80 FR 13799 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 51 (March 17, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 51 (March 17, 2015)
| Page Range | 13799-13803 | |
| FR Document | 2015-05720 |
[Federal Register Volume 80, Number 51 (Tuesday, March 17, 2015)] [Proposed Rules] [Pages 13799-13803] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-05720] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0490; Directorate Identifier 2014-NM-018-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) 2008-22- 20, for certain Airbus Model A330-200, A330-300, and A340-300 series airplanes. AD 2008-22-20 currently requires repetitive high frequency eddy current (HFEC) inspections for cracking, repair if necessary, and modification of the upper shell structure of the fuselage. Since we issued AD 2008-22-20, we have determined from a fatigue and damage tolerance evaluation that the compliance times must be reduced. This proposed AD would shorten certain compliance times. We are proposing this AD to prevent fatigue cracking of the upper shell structure of the fuselage, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by May 1, 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 proposed AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 0490; 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. SUPPLEMENTARY INFORMATION: 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-2015-0490; Directorate Identifier 2014-NM-018-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 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 proposed AD. Discussion On October 20, 2008, we issued AD 2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008). AD 2008-22-20 requires actions intended to address an unsafe condition on certain Airbus Model A330- 200, A330-300, and A340-300 series airplanes. Since we issued AD 2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008), it has been determined from a fatigue and damage tolerance evaluation that the compliance times for certain inspections and modification must be reduced. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0012R1, dated January 24, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states: During fatigue tests (EF3) on the A340-600, damage was found in the longitudinal doubler at the Vertical Tail Plane (VTP) attachment cut out between Frame (FR) 80 and FR86. This damage occurred between 58,341 and 72,891 simulated flight cycles (FC). Due to the higher Design Service Goal and different design of the affected structural area (e.g., doubler thickness) for A330-200/ -300 and A340-300 airplane series, the damage assessment concluded that these airplanes may be also potentially affected. This condition, if not detected and corrected, could affect the structural integrity of the upper shell structure between FR80 and FR86. Prompted by these findings, EASA issued AD 2007-0284 [(http://ad.easa.europa.eu/blob/easa_ad_2007_0284_superseded.pdf/AD_2007-0284_1)] to require implementation of an inspection programme of this structural area using a high frequency eddy current (HFEC) method and a modification to improve the upper shell structure. Since that [EASA] AD was issued, in the frame of a new fatigue and damage tolerance evaluation, taking into account the airplane [[Page 13800]] utilisation, the inspection threshold and intervals have been reassessed and the conclusion was that the thresholds and intervals for inspection, as well as the threshold for modifying the airplane, must be reduced. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2007-0284, which is superseded and introduces redefined thresholds and intervals. This [EASA] AD is revised to clarify that, under some conditions, accomplishment of a repair constitutes terminating action for the repetitive inspections. One of the outcome of this clarification is the deletion of paragraph (5) of this [EASA] AD. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-2015-0490. Initial compliance time thresholds range from 7,300 flight cycles or 47,600 flight hours, and up to 25,400 flight cycles or 76,300 flight hours, depending on configuration and range. Repetitive compliance time thresholds range from 1,700 flight cycles or 11,300 flight hours, and up to 4,500 flight cycles or 13,500 flight hours, depending on configuration. Widespread Fatigue Damage Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple- site-damage and multiple-element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as widespread fatigue damage (WFD). As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available; see ADDRESSES for ways to access this service information. Airbus Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010. The service information describes procedures for a modification of the fuselage, which includes inspections (e.g., eddy current rotating probe test of fastener holes for cracking, high frequency eddy current (HFEC) inspections for cracking of the upper shell structure of the fuselage, and checks of the fastener position for clearance) and applicable corrective actions (e.g., repair and rework). Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012. The service information describes procedures for applicable actions, including an eddy current rotating probe test for cracking of the fastener holes and an HFEC inspection for cracks in the upper shell of the fuselage (and including checks of the fastener position for clearance and applicable corrective actions (e.g., repair and rework)), and a modification of the airplane upper shell structure of the fuselage between FR80 and FR86. Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011. The service information describes procedures for a HFEC inspection for cracking of the upper shell structure of the fuselage between FR80 and FR86. Airbus Service Bulletin A340-53-4165, Revision 02, dated March 29, 2010. The service information describes procedures for a modification of the fuselage, which includes inspections (e.g., eddy current rotating probe test of fastener holes for cracking, HFEC inspections for cracking of the upper shell structure of the fuselage, and checks of the fastener position for clearance) and applicable corrective actions (e.g., repair and rework). Airbus Service Bulletin A340-53-4172, Revision 01, dated July 8, 2009. The service information describes procedures for inspections (e.g., rototest inspections of fastener holes for cracking, HFEC inspections for cracking of the upper shell structure of the fuselage, and checks of the fastener position for clearance) and modification of the airplane upper shell structure between FR80 and FR86 (including applicable corrective actions (e.g., repair and rework). Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011. The service information describes procedures for a HFEC inspection for cracking of the upper shell structure of the fuselage between FR80 and FR86. 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. [[Page 13801]] Differences Between This Proposed AD and the MCAI or Service Information Unlike the procedures described in the service information, this proposed AD would not permit further flight if cracks are detected in the upper shell structure. We have determined that, because of the safety implications and consequences associated with that cracking, any cracked upper shell structure must be repaired before further flight. This difference has been coordinated with the EASA and Airbus. Explanation of Compliance Time for Modification The compliance time for the modification specified in this proposed AD for addressing WFD was established to ensure that discrepant structure is modified before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without extensive new data that would substantiate and clearly warrant such an extension. Costs of Compliance We estimate that this proposed AD affects 26 airplanes of U.S. registry. We also estimate that it would take about 208 work-hours per product to comply with the basic requirements (inspection and modification) of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $28,360 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $1,197,040, or $46,040 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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 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) 2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008), and adding the following new AD: Airbus: Docket No. FAA-2015-0490; Directorate Identifier 2014-NM- 018-AD. (a) Comments Due Date We must receive comments by May 1, 2015. (b) Affected ADs This AD replaces AD 2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008). (c) Applicability This AD applies to Airbus Model A330-201, -202, -203, -223, - 243, -301, -302, -303, -321, -322, -323, -341, -342, and -343; and Model A340-311, -312, and -313 airplanes; certificated in any category; all manufacturer serial numbers on which Airbus Modification 44205 has been embodied in production, except those on which Airbus Modification 52974 or 53223 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by the results of a fatigue and damage tolerance evaluation that concluded existing compliance times must be reduced. We are issuing this AD to prevent fatigue cracking of the upper shell structure of the fuselage, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection for Airbus Model A330-300 and A340-300 Airplanes, Except Model A340-300 Weight Variant (WV) 027 Airplanes For Model A330-300 and A340-300 airplanes, except Model A340-300 WV 027 airplanes: At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of the upper shell structure between frame (FR) 80 and FR86, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011; as applicable. Repeat the inspection thereafter at the applicable time specified in paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53- 4174, Revision 02, dated December 21, 2011; as applicable. (1) For airplanes that, as of the effective date of this AD, have not been inspected in accordance with Airbus Service Bulletin A330-53-3168; or Airbus Service Bulletin A340-53-4174; as applicable: Inspect at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. (i) Before reaching the applicable threshold specified in paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53- 3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011; as applicable for airplane model, configuration, and utilization, since the airplane's first flight. (ii) Within the threshold defined in paragraph 1.E, ``COMPLIANCE,'' of Airbus [[Page 13802]] Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008; or Airbus Service Bulletin A340-53-4174, Revision 01, dated February 15, 2008; as applicable for airplane model, configuration, and utilization since the airplane's first flight; or within 12 months after the effective date of this AD; whichever occurs first. (2) For airplanes that, as of the effective date of this AD, have been inspected in accordance with Airbus Service Bulletin A330- 53-3168; or Airbus Service Bulletin A340-53-4174; as applicable: Inspect at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) Within the applicable interval specified in paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53- 4174, Revision 02, dated December 21, 2011; as applicable; to be counted from the last inspection. (ii) Within 12 months after the effective date of this AD without exceeding the intervals defined in paragraph 1.E, ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008; or Airbus Service Bulletin A340-53- 4174, Revision 01, dated February 15, 2008; as applicable for airplane model, configuration, and utilization to be counted from the last inspection. (h) Corrective Action for Airbus Model A330-300 and A340-300 Airplanes, Except Model A340-300 WV 027 Airplanes If any crack is detected during any HFEC inspection required by the introductory text to paragraph (g) of this AD: Before further flight, repair 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). Accomplishment of a repair for a specific area, as required by this paragraph, is terminating action for the repetitive HFEC inspections required by the introductory text to paragraph (g) of this AD, as applicable, for that specific repaired area only. The need and definition of subsequent repetitive inspections (if any) for that specific repaired area will be defined in the applicable repair 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). (i) Optional Terminating Action For Airbus Model A330-300 and A340-300 airplanes, except Model A340-300 WV 027 airplanes: Modification, which includes inspections and applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010; or Airbus Service Bulletin A340- 53-4165, Revision 02, dated March 29, 2010; as applicable; terminates the repetitive HFEC inspections required by the introductory text to paragraph (g) of this AD, except where Airbus Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010; or Airbus Service Bulletin A340-53-4165, Revision 02, dated March 29, 2010; as applicable; specifies to contact the manufacturer, repair using a method approved by the Manager, International Branch, ANM- 116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (j) Inspection and Modification for Airbus Model A330-200 Airplanes (1) Within the compliance times specified in paragraph (j)(1)(i) or (j)(1)(ii) of this AD, whichever occurs later: Do all applicable actions, including an eddy current rotating probe test and an HFEC inspection for cracks, and modify the airplane upper shell structure between FR80 and FR86; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012. (i) Within the compliance times identified in paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012, as applicable for airplane configuration and utilization since the airplane's first flight. (ii) Within 12 months after the effective date of this AD without exceeding the threshold, defined in paragraph 1.E, ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3160, Revision 02, dated March 29, 2010, since the airplane's first flight. (k) Inspection and Modification for Airbus Model A340-300 Airplanes, Only WV 027 For Model A340-300 airplanes, WV 027 only: Before the accumulation of 14,200 total flight cycles from the airplane's first flight, do all applicable inspections and modify the airplane upper shell structure between FR80 and FR86; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-53-4172, Revision 01, dated July 8, 2009. (l) Corrective Action for Airbus Model A330-200 Airplanes; and Model A340-300 Airplanes, Only WV 027 If any crack is detected during the inspection required by paragraph (j) or (k) of this AD, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA; concurrently with modification required by paragraph (j) or (k) of this AD. (m) Definition of ``Threshold'' and ``Interval'' (1) For the purposes of this AD, the term ``Threshold,'' as used in paragraph 1.E., ``COMPLIANCE,'' of the service information specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD means the total flight cycles or flight hours accumulated since the airplane's first flight. (2) For the purposes of this AD, the term ``Interval'' as used in paragraph 1.E., ``COMPLIANCE,'' of the service information specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD means the total flight cycles or flight hours accumulated since the last inspection, as applicable. (i) Airbus Service Bulletin A330-53-3168, dated September 19, 2007. (ii) Airbus Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008. (iii) Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011. (iv) Airbus Service Bulletin A340-53-4174, dated September 19, 2007. (v) Airbus Service Bulletin A340-53-4174, Revision 01, dated February 15, 2008. (vi) Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011. (n) Credit for Previous Actions (1) For Model A330-300 and A340-300 airplanes, except Model A340-300 WV 027 airplanes: This paragraph provides credit for the modification specified in paragraph (i) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD, as applicable. This service information is not incorporated by reference in this AD. (i) Airbus Service Bulletin A330-53-3159, dated September 19, 2007. (ii) Airbus Service Bulletin A330-53-3159, Revision 01, dated June 15, 2009. (iii) Airbus Service Bulletin A340-53-4165, dated September 19, 2007. (iv) Airbus Service Bulletin A340-53-4165, Revision 01, dated June 17, 2009. (2) For Model A330-200 airplanes: This paragraph provides credit for the inspection and modification required by paragraph (j) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (n)(2)(i), (n)(2)(ii), or (n)(2)(iii) of this AD, as applicable. This service information is not incorporated by reference in this AD. (i) Airbus Service Bulletin A330-53-3160, dated July 9, 2007. (ii) Airbus Service Bulletin A330-53-3160, Revision 01, dated April 28, 2009. (iii) Airbus Service Bulletin A330-53-3160, Revision 02, dated March 29, 2010. (3) For Model A340-300 airplanes, WV 027 only: This paragraph provides credit for the inspection and modification required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A340-53- 4172, dated July 10, 2007, which is not incorporated by reference in this AD. (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425- 227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal [[Page 13803]] inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference 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 EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0012R1, dated January 24, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-0490. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. 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 March 2, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-05720 Filed 3-16-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 51 / Tuesday, March 17, 2015 / Proposed Rules 13799
(g) Related Information which could result in reduced structural ADDRESSES section. Include ‘‘Docket No.
(1) For more information about this AD, integrity of the airplane. FAA–2015–0490; Directorate Identifier
contact Tomasz Rakowski, Aerospace DATES: We must receive comments on 2014–NM–018–AD’’ at the beginning of
Engineer, Engine Certification Office, FAA, this proposed AD by May 1, 2015. your comments. We specifically invite
Engine & Propeller Directorate, 12 New comments on the overall regulatory,
England Executive Park, Burlington, MA ADDRESSES: You may send comments by
any of the following methods: economic, environmental, and energy
01803; phone: 781–238–7735; fax: 781–238–
7199; email: tomasz.rakowski@faa.gov. • Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
(2) GE GEnx-1B Service Bulletin (SB) No. http://www.regulations.gov. Follow the consider all comments received by the
73–0036, dated January 6, 2015, and GE instructions for submitting comments. closing date and may amend this
GEnx-2B SB No. 73–0035, dated September • Fax: (202) 493–2251. proposed AD based on those comments.
16, 2014, which are not incorporated by • Mail: U.S. Department of We will post all comments we
reference in this proposed AD, can be Transportation, Docket Operations, M– receive, without change, to http://
obtained from GE using the contact www.regulations.gov, including any
30, West Building Ground Floor, Room
information in paragraph (g)(3) of this personal information you provide. We
proposed AD. W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590. will also post a report summarizing each
(3) For service information identified in
this proposed AD, contact General Electric • Hand Delivery: U.S. Department of substantive verbal contact we receive
Company, GE Aviation, Room 285, 1 Transportation, Docket Operations, M– about this proposed AD.
Neumann Way, Cincinnati, OH 45215; 30, West Building Ground Floor, Room Discussion
phone: 513–552–3272; email: geae.aoc@ W12–140, 1200 New Jersey Avenue SE.,
ge.com. Washington, DC, between 9 a.m. and 5 On October 20, 2008, we issued AD
(4) You may view this service information p.m., Monday through Friday, except 2008–22–20, Amendment 39–15717 (73
at the FAA, Engine & Propeller Directorate, FR 66747, November 12, 2008). AD
12 New England Executive Park, Burlington, Federal holidays.
For service information identified in 2008–22–20 requires actions intended to
MA. For information on the availability of address an unsafe condition on certain
this material at the FAA, call 781–238–7125. this proposed AD, contact Airbus SAS,
Airworthiness Office—EAL, 1 Rond Airbus Model A330–200, A330–300,
Issued in Burlington, Massachusetts, on and A340–300 series airplanes.
March 6, 2015. Point Maurice Bellonte, 31707 Blagnac
Since we issued AD 2008–22–20,
Cedex, France; telephone +33 5 61 93 36
Ann C. Mollica, Amendment 39–15717 (73 FR 66747,
96; fax +33 5 61 93 45 80; email
Acting Directorate Manager, Engine & November 12, 2008), it has been
airworthiness.A330-A340@airbus.com;
Propeller Directorate, Aircraft Certification determined from a fatigue and damage
Service. Internet http://www.airbus.com. You
tolerance evaluation that the
may view this referenced service
[FR Doc. 2015–05897 Filed 3–16–15; 8:45 am] compliance times for certain inspections
information at the FAA, Transport
BILLING CODE 4910–13–P and modification must be reduced.
Airplane Directorate, 1601 Lind Avenue
The European Aviation Safety Agency
SW., Renton, WA. For information on
(EASA), which is the Technical Agent
DEPARTMENT OF TRANSPORTATION the availability of this material at the
for the Member States of the European
FAA, call 425–227–1221.
Union, has issued EASA Airworthiness
Federal Aviation Administration Examining the AD Docket Directive 2014–0012R1, dated January
You may examine the AD docket on 24, 2014 (referred to after this as the
14 CFR Part 39 Mandatory Continuing Airworthiness
the Internet at http://
[Docket No. FAA–2015–0490; Directorate www.regulations.gov by searching for Information, or ‘‘the MCAI’’), to correct
Identifier 2014–NM–018–AD] and locating Docket No. FAA–2015– an unsafe condition for the specified
0490; or in person at the Docket products. The MCAI states:
RIN 2120–AA64
Management Facility between 9 a.m. During fatigue tests (EF3) on the A340–600,
Airworthiness Directives; Airbus and 5 p.m., Monday through Friday, damage was found in the longitudinal
Airplanes except Federal holidays. The AD docket doubler at the Vertical Tail Plane (VTP)
contains this proposed AD, the attachment cut out between Frame (FR) 80
AGENCY: Federal Aviation and FR86. This damage occurred between
Administration (FAA), DOT. regulatory evaluation, any comments 58,341 and 72,891 simulated flight cycles
received, and other information. The (FC).
ACTION: Notice of proposed rulemaking
street address for the Docket Operations Due to the higher Design Service Goal and
(NPRM). office (telephone (800) 647–5527) is in different design of the affected structural area
SUMMARY: We propose to supersede the ADDRESSES section. Comments will (e.g., doubler thickness) for A330–200/–300
Airworthiness Directive (AD) 2008–22– be available in the AD docket shortly and A340–300 airplane series, the damage
20, for certain Airbus Model A330–200, after receipt. assessment concluded that these airplanes
may be also potentially affected.
A330–300, and A340–300 series FOR FURTHER INFORMATION CONTACT:
This condition, if not detected and
airplanes. AD 2008–22–20 currently Vladimir Ulyanov, Aerospace Engineer, corrected, could affect the structural integrity
requires repetitive high frequency eddy International Branch, ANM–116, of the upper shell structure between FR80
current (HFEC) inspections for cracking, Transport Airplane Directorate, FAA, and FR86.
repair if necessary, and modification of 1601 Lind Avenue SW., Renton, WA Prompted by these findings, EASA issued
the upper shell structure of the fuselage. 98057–3356; telephone 425–227–1138; AD 2007–0284 [(http://ad.easa.europa.eu/
rljohnson on DSK3VPTVN1PROD with PROPOSALS
Since we issued AD 2008–22–20, we fax 425–227–1149. blob/easa_ad_2007_0284_superseded.pdf/
have determined from a fatigue and AD_2007-0284_1)] to require implementation
SUPPLEMENTARY INFORMATION:
damage tolerance evaluation that the of an inspection programme of this structural
Comments Invited area using a high frequency eddy current
compliance times must be reduced. This (HFEC) method and a modification to
proposed AD would shorten certain We invite you to send any written improve the upper shell structure.
compliance times. We are proposing relevant data, views, or arguments about Since that [EASA] AD was issued, in the
this AD to prevent fatigue cracking of this proposed AD. Send your comments frame of a new fatigue and damage tolerance
the upper shell structure of the fuselage, to an address listed under the evaluation, taking into account the airplane
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![13800 Federal Register / Vol. 80, No. 51 / Tuesday, March 17, 2015 / Proposed Rules
utilisation, the inspection threshold and The FAA’s WFD final rule (75 FR 2012. The service information describes
intervals have been reassessed and the 69746, November 15, 2010) became procedures for applicable actions,
conclusion was that the thresholds and effective on January 14, 2011. The WFD including an eddy current rotating
intervals for inspection, as well as the rule requires certain actions to prevent
threshold for modifying the airplane, must be
probe test for cracking of the fastener
reduced.
structural failure due to WFD holes and an HFEC inspection for cracks
For the reason described above, this throughout the operational life of in the upper shell of the fuselage (and
[EASA] AD retains the requirements of EASA certain existing transport category including checks of the fastener position
AD 2007–0284, which is superseded and airplanes and all of these airplanes that for clearance and applicable corrective
introduces redefined thresholds and will be certificated in the future. For actions (e.g., repair and rework)), and a
intervals. existing and future airplanes subject to modification of the airplane upper shell
This [EASA] AD is revised to clarify that, the WFD rule, the rule requires that structure of the fuselage between FR80
under some conditions, accomplishment of a DAHs establish a limit of validity (LOV) and FR86.
repair constitutes terminating action for the of the engineering data that support the
repetitive inspections. One of the outcome of structural maintenance program. • Airbus Service Bulletin A330–53–
this clarification is the deletion of paragraph 3168, Revision 02, dated December 21,
(5) of this [EASA] AD.
Operators affected by the WFD rule may
not fly an airplane beyond its LOV, 2011. The service information describes
You may examine the MCAI in the unless an extended LOV is approved. procedures for a HFEC inspection for
AD docket on the Internet at http:// The WFD rule (75 FR 69746, cracking of the upper shell structure of
www.regulations.gov by searching for November 15, 2010) does not require the fuselage between FR80 and FR86.
and locating it in Docket No. FAA– identifying and developing maintenance • Airbus Service Bulletin A340–53–
2015–0490. actions if the DAHs can show that such 4165, Revision 02, dated March 29,
Initial compliance time thresholds actions are not necessary to prevent 2010. The service information describes
range from 7,300 flight cycles or 47,600 WFD before the airplane reaches the procedures for a modification of the
flight hours, and up to 25,400 flight LOV. Many LOVs, however, do depend fuselage, which includes inspections
cycles or 76,300 flight hours, depending on accomplishment of future (e.g., eddy current rotating probe test of
on configuration and range. maintenance actions. As stated in the fastener holes for cracking, HFEC
WFD rule, any maintenance actions inspections for cracking of the upper
Repetitive compliance time
necessary to reach the LOV will be shell structure of the fuselage, and
thresholds range from 1,700 flight cycles
mandated by airworthiness directives checks of the fastener position for
or 11,300 flight hours, and up to 4,500
through separate rulemaking actions. clearance) and applicable corrective
flight cycles or 13,500 flight hours, In the context of WFD, this action is
depending on configuration. actions (e.g., repair and rework).
necessary to enable DAHs to propose
Widespread Fatigue Damage LOVs that allow operators the longest • Airbus Service Bulletin A340–53–
operational lives for their airplanes, and 4172, Revision 01, dated July 8, 2009.
Structural fatigue damage is still ensure that WFD will not occur. The service information describes
progressive. It begins as minute cracks, This approach allows for an procedures for inspections (e.g., rototest
and those cracks grow under the action implementation strategy that provides inspections of fastener holes for
of repeated stresses. This can happen flexibility to DAHs in determining the cracking, HFEC inspections for cracking
because of normal operational timing of service information of the upper shell structure of the
conditions and design attributes, or development (with FAA approval), fuselage, and checks of the fastener
because of isolated situations or while providing operators with certainty position for clearance) and modification
incidents such as material defects, poor regarding the LOV applicable to their of the airplane upper shell structure
fabrication quality, or corrosion pits, airplanes. between FR80 and FR86 (including
dings, or scratches. Fatigue damage can applicable corrective actions (e.g., repair
occur locally, in small areas or Related Service Information Under 1 and rework).
structural design details, or globally. CFR Part 51
• Airbus Service Bulletin A340–53–
Global fatigue damage is general Airbus has issued the following 4174, Revision 02, dated December 21,
degradation of large areas of structure service information. The actions 2011. The service information describes
with similar structural details and stress described in this service information are procedures for a HFEC inspection for
levels. Multiple-site damage is global intended to correct the unsafe condition cracking of the upper shell structure of
damage that occurs in a large structural identified in the MCAI. This service
element such as a single rivet line of a the fuselage between FR80 and FR86.
information is reasonably available; see
lap splice joining two large skin panels. ADDRESSES for ways to access this FAA’s Determination and Requirements
Global damage can also occur in service information. of This Proposed AD
multiple elements such as adjacent • Airbus Service Bulletin A330–53–
frames or stringers. Multiple-site- 3159, Revision 02, dated March 29, This product has been approved by
damage and multiple-element-damage 2010. The service information describes the aviation authority of another
cracks are typically too small initially to procedures for a modification of the country, and is approved for operation
be reliably detected with normal fuselage, which includes inspections in the United States. Pursuant to our
inspection methods. Without (e.g., eddy current rotating probe test of bilateral agreement with the State of
intervention, these cracks will grow, fastener holes for cracking, high Design Authority, we have been notified
rljohnson on DSK3VPTVN1PROD with PROPOSALS
and eventually compromise the frequency eddy current (HFEC) of the unsafe condition described in the
structural integrity of the airplane, in a inspections for cracking of the upper MCAI and service information
condition known as widespread fatigue shell structure of the fuselage, and referenced above. We are proposing this
damage (WFD). As an airplane ages, checks of the fastener position for AD because we evaluated all pertinent
WFD will likely occur, and will clearance) and applicable corrective information and determined an unsafe
certainly occur if the airplane is actions (e.g., repair and rework). condition exists and is likely to exist or
operated long enough without any • Airbus Service Bulletin A330–53– develop on other products of the same
intervention. 3160, Revision 03, dated January 6, type design.
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![Federal Register / Vol. 80, No. 51 / Tuesday, March 17, 2015 / Proposed Rules 13801
Differences Between This Proposed AD General requirements.’’ Under that (b) Affected ADs
and the MCAI or Service Information section, Congress charges the FAA with This AD replaces AD 2008–22–20,
Unlike the procedures described in promoting safe flight of civil aircraft in Amendment 39–15717 (73 FR 66747,
air commerce by prescribing regulations November 12, 2008).
the service information, this proposed
AD would not permit further flight if for practices, methods, and procedures (c) Applicability
cracks are detected in the upper shell the Administrator finds necessary for
This AD applies to Airbus Model A330–
structure. We have determined that, safety in air commerce. This regulation 201, –202, –203, –223, –243, –301, –302,
because of the safety implications and is within the scope of that authority –303, –321, –322, –323, –341, –342, and
consequences associated with that because it addresses an unsafe condition –343; and Model A340–311, –312, and –313
cracking, any cracked upper shell that is likely to exist or develop on airplanes; certificated in any category; all
structure must be repaired before further products identified in this rulemaking manufacturer serial numbers on which
flight. This difference has been action. Airbus Modification 44205 has been
embodied in production, except those on
coordinated with the EASA and Airbus. Regulatory Findings which Airbus Modification 52974 or 53223
Explanation of Compliance Time for We determined that this proposed AD has been embodied in production.
Modification would not have federalism implications (d) Subject
The compliance time for the under Executive Order 13132. This Air Transport Association (ATA) of
modification specified in this proposed proposed AD would not have a America Code 53, Fuselage.
AD for addressing WFD was established substantial direct effect on the States, on
(e) Reason
to ensure that discrepant structure is the relationship between the national
modified before WFD develops in Government and the States, or on the This AD was prompted by the results of a
airplanes. Standard inspection distribution of power and fatigue and damage tolerance evaluation that
concluded existing compliance times must be
techniques cannot be relied on to detect responsibilities among the various
reduced. We are issuing this AD to prevent
WFD before it becomes a hazard to levels of government. fatigue cracking of the upper shell structure
flight. We will not grant any extensions For the reasons discussed above, I of the fuselage, which could result in
of the compliance time to complete any certify this proposed regulation: reduced structural integrity of the airplane.
AD-mandated service bulletin related to 1. Is not a ‘‘significant regulatory
WFD without extensive new data that (f) Compliance
action’’ under Executive Order 12866;
would substantiate and clearly warrant 2. Is not a ‘‘significant rule’’ under the Comply with this AD within the
such an extension. DOT Regulatory Policies and Procedures compliance times specified, unless already
done.
Costs of Compliance (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in (g) Inspection for Airbus Model A330–300
We estimate that this proposed AD Alaska; and and A340–300 Airplanes, Except Model
affects 26 airplanes of U.S. registry. We 4. Will not have a significant A340–300 Weight Variant (WV) 027
also estimate that it would take about economic impact, positive or negative, Airplanes
208 work-hours per product to comply on a substantial number of small entities For Model A330–300 and A340–300
with the basic requirements (inspection under the criteria of the Regulatory airplanes, except Model A340–300 WV 027
and modification) of this proposed AD. Flexibility Act. airplanes: At the applicable time specified in
The average labor rate is $85 per work- paragraph (g)(1) or (g)(2) of this AD, do a high
hour. Required parts would cost about List of Subjects in 14 CFR Part 39 frequency eddy current (HFEC) inspection for
$28,360 per product. Based on these cracking of the upper shell structure between
Air transportation, Aircraft, Aviation frame (FR) 80 and FR86, in accordance with
figures, we estimate the cost of this safety, Incorporation by reference, the Accomplishment Instructions of Airbus
proposed AD on U.S. operators to be Safety. Service Bulletin A330–53–3168, Revision 02,
$1,197,040, or $46,040 per product. dated December 21, 2011; or Airbus Service
We have received no definitive data The Proposed Amendment Bulletin A340–53–4174, Revision 02, dated
that would enable us to provide cost Accordingly, under the authority December 21, 2011; as applicable. Repeat the
estimates for the on-condition actions delegated to me by the Administrator, inspection thereafter at the applicable time
specified in this proposed AD. the FAA proposes to amend 14 CFR part specified in paragraph 1.E., ‘‘COMPLIANCE,’’
According to the manufacturer, some 39 as follows: of Airbus Service Bulletin A330–53–3168,
of the costs of this proposed AD may be Revision 02, dated December 21, 2011; or
covered under warranty, thereby PART 39—AIRWORTHINESS Airbus Service Bulletin A340–53–4174,
reducing the cost impact on affected Revision 02, dated December 21, 2011; as
DIRECTIVES applicable.
individuals. We do not control warranty (1) For airplanes that, as of the effective
coverage for affected individuals. As a ■ 1. The authority citation for part 39 date of this AD, have not been inspected in
result, we have included all costs in our continues to read as follows: accordance with Airbus Service Bulletin
cost estimate. Authority: 49 U.S.C. 106(g), 40113, 44701. A330–53–3168; or Airbus Service Bulletin
A340–53–4174; as applicable: Inspect at the
Authority for This Rulemaking § 39.13 [Amended] later of the times specified in paragraphs
Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by (g)(1)(i) and (g)(1)(ii) of this AD.
specifies the FAA’s authority to issue removing Airworthiness Directive (AD) (i) Before reaching the applicable threshold
rules on aviation safety. Subtitle I, 2008–22–20, Amendment 39–15717 (73 specified in paragraph 1.E., ‘‘COMPLIANCE,’’
rljohnson on DSK3VPTVN1PROD with PROPOSALS
section 106, describes the authority of of Airbus Service Bulletin A330–53–3168,
FR 66747, November 12, 2008), and Revision 02, dated December 21, 2011; or
the FAA Administrator. ‘‘Subtitle VII: adding the following new AD: Airbus Service Bulletin A340–53–4174,
Aviation Programs,’’ describes in more Revision 02, dated December 21, 2011; as
Airbus: Docket No. FAA–2015–0490;
detail the scope of the Agency’s Directorate Identifier 2014–NM–018–AD. applicable for airplane model, configuration,
authority. and utilization, since the airplane’s first
We are issuing this rulemaking under (a) Comments Due Date flight.
the authority described in ‘‘Subtitle VII, We must receive comments by May 1, (ii) Within the threshold defined in
Part A, Subpart III, Section 44701: 2015. paragraph 1.E, ‘‘COMPLIANCE,’’ of Airbus
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![Federal Register / Vol. 80, No. 51 / Tuesday, March 17, 2015 / Proposed Rules 13803
inspector, the manager of the local flight DATES: We must receive your comments absolute or competitive preference
standards district office/certificate holding on or before April 16, 2015. priority, affects the overall amount of
district office. The AMOC approval letter funding available to individual
ADDRESSES: Submit your comments
must specifically reference this AD.
through the Federal eRulemaking Portal applicants in any given fiscal year.
(2) Contacting the Manufacturer: As of the
or via postal mail, commercial delivery, In addition, we note that participation
effective date of this AD, for any requirement
in this AD to obtain corrective actions from or hand delivery. We will not accept in this program is voluntary. Potential
a manufacturer, the action must be comments by fax or by email or those applicants need to consider carefully
accomplished using a method approved by submitted after the comment period. To the effort that will be required to
the Manager, International Branch, ANM– ensure that we do not receive duplicate prepare a strong application, their
116, Transport Airplane Directorate, FAA; or copies, please submit your comments capacity to implement a project
the EASA; or Airbus’s EASA DOA. If successfully, and their chances of
approved by the DOA, the approval must
only once. In addition, please include
the Docket ID at the top of your submitting a successful application. We
include the DOA-authorized signature. believe that the costs imposed on
comments.
(p) Related Information • Federal eRulemaking Portal: Go to applicants by the proposed priority
(1) Refer to Mandatory Continuing www.regulations.gov to submit your would be limited to paperwork burden
Airworthiness Information (MCAI) EASA comments electronically. Information related to preparing an application and
Airworthiness Directive 2014–0012R1, dated on using Regulations.gov, including that the benefits of implementing these
January 24, 2014, for related information. instructions for accessing agency proposals would outweigh any costs
This MCAI may be found in the AD docket incurred by applicants. The costs of
documents, submitting comments, and
on the Internet at http://www.regulations.gov carrying out activities would be paid for
by searching for and locating Docket No. viewing the docket, is available on the
site under ‘‘Are you new to this site?’’ with program funds and with matching
FAA–2015–0490. funds provided by private-sector
(2) For service information identified in • Postal Mail, Commercial Delivery,
this AD, contact Airbus SAS, Airworthiness or Hand Delivery: If you mail or deliver partners. Thus, the costs of
Office—EAL, 1 Rond Point Maurice Bellonte, your comments about these proposed implementation would not be a burden
31707 Blagnac Cedex, France; telephone +33 regulations, address them to Allison for any eligible applicants, including
5 61 93 36 96; fax +33 5 61 93 45 80; email Moss, U.S. Department of Education, small entities.
airworthiness.A330-A340@airbus.com; 400 Maryland Avenue SW., Room Invitation to Comment: We invite you
Internet http://www.airbus.com. You may 4W319, Washington, DC 20202–5930. to submit comments regarding this
view this service information at the FAA, notice.
Transport Airplane Directorate, 1601 Lind Privacy Note: The Department of We invite you to assist us in
Avenue SW., Renton, WA. For information Education’s (Department) policy is to make complying with the specific
on the availability of this material at the all comments received from members of the requirements of Executive Orders 12866
FAA, call 425–227–1221. public available for public viewing in their
and 13563 and their overall requirement
entirety on the Federal eRulemaking Portal at
Issued in Renton, Washington, on March 2, www.regulations.gov. Therefore, commenters of reducing regulatory burden that
2015. should be careful to include in their might result from this proposed priority.
Jeffrey E. Duven, comments only information that they wish to Please let us know of any further ways
Manager, Transport Airplane Directorate, make publicly available. we could reduce potential costs or
Aircraft Certification Service. increase potential benefits while
FOR FURTHER INFORMATION CONTACT:
[FR Doc. 2015–05720 Filed 3–16–15; 8:45 am] preserving the effective and efficient
Allison Moss. Telephone: (202) 205– administration of the program.
BILLING CODE 4910–13–P
7726 or by email: Allison.moss@ed.gov. During and after the comment period,
If you use a telecommunications you may inspect all public comments
device for the deaf (TDD) or a text about this notice by accessing
DEPARTMENT OF EDUCATION telephone (TTY), call the Federal Relay Regulations.gov. You may also inspect
Service (FRS), toll free, at 1–800–877– the comments in person in Room
34 CFR Subtitle A
8339. 4W335, 400 Maryland Avenue SW.,
[Docket No.: ED–2015–OII–0006; (CFDA) SUPPLEMENTARY INFORMATION: Washington, DC, between the hours of
Numbers: 84.411A (Scale-up grants),
Summary of the Major Provisions of 8:30 a.m. and 4:00 p.m., Washington,
84.411B (Validation grants), and 84.411C
(Development grants)] This Regulatory Action: In this DC time, Monday through Friday of
document, the Department proposes a each week except Federal holidays.
RIN 1855–ZA10 priority for the i3 program that would Please contact the person listed under
promote the implementation of FOR FURTHER INFORMATION CONTACT in
Proposed Priority—Investing in comprehensive high school reform and order to schedule a time to inspect
Innovation Fund; Catalog of Federal redesign strategies. This proposed comments in person.
Domestic Assistance priority could be used in the Assistance to Individuals With
AGENCY: Office of Innovation and Development, Validation, or Scale-up Disabilities in Reviewing the
Improvement, Department of Education. tier of the i3 program in future years, as Rulemaking Record: On request we will
ACTION: Proposed priority. appropriate. provide an appropriate accommodation
Costs and Benefits: The Assistant or auxiliary aid to an individual with a
SUMMARY: The Assistant Deputy Deputy Secretary believes that the disability who needs assistance to
Secretary for Innovation and proposed priority would not impose review the comments or other
rljohnson on DSK3VPTVN1PROD with PROPOSALS
Improvement proposes a priority under significant costs on eligible applicants documents in the public rulemaking
the Investing in Innovation Fund (i3). seeking assistance through the i3 record for this notice. If you want to
The Assistant Deputy Secretary may use program. schedule an appointment for this type of
this priority for competitions in fiscal The proposed priority is designed to accommodation or auxiliary aid, please
year (FY) 2015 and later years. The be used in conjunction with several contact the person listed under FOR
proposed priority would not repeal or priorities that have already been FURTHER INFORMATION CONTACT.
replace currently established priorities established under the i3 program, and Purpose of Program: The i3 program
for this program. no priority, whether it is used as an addresses two related challenges. First,
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Document Created: 2015-12-18 12:01:09
Document Modified: 2015-12-18 12:01:09
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by May 1, 2015. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. | |
| FR Citation | 80 FR 13799 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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