80 FR 23232 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 80 (April 27, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 80 (April 27, 2015)
| Page Range | 23232-23237 | |
| FR Document | 2015-09465 |
[Federal Register Volume 80, Number 80 (Monday, April 27, 2015)] [Rules and Regulations] [Pages 23232-23237] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-09465] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0930; Directorate Identifier 2015-NM-040-AD; Amendment 39-18144; AD 2015-08-08] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). [[Page 23233]] ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2014-26-53 and AD 2015-03-02 for certain Airbus Model A319-115, A319-133, A320-214, A320-232, and A320-233 airplanes. AD 2014-26-53 required repetitive detailed visual inspections to detect discrepancies of the wing lower skin surface and inboard main landing gear (MLG) support rib lower flange location fasteners and, depending on findings, accomplishment of applicable corrective action(s). AD 2015-03-02 required repetitive detailed visual inspections of the outboard MLG support rib lower flange fasteners for discrepancies, and corrective actions if necessary. This new AD retains the repetitive detailed visual inspections to detect discrepancies of the fasteners located in the wing lower skin surface and inboard MLG support rib lower flange with extended compliance times and repetitive intervals, and accomplishment of applicable corrective actions. This new AD also retains the repetitive detailed visual inspections of the outboard MLG support rib lower flange fasteners for discrepancies, and corrective actions if necessary. In addition, this new AD adds airplanes to the applicability. This AD was prompted by a determination that certain airplanes were missing from the applicability of AD 2014-26-53 and AD 2015-03-02 and that those airplanes may be affected by the unsafe condition addressed in AD 2014-26-53 and AD 2015-03-02. We are issuing this AD to detect and correct discrepancies of the fasteners at the external surface of the lower wing skin and inboard and outboard MLG support rib lower flanges, which could result in an airplane not meeting its maximum loads expected in service. This condition could result in structural failure. DATES: This AD becomes effective May 12, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 12, 2015. We must receive comments on this AD by June 11, 2015. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Portal: Go to http://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 AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. 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-2015- 0930. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 0930; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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 On January 7, 2015, we issued AD 2014-26-53, Amendment 39-18068 (80 FR 3155, January 22, 2015). AD 2014-26-53 applied to certain Airbus Model A319-115, A319-133, A320-214, A320-232, and A320-233 airplanes. AD 2014-26-53 was prompted by reports of failure of certain fasteners located at the wing lower skin surface and inboard MLG support rib lower flange. AD 2014-26-53 required repetitive detailed visual inspections to detect discrepancies of the wing lower skin surface and inboard MLG support rib lower flange location fasteners and, depending on findings, accomplishment of applicable corrective action(s). We issued AD 2014-26-53 to detect and correct discrepancies of the fasteners at the external surface of the lower wing skin and inboard MLG support rib lower flange, which could result in an airplane not meeting its maximum loads expected in service. This condition could result in structural failure. On January 30, 2015, we issued AD 2015-03-02, Amendment 39-18098 (80 FR 6897, February 9, 2015). AD 2015-03-02 applied to certain Airbus Model A319-115, A319-133, A320-214, A320-232, and A320-233 airplanes. AD 2015-03-02 was prompted by reports of failure of certain fasteners on the MLG support rib lower flange. AD 2015-03-02 required repetitive detailed visual inspections of the outboard MLG support rib lower flange fasteners for discrepancies, and corrective actions if necessary. We issued AD 2015-03-02 to detect and correct discrepancies of the fasteners at the outboard MLG support rib lower flange, which could result in an airplane not meeting its maximum loads expected in service. This condition could result in structural failure. Since we issued AD 2014-26-53, Amendment 39-18068 (80 FR 3155, January 22, 2015); and AD 2015-03-02, Amendment 39-18098 (80 FR 6897, February 9, 2015); we have determined that certain airplanes were missing from the applicability of AD 2014-26-53 and AD 2015-03-02. Airbus Model A319-132 airplanes are affected with the identified unsafe condition and should have been included in the applicability of those ADs. In addition, we have also determined that the repetitive detailed visual inspections to detect discrepancies of the wing lower skin surface and inboard MLG support rib lower flange could be extended from 8-day intervals to 60-day intervals. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0026, dated February 19, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A319-115, A319-132, A319-133, A320-214, A320-232, and A320-233 airplanes. The MCAI states: During production of wings, a number of taperlok fasteners were found failed after installation. The fasteners in question are located at the bottom skin of the Main Landing Gear (MLG) reinforcing plate, wing skin and Gear Support Rib 5 lower flange. Based on the results of the preliminary investigation, this affects only certain A319 [[Page 23234]] and A320 aeroplanes delivered since January 2014. This condition, if not detected and corrected could reduce the design safety margin of the structure. Prompted by these findings, EASA issued Emergency AD 2014-0270-E (later revised) [which corresponds to certain requirements of AD 2014-26-53, Amendment 39-18068 (80 FR 3155, January 22, 2015)] to require repetitive detailed inspections (DET) of the bottom skin taperlok fasteners at the MLG Rib 5 footprint location and, depending on findings, accomplishment of applicable corrective action(s). Since EASA AD 2014-0270R1 [which corresponds to certain requirements of AD 2015-03-02, Amendment 39-18098 (80 FR 6897, February 19, 2015)] was issued, based on in service feedback and further investigation, Airbus issued Revision 01 of Alert Operators Transmission (AOT) A57N006-14 to extend the original 8 calendar days inspection interval to 60 calendar days for the external area and for the internal inboard side. In addition, it was identified that the model A319-132 was missing from the [EASA] AD applicability. For the reasons described above, this AD retains the requirements of EASA AD 2014-0270R1, which is superseded, to amend the Applicability and to require those actions within the new thresholds and intervals. This [EASA] AD is still considered to be an interim action and further [EASA] AD action may follow. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 0930. Related Service Information Under 1 CFR Part 51 Airbus has issued Airbus Alert Operators Transmission (AOT) A57N006-14, Revision 01, dated February 16, 2015. The service information describes procedures for repetitive detailed visual inspections to detect discrepancies of the wing lower skin surface and inboard and outboard MLG support rib lower flange location fasteners and corrective actions. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 0930. Or see ADDRESSES for other ways to access this service information. FAA's Determination and Requirements of This 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 issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs. FAA's Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because failure of more than two fasteners at the outboard MLG support rib lower flange could result in an airplane not meeting its maximum loads expected in-service. This condition could result in failure of the structure. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-0930; Directorate Identifier 2015-NM-040-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD affects 148 airplanes of U.S. registry. The actions required by AD 2014-26-53, Amendment 39-18068 (80 FR 3155, January 22, 2015); and AD 2015-03-2, Amendment 39-18098 (80 FR 6897, February 9, 2015); and retained in this AD, take about 2 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 were required by AD 2014-26-53 and AD 2015-03-06 is $170 per product, per inspection cycle. We also estimate that it will take about 2 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 $25,160, or $170 per product, per inspection cycle. In addition, we estimate that any fastener replacement will take about 3 work-hours and require parts costing $400, for a cost of $655 per fastener replacement. We have no way of determining the number of aircraft that might need these actions. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. [[Page 23235]] 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: 0 a. Removing Airworthiness Directive (AD) 2014-26-53, Amendment 39-18068 (80 FR 3155, January 22, 2015); and AD 2015-03-02, Amendment 39-18098 (80 FR 6897, February 9, 2015; and 0 b. Adding the following new AD: 2015-08-08 Airbus: Amendment 39-18144. Docket No. FAA-2015-0930; Directorate Identifier 2015-NM-040-AD. (a) Effective Date This AD becomes effective May 12, 2015. (b) Affected ADs This AD replaces the following: (1) AD 2014-26-53, Amendment 39-18068 (80 FR 3155, January 22, 2015). (2) AD 2015-03-02, Amendment 39-18098 (80 FR 6897, February 9, 2015). (c) Applicability This AD applies to Airbus Model A319-115, A319-132, A319-133, A320-214, A320-232, and A320-233 airplanes, certificated in any category, manufacturer serial numbers (MSN) 5817, 5826, 5837, 5848, 5855, 5864, 5875, 5886, 5896, 5910, and 5918 and subsequent. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a determination that certain airplanes were not included in the applicability of AD 2014-26-53, Amendment 39-18068 (80 FR 3155, January 22, 2015); and AD 2015-03-02, Amendment 39-18098 (80 FR 6897, February 9, 2015). This AD was also prompted by reports of failure of certain fasteners located at the wing lower skin surface, and inboard and outboard main landing gear (MLG) support rib lower flanges. We are issuing this AD to detect and correct discrepancies of the fasteners at the external surface of the lower wing skin and inboard and outboard MLG support rib lower flanges, which could result in an airplane not meeting its maximum loads expected in service. This condition could result in structural failure. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained for All Airplanes Except Airbus Model A319-132 Airplanes: Repetitive Inspections, With Extended Compliance Time and New Service Information This paragraph restates the requirements of paragraph (g) of AD 2014-26-53, Amendment 39-18068 (80 FR 3155, January 22, 2015), with an extended compliance time and new service information. For Airbus Model A319-115, A319-133, A320-214, A320-232, and A320-233 airplanes: Within 60 days after February 6, 2015 (the effective date of AD 2014-26-53), or within 60 days since the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness, or before further flight for any airplane that is not in operation for more than 60 days, whichever occurs later: Do the inspections required by paragraphs (g)(1) and (g)(2) of this AD, in accordance with Airbus Alert Operators Transmission (AOT) A57N006-14, Revision 00, dated December 4, 2014; or Airbus AOT A57N006-14, Revision 01, dated February 16, 2015. Repeat the inspections thereafter at intervals not to exceed 60 days. As of the effective date of this AD, only use Airbus AOT A57N006-14, Revision 01, dated February 16, 2015, to accomplish the actions required by this paragraph. (1) Do a detailed visual inspection of the external surface of the left-hand and right-hand wing lower skin surface to detect missing or broken or migrated fasteners. (2) Do a detailed visual inspection of the inboard MLG support rib lower flange to detect missing or broken nuts or fastener tails. (h) Retained for All Airplanes Except Airbus Model A319-132 Airplanes: Corrective Actions for the Inspections Required by Paragraph (g)(1) of This AD, With New Service Information This paragraph restates the requirements of paragraph (h) of AD 2014-26-53, Amendment 39-18068 (80 FR 3155, January 22, 2015), with new service information. (1) If, during any inspection required by paragraph (g)(1) of this AD, only one discrepancy (any missing or broken or migrated fastener) is found on the left- or right-side: Before further flight, do corrective actions in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. Replacement of fasteners on an airplane does not constitute terminating action for any inspection required by paragraph (g) of this AD. (2) If, during any inspection required by paragraph (g)(1) of this AD, more than one discrepancy (any missing or broken or migrated fastener) is found on the left- or right-side: Before further flight, replace all affected fasteners on the affected side(s), in accordance with Airbus AOT A57N006-14, Revision 00, dated December 4, 2014; or Airbus AOT A57N006-14, Revision 01, dated February 16, 2015. One fastener per side may be missing or broken or migrated provided the applicable actions required by paragraph (h)(1) of this AD are done. Replacement of fasteners on an airplane does not constitute terminating action for any inspection required by paragraph (g) of this AD. As of the effective date of this AD, only use Airbus AOT A57N006-14, Revision 01, dated February 16, 2015, to accomplish the actions required by this paragraph. (i) Retained for All Airplanes Except Airbus Model A319-132 Airplanes: Corrective Actions for the Inspections Required by Paragraph (g)(2) of This AD, With New Service Information This paragraph restates the requirements of paragraph (i) of AD 2014-26-53, Amendment 39-18068 (80 FR 3155, January 22, 2015), with new service information. (1) If, during any inspection required by paragraph (g)(2) of this AD, only one discrepancy (any missing or broken nut or fastener tail) is found on the left- or right-side: Before further flight, do corrective actions in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. Replacement of fasteners on an airplane does not constitute terminating action for any inspection required by paragraph (g) of this AD. (2) If, during any inspection required by paragraph (g)(2) of this AD, more than one discrepancy (any missing or broken nut or fastener tail) is found on the left- or right-side: Before further flight, replace all affected fasteners on the affected side(s), in accordance with Airbus AOT A57N006-14, Revision 00, dated December 4, 2014; or Airbus AOT A57N006-14, Revision 01, dated February 16, 2015. One fastener per side may be missing or broken or migrated provided the applicable actions required by paragraph (i)(1) of this AD are done. Replacement of fasteners on an airplane does not constitute terminating action for any inspection required by paragraph (g) of this AD. As of the effective date of this AD, only use Airbus AOT A57N006-14, Revision 01, dated February 16, 2015, to accomplish the actions required by this paragraph. (j) Retained for All Airplanes Except Airbus Model A319-132 Airplanes: Repetitive Inspections of the Outboard MLG Support Rib Lower Flange, With New Service Information This paragraph restates the requirements of paragraph (g) of AD 2015-03-02, Amendment 39-18098 (80 FR 6897, February 9, 2015), with new service information. For Airbus Model A319-115, A319-133, A320- 214, A320-232, and A320-233 airplanes: Within 4 months after February 24, 2015 (the effective date of AD 2015-03-02), or within 4 months after the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness, or before further flight for any airplane that is not in operation for more than 4 months, whichever occurs latest: Do a detailed visual inspection of the left and right outboard MLG support rib lower flange to detect any discrepancy (broken or missing fastener tails or nuts), in accordance with Airbus AOT A57N006-14, Revision 00, dated December 4, [[Page 23236]] 2014; or Airbus AOT A57N006-14, Revision 01, dated February 16, 2015. Repeat the inspection thereafter at intervals not to exceed 4 months. As of the effective date of this AD, only use Airbus AOT A57N006-14, Revision 01, dated February 16, 2015, for the actions required by this paragraph. (k) Retained for All Airplanes Except Airbus Model A319-132 Airplanes: Corrective Actions for the Inspections Required by Paragraph (j) of This AD, With New Service Information This paragraph restates the requirements of paragraph (h) of AD 2015-03-02, Amendment 39-18098 (80 FR 6897, February 9, 2015), with new service information. If, during any inspection required by paragraph (j) of this AD, any discrepancy is found on the left or right outboard MLG support rib lower flange: Before further flight, replace all affected fasteners on the affected side(s), in accordance with Airbus AOT A57N006-14, Revision 00, dated December 4, 2014; or Airbus AOT A57N006-14, Revision 01, dated February 16, 2015. Replacement of fasteners on an airplane does not constitute terminating action for the repetitive inspections required by paragraph (j) of this AD. As of the effective date of this AD, only use Airbus AOT A57N006-14, Revision 01, dated February 16, 2015, for the actions required by this paragraph. (l) For Airbus Model A319-132 Airplanes: New Repetitive Inspections of External Surface of Wing Lower Skin and Inboard MLG Support Rib Lower Flange For Airbus Model A319-132 airplanes: Within 60 days after the effective date of this AD, or within 60 days since the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness, or before further flight for any airplane that is not in operation for more than 60 days, whichever occurs later: Do the inspections required by paragraphs (l)(1) and (l)(2) of this AD, in accordance with Airbus AOT A57N006-14, Revision 01, dated February 16, 2015. Repeat the inspections thereafter at intervals not to exceed 60 days. (1) Do a detailed visual inspection of the external surface of the left-hand and right-hand wing lower skin surface to detect missing or broken or migrated fasteners. (2) Do a detailed visual inspection of the inboard MLG support rib lower flange to detect missing or broken nuts or fastener tails. (m) For Airbus Model A319-132 Airplanes: Corrective Actions for the Inspections Required by Paragraph (l)(1) of This AD (1) If, during any inspection required by paragraph (l)(1) of this AD, only one discrepancy (any missing or broken or migrated fastener) is found on the left- or right-side: Before further flight, do corrective actions in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. Replacement of fasteners on an airplane does not constitute terminating action for any inspection required by paragraph (l) of this AD. (2) If, during any inspection required by paragraph (l)(1) of this AD, more than one discrepancy (any missing or broken or migrated fastener) is found on the left- or right-side: Before further flight, replace all affected fasteners on the affected side(s), in accordance with Airbus AOT A57N006-14, Revision 01, dated February 16, 2015. One fastener per side may be missing or broken or migrated provided the applicable actions required by paragraph (m)(1) of this AD are done. Replacement of fasteners on an airplane does not constitute terminating action for any inspection required by paragraph (l) of this AD. (n) For Airbus Model A319-132 Airplanes: Corrective Actions for the Inspections Required by Paragraph (l)(2) of This AD (1) If, during any inspection required by paragraph (l)(2) of this AD, only one discrepancy (any missing or broken nut or fastener tail) is found on the left- or right-side: Before further flight, do corrective actions in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. Replacement of fasteners on an airplane does not constitute terminating action for any inspection required by paragraph (l) of this AD. (2) If, during any inspection required by paragraph (l)(2) of this AD, more than one discrepancy (any missing or broken nut or fastener tail) is found on the left- or right-side: Before further flight, replace all affected fasteners on the affected side(s), in accordance with Airbus AOT A57N006-14, Revision 01, dated February 16, 2015. One fastener per side may be missing or broken or migrated provided the applicable actions required by paragraph (n)(1) of this AD are done. Replacement of fasteners on an airplane does not constitute terminating action for any inspection required by paragraph (l) of this AD. (o) For Airbus Model A319-132 Airplanes: New Repetitive Inspections of Outboard MLG Support Rib Lower Flange For Airbus Model A319-132 airplanes: Within 4 months after the effective date of this AD, or within 4 months after the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness, or before further flight for any airplane that is not in operation for more than 4 months, whichever occurs later: Do a detailed visual inspection of the left and right outboard MLG support rib lower flange to detect any discrepancy (broken or missing fastener tails or nuts), in accordance with Airbus AOT A57N006-14, Revision 01, dated February 16, 2015. Repeat the inspection thereafter at intervals not to exceed 4 months. (p) For Airbus Model A319-132 Airplanes: Corrective Actions for the Inspections Required by Paragraph (o) of This AD If, during any inspection required by paragraph (o) of this AD, any discrepancy is found on the left or right outboard MLG support rib lower flange: Before further flight, replace all affected fasteners on the affected side(s), in accordance with Airbus AOT A57N006-14, Revision 01, dated February 16, 2015. Replacement of fasteners on an airplane does not constitute terminating action for the repetitive inspections required by paragraph (o) of this AD. (q) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (l), (m)(2), (n)(2), (o), and (p) of this AD, if those actions were performed before the effective date of this AD using Airbus AOT A57N006-14, Revision 00, dated December 4, 2014, which was incorporated by reference in AD 2014-26-53, Amendment 39-18068 (80 FR 3155, January 22, 2015). (r) Other FAA AD Provisions (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 2014-26-53, Amendment 39- 18068 (80 FR 3155, January 22, 2015); and AD 2015-03-02, Amendment 39-18098 (80 FR 6897, February 19, 2015); are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (s) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (t) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0026, dated February 19, 2015, 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-2015-0930. [[Page 23237]] (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (u)(3) and (u)(4) of this AD. (u) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Alert Operators Transmission A57N006-14, Revision 01, dated February 16, 2015. (ii) Reserved. (3) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on April 14, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-09465 Filed 4-24-15; 8:45 am] BILLING CODE 4910-13-P
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Générale de l’Aviation Civile (DGAC), for the task is at the applicable time specified (n) Material Incorporated by Reference
operators are required to contact the in paragraphs (k)(1), (k)(2), and (k)(3) of this (1) The Director of the Federal Register
Manager, International Branch, ANM–116, AD. approved the incorporation by reference
Transport Airplane Directorate, FAA. The (1) For airplanes having accumulated less (IBR) of the service information listed in this
actions must otherwise be accomplished in than 40,000 total flight hours since first flight paragraph under 5 U.S.C. 552(a) and 1 CFR
accordance with the applicable CMRs. of the airplane as of the effective date of this part 51.
(h) Retained Transition/Grace Period for AD: Before the accumulation of 40,001 total (2) You must use this service information
Maintenance Significant Item (MSI) 78.30.00 flight hours. as applicable to do the actions required by
Tasks (2) For airplanes having accumulated this AD, unless this AD specifies otherwise.
40,000 total flight hours or more since first (3) The following service information was
This paragraph restates the requirements of
flight of the airplane as of the effective date approved for IBR on June 1, 2015.
paragraph (g) of AD 2007–14–05,
Amendment 39–15127 (72 FR 39307, July 18, of this AD, and on which Aging Systems (i) Airbus A300–600 Airworthiness
2007), with no changes. For tasks identified Maintenance (ASM) Task 213115–04–1, Limitations Section Part 3, Certification
in MSI 78.30.00, ‘‘Thrust Reverser Actuation ‘‘Cabin Pressure Safety Valve;’’ or Maintenance Requirements, dated April 18,
and Cowling,’’ of Section 2, ‘‘CMR ‘Two Star’ Maintenance Review Board Report (MRBR) 2012.
Tasks,’’ of Airbus A300–600 CMR AI/ST5/ Tasks 21.30.00/06 and 21.30.00/08, (ii) Airbus A310 Airworthiness Limitations
829/85, Issue 12, dated February 2005; and ‘‘Pressurization Control,’’ have been Section Part 3, Certification Maintenance
Airbus A310 CMR AI/ST5/849/85, Issue 12, accomplished: Before the accumulation of Requirements, dated November 30, 2012.
dated February 2005: The initial compliance 14,000 flight hours after the most recent (4) The following service information was
time is within 2,000 flight cycles or 12 accomplishment of ASM Tasks 213115–04–1, approved for IBR on August 22, 2007 (72 FR
months after August 22, 2007 (the effective or MRBR Tasks 21.30.00/06 and 21.30.00/08, 39307, July 18, 2007).
date of AD 2007–14–05), whichever occurs whichever occurs later. (i) Airbus A300–600 Certification
later. Thereafter, actions identified in MSI (3) For airplanes having accumulated Maintenance Requirements AI/ST5/829/85,
78.30.00 must be accomplished within the 40,000 total flight hours or more since first Issue 12, dated February 2005.
repetitive interval specified in the applicable (ii) Airbus A310 Certification Maintenance
flight of the airplane as of the effective date
CMRs. Where the CMRs specify to contact Requirements AI/ST5/849/85, Issue 12, dated
of this AD, and on which ASM Task 213115–
the DGAC, operators are required to contact February 2005.
04–1, or MRBR Tasks 21.30.00/06 and
the Manager, International Branch, ANM– (5) For service information identified in
21.30.00/08, have not been accomplished: this AD, contact Airbus SAS—EAW
116, Transport Airplane Directorate, FAA, for Within 3 months after the effective date of
such approvals. The actions must be (Airworthiness Office), 1 Rond Point Maurice
this AD. Bellonte, 31707 Blagnac Cedex, France;
accomplished in accordance with the
applicable CMRs. (l) Other FAA AD Provisions telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
(i) New Revision of Maintenance or The following provisions also apply to this airbus.com; Internet http://www.airbus.com.
Inspection Program AD: (6) You may view this service information
Within 3 months after the effective date of (1) Alternative Methods of Compliance at the FAA, Transport Airplane Directorate,
this AD, revise the maintenance or inspection (AMOCs): The Manager, International 1601 Lind Avenue SW., Renton, WA. For
program, as applicable, to incorporate Airbus Branch, ANM–116, Transport Airplane information on the availability of this
A310 Airworthiness Limitations Section Directorate, FAA, has the authority to material at the FAA, call 425–227–1221.
(ALS) Part 3, Certification Maintenance approve AMOCs for this AD, if requested (7) You may view this service information
Requirements (CMR), dated November 30, using the procedures found in 14 CFR 39.19. that is incorporated by reference at the
2012; or Airbus A300–600 ALS Part 3, In accordance with 14 CFR 39.19, send your National Archives and Records
Certification Maintenance Requirements request to your principal inspector or local Administration (NARA). For information on
(CMR), dated April 18, 2012. Except as Flight Standards District Office, as the availability of this material at NARA, call
required by paragraph (k) of this AD, the appropriate. If sending information directly 202–741–6030, or go to: http://
initial compliance time for accomplishing the to the International Branch, send it to ATTN: www.archives.gov/federal-register/cfr/ibr-
actions is at the applicable time specified in Dan Rodina, Aerospace Engineer, locations.html.
Airbus A310 ALS Part 3, Certification International Branch, ANM–116, Transport
Issued in Renton, Washington, on April 9,
Maintenance Requirements (CMR), dated Airplane Directorate, FAA, 1601 Lind
2015.
November 30, 2012; or Airbus A300–600 ALS Avenue SW., Renton, WA 98057–3356;
Part 3, Certification Maintenance telephone 425–227–2125; fax 425–227–1149. Jeffrey E. Duven,
Requirements (CMR), dated April 18, 2012, Information may be emailed to: 9-ANM-116- Manager, Transport Airplane Directorate,
as applicable; or within 3 months after the AMOC-REQUESTS@faa.gov. Aircraft Certification Service.
effective date of this AD; whichever occurs (2) Contacting the Manufacturer: As of the [FR Doc. 2015–09285 Filed 4–24–15; 8:45 am]
later. Accomplishing the requirements in this effective date of this AD, for any requirement BILLING CODE 4910–13–P
paragraph terminates the requirements in in this AD to obtain corrective actions from
paragraph (g) of this AD. a manufacturer, the action must be
(j) New No Alternative Actions or Intervals accomplished using a method approved by DEPARTMENT OF TRANSPORTATION
the Manager, International Branch, ANM–
After accomplishment of the revision
116, Transport Airplane Directorate, FAA; or Federal Aviation Administration
required by paragraph (i) of this AD, no
alternative actions (e.g., inspections) or the European Aviation Safety Agency
intervals, may be used unless the actions or (EASA); or Airbus’s EASA Design 14 CFR Part 39
intervals are approved as an alternative Organization Approval (DOA). If approved by
method of compliance (AMOC) in the DOA, the approval must include the [Docket No. FAA–2015–0930; Directorate
accordance with the procedures specified in DOA-authorized signature. Identifier 2015–NM–040–AD; Amendment
paragraph (l) of this AD. (m) Related Information 39–18144; AD 2015–08–08]
(k) New Compliance Time for Model A300– Refer to Mandatory Continuing RIN 2120–AA64
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600 Series Airplanes Airworthiness Information (MCAI) EASA
For CMR Task 213000–A0001–1–C, Airworthiness Directive 2013–0072, dated Airworthiness Directives; Airbus
‘‘Pressurization Control,’’ as identified in March 20, 2013, (corrected January 15, 2015) Airplanes
Sub-part 3–1, CMR Tasks, of the Airbus for related information. This MCAI may be
A300–600 ALS Part 3, Certification found in the AD docket on the Internet at AGENCY: Federal Aviation
Maintenance Requirements (CMR), dated http://www.regulations.gov by searching for Administration (FAA), Department of
April 18, 2012: The initial compliance time and locating Docket No. FAA–2014–0655. Transportation (DOT).
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![23234 Federal Register / Vol. 80, No. 80 / Monday, April 27, 2015 / Rules and Regulations
and A320 aeroplanes delivered since January of the unsafe condition described in the AD 2015–03–06 is $170 per product, per
2014. MCAI and service information inspection cycle.
This condition, if not detected and referenced above. We are issuing this
corrected could reduce the design safety
We also estimate that it will take
AD because we evaluated all pertinent about 2 work-hours per product to
margin of the structure.
Prompted by these findings, EASA issued information and determined the unsafe comply with the basic requirements of
Emergency AD 2014–0270–E (later revised) condition exists and is likely to exist or this AD. The average labor rate is $85
[which corresponds to certain requirements develop on other products of these same per work-hour. Based on these figures,
of AD 2014–26–53, Amendment 39–18068 type designs. we estimate the cost of this AD on U.S.
(80 FR 3155, January 22, 2015)] to require operators to be $25,160, or $170 per
repetitive detailed inspections (DET) of the FAA’s Determination of the Effective
Date product, per inspection cycle.
bottom skin taperlok fasteners at the MLG
Rib 5 footprint location and, depending on In addition, we estimate that any
An unsafe condition exists that
findings, accomplishment of applicable fastener replacement will take about 3
requires the immediate adoption of this
corrective action(s). work-hours and require parts costing
AD. The FAA has found that the risk to
Since EASA AD 2014–0270R1 [which $400, for a cost of $655 per fastener
the flying public justifies waiving notice
corresponds to certain requirements of AD replacement. We have no way of
2015–03–02, Amendment 39–18098 (80 FR and comment prior to adoption of this
determining the number of aircraft that
6897, February 19, 2015)] was issued, based rule because failure of more than two
might need these actions.
on in service feedback and further fasteners at the outboard MLG support
investigation, Airbus issued Revision 01 of rib lower flange could result in an Authority for This Rulemaking
Alert Operators Transmission (AOT) airplane not meeting its maximum loads
A57N006–14 to extend the original 8 expected in-service. This condition Title 49 of the United States Code
calendar days inspection interval to 60 could result in failure of the structure. specifies the FAA’s authority to issue
calendar days for the external area and for Therefore, we determined that notice rules on aviation safety. Subtitle I,
the internal inboard side. In addition, it was
and opportunity for public comment section 106, describes the authority of
identified that the model A319–132 was the FAA Administrator. ‘‘Subtitle VII:
missing from the [EASA] AD applicability. before issuing this AD are impracticable
and that good cause exists for making Aviation Programs,’’ describes in more
For the reasons described above, this AD detail the scope of the Agency’s
retains the requirements of EASA AD 2014– this amendment effective in fewer than
30 days. authority.
0270R1, which is superseded, to amend the
Applicability and to require those actions We are issuing this rulemaking under
within the new thresholds and intervals. Comments Invited the authority described in ‘‘Subtitle VII,
This [EASA] AD is still considered to be This AD is a final rule that involves Part A, Subpart III, Section 44701:
an interim action and further [EASA] AD requirements affecting flight safety, and General requirements.’’ Under that
action may follow. we did not precede it by notice and section, Congress charges the FAA with
You may examine the MCAI on the opportunity for public comment. We promoting safe flight of civil aircraft in
Internet at http://www.regulations.gov invite you to send any written relevant air commerce by prescribing regulations
by searching for and locating Docket No. data, views, or arguments about this AD. for practices, methods, and procedures
FAA–2015–0930. Send your comments to an address the Administrator finds necessary for
listed under the ADDRESSES section. safety in air commerce. This regulation
Related Service Information Under 1 Include ‘‘Docket No. FAA–2015–0930; is within the scope of that authority
CFR Part 51 Directorate Identifier 2015–NM–040– because it addresses an unsafe condition
Airbus has issued Airbus Alert AD’’ at the beginning of your comments. that is likely to exist or develop on
Operators Transmission (AOT) We specifically invite comments on the products identified in this rulemaking
A57N006–14, Revision 01, dated overall regulatory, economic, action.
February 16, 2015. The service environmental, and energy aspects of Regulatory Findings
information describes procedures for this AD. We will consider all comments
repetitive detailed visual inspections to received by the closing date and may We determined that this AD will not
detect discrepancies of the wing lower amend this AD because of those have federalism implications under
skin surface and inboard and outboard comments. Executive Order 13132. This AD will
MLG support rib lower flange location We will post all comments we not have a substantial direct effect on
fasteners and corrective actions. The receive, without change, to http:// the States, on the relationship between
actions described in this service www.regulations.gov, including any the national government and the States,
information are intended to correct the personal information you provide. We or on the distribution of power and
unsafe condition identified in the will also post a report summarizing each responsibilities among the various
MCAI. substantive verbal contact we receive levels of government.
This service information is reasonably about this AD. For the reasons discussed above, I
available at http://www.regulations.gov certify that this AD:
by searching for and locating Docket No. Costs of Compliance
1. Is not a ‘‘significant regulatory
FAA–2015–0930. Or see ADDRESSES for We estimate that this AD affects 148
action’’ under Executive Order 12866;
other ways to access this service airplanes of U.S. registry.
The actions required by AD 2014–26– 2. Is not a ‘‘significant rule’’ under the
information.
53, Amendment 39–18068 (80 FR 3155, DOT Regulatory Policies and Procedures
FAA’s Determination and Requirements January 22, 2015); and AD 2015–03–2, (44 FR 11034, February 26, 1979);
of This AD
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Amendment 39–18098 (80 FR 6897, 3. Will not affect intrastate aviation in
This product has been approved by February 9, 2015); and retained in this Alaska; and
the aviation authority of another AD, take about 2 work-hours per 4. Will not have a significant
country, and is approved for operation product, at an average labor rate of $85 economic impact, positive or negative,
in the United States. Pursuant to our per work-hour. Based on these figures, on a substantial number of small entities
bilateral agreement with the State of the estimated cost of the actions that under the criteria of the Regulatory
Design Authority, we have been notified were required by AD 2014–26–53 and Flexibility Act.
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![Federal Register / Vol. 80, No. 80 / Monday, April 27, 2015 / Rules and Regulations 23235
List of Subjects in 14 CFR Part 39 (f) Compliance the applicable actions required by paragraph
Comply with this AD within the (h)(1) of this AD are done. Replacement of
Air transportation, Aircraft, Aviation fasteners on an airplane does not constitute
compliance times specified, unless already
safety, Incorporation by reference, done. terminating action for any inspection
Safety. required by paragraph (g) of this AD. As of
(g) Retained for All Airplanes Except Airbus the effective date of this AD, only use Airbus
Adoption of the Amendment Model A319–132 Airplanes: Repetitive AOT A57N006–14, Revision 01, dated
Accordingly, under the authority Inspections, With Extended Compliance February 16, 2015, to accomplish the actions
Time and New Service Information required by this paragraph.
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as This paragraph restates the requirements of (i) Retained for All Airplanes Except Airbus
follows: paragraph (g) of AD 2014–26–53, Model A319–132 Airplanes: Corrective
Amendment 39–18068 (80 FR 3155, January Actions for the Inspections Required by
PART 39—AIRWORTHINESS 22, 2015), with an extended compliance time Paragraph (g)(2) of This AD, With New
and new service information. For Airbus Service Information
DIRECTIVES Model A319–115, A319–133, A320–214,
A320–232, and A320–233 airplanes: Within This paragraph restates the requirements of
■ 1. The authority citation for part 39 60 days after February 6, 2015 (the effective paragraph (i) of AD 2014–26–53, Amendment
continues to read as follows: date of AD 2014–26–53), or within 60 days 39–18068 (80 FR 3155, January 22, 2015),
Authority: 49 U.S.C. 106(g), 40113, 44701. since the date of issuance of the original with new service information.
certificate of airworthiness or the original (1) If, during any inspection required by
§ 39.13 [Amended] export certificate of airworthiness, or before paragraph (g)(2) of this AD, only one
further flight for any airplane that is not in discrepancy (any missing or broken nut or
■ 2. The FAA amends § 39.13 by: fastener tail) is found on the left- or right-
operation for more than 60 days, whichever
■ a. Removing Airworthiness Directive occurs later: Do the inspections required by side: Before further flight, do corrective
(AD) 2014–26–53, Amendment 39– paragraphs (g)(1) and (g)(2) of this AD, in actions in accordance with a method
18068 (80 FR 3155, January 22, 2015); accordance with Airbus Alert Operators approved by the Manager, International
and AD 2015–03–02, Amendment 39– Transmission (AOT) A57N006–14, Revision Branch, ANM–116, Transport Airplane
18098 (80 FR 6897, February 9, 2015; 00, dated December 4, 2014; or Airbus AOT Directorate, FAA. Replacement of fasteners
and A57N006–14, Revision 01, dated February on an airplane does not constitute
16, 2015. Repeat the inspections thereafter at terminating action for any inspection
■ b. Adding the following new AD:
intervals not to exceed 60 days. As of the required by paragraph (g) of this AD.
2015–08–08 Airbus: Amendment 39–18144.
effective date of this AD, only use Airbus (2) If, during any inspection required by
Docket No. FAA–2015–0930; Directorate
AOT A57N006–14, Revision 01, dated paragraph (g)(2) of this AD, more than one
Identifier 2015–NM–040–AD.
February 16, 2015, to accomplish the actions discrepancy (any missing or broken nut or
(a) Effective Date required by this paragraph. fastener tail) is found on the left- or right-
This AD becomes effective May 12, 2015. (1) Do a detailed visual inspection of the side: Before further flight, replace all affected
external surface of the left-hand and right- fasteners on the affected side(s), in
(b) Affected ADs hand wing lower skin surface to detect accordance with Airbus AOT A57N006–14,
This AD replaces the following: missing or broken or migrated fasteners. Revision 00, dated December 4, 2014; or
(1) AD 2014–26–53, Amendment 39–18068 (2) Do a detailed visual inspection of the Airbus AOT A57N006–14, Revision 01, dated
(80 FR 3155, January 22, 2015). inboard MLG support rib lower flange to February 16, 2015. One fastener per side may
(2) AD 2015–03–02, Amendment 39–18098 detect missing or broken nuts or fastener be missing or broken or migrated provided
(80 FR 6897, February 9, 2015). tails. the applicable actions required by paragraph
(i)(1) of this AD are done. Replacement of
(c) Applicability (h) Retained for All Airplanes Except Airbus
fasteners on an airplane does not constitute
Model A319–132 Airplanes: Corrective
This AD applies to Airbus Model A319– terminating action for any inspection
Actions for the Inspections Required by
115, A319–132, A319–133, A320–214, A320– required by paragraph (g) of this AD. As of
Paragraph (g)(1) of This AD, With New
232, and A320–233 airplanes, certificated in the effective date of this AD, only use Airbus
Service Information
any category, manufacturer serial numbers AOT A57N006–14, Revision 01, dated
(MSN) 5817, 5826, 5837, 5848, 5855, 5864, This paragraph restates the requirements of February 16, 2015, to accomplish the actions
5875, 5886, 5896, 5910, and 5918 and paragraph (h) of AD 2014–26–53, required by this paragraph.
subsequent. Amendment 39–18068 (80 FR 3155, January
22, 2015), with new service information. (j) Retained for All Airplanes Except Airbus
(d) Subject (1) If, during any inspection required by Model A319–132 Airplanes: Repetitive
paragraph (g)(1) of this AD, only one Inspections of the Outboard MLG Support
Air Transport Association (ATA) of
discrepancy (any missing or broken or Rib Lower Flange, With New Service
America Code 57, Wings.
migrated fastener) is found on the left- or Information
(e) Reason right-side: Before further flight, do corrective This paragraph restates the requirements of
This AD was prompted by a determination actions in accordance with a method paragraph (g) of AD 2015–03–02,
that certain airplanes were not included in approved by the Manager, International Amendment 39–18098 (80 FR 6897, February
the applicability of AD 2014–26–53, Branch, ANM–116, Transport Airplane 9, 2015), with new service information. For
Amendment 39–18068 (80 FR 3155, January Directorate, FAA. Replacement of fasteners Airbus Model A319–115, A319–133, A320–
22, 2015); and AD 2015–03–02, Amendment on an airplane does not constitute 214, A320–232, and A320–233 airplanes:
39–18098 (80 FR 6897, February 9, 2015). terminating action for any inspection Within 4 months after February 24, 2015 (the
This AD was also prompted by reports of required by paragraph (g) of this AD. effective date of AD 2015–03–02), or within
failure of certain fasteners located at the wing (2) If, during any inspection required by 4 months after the date of issuance of the
lower skin surface, and inboard and outboard paragraph (g)(1) of this AD, more than one original certificate of airworthiness or the
main landing gear (MLG) support rib lower discrepancy (any missing or broken or original export certificate of airworthiness, or
flanges. We are issuing this AD to detect and migrated fastener) is found on the left- or before further flight for any airplane that is
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correct discrepancies of the fasteners at the right-side: Before further flight, replace all not in operation for more than 4 months,
external surface of the lower wing skin and affected fasteners on the affected side(s), in whichever occurs latest: Do a detailed visual
inboard and outboard MLG support rib lower accordance with Airbus AOT A57N006–14, inspection of the left and right outboard MLG
flanges, which could result in an airplane not Revision 00, dated December 4, 2014; or support rib lower flange to detect any
meeting its maximum loads expected in Airbus AOT A57N006–14, Revision 01, dated discrepancy (broken or missing fastener tails
service. This condition could result in February 16, 2015. One fastener per side may or nuts), in accordance with Airbus AOT
structural failure. be missing or broken or migrated provided A57N006–14, Revision 00, dated December 4,
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![Federal Register / Vol. 80, No. 80 / Monday, April 27, 2015 / Rules and Regulations 23237
(2) Service information identified in this under common control (controlled regarding the agent for an affiliated
AD that is not incorporated by reference is groups). group of corporations that files a
available at the addresses specified in consolidated return (consolidated
paragraphs (u)(3) and (u)(4) of this AD. DATES: This correction is effective April
27, 2015 and applicable April 3, 2015. group).
(u) Material Incorporated by Reference DATES: This correction is effective on
FOR FURTHER INFORMATION CONTACT:
(1) The Director of the Federal Register April 27, 2015 and applicable April 1,
approved the incorporation by reference
James Holmes at (202) 317–4137 (not a
toll-free number). 2015.
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT:
part 51. Gerald Fleming at (202) 317–6975 or
(2) You must use this service information Background Richard M. Heinecke at (202) 317–6065
as applicable to do the actions required by The final regulations (TD 9717) that (not a toll free number).
this AD, unless this AD specifies otherwise. are the subject of this correction is SUPPLEMENTARY INFORMATION:
(i) Airbus Alert Operators Transmission
under section 41 of the Internal Revenue Background
A57N006–14, Revision 01, dated February
16, 2015. Code.
(ii) Reserved.
The final regulations (TD 9715) that
Need for Correction are the subject of this correction is
(3) For service information identified in
this AD, contact Airbus, Airworthiness As published, the final regulation (TD under section 1502 of the Internal
Office—EIAS, 1 Rond Point Maurice 9717) contains errors that may prove to Revenue Code.
Bellonte, 31707 Blagnac Cedex, France; be misleading and are in need of
telephone +33 5 61 93 36 96; fax +33 5 61 Need for Correction
clarification.
93 44 51; email account.airworth-eas@ As published, the final regulations
airbus.com; Internet http://www.airbus.com. Correction of Publication (TD 9715) contain errors that may prove
(4) You may view this service information to be misleading and are in need of
at the FAA, Transport Airplane Directorate,
Accordingly, the final regulation (TD
9717), that are the subject of FR Doc. clarification.
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this 2015–07331, are corrected as follows: List of Subjects in 26 CFR Part 1
material at the FAA, call 425–227–1221. 1. On page 18096, in the preamble,
(5) You may view this service information under paragraph heading Income taxes, Reporting and
that is incorporated by reference at the ‘‘Background,’’ the last line, ‘‘Act’’ is recordkeeping requirements.
National Archives and Records corrected to read ‘‘American Taxpayer Correction of Publication
Administration (NARA). For information on Relief Act of 2012, PL 112–240, H. R. 8
the availability of this material at NARA, call (the ‘‘Act’’). Accordingly, 26 CFR part 1 is
202–741–6030, or go to: http://
2. On page 18097, in the third corrected by making the following
www.archives.gov/federal-register/cfr/ibr- correcting amendments:
locations.html. column, under the paragraph heading
‘‘Explanation of Provisions’’, the first PART 1—INCOME TAXES
Issued in Renton, Washington, on April 14, full paragraph, fourth line of the
2015.
paragraph, ‘‘credit determined under ■ Paragraph 1. The authority citation
Michael Kaszycki, 41(a) for a’’ is corrected to read ‘‘credit for part 1 continues to read in part as
Acting Manager, Transport Airplane determined under section 41(a) for a’’. follows:
Directorate, Aircraft Certification Service.
[FR Doc. 2015–09465 Filed 4–24–15; 8:45 am] Martin V. Franks, Authority: 26 U.S.C. 7805 * * *
BILLING CODE 4910–13–P Chief, Publications and Regulations Branch, ■ Par. 2. Section 1.1502–77 is amended
Legal Processing Division, Associate Chief by revising the second sentence of
Counsel, (Procedure and Administration). paragraph (c)(1) and the first sentence of
[FR Doc. 2015–09604 Filed 4–24–15; 8:45 am] paragraph (g) to read as follows:
DEPARTMENT OF THE TREASURY
BILLING CODE 4830–01–P
Internal Revenue Service § 1.1502–77 Agent for the group.
* * * * *
26 CFR Part 1 DEPARTMENT OF THE TREASURY (c) * * * (1) * * * Except as
specifically provided otherwise in this
[TD 9717] Internal Revenue Service paragraph (c), any entity that is an agent
RIN 1545–BL77 pursuant to paragraph (c)(3) of this
26 CFR Part 1 section (agent following group structure
Allocation of Controlled Group [TD 9715] change), paragraph (c)(5) of this section
Research Credit; Correction (agent designated by agent terminating
RIN 1545–BH31 without default successor), paragraph
AGENCY: Internal Revenue Service (IRS),
Treasury. (c)(6) of this section (agent designated
Regulations Revising Rules Regarding by Commissioner), or paragraph (c)(7) of
ACTION: Final and temporary Agency for a Consolidated Group; this section (agent designated by
regulations; correction. Correction resigning agent), or any entity
SUMMARY: This document contains AGENCY: Internal Revenue Service (IRS), subsequently serving as agent following
corrections to final regulations (TD Treasury. such agent, acts as an agent for and
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9717) that were published in the ACTION: Correcting amendment.
under the same terms and conditions
Federal Register on Friday, April 3, that apply to a common parent. * * *
2015 (80 FR 18096). The final SUMMARY: This document contains * * * * *
regulations are relating to the allocation corrections to final regulations (TD (g) Examples. Unless otherwise
of the credit for increasing research 9715) that were published in the indicated, all entities are domestic and
activities (research credit) to Federal Register on April 1, 2015 (80 FR have a calendar year taxable year, and
corporations and trades or businesses 17314). The final regulations are each of P, S, S–1, S–2, S–3, T, U, V, W,
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Document Created: 2015-12-16 08:29:58
Document Modified: 2015-12-16 08:29:58
| 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; request for comments. | |
| Dates | This AD becomes effective May 12, 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 23232 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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