Airworthiness Directives; Airbus Airplanes, 47537-47543 [2013-18774]

Download as PDF Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 47537 FIGURE 1 TO PARAGRAPH (c)—TGB RADIAL GEARSHAFT P/N 1995M24P02 S/N’ S—Continued FIA0JETL FIA0JER8 FIA0J7WC FIA0JETE FIA0K3AT FIA0JJ59 FIA0K3AW FIA0JVRN FIA0JNH8 FIA0JETN FIA0HY78 FIA0HY75 FIA0HEG0 FIA0KH9E FIA0KH9F FIA0H0T9 FIA0HLY3 FIA0K62V FIA0HEGY FIA0HWKC FIA0K3A0 FIA0JVRJ FIA0K8AA FIA0KCYT FIA0KH9T FIA0KH9W FIA0HEG1 FIA0HEG3 FIA0J7WJ FIA0JER7 FIA0JVRF FIA0K63K FIA0J7WK FIA0JER5 FIA0JETM (d) Unsafe Condition This AD was prompted by reports of three failures of TGB radial gearshafts which resulted in in-flight shutdowns (IFSDs). We are issuing this AD to prevent failure of the TGB radial gearshaft, which could result in IFSD of one or more engines, loss of thrust control, and damage to the airplane. (e) Compliance (1) Comply with this AD within the compliance times specified, unless already done. (2) Before further flight after the effective date of this AD, do not operate the airplane if more than one installed engine has a TGB radial gearshaft P/N and S/N listed in Figure 1 to paragraph (c) of this AD. (f) Mandatory Terminating Action No later than 60 days after the effective date of this AD, as terminating action to the requirements of paragraph (e) of this AD, replace all TGB radial gearshafts identified in Figure 1 to paragraph (c) of this AD that are installed on an airplane with TGB radial gearshafts that are eligible for installation. (g) Prohibition on Operation Sixty days after the effective date of this AD, do not operate any airplane that has an engine installed that has a TGB radial gearshaft P/N and S/N listed in Figure 1 to paragraph (c) of this AD. tkelley on DSK3SPTVN1PROD with RULES (h) Definition For the purposes of this AD, a TGB radial gearshaft eligible for installation is: (1) A TGB radial gearshaft P/N and S/ N, not listed in this AD or (2) A TGB radial gearshaft with an S/ N listed in paragraph (c) of this AD with part number 1995M24P04, 2205M61P01 or 2205M61P02. VerDate Mar<15>2010 17:14 Aug 05, 2013 Jkt 229001 FIA0KH9J FIA0HY8G FIA0HY8M FIA0HY8A FIA0H0VG FIA0K3AR FIA0JETC FIA0JNJC FIA0K63L FIA0KCYN FIA0JVRG FIA0HY8L FIA0HY8J FIA0H0VH FIA0HLY1 FIA0H0VF (i) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures in 14 CFR 39.19 to make your request. (j) Related Information (k) Material Incorporated by Reference None. Frm 00011 Fmt 4700 Sfmt 4700 FIA0HLY4 Issued in Burlington, Massachusetts, on July 25, 2013. Frank P. Paskiewicz, Acting Director, Aircraft Certification Service. [FR Doc. 2013–18840 Filed 8–5–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION (1) For more information about this AD, contact Carlos Fernandes, Aerospace Engineer, Engine Certification Office, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7189; fax: 781– 238–7199; email: carlos.fernandes@faa.gov. (2) GE GE90–100 Series Alert Service Bulletin No. GE90–100 S/B 72–A0568, Revision 0, dated July 10, 2013; GE GE90–100 Series Service Bulletin (SB) No. GE90–100 S/B 72–0569, Revision 0, dated July 19, 2013; GE GE90–100 Series SB No. GE90–100 S/B 72–0563, Revision 0, dated June 21, 2013, and Revision 1, dated July 10, 2013; GE GE90 SB No. GE90 S/B 72–1066, Revision 0, dated June 21, 2013; and GE GE90 SB No. GE90 S/B 72–1091, Revision 0, dated June 11, 2013, can be obtained from GE using the contact information in paragraph (j)(3) of this AD. (3) For service information identified in this AD, contact General Electric Company, One Neumann Way, Room 285, Cincinnati, OH; phone: 513–552– 3272; email: geae.aoc@ge.com. (4) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. PO 00000 FIA0J7VW FIA0J7VY FIA0J7VT FIA0J7WF FIA0J7V6 FIA0K89G FIA0K89K FIA0K89R FIA0KCYJ FIA0JJ6G FIA0JJ6A FIA0HY8K FIA0HLY6 FIA0HLY0 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1033; Directorate Identifier 2010–NM–266–AD; Amendment 39–17504; AD 2013–13–16] 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) 2005–07– 04 for all Airbus Model A330–200 and –300 series airplanes, and Model A340– 200 and –300 series airplanes. AD 2005– 07–04 required repetitive inspections to detect discrepancies of the transfer tubes and the collar of the ball nut of the trimmable horizontal stabilizer actuator (THSA), and corrective action if necessary; repetitive inspections for discrepancies of the ball screw assembly, and corrective action if necessary; 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 removes certain inspections, revises certain actions, and adds airplanes to the applicability. This AD was prompted by several reports of SUMMARY: E:\FR\FM\06AUR1.SGM 06AUR1 47538 Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations disconnection of the transfer tube from the ball nut of the THSA. We are issuing this AD to prevent degraded operation of the THSA, which could result in reduced controllability of the airplane. DATES: This AD becomes effective September 10, 2013. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 10, 2013. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of May 4, 2005 (70 FR 16104, March 30, 2005). ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. 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: tkelley on DSK3SPTVN1PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. The NPRM was published in the Federal Register on October 2, 2012 (77 FR 60075), and proposed to supersede AD 2005–07–04, Amendment 39–14028 (70 FR 16104, March 30, 2005). (AD 2005– 07–04 superseded AD 2001–11–09, Amendment 39–12252 (66 FR 31143, June 11, 2001).) The NPRM proposed to correct an unsafe condition for the specified products. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2010–0192 (corrected), dated October 11, 2010; and EASA Airworthiness Directive 2010–0193 (corrected), dated October 11, 2010; (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. 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. This condition is caused by water ingress into the ball-nut resulting in the jamming of VerDate Mar<15>2010 17:14 Aug 05, 2013 Jkt 229001 the ball transfer circuit when the water freezes. If the three (independent) ball circuits fail, then the THSA will operate on a fail-safe nut. This nut (which operates without balls) would then jam after several movements on the screw of the THSA. This degraded operation is not detectable in the cockpit by the crew as long as the THSA does not jam and could damage the ball screw and the fail-safe nut. ´ To detect this unsafe condition, [Direccion ´ General de Aviacion Civil] DGAC France AD F–2001–356 [and F–2001–357] was issued to require repetitive inspections of the transfer tubes and their collars in order to detect at an early stage any distortion or initiation of disconnection. Further to a new case of transfer tube disconnection, * * * [revised DGAC ADs] required an additional repetitive greasing task with reinforcement of the ball-nut maintenance greasing instructions. 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 ECAM [electronic centralized aircraft monitor]. In this case a mandatory inspection of the THSA is required before the next flight. DGAC France AD F–2002–038 [and F– 2002–037] required application of a final fix (related to inspection and greasing task required by DGAC France AD F–2001–356 [and F–2001–357]) for the THSA P/N 47172 by application of Airbus modification 49590/ Service Bulletin (SB) A330–27–3085 [or SB A340–27–4089]. It changes the THSA P/N from 47172 to 47172–300. Later on, DGAC France AD F–2002–414R3 replaced the DGAC AD France F–2001– 356R2 and F–2002–038 [and DGAC France AD F2002–415R2 superseded DGAC France ADs F–2001–357R2 and F–2002–037] requiring: —the repetitive [detailed] inspection [for discrepancies] of all THSA P/N in service [for integrity of the primary and secondary load path and check the Checkable Shear Pins (CSPs)], and —the lubrication of some THSA P/N, and —the replacement of THSA P/N 47172, 47147–400 and 47147–2XX/–3XX [DGAC France AD F–2002–414R3 and F– 2002–415R2 correspond to FAA AD 2005– 07–04, Amendment 39–14028 (70 FR 16104, March 30, 2005).] Airbus has later introduced 4 new THSA P/N (47172–500, 47172–510, 47172–520 and 47172–530). This [EASA] AD retains the requirements of DGAC France AD F–2002–414R3 [and F– 2002–415R2], which is superseded, and requires repetitive inspections and lubrications of the new THSA P/N. The repetitive inspection and lubrication requirements for THSA P/N 47172–520 and 47172–530 shall [also] be included in the next Airworthiness Limitation Section (ALS) Part 4 revision. * * * * * Corrective actions include replacing the THSA with a new THSA if cracks, dents, or corrosion are found, or if the PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 feeler gage has failed at any of the four gaps. Other corrective action includes using a method approved by the FAA or the EASA (or its delegated agent) for a finding of metallic debris, loose nut, damaged or missing lock washers, pins and parts, or incorrect installation of items. AD 2005–07–04, Amendment 39– 14028 (70 FR 16104, March 30, 2005), required repetitive inspections for discrepancies. This AD requires, for certain airplanes, repetitive inspections for the integrity of the primary and secondary load path, and the CSPs. The unsafe condition is the degraded operation of the THSA, which could result in reduced controllability of the airplane. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received. Request To Use Later Document Revision Delta Airlines (Delta) requested that paragraph (j)(2) of the NPRM (77 FR 60075, October 2, 2012) refer to Airbus A330 Airworthiness Limitations Section (ALS) Part 4—Ageing Systems Maintenance, Revision 03, dated September 9, 2011; instead of Revision 02, dated December 16, 2009. Delta stated that Revision 03 of that ALS specifies the 1,000 flight-hour lubrication threshold and repetitive interval that are specified in paragraph (j)(2) of the NPRM, whereas Revision 02 of this ALS specifies 700 flight hours for the lubrication threshold and repetitive interval. We agree that Airbus A330 Airworthiness Limitations Section (ALS) Part 4—Ageing Systems Maintenance, Revision 03, dated September 9, 2011, correctly specifies the lubrication threshold and repetitive interval. We have changed paragraph (j)(2) of this AD accordingly. In addition, we have changed paragraph (j)(2) of this AD to reference Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated October 12, 2011; and Revision 03, dated November 15, 2012; for the same reason. Request To Change Wording Delta requested that we change the wording in paragraph (l) of the NPRM (77 FR 60075, October 2, 2012), which states ‘‘For airplanes identified in paragraph (k) of this AD.’’ The commenter asked that the wording ‘‘identified in’’ be replaced with E:\FR\FM\06AUR1.SGM 06AUR1 Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations ‘‘affected by.’’ The commenter provided no reason for the change. We disagree to change the wording in paragraph (n) in this AD (identified as paragraph (l) in the NPRM (77 FR 60075, October 2, 2012)) as requested by the commenter. However, we have moved the content of paragraphs (k)(1), (k)(2), and (k)(3) of the NPRM to new paragraph (l) in this AD to clarify the actions and affected airplanes. We have also moved the content of paragraph (k)(6) of the NPRM to new paragraph (m) of this AD, and re-identified succeeding paragraphs accordingly. Finally, in paragraph (n) of this AD, we revised the wording to describe the affected airplanes. Request To Include Additional Part Number Delta requested that we include THSA P/N 47172–520 and P/N ‘‘47127–530’’ in paragraph (m) of the NPRM (77 FR 60075, October 2, 2012) as applicable part numbers for Model A330 series airplanes. We disagree to include THSA P/N 47127–530 as there is no such part number. We infer that the commenter meant to specify THSA P/N 47172–530. THSA P/N 47172–520 and P/N 47172– 530 are not included in the MCAI. However, all necessary tasks for those THSA part numbers are contained in Airbus A330 Airworthiness Limitations Section (ALS) Part 4—Ageing Systems Maintenance, Revision 03, dated September 9, 2011; and Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated October 12, 2011, and Revision 03, dated November 15, 2012. The FAA NPRMs to mandate these ALS Part 4 documents are pending at this time. Therefore, we have not changed this AD in this regard. tkelley on DSK3SPTVN1PROD with RULES Request To Consider Another EASA AD Corinne Dayde stated that she ‘‘Cannot see how EASA 2012–0061 is considered.’’ We are considering addressing EASA AD 2012–0061R1, dated November 30, 2012, in a separate FAA AD. We have not changed this AD in this regard. Conclusion We reviewed the available data, including the comments received, 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 changes: • Are consistent with the intent that was proposed in the NPRM (77 FR 60075, October 2, 2012) for correcting the unsafe condition; and VerDate Mar<15>2010 17:14 Aug 05, 2013 Jkt 229001 • Do not add any additional burden upon the public than was already proposed in the NPRM (77 FR 60075, October 2, 2012). Costs of Compliance We estimate that this AD will affect about 33 products of U.S. registry. The actions that are required by AD 2005–07–04, Amendment 39–14028 (70 FR 16104, March 30, 2005), and retained in this AD take up to 36 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the retained actions is up to $3,060 per product. We estimate that it will take about 2 work-hours per product to comply with the new basic requirements of this AD. The average labor rate is $85 per workhour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $5,610, or $170 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. 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; PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 47539 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. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office 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 Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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) 2005–07–04, Amendment 39–14028 (70 FR 16104, March 30, 2005), and adding the following new AD: ■ 2013–13–16 Airbus: Amendment 39–17504. Docket No. FAA–2012–1033; Directorate Identifier 2010–NM–266–AD. (a) Effective Date This airworthiness directive (AD) becomes effective September 10, 2013. (b) Affected ADs This AD supersedes AD 2005–07–04, Amendment 39–14028 (70 FR 16104, March 30, 2005). (c) Applicability This AD applies to all Airbus Model A330– 201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340– E:\FR\FM\06AUR1.SGM 06AUR1 47540 Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 211, –212, –213, –311, –312, and –313 airplanes; certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 27: Flight Controls. (e) Reason This AD was prompted by several reports of disconnection of the transfer tube from the ball nut of the trimmable horizontal stabilizer actuator (THSA). We are issuing this AD to prevent degraded operation of the THSA, which could result in reduced controllability of the airplane. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Retained Modification or Replacement This paragraph restates the requirements of paragraph (g) of AD 2005–07–04, Amendment 39–14028 (70 FR 16104, March 30, 2005). Except for Model A330–223F and –243F airplanes: Within 24 months after May 4, 2005 (the effective date of AD 2005–07– 04), modify the ball nut of each THSA by doing paragraph (g)(1) or (g)(2) of this AD, as applicable. (1) For THSAs having part number (P/N) 47172: Modify the ball nut of the THSA, or replace the existing THSA with a serviceable part having P/N 47172–300; in accordance with Airbus Service Bulletin A330–27–3085 (for Model A330 series airplanes) or A340– 27–4089 (for Model A340–313 series airplanes), both Revision 02, both dated September 5, 2002; as applicable. Note 1 to paragraph (g)(1) of this AD: Airbus Service Bulletins A330–27–3085 and A340–27–4089, both Revision 02, both dated September 5, 2002, refer to TRW Aeronautical Systems Service Bulletin 47172–27–03, dated October 24, 2001 (which is not incorporated by reference in this AD), as additional guidance for accomplishing the modification of the ball nut of the THSA. (2) For THSAs having P/N 47147–200, –210, –213, –300, –303, –350, or –400: Modify the ball nut of the THSA, or replace the existing THSA with an improved part having P/N 47147–500; as applicable; in accordance with Airbus Service Bulletin A330–27–3093 (for Model A330 series airplanes) or A340–27–4099 (for Model A340–200 and –300 series airplanes), both Revision 01, both dated September 5, 2002; as applicable. Note 2 to paragraph (g)(2) of this AD: Airbus Service Bulletins A330–27–3093 and A340–27–4099, both Revision 01, both dated September 5, 2002, refer to TRW Aeronautical Systems Service Bulletin 47147–27–10, dated June 27, 2002 (which is not incorporated by reference in this AD), as additional guidance for accomplishing the modification of the ball nut of the THSA. (h) Retained Previous/Concurrent Requirements This paragraph restates the requirements of paragraph (h) of AD 2005–07–04, Amendment 39–14028 (70 FR 16104, March 30, 2005). (1) Except for Model A330–223F and –243F airplanes, prior to or concurrently with accomplishing the requirements of paragraph (g)(2) of this AD, do all of the actions specified in the Accomplishment Instructions of the applicable Airbus service bulletins listed in table 1 or 2 to paragraph (h)(1) of this AD, as applicable, in accordance with those service bulletins. Note 3 to paragraph (h)(1) of this AD: Airbus Service Bulletin A330–27–3093, Revision 01, dated September 5, 2002, specifies that the actions in Airbus Service Bulletin A330–27–3052 be accomplished previously or concurrently. Airbus Service Bulletin A330–27–3052, Revision 03, dated December 5, 2001, specifies that the actions in Airbus Service Bulletins A330–27–3007, A330–27–3015, A330–27–3047, A330–27– 3050, and A330–55–3020 be accomplished previously or concurrently. Note 4 to paragraph (h)(1) of this AD: Airbus Service Bulletin A340–27–4099, Revision 01, dated September 5, 2002, specifies that the actions in Airbus Service Bulletin A340–27–4059 be accomplished previously or concurrently. Airbus Service Bulletin A340–27–4059, Revision 03, dated December 5, 2001, specifies that the actions in Airbus Service Bulletins A340–27–4007, A340–27–4025, A340–27–4054, A340–27– 4057, and A340–55–4021 be accomplished previously or concurrently. TABLE 1 TO PARAGRAPH (h)(1) OF THIS AD—RETAINED PREVIOUS/CONCURRENT REQUIREMENTS FOR MODEL A330 SERIES AIRPLANES Airbus service bulletin— Revision level— Date— Main action— Additional source of guidance (not incorporated by reference in this AD)— Samm Avionique Service Bulletin SC5300–27–24–01, dated April 15, 1994. Lucas Aerospace Service Bulletin 47147– 27–02, Revision 1, dated January 31, 1996. Lucas Aerospace Service Bulletin 47147– 27–04, Revision 1, dated June 20, 1997. Lucas Aerospace Service Bulletin 47147– 27–05, dated November 8, 1996. Lucas Aerospace Service Bulletin 47147– 27–07, dated May 4, 1998. None. A330-27-3007 ..... 01 September 18, 1996 .... Replace rudder servo controls with modified parts. A330-27-3015 ..... ................ June 7, 1995 ................ A330-27-3047 ..... 01 November 26, 1997 ..... Modify the control valve detent and the jamming protection device on the THSA. Replace hydraulic motors on the THSA with new parts. A330-27-3050 ..... ................ November 15, 1996 ..... A330-27-3052 ..... 03 December 5, 2001 ....... A330-55-3020 ..... 01 October 21, 1998 ......... Replace mechanical input shaft for THSA with modified part. Replace THSA with a modified THSA ...... Perform a general visual inspection of the THSA screw jack fitting assembly for correct installation of a washer; and correctly install washer as applicable. tkelley on DSK3SPTVN1PROD with RULES TABLE 2 TO PARAGRAPH (h)(1) OF THIS AD—RETAINED PREVIOUS/CONCURRENT REQUIREMENTS FOR MODEL A340 SERIES AIRPLANES Airbus service bulletin— Revision level— Date— Main action— Additional source of guidance (not incorporated by reference in this AD)— A340-27-4007 ..... ................ April 7, 1994 ................. A340-27-4025 ..... ................ June 7, 1995 ................ Replace hydraulic motors on the THSA with new parts. Modify the control valve detent and the jamming protection device on the THSA. Lucas Aerospace Service Bulletin 47147– 27–01, dated May 4, 1998. Lucas Aerospace Service Bulletin 47147– 27–02, Revision 1, dated January 31, 1996. VerDate Mar<15>2010 19:12 Aug 05, 2013 Jkt 229001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\06AUR1.SGM 06AUR1 Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 47541 TABLE 2 TO PARAGRAPH (h)(1) OF THIS AD—RETAINED PREVIOUS/CONCURRENT REQUIREMENTS FOR MODEL A340 SERIES AIRPLANES—Continued Airbus service bulletin— Revision level— Date— Main action— Additional source of guidance (not incorporated by reference in this AD)— Lucas Aerospace Service Bulletin 47147– 27–04, Revision 1, dated June 20, 1997. Lucas Aerospace Service Bulletin 47147– 27–05, dated November 8, 1996. Lucas Aerospace Service Bulletin 47147– 27–07, dated May 4, 1998. None. A340-27-4054 ..... 01 November 26, 1997 ..... Replace hydraulic motors on the THSA with new parts. A340-27-4057 ..... ................ November 15, 1996 ..... A340-27-4059 ..... 03 December 5, 2001 ....... Replace mechanical input shaft for THSA with modified part. Replace THSA with a modified THSA ...... A340-55-4021 ..... 01 October 21, 1998 ......... (2) For the purposes of this AD, a general visual inspection is: A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked. tkelley on DSK3SPTVN1PROD with RULES (i) Retained Credit for Previous Actions (1) This paragraph provides credit for the requirements of paragraph (g)(1) of this AD, if those actions were performed before May 4, 2005 (the effective date of AD 2005–07–04, Amendment 39–14028 (70 FR 16104, March 30, 2005)), using Airbus Service Bulletin A330–27–3085 (for Model A330 series airplanes) or A340–27–4089 (for Model A340–313 series airplanes), both Revision 01, both dated January 23, 2002 (which are not incorporated by reference in this AD), as applicable. (2) This paragraph provides credit for the requirements of paragraphs (g)(2) of this AD, if those actions were performed before May 4, 2005 (the effective date of AD 2005–07–04, Amendment 39–14028 (70 FR 16104, March 30, 2005)), using Airbus Service Bulletin A330–27–3093 (for Model A330 series airplanes) or A340–27–4099 (for Model A340–200 and –300 series airplanes), both dated June 27, 2002 (which are not incorporated by reference in this AD), as applicable. (j) New Repetitive Greasing Procedure (1) Within 700 flight hours after the effective date of this AD, or within 700 flight hours after the date of the last lubrication, whichever occurs later; and thereafter at intervals not to exceed 700 flight hours from the last lubrication of the trimmable horizontal stabilizer (THS) actuator ball screw nut: Perform Task 27.40.00/02, Lubrication of THS Actuator Ball Screw Nut, in accordance with Airbus A330 Maintenance Review Board Report (MRBR), Revision 12, dated July 1, 2010 (for Model A330 series airplanes); or Airbus A340 VerDate Mar<15>2010 19:12 Aug 05, 2013 Jkt 229001 Perform a general visual inspection of the THSA screw jack fitting assembly for correct installation of a washer; and correctly install washer as applicable. MRBR, Revision 12, dated July 1, 2010 (for Model A340 series airplanes); on all THSAs. (2) For airplanes identified in paragraphs (j)(2)(i), (j)(2)(ii), and (j)(2)(iii) of this AD, as applicable, lubrication of the THS actuator ball screw nut performed at a threshold of 1,000 flight hours and a repetitive interval not exceeding 1,000 flight hours, in accordance with Task 274400–00002–1–E, Lubrication of the THSA Ball Nut, of Airbus A330 Airworthiness Limitations Section (ALS) Part 4—Ageing Systems Maintenance, Revision 03, dated September 9, 2011 (for Model A330 series airplanes); or 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, or Revision 03, dated November 15, 2012 (for Model A340–200 and –300 series airplanes); is acceptable for compliance with the requirements of paragraph (j)(1) of this AD. (i) Airplanes on which Airbus Modifications 52269, 56056, and 55780 have been done in production. (ii) Model A330 series airplanes on which the actions specified in Airbus Mandatory Service Bulletin A330–27–3137, dated March 20, 2007, or Revision 01, dated December 6, 2007, or Revision 02, dated January 18, 2010; and Airbus Mandatory Service Bulletin A330–92–3046, Revision 04, dated July 16, 2010, or Revision 05, dated November 7, 2011; which are not incorporated by reference in this AD; have been done in service. (iii) Model A340–200 and –300 series airplanes on which the actions specified in Airbus Mandatory Service Bulletin A340–27– 4136, dated March 20, 2007, Revision 01, dated December 6, 2007, or Revision 02, dated February 24, 2010; and Airbus Mandatory Service Bulletin A340–92–4056, Revision 03, dated July 16, 2010; which are not incorporated by reference in this AD; have been done in service. (k) New Repetitive Inspections of the Ball Screw Assembly and Corrective Actions For airplanes other than those identified in paragraphs (l)(1), (l)(2), and (l)(3) of this AD: Do the applicable actions specified in paragraphs (k)(1) and (k)(2) of this AD within 700 flight hours after the effective date of this AD, and repeat the inspection thereafter at intervals not to exceed 700 flight hours. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 (1) For airplanes on which the actions specified in Airbus Mandatory Service Bulletin A330–27–3137, dated March 20, 2007, Revision 01, dated December 6, 2007, or Revision 02, dated January 18, 2010 (for Model A330 series airplanes); or Airbus Mandatory Service Bulletin A340–27–4136, dated March 20, 2007, Revision 01, dated December 6, 2007, or Revision 02, dated February 24, 2010 (for Model A340–200 and –300 series airplanes); none of which are incorporated by reference in this AD; have been done: Do the applicable detailed inspection of the ball screw assembly for integrity of the primary and secondary load path and check the checkable shear pins (CSP), and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–27–3102, Revision 08, dated December 6, 2007 (for Model A330 series airplanes); or Airbus Mandatory Service Bulletin A340–27–4107, Revision 08, dated December 6, 2007 (for Model A340–200 and –300 series airplanes); except as required by paragraph (m) of this AD. Do all applicable corrective actions before further flight. (2) For airplanes on which the actions specified in Airbus Mandatory Service Bulletin A330–27–3137, dated March 20, 2007, Revision 01, dated December 6, 2007, or Revision 02, dated January 18, 2010 (for Model A330 series airplanes); or Airbus Mandatory Service Bulletin A340–27–4136, dated March 20, 2007, Revision 01, dated December 6, 2007, or Revision 02, dated February 24, 2010 (for Model A340–200 and –300 series airplanes); none of which are incorporated by reference in this AD; have not been done: Perform a detailed inspection of the ball screw assembly for integrity of the primary and secondary load path, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–27– 3102, Revision 08, dated December 6, 2007 (for Model A330 series airplanes); or Airbus Mandatory Service Bulletin A340–27–4107, Revision 08, dated December 6, 2007 (for Model A340 series airplanes); except as required by paragraph (m) of this AD. Do all applicable corrective actions before further flight. E:\FR\FM\06AUR1.SGM 06AUR1 47542 Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations (l) Certain Airplanes Excluded From Paragraphs (k) and (n) of This AD This paragraph specifies the airplanes excluded from the actions required by paragraphs (k) and (n) of this AD. (1) Airplanes on which the actions specified in Airbus Modifications 52269, 56056, and 55780 have been done in production. (2) Model A330 series airplanes on which Airbus Mandatory Service Bulletin A330–27– 3137, dated March 20, 2007, Revision 01, dated December 6, 2007, or Revision 02, dated January 18, 2010; and Airbus Mandatory Service Bulletin A330–92–3046, Revision 04, dated July 16, 2010, or Revision 05, dated November 7, 2011; none of which are incorporated by reference in this AD; have been done in service. (3) Model A340–200 and –300 series airplanes on which the actions specified in Airbus Mandatory Service Bulletin A340–27– 4136, dated March 20, 2007, Revision 01, dated December 6, 2007, or Revision 02, dated February 24, 2010; and Airbus Mandatory Service Bulletin A340–92–4056, Revision 03, dated July 16, 2010; have been done in service. (m) Service Information Exception Where Airbus Mandatory Service Bulletin A330–27–3102, Revision 08, dated December 6, 2007 (for Model A330 series airplanes); or Airbus Mandatory Service Bulletin A340–27– 4107, Revision 08, dated December 6, 2007 (for Model A340 series airplanes); specify contacting Airbus for a damage assessment, this AD requires contacting the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent); for required actions before further flight, and doing the specified actions within the times given. tkelley on DSK3SPTVN1PROD with RULES (n) New Actions for Electronic Centralized Aircraft Monitor (ECAM) Fault Messages For airplanes other than those identified in paragraphs (l)(1), (l)(2), and (l)(3) of this AD, if one of the ‘‘PRIM X PITCH FAULT’’ or ‘‘STAB CTL FAULT’’ messages is displayed on the ECAM associated with the ‘‘PITCH TRIM ACTR (1CS)’’ maintenance message, do the applicable detailed inspection and all applicable corrective actions specified in paragraph (k)(1) or (k)(2) of this AD, as applicable to airplane configuration, before further flight after the message is displayed on the ECAM. (o) New Optional Method of Compliance For airplanes having THSA P/N 47147– 500, 47147–700, 47172–300, 47172–500, or 47172–510, accomplishing the repetitive actions specified in paragraph (o)(1) or (o)(2) of this AD, as applicable, is acceptable for compliance with the corresponding actions specified in paragraph (k)(1) or (k)(2) of this AD, as applicable. (1) For Model A330 series airplanes: The repetitive actions specified in paragraphs (o)(1)(i) through (o)(1)(viii) of this AD. (i) Task 274400–00001–1–E of Airbus A330 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated December 16, 2009. (ii) Task 274400–00001–1–E of Airbus A330 ALS Part 4—Ageing Systems VerDate Mar<15>2010 17:14 Aug 05, 2013 Jkt 229001 Maintenance, Revision 03, dated September 9, 2011. (iii) Task 274400–00001–2–E of Airbus A330 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated December 16, 2009. (iv) Task 274400–00001–2–E of Airbus A330 ALS Part 4—Ageing Systems Maintenance, Revision 03, dated September 9, 2011. (v) Task 274400–00001–3–E of Airbus A330 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated December 16, 2009. (vi) Task 274400–00001–3–E of Airbus A330 ALS Part 4—Ageing Systems Maintenance, Revision 03, dated September 9, 2011. (vii) Task 274400–00001–4–E of Airbus A330 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated December 16, 2009. (viii) Task 274400–00001–4–E of Airbus A330 ALS Part 4—Ageing Systems Maintenance, Revision 03, dated September 9, 2011. (2) For Model A340–200 and –300 series airplanes: The repetitive actions specified in paragraphs (o)(2)(i) through (o)(2)(viii) of this AD. (i) Task 274400–00001–1–E of Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 15, 2009. (ii) Task 274400–00001–1–E of Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated October 12, 2011. (iii) Task 274400–00001–2–E of Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 15, 2009. (iv) Task 274400–00001–2–E of Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated October 12, 2011. (v) Task 274400–00001–3–E of Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 15, 2009. (vi) Task 274400–00001–3–E of Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated October 12, 2011. (vii) Task 274400–00001–4–E of Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 15, 2009. (viii) Task 274400–00001–4–E of Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated October 12, 2011. (p) New Credit for Previous Actions (1) For Model A300 series airplanes: This paragraph provides credit for the actions specified in paragraph (j) of this AD, if those actions were performed before the effective date of this AD using Task 27.40.00/02, Lubrication of THS Actuator Ball Screw Nut, of Airbus A330 MRBR, Revision 11, dated June 18, 2008 (which is not incorporated by reference in this AD). (2) For Model A340 series airplanes: This paragraph provides credit for the actions specified in paragraph (j) of this AD, if those actions were performed before the effective PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 date of this AD using Task 27.40.00/02, Lubrication of THS Actuator Ball Screw Nut, of Airbus A340 MRBR, Revision 11, dated June 18, 2008 (which is not incorporated by reference in this AD). (3) For Model A330 series airplanes: This paragraph provides credit for the inspections and corrective actions required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraphs (p)(3)(i) through (p)(3)(vi) of this AD (which are not incorporated by reference in this AD). (i) Airbus Service Bulletin A330–27–3102, Revision 02, dated November 7, 2002. (ii) Airbus Service Bulletin A330–27–3102, Revision 03, dated June 20, 2003. (iii) Airbus Service Bulletin A330–27– 3102, Revision 04, dated December 8, 2003. (iv) Airbus Mandatory Service Bulletin A330–27–3102, Revision 05, dated July 7, 2004. (v) Airbus Mandatory Service Bulletin A330–27–3102, Revision 06, dated December 16, 2005. (vi) Airbus Mandatory Service Bulletin A330–27–3102, Revision 07, dated March 16, 2007. (4) For Model A340 series airplanes: This paragraph provides credit for the inspections and corrective actions required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraphs (p)(4)(i) through (p)(4)(vi) of this AD (which are not incorporated by reference in this AD). (i) Airbus Mandatory Service Bulletin A340–27–4107, Revision 02, dated September 23, 2002. (ii) Airbus Service Bulletin A340–27–4107, Revision 03, dated December 4, 2002. (iii) Airbus Mandatory Service Bulletin A340–27–4107, Revision 04, dated June 20, 2003. (iv) Airbus Mandatory Service Bulletin A340–27–4107, Revision 05, dated December 8, 2003. (v) Airbus Mandatory Service Bulletin A340–27–4107, Revision 06, dated December 16, 2005. (vi) Airbus Mandatory Service Bulletin A340–27–4107, Revision 07, dated March 16, 2007. (q) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–1138; fax (425) 227– 1149. Information may be emailed to: 9- E:\FR\FM\06AUR1.SGM 06AUR1 Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations ANM-116-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. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. tkelley on DSK3SPTVN1PROD with RULES (r) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2010–0192 (corrected), dated October 11, 2010; and EASA Airworthiness Directive 2010–0193 (corrected), dated October 11, 2010; for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov. (2) Service information identified in this AD that is not incorporated by reference may be obtained at the addresses specified in paragraphs (s)(5), (s)(6), and (s)(7) of this AD. (s) 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 the AD specifies otherwise. (3) The following service information was approved for IBR on September 10, 2013. (i) Airbus Mandatory Service Bulletin A330–27–3102, Revision 08, dated December 6, 2007. (ii) Airbus Mandatory Service Bulletin A340–27–4107, Revision 08, dated December 6, 2007. (iii) Task 27.40.00/02, Lubrication of Trimmable Horizontal Stabilizer (THS) Actuator Ball Screw Nut, of Airbus A330 Maintenance Review Board Report (MRBR), Revision 12, dated July 1, 2010. (iv) Task 27.40.00/02, Lubrication of THS Actuator Ball Screw Nut, of Airbus A340 MRBR, Revision 12, dated July 1, 2010. (v) A330 Airworthiness Limitations Section (ALS) Part 4—Ageing Systems Maintenance, Revision 02, dated December 16, 2009. Only the title page and Record of Revision of this document contain the revision level; no other page of the document contains this information. The title page of this document does not contain an issue date. (vi) Airbus A330 ALS Part 4—Ageing Systems Maintenance, Revision 03, dated September 9, 2011. Only the title page and Record of Revision of this document contain the revision level; no other page of the document contains this information. The title page of this document does not contain an issue date. (vii) Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated VerDate Mar<15>2010 17:14 Aug 05, 2013 Jkt 229001 December 15, 2009. Only the title page and Record of Revision of this document contains the revision level; no other page of this document contains this information. The title page of this document does not contain an issue date. (viii) Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated October 12, 2011. Only the title page and Record of Revision of this document contain the revision level; no other page of the document contains this information. The title page of this document does not contain an issue date. (ix) Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 03, dated November 15, 2012. Only the title page and Record of Revision of this document contain the revision level; no other page of the document contains this information. The title page of this document does not contain an issue date. (4) The following service information was approved for IBR on May 4, 2005 (60 FR 16104, March 30, 2005). (i) Airbus Service Bulletin A330–27–3007, Revision 01, dated September 18, 1996. (ii) Airbus Service Bulletin A330–27–3015, dated June 7, 1995. (iii) Airbus Service Bulletin A330–27– 3047, Revision 01, dated November 26, 1997. (iv) Airbus Service Bulletin A330–27– 3050, dated November 15, 1996. (v) Airbus Service Bulletin A330–27–3052, Revision 03, dated December 5, 2001. (vi) Airbus Service Bulletin A330–27– 3085, Revision 02, dated September 5, 2002. (vii) Airbus Service Bulletin A330–27– 3093, Revision 01, dated September 5, 2002. (viii) Airbus Service Bulletin A330–55– 3020, Revision 01, dated October 21, 1998. (ix) Airbus Service Bulletin A340–27– 4007, dated April 7, 1994. (x) Airbus Service Bulletin A340–27–4025, dated June 7, 1995. (xi) Airbus Service Bulletin A340–27– 4054, Revision 01, dated November 26, 1997. (xii) Airbus Service Bulletin A340–27– 4057, dated November 15, 1996. (xiii) Airbus Service Bulletin A340–27– 4059, Revision 03, dated December 5, 2001. (xiv) Airbus Service Bulletin A340–27– 4089, Revision 02, dated September 5, 2002. (xv) Airbus Service Bulletin A340–27– 4099, Revision 01, dated September 5, 2002. (xvi) Airbus Service Bulletin A340–55– 4021, Revision 01, October 21, 1998. (5) For Airbus service information identified in this AD, contact Airbus SAS— Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330A340@airbus.com; Internet: http:// www.airbus.com. (6) For TRW Aeronautical Systems, SAMM Avionique, and Lucas Aerospace service information identified in this AD, contact Goodrich Corporation, Actuation Systems, Stafford Road, Fordhouses, Wolverhampton WV10 7EH, England; telephone +44 (0) 1902 624938; fax +44 (0) 1902 788100; email techpubs.wolverhampton@goodrich.com; Internet http://www.goodrich.com/TechPubs. (7) You may review copies of the service information at the FAA, Transport Airplane PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 47543 Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (8) 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. Issued in Renton, Washington, on June 21, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–18774 Filed 8–5–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0209; Directorate Identifier 2012–NM–127–AD; Amendment 39–17514; AD 2013–14–09] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding airworthiness directive (AD) 2012–14– 04 for certain Bombardier, Inc. Model DHC–8–100, –200, and –300 series airplanes. AD 2012–14–04 required replacing certain parking brake accumulators. This new AD retains this requirement. This new AD also requires installing restraint devices around the parking brake accumulator end caps. We are issuing this AD to prevent failure of a parking brake accumulator screw cap or end cap resulting in loss of the number 2 hydraulic system and damage to airplane structures, which could adversely affect the controllability of the airplane. DATES: This AD becomes effective September 10, 2013. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 10, 2013. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of August 27, 2012 (77 FR 42956, July 23, 2012). ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the SUMMARY: E:\FR\FM\06AUR1.SGM 06AUR1

Agencies

[Federal Register Volume 78, Number 151 (Tuesday, August 6, 2013)]
[Rules and Regulations]
[Pages 47537-47543]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-18774]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1033; Directorate Identifier 2010-NM-266-AD; 
Amendment 39-17504; AD 2013-13-16]
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) 2005-07-04 for 
all Airbus Model A330-200 and -300 series airplanes, and Model A340-200 
and -300 series airplanes. AD 2005-07-04 required repetitive 
inspections to detect discrepancies of the transfer tubes and the 
collar of the ball nut of the trimmable horizontal stabilizer actuator 
(THSA), and corrective action if necessary; repetitive inspections for 
discrepancies of the ball screw assembly, and corrective action if 
necessary; 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 removes certain inspections, revises certain actions, and 
adds airplanes to the applicability. This AD was prompted by several 
reports of

[[Page 47538]]

disconnection of the transfer tube from the ball nut of the THSA. We 
are issuing this AD to prevent degraded operation of the THSA, which 
could result in reduced controllability of the airplane.

DATES: This AD becomes effective September 10, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 10, 
2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of May 4, 
2005 (70 FR 16104, March 30, 2005).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.

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 include an AD that would apply to the specified products. 
The NPRM was published in the Federal Register on October 2, 2012 (77 
FR 60075), and proposed to supersede AD 2005-07-04, Amendment 39-14028 
(70 FR 16104, March 30, 2005). (AD 2005-07-04 superseded AD 2001-11-09, 
Amendment 39-12252 (66 FR 31143, June 11, 2001).) The NPRM proposed to 
correct an unsafe condition for the specified products. The European 
Aviation Safety Agency (EASA), which is the Technical Agent for the 
Member States of the European Community, has issued EASA Airworthiness 
Directive 2010-0192 (corrected), dated October 11, 2010; and EASA 
Airworthiness Directive 2010-0193 (corrected), dated October 11, 2010; 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for the 
specified products. 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.
    This condition is caused by water ingress into the ball-nut 
resulting in the jamming of the ball transfer circuit when the water 
freezes.
    If the three (independent) ball circuits fail, then the THSA 
will operate on a fail-safe nut. This nut (which operates without 
balls) would then jam after several movements on the screw of the 
THSA.
    This degraded operation is not detectable in the cockpit by the 
crew as long as the THSA does not jam and could damage the ball 
screw and the fail-safe nut.
    To detect this unsafe condition, [Direcci[oacute]n General de 
Aviaci[oacute]n Civil] DGAC France AD F-2001-356 [and F-2001-357] 
was issued to require repetitive inspections of the transfer tubes 
and their collars in order to detect at an early stage any 
distortion or initiation of disconnection.
    Further to a new case of transfer tube disconnection, * * * 
[revised DGAC ADs] required an additional repetitive greasing task 
with reinforcement of the ball-nut maintenance greasing 
instructions.
    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 ECAM [electronic centralized aircraft monitor]. In this case a 
mandatory inspection of the THSA is required before the next flight.
    DGAC France AD F-2002-038 [and F-2002-037] required application 
of a final fix (related to inspection and greasing task required by 
DGAC France AD F-2001-356 [and F-2001-357]) for the THSA P/N 47172 
by application of Airbus modification 49590/Service Bulletin (SB) 
A330-27-3085 [or SB A340-27-4089]. It changes the THSA P/N from 
47172 to 47172-300.
    Later on, DGAC France AD F-2002-414R3 replaced the DGAC AD 
France F-2001-356R2 and F-2002-038 [and DGAC France AD F2002-415R2 
superseded DGAC France ADs F-2001-357R2 and F-2002-037] requiring:

--the repetitive [detailed] inspection [for discrepancies] of all 
THSA P/N in service [for integrity of the primary and secondary load 
path and check the Checkable Shear Pins (CSPs)], and
--the lubrication of some THSA P/N, and
--the replacement of THSA P/N 47172, 47147-400 and 47147-2XX/-3XX

[DGAC France AD F-2002-414R3 and F-2002-415R2 correspond to FAA AD 
2005-07-04, Amendment 39-14028 (70 FR 16104, March 30, 2005).]

    Airbus has later introduced 4 new THSA P/N (47172-500, 47172-
510, 47172-520 and 47172-530).
    This [EASA] AD retains the requirements of DGAC France AD F-
2002-414R3 [and F-2002-415R2], which is superseded, and requires 
repetitive inspections and lubrications of the new THSA P/N.
    The repetitive inspection and lubrication requirements for THSA 
P/N 47172-520 and 47172-530 shall [also] be included in the next 
Airworthiness Limitation Section (ALS) Part 4 revision.
* * * * *
    Corrective actions include replacing the THSA with a new THSA if 
cracks, dents, or corrosion are found, or if the feeler gage has failed 
at any of the four gaps. Other corrective action includes using a 
method approved by the FAA or the EASA (or its delegated agent) for a 
finding of metallic debris, loose nut, damaged or missing lock washers, 
pins and parts, or incorrect installation of items. AD 2005-07-04, 
Amendment 39-14028 (70 FR 16104, March 30, 2005), required repetitive 
inspections for discrepancies. This AD requires, for certain airplanes, 
repetitive inspections for the integrity of the primary and secondary 
load path, and the CSPs. The unsafe condition is the degraded operation 
of the THSA, which could result in reduced controllability of the 
airplane. You may obtain further information by examining the MCAI in 
the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Request To Use Later Document Revision

    Delta Airlines (Delta) requested that paragraph (j)(2) of the NPRM 
(77 FR 60075, October 2, 2012) refer to Airbus A330 Airworthiness 
Limitations Section (ALS) Part 4--Ageing Systems Maintenance, Revision 
03, dated September 9, 2011; instead of Revision 02, dated December 16, 
2009. Delta stated that Revision 03 of that ALS specifies the 1,000 
flight-hour lubrication threshold and repetitive interval that are 
specified in paragraph (j)(2) of the NPRM, whereas Revision 02 of this 
ALS specifies 700 flight hours for the lubrication threshold and 
repetitive interval.
    We agree that Airbus A330 Airworthiness Limitations Section (ALS) 
Part 4--Ageing Systems Maintenance, Revision 03, dated September 9, 
2011, correctly specifies the lubrication threshold and repetitive 
interval. We have changed paragraph (j)(2) of this AD accordingly. In 
addition, we have changed paragraph (j)(2) of this AD to reference 
Airbus A340 ALS Part 4--Ageing Systems Maintenance, Revision 02, dated 
October 12, 2011; and Revision 03, dated November 15, 2012; for the 
same reason.

Request To Change Wording

    Delta requested that we change the wording in paragraph (l) of the 
NPRM (77 FR 60075, October 2, 2012), which states ``For airplanes 
identified in paragraph (k) of this AD.'' The commenter asked that the 
wording ``identified in'' be replaced with

[[Page 47539]]

``affected by.'' The commenter provided no reason for the change.
    We disagree to change the wording in paragraph (n) in this AD 
(identified as paragraph (l) in the NPRM (77 FR 60075, October 2, 
2012)) as requested by the commenter. However, we have moved the 
content of paragraphs (k)(1), (k)(2), and (k)(3) of the NPRM to new 
paragraph (l) in this AD to clarify the actions and affected airplanes. 
We have also moved the content of paragraph (k)(6) of the NPRM to new 
paragraph (m) of this AD, and re-identified succeeding paragraphs 
accordingly. Finally, in paragraph (n) of this AD, we revised the 
wording to describe the affected airplanes.

Request To Include Additional Part Number

    Delta requested that we include THSA P/N 47172-520 and P/N ``47127-
530'' in paragraph (m) of the NPRM (77 FR 60075, October 2, 2012) as 
applicable part numbers for Model A330 series airplanes.
    We disagree to include THSA P/N 47127-530 as there is no such part 
number. We infer that the commenter meant to specify THSA P/N 47172-
530. THSA P/N 47172-520 and P/N 47172-530 are not included in the MCAI. 
However, all necessary tasks for those THSA part numbers are contained 
in Airbus A330 Airworthiness Limitations Section (ALS) Part 4--Ageing 
Systems Maintenance, Revision 03, dated September 9, 2011; and Airbus 
A340 ALS Part 4--Ageing Systems Maintenance, Revision 02, dated October 
12, 2011, and Revision 03, dated November 15, 2012. The FAA NPRMs to 
mandate these ALS Part 4 documents are pending at this time. Therefore, 
we have not changed this AD in this regard.

Request To Consider Another EASA AD

    Corinne Dayde stated that she ``Cannot see how EASA 2012-0061 is 
considered.''
    We are considering addressing EASA AD 2012-0061R1, dated November 
30, 2012, in a separate FAA AD. We have not changed this AD in this 
regard.

Conclusion

    We reviewed the available data, including the comments received, 
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 changes:
     Are consistent with the intent that was proposed in the 
NPRM (77 FR 60075, October 2, 2012) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 60075, October 2, 2012).

Costs of Compliance

    We estimate that this AD will affect about 33 products of U.S. 
registry.
    The actions that are required by AD 2005-07-04, Amendment 39-14028 
(70 FR 16104, March 30, 2005), and retained in this AD take up to 36 
work-hours per product, at an average labor rate of $85 per work-hour. 
Based on these figures, the estimated cost of the retained actions is 
up to $3,060 per product.
    We estimate that it will take about 2 work-hours per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $5,610, or $170 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
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 Operations office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

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) 
2005-07-04, Amendment 39-14028 (70 FR 16104, March 30, 2005), and 
adding the following new AD:

2013-13-16 Airbus: Amendment 39-17504. Docket No. FAA-2012-1033; 
Directorate Identifier 2010-NM-266-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective September 
10, 2013.

(b) Affected ADs

    This AD supersedes AD 2005-07-04, Amendment 39-14028 (70 FR 
16104, March 30, 2005).

(c) Applicability

    This AD applies to all Airbus Model A330-201, -202, -203, -223, 
-223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes; and Model A340-

[[Page 47540]]

211, -212, -213, -311, -312, and -313 airplanes; certificated in any 
category.

(d) Subject

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

(e) Reason

    This AD was prompted by several reports of disconnection of the 
transfer tube from the ball nut of the trimmable horizontal 
stabilizer actuator (THSA). We are issuing this AD to prevent 
degraded operation of the THSA, which could result in reduced 
controllability of the airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Retained Modification or Replacement

    This paragraph restates the requirements of paragraph (g) of AD 
2005-07-04, Amendment 39-14028 (70 FR 16104, March 30, 2005). Except 
for Model A330-223F and -243F airplanes: Within 24 months after May 
4, 2005 (the effective date of AD 2005-07-04), modify the ball nut 
of each THSA by doing paragraph (g)(1) or (g)(2) of this AD, as 
applicable.
    (1) For THSAs having part number (P/N) 47172: Modify the ball 
nut of the THSA, or replace the existing THSA with a serviceable 
part having P/N 47172-300; in accordance with Airbus Service 
Bulletin A330-27-3085 (for Model A330 series airplanes) or A340-27-
4089 (for Model A340-313 series airplanes), both Revision 02, both 
dated September 5, 2002; as applicable.

    Note 1 to paragraph (g)(1) of this AD: Airbus Service Bulletins 
A330-27-3085 and A340-27-4089, both Revision 02, both dated 
September 5, 2002, refer to TRW Aeronautical Systems Service 
Bulletin 47172-27-03, dated October 24, 2001 (which is not 
incorporated by reference in this AD), as additional guidance for 
accomplishing the modification of the ball nut of the THSA.

    (2) For THSAs having P/N 47147-200, -210, -213, -300, -303, -
350, or -400: Modify the ball nut of the THSA, or replace the 
existing THSA with an improved part having P/N 47147-500; as 
applicable; in accordance with Airbus Service Bulletin A330-27-3093 
(for Model A330 series airplanes) or A340-27-4099 (for Model A340-
200 and -300 series airplanes), both Revision 01, both dated 
September 5, 2002; as applicable.

    Note 2 to paragraph (g)(2) of this AD: Airbus Service Bulletins 
A330-27-3093 and A340-27-4099, both Revision 01, both dated 
September 5, 2002, refer to TRW Aeronautical Systems Service 
Bulletin 47147-27-10, dated June 27, 2002 (which is not incorporated 
by reference in this AD), as additional guidance for accomplishing 
the modification of the ball nut of the THSA.

(h) Retained Previous/Concurrent Requirements

    This paragraph restates the requirements of paragraph (h) of AD 
2005-07-04, Amendment 39-14028 (70 FR 16104, March 30, 2005).
    (1) Except for Model A330-223F and -243F airplanes, prior to or 
concurrently with accomplishing the requirements of paragraph (g)(2) 
of this AD, do all of the actions specified in the Accomplishment 
Instructions of the applicable Airbus service bulletins listed in 
table 1 or 2 to paragraph (h)(1) of this AD, as applicable, in 
accordance with those service bulletins.

    Note 3 to paragraph (h)(1) of this AD: Airbus Service Bulletin 
A330-27-3093, Revision 01, dated September 5, 2002, specifies that 
the actions in Airbus Service Bulletin A330-27-3052 be accomplished 
previously or concurrently. Airbus Service Bulletin A330-27-3052, 
Revision 03, dated December 5, 2001, specifies that the actions in 
Airbus Service Bulletins A330-27-3007, A330-27-3015, A330-27-3047, 
A330-27-3050, and A330-55-3020 be accomplished previously or 
concurrently.


    Note 4 to paragraph (h)(1) of this AD:  Airbus Service Bulletin 
A340-27-4099, Revision 01, dated September 5, 2002, specifies that 
the actions in Airbus Service Bulletin A340-27-4059 be accomplished 
previously or concurrently. Airbus Service Bulletin A340-27-4059, 
Revision 03, dated December 5, 2001, specifies that the actions in 
Airbus Service Bulletins A340-27-4007, A340-27-4025, A340-27-4054, 
A340-27-4057, and A340-55-4021 be accomplished previously or 
concurrently.


                    Table 1 to Paragraph (h)(1) of This AD--Retained Previous/Concurrent Requirements for Model A330 Series Airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                      Additional source of guidance (not
   Airbus service bulletin--     Revision                  Date--                            Main action--             incorporated by reference in this
                                 level--                                                                                             AD)--
--------------------------------------------------------------------------------------------------------------------------------------------------------
A330[dash]27[dash]3007........         01  September 18, 1996...................  Replace rudder servo controls with  Samm Avionique Service Bulletin
                                                                                   modified parts.                     SC5300-27-24-01, dated April 15,
                                                                                                                       1994.
A330[dash]27[dash]3015........  .........  June 7, 1995.........................  Modify the control valve detent     Lucas Aerospace Service Bulletin
                                                                                   and the jamming protection device   47147-27-02, Revision 1, dated
                                                                                   on the THSA.                        January 31, 1996.
A330[dash]27[dash]3047........         01  November 26, 1997....................  Replace hydraulic motors on the     Lucas Aerospace Service Bulletin
                                                                                   THSA with new parts.                47147-27-04, Revision 1, dated
                                                                                                                       June 20, 1997.
A330[dash]27[dash]3050........  .........  November 15, 1996....................  Replace mechanical input shaft for  Lucas Aerospace Service Bulletin
                                                                                   THSA with modified part.            47147-27-05, dated November 8,
                                                                                                                       1996.
A330[dash]27[dash]3052........         03  December 5, 2001.....................  Replace THSA with a modified THSA.  Lucas Aerospace Service Bulletin
                                                                                                                       47147-27-07, dated May 4, 1998.
A330[dash]55[dash]3020........         01  October 21, 1998.....................  Perform a general visual            None.
                                                                                   inspection of the THSA screw jack
                                                                                   fitting assembly for correct
                                                                                   installation of a washer; and
                                                                                   correctly install washer as
                                                                                   applicable.
--------------------------------------------------------------------------------------------------------------------------------------------------------


                    Table 2 to Paragraph (h)(1) of This AD--Retained Previous/Concurrent Requirements for Model A340 Series Airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                      Additional source of guidance (not
   Airbus service bulletin--     Revision                  Date--                            Main action--             incorporated by reference in this
                                 level--                                                                                             AD)--
--------------------------------------------------------------------------------------------------------------------------------------------------------
A340[dash]27[dash]4007........  .........  April 7, 1994........................  Replace hydraulic motors on the     Lucas Aerospace Service Bulletin
                                                                                   THSA with new parts.                47147-27-01, dated May 4, 1998.
A340[dash]27[dash]4025........  .........  June 7, 1995.........................  Modify the control valve detent     Lucas Aerospace Service Bulletin
                                                                                   and the jamming protection device   47147-27-02, Revision 1, dated
                                                                                   on the THSA.                        January 31, 1996.

[[Page 47541]]

 
A340[dash]27[dash]4054........         01  November 26, 1997....................  Replace hydraulic motors on the     Lucas Aerospace Service Bulletin
                                                                                   THSA with new parts.                47147-27-04, Revision 1, dated
                                                                                                                       June 20, 1997.
A340[dash]27[dash]4057........  .........  November 15, 1996....................  Replace mechanical input shaft for  Lucas Aerospace Service Bulletin
                                                                                   THSA with modified part.            47147-27-05, dated November 8,
                                                                                                                       1996.
A340[dash]27[dash]4059........         03  December 5, 2001.....................  Replace THSA with a modified THSA.  Lucas Aerospace Service Bulletin
                                                                                                                       47147-27-07, dated May 4, 1998.
A340[dash]55[dash]4021........         01  October 21, 1998.....................  Perform a general visual            None.
                                                                                   inspection of the THSA screw jack
                                                                                   fitting assembly for correct
                                                                                   installation of a washer; and
                                                                                   correctly install washer as
                                                                                   applicable.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    (2) For the purposes of this AD, a general visual inspection is: 
A visual examination of an interior or exterior area, installation, 
or assembly to detect obvious damage, failure, or irregularity. This 
level of inspection is made from within touching distance unless 
otherwise specified. A mirror may be necessary to ensure visual 
access to all surfaces in the inspection area. This level of 
inspection is made under normally available lighting conditions such 
as daylight, hangar lighting, flashlight, or droplight and may 
require removal or opening of access panels or doors. Stands, 
ladders, or platforms may be required to gain proximity to the area 
being checked.

(i) Retained Credit for Previous Actions

    (1) This paragraph provides credit for the requirements of 
paragraph (g)(1) of this AD, if those actions were performed before 
May 4, 2005 (the effective date of AD 2005-07-04, Amendment 39-14028 
(70 FR 16104, March 30, 2005)), using Airbus Service Bulletin A330-
27-3085 (for Model A330 series airplanes) or A340-27-4089 (for Model 
A340-313 series airplanes), both Revision 01, both dated January 23, 
2002 (which are not incorporated by reference in this AD), as 
applicable.
    (2) This paragraph provides credit for the requirements of 
paragraphs (g)(2) of this AD, if those actions were performed before 
May 4, 2005 (the effective date of AD 2005-07-04, Amendment 39-14028 
(70 FR 16104, March 30, 2005)), using Airbus Service Bulletin A330-
27-3093 (for Model A330 series airplanes) or A340-27-4099 (for Model 
A340-200 and -300 series airplanes), both dated June 27, 2002 (which 
are not incorporated by reference in this AD), as applicable.

(j) New Repetitive Greasing Procedure

    (1) Within 700 flight hours after the effective date of this AD, 
or within 700 flight hours after the date of the last lubrication, 
whichever occurs later; and thereafter at intervals not to exceed 
700 flight hours from the last lubrication of the trimmable 
horizontal stabilizer (THS) actuator ball screw nut: Perform Task 
27.40.00/02, Lubrication of THS Actuator Ball Screw Nut, in 
accordance with Airbus A330 Maintenance Review Board Report (MRBR), 
Revision 12, dated July 1, 2010 (for Model A330 series airplanes); 
or Airbus A340 MRBR, Revision 12, dated July 1, 2010 (for Model A340 
series airplanes); on all THSAs.
    (2) For airplanes identified in paragraphs (j)(2)(i), 
(j)(2)(ii), and (j)(2)(iii) of this AD, as applicable, lubrication 
of the THS actuator ball screw nut performed at a threshold of 1,000 
flight hours and a repetitive interval not exceeding 1,000 flight 
hours, in accordance with Task 274400-00002-1-E, Lubrication of the 
THSA Ball Nut, of Airbus A330 Airworthiness Limitations Section 
(ALS) Part 4--Ageing Systems Maintenance, Revision 03, dated 
September 9, 2011 (for Model A330 series airplanes); or 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, 
or Revision 03, dated November 15, 2012 (for Model A340-200 and -300 
series airplanes); is acceptable for compliance with the 
requirements of paragraph (j)(1) of this AD.
    (i) Airplanes on which Airbus Modifications 52269, 56056, and 
55780 have been done in production.
    (ii) Model A330 series airplanes on which the actions specified 
in Airbus Mandatory Service Bulletin A330-27-3137, dated March 20, 
2007, or Revision 01, dated December 6, 2007, or Revision 02, dated 
January 18, 2010; and Airbus Mandatory Service Bulletin A330-92-
3046, Revision 04, dated July 16, 2010, or Revision 05, dated 
November 7, 2011; which are not incorporated by reference in this 
AD; have been done in service.
    (iii) Model A340-200 and -300 series airplanes on which the 
actions specified in Airbus Mandatory Service Bulletin A340-27-4136, 
dated March 20, 2007, Revision 01, dated December 6, 2007, or 
Revision 02, dated February 24, 2010; and Airbus Mandatory Service 
Bulletin A340-92-4056, Revision 03, dated July 16, 2010; which are 
not incorporated by reference in this AD; have been done in service.

(k) New Repetitive Inspections of the Ball Screw Assembly and 
Corrective Actions

    For airplanes other than those identified in paragraphs (l)(1), 
(l)(2), and (l)(3) of this AD: Do the applicable actions specified 
in paragraphs (k)(1) and (k)(2) of this AD within 700 flight hours 
after the effective date of this AD, and repeat the inspection 
thereafter at intervals not to exceed 700 flight hours.
    (1) For airplanes on which the actions specified in Airbus 
Mandatory Service Bulletin A330-27-3137, dated March 20, 2007, 
Revision 01, dated December 6, 2007, or Revision 02, dated January 
18, 2010 (for Model A330 series airplanes); or Airbus Mandatory 
Service Bulletin A340-27-4136, dated March 20, 2007, Revision 01, 
dated December 6, 2007, or Revision 02, dated February 24, 2010 (for 
Model A340-200 and -300 series airplanes); none of which are 
incorporated by reference in this AD; have been done: Do the 
applicable detailed inspection of the ball screw assembly for 
integrity of the primary and secondary load path and check the 
checkable shear pins (CSP), and do all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A330-27-3102, Revision 08, dated 
December 6, 2007 (for Model A330 series airplanes); or Airbus 
Mandatory Service Bulletin A340-27-4107, Revision 08, dated December 
6, 2007 (for Model A340-200 and -300 series airplanes); except as 
required by paragraph (m) of this AD. Do all applicable corrective 
actions before further flight.
    (2) For airplanes on which the actions specified in Airbus 
Mandatory Service Bulletin A330-27-3137, dated March 20, 2007, 
Revision 01, dated December 6, 2007, or Revision 02, dated January 
18, 2010 (for Model A330 series airplanes); or Airbus Mandatory 
Service Bulletin A340-27-4136, dated March 20, 2007, Revision 01, 
dated December 6, 2007, or Revision 02, dated February 24, 2010 (for 
Model A340-200 and -300 series airplanes); none of which are 
incorporated by reference in this AD; have not been done: Perform a 
detailed inspection of the ball screw assembly for integrity of the 
primary and secondary load path, and do all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A330-27-3102, Revision 08, dated 
December 6, 2007 (for Model A330 series airplanes); or Airbus 
Mandatory Service Bulletin A340-27-4107, Revision 08, dated December 
6, 2007 (for Model A340 series airplanes); except as required by 
paragraph (m) of this AD. Do all applicable corrective actions 
before further flight.

[[Page 47542]]

(l) Certain Airplanes Excluded From Paragraphs (k) and (n) of This AD

    This paragraph specifies the airplanes excluded from the actions 
required by paragraphs (k) and (n) of this AD.
    (1) Airplanes on which the actions specified in Airbus 
Modifications 52269, 56056, and 55780 have been done in production.
    (2) Model A330 series airplanes on which Airbus Mandatory 
Service Bulletin A330-27-3137, dated March 20, 2007, Revision 01, 
dated December 6, 2007, or Revision 02, dated January 18, 2010; and 
Airbus Mandatory Service Bulletin A330-92-3046, Revision 04, dated 
July 16, 2010, or Revision 05, dated November 7, 2011; none of which 
are incorporated by reference in this AD; have been done in service.
    (3) Model A340-200 and -300 series airplanes on which the 
actions specified in Airbus Mandatory Service Bulletin A340-27-4136, 
dated March 20, 2007, Revision 01, dated December 6, 2007, or 
Revision 02, dated February 24, 2010; and Airbus Mandatory Service 
Bulletin A340-92-4056, Revision 03, dated July 16, 2010; have been 
done in service.

(m) Service Information Exception

    Where Airbus Mandatory Service Bulletin A330-27-3102, Revision 
08, dated December 6, 2007 (for Model A330 series airplanes); or 
Airbus Mandatory Service Bulletin A340-27-4107, Revision 08, dated 
December 6, 2007 (for Model A340 series airplanes); specify 
contacting Airbus for a damage assessment, this AD requires 
contacting the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA) (or its delegated agent); for required actions before further 
flight, and doing the specified actions within the times given.

(n) New Actions for Electronic Centralized Aircraft Monitor (ECAM) 
Fault Messages

    For airplanes other than those identified in paragraphs (l)(1), 
(l)(2), and (l)(3) of this AD, if one of the ``PRIM X PITCH FAULT'' 
or ``STAB CTL FAULT'' messages is displayed on the ECAM associated 
with the ``PITCH TRIM ACTR (1CS)'' maintenance message, do the 
applicable detailed inspection and all applicable corrective actions 
specified in paragraph (k)(1) or (k)(2) of this AD, as applicable to 
airplane configuration, before further flight after the message is 
displayed on the ECAM.

(o) New Optional Method of Compliance

    For airplanes having THSA P/N 47147-500, 47147-700, 47172-300, 
47172-500, or 47172-510, accomplishing the repetitive actions 
specified in paragraph (o)(1) or (o)(2) of this AD, as applicable, 
is acceptable for compliance with the corresponding actions 
specified in paragraph (k)(1) or (k)(2) of this AD, as applicable.
    (1) For Model A330 series airplanes: The repetitive actions 
specified in paragraphs (o)(1)(i) through (o)(1)(viii) of this AD.
    (i) Task 274400-00001-1-E of Airbus A330 ALS Part 4--Ageing 
Systems Maintenance, Revision 02, dated December 16, 2009.
    (ii) Task 274400-00001-1-E of Airbus A330 ALS Part 4--Ageing 
Systems Maintenance, Revision 03, dated September 9, 2011.
    (iii) Task 274400-00001-2-E of Airbus A330 ALS Part 4--Ageing 
Systems Maintenance, Revision 02, dated December 16, 2009.
    (iv) Task 274400-00001-2-E of Airbus A330 ALS Part 4--Ageing 
Systems Maintenance, Revision 03, dated September 9, 2011.
    (v) Task 274400-00001-3-E of Airbus A330 ALS Part 4--Ageing 
Systems Maintenance, Revision 02, dated December 16, 2009.
    (vi) Task 274400-00001-3-E of Airbus A330 ALS Part 4--Ageing 
Systems Maintenance, Revision 03, dated September 9, 2011.
    (vii) Task 274400-00001-4-E of Airbus A330 ALS Part 4--Ageing 
Systems Maintenance, Revision 02, dated December 16, 2009.
    (viii) Task 274400-00001-4-E of Airbus A330 ALS Part 4--Ageing 
Systems Maintenance, Revision 03, dated September 9, 2011.
    (2) For Model A340-200 and -300 series airplanes: The repetitive 
actions specified in paragraphs (o)(2)(i) through (o)(2)(viii) of 
this AD.
    (i) Task 274400-00001-1-E of Airbus A340 ALS Part 4--Ageing 
Systems Maintenance, Revision 01, dated December 15, 2009.
    (ii) Task 274400-00001-1-E of Airbus A340 ALS Part 4--Ageing 
Systems Maintenance, Revision 02, dated October 12, 2011.
    (iii) Task 274400-00001-2-E of Airbus A340 ALS Part 4--Ageing 
Systems Maintenance, Revision 01, dated December 15, 2009.
    (iv) Task 274400-00001-2-E of Airbus A340 ALS Part 4--Ageing 
Systems Maintenance, Revision 02, dated October 12, 2011.
    (v) Task 274400-00001-3-E of Airbus A340 ALS Part 4--Ageing 
Systems Maintenance, Revision 01, dated December 15, 2009.
    (vi) Task 274400-00001-3-E of Airbus A340 ALS Part 4--Ageing 
Systems Maintenance, Revision 02, dated October 12, 2011.
    (vii) Task 274400-00001-4-E of Airbus A340 ALS Part 4--Ageing 
Systems Maintenance, Revision 01, dated December 15, 2009.
    (viii) Task 274400-00001-4-E of Airbus A340 ALS Part 4--Ageing 
Systems Maintenance, Revision 02, dated October 12, 2011.

(p) New Credit for Previous Actions

    (1) For Model A300 series airplanes: This paragraph provides 
credit for the actions specified in paragraph (j) of this AD, if 
those actions were performed before the effective date of this AD 
using Task 27.40.00/02, Lubrication of THS Actuator Ball Screw Nut, 
of Airbus A330 MRBR, Revision 11, dated June 18, 2008 (which is not 
incorporated by reference in this AD).
    (2) For Model A340 series airplanes: This paragraph provides 
credit for the actions specified in paragraph (j) of this AD, if 
those actions were performed before the effective date of this AD 
using Task 27.40.00/02, Lubrication of THS Actuator Ball Screw Nut, 
of Airbus A340 MRBR, Revision 11, dated June 18, 2008 (which is not 
incorporated by reference in this AD).
    (3) For Model A330 series airplanes: This paragraph provides 
credit for the inspections and corrective actions required by 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using the service information specified in 
paragraphs (p)(3)(i) through (p)(3)(vi) of this AD (which are not 
incorporated by reference in this AD).
    (i) Airbus Service Bulletin A330-27-3102, Revision 02, dated 
November 7, 2002.
    (ii) Airbus Service Bulletin A330-27-3102, Revision 03, dated 
June 20, 2003.
    (iii) Airbus Service Bulletin A330-27-3102, Revision 04, dated 
December 8, 2003.
    (iv) Airbus Mandatory Service Bulletin A330-27-3102, Revision 
05, dated July 7, 2004.
    (v) Airbus Mandatory Service Bulletin A330-27-3102, Revision 06, 
dated December 16, 2005.
    (vi) Airbus Mandatory Service Bulletin A330-27-3102, Revision 
07, dated March 16, 2007.
    (4) For Model A340 series airplanes: This paragraph provides 
credit for the inspections and corrective actions required by 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using the service information specified in 
paragraphs (p)(4)(i) through (p)(4)(vi) of this AD (which are not 
incorporated by reference in this AD).
    (i) Airbus Mandatory Service Bulletin A340-27-4107, Revision 02, 
dated September 23, 2002.
    (ii) Airbus Service Bulletin A340-27-4107, Revision 03, dated 
December 4, 2002.
    (iii) Airbus Mandatory Service Bulletin A340-27-4107, Revision 
04, dated June 20, 2003.
    (iv) Airbus Mandatory Service Bulletin A340-27-4107, Revision 
05, dated December 8, 2003.
    (v) Airbus Mandatory Service Bulletin A340-27-4107, Revision 06, 
dated December 16, 2005.
    (vi) Airbus Mandatory Service Bulletin A340-27-4107, Revision 
07, dated March 16, 2007.

(q) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Information may be emailed to: 9-

[[Page 47543]]

ANM-116-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. The AMOC approval letter 
must specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(r) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2010-0192 (corrected), dated 
October 11, 2010; and EASA Airworthiness Directive 2010-0193 
(corrected), dated October 11, 2010; for related information. This 
MCAI may be found in the AD docket on the Internet at http://www.regulations.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference may be obtained at the addresses specified 
in paragraphs (s)(5), (s)(6), and (s)(7) of this AD.

(s) 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 the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
September 10, 2013.
    (i) Airbus Mandatory Service Bulletin A330-27-3102, Revision 08, 
dated December 6, 2007.
    (ii) Airbus Mandatory Service Bulletin A340-27-4107, Revision 
08, dated December 6, 2007.
    (iii) Task 27.40.00/02, Lubrication of Trimmable Horizontal 
Stabilizer (THS) Actuator Ball Screw Nut, of Airbus A330 Maintenance 
Review Board Report (MRBR), Revision 12, dated July 1, 2010.
    (iv) Task 27.40.00/02, Lubrication of THS Actuator Ball Screw 
Nut, of Airbus A340 MRBR, Revision 12, dated July 1, 2010.
    (v) A330 Airworthiness Limitations Section (ALS) Part 4--Ageing 
Systems Maintenance, Revision 02, dated December 16, 2009. Only the 
title page and Record of Revision of this document contain the 
revision level; no other page of the document contains this 
information. The title page of this document does not contain an 
issue date.
    (vi) Airbus A330 ALS Part 4--Ageing Systems Maintenance, 
Revision 03, dated September 9, 2011. Only the title page and Record 
of Revision of this document contain the revision level; no other 
page of the document contains this information. The title page of 
this document does not contain an issue date.
    (vii) Airbus A340 ALS Part 4--Ageing Systems Maintenance, 
Revision 01, dated December 15, 2009. Only the title page and Record 
of Revision of this document contains the revision level; no other 
page of this document contains this information. The title page of 
this document does not contain an issue date.
    (viii) Airbus A340 ALS Part 4--Ageing Systems Maintenance, 
Revision 02, dated October 12, 2011. Only the title page and Record 
of Revision of this document contain the revision level; no other 
page of the document contains this information. The title page of 
this document does not contain an issue date.
    (ix) Airbus A340 ALS Part 4--Ageing Systems Maintenance, 
Revision 03, dated November 15, 2012. Only the title page and Record 
of Revision of this document contain the revision level; no other 
page of the document contains this information. The title page of 
this document does not contain an issue date.
    (4) The following service information was approved for IBR on 
May 4, 2005 (60 FR 16104, March 30, 2005).
    (i) Airbus Service Bulletin A330-27-3007, Revision 01, dated 
September 18, 1996.
    (ii) Airbus Service Bulletin A330-27-3015, dated June 7, 1995.
    (iii) Airbus Service Bulletin A330-27-3047, Revision 01, dated 
November 26, 1997.
    (iv) Airbus Service Bulletin A330-27-3050, dated November 15, 
1996.
    (v) Airbus Service Bulletin A330-27-3052, Revision 03, dated 
December 5, 2001.
    (vi) Airbus Service Bulletin A330-27-3085, Revision 02, dated 
September 5, 2002.
    (vii) Airbus Service Bulletin A330-27-3093, Revision 01, dated 
September 5, 2002.
    (viii) Airbus Service Bulletin A330-55-3020, Revision 01, dated 
October 21, 1998.
    (ix) Airbus Service Bulletin A340-27-4007, dated April 7, 1994.
    (x) Airbus Service Bulletin A340-27-4025, dated June 7, 1995.
    (xi) Airbus Service Bulletin A340-27-4054, Revision 01, dated 
November 26, 1997.
    (xii) Airbus Service Bulletin A340-27-4057, dated November 15, 
1996.
    (xiii) Airbus Service Bulletin A340-27-4059, Revision 03, dated 
December 5, 2001.
    (xiv) Airbus Service Bulletin A340-27-4089, Revision 02, dated 
September 5, 2002.
    (xv) Airbus Service Bulletin A340-27-4099, Revision 01, dated 
September 5, 2002.
    (xvi) Airbus Service Bulletin A340-55-4021, Revision 01, October 
21, 1998.
    (5) For Airbus service information identified in this AD, 
contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet: http://www.airbus.com.
    (6) For TRW Aeronautical Systems, SAMM Avionique, and Lucas 
Aerospace service information identified in this AD, contact 
Goodrich Corporation, Actuation Systems, Stafford Road, Fordhouses, 
Wolverhampton WV10 7EH, England; telephone +44 (0) 1902 624938; fax 
+44 (0) 1902 788100; email techpubs.wolverhampton@goodrich.com; 
Internet http://www.goodrich.com/TechPubs.
    (7) You may review copies of the 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.
    (8) 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 21, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-18774 Filed 8-5-13; 8:45 am]
BILLING CODE 4910-13-P