80 FR 19892 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 71 (April 14, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 71 (April 14, 2015)
| Page Range | 19892-19895 | |
| FR Document | 2015-08071 |
[Federal Register Volume 80, Number 71 (Tuesday, April 14, 2015)] [Proposed Rules] [Pages 19892-19895] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-08071] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0824; Directorate Identifier 2013-NM-191-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) 98-20-27, for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 98-20-27 currently requires repetitive inspections to detect fatigue cracking of the wing top skin at the front spar joint; and a follow-on eddy current inspection and repair, if necessary. Since we issued AD 98-20-27, we have received reports of cracking of the wing top skin in an area not required for inspection by AD 98-20-27. This proposed AD would reduce the inspection compliance time and intervals, and extend the inspection area of the wing top skin at the front spar joint. We are proposing this AD to detect and correct fatigue cracking of the wing top skin at the front spar joint, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by May 29, 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--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. 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- 0824; 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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 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-2015-0824; Directorate Identifier 2013-NM-191-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 September 16, 1998, we issued AD 98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998). AD 98-20-27 requires actions intended to address an unsafe condition on all Airbus Model A300 B4- 600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). Since we issued AD 98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998): The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013-0232R1, dated October 2, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition. The MCAI states: During full-scale fatigue testing conducted in the early 1990's, cracks were found on the top skin of the wing between Ribs 1 and 7, starting at the front spar fastener holes. This condition, if not detected and corrected, could adversely affect the structural integrity of the wing. Consequently, Airbus issued Service Bulletin (SB) A300-57-6045 and DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 97-374-238 [http://ad.easa.europa.eu/blob/19973740tb_superseded.pdf/AD_F-1997-374-238_2] for A300-600 aeroplanes and AD 1999-008-020 [http://ad.easa.europa.eu/blob/19980080tb_superseded.pdf/AD_F-1999-008-020_2] for A300-600ST aeroplanes to require repetitive detailed inspections of the wing top skin and, in case of findings, an Eddy Current (EC) inspection, and, depending on the size of the cracks, repair. After those [DGAC] ADs were issued, further cracks to the wing top skin were reported by operators, within an area not covered by the existing [DGAC] ADs. To address this potential unsafe condition, Airbus revised SB A300-57-6045 to extend the area to be inspected. In addition, a fleet survey and updated Fatigue and Damage Tolerance analyses were performed in order to substantiate the second A300-600 Extended Service Goal (ESG2) exercise. The results of these analyses have determined that the inspection thresholds and intervals must be reduced to allow timely detection of these cracks and the accomplishment of applicable corrective action(s). As the ESG2 exercise is only applicable to A300-600 aeroplanes, A300-600ST aeroplanes are now addressed through new Airbus SB A300- 57-9026. For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD 97-374-238(B) [http://ad.easa.europa.eu/blob/19973740tb_superseded.pdf/AD_F-1997-374-238_2] [which corresponds to FAA AD 98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998)] and [DGAC] AD 1999-008-020(B) [http://ad.easa.europa.eu/blob/19980080tb_superseded.pdf/AD_F-1999-008-020_2], which are superseded, but requires [[Page 19893]] those actions, for A300-600 aeroplanes only, within reduced thresholds and intervals. * * * * * You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 0824. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300-57-6045, Revision 10, dated November 13, 2013. The service information describes inspection procedures for fatigue cracking of the wing top skin at the front spar joint between ribs 1 and 7. 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. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This Proposed AD and the MCAI or Service Information Unlike the procedures described in the MCAI and Airbus Service Bulletin A300-57-6045, Revision 10, dated November 13, 2013, this proposed AD would not permit further flight if cracks are detected in the wing top skin at the front spar joint. We have determined that, because of the safety implications and consequences associated with that cracking, any cracked wing top skin at the front spar joint must be repaired before further flight. This difference has been coordinated with the EASA. Costs of Compliance We estimate that this proposed AD affects 130 airplanes of U.S. registry. The actions that are required by AD 98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998), and retained in this proposed 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 are required by AD 98-20-27 is $170 per product. We also estimate that it would take about 2 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $22,100, or $170 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. 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) 98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998), and adding the following new AD: Airbus: Docket No. FAA-2015-0824; Directorate Identifier 2013-NM- 191-AD. (a) Comments Due Date We must receive comments by May 29, 2015. (b) Affected ADs This AD replaces AD 98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (2) Airbus Model A300 B4-605R and B4-622R airplanes. (3) Airbus Model A300 F4-605R and F4-622R airplanes. (4) Airbus Model A300 C4-605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports of cracking of wing top skin in an area not required for inspection by AD 98-20-27, Amendment 39- 10793 (63 FR 50981, September 24, 1998). We are issuing this AD to detect and correct fatigue cracking of the wing top skin at the front spar joint, 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) Retained Repetitive Inspections, With Revised Service Information This paragraph restates the requirements of paragraph (a) of AD 98-20-27, Amendment [[Page 19894]] 39-10793 (63 FR 50981, September 24, 1998), with revised service information. Prior to the accumulation of 22,000 total flight cycles, or within 2,000 flight cycles after October 29, 1998 (the effective date of AD 98-20-27), whichever occurs later: Perform a detailed visual inspection to detect fatigue cracking of the wing top skin at the front spar joint, in accordance with Airbus Service Bulletin A300-57-6045, Revision 1, dated August 3, 1994, including Appendix 1, Revision 1, dated August 3, 1994; Airbus Service Bulletin A300-57-6045, Revision 02, dated April 21, 1998, including Appendix 1, Revision 02, dated April 21, 1998; or Airbus Service Bulletin A300-57-6045, Revision 10, dated November 13, 2013. Repeat the detailed visual inspection thereafter at intervals not to exceed 8,000 flight cycles. (h) Retained Inspection and Repair, With Revised Service Information This paragraph restates the requirements of paragraph (b) of AD 98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998), with revised service information. If any cracking is suspected or detected during any inspection required by paragraph (g) of this AD: Prior to further flight, perform an eddy current inspection to confirm the findings of the visual inspection, in accordance with Airbus Service Bulletin A300-57-6045, Revision 01, dated August 3, 1994, including Appendix 1, Revision 01, dated August 3, 1994; Airbus Service Bulletin A300-57-6045, Revision 02, dated April 21, 1998, including Appendix 1, Revision 02, dated April 21, 1998; or Airbus Service Bulletin A300-57-6045, Revision 10, dated November 13, 2013. If any cracking is detected during any eddy current inspection, prior to further flight, repair using a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its delegated agent). (i) New Requirement of This AD: Initial Inspection At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD: Do a detailed inspection of the wing top skin between ribs one and seven for cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6045, Revision 10, dated November 13, 2013. Accomplishment of the initial inspection required by this paragraph terminates the requirements of paragraph (g) of this AD. (1) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes, Model A300 B4-605R and B4-622R airplanes, and Model A300 C4-605R Variant F airplanes: At the later of the times specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. (i) Before the accumulation of 17,100 total flight cycles or 38,400 total flight hours, whichever occurs first. (ii) Within 1,000 flight cycles or 2,200 flight hours, whichever occurs first after the effective date of this AD. (2) For Model A300 F4-605R and F4-622R airplanes: At the later of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD. (i) Before the accumulation of 22,000 total flight cycles or 49,500 total flight hours, whichever occurs first. (ii) Within 1,300 flight cycles or 2,800 flight hours, whichever occurs first after the effective date of this AD. (j) New Requirement of This AD: Repetitive Inspections Repeat the inspection required by paragraph (i) of this AD thereafter at the applicable time and intervals specified in paragraphs (j)(1) and (j)(2) of this AD. (1) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes, Model A300 B4-605R and B4-622R airplanes, and Model A300 C4-605R Variant F airplanes: At the applicable time specified in paragraph (j)(1)(i) or (j)(1)(ii) of this AD. (i) For airplanes that have an average flight time (AFT) that is equal to or more than one and one-half hours: At intervals not to exceed 5,100 flight cycles or 11,000 flight hours, whichever occurs first. (ii) For airplanes that have an AFT that is less than one and one-half hours: At intervals not to exceed 5,500 flight cycles or 8,300 flight hours, whichever occurs first. (2) For Model A300 F4-605R and F4-622R airplanes: At the applicable time specified in paragraph (j)(2)(i) or (j)(2)(ii) of this AD. (i) For airplanes that have an AFT that is equal to or more than one and one-half hours: At intervals not to exceed 6,500 flight cycles or 14,100 flight hours, whichever occurs first. (ii) For airplanes that have an AFT that is less than one and one-half hours: At intervals not to exceed 7,000 flight cycles or 10,600 flight hours, whichever occurs first. (k) New Requirement of This AD: Repair of Cracking (1) If any crack in the top skin in the area forward of the front spar attachment is found during any inspection required by paragraph (i) 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. (2) If any crack or sign of a crack is found in the top skin at or aft of the spar attachment during any inspection required by paragraph (i) of this AD: Before further flight, do an eddy current inspection of the cracks or of the signs of cracking to confirm the findings of the detailed inspection, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6045, Revision 10, dated November 13, 2013. If there are any cracks at or aft of the spar attachment, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; EASA; or Airbus's EASA DOA. (l) No Terminating Action Accomplishment of any repair required by paragraph (k) this AD does not constitute terminating action for the repetitive inspections required by paragraph (j) of this AD. (m) No Reporting Required Although Airbus Service Bulletin A300-57-6045, Revision 10, dated November 13, 2013, specifies to submit certain information to the manufacturer, this AD does not include that requirement. (n) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (i), (j) and (k) of this AD, if those actions were performed before the effective date of this AD using the Airbus service bulletins specified in paragraphs (n)(1) through (n)(10) of this AD, which are not incorporated by reference in this AD. (1) Airbus Service Bulletin A300-57-6045, dated March 18, 1993. (2) Airbus Service Bulletin A300-57-6045, Revision 01, dated August 3, 1994. (3) Airbus Service Bulletin A300-57-6045, Revision 02, dated April 21, 1998. (4) Airbus Service Bulletin A300-57-6045, Revision 03, dated October 25, 1999. (5) Airbus Service Bulletin A300-57-6045, Revision 04, dated January 13, 2002. (6) Airbus Service Bulletin A300-57-6045, Revision 05, dated June 13, 2003. (7) Airbus Service Bulletin A300-57-6045, Revision 06, dated January 13, 2005. (8) Airbus Service Bulletin A300-57-6045, Revision 07, dated August 14, 2008. (9) Airbus Service Bulletin A300-57-6045, Revision 08, dated June 6, 2011. (10) Airbus Service Bulletin A300-57-6045, Revision 09, dated May 21, 2013. (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, 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: Dan Rodina, Aerospace Engineer, International Branch, ANM- 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. Information may be emailed to: [email protected]. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously for AD 98-20-27, Amendment 39- 10793 (63 FR 50981, September 24, 1998), 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 EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. [[Page 19895]] (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013-0232R1, dated October 2, 2013, 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-2015-0824. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. 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 27, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-08071 Filed 4-13-15; 8:45 am] BILLING CODE 4910-13-P
![19892 Federal Register / Vol. 80, No. 71 / Tuesday, April 14, 2015 / Proposed Rules
Issued in Kansas City, Missouri, on April p.m., Monday through Friday, except FR 50981, September 24, 1998). AD 98–
6, 2015. Federal holidays. 20–27 requires actions intended to
Pat Mullen, For service information identified in address an unsafe condition on all
Acting Manager, Small Airplane Directorate, this proposed AD, contact Airbus SAS, Airbus Model A300 B4–600, B4–600R,
Aircraft Certification Service. Airworthiness Office—EAW, 1 Rond and F4–600R series airplanes, and
[FR Doc. 2015–08586 Filed 4–13–15; 8:45 am] Point Maurice Bellonte, 31707 Blagnac Model A300 C4–605R Variant F
BILLING CODE 4910–13–P Cedex, France; telephone +33 5 61 93 36 airplanes (collectively called Model
96; fax +33 5 61 93 44 51; email A300–600 series airplanes).
account.airworth-eas@airbus.com; Since we issued AD 98–20–27,
DEPARTMENT OF TRANSPORTATION Internet http://www.airbus.com. You Amendment 39–10793 (63 FR 50981,
may view this referenced service September 24, 1998): The European
Federal Aviation Administration information at the FAA, Transport Aviation Safety Agency (EASA), which
Airplane Directorate, 1601 Lind Avenue is the Technical Agent for the Member
14 CFR Part 39 SW., Renton, WA. For information on States of the European Union, has
[Docket No. FAA–2015–0824; Directorate the availability of this material at the issued EASA Airworthiness Directive
Identifier 2013–NM–191–AD] FAA, call 425–227–1221. 2013–0232R1, dated October 2, 2013
RIN 2120–AA64 Examining the AD Docket (referred to after this as the Mandatory
Continuing Airworthiness Information,
You may examine the AD docket on
Airworthiness Directives; Airbus or ‘‘the MCAI’’), to correct an unsafe
the Internet at http://
Airplanes condition. The MCAI states:
www.regulations.gov by searching for
and locating Docket No. FAA–2015– During full-scale fatigue testing conducted
AGENCY: Federal Aviation in the early 1990’s, cracks were found on the
Administration (FAA), DOT. 0824; or in person at the Docket
Management Facility between 9 a.m. top skin of the wing between Ribs 1 and 7,
ACTION: Notice of proposed rulemaking starting at the front spar fastener holes.
and 5 p.m., Monday through Friday,
(NPRM). This condition, if not detected and
except Federal holidays. The AD docket corrected, could adversely affect the
SUMMARY: We propose to supersede contains this proposed AD, the structural integrity of the wing.
Airworthiness Directive (AD) 98–20–27, regulatory evaluation, any comments Consequently, Airbus issued Service
for all Airbus Model A300 B4–600, B4– received, and other information. The Bulletin (SB) A300–57–6045 and DGAC
600R, and F4–600R series airplanes, and street address for the Docket Operations [Direction Générale de l’Aviation Civile]
Model A300 C4–605R Variant F office (telephone 800–647–5527) is in France issued AD 97–374–238 [http://
the ADDRESSES section. Comments will ad.easa.europa.eu/blob/19973740tb_
airplanes (collectively called Model superseded.pdf/AD_F-1997-374-238_2] for
A300–600 series airplanes). AD 98–20– be available in the AD docket shortly
after receipt. A300–600 aeroplanes and AD 1999–008–020
27 currently requires repetitive [http://ad.easa.europa.eu/blob/19980080tb_
inspections to detect fatigue cracking of FOR FURTHER INFORMATION CONTACT: Dan superseded.pdf/AD_F-1999-008-020_2] for
the wing top skin at the front spar joint; Rodina, Aerospace Engineer, A300–600ST aeroplanes to require repetitive
and a follow-on eddy current inspection International Branch, ANM–116, detailed inspections of the wing top skin and,
and repair, if necessary. Since we issued Transport Airplane Directorate, FAA, in case of findings, an Eddy Current (EC)
AD 98–20–27, we have received reports 1601 Lind Avenue SW., Renton, WA inspection, and, depending on the size of the
98057–3356; telephone 425–227–2125; cracks, repair.
of cracking of the wing top skin in an
fax 425–227–1149. After those [DGAC] ADs were issued,
area not required for inspection by AD further cracks to the wing top skin were
98–20–27. This proposed AD would SUPPLEMENTARY INFORMATION:
reported by operators, within an area not
reduce the inspection compliance time Comments Invited covered by the existing [DGAC] ADs. To
and intervals, and extend the inspection address this potential unsafe condition,
area of the wing top skin at the front We invite you to send any written Airbus revised SB A300–57–6045 to extend
spar joint. We are proposing this AD to relevant data, views, or arguments about the area to be inspected.
detect and correct fatigue cracking of the this proposed AD. Send your comments In addition, a fleet survey and updated
wing top skin at the front spar joint, to an address listed under the Fatigue and Damage Tolerance analyses were
ADDRESSES section. Include ‘‘Docket No. performed in order to substantiate the second
which could result in reduced structural
FAA–2015–0824; Directorate Identifier A300–600 Extended Service Goal (ESG2)
integrity of the airplane. exercise. The results of these analyses have
2013–NM–191–AD’’ at the beginning of
DATES: We must receive comments on determined that the inspection thresholds
your comments. We specifically invite
this proposed AD by May 29, 2015. and intervals must be reduced to allow
comments on the overall regulatory, timely detection of these cracks and the
ADDRESSES: You may send comments by economic, environmental, and energy
any of the following methods: accomplishment of applicable corrective
aspects of this proposed AD. We will action(s).
• Federal eRulemaking Portal: Go to consider all comments received by the As the ESG2 exercise is only applicable to
http://www.regulations.gov. Follow the closing date and may amend this A300–600 aeroplanes, A300–600ST
instructions for submitting comments. proposed AD based on those comments. aeroplanes are now addressed through new
• Fax: (202) 493–2251. We will post all comments we Airbus SB A300–57–9026.
• Mail: U.S. Department of receive, without change, to http:// For the reasons described above, this
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Transportation, Docket Operations, www.regulations.gov, including any [EASA] AD retains the requirements of DGAC
M–30, West Building Ground Floor, personal information you provide. We France AD 97–374–238(B) [http://
Room W12–140, 1200 New Jersey ad.easa.europa.eu/blob/19973740tb_
will also post a report summarizing each superseded.pdf/AD_F-1997-374-238_2]
Avenue SE., Washington, DC 20590. substantive verbal contact we receive [which corresponds to FAA AD 98–20–27,
• Hand Delivery: U.S. Department of about this proposed AD. Amendment 39–10793 (63 FR 50981,
Transportation, Docket Operations, M– September 24, 1998)] and [DGAC] AD 1999–
30, West Building Ground Floor, Room Discussion
008–020(B) [http://ad.easa.europa.eu/blob/
W12–140, 1200 New Jersey Avenue SE., On September 16, 1998, we issued AD 19980080tb_superseded.pdf/AD_F-1999-008-
Washington, DC, between 9 a.m. and 5 98–20–27, Amendment 39–10793 (63 020_2], which are superseded, but requires
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![Federal Register / Vol. 80, No. 71 / Tuesday, April 14, 2015 / Proposed Rules 19893
those actions, for A300–600 aeroplanes only, the actions that are required by AD 98– List of Subjects in 14 CFR Part 39
within reduced thresholds and intervals. 20–27 is $170 per product. Air transportation, Aircraft, Aviation
* * * * * We also estimate that it would take safety, Incorporation by reference,
You may examine the MCAI in the about 2 work-hours per product to Safety.
AD docket on the Internet at http:// comply with the basic requirements of
The Proposed Amendment
www.regulations.gov by searching for this proposed AD. The average labor
and locating Docket No. FAA–2015– rate is $85 per work-hour. Based on Accordingly, under the authority
0824. these figures, we estimate the cost of delegated to me by the Administrator,
this proposed AD on U.S. operators to the FAA proposes to amend 14 CFR part
Related Service Information Under 1 be $22,100, or $170 per product. 39 as follows:
CFR Part 51
We have received no definitive data PART 39—AIRWORTHINESS
Airbus has issued Service Bulletin that would enable us to provide cost DIRECTIVES
A300–57–6045, Revision 10, dated estimates for the on-condition actions
November 13, 2013. The service specified in this proposed AD. ■ 1. The authority citation for part 39
information describes inspection continues to read as follows:
procedures for fatigue cracking of the Authority for This Rulemaking
Authority: 49 U.S.C. 106(g), 40113, 44701.
wing top skin at the front spar joint
between ribs 1 and 7. The actions Title 49 of the United States Code
§ 39.13 [Amended]
described in this service information are specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I, ■ 2. The FAA amends § 39.13 by
intended to correct the unsafe condition removing Airworthiness Directive (AD)
identified in the MCAI. This service section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII: 98–20–27, Amendment 39–10793 (63
information is reasonably available; see FR 50981, September 24, 1998), and
ADDRESSES for ways to access this
Aviation Programs,’’ describes in more
detail the scope of the Agency’s adding the following new AD:
service information.
authority. Airbus: Docket No. FAA–2015–0824;
FAA’s Determination and Requirements We are issuing this rulemaking under
Directorate Identifier 2013–NM–191–AD.
of This Proposed AD the authority described in ‘‘Subtitle VII, (a) Comments Due Date
This product has been approved by Part A, Subpart III, Section 44701: We must receive comments by May 29,
the aviation authority of another General requirements.’’ Under that 2015.
country, and is approved for operation section, Congress charges the FAA with (b) Affected ADs
in the United States. Pursuant to our promoting safe flight of civil aircraft in
This AD replaces AD 98–20–27,
bilateral agreement with the State of air commerce by prescribing regulations
Amendment 39–10793 (63 FR 50981,
Design Authority, we have been notified for practices, methods, and procedures September 24, 1998).
of the unsafe condition described in the the Administrator finds necessary for
MCAI and service information safety in air commerce. This regulation (c) Applicability
referenced above. We are proposing this is within the scope of that authority This AD applies to the Airbus airplanes
AD because we evaluated all pertinent because it addresses an unsafe condition identified in paragraphs (c)(1) through (c)(4)
information and determined an unsafe that is likely to exist or develop on of this AD, certificated in any category, all
products identified in this rulemaking manufacturer serial numbers.
condition exists and is likely to exist or
(1) Airbus Model A300 B4–601, B4–603,
develop on other products of the same action. B4–620, and B4–622 airplanes.
type design. (2) Airbus Model A300 B4–605R and B4–
Regulatory Findings
Differences Between This Proposed AD 622R airplanes.
We determined that this proposed AD (3) Airbus Model A300 F4–605R and F4–
and the MCAI or Service Information
would not have federalism implications 622R airplanes.
Unlike the procedures described in under Executive Order 13132. This (4) Airbus Model A300 C4–605R Variant F
the MCAI and Airbus Service Bulletin airplanes.
proposed AD would not have a
A300–57–6045, Revision 10, dated substantial direct effect on the States, on (d) Subject
November 13, 2013, this proposed AD the relationship between the national Air Transport Association (ATA) of
would not permit further flight if cracks Government and the States, or on the America Code 57, Wings.
are detected in the wing top skin at the distribution of power and
front spar joint. We have determined (e) Reason
responsibilities among the various
that, because of the safety implications levels of government. This AD was prompted by reports of
and consequences associated with that cracking of wing top skin in an area not
cracking, any cracked wing top skin at For the reasons discussed above, I required for inspection by AD 98–20–27,
the front spar joint must be repaired certify this proposed regulation: Amendment 39–10793 (63 FR 50981,
September 24, 1998). We are issuing this AD
before further flight. This difference has 1. Is not a ‘‘significant regulatory
to detect and correct fatigue cracking of the
been coordinated with the EASA. action’’ under Executive Order 12866; wing top skin at the front spar joint, which
Costs of Compliance 2. Is not a ‘‘significant rule’’ under the could result in reduced structural integrity of
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
DOT Regulatory Policies and Procedures the airplane.
We estimate that this proposed AD (44 FR 11034, February 26, 1979);
affects 130 airplanes of U.S. registry. (f) Compliance
The actions that are required by AD 3. Will not affect intrastate aviation in Comply with this AD within the
98–20–27, Amendment 39–10793 (63 Alaska; and compliance times specified, unless already
done.
FR 50981, September 24, 1998), and 4. Will not have a significant
retained in this proposed AD take about economic impact, positive or negative, (g) Retained Repetitive Inspections, With
2 work-hours per product, at an average on a substantial number of small entities Revised Service Information
labor rate of $85 per work-hour. Based under the criteria of the Regulatory This paragraph restates the requirements of
on these figures, the estimated cost of Flexibility Act. paragraph (a) of AD 98–20–27, Amendment
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![Federal Register / Vol. 80, No. 71 / Tuesday, April 14, 2015 / Proposed Rules 19895
(p) Related Information notice as posted within Docket No. Definition
(1) Refer to Mandatory Continuing TTB–2015–0007 at Regulations.gov, the Section 4.25(e)(1)(i) of the TTB
Airworthiness Information (MCAI) EASA Federal e-rulemaking portal); regulations (27 CFR 4.25(e)(1)(i)) defines
Airworthiness Directive 2013–0232R1, dated
• U.S. Mail: Director, Regulations and a viticultural area for American wine as
October 2, 2013, for related information. This
MCAI may be found in the AD docket on the Rulings Division, Alcohol and Tobacco a delimited grape-growing region having
Internet at http://www.regulations.gov by Tax and Trade Bureau, 1310 G Street distinguishing features, as described in
searching for and locating Docket No. FAA– NW., Box 12, Washington, DC 20005; or part 9 of the regulations, and a name
2015–0824. • Hand delivery/courier in lieu of and a delineated boundary, as
(2) For service information identified in mail: Alcohol and Tobacco Tax and established in part 9 of the regulations.
this AD, contact Airbus SAS, Airworthiness These designations allow vintners and
Trade Bureau, 1310 G Street NW., Suite
Office—EAW, 1 Rond Point Maurice consumers to attribute a given quality,
Bellonte, 31707 Blagnac Cedex, France; 200–E, Washington, DC 20005.
reputation, or other characteristic of a
telephone +33 5 61 93 36 96; fax +33 5 61 See the PUBLIC PARTICIPATION section wine made from grapes grown in an area
93 44 51; email account.airworth-eas@ of this notice for specific instructions
airbus.com; Internet http://www.airbus.com. to the wine’s geographic origin. The
and requirements for submitting establishment of AVAs allows vintners
You may view this service information at the comments, and for information on how
FAA, Transport Airplane Directorate, 1601 to describe more accurately the origin of
Lind Avenue SW., Renton, WA. For
to request a public hearing or view or their wines to consumers and helps
information on the availability of this obtain copies of the petition and consumers to identify wines they may
material at the FAA, call 425–227–1221. supporting materials. purchase. Establishment of an AVA is
Issued in Renton, Washington, on March FOR FURTHER INFORMATION CONTACT: neither an approval nor an endorsement
27, 2015. Karen A. Thornton, Regulations and by TTB of the wine produced in that
Michael Kaszycki, Rulings Division, Alcohol and Tobacco area.
Acting Manager, Transport Airplane Tax and Trade Bureau, 1310 G St. NW., Requirements
Directorate, Aircraft Certification Service. Box 12, Washington, DC 20005; phone
[FR Doc. 2015–08071 Filed 4–13–15; 8:45 am] 202–453–1039, ext. 175. Section 4.25(e)(2) of the TTB
BILLING CODE 4910–13–P
regulations (27 CFR 4.25(e)(2)) outlines
SUPPLEMENTARY INFORMATION: the procedure for proposing an AVA
Background on Viticultural Areas and provides that any interested party
may petition TTB to establish a grape-
DEPARTMENT OF THE TREASURY TTB Authority growing region as an AVA. Section 9.12
Alcohol and Tobacco Tax and Trade of the TTB regulations (27 CFR 9.12)
Section 105(e) of the Federal Alcohol prescribes the standards for petitions for
Bureau Administration Act (FAA Act), 27 the establishment or modification of
U.S.C. 205(e), authorizes the Secretary AVAs. Petitions to establish an AVA
27 CFR Part 9 of the Treasury to prescribe regulations must include the following:
[Docket No. TTB–2015–0007; Notice No. for the labeling of wine, distilled spirits, • Evidence that the area within the
151] and malt beverages. The FAA Act proposed AVA boundary is nationally
provides that these regulations should, or locally known by the AVA name
RIN 1513–AC17
among other things, prohibit consumer specified in the petition;
Proposed Establishment of the deception and the use of misleading • An explanation of the basis for
Lamorinda Viticultural Area statements on labels, and ensure that defining the boundary of the proposed
labels provide the consumer with AVA;
AGENCY: Alcohol and Tobacco Tax and adequate information as to the identity • A narrative description of the
Trade Bureau, Treasury. and quality of the product. The Alcohol features of the proposed AVA affecting
ACTION: Notice of proposed rulemaking. and Tobacco Tax and Trade Bureau viticulture, such as climate, geology,
(TTB) administers the FAA Act soils, physical features, and elevation,
SUMMARY: The Alcohol and Tobacco Tax pursuant to section 1111(d) of the that make the proposed AVA distinctive
and Trade Bureau (TTB) proposes to Homeland Security Act of 2002, and distinguish it from adjacent areas
establish the approximately 29,369-acre codified at 6 U.S.C. 531(d). The outside the proposed AVA boundary;
‘‘Lamorinda’’ viticultural area in Contra Secretary has delegated various • The appropriate United States
Costa County, California. The proposed authorities through Treasury Geological Survey (USGS) map(s)
viticultural area lies entirely within the Department Order 120–01 (Revised), showing the location of the proposed
larger San Francisco Bay viticultural dated December 10, 2013, to the TTB AVA, with the boundary of the
area and the multicounty Central Coast Administrator to perform the functions proposed AVA clearly drawn thereon;
viticultural area. TTB designates and duties in the administration and and
viticultural areas to allow vintners to enforcement of this law. • A detailed narrative description of
better describe the origin of their wines Part 4 of the TTB regulations (27 CFR the proposed AVA boundary based on
and to allow consumers to better part 4) authorizes TTB to establish USGS map markings.
identify wines they may purchase. TTB definitive viticultural areas and regulate
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
invites comments on this proposed the use of their names as appellations of Lamorinda Petition
addition to its regulations. origin on wine labels and in wine TTB received a petition from Patrick
DATES: Comments must be received by advertisements. Part 9 of the TTB L. Shabram, on behalf of the Lamorinda
June 15, 2015. regulations (27 CFR part 9) sets forth Wine Growers Association, proposing
ADDRESSES: Please send your comments standards for the preparation and the establishment of the ‘‘Lamorinda’’
on this notice to one of the following submission of petitions for the AVA. The proposed Lamorinda AVA is
addresses: establishment or modification of located in Contra Costa County,
• Internet: http://www.regulations.gov American viticultural areas (AVAs) and California, and contains the cities of
(via the online comment form for this lists the approved AVAs. Lafayette, Moraga, and Orinda. The
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Document Created: 2015-12-18 11:09:28
Document Modified: 2015-12-18 11:09:28
| 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 29, 2015. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. | |
| FR Citation | 80 FR 19892 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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