Airworthiness Directives; Airbus Airplanes, 62928-62932 [2014-25023]

Download as PDF 62928 Federal Register / Vol. 79, No. 203 / Tuesday, October 21, 2014 / Proposed Rules including any personal information provided in the comments (except information deemed to be exempt from public disclosure). mstockstill on DSK4VPTVN1PROD with PROPOSALS C. Issues on Which DOE Seeks Comment Although DOE welcomes comments on any aspect of this proposed determination, DOE is particularly interested in receiving comments and views of interested parties concerning the following issues: 1. The HID lamps selected for and excluded from analysis of economic justification for standards; 2. The technology options analyzed and in particular the elimination of sapphire arc tubes and starting method as technology option(s); 3. The equipment classes analyzed in this NOPD; 4. The design options identified in the screening analysis; 5. The representative equipment classes analyzed in this NOPD; 6. The baseline lamps selected, including the inclusion of a 150 W MH lamp; 7. The selection of more efficacious substitute lamps analyzed in this NOPD; 8. The decision to analyze equal wattage replacement lamps, as well as the methodology used to select the equal wattage replacement lamps; 9. The methodology used to determine ELs, as well as the resulting ELs analyzed in this NOPD; 10. The factors used in this NOPD to scale to equipment classes not directly analyzed; 11. The decision to include replacement pathways other than full fixture replacement in this NOPD; 12. The results and methodology from the equipment price determination; 13. Methods to improve DOE’s energy use analysis, as well as any data supporting alternate operating hour estimates or assumptions regarding dimming of HID lamp-and-ballast systems; 14. The assumptions and methodology for estimating annual operating hours, which were based on data from the 2010 U.S. Lighting Market Characterization; 15. Methods to improve DOE’s equipment price projections beyond the assumption of constant real prices, as well as any data supporting alternate methods; 16. The reasonableness of assuming a zero percent rebound effect (the potential tendency for customers to increase HID lamp usage in response to more efficient lamp-and-ballast systems); VerDate Sep<11>2014 17:11 Oct 20, 2014 Jkt 235001 17. Whether the shipment scenarios under various policy scenarios are reasonable and likely to occur; 18. The impediments that prevent users of HID lamps from switching to LED lighting to garner further energy savings; 19. The expected impact of potential standards on the rate at which HID lamp customers transition to non-HID technology; 20. The methodology used in the MIA and the results of the MIA; 21. The proposal of a negative determination stating that standards for HID lamps are not justified. [Docket No. FAA–2014–0753; Directorate Identifier 2014–NM–128–AD] have been installed and may have the potential of cracks in the rod eye-end. This proposed AD would also require an inspection to determine if certain elevator servo-control parts are installed, and replacement if necessary. We are proposing this AD to detect and correct rod eye-end cracking, which could result in an uncontrolled elevator surface and consequent reduced control of the airplane. DATES: We must receive comments on this proposed AD by December 5, 2014. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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. 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. RIN 2120–AA64 Examining the AD Docket VIII. Approval of the Office of the Secretary The Secretary of Energy has approved publication of this NOPD. List of Subjects in 10 CFR Part 431 Administrative practice and procedure, Confidential business information, Energy conservation, and Reporting and recordkeeping requirements. Issued in Washington, DC, on October 10, 2014. Kathleen B. Hogan, Deputy Assistant Secretary for Energy Efficiency, Energy Efficiency and Renewable Energy. [FR Doc. 2014–24971 Filed 10–20–14; 8:45 am] BILLING CODE 6450–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2011–19– 04, for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2011–19–04 currently requires 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. Since we issued AD 2011– 19–04, we have determined that certain elevator servo-control parts that do not conform to the approved type design SUMMARY: PO 00000 Frm 00038 Fmt 4702 Sfmt 4702 You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA E:\FR\FM\21OCP1.SGM 21OCP1 Federal Register / Vol. 79, No. 203 / Tuesday, October 21, 2014 / Proposed Rules 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2014–0753; Directorate Identifier 2014–NM–128–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. mstockstill on DSK4VPTVN1PROD with PROPOSALS Discussion On September 7, 2011, we issued AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011). AD 2011–19–04 requires actions intended to address an unsafe condition on all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2011–19–04 superseded AD 2009–17–04, Amendment 39–15995 (74 FR 41611, August 18, 2009). Since we issued AD 2011–19–04, Amendment 39–16809 (76 FR 57630, September 16, 2011), the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, 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 for all Model A318, A319, A320, and Model A321 series airplanes. 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. VerDate Sep<11>2014 17:11 Oct 20, 2014 Jkt 235001 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 39–5995 (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 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 proposed AD would require an inspection to determine whether any elevator control part having P/N 31075– 0xx, 31075–1xx, or 31075–3xx is PO 00000 Frm 00039 Fmt 4702 Sfmt 4702 62929 installed and replacement if necessary. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0753. Relevant Service Information Airbus has issued Service Bulletin A320–27–1223, dated September 3, 2013. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This Proposed AD and the MCAI or Service Information The MCAI does not include an action for airplanes installed with elevator control parts having part number (P/N) 31075–0xx, 31075–1xx, or 31075–3xx. This proposed AD would require an inspection to determine if those elevator servo-control parts are installed, and replacement if necessary. Costs of Compliance We estimate that this proposed 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 proposed 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 proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed 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 E:\FR\FM\21OCP1.SGM 21OCP1 62930 Federal Register / Vol. 79, No. 203 / Tuesday, October 21, 2014 / Proposed Rules 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 proposed regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: 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. mstockstill on DSK4VPTVN1PROD with PROPOSALS List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ VerDate Sep<11>2014 17:11 Oct 20, 2014 Jkt 235001 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: ■ Airbus: Docket No. FAA–2014–0753; Directorate Identifier 2014–NM–128–AD. (a) Comments Due Date We must receive comments by December 5, 2014. (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 Airbus 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 PO 00000 Frm 00040 Fmt 4702 Sfmt 4702 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 E:\FR\FM\21OCP1.SGM 21OCP1 62931 Federal Register / Vol. 79, No. 203 / Tuesday, October 21, 2014 / Proposed Rules 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. (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)). (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. (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. (l) New Requirement of This AD: Replacement of Certain Parts (j) Retained Parts 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. (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 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 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). (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 Instruction of Airbus Service Bulletin A320– 27–1223, dated September 3, 2013, or Goodrich Service Bulletin 31075–27–22, dated July 2, 2013. 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. (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 is applicable to elevator servo-controls having P/N 31075– 6xx or P/N 31075–8xx. (n) New Exception to Certain Inspections 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-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 table 1 to paragraph (o)(1)(i) of this AD. TABLE 1 TO PARAGRAPH (o)(1)(i) OF THIS AD—CREDIT SERVICE INFORMATION FOR PARAGRAPH (g) OF THIS AD Airbus AOT— Revision— mstockstill on DSK4VPTVN1PROD with PROPOSALS A320–27A1186 A320–27A1186 A320–27A1186 A320–27A1186 A320–27A1186 ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... ............................................................................................................................................... (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. (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 VerDate Sep<11>2014 17:11 Oct 20, 2014 Jkt 235001 57630, September 16, 2011)), using Airbus Service Bulletin A320–27A1186, Revision 06, dated December 14, 2010. (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 PO 00000 Frm 00041 Fmt 4702 Sfmt 4702 Dated— Original ............... 01 ....................... 02 ....................... 03 ....................... 04 ....................... June 23, 2008. August 11, 2008. March 30, 2009. April 1, 2009. April 3, 2009. (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: E:\FR\FM\21OCP1.SGM 21OCP1 62932 Federal Register / Vol. 79, No. 203 / Tuesday, October 21, 2014 / Proposed Rules (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. (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 Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. mstockstill on DSK4VPTVN1PROD with PROPOSALS (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) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet https://www.airbus.com. 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. DEPARTMENT OF HEALTH AND HUMAN SERVICES ENVIRONMENTAL PROTECTION AGENCY Food and Drug Administration 40 CFR Part 52 21 CFR Part 73 [EPA–R09–OAR–2014–0711; FRL–9917–80– Region 9] [Docket No. FDA–2014–C–1616] EMD Millipore Corp.; Filing of Color Additive Petition AGENCY: Food and Drug Administration, HHS. ACTION: Notice of petition. The Food and Drug Administration (FDA or we) is announcing that we have filed a petition, submitted by EMD Millipore Corp., proposing that the color additive regulations be amended to expand the safe use of mica-based pearlescent pigments in alcoholic beverages to include cordials, liqueurs, cocktails, and certain other alcoholic beverages, and non-alcoholic mixers and mixes. SUMMARY: The color additive petition was filed on August 21, 2014. DATES: FOR FURTHER INFORMATION CONTACT: Ellen Anderson, Center for Food Safety and Applied Nutrition (HFS–265), Food and Drug Administration, 5100 Paint Branch Pkwy., College Park, MD 20740– 3835, 240–402–1309. Under section 721(d)(1) of the Federal Food, Drug, and Cosmetic Act (21 U.S.C. 379e(d)(1)), we are giving notice that we have filed a color additive petition (CAP 4C0299), submitted by EMD Millipore Corp., c/o Hyman, Phelps & McNamara, P.C., 700 13th Street NW., Suite 1200, Washington, DC 20005. The petition proposes to amend the color additive regulations in 21 CFR 73.350, Micabased pearlescent pigments, to expand the safe use of mica-based pearlescent pigments in alcoholic beverages to include cordials, liqueurs, cocktails, and certain other alcoholic beverages, and non-alcoholic mixers and mixes. We have determined under 21 CFR 25.32(k) that this action is of a type that does not individually or cumulatively have a significant effect on the human environment. Therefore, neither an environmental assessment nor an environmental impact statement is required. SUPPLEMENTARY INFORMATION: Issued in Renton, Washington, on October 13, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. Dated: October 16, 2014. Dennis M. Keefe, Director, Office of Food Additive Safety, Center for Food Safety and Applied Nutrition. [FR Doc. 2014–25023 Filed 10–20–14; 8:45 am] [FR Doc. 2014–24962 Filed 10–20–14; 8:45 am] BILLING CODE 4910–13–P BILLING CODE 4164–01–P VerDate Sep<11>2014 17:11 Oct 20, 2014 Jkt 235001 PO 00000 Frm 00042 Fmt 4702 Sfmt 4702 Approval and Promulgation of Implementation Plans; Revisions to the Nevada State Implementation Plan; Stationary Source Permits Environmental Protection Agency (EPA). ACTION: Proposed rule. AGENCY: The Environmental Protection Agency (EPA) is proposing to approve revisions to the applicable state implementation plan for the State of Nevada submitted by the Nevada Division of Environmental Protection. The revisions include amended State rules related to applications for, and issuance of, permits for stationary sources, but not including review and permitting of major sources and major modifications under parts C and D of title I of the Clean Air Act. EPA is taking action under the Clean Air Act obligation to take action on State submittals of revisions to state implementation plans. The intended effect of the proposed approval is to fix deficiencies in the previously-approved version of the permitting rules and to ensure that new or modified stationary sources do not interfere with attainment or maintenance of the national ambient air quality standards. DATES: Any comments must arrive by November 20, 2014. ADDRESSES: Submit comments, identified by docket number EPA–R09– OAR–2014–0711, by one of the following methods: 1. Federal eRulemaking Portal: www.regulations.gov. Follow the on-line instructions. 2. Email: R9airpermits@epa.gov. 3. Mail or deliver: Laura Yannayon (AIR–3), U.S. Environmental Protection Agency Region IX, 75 Hawthorne Street, San Francisco, CA 94105–3901. Instructions: All comments will be included in the public docket without change and may be made available online at www.regulations.gov, including any personal information provided, unless the comment includes Confidential Business Information (CBI) or other information whose disclosure is restricted by statute. Information that you consider CBI or otherwise protected should be clearly identified as such and should not be submitted through www.regulations.gov or email. www.regulations.gov is an ‘‘anonymous access’’ system, and EPA will not know SUMMARY: E:\FR\FM\21OCP1.SGM 21OCP1

Agencies

[Federal Register Volume 79, Number 203 (Tuesday, October 21, 2014)]
[Proposed Rules]
[Pages 62928-62932]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-25023]


=======================================================================
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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]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2011-19-
04, for all Airbus Model A318, A319, A320, and A321 series airplanes. 
AD 2011-19-04 currently requires 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. Since we 
issued AD 2011-19-04, we have determined 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. This 
proposed AD would also require an inspection to determine if certain 
elevator servo-control parts are installed, and replacement if 
necessary. We are proposing this AD to detect and correct rod eye-end 
cracking, which could result in an uncontrolled elevator surface and 
consequent reduced control of the airplane.

DATES: We must receive comments on this proposed AD by December 5, 
2014.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed 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. 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA

[[Page 62929]]

98057-3356; telephone 425-227-1405; fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0753; 
Directorate Identifier 2014-NM-128-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On September 7, 2011, we issued AD 2011-19-04, Amendment 39-16809 
(76 FR 57630, September 16, 2011). AD 2011-19-04 requires actions 
intended to address an unsafe condition on all Airbus Model A318, A319, 
A320, and A321 series airplanes. AD 2011-19-04 superseded AD 2009-17-
04, Amendment 39-15995 (74 FR 41611, August 18, 2009).
    Since we issued AD 2011-19-04, Amendment 39-16809 (76 FR 57630, 
September 16, 2011), the European Aviation Safety Agency (EASA), which 
is the Technical Agent for the Member States of the European Community, 
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 for all 
Model A318, A319, A320, and Model A321 series airplanes. 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 39-5995 (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 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 proposed AD would require 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 by searching 
for and locating Docket No. FAA-2014-0753.

Relevant Service Information

    Airbus has issued Service Bulletin A320-27-1223, dated September 3, 
2013. The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This Proposed AD and the MCAI or Service 
Information

    The MCAI does not include an action for airplanes installed with 
elevator control parts having part number (P/N) 31075-0xx, 31075-1xx, 
or 31075-3xx. This proposed AD would require an inspection to determine 
if those elevator servo-control parts are installed, and replacement if 
necessary.

Costs of Compliance

    We estimate that this proposed 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 proposed 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 proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed 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

[[Page 62930]]

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 proposed regulation is 
within the scope of that authority because it addresses an unsafe 
condition that is likely to exist or develop on products identified in 
this rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:

Airbus: Docket No. FAA-2014-0753; Directorate Identifier 2014-NM-
128-AD.

(a) Comments Due Date

    We must receive comments by December 5, 2014.

(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 Airbus 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

[[Page 62931]]

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.
    (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 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 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).
    (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 
Instruction of Airbus Service Bulletin A320-27-1223, dated September 
3, 2013, or Goodrich Service Bulletin 31075-27-22, dated July 2, 
2013. 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.

(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 is applicable to elevator servo-
controls having P/N 31075-6xx or P/N 31075-8xx.

(n) New Exception to Certain Inspections

    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-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 table 1 to paragraph (o)(1)(i) of 
this AD.

       Table 1 to Paragraph (o)(1)(i) of This AD--Credit Service Information for Paragraph (g) of This AD
----------------------------------------------------------------------------------------------------------------
               Airbus AOT--                            Revision--                           Dated--
----------------------------------------------------------------------------------------------------------------
A320-27A1186.............................  Original..........................  June 23, 2008.
A320-27A1186.............................  01................................  August 11, 2008.
A320-27A1186.............................  02................................  March 30, 2009.
A320-27A1186.............................  03................................  April 1, 2009.
A320-27A1186.............................  04................................  April 3, 2009.
----------------------------------------------------------------------------------------------------------------

    (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.
    (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.

(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:

[[Page 62932]]

    (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.
    (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 Design Organization Approval (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) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. 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.

    Issued in Renton, Washington, on October 13, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-25023 Filed 10-20-14; 8:45 am]
BILLING CODE 4910-13-P