary nut trunnion, of Airbus A330 ALS Part 4— System Equipment Maintenance Requirements (SEMR), Revision 05, dated October 19, 2015. (2) Task 274400–00001–2–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load VerDate Sep<11>2014 16:26 Jul 21, 2017 Jkt 241001 path and check the CSPs, of Airbus A330 ALS Part 4—System Equipment Maintenance Requirements (SEMR), Revision 05, dated October 19, 2015. (3) Task 274400–00001–3–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and check the CSPs, of Airbus A330 ALS Part 4—System Equipment Maintenance Requirements (SEMR), Revision 05, dated October 19, 2015. (4) Task 274400–00001–4–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and check the CSPs, of Airbus A330 ALS Part 4—System Equipment Maintenance Requirements (SEMR), Revision 05, dated October 19, 2015. (l) Terminating Action for Repetitive Inspections of Airbus Model A340–200 and –300 Series Airplanes Accomplishment of a modification in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340– 27–4143, dated February 21, 2012; and Airbus Service Bulletin A340–92–4056, Revision 03, dated July 16, 2010; terminates the actions required by paragraph (g)(1) of this AD for modified Airbus Model A340– 200 and –300 series airplanes only. Modification of an airplane as specified in PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 this paragraph does not constitute terminating action for the actions specified in paragraph (g)(2) of this AD, or the additional work specified in paragraph (i) of this AD. (m) Terminating Action for Repetitive Inspections of Airbus Model A340–200 and –300 Series Airplanes Accomplishment of a modification before the effective date of this AD using the Accomplishment Instructions of Airbus Service Bulletin A340–27–4136, including Appendix 1, dated March 20, 2007; or Revision 01, including Appendix 1, dated December 6, 2007; and Airbus Service Bulletin A340–92–4056, Revision 03, dated July 16, 2010; terminates the repetitive inspections specified in paragraphs (m)(1) through (m)(4) of this AD. Modification of an airplane as specified in this paragraph does not constitute terminating action for the actions specified in paragraph (g)(2) of this AD, or the additional work specified in paragraph (i) of this AD. (1) Task 274400–00001–1–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and gap check at the secondary nut trunnion, of Airbus A340 ALS Part 4— System Equipment Maintenance Requirements (SEMR), Revision 04, dated October 19, 2015. E:\FR\FM\24JYR1.SGM 24JYR1 34256 Federal Register / Vol. 82, No. 140 / Monday, July 24, 2017 / Rules and Regulations (2) Task 274400–00001–2–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and CSP check, of Airbus A340 ALS Part 4—System Equipment Maintenance Requirements (SEMR), Revision 04, dated October 19, 2015. (3) Task 274400–00001–3–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and CSP check, of Airbus A340 ALS Part 4—System Equipment Maintenance Requirements (SEMR), Revision 04, dated October 19, 2015. (4) Task 274400–00001–4–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and CSP check, of A340 ALS Part 4— System Equipment Maintenance Requirements (SEMR), Revision 04, dated October 19, 2015. (n) Exceptions to the Actions in Certain Service Information and Paragraph (h) of This AD (1) Where Airbus Service Bulletin A330– 27–3102, Revision 09, dated March 29, 2016 (for Model A330 series airplanes); or Airbus Service Bulletin A340–27–4107, Revision 09, dated March 29, 2016 (for Model A340 series airplanes); specifies to contact Airbus for a damage assessment: Before further flight, accomplish the required actions in accordance with the procedures specified in paragraph (s)(2) of this AD. (2) For airplanes that already had the electrical harness installed during production using Airbus Modifications 52269 and 56056 for Airbus Model A330–200 and –300 series airplanes and Airbus Model A340–200 and –300 series airplanes, and using Airbus Modifications 52191 and 56058 for Model A340–500 and –600 series airplanes: Only the CSP must be installed on the THSA in accordance with applicable Airbus service bulletins and within the compliance time specified in paragraph (h) of this AD. srobinson on DSKBC5CHB2PROD with RULES (o) Terminating Action for Repetitive Inspections for Airplanes on Which Actions Required by Paragraph (h), (i), or (j) of This AD Are Done Modification of an airplane as required by paragraph (h), (i), or (j) of this AD, as applicable, constitutes terminating action for that airplane for the applicable actions identified in paragraphs (o)(1) through (o)(4) of this AD. (1) For all airplanes: The actions required by paragraph (g) of this AD. (2) For Model A340–500 and –600 series airplanes: Task 274000–B0002–1–C, Inspection of the ball-screw assembly for integrity of the primary and secondary load paths, of Airbus A340 ALS Part 3— Certification Maintenance Requirements (CMR), Revision 03, dated October 19, 2015. (3) For Model A330–200 and –300 series airplanes: The ALS tasks identified in paragraphs (k)(1) through (k)(4) of this AD. (4) For Model A340–200 and –300 series airplanes: The ALS tasks identified in paragraphs (m)(1) through (m)(4) of this AD. VerDate Sep<11>2014 16:26 Jul 21, 2017 Jkt 241001 (p) Ball-Screw Assembly Inspection for Certain Airplanes For Model A340–500 and –600 airplanes that are in post-Airbus Service Bulletin A340–92–5008, at Revision 06 or earlier, configuration: Before exceeding the threshold or interval, as applicable, of Task 274000– B0002–1–C, Inspection of the ball-screw assembly for integrity of the primary and secondary load paths, of Airbus A340 ALS Part 3—Certification Maintenance Requirements (CMR), Revision 03, dated October 19, 2015, or within 3 months after the effective date of this AD, whichever occurs later, accomplish Task 274000– B0002–1–C, Inspection of the ball-screw assembly for integrity of the primary and secondary load paths, of Airbus A340 ALS Part 3—Certification Maintenance Requirements (CMR), Revision 03, dated October 19, 2015; and do all applicable corrective actions. Do all applicable corrective actions before further flight using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. Repeat Task 274000– B0002–1–C, Inspection of the ball-screw assembly for integrity of the primary and secondary load paths, thereafter at the applicable intervals specified in Airbus A340 ALS Part 3—CMRs, Revision 03, dated October 19, 2015. (q) Parts Installation Prohibitions (1) For all airplanes except Group 2 airplanes as identified in figure 1 to paragraphs (g), (h), and (q) of this AD: After modification of the airplane as required by paragraph (h), (i), or (j) of this AD, as applicable, no person may install any THSA having part number (P/N) 47172–300, P/N 47147–500, P/N 47175–200, or P/N 47175– 300. (2) For Group 2 airplanes, as identified in figure 1 to paragraphs (g), (h), and (q) of this AD: As of the effective date of this AD, no person may install on any Group 2 airplane any THSA having P/N 47172–300, P/N 47147–500, P/N 47175–200, or P/N 47175– 300. (r) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (g)(2) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraphs (r)(1)(i) through (r)(1)(iv) of this AD. (i) Task 274400–00002–1–E, Lubrication of the THSA ball-nut, of Airbus A330 ALS Part 4—Ageing Systems Maintenance, Revision 03, dated September 9, 2011 (for Model A330 series airplanes). (ii) Task 274400–00002–1–E, Lubrication of the THSA ball-nut, of Airbus A330 ALS Part 4—Ageing Systems Maintenance, Revision 04, dated August 27, 2013 (for Model A330 series airplanes). (iii) Task 274400–00002–1–E, Lubrication of the THSA ball-nut, of Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated October 12, 2011 (for Model A340–200 and –300 series airplanes). (iv) Task 274400–00002–1–E, Lubrication of the THSA ball-nut, of Airbus A340 ALS PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Part 4—Ageing Systems Maintenance, Revision 03, dated November 15, 2012 (for Model A340–200 and –300 series airplanes). (2) This paragraph provides credit for the electrical harness installation required by paragraph (h) of this AD and the inspection and electrical harness installation required by paragraph (j) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A330– 92–3046, Revision 06, dated November 15, 2013. (s) 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 it to the attention of the person identified in paragraph (t)(2) of this AD. Information may be emailed to: 9-ANM-116-ACO-AMOCREQUESTS@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: 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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (t) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0219, dated September 29, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2016–9393. (2) For more information about this AD, 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. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (u)(3) and (u)(4) of this AD. (u) 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. E:\FR\FM\24JYR1.SGM 24JYR1 srobinson on DSKBC5CHB2PROD with RULES Federal Register / Vol. 82, No. 140 / Monday, July 24, 2017 / Rules and Regulations (i) Airbus A330 Airworthiness Limitations Section (ALS) Part 4—System Equipment Maintenance Requirements (SEMR), Revision 05, dated October 19, 2015. (ii) Airbus A340 Airworthiness Limitations Section (ALS) Part 3—Certification Maintenance Requirements (CMR), Revision 03, dated October 19, 2015. (iii) Airbus A340 Airworthiness Limitations Section (ALS) Part 4—System Equipment Maintenance Requirements (SEMR), Revision 04, dated October 19, 2015. (iv) Airbus Service Bulletin A330–27– 3102, Revision 09, dated March 29, 2016. (v) Airbus Service Bulletin A330–27–3137, including Appendix 01, dated March 20, 2007. (vi) Airbus Service Bulletin A330–27– 3137, Revision 01, including Appendix 1, dated December 6, 2007. (vii) Airbus Service Bulletin A330–27– 3137, Revision 02, dated January 18, 2010. (viii) Airbus Service Bulletin A330–27– 3143, Revision 01, dated July 10, 2012. (ix) Airbus Service Bulletin A330–92– 3046, Revision 04, dated July 16, 2010. (x) Airbus Service Bulletin A330–92–3046, Revision 05, dated November 7, 2011. (xi) Airbus Service Bulletin A330–92– 3046, Revision 07, dated January 13, 2017. (xii) Airbus Service Bulletin A340–27– 4107, Revision 09, dated March 29, 2016. (xiii) Airbus Service Bulletin A340–27– 4136, including Appendix 01, dated March 20, 2007. (xiv) Airbus Service Bulletin A340–27– 4136, Revision 01, including Appendix 1, dated December 6, 2007. (xv) Airbus Service Bulletin A340–27– 4136, Revision 02, including Appendix 1, dated February 24, 2010. (xvi) Airbus Service Bulletin A340–27– 4143, dated February 21, 2012. (xvii) Airbus Service Bulletin A340–27– 5030, Revision 01, including Appendix 1, dated November 20, 2009. (xviii) Airbus Service Bulletin A340–92– 4056, Revision 03, dated July 16, 2010. (xix) Airbus Service Bulletin A340–92– 4056, Revision 04, dated December 5, 2013. (xx) Airbus Service Bulletin A340–92– 5008, Revision 07, dated February 8, 2013. (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 http://www.airbus.com. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. VerDate Sep<11>2014 16:26 Jul 21, 2017 Jkt 241001 Issued in Renton, Washington, on June 15, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–14923 Filed 7–21–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0157; Directorate Identifier 2016–CE–039–AD; Amendment 39–18965; AD 2017–15–05] RIN 2120–AA64 Airworthiness Directives; Piper Aircraft, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 69–13–03 for all Piper Aircraft, Inc. Models PA– 23, PA–23–160, PA–23–235, PA–23– 250, PA–E23–250, and PA–30 airplanes. AD 69–13–03 required inspection of the heater exhaust extension, replacement of the extension as necessary, and overhaul of the combustion heater assembly. This AD retains the inspection of the heater exhaust extension with replacement of the extension as necessary and removes the overhaul requirement of the combustion heater assembly. This AD was prompted by a recently issued AD that applies to the Meggitt (Troy), Inc. combustion heaters, and the combustion heater AD incorporates corrective actions for the heater that contradict the overhaul requirement of AD 69–13–03. We are issuing this AD to continue to address the unsafe condition on these products and avoid potential contradiction of actions. SUMMARY: DATES: This AD is effective August 28, 2017. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0157; 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 final rule, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 34257 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: Scott Hopper, Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474– 5535; fax: (404) 474–5606; email: scott.hopper@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 69–13–03, Amendment 39–785 (34 FR 9748, June 24, 1969) as amended by AD 69–13–03, Amendment 39–1749 (38 FR 33765, December 7, 1973), (‘‘AD 69–13–03’’). AD 69–13–03 applied to certain Piper Aircraft, Inc. Models PA–23, PA–23– 160, PA–23–235, PA–23–250, PA–E23– 250, and PA–30 airplanes. AD 69–13–03 required inspection of the heater exhaust extension to determine if it is mild steel or stainless steel, repetitive inspections of the mild steel extensions for deterioration, replacement of the extension as necessary, and overhaul of the combustion heater assembly. AD 69–13–03 resulted from the potential of carbon monoxide entering the airplane cabin. The NPRM was prompted by another AD action that applies to the Meggitt (Troy), Inc. combustion heaters installed on the airplanes AD 69–13–03 applied to. AD 2017–06–03; Amendment 39– 18827 (82 FR 15988, March 31, 2017), which applies to the Meggitt combustion heaters incorporates corrective actions for the heater that contradict the overhaul requirement of AD 69–13–03. The NPRM proposed to retain certain requirements of AD 69– 13–03 and remove the requirement for overhaul of the heater assembly. We are issuing this AD continue to address the unsafe condition on these products and avoid potential contradiction of actions. Comments We gave the public the opportunity to participate in developing this AD. One comment was received from Ahmed Ali who agrees with the AD action. The following presents the other comment received on the NPRM and the FAA’s response to the comment. Request To Withdraw NPRM Jeff Aryan stated the AD is not necessary. The commenter has owned a Model PA–30 airplane for 25 years and does not believe heater fumes can enter the cabin. He has used the heater for E:\FR\FM\24JYR1.SGM 24JYR1

Agencies

[Federal Register Volume 82, Number 140 (Monday, July 24, 2017)]
[Rules and Regulations]
[Pages 34251-34257]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-14923]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

========================================================================


Federal Register / Vol. 82, No. 140 / Monday, July 24, 2017 / Rules 
and Regulations

[[Page 34251]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9393; Directorate Identifier 2014-NM-199-AD; 
Amendment 39-18935; AD 2017-13-05]
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) 2013-13-16 for 
all Airbus Model A330-200, A330-200 Freighter, A330-300 series 
airplanes; and all Airbus Model A340-200, -300, -500, and -600 series 
airplanes. AD 2013-13-16 required repetitive inspections for 
discrepancies of the ball-screw assembly of the trimmable horizontal 
stabilizer actuator (THSA), repetitive greasing of the THSA ball-nut, 
and replacement of the THSA if necessary; and modification or 
replacement (as applicable) of the ball-nut assembly, which ends 
certain repetitive inspections. This new AD requires an inspection, 
corrective actions if necessary, lubrication of the ball-nut, 
modification of the THSA, and removal of certain airplanes from the 
applicability. This AD was prompted by a determination that a 
modification that automatically detects failure of the ball-screw 
assembly is necessary. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective August 28, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 28, 
2017.

ADDRESSES: For service information identified in this final rule, 
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 
http://www.airbus.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 http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9393.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9393; 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 street 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 2013-13-16, Amendment 39-17504 (78 FR 47537, 
August 6, 2013) (``AD 2013-13-16''). AD 2013-13-16 applied to all 
Airbus Model A330-200, A330-200 Freighter, A330-300 series airplanes, 
and all Airbus Model A340-200, -300, -500, and -600 series airplanes. 
The NPRM published in the Federal Register on December 19, 2016 (81 FR 
91882) (``the NPRM'').
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0219, dated September 29, 2014 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on all Airbus Model A330 
and Model A340 series airplanes. The MCAI states:

    Several cases of transfer tube disconnection from the ball-nut 
of the trimmable horizontal stabilizer actuator (THSA) part number 
(P/N) 47172 and 47147-400 were detected on the ground during 
greasing and maintenance. Investigation results showed that this was 
caused by water ingress into the ball-nut, resulting in the jamming 
of the ball transfer circuit when the water froze. If the three 
(independent) ball circuits fail, then the THSA operates on a fail-
safe nut (which operates without balls), which jams after several 
movements on the ballscrew of the THSA.
    This condition, if not detected and corrected, could damage the 
ball screw and the fail-safe nut, possibly resulting in jamming of 
the THSA and consequent reduced control of the aeroplane.
    To detect at an early stage any distortion or initiation of 
disconnection, [Directorate General for Civil Aviation] DGAC France 
issued AD 2001-356 and AD 2001-357 to require repetitive inspections 
of the transfer tubes and their collars and, depending on findings, 
corrective action(s).
    Prompted by another case of transfer tube disconnection, DGAC 
France issued AD 2001-356R2 and AD 2001-357R2 to require additional 
repetitive greasing and reinforcement of the ball-nut maintenance 
greasing instructions.
    Subsequently, DGAC France issued AD 2002-037 and AD 2002-038 to 
require a modification that was also terminating action for the 
repetitive inspections and greasing tasks required by DGAC France AD 
2001-356R2 and AD 2001-357R2 for the THSA P/N 47172 by application 
of Service Bulletin (SB) A330-27-3085 or SB A340-27-4089 (equivalent 
to Airbus production modification 49590), as applicable, changing 
the THSA P/N from 47172 to 47172-300.
    Later on, DGAC France issued AD 2002-414 (later revised to R3) 
and AD 2002-415 (later revised to R2), which superseded the DGAC 
France AD 2001-356R2, AD 2001-357R2, AD 2002-037, and AD 2002-038, 
requiring:

--Repetitive inspections of all THSA P/N in service,
--repetitive lubrication of some THSA P/N, and
--replacement of THSA P/N 47172, 47147-400 and 47147-2XX/-3XX.

    In addition, the electrical flight control computers monitor the 
operation of the THSA and the jamming of this actuator could be 
detected and indicated by messages on the maintenance system and on 
the [electronic centralized aircraft monitor] ECAM. For that

[[Page 34252]]

reason, DGAC France AD 2002-414 and AD 2002-415 also required 
inspection of the THSA after display of such message(s).
    After those [DGAC France] ADs were issued, Airbus introduced 4 
new THSA, P/N 47172-500, P/N 47172-510, P/N 47172-520 and P/N 47172-
530.
    As these new THSA also needed to be inspected/lubricated, EASA 
issued AD 2010-0192 and [EASA] AD 2010-0193 [which correspond to FAA 
AD 2013-13-16], which retained the requirements of DGAC France AD F-
2002-414R3 and AD F-2002-415R2 respectively, which were superseded, 
to add required repetitive inspections and lubrications of the new 
THSA P/N.
    Since those [EASA] ADs were issued, all requirements of EASA AD 
2010-0192 and [EASA] AD 2010-0193 were transferred into Airbus 
Airworthiness Limitations Section (ALS) Part 4, except the 
requirement of paragraph (2.3) of those [EASA] ADs. At this time, 
compliance with ALS Part 4 tasks is required by EASA AD 2013-0268 
(A330 aeroplanes) and [EASA] AD 2013-0269 (A340 aeroplanes), 
respectively [which correspond to FAA AD 2015-16-02, Amendment 39-
18227 (80 FR 48019, August 11, 2015) (A330 airplanes); and AD 2014-
23-17, Amendment 39-18033 (79 FR 71304, December 2, 2014) (A340 
airplanes); respectively.]
    In addition, Airbus developed a Checkable Shear Pin (CSP) for 
the THSA and an associated additional electrical harness, which 
consists of installation of two Electrical Detection Devices (EDD) 
on the lower attachment secondary load path, which gives an 
indication to the Flight Control Primary Computers of secondary load 
path engagement.
    After embodiment of these modifications on an aeroplane, the 
repetitive inspections of the ballscrew assembly for integrity of 
the primary and secondary load paths is no longer required, because 
the failure is detected automatically by this new device.
    For the reasons described above, this [EASA] AD retains only the 
requirement of paragraph (2.3) of EASA AD 2010-0192 and 2010-0193 
[actions following ECAM fault messages], which are superseded, and 
requires the installation of CSP and associated additional 
electrical harness on the THSA of the aeroplane. This [EASA] AD also 
requires, for A340-500/-600 aeroplanes that are post-SB A340-92-5008 
(at Revision 06 or earlier), accomplishment of A340 ALS Part 3 task 
274000-B0002-1-C, providing a grace period of 3 months for 
aeroplanes that have exceeded the applicable threshold or interval.

    The unsafe condition is the degraded operation of the THSA, which 
could result in reduced control of the airplane.
    Model A330-223F and A330-243F airplanes have been removed from the 
applicability of this AD to correspond with the MCAI.
    Required actions include a detailed inspection and corrective 
actions if an ECAM fault message is displayed, repetitive lubrication 
of the THSA ball-nut, and a modification of the THSA by installing a 
CSP and associated electrical harness.
    Required actions also include certain ``Additional Work'' that is 
described in the following service information.
     ``Additional Work'' in Airbus Service Bulletin A330-27-
3143, Revision 01, dated July 10, 2012, is described as removing the 
closing plug from the electrical harness 4515VB and connecting the 
electrical harness 4515VB to the THSA.
     ``Additional Work'' in Airbus Service Bulletin A330-92-
3046, Revision 07, dated January 13, 2017; and in Airbus Service 
Bulletin A340-92-4056, Revision 04, dated December 5, 2013; is 
described as replacement of a certain harness item, installation of 
placards and cable support, modification of a certain bracket, and 
installation of a certain spacer.
     ``Additional Work'' in Airbus Service Bulletin A340-92-
5008, Revision 07, dated February 8, 2013, is described as replacing a 
certain wiring harness, replacing a certain THSA harness, installing 
additional placards, and modifying a certain wire harness installation 
order.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9393.

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.

New Service Information

    Since we issued the NPRM, we have reviewed Airbus Service Bulletin 
A330-92-3046, Revision 07, dated January 13, 2017 (we referred to 
Airbus Service Bulletin A330-92-3046, Revision 06, dated November 15, 
2013, as one of the appropriate sources of service information for 
installing an electrical harness). Airbus Service Bulletin A330-92-
3046, Revision 07, dated January 13, 2017, includes minor updates to 
the procedures and illustrations. We have revised figure 2 to 
paragraphs (h) and (i) of this AD and figure 3 to paragraph (j) of this 
AD to refer to Airbus Service Bulletin A330-92-3046, Revision 07, dated 
January 13, 2017. We have also added paragraph (r)(2) to this AD to 
give credit for actions done in accordance with Airbus Service Bulletin 
A330-92-3046, Revision 06, dated November 15, 2013.

Costs of Compliance Change

    The costs of compliance information in the NPRM included a parts 
cost of $14,198. We have revised the costs of compliance information in 
this AD based on receiving updated cost information from the 
manufacturer to include a parts cost of $17,481.

Conclusion

    We reviewed the relevant data, and determined that air safety and 
the public interest require adopting this AD with the changes described 
previously and 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.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information. The service 
bulletins having the same document number are distinct because each 
revision contains unique editorial changes.
    The following service information describes procedures for doing 
repetitive inspections for integrity of the primary and secondary load 
paths of the ball-screw assembly of the THSA. These service bulletins 
are distinct because they apply to different airplane models.
     Airbus Service Bulletin A330-27-3102, Revision 09, dated 
March 29, 2016.
     Airbus Service Bulletin A340-27-4107, Revision 09, dated 
March 29, 2016.
    The following service information describes procedures for 
installing two electrical detection devices, also called CSPs, on the 
lower attachment secondary load path of the THSA, and modifying the 
THSA. These service bulletins are distinct because they apply to 
different airplane models equipped with THSAs having different part 
numbers.
     Airbus Service Bulletin A330-27-3137, including Appendix 
01, dated March 20, 2007.
     Airbus Service Bulletin A330-27-3137, Revision 01, 
including Appendix 1, dated December 6, 2007.
     Airbus Service Bulletin A330-27-3137, Revision 02, dated 
January 18, 2010.
     Airbus Service Bulletin A330-27-3143, Revision 01, dated 
July 10, 2012.

[[Page 34253]]

     Airbus Service Bulletin A340-27-4136, including Appendix 
01, dated March 20, 2007.
     Airbus Service Bulletin A340-27-4136, Revision 01, 
including Appendix 1, dated December 6, 2007.
     Airbus Service Bulletin A340-27-4136, Revision 02, 
including Appendix 1, dated February 24, 2010.
     Airbus Service Bulletin A340-27-4143, dated February 21, 
2012.
     Airbus Service Bulletin A340-27-5030, Revision 01, 
including Appendix 1, dated November 20, 2009.
    The following service information describes procedures for 
installing electrical wiring harnesses and brackets to connect the 
secondary nut detection device to the monitoring systems. These service 
bulletins are distinct because they apply to different airplane models.
     Airbus Service Bulletin A330-92-3046, Revision 04, dated 
July 16, 2010.
     Airbus Service Bulletin A330-92-3046, Revision 05, dated 
November 7, 2011.
     Airbus Service Bulletin A330-92-3046, Revision 07, dated 
January 13, 2017.
     Airbus Service Bulletin A340-92-4056, Revision 03, dated 
July 16, 2010.
     Airbus Service Bulletin A340-92-4056, Revision 04, dated 
December 5, 2013.
     Airbus Service Bulletin A340-92-5008, Revision 07, dated 
February 8, 2013.
    The following service information describes system equipment 
maintenance requirements (SEMRs) that refer to preventative maintenance 
requirements found necessary to comply with safety objectives. These 
documents are distinct because they apply to different airplane models.
     Airbus A330 Airworthiness Limitations Section (ALS) Part 
4--System Equipment Maintenance Requirements (SEMR), Revision 05, dated 
October 19, 2015.
     Airbus A340 Airworthiness Limitations Section (ALS) Part 
4--System Equipment Maintenance Requirements (SEMR), Revision 04, dated 
October 19, 2015.
    Airbus A340 Airworthiness Limitations Section (ALS) Part 3--
Certification Maintenance Requirements (CMR), Revision 03, dated 
October 19, 2015, describes CMRs that are system-related periodic tasks 
established during type certification.
    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 33 airplanes of U.S. registry.
    The actions required by AD 2013-13-16, and retained in this AD take 
about 1 work-hour per product, at an average labor rate of $85 per 
work-hour. Based on these figures, the estimated cost of the actions 
that are required by AD 2013-13-16 is $85 per product.
    We also estimate that it takes about 67 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts would cost about $17,481 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $764,808, or $23,176 per product.

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) 
2013-13-16, Amendment 39-17504 (78 FR 47537, August 6, 2013), and 
adding the following new AD:

2017-13-05 Airbus: Amendment 39-18935; Docket No. FAA-2016-9393; 
Directorate Identifier 2014-NM-199-AD.

(a) Effective Date

    This AD is effective August 28, 2017.

(b) Affected ADs

    This AD replaces AD 2013-13-16, Amendment 39-17504 (78 FR 47537, 
August 6, 2013) (``AD 2013-13-16'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes, all 
manufacturer serial numbers.
    (2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541, 
and -642 airplanes, all manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
Controls.

(e) Reason

    This AD was prompted by the determination that a modification 
that automatically detects failure of the ball-screw assembly is 
necessary. We are issuing this AD to detect and correct wear on the 
trimmable horizontal stabilizer actuator (THSA), possibly resulting 
in damage to the ball-screw and fail-safe nut, which could jam the 
THSA and result in reduced control of the airplane.

(f) Compliance

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

(g) Actions for Electronic Centralized Aircraft Monitor (ECAM) Fault 
Messages

    For airplanes other than those identified in figure 1 to 
paragraphs (g), (h), and (q) of this AD: If, during any flight, one 
of the ``PRIM

[[Page 34254]]

X PITCH FAULT'' or ``STAB CTL FAULT'' messages is displayed on the 
ECAM associated with the ``PITCH TRIM ACTR (1CS)'' maintenance 
message, before further flight after each time the message is 
displayed on the ECAM, do the actions specified in paragraphs (g)(1) 
and (g)(2) of this AD.
    (1) Do the applicable detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path; check 
the checkable shear pins (CSP), if installed; and do all applicable 
corrective actions; as specified in paragraph (g)(1)(i), (g)(1)(ii), 
or (g)(1)(iii) of this AD. Do all applicable corrective actions 
before further flight.
    (i) For Model A330 series airplanes: Do the actions in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-27-3102, Revision 09, dated March 29, 2016, except as 
required by paragraph (n)(1) of this AD.
    (ii) For Model A340-200 and -300 series airplanes: Do the 
actions in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A340-27-4107, Revision 09, dated March 29, 2016, 
except as required by paragraph (n)(1) of this AD.
    (iii) For Model A340-500 and -600 series airplanes: Do the 
actions 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).
    Note 1 to paragraph (g)(1)(iii) of this AD: Guidance for the 
inspection of the ball-screw assembly can be found in Task 274000-
B0002-1-C, Inspection of the ball-screw assembly for integrity of 
the primary and secondary load paths, of the Airbus A340 
Airworthiness Limitations Section (ALS) Part 3--Certification 
Maintenance Requirements (CMR), Revision 03, dated October 19, 2015.
    (2) Lubricate the THSA ball-nut in accordance with the 
applicable service information specified in paragraph (g)(2)(i), 
(g)(2)(ii), or (g)(2)(iii) of this AD.
    (i) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A330 ALS Part 4--System Equipment Maintenance Requirements 
(SEMR), Revision 05, dated October 19, 2015 (for Model A330 series 
airplanes).
    (ii) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A340 ALS Part 4--System Equipment Maintenance Requirements 
(SEMR), Revision 04, dated October 19, 2015 (for Model A340-200 and 
-300 series airplanes).
    (iii) Task 274000-B0003-1-C, Lubrication of THS Actuator ball-
screw nut, of Airbus A340 ALS Part 3--Certification Maintenance 
Requirements (CMR), Revision 03, dated October 19, 2015 (for Model 
A340-500 and -600 series airplanes).

   Figure 1 to Paragraphs (g), (h), and (q) of This AD--Definition of
                             Airplane Groups
------------------------------------------------------------------------
                                                        On which the
                                                    following actions or
             Group               Airplane models     modifications have
                                                         been done
------------------------------------------------------------------------
Group 1 airplanes.............  Airbus Model A330- On which the actions
                                 200 and -300       specified in Airbus
                                 series airplanes.  Service Bulletin
                                                    A330-27-3137, dated
                                                    March 20, 2007; or
                                                    Revision 01, dated
                                                    December 6, 2007;
                                                    and Airbus Service
                                                    Bulletin A330-92-
                                                    3046, Revision 04,
                                                    dated July 16, 2010;
                                                    or Revision 05,
                                                    dated November 7,
                                                    2011; or Revision
                                                    06, dated November
                                                    15, 2013; have been
                                                    embodied in service.
                                Airbus Model A340- On which the actions
                                 200 and -300       specified in Airbus
                                 series airplanes.  Service Bulletin
                                                    A340-27-4136,
                                                    including Appendix
                                                    1, dated March 20,
                                                    2007; or Revision
                                                    01, including
                                                    Appendix 1, dated
                                                    December 6, 2007;
                                                    and Airbus Service
                                                    Bulletin A340-92-
                                                    4056, Revision 03,
                                                    dated July 16, 2010;
                                                    have been embodied
                                                    in service.
Group 2 airplanes.............  Airbus Model A330- On which Airbus
                                 200 and -300       Modifications 55780,
                                 series airplanes   52269, and 56056
                                 and Model A340-    have been embodied
                                 200 and -300       in production.
                                 series airplanes.
                                Airbus Model A340- On which Airbus
                                 500 and -600       Modifications 54882,
                                 series airplanes.  52191, and 56058
                                                    have been embodied
                                                    in production.
Group 3 airplanes.............  Airbus Model A330- On which Airbus
                                 200 and -300       Service Bulletin
                                 series airplanes.  A330-27-3137, dated
                                                    March 20, 2007; or
                                                    Revision 01, dated
                                                    December 6, 2007;
                                                    has been embodied in
                                                    service and Airbus
                                                    Modifications 52269
                                                    and 56056 have been
                                                    embodied in
                                                    production.
                                Airbus Model A330- On which Airbus
                                 200 and -300       Modification 55780
                                 series airplanes.  has been embodied in
                                                    production and
                                                    Airbus Service
                                                    Bulletin A330-92-
                                                    3046 Revision 04,
                                                    dated July 16, 2010;
                                                    or Revision 05,
                                                    dated November 07,
                                                    2011; or Revision
                                                    06, dated November
                                                    15, 2013; has been
                                                    embodied in service.
                                Airbus Model A340- On which Airbus
                                 200 and -300       Service Bulletin
                                 series airplanes.  A340-27-4136,
                                                    including Appendix
                                                    1, dated March 20,
                                                    2007; or Revision
                                                    01, including
                                                    Appendix 1, dated
                                                    December 6, 2007;
                                                    has been embodied in
                                                    service and Airbus
                                                    Modifications 52269
                                                    and 56056 have been
                                                    embodied in
                                                    production.
                                Airbus Model A340- On which Airbus
                                 200 and -300       Modification 55780
                                 series airplanes.  has been embodied in
                                                    production and
                                                    Airbus Service
                                                    Bulletin A340-92-
                                                    4056, Revision 03,
                                                    dated July 16, 2010,
                                                    has been embodied in
                                                    service.
------------------------------------------------------------------------

(h) Installation of CSP and Electrical Harness

    For all airplanes, except Group 2 airplanes specified in figure 
1 to paragraphs (g), (h), and (q) of this AD, and except for 
airplanes identified in paragraphs (i), (j), and (n)(2) of this AD: 
Within 12 months after the effective date of this AD, modify the 
airplane by installing a CSP on the THSA and an additional 
electrical harness, in accordance with the Accomplishment 
Instructions of the Airbus service information specified in figure 2 
to paragraphs (h) and (i) of this AD, as applicable to the part 
number of the THSA installed on the airplane, except as provided by 
paragraph (n)(2) of this AD.

         Figure 2 to Paragraphs (h) and (i) of this AD--Applicable Service Information for Modification
----------------------------------------------------------------------------------------------------------------
                                                                                        Service bulletin for
         THSA Part No. (P/N)              Service bulletin for CSP installation          electrical harness
                                                                                            installation
----------------------------------------------------------------------------------------------------------------
47172-300............................  Airbus Service Bulletin A330-27-3137,       Airbus Service Bulletin A330-
                                        Revision 02, dated January 18, 2010, for    92-3046, Revision 07, dated
                                        Airbus Model A330-200 and -300 series       January 13, 2017, for Airbus
                                        airplanes; and                              Model A330-200 and -300
                                                                                    series airplanes; and
                                       Airbus Service Bulletin A340-27-4136,
                                        Revision 02, including Appendix 1, dated
                                        February 24, 2010, for Airbus Model A340-
                                        200 and -300 series airplanes.

[[Page 34255]]

 
47147-500............................  Airbus Service Bulletin A330-27-3143,       Airbus Service Bulletin A340-
                                        Revision 01, dated July 10, 2012, for       92-4056, Revision 04, dated
                                        Airbus Model A330-200 and -300 series       December 5, 2013, for Airbus
                                        airplanes; and                              Model A340-200 and -300
                                                                                    series airplanes.
                                       Airbus Service Bulletin A340-27-4143,
                                        dated February 21, 2012, for Airbus Model
                                        A340-200 and -300 series airplanes.
47175-200, 47175-300.................  Airbus Service Bulletin A340-27-5030,       Airbus Service Bulletin A340-
                                        Revision 01, including Appendix 1, dated    92-5008, Revision 07, dated
                                        November 20, 2009, for Airbus Model A340-   February 8, 2013, for Airbus
                                        541 and -642 airplanes.                     Model A340-541 and -642
                                                                                    airplanes.
----------------------------------------------------------------------------------------------------------------

(i) ``Additional Work'' on Previously Modified Airplanes

    For airplanes that have already been modified (installation of 
CSP on the THSA and electrical harness) before the effective date of 
this AD in accordance with the Accomplishment Instructions of any 
previous revision of an Airbus service bulletin specified in figure 
2 to paragraphs (h) and (i) of this AD, as applicable: Within 12 
months after the effective date of this AD, do the ``Additional 
Work'' specified in, and in accordance with, the Accomplishment 
Instructions of the applicable Airbus service information specified 
in figure 2 to paragraphs (h) and (i) of this AD.

(j) Installation of Electrical Harness on Airplanes Equipped With a CSP

    For airplanes having one of the THSAs installed with a part 
number listed in figure 3 to paragraph (j) of this AD, and which 
have been modified by installing a CSP on the THSA as required by 
paragraph (h) of this AD: Within 12 months after the effective date 
of this AD, inspect to determine if the electrical harness 
identified in the applicable Airbus service information specified in 
figure 3 to paragraph (j) of this AD is installed on the airplane, 
and if found not to be installed, modify the airplane by installing 
an electrical harness, in accordance with the Accomplishment 
Instructions of the Airbus service information specified in figure 3 
to paragraph (j) of this AD, as applicable to the part number of the 
THSA installed on the airplane. Airplanes having one of the THSAs 
installed with a part number listed in figure 3 to paragraph (j) of 
this AD already have the CSP installed on the THSA, and only the 
electrical harness must be installed on the airplane.

  Figure 3 to Paragraph (j) of This AD--Electrical Harness Installation
------------------------------------------------------------------------
                                             Service information for
                THSA P/N                 electrical harness installation
------------------------------------------------------------------------
47172-500, 47172-510, 47172-520, 47172-  Airbus Service Bulletin A330-92-
 530, 47147-700, 47147-710.               3046, Revision 07, dated
                                          January 13, 2017, for Airbus
                                          Model A330-200 and -300 series
                                          airplanes.
                                         Airbus Service Bulletin A340-92-
                                          4056, Revision 04, dated
                                          December 5, 2013, for Airbus
                                          Model A340-200 and -300 series
                                          airplanes.
47175-500, 47175-520, 47175-530........  Airbus Service Bulletin A340-92-
                                          5008, Revision 07, dated
                                          February 8, 2013, for Airbus
                                          Model A340-541 and -642
                                          airplanes.
------------------------------------------------------------------------

(k) Terminating Action for Repetitive Inspections of Airbus Model A330-
200 and -300 Series Airplanes

    Accomplishment of a modification before the effective date of 
this AD, using the Accomplishment Instructions of Airbus Service 
Bulletin A330-27-3137, dated March 20, 2007; or Revision 01, dated 
December 6, 2007; and Airbus Service Bulletin A330-92-3046, Revision 
04, dated July 15, 2010; or Revision 05, dated November 7, 2011; or 
Revision 06, dated November 15, 2013; terminates the repetitive 
inspections specified in paragraphs (k)(1) through (k)(4) of this 
AD. Modification of an airplane as required by this paragraph does 
not constitute terminating action for the actions specified in 
paragraph (g)(2) of this AD or the additional work specified in 
paragraph (i) of this AD.
    (1) Task 274400-00001-1-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
check the gap at the secondary nut trunnion, of Airbus A330 ALS Part 
4--System Equipment Maintenance Requirements (SEMR), Revision 05, 
dated October 19, 2015.
    (2) Task 274400-00001-2-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
check the CSPs, of Airbus A330 ALS Part 4--System Equipment 
Maintenance Requirements (SEMR), Revision 05, dated October 19, 
2015.
    (3) Task 274400-00001-3-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
check the CSPs, of Airbus A330 ALS Part 4--System Equipment 
Maintenance Requirements (SEMR), Revision 05, dated October 19, 
2015.
    (4) Task 274400-00001-4-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
check the CSPs, of Airbus A330 ALS Part 4--System Equipment 
Maintenance Requirements (SEMR), Revision 05, dated October 19, 
2015.

(l) Terminating Action for Repetitive Inspections of Airbus Model A340-
200 and -300 Series Airplanes

    Accomplishment of a modification in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A340-27-4143, 
dated February 21, 2012; and Airbus Service Bulletin A340-92-4056, 
Revision 03, dated July 16, 2010; terminates the actions required by 
paragraph (g)(1) of this AD for modified Airbus Model A340-200 and -
300 series airplanes only. Modification of an airplane as specified 
in this paragraph does not constitute terminating action for the 
actions specified in paragraph (g)(2) of this AD, or the additional 
work specified in paragraph (i) of this AD.

(m) Terminating Action for Repetitive Inspections of Airbus Model A340-
200 and -300 Series Airplanes

    Accomplishment of a modification before the effective date of 
this AD using the Accomplishment Instructions of Airbus Service 
Bulletin A340-27-4136, including Appendix 1, dated March 20, 2007; 
or Revision 01, including Appendix 1, dated December 6, 2007; and 
Airbus Service Bulletin A340-92-4056, Revision 03, dated July 16, 
2010; terminates the repetitive inspections specified in paragraphs 
(m)(1) through (m)(4) of this AD. Modification of an airplane as 
specified in this paragraph does not constitute terminating action 
for the actions specified in paragraph (g)(2) of this AD, or the 
additional work specified in paragraph (i) of this AD.
    (1) Task 274400-00001-1-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
gap check at the secondary nut trunnion, of Airbus A340 ALS Part 4--
System Equipment Maintenance Requirements (SEMR), Revision 04, dated 
October 19, 2015.

[[Page 34256]]

    (2) Task 274400-00001-2-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
CSP check, of Airbus A340 ALS Part 4--System Equipment Maintenance 
Requirements (SEMR), Revision 04, dated October 19, 2015.
    (3) Task 274400-00001-3-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
CSP check, of Airbus A340 ALS Part 4--System Equipment Maintenance 
Requirements (SEMR), Revision 04, dated October 19, 2015.
    (4) Task 274400-00001-4-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
CSP check, of A340 ALS Part 4--System Equipment Maintenance 
Requirements (SEMR), Revision 04, dated October 19, 2015.

(n) Exceptions to the Actions in Certain Service Information and 
Paragraph (h) of This AD

    (1) Where Airbus Service Bulletin A330-27-3102, Revision 09, 
dated March 29, 2016 (for Model A330 series airplanes); or Airbus 
Service Bulletin A340-27-4107, Revision 09, dated March 29, 2016 
(for Model A340 series airplanes); specifies to contact Airbus for a 
damage assessment: Before further flight, accomplish the required 
actions in accordance with the procedures specified in paragraph 
(s)(2) of this AD.
    (2) For airplanes that already had the electrical harness 
installed during production using Airbus Modifications 52269 and 
56056 for Airbus Model A330-200 and -300 series airplanes and Airbus 
Model A340-200 and -300 series airplanes, and using Airbus 
Modifications 52191 and 56058 for Model A340-500 and -600 series 
airplanes: Only the CSP must be installed on the THSA in accordance 
with applicable Airbus service bulletins and within the compliance 
time specified in paragraph (h) of this AD.

(o) Terminating Action for Repetitive Inspections for Airplanes on 
Which Actions Required by Paragraph (h), (i), or (j) of This AD Are 
Done

    Modification of an airplane as required by paragraph (h), (i), 
or (j) of this AD, as applicable, constitutes terminating action for 
that airplane for the applicable actions identified in paragraphs 
(o)(1) through (o)(4) of this AD.
    (1) For all airplanes: The actions required by paragraph (g) of 
this AD.
    (2) For Model A340-500 and -600 series airplanes: Task 274000-
B0002-1-C, Inspection of the ball-screw assembly for integrity of 
the primary and secondary load paths, of Airbus A340 ALS Part 3--
Certification Maintenance Requirements (CMR), Revision 03, dated 
October 19, 2015.
    (3) For Model A330-200 and -300 series airplanes: The ALS tasks 
identified in paragraphs (k)(1) through (k)(4) of this AD.
    (4) For Model A340-200 and -300 series airplanes: The ALS tasks 
identified in paragraphs (m)(1) through (m)(4) of this AD.

(p) Ball-Screw Assembly Inspection for Certain Airplanes

    For Model A340-500 and -600 airplanes that are in post-Airbus 
Service Bulletin A340-92-5008, at Revision 06 or earlier, 
configuration: Before exceeding the threshold or interval, as 
applicable, of Task 274000-B0002-1-C, Inspection of the ball-screw 
assembly for integrity of the primary and secondary load paths, of 
Airbus A340 ALS Part 3--Certification Maintenance Requirements 
(CMR), Revision 03, dated October 19, 2015, or within 3 months after 
the effective date of this AD, whichever occurs later, accomplish 
Task 274000-B0002-1-C, Inspection of the ball-screw assembly for 
integrity of the primary and secondary load paths, of Airbus A340 
ALS Part 3--Certification Maintenance Requirements (CMR), Revision 
03, dated October 19, 2015; and do all applicable corrective 
actions. Do all applicable corrective actions before further flight 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA 
DOA. Repeat Task 274000-B0002-1-C, Inspection of the ball-screw 
assembly for integrity of the primary and secondary load paths, 
thereafter at the applicable intervals specified in Airbus A340 ALS 
Part 3--CMRs, Revision 03, dated October 19, 2015.

(q) Parts Installation Prohibitions

    (1) For all airplanes except Group 2 airplanes as identified in 
figure 1 to paragraphs (g), (h), and (q) of this AD: After 
modification of the airplane as required by paragraph (h), (i), or 
(j) of this AD, as applicable, no person may install any THSA having 
part number (P/N) 47172-300, P/N 47147-500, P/N 47175-200, or P/N 
47175-300.
    (2) For Group 2 airplanes, as identified in figure 1 to 
paragraphs (g), (h), and (q) of this AD: As of the effective date of 
this AD, no person may install on any Group 2 airplane any THSA 
having P/N 47172-300, P/N 47147-500, P/N 47175-200, or P/N 47175-
300.

(r) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g)(2) of this AD, if those actions were performed before 
the effective date of this AD using the applicable service 
information specified in paragraphs (r)(1)(i) through (r)(1)(iv) of 
this AD.
    (i) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A330 ALS Part 4--Ageing Systems Maintenance, Revision 03, 
dated September 9, 2011 (for Model A330 series airplanes).
    (ii) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A330 ALS Part 4--Ageing Systems Maintenance, Revision 04, 
dated August 27, 2013 (for Model A330 series airplanes).
    (iii) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, 
of Airbus A340 ALS Part 4--Ageing Systems Maintenance, Revision 02, 
dated October 12, 2011 (for Model A340-200 and -300 series 
airplanes).
    (iv) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A340 ALS Part 4--Ageing Systems Maintenance, Revision 03, 
dated November 15, 2012 (for Model A340-200 and -300 series 
airplanes).
    (2) This paragraph provides credit for the electrical harness 
installation required by paragraph (h) of this AD and the inspection 
and electrical harness installation required by paragraph (j) of 
this AD, if those actions were performed before the effective date 
of this AD using Airbus Service Bulletin A330-92-3046, Revision 06, 
dated November 15, 2013.

(s) 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 it to the attention 
of the person identified in paragraph (t)(2) of this AD. Information 
may be emailed to: 9-ANM-116-ACO-AMOC-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: 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 EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(t) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0219, dated September 29, 
2014, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-9393.
    (2) For more information about this AD, 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.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (u)(3) and (u)(4) of this AD.

(u) 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.

[[Page 34257]]

    (i) Airbus A330 Airworthiness Limitations Section (ALS) Part 4--
System Equipment Maintenance Requirements (SEMR), Revision 05, dated 
October 19, 2015.
    (ii) Airbus A340 Airworthiness Limitations Section (ALS) Part 
3--Certification Maintenance Requirements (CMR), Revision 03, dated 
October 19, 2015.
    (iii) Airbus A340 Airworthiness Limitations Section (ALS) Part 
4--System Equipment Maintenance Requirements (SEMR), Revision 04, 
dated October 19, 2015.
    (iv) Airbus Service Bulletin A330-27-3102, Revision 09, dated 
March 29, 2016.
    (v) Airbus Service Bulletin A330-27-3137, including Appendix 01, 
dated March 20, 2007.
    (vi) Airbus Service Bulletin A330-27-3137, Revision 01, 
including Appendix 1, dated December 6, 2007.
    (vii) Airbus Service Bulletin A330-27-3137, Revision 02, dated 
January 18, 2010.
    (viii) Airbus Service Bulletin A330-27-3143, Revision 01, dated 
July 10, 2012.
    (ix) Airbus Service Bulletin A330-92-3046, Revision 04, dated 
July 16, 2010.
    (x) Airbus Service Bulletin A330-92-3046, Revision 05, dated 
November 7, 2011.
    (xi) Airbus Service Bulletin A330-92-3046, Revision 07, dated 
January 13, 2017.
    (xii) Airbus Service Bulletin A340-27-4107, Revision 09, dated 
March 29, 2016.
    (xiii) Airbus Service Bulletin A340-27-4136, including Appendix 
01, dated March 20, 2007.
    (xiv) Airbus Service Bulletin A340-27-4136, Revision 01, 
including Appendix 1, dated December 6, 2007.
    (xv) Airbus Service Bulletin A340-27-4136, Revision 02, 
including Appendix 1, dated February 24, 2010.
    (xvi) Airbus Service Bulletin A340-27-4143, dated February 21, 
2012.
    (xvii) Airbus Service Bulletin A340-27-5030, Revision 01, 
including Appendix 1, dated November 20, 2009.
    (xviii) Airbus Service Bulletin A340-92-4056, Revision 03, dated 
July 16, 2010.
    (xix) Airbus Service Bulletin A340-92-4056, Revision 04, dated 
December 5, 2013.
    (xx) Airbus Service Bulletin A340-92-5008, Revision 07, dated 
February 8, 2013.
    (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 http://www.airbus.com.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on June 15, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-14923 Filed 7-21-17; 8:45 am]
 BILLING CODE 4910-13-P