81 FR 1870 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 9 (January 14, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 9 (January 14, 2016)
| Page Range | 1870-1874 | |
| FR Document | 2015-32519 |
[Federal Register Volume 81, Number 9 (Thursday, January 14, 2016)] [Rules and Regulations] [Pages 1870-1874] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-32519] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1275; Directorate Identifier 2014-NM-070-AD; Amendment 39-18354; AD 2015-26-06] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2004-14-09 for certain Airbus Model A320-211, -212, and -231 airplanes. AD 2004-14-09 required repetitive inspections for fatigue cracking of the lower surface panel on the wing center box, and repair if necessary; and modification of the lower surface panel on the wing center box, which constitutes terminating action for the repetitive inspections. This new AD retains the requirements of AD 2004-14-09, reduces the compliance times for the repetitive inspections, and requires an additional repair for certain airplanes. This AD was [[Page 1871]] prompted by a determination that, based on the average flight duration, the average weight of fuel at landing is higher than that defined for the analysis of the fatigue-related tasks; and that shot peening might have been improperly done on the chromic acid anodizing (CAA) protection, which would adversely affect fatigue crack protection. We are issuing this AD to detect and correct fatigue cracking of the lower surface panel on the wing center box, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective February 18, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 18, 2016. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of August 13, 2004 (69 FR 41398, July 9, 2004). The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of November 27, 1998 (63 FR 56542, October 22, 1998). ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-1275; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this final rule, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 1275. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004). AD 2004-14-09 applied to certain Airbus Model A320-211, -212, and -231 airplanes. The NPRM published in the Federal Register on May 8, 2015 (80 FR 26492). The NPRM was prompted by a determination that, based on the average flight duration, the average weight of fuel at landing is higher than that defined for the analysis of the fatigue- related tasks; and that shot peening might have been improperly done on the CAA protection, which would adversely affect fatigue crack protection. The NPRM proposed to continue to require repetitive inspections for fatigue cracking of the lower surface panel on the wing center box, and repair if necessary; and modification of the lower surface panel on the wing center box, which constitutes terminating action for the repetitive inspections. The NPRM also proposed to reduce the compliance times for the repetitive inspections, and would require a repair for certain airplanes. We are issuing this AD to detect and correct fatigue cracking of the lower surface panel on the wing center box, which could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0065, dated March 14, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on certain Model A320- 211, -212, and -231 airplanes. The MCAI states: During center fuselage certification full scale test, damage was found in the center wing box (CWB) lower surface panel. This condition, if not detected and corrected, could affect the structural integrity of the CWB. To prevent such damage, Airbus developed mod 22418 which consists in shot-peening of the lower panel in the related area. Mod 22418 has been embodied in production from aeroplane [manufacturer serial number] (MSN) 0359. For unmodified in-service aeroplanes, Airbus issued Service Bulletin (SB) A320-57-1082 to introduce repetitive High Frequency Eddy Current (HFEC) inspections on the external face of the center wing box lower panel between Frame (FR) 41 and FR42 to detect damage. DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 2002-342 [http://ad.easa.europa.eu/blob/20023420tb_superseded.pdf/AD_F-2002-342_1] to require these inspections and, depending on findings, applicable corrective action(s). Airbus also issued SB A320-57-1043 as an optional terminating action for the repetitive inspections required by DGAC France AD 2002-342. Since that [DGAC] AD was issued, the results of a survey, carried out on the A320 fleet, highlighted some differences between the mission parameters, mainly on the weight of fuel at landing and on the average flight duration, which are higher than those defined for the analysis of the fatigue related tasks. These findings have led to an adjustment of the A320 reference fatigue mission. Consequently, the threshold and intervals of these repetitive inspections have been revised and a new threshold figure expressed in flight hours (FH) has been established. In addition, it has been identified that, on aeroplanes that have been modified in accordance with Airbus SB A320-57-1043 (Airbus mod 22418) at Revision 05 or an earlier Revision, the shot peening may have been improperly done on the Chromic Acid Anodizing (CAA) protection, which has no fatigue benefit effect. Therefore, the inspections per Airbus SB A320-57-1082 are required again on these aeroplanes. Consequently, new shot-peening procedures with proper CAA protection removal instructions have been developed and their embodiment through Airbus SB A320-57-1043 Revision 06 cancels the repetitive inspections per Airbus SB A320-57-1082, as required by DGAC France AD 2002-342. For the reasons described above, this new [EASA] AD retains the requirements of DGAC France AD 2002-342, which is superseded, but requires these actions to be accomplished within reduced thresholds and intervals. In addition, the optional terminating action provision (SB A320-57-1043) is amended by including reference to the SB at Revision 06. The optional terminating action described in Airbus Service Bulletin A320-57-1043, Revision 06, dated December 5, 2013, is accomplishing shot peening in the radius of the milling step between stiffeners 13 and 14 near the fuel pump aperture. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-1275-0002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 26492, May 8, 2015) or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM (80 FR [[Page 1872]] 26492, May 8, 2015) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 26492, May 8, 2015). Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-57-1043, Revision 06, dated December 5, 2013. This service information describes procedures for shot peening in the radius of the milling step between stiffeners 13 and 14 near the fuel pump aperture. Airbus has also issued Service Bulletin A320-57-1082, Revision 04, dated December 5, 2013. This service information describes procedures for inspections for cracking of the lower surface panel on the wing center box. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 46 airplanes of U.S. registry. The actions that were required by AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), and retained in this AD take about 25 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that were required by AD 2004-14-09 is $2,125 per product. The new requirements of this AD will add no additional economic burden. We have received no definitive data that will enable us to provide cost estimates for the on-condition actions specified in this AD. We have no way of determining the number of aircraft that might need these actions. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-1275; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647- 5527) is in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), and adding the following new AD: 2015-26-06 Airbus: Amendment 39-18354. Docket No. FAA-2015-1275; Directorate Identifier 2014-NM-070-AD. (a) Effective Date This AD becomes effective February 18, 2016. (b) Affected ADs This AD replaces AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004). (c) Applicability This AD applies to Airbus Model A320-211, -212, and -231 airplanes, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification 22418 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a determination that, based on the average flight duration, the average weight of fuel at landing is higher than that defined for the analysis of the fatigue-related tasks; and that shot peening might have been improperly done on the chromic acid anodizing (CAA) protection, which would adversely affect fatigue crack protection. We are issuing this AD to detect and correct fatigue cracking of the lower surface panel on the wing center box (WCB), 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 No Changes This paragraph restates the requirements of paragraph (a) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no changes. Except as provided by paragraph (k) of this AD: Prior to the accumulation of 20,000 total flight cycles, or within 60 days after November 27, 1998 (the effective date of AD 98-22-05, Amendment 39-10851 (63 FR 56542, October 22, 1998)), whichever occurs later, perform a high frequency eddy current (HFEC) inspection to detect fatigue cracking of the lower surface panel on the WCB, in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03, dated April 30, 2002. Repeat the HFEC inspection thereafter at intervals not to exceed 7,500 flight cycles until the actions required by paragraph (i) of this AD are accomplished. (h) Retained Repair, With No Changes This paragraph restates the requirements of paragraph (b) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no changes. Except as provided by paragraph (j) of this AD, if any cracking is detected during any inspection required by paragraph (g) of this AD: Prior to further flight, repair in accordance with Airbus [[Page 1873]] Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03, dated April 30, 2002. Accomplishment of the repair constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD for the repaired area only. (i) Retained Inspection/Modification/Repair, With New Terminating Action This paragraph restates the requirements of paragraph (c) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with new terminating action provided. Prior to the accumulation of 25,000 total flight cycles, or within 60 days after November 27, 1998 (the effective date of AD 98-22-05, Amendment 39-10851 (63 FR 56542, October 22, 1998)), whichever occurs later: Perform an HFEC inspection to detect fatigue cracking of the lower surface panel on the WCB, in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03, dated April 30, 2002. Accomplishment of the initial inspection required by paragraph (p) of this AD constitutes terminating action for the inspection requirements of this paragraph. (1) If no cracking is detected: Prior to further flight, modify the lower surface panel on the WCB, in accordance with Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997; or Revision 05, dated April 30, 2002. Accomplishment of the modification constitutes terminating action for the requirements of paragraph (g) of this AD. (2) Except as provided by paragraph (j) of this AD: If any cracking is detected, prior to further flight, repair in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997, or Revision 03, dated April 30, 2002; and modify any uncracked area, in accordance with Airbus Service Bulletin A320- 57-1043, Revision 02, dated May 14, 1997, or Revision 05, dated April 30, 2002. Accomplishment of the repair of cracked area(s) and modification of uncracked area(s) constitutes terminating action for the requirements of paragraph (g) of this AD. (j) Retained Service Bulletin Exception, With Revised Repair Instructions This paragraph restates the requirements of paragraph (d) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with revised repair instructions. If any cracking is detected during any inspection required by paragraph (h) or (i)(2) of this AD, and the applicable service bulletin specifies to contact Airbus for an appropriate action: 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 (DGAC) (or its delegated agent); or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). After the effective date of this AD only repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. (k) Retained Provision for Certain Inspection Exception, With No Changes This paragraph restates the provision of paragraph (e) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no changes. The actions required by paragraph (g) of this AD are not required to be accomplished if the requirements of paragraph (i) of this AD are accomplished at the time specified in paragraph (g) of this AD. (l) Retained Initial Inspection, With Terminating Action This paragraph restates the requirements of paragraph (f) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with terminating action provided. For airplanes on which neither the inspection required by paragraph (g) of this AD nor the modification required by paragraph (i)(1) of this AD has been done before August 13, 2004 (the effective date of AD 2004-14-09): Perform an HFEC inspection to detect fatigue cracking of the lower surface panel on the WCB, in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03, dated April 30, 2002; at the later of the times specified in paragraphs (l)(1) and (l)(2) of this AD. Accomplishment of the inspection required by this paragraph terminates the requirements of paragraph (g) of this AD. Accomplishment of the initial inspection required by paragraph (p) of this AD terminates the inspection requirements of this paragraph. (1) Prior to the accumulation of 13,200 total flight cycles or 39,700 total flight hours, whichever is first. (2) Prior to the accumulation of 20,000 total flight cycles, or within 3,500 flight cycles after August 13, 2004 (the effective date of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004)), whichever is later. (m) Retained Repetitive Inspections, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no changes. If no cracking is detected during the inspection required by paragraph (g) or (l) of this AD: Repeat the inspection required by paragraph (l) of this AD at the applicable time specified in paragraph (m)(1) or (m)(2) of this AD. Accomplishment of the modification required by paragraph (i)(1) of this AD terminates the requirements of this paragraph. (1) For airplanes on which the inspections required by paragraph (g) of this AD have been initiated before August 13, 2004 (the effective date of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004)): Do the next inspection within 5,700 flight cycles after accomplishment of the last inspection, or within 1,800 flight cycles after August 13, 2004, whichever is later. Repeat the inspection thereafter at intervals not to exceed 5,700 flight cycles. (2) For airplanes on which no inspection required by paragraph (g) of this AD has been done before August 13, 2004 (the effective date of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004)): Do the next inspection within 5,700 flight cycles after accomplishment of the inspection required by paragraph (l) of this AD. Repeat the inspection thereafter at intervals not to exceed 5,700 flight cycles. (n) Retained Repair/Modification, With Revised Repair Instructions This paragraph restates the requirements of paragraph (h) of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with revised repair instructions. If any cracking is detected during any inspection required by paragraph (l) or (m) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997, or Revision 03, dated April 30, 2002; and modify any uncracked area, in accordance with Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997, or Revision 05, dated April 30, 2002. Where Airbus Service Bulletin A320-57-1082 specifies to contact Airbus for an appropriate repair action: Prior to further flight, repair using a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the DGAC (or its delegated agent)); or EASA; or Airbus's EASA DOA. After the effective date of this AD only repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. Accomplishment of the repair of cracked area(s) and modification of uncracked area(s) constitutes terminating action for the requirements of paragraphs (g) through (n) of this AD. (o) New Requirement of This AD: Repair of Certain Airplanes For airplanes on which the actions specified in Airbus Service Bulletin A320-57-1043 have not been accomplished, and on which a repair has been accomplished, as specified in the service information identified in paragraph (o)(1), (o)(2), (o)(3), or (o)(4) of this AD: Within 30 days after the effective date of this AD, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the EASA; or Airbus's EASA DOA. (1) Airbus Service Bulletin A320-57-1082, dated October 31, 1996. (2) Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997. (3) Airbus Service Bulletin A320-57-1082, Revision 02, dated July 26, 1999. (4) Airbus Service Bulletin A320-57-1082, Revision 03, dated April 30, 2002. (p) New Requirement of This AD: Repetitive WCB Inspections At the applicable time specified in paragraphs (p)(1) and (p)(2) of this AD: Do an HFEC inspection for cracking of the lower surface panel on the WCB, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1082, Revision 04, dated December 5, 2013. Repeat the inspection of the lower surface panel on the WCB thereafter at intervals not to exceed 7,200 flight cycles or 14,400 flight hours, whichever occurs first. Accomplishment of [[Page 1874]] the initial inspection required by this paragraph terminates the inspections required by paragraphs (g), (i), and (l) of this AD. (1) For airplanes on which the actions specified in Airbus Service Bulletin A320-57-1043 have not been done: At the later of the times specified in paragraphs (p)(1)(i) and (p)(1)(ii) of this AD. (i) Before the accumulation of 20,700 flight cycles or 41,400 flight hours, whichever occurs first since first flight of the airplane. (ii) Within 7,200 flight cycles or 14,400 flight hours, whichever occurs first after doing the most recent inspection as specified in the service information specified in paragraph (o)(1), (o)(2), (o)(3), or (o)(4) of this AD. (2) For airplanes on which the actions specified in Airbus Service Bulletin A320-57-1043 have been done: At the latest of the times specified in paragraphs (p)(2)(i), (p)(2)(ii), and (p)(2)(iii) of this AD. (i) Within 7,200 flight cycles or 14,400 flight hours, whichever occurs first since doing the actions specified in Airbus Service Bulletin A320-57-1043. (ii) Within 3,750 flight cycles or 7,500 flight hours, whichever occurs first after July 31, 2012 (as described in Airbus Service Bulletin A320-57-1082, Revision 04, dated December 5, 2013). (iii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first after the effective date of this AD. (q) New Requirement of This AD: Repair of WCB If any crack is found during any inspection required by paragraph (p) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the EASA; or Airbus's EASA DOA. (r) New Optional Terminating Action Modification of an airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1043, Revision 06, dated December 5, 2013, constitutes terminating action for the actions required by paragraph (p) of this AD. (s) Credit for Previous Actions This paragraph provides credit for applicable actions required by paragraphs (g) through (n) of this AD, if those actions were performed before the effective date of this AD using the applicable Airbus Service Information provided in paragraphs (s)(1) through (s)(8) of this AD. (1) Airbus Service Bulletin A320-57-1043, dated February 16, 1993, which is not incorporated by reference in this AD. (2) Airbus Service Bulletin A320-57-1043, Revision 01, dated June 14, 1996, which is not incorporated by reference in this AD. (3) Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997, which was incorporated by reference on November 27, 1998 (63 FR 56542, October 22, 1998). (4) Airbus Service Bulletin A320-57-1043, Revision 03, dated October 24, 1997, which is not incorporated by reference in this AD. (5) Airbus Service Bulletin A320-57-1043, Revision 04, dated May 15, 1999, which is not incorporated by reference in this AD. (6) Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997, which was incorporated by reference on November 27, 1998 (63 FR 56542, October 22, 1998). (7) Airbus Service Bulletin A320-57-1082, Revision 02, dated July 26, 1999, which is not incorporated by reference in this AD. (8) Airbus Service Bulletin A320-57-1082, Revision 03, dated April 30, 2002, which was incorporated by reference on August 13, 2004 (69 FR 41398, July 9, 2004). (t) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; fax 425-227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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. (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. (u) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0065, dated March 14, 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-2015-1275. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (v)(6) and (v)(7) of this AD. (v) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on February 18, 2016. (i) Airbus Service Bulletin A320-57-1043, Revision 06, dated December 5, 2013. (ii) Airbus Service Bulletin A320-57-1082, Revision 04, dated December 5, 2013. (4) The following service information was approved for IBR on August 13, 2004 (69 FR 41398, July 9, 2004). (i) Airbus Service Bulletin A320-57-1043, Revision 05, dated April 30, 2002. (ii) Airbus Service Bulletin A320-57-1082, Revision 03, dated April 30, 2002. (5) The following service information was approved for IBR on November 27, 1998 (63 FR 56542, October 22, 1998). (i) Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997. Pages 1 through 6, 8, 13, and 14 of this service bulletin are marked Revision 02, dated May 14, 1997; pages 7, 9 through 12, and 15 of this service bulletin are from the original issue, dated February 16, 1993. (ii) Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997. (6) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. (7) 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. (8) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on December 18, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-32519 Filed 1-13-16; 8:45 am] BILLING CODE 4910-13-P
![1870 Federal Register / Vol. 81, No. 9 / Thursday, January 14, 2016 / Rules and Regulations
priority project in each state, up to 7 (4) Problems, delays, or adverse accordance with a Presidentially-
points for the second highest priority conditions which will affect attainment declared disaster, or on a case-by-case
project in each state and up to 5 points of overall program objectives, prevent basis, when such an exception is in the
for the third highest priority project that meeting time schedules or objectives, or best financial interest of the Federal
address unforeseen exigencies or preclude the attainment of particular Government and is otherwise not in
emergencies, such as the loss of a objectives during established time conflict with applicable laws. No
community facility due to an accident periods. This disclosure shall be exceptions, however, will be granted for
or natural disaster, or other areas of accomplished by a Statement of the Applicant, Ultimate Recipient, or
need in their particular state. The State action taken or planned to resolve the Project eligibility.
Director will place written situation;
documentation in the project file each (5) Objectives and timetables § 3570.284 Review or appeal rights.
time the State Director assigns these established for the next reporting A person may seek a review of an
points—Up to 10 points. period; Agency decision under this subpart
(i) Administrator discretionary points. (6) A summary of the race, sex, and from the appropriate Agency official
The Administrator may award up to 20 national origin of the Ultimate that oversees the program in question or
discretionary points for projects to Recipients; appeal to the USDA National Appeals
address geographic distribution of (7) The final report will also address Division in accordance with 7 CFR part
funds, emergency conditions caused by the following: 11.
economic problems, natural disasters (i) What have been the most
§§ 3570.285–3570.299 [Reserved]
and other initiatives identified by the challenging or unexpected aspects of
Secretary—Up to 20 points. this grant? § 3570.300 OMB control number.
(ii) What advice would you give to The reporting and recordkeeping
§ 3570.274 Fund disbursement. other organizations planning a similar requirements contained in this
The Agency will make payments grant? What are the strengths and regulation have been submitted to the
under this agreement in accordance limitations of this grant? If you had the Office of Management and Budget
with 2 CFR 200.305. All requests for opportunity, what would you have done (OMB) for approval.
advances or reimbursements must be in differently?
compliance with 2 CFR 200.306 and (iii) Are there any post-grant plans for Dated: December 11, 2015.
include any required matching fund this Project? If yes, how will they be Tony Hernandez,
usage. financed? Administrator, Rural Housing Service.
(b) [Reserved] [FR Doc. 2016–00479 Filed 1–13–16; 8:45 am]
§ 3570.275 Grant cancellation or major
BILLING CODE 3410–XV–P
changes. § 3570.277 Audit or financial statement.
Any change in the scope of the The Grantee will provide an Audit
Project, budget adjustments of more report or financial Statement in
than 10 percent of the total budget, and accordance with 2 CFR 200.500–200.517 DEPARTMENT OF TRANSPORTATION
any other significant change in the and as follows: Federal Aviation Administration
Project must be in compliance with 2 (a) Grantees expending $750,000 or
CFR 200.308 and 200.339. The changes more Federal funds per fiscal year will 14 CFR Part 39
must be requested in writing and submit an Audit conducted in
approved by the Agency in writing. Any accordance with 2 CFR parts 200, 215, [Docket No. FAA–2015–1275; Directorate
change not approved may be cause for 220, 225, 230 and 400, ‘‘Uniform Identifier 2014–NM–070–AD; Amendment
termination of the grant. Administrative Requirements, Cost 39–18354; AD 2015–26–06]
Principles, and Audit Requirements for RIN 2120–AA64
§ 3570.276 Reporting.
Federal Awards.’’
(a) The Grantee must provide periodic (b) Grantees expending less than Airworthiness Directives; Airbus
reports as required by the Agency. A $750,000 will provide annual financial Airplanes
financial status report, SF 425 ‘‘Federal Statements covering the grant period,
Financial Report,’’, and a project consisting of the organization’s AGENCY: Federal Aviation
performance report will be required as statement of income and expense and Administration (FAA), Department of
provided in the grant agreement. The balance sheet signed by an appropriate Transportation (DOT).
financial status report must show how Official of the organization. Financial ACTION: Final rule.
grant funds and matching funds have statements will be submitted within 90
been used to date. A final report may days after the Grantee’s fiscal year. SUMMARY: We are superseding
serve as the last report. Grantees shall Airworthiness Directive (AD) 2004–14–
constantly monitor performance to §§ 3570.278—3570.280 [Reserved] 09 for certain Airbus Model A320–211,
ensure that time schedules are being –212, and –231 airplanes. AD 2004–14–
§ 3570.281 Grant servicing.
met and projected goals by time periods 09 required repetitive inspections for
are being accomplished. The Project Grants will be serviced in accordance fatigue cracking of the lower surface
performance reports shall include, but with 7 CFR part 1951, subpart E. panel on the wing center box, and repair
are not limited to, the following: § 3570.282 [Reserved] if necessary; and modification of the
(1) A description of the activities that lower surface panel on the wing center
mstockstill on DSK4VPTVN1PROD with RULES
the funds reflected in the financial § 3570.283 Exception authority. box, which constitutes terminating
status report were used for; The Administrator may make an action for the repetitive inspections.
(2) A comparison of actual exception to any requirement or This new AD retains the requirements of
accomplishments to the objectives for provision of this subpart, if such an AD 2004–14–09, reduces the
that period; exception is necessary to implement the compliance times for the repetitive
(3) Reasons why established intent of the authorizing statutes in a inspections, and requires an additional
objectives were not met, if applicable; time of national emergency or in repair for certain airplanes. This AD was
VerDate Sep<11>2014 16:27 Jan 13, 2016 Jkt 238001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\14JAR1.SGM 14JAR1](https://thefederalregister.org/doc/81_FR_1879/page/1.svg)
![Federal Register / Vol. 81, No. 9 / Thursday, January 14, 2016 / Rules and Regulations 1871
prompted by a determination that, based Discussion Airbus also issued SB A320–57–1043 as an
on the average flight duration, the optional terminating action for the repetitive
We issued a notice of proposed inspections required by DGAC France AD
average weight of fuel at landing is rulemaking (NPRM) to amend 14 CFR 2002–342.
higher than that defined for the analysis part 39 to supersede AD 2004–14–09, Since that [DGAC] AD was issued, the
of the fatigue-related tasks; and that shot Amendment 39–13718 (69 FR 41398, results of a survey, carried out on the A320
peening might have been improperly July 9, 2004). AD 2004–14–09 applied to fleet, highlighted some differences between
done on the chromic acid anodizing certain Airbus Model A320–211, –212, the mission parameters, mainly on the weight
(CAA) protection, which would and –231 airplanes. The NPRM of fuel at landing and on the average flight
adversely affect fatigue crack protection. published in the Federal Register on duration, which are higher than those
We are issuing this AD to detect and defined for the analysis of the fatigue related
May 8, 2015 (80 FR 26492). The NPRM
correct fatigue cracking of the lower tasks.
was prompted by a determination that, These findings have led to an adjustment
surface panel on the wing center box, based on the average flight duration, the of the A320 reference fatigue mission.
which could result in reduced structural average weight of fuel at landing is Consequently, the threshold and intervals of
integrity of the airplane. higher than that defined for the analysis these repetitive inspections have been
DATES: This AD becomes effective of the fatigue-related tasks; and that shot revised and a new threshold figure expressed
February 18, 2016. peening might have been improperly in flight hours (FH) has been established.
done on the CAA protection, which In addition, it has been identified that, on
The Director of the Federal Register aeroplanes that have been modified in
approved the incorporation by reference would adversely affect fatigue crack
accordance with Airbus SB A320–57–1043
of certain publications listed in this AD protection. The NPRM proposed to
(Airbus mod 22418) at Revision 05 or an
as of February 18, 2016. continue to require repetitive earlier Revision, the shot peening may have
inspections for fatigue cracking of the been improperly done on the Chromic Acid
The Director of the Federal Register lower surface panel on the wing center Anodizing (CAA) protection, which has no
approved the incorporation by reference box, and repair if necessary; and fatigue benefit effect. Therefore, the
of certain other publications listed in modification of the lower surface panel inspections per Airbus SB A320–57–1082 are
this AD as of August 13, 2004 (69 FR on the wing center box, which required again on these aeroplanes.
41398, July 9, 2004). constitutes terminating action for the Consequently, new shot-peening
The Director of the Federal Register repetitive inspections. The NPRM also procedures with proper CAA protection
removal instructions have been developed
approved the incorporation by reference proposed to reduce the compliance
and their embodiment through Airbus SB
of certain other publications listed in times for the repetitive inspections, and A320–57–1043 Revision 06 cancels the
this AD as of November 27, 1998 (63 FR would require a repair for certain repetitive inspections per Airbus SB A320–
56542, October 22, 1998). airplanes. We are issuing this AD to 57–1082, as required by DGAC France AD
detect and correct fatigue cracking of the 2002–342.
ADDRESSES: You may examine the AD
lower surface panel on the wing center For the reasons described above, this new
docket on the Internet at http://www. [EASA] AD retains the requirements of DGAC
box, which could result in reduced
regulations.gov/#!docketDetail;D=FAA- France AD 2002–342, which is superseded,
structural integrity of the airplane.
2015-1275; or in person at the Docket The European Aviation Safety Agency but requires these actions to be accomplished
Management Facility, U.S. Department (EASA), which is the Technical Agent within reduced thresholds and intervals. In
of Transportation, Docket Operations, for the Member States of the European addition, the optional terminating action
M–30, West Building Ground Floor, provision (SB A320–57–1043) is amended by
Union, has issued EASA Airworthiness including reference to the SB at Revision 06.
Room W12–140, 1200 New Jersey Directive 2014–0065, dated March 14,
Avenue SE., Washington, DC. 2014 (referred to after this as the The optional terminating action
For service information identified in Mandatory Continuing Airworthiness described in Airbus Service Bulletin
this final rule, contact Airbus, Information, or ‘‘the MCAI’’), to correct A320–57–1043, Revision 06, dated
Airworthiness Office—EIAS, 1 Rond an unsafe condition on certain Model December 5, 2013, is accomplishing
Point Maurice Bellonte, 31707 Blagnac A320–211, -212, and -231 airplanes. The shot peening in the radius of the milling
Cedex, France; telephone +33 5 61 93 36 MCAI states: step between stiffeners 13 and 14 near
96; fax +33 5 61 93 44 51; email the fuel pump aperture. You may
During center fuselage certification full
account.airworth-eas@airbus.com; scale test, damage was found in the center examine the MCAI in the AD docket on
Internet http://www.airbus.com. You wing box (CWB) lower surface panel. the Internet at http://www.regulations.
may view this referenced service This condition, if not detected and gov/#!documentDetail;D=FAA-2015-
information at the FAA, Transport corrected, could affect the structural integrity 1275-0002.
Airplane Directorate, 1601 Lind Avenue of the CWB.
To prevent such damage, Airbus developed Comments
SW., Renton, WA. For information on
the availability of this material at the mod 22418 which consists in shot-peening of We gave the public the opportunity to
FAA, call 425–227–1221. It is also the lower panel in the related area. Mod
participate in developing this AD. We
22418 has been embodied in production from
available on the Internet at http:// aeroplane [manufacturer serial number] received no comments on the NPRM (80
www.regulations.gov by searching for (MSN) 0359. For unmodified in-service FR 26492, May 8, 2015) or on the
and locating Docket No. FAA–2015– aeroplanes, Airbus issued Service Bulletin determination of the cost to the public.
1275. (SB) A320–57–1082 to introduce repetitive
Conclusion
High Frequency Eddy Current (HFEC)
FOR FURTHER INFORMATION CONTACT: inspections on the external face of the center We reviewed the available data and
mstockstill on DSK4VPTVN1PROD with RULES
Sanjay Ralhan, Aerospace Engineer, wing box lower panel between Frame (FR) 41 determined that air safety and the
International Branch, ANM–116, and FR42 to detect damage. public interest require adopting this AD
Transport Airplane Directorate, FAA, DGAC [Direction Générale de l’Aviation
as proposed except for minor editorial
1601 Lind Avenue SW., Renton, WA Civile] France issued AD 2002–342 [http://
ad.easa.europa.eu/blob/20023420tb_ changes. We have determined that these
98057–3356; telephone 425–227–1405; minor changes:
fax 425–227–1149. superseded.pdf/AD_F-2002-342_1] to require
these inspections and, depending on • Are consistent with the intent that
SUPPLEMENTARY INFORMATION: findings, applicable corrective action(s). was proposed in the NPRM (80 FR
VerDate Sep<11>2014 16:27 Jan 13, 2016 Jkt 238001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\14JAR1.SGM 14JAR1](https://thefederalregister.org/doc/81_FR_1879/page/2.svg)
![1872 Federal Register / Vol. 81, No. 9 / Thursday, January 14, 2016 / Rules and Regulations
26492, May 8, 2015) for correcting the because it addresses an unsafe condition 2015–26–06 Airbus: Amendment 39–18354.
unsafe condition; and that is likely to exist or develop on Docket No. FAA–2015–1275; Directorate
• Do not add any additional burden products identified in this rulemaking Identifier 2014–NM–070–AD.
upon the public than was already action. (a) Effective Date
proposed in the NPRM (80 FR 26492, This AD becomes effective February 18,
Regulatory Findings
May 8, 2015). 2016.
We determined that this AD will not
Related Service Information Under 1 have federalism implications under (b) Affected ADs
CFR Part 51 Executive Order 13132. This AD will This AD replaces AD 2004–14–09,
Airbus has issued Service Bulletin not have a substantial direct effect on Amendment 39–13718 (69 FR 41398, July 9,
A320–57–1043, Revision 06, dated the States, on the relationship between 2004).
December 5, 2013. This service the national government and the States, (c) Applicability
information describes procedures for or on the distribution of power and This AD applies to Airbus Model A320–
shot peening in the radius of the milling responsibilities among the various 211, –212, and –231 airplanes, certificated in
step between stiffeners 13 and 14 near levels of government. any category, all manufacturer serial
the fuel pump aperture. For the reasons discussed above, I numbers, except those on which Airbus
Airbus has also issued Service certify that this AD: Modification 22418 has been embodied in
Bulletin A320–57–1082, Revision 04, 1. Is not a ‘‘significant regulatory production.
dated December 5, 2013. This service action’’ under Executive Order 12866; (d) Subject
information describes procedures for 2. Is not a ‘‘significant rule’’ under the Air Transport Association (ATA) of
inspections for cracking of the lower DOT Regulatory Policies and Procedures America Code 57, Wings.
surface panel on the wing center box. (44 FR 11034, February 26, 1979);
This service information is reasonably 3. Will not affect intrastate aviation in (e) Reason
available because the interested parties Alaska; and This AD was prompted by a determination
have access to it through their normal 4. Will not have a significant that, based on the average flight duration, the
course of business or by the means economic impact, positive or negative, average weight of fuel at landing is higher
than that defined for the analysis of the
identified in the ADDRESSES section. on a substantial number of small entities fatigue-related tasks; and that shot peening
under the criteria of the Regulatory might have been improperly done on the
Costs of Compliance
Flexibility Act. chromic acid anodizing (CAA) protection,
We estimate that this AD affects 46 which would adversely affect fatigue crack
airplanes of U.S. registry. Examining the AD Docket
protection. We are issuing this AD to detect
The actions that were required by AD You may examine the AD docket on and correct fatigue cracking of the lower
2004–14–09, Amendment 39–13718 (69 the Internet at http://www.regulations. surface panel on the wing center box (WCB),
FR 41398, July 9, 2004), and retained in gov/#!docketDetail;D=FAA-2015-1275; which could result in reduced structural
this AD take about 25 work-hours per or in person at the Docket Management integrity of the airplane.
product, at an average labor rate of $85 Facility between 9 a.m. and 5 p.m., (f) Compliance
per work-hour. Based on these figures, Monday through Friday, except Federal Comply with this AD within the
the estimated cost of the actions that holidays. The AD docket contains this compliance times specified, unless already
were required by AD 2004–14–09 is AD, the regulatory evaluation, any done.
$2,125 per product. comments received, and other
The new requirements of this AD will (g) Retained Repetitive Inspections, With No
information. The street address for the Changes
add no additional economic burden. Docket Operations office (telephone
We have received no definitive data 800–647–5527) is in the ADDRESSES This paragraph restates the requirements of
that will enable us to provide cost paragraph (a) of AD 2004–14–09,
section. Amendment 39–13718 (69 FR 41398, July 9,
estimates for the on-condition actions
List of Subjects in 14 CFR Part 39 2004), with no changes. Except as provided
specified in this AD. We have no way by paragraph (k) of this AD: Prior to the
of determining the number of aircraft Air transportation, Aircraft, Aviation accumulation of 20,000 total flight cycles, or
that might need these actions. safety, Incorporation by reference, within 60 days after November 27, 1998 (the
Authority for This Rulemaking Safety. effective date of AD 98–22–05, Amendment
39–10851 (63 FR 56542, October 22, 1998)),
Title 49 of the United States Code Adoption of the Amendment whichever occurs later, perform a high
specifies the FAA’s authority to issue Accordingly, under the authority frequency eddy current (HFEC) inspection to
rules on aviation safety. Subtitle I, delegated to me by the Administrator, detect fatigue cracking of the lower surface
section 106, describes the authority of the FAA amends 14 CFR part 39 as panel on the WCB, in accordance with
the FAA Administrator. ‘‘Subtitle VII: Airbus Service Bulletin A320–57–1082,
follows: Revision 01, dated December 10, 1997; or
Aviation Programs,’’ describes in more Revision 03, dated April 30, 2002. Repeat the
detail the scope of the Agency’s PART 39—AIRWORTHINESS HFEC inspection thereafter at intervals not to
authority. DIRECTIVES exceed 7,500 flight cycles until the actions
We are issuing this rulemaking under required by paragraph (i) of this AD are
the authority described in ‘‘Subtitle VII, ■ 1. The authority citation for part 39 accomplished.
Part A, Subpart III, Section 44701: continues to read as follows:
(h) Retained Repair, With No Changes
General requirements.’’ Under that Authority: 49 U.S.C. 106(g), 40113, 44701.
mstockstill on DSK4VPTVN1PROD with RULES
section, Congress charges the FAA with This paragraph restates the requirements of
§ 39.13 [Amended] paragraph (b) of AD 2004–14–09,
promoting safe flight of civil aircraft in
Amendment 39–13718 (69 FR 41398, July 9,
air commerce by prescribing regulations ■ 2. The FAA amends § 39.13 by 2004), with no changes. Except as provided
for practices, methods, and procedures removing Airworthiness Directive (AD) by paragraph (j) of this AD, if any cracking
the Administrator finds necessary for 2004–14–09, Amendment 39–13718 (69 is detected during any inspection required by
safety in air commerce. This regulation FR 41398, July 9, 2004), and adding the paragraph (g) of this AD: Prior to further
is within the scope of that authority following new AD: flight, repair in accordance with Airbus
VerDate Sep<11>2014 16:27 Jan 13, 2016 Jkt 238001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\14JAR1.SGM 14JAR1](https://thefederalregister.org/doc/81_FR_1879/page/3.svg)
![1874 Federal Register / Vol. 81, No. 9 / Thursday, January 14, 2016 / Rules and Regulations
the initial inspection required by this (5) Airbus Service Bulletin A320–57–1043, (i) Airbus Service Bulletin A320–57–1043,
paragraph terminates the inspections Revision 04, dated May 15, 1999, which is Revision 06, dated December 5, 2013.
required by paragraphs (g), (i), and (l) of this not incorporated by reference in this AD. (ii) Airbus Service Bulletin A320–57–1082,
AD. (6) Airbus Service Bulletin A320–57–1082, Revision 04, dated December 5, 2013. (4) The
(1) For airplanes on which the actions Revision 01, dated December 10, 1997, which following service information was approved
specified in Airbus Service Bulletin A320– was incorporated by reference on November for IBR on August 13, 2004 (69 FR 41398,
57–1043 have not been done: At the later of 27, 1998 (63 FR 56542, October 22, 1998). July 9, 2004).
the times specified in paragraphs (p)(1)(i) and (7) Airbus Service Bulletin A320–57–1082, (i) Airbus Service Bulletin A320–57–1043,
(p)(1)(ii) of this AD. Revision 02, dated July 26, 1999, which is Revision 05, dated April 30, 2002.
(i) Before the accumulation of 20,700 flight not incorporated by reference in this AD. (ii) Airbus Service Bulletin A320–57–1082,
cycles or 41,400 flight hours, whichever (8) Airbus Service Bulletin A320–57–1082, Revision 03, dated April 30, 2002.
Revision 03, dated April 30, 2002, which was (5) The following service information was
occurs first since first flight of the airplane.
incorporated by reference on August 13, 2004 approved for IBR on November 27, 1998 (63
(ii) Within 7,200 flight cycles or 14,400
(69 FR 41398, July 9, 2004). FR 56542, October 22, 1998).
flight hours, whichever occurs first after
doing the most recent inspection as specified (t) Other FAA AD Provisions (i) Airbus Service Bulletin A320–57–1043,
in the service information specified in Revision 02, dated May 14, 1997. Pages 1
The following provisions also apply to this through 6, 8, 13, and 14 of this service
paragraph (o)(1), (o)(2), (o)(3), or (o)(4) of this AD:
AD. bulletin are marked Revision 02, dated May
(1) Alternative Methods of Compliance 14, 1997; pages 7, 9 through 12, and 15 of
(2) For airplanes on which the actions (AMOCs): The Manager, International this service bulletin are from the original
specified in Airbus Service Bulletin A320– Branch, ANM–116, Transport Airplane issue, dated February 16, 1993.
57–1043 have been done: At the latest of the Directorate, FAA, has the authority to (ii) Airbus Service Bulletin A320–57–1082,
times specified in paragraphs (p)(2)(i), approve AMOCs for this AD, if requested Revision 01, dated December 10, 1997.
(p)(2)(ii), and (p)(2)(iii) of this AD. using the procedures found in 14 CFR 39.19. (6) For service information identified in
(i) Within 7,200 flight cycles or 14,400 In accordance with 14 CFR 39.19, send your this AD, contact Airbus, Airworthiness
flight hours, whichever occurs first since request to your principal inspector or local Office—EIAS, 1 Rond Point Maurice
doing the actions specified in Airbus Service Flight Standards District Office, as
Bellonte, 31707 Blagnac Cedex, France;
Bulletin A320–57–1043. appropriate. If sending information directly
telephone +33 5 61 93 36 96; fax +33 5 61
(ii) Within 3,750 flight cycles or 7,500 to the International Branch, send it to ATTN:
93 44 51; email account.airworth-eas@
flight hours, whichever occurs first after July Sanjay Ralhan, Aerospace Engineer,
airbus.com; Internet http://www.airbus.com.
31, 2012 (as described in Airbus Service International Branch, ANM–116, Transport
(7) You may view this service information
Bulletin A320–57–1082, Revision 04, dated Airplane Directorate, FAA, 1601 Lind
at the FAA, Transport Airplane Directorate,
December 5, 2013). Avenue SW., Renton, WA 98057–3356;
1601 Lind Avenue SW., Renton, WA. For
(iii) Within 850 flight cycles or 1,700 flight telephone 425–227–1405; fax 425–227–1149.
information on the availability of this
hours, whichever occurs first after the Information may be emailed to: 9-ANM-116-
material at the FAA, call 425–227–1221.
effective date of this AD. AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate (8) You may view this service information
(q) New Requirement of This AD: Repair of principal inspector, or lacking a principal that is incorporated by reference at the
WCB inspector, the manager of the local flight National Archives and Records
standards district office/certificate holding Administration (NARA). For information on
If any crack is found during any inspection the availability of this material at NARA, call
required by paragraph (p) of this AD: Before district office.
(2) Contacting the Manufacturer: As of the 202–741–6030, or go to: http://www.archives.
further flight, repair using a method gov/federal-register/cfr/ibr-locations.html.
approved by the Manager, International effective date of this AD, for any requirement
Branch, ANM–116, Transport Airplane in this AD to obtain corrective actions from Issued in Renton, Washington, on
Directorate, FAA; the EASA; or Airbus’s a manufacturer, the action must be December 18, 2015.
EASA DOA. accomplished using a method approved by Jeffrey E. Duven,
the Manager, International Branch, ANM–
(r) New Optional Terminating Action 116, Transport Airplane Directorate, FAA; or Manager, Transport Airplane Directorate,
the EASA; or Airbus’s EASA DOA. If Aircraft Certification Service.
Modification of an airplane, in accordance
approved by the DOA, the approval must [FR Doc. 2015–32519 Filed 1–13–16; 8:45 am]
with the Accomplishment Instructions of
Airbus Service Bulletin A320–57–1043, include the DOA-authorized signature. BILLING CODE 4910–13–P
Revision 06, dated December 5, 2013, (u) Related Information
constitutes terminating action for the actions
(1) Refer to Mandatory Continuing DEPARTMENT OF TRANSPORTATION
required by paragraph (p) of this AD. Airworthiness Information (MCAI) EASA
(s) Credit for Previous Actions Airworthiness Directive 2014–0065, dated Federal Aviation Administration
March 14, 2014, for related information. This
This paragraph provides credit for
MCAI may be found in the AD docket on the
applicable actions required by paragraphs (g) 14 CFR Part 39
Internet at http://www.regulations.gov by
through (n) of this AD, if those actions were
searching for and locating Docket No. FAA– [Docket No. FAA–2015–1982; Directorate
performed before the effective date of this AD 2015–1275.
using the applicable Airbus Service Identifier 2014–NM–108–AD; Amendment
(2) Service information identified in this 39–18353; AD 2015–26–05]
Information provided in paragraphs (s)(1) AD that is not incorporated by reference is
through (s)(8) of this AD. available at the addresses specified in
(1) Airbus Service Bulletin A320–57–1043, RIN 2120–AA64
paragraphs (v)(6) and (v)(7) of this AD.
dated February 16, 1993, which is not
incorporated by reference in this AD. (v) Material Incorporated by Reference Airworthiness Directives; Fokker
(2) Airbus Service Bulletin A320–57–1043, Services B.V. Airplanes
(1) The Director of the Federal Register
Revision 01, dated June 14, 1996, which is approved the incorporation by reference AGENCY: Federal Aviation
mstockstill on DSK4VPTVN1PROD with RULES
not incorporated by reference in this AD. (IBR) of the service information listed in this Administration (FAA), Department of
(3) Airbus Service Bulletin A320–57–1043, paragraph under 5 U.S.C. 552(a) and 1 CFR
Revision 02, dated May 14, 1997, which was part 51.
Transportation (DOT).
incorporated by reference on November 27, (2) You must use this service information ACTION: Final rule.
1998 (63 FR 56542, October 22, 1998). as applicable to do the actions required by
(4) Airbus Service Bulletin A320–57–1043, this AD, unless this AD specifies otherwise. SUMMARY: We are adopting a new
Revision 03, dated October 24, 1997, which (3) The following service information was airworthiness directive (AD) for all
is not incorporated by reference in this AD. approved for IBR on February 18, 2016. Fokker Services B.V. Model F.28 Mark
VerDate Sep<11>2014 16:27 Jan 13, 2016 Jkt 238001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\14JAR1.SGM 14JAR1](https://thefederalregister.org/doc/81_FR_1879/page/5.svg)
Document Created: 2016-01-14 02:50:36
Document Modified: 2016-01-14 02:50:36
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD becomes effective February 18, 2016. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. | |
| FR Citation | 81 FR 1870 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR