80 FR 57086 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 183 (September 22, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 183 (September 22, 2015)
| Page Range | 57086-57090 | |
| FR Document | 2015-23541 |
[Federal Register Volume 80, Number 183 (Tuesday, September 22, 2015)] [Rules and Regulations] [Pages 57086-57090] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-23541] ----------------------------------------------------------------------- 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 http://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 [email protected]; Internet http://www.airbus.com. For UTC service information identified in this AD, contact UTC Aerospace Systems; Roger Dangremont; telephone +01 34 32 63 28; email [email protected]. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-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 (http://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) (http://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 http://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 http://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: [email protected]. (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 http://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 [email protected]; Internet http://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 [email protected]. (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: http://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
![57086 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations
the availability of this material at NARA, call this AD as of September 22, 2009 (74 FR installed, and replacement if necessary.
202–741–6030, or go to: http:// 41611 August 18, 2009). We are issuing this AD to detect and
www.archives.gov/federal-register/cfr/ibr- correct rod eye-end cracking, which
ADDRESSES: You may examine the AD
locations.html. could result in uncontrolled elevator
docket on the Internet at http://
Issued in Renton, Washington, on www.regulations.gov/ surface and consequent reduced control
September 9, 2015. #!docketDetail;D=FAA-2014-0753; or in of the airplane.
Michael Kaszycki, person at the Docket Management The European Aviation Safety Agency
Acting Manager, Transport Airplane Facility, U.S. Department of (EASA), which is the Technical Agent
Directorate, Aircraft Certification Service. Transportation, Docket Operations, M– for the Member States of the European
[FR Doc. 2015–23539 Filed 9–21–15; 8:45 am] 30, West Building Ground Floor, Room Union, has issued EASA Airworthiness
BILLING CODE 4910–13–P W12–140, 1200 New Jersey Avenue SE., Directive 2014–0137, dated May 28,
Washington, DC. 2014 (referred to after this as the
For Airbus service information Mandatory Continuing Airworthiness
DEPARTMENT OF TRANSPORTATION identified in this AD, contact Airbus, Information, or ‘‘the MCAI’’), to correct
Airworthiness Office—EIAS, 1 Rond an unsafe condition. The MCAI states:
Federal Aviation Administration Point Maurice Bellonte, 31707 Blagnac One case of elevator servo-control
Cedex, France; telephone +33 5 61 93 36 disconnection was reported on an A320
14 CFR Part 39 96; fax +33 5 61 93 44 51; email family aeroplane. Investigation results
[Docket No. FAA–2014–0753; Directorate account.airworth-eas@airbus.com; revealed that the failure occurred at the
Identifier 2014–NM–128–AD; Amendment Internet http://www.airbus.com. For servo-control rod eye-end. Prompted by this
39–18270; AD 2015–19–08] UTC service information identified in finding, additional inspections revealed
cracking at the same location on a number of
this AD, contact UTC Aerospace
RIN 2120–AA64 other servo-control rod eye-ends. In several
Systems; Roger Dangremont; telephone cases, both actuators of the same elevator
Airworthiness Directives; Airbus +01 34 32 63 28; email surface were affected.
Airplanes roger.dangrement@goodrich.com. You It was determined that the detected rod
may view this referenced service end cracks are caused by fatigue, induced by
AGENCY: Federal Aviation information at the FAA, Transport a bending effect which is linked to the
Administration (FAA), Department of Airplane Directorate, 1601 Lind Avenue spherical bearing rotational torque. As the
Transportation (DOT). SW., Renton, WA. For information on elevator surface is neither actuated nor
damped, a dual servo-control disconnection
ACTION: Final rule. the availability of this material at the
on the same elevator would result in an
FAA, call 425–227–1221. It is also uncontrolled surface.
SUMMARY: We are superseding available on the Internet at http:// This condition, if not corrected, could
Airworthiness Directive (AD) 2011–19– www.regulations.gov by searching for result in reduced control of the aeroplane.
04, for all Airbus Model A318, A319, and locating Docket No. FAA–2014– To address this potential unsafe condition,
A320, and A321 series airplanes. AD 0753. EASA issued [an airworthiness directive
2011–19–04 required repetitive (later revised)] [which corresponds to FAA
FOR FURTHER INFORMATION CONTACT:
inspections for cracking of the left-hand AD 2009–17–04, Amendment 39–15995 (74
Sanjay Ralhan, Aerospace Engineer, FR 41611, August 18, 2009)] to require a one-
and right-hand inboard and outboard
International Branch, ANM–116, time inspection of the elevator servo-control
elevator servo-control rod eye-ends, and
Transport Airplane Directorate, FAA, rod eye-ends for aeroplanes which had
corrective actions if necessary. This new
1601 Lind Avenue SW., Renton, WA accumulated more than 10,000 flight cycles
AD requires an inspection to determine (FC) since aeroplane first flight and, in case
98057–3356; telephone 425–227–1405;
if certain elevator servo-control parts are of findings, accomplishment of corrective
fax 425–227–1149.
installed, and replacement if necessary. actions.
SUPPLEMENTARY INFORMATION:
This AD was prompted by a As a result of EASA AD 2008–0149, a
determination that certain elevator Discussion significant number of rod eye-ends were
servo-control parts that do not conform found cracked. In addition, some cracks were
We issued a notice of proposed reported on rod eye-ends that had not yet
to the approved type design have been rulemaking (NPRM) to amend 14 CFR
installed and may have the potential of accumulated the 10,000 FC of the established
part 39 to supersede AD 2011–19–04, threshold.
cracks in the rod eye-end. We are Amendment 39–16809 (76 FR 57630, Prompted by these findings, EASA issued
issuing this AD to detect and correct rod September 16, 2011). AD 2011–19–04 [an airworthiness directive (later revised)]
eye-end cracking, which could result in applied to all Model A318, A319, A320, [which corresponds to FAA AD 2011–19–04,
uncontrolled elevator surface and and A321 series airplanes. The NPRM Amendment 39–16809 (76 FR 57630,
consequent reduced control of the published in the Federal Register on September 16, 2011)], which partially
airplane. October 21, 2014 (79 FR 62928). The retained the initial inspection requirement of
EASA AD 2008–0149, which was
DATES: This AD becomes effective NPRM was prompted by a superseded, reduced the compliance time of
October 27, 2015. determination that certain elevator the initial inspection and introduced a
The Director of the Federal Register servo-control parts that do not conform repetitive inspection programme.
approved the incorporation by reference to the approved type design have been After EASA AD 2010–0046R1 (http://
of a certain publication listed in this AD installed and may have the potential of ad.easa.europa.eu/blob/easa_ad_2010_0046_
as of October 27, 2015. cracks in the rod eye-end. The NPRM R1_superseded.pdf/AD_2010-0046R1_1) was
The Director of the Federal Register proposed to continue to require issued, a new elevator servo-control rod eye-
approved the incorporation by reference repetitive inspections of the left-hand end was developed, incorporating a re-
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greasable roller bearing.
of a certain other publication listed in and right-hand inboard and outboard
Consequently, EASA issued [EASA] AD
this AD as of October 21, 2011 (76 FR elevator servo-control rod eye-ends for 2013–0309 (later corrected) (http://
57630, September 16, 2011). cracking, and corrective actions if ad.easa.europa.eu/blob/easa_ad_2013_0309_
The Director of the Federal Register necessary. The NPRM also proposed to superseded.pdf/AD_2013-0309_1), retaining
approved the incorporation by reference require an inspection to determine if the requirements of EASA AD 2010–0046R1,
of a certain other publication listed in certain elevator servo-control parts are which was superseded, and introduced an
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![Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations 57087
optional terminating action for the repetitive eye-ends are affected. However, burden on any operator or increase the
inspections by replacing the existing elevator paragraph (n) of this AD addresses the scope of this AD.
servo-control rod eye-ends with the new commenter’s concern. Paragraph (n) of
elevator servo-control rod eye-end. In Related Service Information Under 1
this AD identifies airplanes that are not
addition, that [EASA] AD prohibited, for CFR Part 51
aeroplanes that incorporate this optional
affected by the requirements of
paragraphs (g), (h), (k) and (l) of this AD. Airbus has issued Service Bulletin
modification, (re)installation of unmodified
elevator servo-controls. We have not changed this AD as A320–27–1223, dated September 3,
At the time that EASA AD 2013–0309 was requested by the commenter, but we 2013; and UTC Aerospace Systems
issued, it was planned that Airbus would have revised the heading of paragraph Service Bulletin 31075–27–22, dated
proceed with the certification of certain (n) of this AD to more accurately reflect July 2, 2013. The service information
elevator servo-controls, Part Number (P/N) the content of that paragraph. describes procedures for modifying and
31075–0xx, P/N 31075–1xx and P/N 31075– replacing the elevator servo-control eye-
3xx (originally certified only for installation Request To Permit the Use of end. This service information is
on Model A320–111 aeroplanes, which are Serviceable Parts, and Relocate the reasonably available because the
no longer in service), to allow installation of Definition of Serviceable Parts interested parties have access to it
those parts on other A320 family aeroplane
Models. UAL requested that we permit the use through their normal course of business
Since that [EASA] AD was issued, Airbus of serviceable parts in paragraph (l)(1) of or by the means identified in the
decided not to progress with certification of the proposed AD (79 FR 62928, October ADDRESSES section of this AD.
the affected elevator servo-controls for 21, 2014), and move the definition of a
Costs of Compliance
installation on other Models. serviceable part from paragraph (l)(2) of
For the reason described above, and the proposed AD to paragraph (l)(1) of We estimate that this AD affects 851
because of evidence that such parts remain the proposed AD. airplanes of U.S. registry.
available as spares in the field, this [EASA] We agree with the commenter’s The actions that are required by AD
AD retains the requirements of EASA AD requests. We have determined that the 2011–19–04, Amendment 39–16809 (76
2013–0309, which is superseded, and adds a FR 57630, September 16, 2011), and
prohibition to install the affected elevator
use of serviceable parts is acceptable as
replacement parts in paragraph (l)(1) of retained in this AD take about 25 work-
servo-controls that were only intended for
A320–111 aeroplanes. this AD. We have changed the wording hours per product, at an average labor
of paragraph (l)(1) of this AD to specify rate of $85 per work-hour. Based on
This AD requires an inspection to that serviceable parts may be used as these figures, the estimated cost of the
determine whether any elevator control replacement parts. We have also moved actions that are required by AD 2011–
part having P/N 31075–0xx, 31075–1xx, the definition of serviceable parts from 19–04 is $2,125 per product.
or 31075–3xx is installed, and paragraph (l)(2) of this AD to paragraph We also estimate that it would take
replacement if necessary. (l)(1) of this AD since both paragraphs about 14 work-hours per product to
You may examine the MCAI in the (l)(1) and (l)(2) of this AD specify the comply with the basic requirements of
AD docket on the Internet at http:// use of serviceable parts. this AD. The average labor rate is $85
www.regulations.gov/ per work-hour. Based on these figures,
#!documentDetail;D=FAA-2014-0753- Request To Revise Service Information we estimate the cost of this AD on U.S.
0002. Title operators to be $1,012,690, or $1,190 per
Comments UAL requested that we revise product.
paragraph (l)(2) of the proposed AD (79 In addition, we estimate that any
We gave the public the opportunity to FR 62928, October 21, 2014) to replace necessary follow-on actions would take
participate in developing this AD. The the service information nomenclature about 2 work-hours and require parts
following presents the comments from Goodrich Service Bulletin 31075– costing $4,000, for a cost of $4,170 per
received on the NPRM (79 FR 62928, 27–22, dated July 2, 2013, to UTC product. We have no way of
October 21, 2014) and the FAA’s Aerospace Systems Service Bulletin determining the number of aircraft that
response to each comment. 31075–27–22, dated July 2, 2013. might need this action.
Request To Clarify Affected Airplanes We agree with the commenter’s Authority for This Rulemaking
for Certain Proposed Requirements request. The requested service bulletin
title change is correct. We have revised Title 49 of the United States Code
United Airlines (UAL) requested that, paragraph (l)(2) of this AD accordingly. specifies the FAA’s authority to issue
for clarity reasons, we revise the rules on aviation safety. Subtitle I,
identity of affected airplanes in Conclusion section 106, describes the authority of
paragraphs (g) through (j) of the We reviewed the available data, the FAA Administrator. ‘‘Subtitle VII:
proposed AD (79 FR 62928, October 21, including the comments received, and Aviation Programs,’’ describes in more
2014) to pertain only to elevator servo- determined that air safety and the detail the scope of the Agency’s
controls having part number (P/N) public interest require adopting this AD authority.
341203 or P/N 341203–xxx rod eye- with the changes described previously We are issuing this rulemaking under
ends. UAL stated that per Airbus and minor editorial changes. We have the authority described in ‘‘Subtitle VII,
Service Bulletin A320–27A1186, determined that these changes: Part A, Subpart III, Section 44701:
Revision 07, dated March 2, 2011; and • Are consistent with the intent that General requirements.’’ Under that
Goodrich Service Bulletin 31075–27–22, was proposed in the NPRM (79 FR section, Congress charges the FAA with
dated July 2, 2013, it understands that 62928, October 21, 2014) for correcting promoting safe flight of civil aircraft in
only the rod eye-ends fitted with self- the unsafe condition; and air commerce by prescribing regulations
Lhorne on DSK5TPTVN1PROD with RULES
lubricating spherical bearings are • Do not add any additional burden for practices, methods, and procedures
required to have initial and repetitive upon the public than was already the Administrator finds necessary for
inspections for cracks. proposed in the NPRM (79 FR 62928, safety in air commerce. This regulation
We partially agree with the October 21, 2014). is within the scope of that authority
commenter’s request. We agree that only We also determined that these because it addresses an unsafe condition
certain elevator servo-controls and rod changes will not increase the economic that is likely to exist or develop on
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![57088 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations
products identified in this rulemaking 2015–19–08 Airbus: Amendment 39–18270; (B) Within 1,500 flight cycles after
action. Docket No. FAA–2014–0753; Directorate accumulating 10,000 total flight cycles since
Identifier 2014–NM–128–AD. first flight of the airplane.
Regulatory Findings (ii) For airplanes that have accumulated
(a) Effective Date less than 10,000 total flight cycles as of
We determined that this AD will not This AD becomes effective October 27, September 22, 2009 (the effective date of AD
have federalism implications under 2015. 2009–17–04, Amendment 39–15995 (74 FR
Executive Order 13132. This AD will 41611, August 18, 2009)): At the later of the
(b) Affected ADs
not have a substantial direct effect on times specified in paragraphs (g)(1)(ii)(A) and
the States, on the relationship between This AD replaces AD 2011–19–04, (g)(1)(ii)(B) of this AD.
Amendment 39–16809 (76 FR 57630, (A) Before the accumulation of 5,000 total
the national government and the States,
September 16, 2011). flight cycles.
or on the distribution of power and
(c) Applicability (B) Within 20 months after October 21,
responsibilities among the various 2011 (the effective date of AD 2011–19–04,
levels of government. This AD applies to the airplanes identified Amendment 39–16809 (76 FR 57630,
For the reasons discussed above, I in paragraphs (c)(1) through (c)(4) of this AD, September 16, 2011)) but no later than before
certify that this AD: certificated in any category, all manufacturer the accumulation of 11,500 total flight cycles.
serial numbers. (2) At the applicable time specified in
1. Is not a ‘‘significant regulatory (1) Airbus Model A318–111, –112, –121,
action’’ under Executive Order 12866; paragraphs (g)(2)(i) and (g)(2)(ii) of this AD:
and –122 airplanes. Inspect both the left-hand and right-hand
2. Is not a ‘‘significant rule’’ under the (2) Airbus Model A319–111, –112, –113, outboard elevator servo-control rod eye-ends
DOT Regulatory Policies and Procedures –114, –115, –131, –132, and –133 airplanes. for cracking, in accordance with the
(44 FR 11034, February 26, 1979); (3) Airbus Model A320–211, –212, –214, instructions of Airbus AOT A320–27A1186,
3. Will not affect intrastate aviation in –231, –232, and –233 airplanes. Revision 04, dated April 3, 2009; or the
(4) Airbus Model A321–111, –112, –131, Accomplishment Instructions of Airbus
Alaska; and –211, –212, –213, –231, and –232 airplanes. Service Bulletin A320–27A1186, Revision 07,
4. Will not have a significant
(d) Subject dated March 2, 2011. As of October 21, 2011
economic impact, positive or negative, (the effective date of AD 2011–19–04,
on a substantial number of small entities Air Transport Association (ATA) of Amendment 39–16809 (76 FR 57630,
under the criteria of the Regulatory America Code 27, Flight Controls. September 16, 2011)), use Airbus Service
Flexibility Act. (e) Reason Bulletin A320–27A1186, Revision 07, dated
March 2, 2011.
Examining the AD Docket This AD was prompted by a determination
(i) For airplanes that have accumulated
that certain elevator servo-control parts that
You may examine the AD docket on 10,000 total flight cycles or more as of
do not conform to the approved type design
the Internet at http:// have been installed and may have the September 22, 2009 (the effective date of AD
potential of cracks in the rod eye-end. We are 2009–17–04, Amendment 39–15995 (74 FR
www.regulations.gov/ 41611, August 18, 2009)): At the later of the
#!docketDetail;D=FAA-2014-0753; or in issuing this AD to detect and correct rod eye-
end cracking, which could result in times specified in paragraphs (g)(2)(i)(A) and
person at the Docket Management (g)(2)(i)(B) of this AD.
uncontrolled elevator surface and consequent
Facility between 9 a.m. and 5 p.m., reduced control of the airplane. (A) Within 3,000 flight cycles after
Monday through Friday, except Federal September 22, 2009 (the effective date of AD
holidays. The AD docket contains this (f) Compliance 2009–17–04, Amendment 39–15995 (74 FR
AD, the regulatory evaluation, any Comply with this AD within the 41611, August 18, 2009)).
comments received, and other compliance times specified, unless already (B) Within 3,000 flight cycles after
done. accumulating 10,000 total flight cycles since
information. The street address for the first flight of the airplane.
Docket Operations office (telephone (g) Retained Inspections (ii) For airplanes that have accumulated
800–647–5527) is in the ADDRESSES This paragraph restates the requirements of less than 10,000 total flight cycles as of
section. paragraph (g) of AD 2011–19–04, September 22, 2009 (the effective date of AD
Amendment 39–16809 (76 FR 57630, 2009–17–04, Amendment 39–15995 (74 FR
List of Subjects in 14 CFR Part 39 41611, August 18, 2009)): At the later of the
September 16, 2011), with no changes.
Air transportation, Aircraft, Aviation (1) At the applicable times specified in times specified in paragraphs (g)(2)(ii)(A) and
safety, Incorporation by reference, paragraphs (g)(1)(i) and (g)(1)(ii) of this AD: (g)(2)(ii)(B) of this AD.
Inspect both the left-hand and right-hand (A) Before the accumulation of 7,500 total
Safety.
inboard elevator servo-control rod eye-ends flight cycles.
Adoption of the Amendment for cracking, in accordance with the (B) Within 40 months after October 21,
instructions of Airbus All Operators Telex 2011 (the effective date of AD 2011–19–04,
Accordingly, under the authority (AOT) A320–27A1186, Revision 04, dated Amendment 39–16809 (76 FR 57630,
delegated to me by the Administrator, April 3, 2009; or the Accomplishment September 16, 2011)), but no later than before
the FAA amends 14 CFR part 39 as Instructions of Airbus Service Bulletin A320– the accumulation of 13,000 total flight cycles.
follows: 27A1186, Revision 07, dated March 2, 2011.
As of October 21, 2011 (the effective date of (h) Retained Repetitive Inspections
PART 39—AIRWORTHINESS AD 2011–19–04, Amendment 39–16809 (76 This paragraph restates the requirements of
DIRECTIVES FR 57630, September 16, 2011)), use Airbus paragraph (h) of AD 2011–19–04,
Service Bulletin A320–27A1186, Revision 07, Amendment 39–16809 (76 FR 57630,
dated March 2, 2011. September 16, 2011), with no changes.
■ 1. The authority citation for part 39 Repeat the inspections of the left-hand and
(i) For airplanes that have accumulated
continues to read as follows: 10,000 total flight cycles or more as of right-hand inboard and outboard elevator
Authority: 49 U.S.C. 106(g), 40113, 44701. September 22, 2009 (the effective date of AD servo-control rod eye-ends for cracking as
2009–17–04, Amendment 39–15995 (74 FR required by paragraphs (g)(1) and (g)(2) of
Lhorne on DSK5TPTVN1PROD with RULES
§ 39.13 [Amended] 41611, August 18, 2009)): At the later of the this AD at the later of the times specified in
times specified in paragraphs (g)(1)(i)(A) and paragraph (h)(1) or (h)(2) of this AD. Repeat
■ 2. The FAA amends § 39.13 by (g)(1)(i)(B) of this AD. the inspections thereafter at intervals not to
removing Airworthiness Directive (AD) (A) Within 1,500 flight cycles after exceed 5,000 flight cycles.
2011–19–04, Amendment 39–16809 (76 September 22, 2009 (the effective date of AD (1) Within 5,000 flight cycles after the last
FR 57630, September 16, 2011), and 2009–17–04, Amendment 39–15995 (74 FR inspection required by paragraph (g)(1) or
adding the following new AD: 41611, August 18, 2009)). (g)(2) of this AD as applicable.
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![57090 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Rules and Regulations
(2) Contacting the Manufacturer: For any the availability of this material at NARA, call into class I or II, or FDA issues an order
requirement in this AD to obtain corrective 202–741–6030, or go to: http:// finding the device to be substantially
actions from a manufacturer, the action must www.archives.gov/federal-register/cfr/ibr- equivalent, in accordance with section
be accomplished using a method approved locations.html. 513(i), to a predicate device that does
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
Issued in Renton, Washington, on not require premarket approval. The
September 11, 2015. Agency determines whether new
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the Michael Kaszycki, devices are substantially equivalent to
DOA-authorized signature. Acting Manager, Transport Airplane predicate devices by means of
Directorate, Aircraft Certification Service. premarket notification procedures in
(r) Related Information
[FR Doc. 2015–23541 Filed 9–21–15; 8:45 am] section 510(k) of the FD&C Act (21
(1) Refer to Mandatory Continuing BILLING CODE 4910–13–P U.S.C. 360(k)) and part 807 (21 CFR part
Airworthiness Information (MCAI) EASA 807) of the regulations.
Airworthiness Directive 2014–0137, dated Section 513(f)(2) of the FD&C Act (21
May 28, 2014, for related information. This U.S.C. 360c(f)(2)), as amended by
MCAI may be found in the AD docket on the DEPARTMENT OF HEALTH AND
Internet at http://www.regulations.gov by HUMAN SERVICES section 607 of the Food and Drug
searching for and locating Docket No. FAA– Administration Safety and Innovation
2014–0753. Food and Drug Administration Act (Pub. L. 112–144), provides two
(2) Airbus Service information identified in procedures by which a person may
this AD that is not incorporated by reference 21 CFR Part 886 request FDA to classify a device under
is available at the addresses specified in the criteria set forth in section 513(a)(1).
paragraphs (s)(6) and (s)(8) of this AD. [Docket No. FDA–2015–N–3044] Under the first procedure, the person
(s) Material Incorporated by Reference submits a premarket notification under
Medical Devices; Ophthalmic Devices;
section 510(k) of the FD&C Act for a
(1) The Director of the Federal Register Classification of the Oral Electronic
approved the incorporation by reference
device that has not previously been
Vision Aid
(IBR) of the service information listed in this classified and, within 30 days of
paragraph under 5 U.S.C. 552(a) and 1 CFR AGENCY: Food and Drug Administration, receiving an order classifying the device
part 51. HHS. into class III under section 513(f)(1), the
(2) You must use this service information ACTION: Final order. person requests a classification under
as applicable to do the actions required by section 513(f)(2). Under the second
this AD, unless this AD specifies otherwise. SUMMARY: The Food and Drug procedure, rather than first submitting a
(3) The following service information was Administration (FDA) is classifying the premarket notification under section
approved for IBR on October 27, 2015. 510(k) and then a request for
oral electronic vision aid into class II
(i) Airbus Service Bulletin A320–27–1223,
(special controls). The special controls classification under the first procedure,
dated September 3, 2013.
(ii) UTC Aerospace Systems Service that will apply to the device are the person determines that there is no
Bulletin 31075–27–22, dated July 2, 2013. identified in this order and will be part legally marketed device upon which to
(4) The following service information was of the codified language for the oral base a determination of substantial
approved for IBR on October 21, 2011 (76 FR electronic vision aid’s classification. equivalence and requests a classification
57630, September 16, 2011). The Agency is classifying the device under section 513(f)(2) of the FD&C Act.
(i) Airbus Service Bulletin A320–27A1186, into class II (special controls) in order If the person submits a request to
Revision 07, including Appendices 1, 2, 3, 4, to provide a reasonable assurance of classify the device under this second
5, and 6, dated March 2, 2011. procedure, FDA may decline to
safety and effectiveness of the device.
(ii) Reserved. undertake the classification request if
(5) The following service information was DATES: This order is effective September
22, 2015. The classification was FDA identifies a legally marketed device
approved for IBR on September 22, 2009 (74
FR 41611, August 18, 2009). applicable on June 18, 2015. that could provide a reasonable basis for
(i) Airbus All Operators Telex A320– review of substantial equivalence with
FOR FURTHER INFORMATION CONTACT: the device or if FDA determines that the
27A1186, Revision 04, dated April 3, 2009.
Dexiu Shi, Center for Devices and device submitted is not of ‘‘low-
The document number and issue date of
Airbus AOT A320–27A1186, Revision 04, Radiological Health, Food and Drug moderate risk’’ or that general controls
dated April 3, 2009, are specified only on the Administration, 10903 New Hampshire would be inadequate to control the risks
first page of the AOT. Ave., Bldg. 66, Rm. 2246, Silver Spring, and special controls to mitigate the risks
(ii) Reserved. MD, 20993–0002, 301–796–6470, cannot be developed.
(6) For Airbus service information dexiu.shi@fda.hhs.gov. In response to a request to classify a
identified in this AD, contact Airbus, SUPPLEMENTARY INFORMATION: device under either procedure provided
Airworthiness Office—EIAS, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex, I. Background by section 513(f)(2) of the FD&C Act,
France; telephone +33 5 61 93 36 96; fax +33 FDA will classify the device by written
5 61 93 44 51; email account.airworth-eas@ In accordance with section 513(f)(1) of order within 120 days. This
airbus.com; Internet http://www.airbus.com. the Federal Food, Drug, and Cosmetic classification will be the initial
(7) For UTC service information identified Act (the FD&C Act) (21 U.S.C. classification of the device.
in this AD, contact UTC Aerospace Systems; 360c(f)(1)), devices that were not in On August 7, 2013, Wicab Inc.,
Roger Dangremont; telephone +01 34 32 63 commercial distribution before May 28, submitted a request for classification of
28; email roger.dangrement@goodrich.com. 1976 (the date of enactment of the the BrainPort V100 under section
(8) You may view this service information Medical Device Amendments of 1976), 513(f)(2) of the FD&C Act. The
at the FAA, Transport Airplane Directorate, generally referred to as postamendments manufacturer recommended that the
Lhorne on DSK5TPTVN1PROD with RULES
1601 Lind Avenue SW., Renton, WA. For devices, are classified automatically by
information on the availability of this
device be classified into class II (Ref. 1).
material at the FAA, call 425–227–1221.
statute into class III without any FDA In accordance with section 513(f)(2) of
(9) You may view this service information rulemaking process. These devices the FD&C Act, FDA reviewed the
that is incorporated by reference at the remain in class III and require request in order to classify the device
National Archives and Records premarket approval, unless and until under the criteria for classification set
Administration (NARA). For information on the device is classified or reclassified forth in section 513(a)(1). FDA classifies
VerDate Sep<11>2014 13:50 Sep 21, 2015 Jkt 235001 PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 E:\FR\FM\22SER1.SGM 22SER1](https://thefederalregister.org/doc/80_FR_57269/page/5.svg)
Document Created: 2015-12-15 09:36:01
Document Modified: 2015-12-15 09:36:01
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD becomes effective October 27, 2015. | |
| 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. | |
| FR Citation | 80 FR 57086 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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