Airworthiness Directives; Airbus Airplanes, 57086-57090 [2015-23541]

Download as PDF 57086 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on September 9, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–23539 Filed 9–21–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0753; Directorate Identifier 2014–NM–128–AD; Amendment 39–18270; AD 2015–19–08] 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) 2011–19– 04, for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2011–19–04 required repetitive inspections for cracking of the left-hand and right-hand inboard and outboard elevator servo-control rod eye-ends, and corrective actions if necessary. This new AD requires an inspection to determine if certain elevator servo-control parts are installed, and replacement if necessary. This AD was prompted by a determination that certain elevator servo-control parts that do not conform to the approved type design have been installed and may have the potential of cracks in the rod eye-end. We are issuing this AD to detect and correct rod eye-end cracking, which could result in uncontrolled elevator surface and consequent reduced control of the airplane. SUMMARY: This AD becomes effective October 27, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 27, 2015. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of October 21, 2011 (76 FR 57630, September 16, 2011). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in Lhorne on DSK5TPTVN1PROD with RULES DATES: VerDate Sep<11>2014 13:50 Sep 21, 2015 Jkt 235001 this AD as of September 22, 2009 (74 FR 41611 August 18, 2009). ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0753; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For Airbus service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. For UTC service information identified in this AD, contact UTC Aerospace Systems; Roger Dangremont; telephone +01 34 32 63 28; email roger.dangrement@goodrich.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0753. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011). AD 2011–19–04 applied to all Model A318, A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on October 21, 2014 (79 FR 62928). The NPRM was prompted by a determination that certain elevator servo-control parts that do not conform to the approved type design have been installed and may have the potential of cracks in the rod eye-end. The NPRM proposed to continue to require repetitive inspections of the left-hand and right-hand inboard and outboard elevator servo-control rod eye-ends for cracking, and corrective actions if necessary. The NPRM also proposed to require an inspection to determine if certain elevator servo-control parts are PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 installed, and replacement if necessary. We are issuing this AD to detect and correct rod eye-end cracking, which could result in uncontrolled elevator surface and consequent reduced control of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0137, dated May 28, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition. The MCAI states: One case of elevator servo-control disconnection was reported on an A320 family aeroplane. Investigation results revealed that the failure occurred at the servo-control rod eye-end. Prompted by this finding, additional inspections revealed cracking at the same location on a number of other servo-control rod eye-ends. In several cases, both actuators of the same elevator surface were affected. It was determined that the detected rod end cracks are caused by fatigue, induced by a bending effect which is linked to the spherical bearing rotational torque. As the elevator surface is neither actuated nor damped, a dual servo-control disconnection on the same elevator would result in an uncontrolled surface. This condition, if not corrected, could result in reduced control of the aeroplane. To address this potential unsafe condition, EASA issued [an airworthiness directive (later revised)] [which corresponds to FAA AD 2009–17–04, Amendment 39–15995 (74 FR 41611, August 18, 2009)] to require a onetime inspection of the elevator servo-control rod eye-ends for aeroplanes which had accumulated more than 10,000 flight cycles (FC) since aeroplane first flight and, in case of findings, accomplishment of corrective actions. As a result of EASA AD 2008–0149, a significant number of rod eye-ends were found cracked. In addition, some cracks were reported on rod eye-ends that had not yet accumulated the 10,000 FC of the established threshold. Prompted by these findings, EASA issued [an airworthiness directive (later revised)] [which corresponds to FAA AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011)], which partially retained the initial inspection requirement of EASA AD 2008–0149, which was superseded, reduced the compliance time of the initial inspection and introduced a repetitive inspection programme. After EASA AD 2010–0046R1 (https:// ad.easa.europa.eu/blob/easa_ad_2010_0046_ R1_superseded.pdf/AD_2010-0046R1_1) was issued, a new elevator servo-control rod eyeend was developed, incorporating a regreasable roller bearing. Consequently, EASA issued [EASA] AD 2013–0309 (later corrected) (https:// ad.easa.europa.eu/blob/easa_ad_2013_0309_ superseded.pdf/AD_2013-0309_1), retaining the requirements of EASA AD 2010–0046R1, which was superseded, and introduced an E:\FR\FM\22SER1.SGM 22SER1 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations optional terminating action for the repetitive inspections by replacing the existing elevator servo-control rod eye-ends with the new elevator servo-control rod eye-end. In addition, that [EASA] AD prohibited, for aeroplanes that incorporate this optional modification, (re)installation of unmodified elevator servo-controls. At the time that EASA AD 2013–0309 was issued, it was planned that Airbus would proceed with the certification of certain elevator servo-controls, Part Number (P/N) 31075–0xx, P/N 31075–1xx and P/N 31075– 3xx (originally certified only for installation on Model A320–111 aeroplanes, which are no longer in service), to allow installation of those parts on other A320 family aeroplane Models. Since that [EASA] AD was issued, Airbus decided not to progress with certification of the affected elevator servo-controls for installation on other Models. For the reason described above, and because of evidence that such parts remain available as spares in the field, this [EASA] AD retains the requirements of EASA AD 2013–0309, which is superseded, and adds a prohibition to install the affected elevator servo-controls that were only intended for A320–111 aeroplanes. This AD requires an inspection to determine whether any elevator control part having P/N 31075–0xx, 31075–1xx, or 31075–3xx is installed, and replacement if necessary. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov/ #!documentDetail;D=FAA-2014-07530002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 62928, October 21, 2014) and the FAA’s response to each comment. Lhorne on DSK5TPTVN1PROD with RULES Request To Clarify Affected Airplanes for Certain Proposed Requirements United Airlines (UAL) requested that, for clarity reasons, we revise the identity of affected airplanes in paragraphs (g) through (j) of the proposed AD (79 FR 62928, October 21, 2014) to pertain only to elevator servocontrols having part number (P/N) 341203 or P/N 341203–xxx rod eyeends. UAL stated that per Airbus Service Bulletin A320–27A1186, Revision 07, dated March 2, 2011; and Goodrich Service Bulletin 31075–27–22, dated July 2, 2013, it understands that only the rod eye-ends fitted with selflubricating spherical bearings are required to have initial and repetitive inspections for cracks. We partially agree with the commenter’s request. We agree that only certain elevator servo-controls and rod VerDate Sep<11>2014 13:50 Sep 21, 2015 Jkt 235001 eye-ends are affected. However, paragraph (n) of this AD addresses the commenter’s concern. Paragraph (n) of this AD identifies airplanes that are not affected by the requirements of paragraphs (g), (h), (k) and (l) of this AD. We have not changed this AD as requested by the commenter, but we have revised the heading of paragraph (n) of this AD to more accurately reflect the content of that paragraph. Request To Permit the Use of Serviceable Parts, and Relocate the Definition of Serviceable Parts UAL requested that we permit the use of serviceable parts in paragraph (l)(1) of the proposed AD (79 FR 62928, October 21, 2014), and move the definition of a serviceable part from paragraph (l)(2) of the proposed AD to paragraph (l)(1) of the proposed AD. We agree with the commenter’s requests. We have determined that the use of serviceable parts is acceptable as replacement parts in paragraph (l)(1) of this AD. We have changed the wording of paragraph (l)(1) of this AD to specify that serviceable parts may be used as replacement parts. We have also moved the definition of serviceable parts from paragraph (l)(2) of this AD to paragraph (l)(1) of this AD since both paragraphs (l)(1) and (l)(2) of this AD specify the use of serviceable parts. Request To Revise Service Information Title UAL requested that we revise paragraph (l)(2) of the proposed AD (79 FR 62928, October 21, 2014) to replace the service information nomenclature from Goodrich Service Bulletin 31075– 27–22, dated July 2, 2013, to UTC Aerospace Systems Service Bulletin 31075–27–22, dated July 2, 2013. We agree with the commenter’s request. The requested service bulletin title change is correct. We have revised paragraph (l)(2) of this AD accordingly. 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 (79 FR 62928, October 21, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 62928, October 21, 2014). We also determined that these changes will not increase the economic PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 57087 burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–27–1223, dated September 3, 2013; and UTC Aerospace Systems Service Bulletin 31075–27–22, dated July 2, 2013. The service information describes procedures for modifying and replacing the elevator servo-control eyeend. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this AD. Costs of Compliance We estimate that this AD affects 851 airplanes of U.S. registry. The actions that are required by AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011), and retained in this AD take about 25 workhours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2011– 19–04 is $2,125 per product. We also estimate that it would take about 14 work-hours per product to comply with the 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 $1,012,690, or $1,190 per product. In addition, we estimate that any necessary follow-on actions would take about 2 work-hours and require parts costing $4,000, for a cost of $4,170 per product. We have no way of determining the number of aircraft that might need this action. 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 E:\FR\FM\22SER1.SGM 22SER1 57088 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations 2015–19–08 Airbus: Amendment 39–18270; Docket No. FAA–2014–0753; Directorate Identifier 2014–NM–128–AD. 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0753; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. 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: ■ Lhorne on DSK5TPTVN1PROD with RULES Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011), and adding the following new AD: ■ VerDate Sep<11>2014 13:50 Sep 21, 2015 Jkt 235001 (a) Effective Date This AD becomes effective October 27, 2015. (b) Affected ADs This AD replaces AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A318–111, –112, –121, and –122 airplanes. (2) Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Airbus Model A320–211, –212, –214, –231, –232, and –233 airplanes. (4) Airbus Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Reason This AD was prompted by a determination that certain elevator servo-control parts that do not conform to the approved type design have been installed and may have the potential of cracks in the rod eye-end. We are issuing this AD to detect and correct rod eyeend cracking, which could result in uncontrolled elevator surface and consequent reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspections This paragraph restates the requirements of paragraph (g) of AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011), with no changes. (1) At the applicable times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD: Inspect both the left-hand and right-hand inboard elevator servo-control rod eye-ends for cracking, in accordance with the instructions of Airbus All Operators Telex (AOT) A320–27A1186, Revision 04, dated April 3, 2009; or the Accomplishment Instructions of Airbus Service Bulletin A320– 27A1186, Revision 07, dated March 2, 2011. As of October 21, 2011 (the effective date of AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011)), use Airbus Service Bulletin A320–27A1186, Revision 07, dated March 2, 2011. (i) For airplanes that have accumulated 10,000 total flight cycles or more as of September 22, 2009 (the effective date of AD 2009–17–04, Amendment 39–15995 (74 FR 41611, August 18, 2009)): At the later of the times specified in paragraphs (g)(1)(i)(A) and (g)(1)(i)(B) of this AD. (A) Within 1,500 flight cycles after September 22, 2009 (the effective date of AD 2009–17–04, Amendment 39–15995 (74 FR 41611, August 18, 2009)). PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 (B) Within 1,500 flight cycles after accumulating 10,000 total flight cycles since first flight of the airplane. (ii) For airplanes that have accumulated less than 10,000 total flight cycles as of September 22, 2009 (the effective date of AD 2009–17–04, Amendment 39–15995 (74 FR 41611, August 18, 2009)): At the later of the times specified in paragraphs (g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD. (A) Before the accumulation of 5,000 total flight cycles. (B) Within 20 months after October 21, 2011 (the effective date of AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011)) but no later than before the accumulation of 11,500 total flight cycles. (2) At the applicable time specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD: Inspect both the left-hand and right-hand outboard elevator servo-control rod eye-ends for cracking, in accordance with the instructions of Airbus AOT A320–27A1186, Revision 04, dated April 3, 2009; or the Accomplishment Instructions of Airbus Service Bulletin A320–27A1186, Revision 07, dated March 2, 2011. As of October 21, 2011 (the effective date of AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011)), use Airbus Service Bulletin A320–27A1186, Revision 07, dated March 2, 2011. (i) For airplanes that have accumulated 10,000 total flight cycles or more as of September 22, 2009 (the effective date of AD 2009–17–04, Amendment 39–15995 (74 FR 41611, August 18, 2009)): At the later of the times specified in paragraphs (g)(2)(i)(A) and (g)(2)(i)(B) of this AD. (A) Within 3,000 flight cycles after September 22, 2009 (the effective date of AD 2009–17–04, Amendment 39–15995 (74 FR 41611, August 18, 2009)). (B) Within 3,000 flight cycles after accumulating 10,000 total flight cycles since first flight of the airplane. (ii) For airplanes that have accumulated less than 10,000 total flight cycles as of September 22, 2009 (the effective date of AD 2009–17–04, Amendment 39–15995 (74 FR 41611, August 18, 2009)): At the later of the times specified in paragraphs (g)(2)(ii)(A) and (g)(2)(ii)(B) of this AD. (A) Before the accumulation of 7,500 total flight cycles. (B) Within 40 months after October 21, 2011 (the effective date of AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011)), but no later than before the accumulation of 13,000 total flight cycles. (h) Retained Repetitive Inspections This paragraph restates the requirements of paragraph (h) of AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011), with no changes. Repeat the inspections of the left-hand and right-hand inboard and outboard elevator servo-control rod eye-ends for cracking as required by paragraphs (g)(1) and (g)(2) of this AD at the later of the times specified in paragraph (h)(1) or (h)(2) of this AD. Repeat the inspections thereafter at intervals not to exceed 5,000 flight cycles. (1) Within 5,000 flight cycles after the last inspection required by paragraph (g)(1) or (g)(2) of this AD as applicable. E:\FR\FM\22SER1.SGM 22SER1 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations (2) Within 6 months after October 21, 2011 (the effective date of AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011)). (i) Retained Corrective Actions This paragraph restates the requirements of paragraph (i) of AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011), with no changes. If any cracking is found during any inspection required by paragraph (g) or (h) of this AD, before further flight, accomplish all applicable corrective actions, in accordance with the Accomplishment Instructions and figures of Airbus Service Bulletin A320–27A1186, Revision 07, dated March 2, 2011. (j) Retained Parts Installation Limitation for Elevator Servo-Control Rod Eye-Ends This paragraph restates the requirements of paragraph (j) of AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011), with a new exception. As of October 21, 2011 (the effective date of AD 2011–19–04, Amendment 39–16809 (76 FR 57360, September 16, 2011)), and except as required by paragraph (p) of this AD, no person may install on any airplane an elevator servocontrol rod eye-end unless it is new or has been inspected in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27A1186, Revision 07, dated March 2, 2011, with no crack findings. Lhorne on DSK5TPTVN1PROD with RULES (k) New Requirement of This AD: Inspection To Determine Part Numbers As of the effective date of this AD: At the later of the times specified in paragraphs (k)(1) and (k)(2) of this AD, do an inspection to determine whether any elevator control part having part number (P/N) 31075–0xx, 31075–1xx, or 31075–3xx is installed. A review of airplane maintenance records is acceptable in lieu of this inspection if the part numbers of the elevator control parts can be conclusively determined from that review. (1) Concurrently with the accomplishment of the next inspection required by paragraph (g) or (h) of this AD. (2) Within 30 days after the effective date of this AD. (l) New Requirement of This AD: Replacement of Certain Parts If the inspection required by paragraph (k) of this AD reveals that any elevator servocontrols having P/Ns 31075–0xx, 31075–1xx, or 31075–3xx are installed: Before further flight, do the actions specified in paragraph (l)(1) or (l)(2) of this AD. (1) Replace all elevator servo-controls having P/N 31075–0xx, 31075–1xx, or 31075–3xx with serviceable parts having P/ N 31075–2xx or 31075–4xx, as applicable, using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). Serviceable parts are those that have been inspected for cracks in the rod eye-ends without any crack findings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27A1186, Revision 07, dated March 2, 2011. VerDate Sep<11>2014 13:50 Sep 21, 2015 Jkt 235001 (2) Replace all elevator servo-controls having P/N 31075–0xx, 31075–1xx, or 31075–3xx with serviceable parts having P/ N 31075–6xx or 31075–8xx, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 27–1223, dated September 3, 2013; or UTC Aerospace Systems Service Bulletin 31075– 27–22, dated July 2, 2013. (m) New Optional Terminating Action for Certain Inspections Modification of an airplane by replacing all 4 elevator servo-control rod eye-ends with modified (i.e. re-greasable) parts, and reidentification of those elevator servo-controls to P/N 31075–6xx or P/N 31075–8xx, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27–1223, dated September 3, 2013; constitutes terminating action for the requirements of paragraphs (g), (h), (k), and (l) of this AD. Note 1 to paragraph (m) of this AD: Maintenance Review Board Report task reference 27.34.00/06, Lubrication of Elevator Servo-control Rod Eye End Bearing, is applicable to elevator servo-controls having P/N 31075–6xx or P/N 31075–8xx. (n) Airplanes Excluded From Certain Inspection Requirements Airplanes on which Airbus Modification 154554 (installation of servo-controls having P/N 31075–6xx or P/N 31075–8xx, fitted with modified rod eye-end roller bearing) has been embodied in production are not affected by the requirements of paragraphs (g), (h), (k), and (l) of this AD, provided that no elevator servo-control having P/N 31075–0xx, or P/N 31075–1xx, or P/N 31075–2xx, or P/N 31075– 3xx, or P/N 31075–4xx, fitted with rod eyeend assembly P/N 341203-xxx, has been reinstalled since first flight. (o) Credit for Previous Actions (1) This paragraph restates the credit specified in paragraph (k) of AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011). (i) This paragraph provides credit for actions required by paragraphs (g)(1) and (g)(2) of this AD, if those actions were performed before October 21, 2011 (the effective date of AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011)), using the service information specified in paragraphs (o)(1)(i)(A) through (o)(1)(i)(E) of this AD. (A) Airbus AOT A320–27A1186, dated June 23, 2008, which is not incorporated by reference in this AD. (B) Airbus AOT A320–7A1186, Revision 01, dated August 11, 2008, which is not incorporated by reference in this AD. (C) Airbus AOT A320–7A1186, Revision 02, dated March 30, 2009, which is not incorporated by reference in this AD. (D) Airbus AOT 320–7A1186, Revision 03, dated April 1, 2009, which is not incorporated by reference in this AD. (E) Airbus AOT A320–27A1186, Revision 04, dated April 3, 2009, which was incorporated by reference in AD 2009–17–04, Amendment 39–15995 (74 FR 41611, August 18, 2009), which continues to be incorporated by reference in this AD. PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 57089 (ii) This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before October 21, 2011 (the effective date of AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011)), using Airbus Service Bulletin A320–27A1186, Revision 05, dated March 10, 2010; or Airbus Service Bulletin A320–27A1186, Revision 06, dated December 14, 2010; which are not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before October 21, 2011 (the effective date of AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011)), using Airbus Service Bulletin A320–27A1186, Revision 06, dated December 14, 2010, which is not incorporated by reference in this AD. (p) New Parts Installation Prohibition (1) As of the effective date of this AD, no person may install on any airplane an elevator servo-control having P/N 31075–0xx, 31075–1xx, or 31075–3xx. (2) No person may install on any airplane an elevator servo-control having P/N 31075– 2xx or P/N 31075–4xx, or an elevator servocontrol rod eye-end having P/N 341203 or P/ N 341203–XXX, as required by paragraphs (p)(2)(i) and (p)(2)(ii) of this AD, as applicable. (i) For airplanes that do not have Airbus Modification 154554 embodied in production: After optional modification of the airplane as specified in paragraph (m) of this AD. (ii) For airplanes on which Airbus Modification 154554 has been embodied in production: As of the effective date of this AD. (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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously for AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011), are approved as AMOCs for the corresponding provisions of this AD. E:\FR\FM\22SER1.SGM 22SER1 57090 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. Lhorne on DSK5TPTVN1PROD with RULES (r) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0137, dated May 28, 2014, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2014–0753. (2) Airbus Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (s)(6) and (s)(8) 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 this AD specifies otherwise. (3) The following service information was approved for IBR on October 27, 2015. (i) Airbus Service Bulletin A320–27–1223, dated September 3, 2013. (ii) UTC Aerospace Systems Service Bulletin 31075–27–22, dated July 2, 2013. (4) The following service information was approved for IBR on October 21, 2011 (76 FR 57630, September 16, 2011). (i) Airbus Service Bulletin A320–27A1186, Revision 07, including Appendices 1, 2, 3, 4, 5, and 6, dated March 2, 2011. (ii) Reserved. (5) The following service information was approved for IBR on September 22, 2009 (74 FR 41611, August 18, 2009). (i) Airbus All Operators Telex A320– 27A1186, Revision 04, dated April 3, 2009. The document number and issue date of Airbus AOT A320–27A1186, Revision 04, dated April 3, 2009, are specified only on the first page of the AOT. (ii) Reserved. (6) For Airbus service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet https://www.airbus.com. (7) For UTC service information identified in this AD, contact UTC Aerospace Systems; Roger Dangremont; telephone +01 34 32 63 28; email roger.dangrement@goodrich.com. (8) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (9) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on VerDate Sep<11>2014 13:50 Sep 21, 2015 Jkt 235001 the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on September 11, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–23541 Filed 9–21–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration 21 CFR Part 886 [Docket No. FDA–2015–N–3044] Medical Devices; Ophthalmic Devices; Classification of the Oral Electronic Vision Aid AGENCY: Food and Drug Administration, HHS. ACTION: Final order. The Food and Drug Administration (FDA) is classifying the oral electronic vision aid into class II (special controls). The special controls that will apply to the device are identified in this order and will be part of the codified language for the oral electronic vision aid’s classification. The Agency is classifying the device into class II (special controls) in order to provide a reasonable assurance of safety and effectiveness of the device. DATES: This order is effective September 22, 2015. The classification was applicable on June 18, 2015. FOR FURTHER INFORMATION CONTACT: Dexiu Shi, Center for Devices and Radiological Health, Food and Drug Administration, 10903 New Hampshire Ave., Bldg. 66, Rm. 2246, Silver Spring, MD, 20993–0002, 301–796–6470, dexiu.shi@fda.hhs.gov. SUPPLEMENTARY INFORMATION: SUMMARY: I. Background In accordance with section 513(f)(1) of the Federal Food, Drug, and Cosmetic Act (the FD&C Act) (21 U.S.C. 360c(f)(1)), devices that were not in commercial distribution before May 28, 1976 (the date of enactment of the Medical Device Amendments of 1976), generally referred to as postamendments devices, are classified automatically by statute into class III without any FDA rulemaking process. These devices remain in class III and require premarket approval, unless and until the device is classified or reclassified PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 into class I or II, or FDA issues an order finding the device to be substantially equivalent, in accordance with section 513(i), to a predicate device that does not require premarket approval. The Agency determines whether new devices are substantially equivalent to predicate devices by means of premarket notification procedures in section 510(k) of the FD&C Act (21 U.S.C. 360(k)) and part 807 (21 CFR part 807) of the regulations. Section 513(f)(2) of the FD&C Act (21 U.S.C. 360c(f)(2)), as amended by section 607 of the Food and Drug Administration Safety and Innovation Act (Pub. L. 112–144), provides two procedures by which a person may request FDA to classify a device under the criteria set forth in section 513(a)(1). Under the first procedure, the person submits a premarket notification under section 510(k) of the FD&C Act for a device that has not previously been classified and, within 30 days of receiving an order classifying the device into class III under section 513(f)(1), the person requests a classification under section 513(f)(2). Under the second procedure, rather than first submitting a premarket notification under section 510(k) and then a request for classification under the first procedure, the person determines that there is no legally marketed device upon which to base a determination of substantial equivalence and requests a classification under section 513(f)(2) of the FD&C Act. If the person submits a request to classify the device under this second procedure, FDA may decline to undertake the classification request if FDA identifies a legally marketed device that could provide a reasonable basis for review of substantial equivalence with the device or if FDA determines that the device submitted is not of ‘‘lowmoderate risk’’ or that general controls would be inadequate to control the risks and special controls to mitigate the risks cannot be developed. In response to a request to classify a device under either procedure provided by section 513(f)(2) of the FD&C Act, FDA will classify the device by written order within 120 days. This classification will be the initial classification of the device. On August 7, 2013, Wicab Inc., submitted a request for classification of the BrainPort V100 under section 513(f)(2) of the FD&C Act. The manufacturer recommended that the device be classified into class II (Ref. 1). In accordance with section 513(f)(2) of the FD&C Act, FDA reviewed the request in order to classify the device under the criteria for classification set forth in section 513(a)(1). FDA classifies E:\FR\FM\22SER1.SGM 22SER1

Agencies

[Federal Register Volume 80, Number 183 (Tuesday, September 22, 2015)]
[Rules and Regulations]
[Pages 57086-57090]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-23541]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0753; Directorate Identifier 2014-NM-128-AD; 
Amendment 39-18270; AD 2015-19-08]
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) 2011-19-04, 
for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 
2011-19-04 required repetitive inspections for cracking of the left-
hand and right-hand inboard and outboard elevator servo-control rod 
eye-ends, and corrective actions if necessary. This new AD requires an 
inspection to determine if certain elevator servo-control parts are 
installed, and replacement if necessary. This AD was prompted by a 
determination that certain elevator servo-control parts that do not 
conform to the approved type design have been installed and may have 
the potential of cracks in the rod eye-end. We are issuing this AD to 
detect and correct rod eye-end cracking, which could result in 
uncontrolled elevator surface and consequent reduced control of the 
airplane.

DATES: This AD becomes effective October 27, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 27, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
October 21, 2011 (76 FR 57630, September 16, 2011).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
September 22, 2009 (74 FR 41611 August 18, 2009).

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0753; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    For Airbus service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. For UTC service information identified in this AD, 
contact UTC Aerospace Systems; Roger Dangremont; telephone +01 34 32 63 
28; email roger.dangrement@goodrich.com. You may view this referenced 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue SW., Renton, WA. For information on the availability of 
this material at the FAA, call 425-227-1221. It is also available on 
the Internet at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2014-0753.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2011-19-04, Amendment 39-16809 (76 FR 57630, 
September 16, 2011). AD 2011-19-04 applied to all Model A318, A319, 
A320, and A321 series airplanes. The NPRM published in the Federal 
Register on October 21, 2014 (79 FR 62928). The NPRM was prompted by a 
determination that certain elevator servo-control parts that do not 
conform to the approved type design have been installed and may have 
the potential of cracks in the rod eye-end. The NPRM proposed to 
continue to require repetitive inspections of the left-hand and right-
hand inboard and outboard elevator servo-control rod eye-ends for 
cracking, and corrective actions if necessary. The NPRM also proposed 
to require an inspection to determine if certain elevator servo-control 
parts are installed, and replacement if necessary. We are issuing this 
AD to detect and correct rod eye-end cracking, which could result in 
uncontrolled elevator surface and consequent reduced control of the 
airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0137, dated May 28, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition. The MCAI states:

    One case of elevator servo-control disconnection was reported on 
an A320 family aeroplane. Investigation results revealed that the 
failure occurred at the servo-control rod eye-end. Prompted by this 
finding, additional inspections revealed cracking at the same 
location on a number of other servo-control rod eye-ends. In several 
cases, both actuators of the same elevator surface were affected.
    It was determined that the detected rod end cracks are caused by 
fatigue, induced by a bending effect which is linked to the 
spherical bearing rotational torque. As the elevator surface is 
neither actuated nor damped, a dual servo-control disconnection on 
the same elevator would result in an uncontrolled surface.
    This condition, if not corrected, could result in reduced 
control of the aeroplane.
    To address this potential unsafe condition, EASA issued [an 
airworthiness directive (later revised)] [which corresponds to FAA 
AD 2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)] to 
require a one-time inspection of the elevator servo-control rod eye-
ends for aeroplanes which had accumulated more than 10,000 flight 
cycles (FC) since aeroplane first flight and, in case of findings, 
accomplishment of corrective actions.
    As a result of EASA AD 2008-0149, a significant number of rod 
eye-ends were found cracked. In addition, some cracks were reported 
on rod eye-ends that had not yet accumulated the 10,000 FC of the 
established threshold.
    Prompted by these findings, EASA issued [an airworthiness 
directive (later revised)] [which corresponds to FAA AD 2011-19-04, 
Amendment 39-16809 (76 FR 57630, September 16, 2011)], which 
partially retained the initial inspection requirement of EASA AD 
2008-0149, which was superseded, reduced the compliance time of the 
initial inspection and introduced a repetitive inspection programme.
    After EASA AD 2010-0046R1 (https://ad.easa.europa.eu/blob/easa_ad_2010_0046_R1_superseded.pdf/AD_2010-0046R1_1) was issued, a 
new elevator servo-control rod eye-end was developed, incorporating 
a re-greasable roller bearing.
    Consequently, EASA issued [EASA] AD 2013-0309 (later corrected) 
(https://ad.easa.europa.eu/blob/easa_ad_2013_0309_superseded.pdf/AD_2013-0309_1), retaining the requirements of EASA AD 2010-0046R1, 
which was superseded, and introduced an

[[Page 57087]]

optional terminating action for the repetitive inspections by 
replacing the existing elevator servo-control rod eye-ends with the 
new elevator servo-control rod eye-end. In addition, that [EASA] AD 
prohibited, for aeroplanes that incorporate this optional 
modification, (re)installation of unmodified elevator servo-
controls.
    At the time that EASA AD 2013-0309 was issued, it was planned 
that Airbus would proceed with the certification of certain elevator 
servo-controls, Part Number (P/N) 31075-0xx, P/N 31075-1xx and P/N 
31075-3xx (originally certified only for installation on Model A320-
111 aeroplanes, which are no longer in service), to allow 
installation of those parts on other A320 family aeroplane Models.
    Since that [EASA] AD was issued, Airbus decided not to progress 
with certification of the affected elevator servo-controls for 
installation on other Models.
    For the reason described above, and because of evidence that 
such parts remain available as spares in the field, this [EASA] AD 
retains the requirements of EASA AD 2013-0309, which is superseded, 
and adds a prohibition to install the affected elevator servo-
controls that were only intended for A320-111 aeroplanes.

This AD requires an inspection to determine whether any elevator 
control part having P/N 31075-0xx, 31075-1xx, or 31075-3xx is 
installed, and replacement if necessary.
    You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0753-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 62928, October 21, 2014) and the FAA's response to each comment.

Request To Clarify Affected Airplanes for Certain Proposed Requirements

    United Airlines (UAL) requested that, for clarity reasons, we 
revise the identity of affected airplanes in paragraphs (g) through (j) 
of the proposed AD (79 FR 62928, October 21, 2014) to pertain only to 
elevator servo-controls having part number (P/N) 341203 or P/N 341203-
xxx rod eye-ends. UAL stated that per Airbus Service Bulletin A320-
27A1186, Revision 07, dated March 2, 2011; and Goodrich Service 
Bulletin 31075-27-22, dated July 2, 2013, it understands that only the 
rod eye-ends fitted with self-lubricating spherical bearings are 
required to have initial and repetitive inspections for cracks.
    We partially agree with the commenter's request. We agree that only 
certain elevator servo-controls and rod eye-ends are affected. However, 
paragraph (n) of this AD addresses the commenter's concern. Paragraph 
(n) of this AD identifies airplanes that are not affected by the 
requirements of paragraphs (g), (h), (k) and (l) of this AD. We have 
not changed this AD as requested by the commenter, but we have revised 
the heading of paragraph (n) of this AD to more accurately reflect the 
content of that paragraph.

Request To Permit the Use of Serviceable Parts, and Relocate the 
Definition of Serviceable Parts

    UAL requested that we permit the use of serviceable parts in 
paragraph (l)(1) of the proposed AD (79 FR 62928, October 21, 2014), 
and move the definition of a serviceable part from paragraph (l)(2) of 
the proposed AD to paragraph (l)(1) of the proposed AD.
    We agree with the commenter's requests. We have determined that the 
use of serviceable parts is acceptable as replacement parts in 
paragraph (l)(1) of this AD. We have changed the wording of paragraph 
(l)(1) of this AD to specify that serviceable parts may be used as 
replacement parts. We have also moved the definition of serviceable 
parts from paragraph (l)(2) of this AD to paragraph (l)(1) of this AD 
since both paragraphs (l)(1) and (l)(2) of this AD specify the use of 
serviceable parts.

Request To Revise Service Information Title

    UAL requested that we revise paragraph (l)(2) of the proposed AD 
(79 FR 62928, October 21, 2014) to replace the service information 
nomenclature from Goodrich Service Bulletin 31075-27-22, dated July 2, 
2013, to UTC Aerospace Systems Service Bulletin 31075-27-22, dated July 
2, 2013.
    We agree with the commenter's request. The requested service 
bulletin title change is correct. We have revised paragraph (l)(2) of 
this AD accordingly.

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 (79 FR 62928, October 21, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 62928, October 21, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-27-1223, dated September 3, 
2013; and UTC Aerospace Systems Service Bulletin 31075-27-22, dated 
July 2, 2013. The service information describes procedures for 
modifying and replacing the elevator servo-control eye-end. This 
service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section of this AD.

Costs of Compliance

    We estimate that this AD affects 851 airplanes of U.S. registry.
    The actions that are required by AD 2011-19-04, Amendment 39-16809 
(76 FR 57630, September 16, 2011), and retained in this AD take about 
25 work-hours per product, at an average labor rate of $85 per work-
hour. Based on these figures, the estimated cost of the actions that 
are required by AD 2011-19-04 is $2,125 per product.
    We also estimate that it would take about 14 work-hours per product 
to comply with the 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 $1,012,690, or $1,190 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 2 work-hours and require parts costing $4,000, for a cost of 
$4,170 per product. We have no way of determining the number of 
aircraft that might need this action.

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

[[Page 57088]]

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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0753; or in person at the 
Docket Management Facility between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this AD, the 
regulatory evaluation, any comments received, and other information. 
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

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) 
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011), and 
adding the following new AD:

2015-19-08 Airbus: Amendment 39-18270; Docket No. FAA-2014-0753; 
Directorate Identifier 2014-NM-128-AD.

(a) Effective Date

    This AD becomes effective October 27, 2015.

(b) Affected ADs

    This AD replaces AD 2011-19-04, Amendment 39-16809 (76 FR 57630, 
September 16, 2011).

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a determination that certain elevator 
servo-control parts that do not conform to the approved type design 
have been installed and may have the potential of cracks in the rod 
eye-end. We are issuing this AD to detect and correct rod eye-end 
cracking, which could result in uncontrolled elevator surface and 
consequent reduced control of the airplane.

(f) Compliance

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

(g) Retained Inspections

    This paragraph restates the requirements of paragraph (g) of AD 
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011), 
with no changes.
    (1) At the applicable times specified in paragraphs (g)(1)(i) 
and (g)(1)(ii) of this AD: Inspect both the left-hand and right-hand 
inboard elevator servo-control rod eye-ends for cracking, in 
accordance with the instructions of Airbus All Operators Telex (AOT) 
A320-27A1186, Revision 04, dated April 3, 2009; or the 
Accomplishment Instructions of Airbus Service Bulletin A320-27A1186, 
Revision 07, dated March 2, 2011. As of October 21, 2011 (the 
effective date of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, 
September 16, 2011)), use Airbus Service Bulletin A320-27A1186, 
Revision 07, dated March 2, 2011.
    (i) For airplanes that have accumulated 10,000 total flight 
cycles or more as of September 22, 2009 (the effective date of AD 
2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At 
the later of the times specified in paragraphs (g)(1)(i)(A) and 
(g)(1)(i)(B) of this AD.
    (A) Within 1,500 flight cycles after September 22, 2009 (the 
effective date of AD 2009-17-04, Amendment 39-15995 (74 FR 41611, 
August 18, 2009)).
    (B) Within 1,500 flight cycles after accumulating 10,000 total 
flight cycles since first flight of the airplane.
    (ii) For airplanes that have accumulated less than 10,000 total 
flight cycles as of September 22, 2009 (the effective date of AD 
2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At 
the later of the times specified in paragraphs (g)(1)(ii)(A) and 
(g)(1)(ii)(B) of this AD.
    (A) Before the accumulation of 5,000 total flight cycles.
    (B) Within 20 months after October 21, 2011 (the effective date 
of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 
2011)) but no later than before the accumulation of 11,500 total 
flight cycles.
    (2) At the applicable time specified in paragraphs (g)(2)(i) and 
(g)(2)(ii) of this AD: Inspect both the left-hand and right-hand 
outboard elevator servo-control rod eye-ends for cracking, in 
accordance with the instructions of Airbus AOT A320-27A1186, 
Revision 04, dated April 3, 2009; or the Accomplishment Instructions 
of Airbus Service Bulletin A320-27A1186, Revision 07, dated March 2, 
2011. As of October 21, 2011 (the effective date of AD 2011-19-04, 
Amendment 39-16809 (76 FR 57630, September 16, 2011)), use Airbus 
Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011.
    (i) For airplanes that have accumulated 10,000 total flight 
cycles or more as of September 22, 2009 (the effective date of AD 
2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At 
the later of the times specified in paragraphs (g)(2)(i)(A) and 
(g)(2)(i)(B) of this AD.
    (A) Within 3,000 flight cycles after September 22, 2009 (the 
effective date of AD 2009-17-04, Amendment 39-15995 (74 FR 41611, 
August 18, 2009)).
    (B) Within 3,000 flight cycles after accumulating 10,000 total 
flight cycles since first flight of the airplane.
    (ii) For airplanes that have accumulated less than 10,000 total 
flight cycles as of September 22, 2009 (the effective date of AD 
2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At 
the later of the times specified in paragraphs (g)(2)(ii)(A) and 
(g)(2)(ii)(B) of this AD.
    (A) Before the accumulation of 7,500 total flight cycles.
    (B) Within 40 months after October 21, 2011 (the effective date 
of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 
2011)), but no later than before the accumulation of 13,000 total 
flight cycles.

(h) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (h) of AD 
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011), 
with no changes. Repeat the inspections of the left-hand and right-
hand inboard and outboard elevator servo-control rod eye-ends for 
cracking as required by paragraphs (g)(1) and (g)(2) of this AD at 
the later of the times specified in paragraph (h)(1) or (h)(2) of 
this AD. Repeat the inspections thereafter at intervals not to 
exceed 5,000 flight cycles.
    (1) Within 5,000 flight cycles after the last inspection 
required by paragraph (g)(1) or (g)(2) of this AD as applicable.

[[Page 57089]]

    (2) Within 6 months after October 21, 2011 (the effective date 
of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 
2011)).

(i) Retained Corrective Actions

    This paragraph restates the requirements of paragraph (i) of AD 
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011), 
with no changes. If any cracking is found during any inspection 
required by paragraph (g) or (h) of this AD, before further flight, 
accomplish all applicable corrective actions, in accordance with the 
Accomplishment Instructions and figures of Airbus Service Bulletin 
A320-27A1186, Revision 07, dated March 2, 2011.

(j) Retained Parts Installation Limitation for Elevator Servo-Control 
Rod Eye-Ends

    This paragraph restates the requirements of paragraph (j) of AD 
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011), 
with a new exception. As of October 21, 2011 (the effective date of 
AD 2011-19-04, Amendment 39-16809 (76 FR 57360, September 16, 
2011)), and except as required by paragraph (p) of this AD, no 
person may install on any airplane an elevator servo-control rod 
eye-end unless it is new or has been inspected in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-
27A1186, Revision 07, dated March 2, 2011, with no crack findings.

(k) New Requirement of This AD: Inspection To Determine Part Numbers

    As of the effective date of this AD: At the later of the times 
specified in paragraphs (k)(1) and (k)(2) of this AD, do an 
inspection to determine whether any elevator control part having 
part number (P/N) 31075-0xx, 31075-1xx, or 31075-3xx is installed. A 
review of airplane maintenance records is acceptable in lieu of this 
inspection if the part numbers of the elevator control parts can be 
conclusively determined from that review.
    (1) Concurrently with the accomplishment of the next inspection 
required by paragraph (g) or (h) of this AD.
    (2) Within 30 days after the effective date of this AD.

(l) New Requirement of This AD: Replacement of Certain Parts

    If the inspection required by paragraph (k) of this AD reveals 
that any elevator servo-controls having P/Ns 31075-0xx, 31075-1xx, 
or 31075-3xx are installed: Before further flight, do the actions 
specified in paragraph (l)(1) or (l)(2) of this AD.
    (1) Replace all elevator servo-controls having P/N 31075-0xx, 
31075-1xx, or 31075-3xx with serviceable parts having P/N 31075-2xx 
or 31075-4xx, as applicable, using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA); or Airbus's EASA 
Design Organization Approval (DOA). Serviceable parts are those that 
have been inspected for cracks in the rod eye-ends without any crack 
findings, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-27A1186, Revision 07, dated March 2, 
2011.
    (2) Replace all elevator servo-controls having P/N 31075-0xx, 
31075-1xx, or 31075-3xx with serviceable parts having P/N 31075-6xx 
or 31075-8xx, as applicable, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1223, dated 
September 3, 2013; or UTC Aerospace Systems Service Bulletin 31075-
27-22, dated July 2, 2013.

(m) New Optional Terminating Action for Certain Inspections

    Modification of an airplane by replacing all 4 elevator servo-
control rod eye-ends with modified (i.e. re-greasable) parts, and 
re-identification of those elevator servo-controls to P/N 31075-6xx 
or P/N 31075-8xx, as applicable, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-27-1223, 
dated September 3, 2013; constitutes terminating action for the 
requirements of paragraphs (g), (h), (k), and (l) of this AD.

    Note 1 to paragraph (m) of this AD:  Maintenance Review Board 
Report task reference 27.34.00/06, Lubrication of Elevator Servo-
control Rod Eye End Bearing, is applicable to elevator servo-
controls having P/N 31075-6xx or P/N 31075-8xx.

(n) Airplanes Excluded From Certain Inspection Requirements

    Airplanes on which Airbus Modification 154554 (installation of 
servo-controls having P/N 31075-6xx or P/N 31075-8xx, fitted with 
modified rod eye-end roller bearing) has been embodied in production 
are not affected by the requirements of paragraphs (g), (h), (k), 
and (l) of this AD, provided that no elevator servo-control having 
P/N 31075-0xx, or P/N 31075-1xx, or P/N 31075-2xx, or P/N 31075-3xx, 
or P/N 31075-4xx, fitted with rod eye-end assembly P/N 341203-xxx, 
has been reinstalled since first flight.

(o) Credit for Previous Actions

    (1) This paragraph restates the credit specified in paragraph 
(k) of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 
2011).
    (i) This paragraph provides credit for actions required by 
paragraphs (g)(1) and (g)(2) of this AD, if those actions were 
performed before October 21, 2011 (the effective date of AD 2011-19-
04, Amendment 39-16809 (76 FR 57630, September 16, 2011)), using the 
service information specified in paragraphs (o)(1)(i)(A) through 
(o)(1)(i)(E) of this AD.
    (A) Airbus AOT A320-27A1186, dated June 23, 2008, which is not 
incorporated by reference in this AD.
    (B) Airbus AOT A320-7A1186, Revision 01, dated August 11, 2008, 
which is not incorporated by reference in this AD.
    (C) Airbus AOT A320-7A1186, Revision 02, dated March 30, 2009, 
which is not incorporated by reference in this AD.
    (D) Airbus AOT 320-7A1186, Revision 03, dated April 1, 2009, 
which is not incorporated by reference in this AD.
    (E) Airbus AOT A320-27A1186, Revision 04, dated April 3, 2009, 
which was incorporated by reference in AD 2009-17-04, Amendment 39-
15995 (74 FR 41611, August 18, 2009), which continues to be 
incorporated by reference in this AD.
    (ii) This paragraph provides credit for actions required by 
paragraph (h) of this AD, if those actions were performed before 
October 21, 2011 (the effective date of AD 2011-19-04, Amendment 39-
16809 (76 FR 57630, September 16, 2011)), using Airbus Service 
Bulletin A320-27A1186, Revision 05, dated March 10, 2010; or Airbus 
Service Bulletin A320-27A1186, Revision 06, dated December 14, 2010; 
which are not incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraph (i) of this AD, if those actions were performed before 
October 21, 2011 (the effective date of AD 2011-19-04, Amendment 39-
16809 (76 FR 57630, September 16, 2011)), using Airbus Service 
Bulletin A320-27A1186, Revision 06, dated December 14, 2010, which 
is not incorporated by reference in this AD.

(p) New Parts Installation Prohibition

    (1) As of the effective date of this AD, no person may install 
on any airplane an elevator servo-control having P/N 31075-0xx, 
31075-1xx, or 31075-3xx.
    (2) No person may install on any airplane an elevator servo-
control having P/N 31075-2xx or P/N 31075-4xx, or an elevator servo-
control rod eye-end having P/N 341203 or P/N 341203-XXX, as required 
by paragraphs (p)(2)(i) and (p)(2)(ii) of this AD, as applicable.
    (i) For airplanes that do not have Airbus Modification 154554 
embodied in production: After optional modification of the airplane 
as specified in paragraph (m) of this AD.
    (ii) For airplanes on which Airbus Modification 154554 has been 
embodied in production: As of the effective date of this AD.

(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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office. The AMOC approval letter must specifically 
reference this AD.
    (ii) AMOCs approved previously for AD 2011-19-04, Amendment 39-
16809 (76 FR 57630, September 16, 2011), are approved as AMOCs for 
the corresponding provisions of this AD.

[[Page 57090]]

    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.

(r) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0137, dated May 28, 2014, 
for related information. This MCAI may be found in the AD docket on 
the Internet at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2014-0753.
    (2) Airbus Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (s)(6) and (s)(8) 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 this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
October 27, 2015.
    (i) Airbus Service Bulletin A320-27-1223, dated September 3, 
2013.
    (ii) UTC Aerospace Systems Service Bulletin 31075-27-22, dated 
July 2, 2013.
    (4) The following service information was approved for IBR on 
October 21, 2011 (76 FR 57630, September 16, 2011).
    (i) Airbus Service Bulletin A320-27A1186, Revision 07, including 
Appendices 1, 2, 3, 4, 5, and 6, dated March 2, 2011.
    (ii) Reserved.
    (5) The following service information was approved for IBR on 
September 22, 2009 (74 FR 41611, August 18, 2009).
    (i) Airbus All Operators Telex A320-27A1186, Revision 04, dated 
April 3, 2009. The document number and issue date of Airbus AOT 
A320-27A1186, Revision 04, dated April 3, 2009, are specified only 
on the first page of the AOT.
    (ii) Reserved.
    (6) For Airbus service information identified in this AD, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet https://www.airbus.com.
    (7) For UTC service information identified in this AD, contact 
UTC Aerospace Systems; Roger Dangremont; telephone +01 34 32 63 28; 
email roger.dangrement@goodrich.com.
    (8) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (9) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on September 11, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-23541 Filed 9-21-15; 8:45 am]
 BILLING CODE 4910-13-P

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