82 FR 10255 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 27 (February 10, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 27 (February 10, 2017)
| Page Range | 10255-10258 | |
| FR Document | 2017-01776 |
[Federal Register Volume 82, Number 27 (Friday, February 10, 2017)] [Rules and Regulations] [Pages 10255-10258] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-01776] ======================================================================== Rules and Regulations Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. ======================================================================== Federal Register / Vol. 82, No. 27 / Friday, February 10, 2017 / Rules and Regulations [[Page 10255]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-5040; Directorate Identifier 2013-NM-192-AD; Amendment 39-18787; AD 2017-02-08] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 series airplanes; and 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). This AD was prompted by a determination that certain inspection thresholds and intervals must be reduced. This AD requires repetitive detailed inspections for corrosion of the lower wing root joint, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 17, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 17, 2017. ADDRESSES: For service information identified in this final rule, 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 5040. 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-2016- 5040; 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 Office (telephone 800-647-5527) is 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 20590. 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A300 series airplanes; and 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). The NPRM published in the Federal Register on April 5, 2016 (81 FR 19509) (``the NPRM''). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2013-0230, dated September 24, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A300 series airplanes; and 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). The MCAI states: Several cases of corrosion on the lower wing root joint, located in the wing bottom skin inboard and outboard of the external lower surface splice, have been reported by operators. This condition, if not detected and corrected, could affect the structural integrity of the airframe. Prompted by these findings, [Direction G[eacute]n[eacute]rale de l'Aviation Civile] (DGAC) France issued AD 1997-006-210 [which corresponds to FAA AD 98-21-34, Amendment 39-10842 (63 FR 55524, October 16, 1998)] to require repetitive inspections to detect the presence of corrosion and prevent crack propagation at the wing bottom skin, inboard and outboard of the Rib 1 external lower surface splice, between Frame (FR) 40 and FR47. DGAC France * * * issued [an AD] to expand the choice of applicable Service Bulletins (SB). [The] DGAC France AD * * * was issued to allow A300-600 operators to use Revision 04 of Airbus SB A300-57-6047, converting flight cycles/''Fatigue rating'' into flight cycles (FC)/flight hours (FH). Subsequently, Airbus modification 10599 was developed to improve the corrosion behaviour of the area. This improvement allowed refining the inspection programme of the A300-600 aeroplane. For post-modification 10599 A300-600 aeroplanes, the application of the Maintenance Review Board Report (MRBR) inspection tasks was deemed sufficient for maintaining an adequate level of safety on these aeroplanes. Consequently, EASA issued AD 2008-0208 (later revised), retaining the requirements of [a] DGAC France AD * * *, which was superseded, to require the use of Airbus SB A300-57-6047 Revision 05 for the inspections and to exclude post-modification 10599 A300-600 aeroplanes from the Applicability. Since EASA AD 2008-0208R1 was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300-600 Extended Service Goal (ESG2) exercise. The results of these analyses determined that the threshold and interval must be reduced to allow timely detection of these cracks and the accomplishment of an applicable corrective action. For the reasons described above, this [EASA] AD takes over and retains the requirements for A300 and A300-600 aeroplanes from EASA AD 2008-0208R1 (which has been revised, remaining applicable only to A310 aeroplanes) and requires accomplishment of the inspections within the new thresholds and intervals. Required actions include repetitive detailed inspections for corrosion of the [[Page 10256]] rib 1 external lower surface splice between FR40 and FR47, repetitive fatigue inspections for cracking of the fasteners and on the surface of the forward and aft lower surface panels if necessary, and corrective actions (including application of new protective coating, removal of corrosion, and measurement of the reworked depth) if necessary. 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-2016- 5040. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Clarify the Applicability United Parcel Service (UPS) requested that we change the information in paragraph (c), Applicability, of the proposed AD. UPS explained that paragraph (c) of the proposed AD defines the airplane models applicable to the proposed rule, then has an exclusion later in paragraph (g) of the proposed AD. UPS reasoned that we should simplify by having related information in the same location, and suggested we combine paragraph (c) and paragraph (g) of the proposed AD into a single paragraph (c) of the proposed AD. For the reasons stated by the commenter, we agree to include the phrase, ``except those on which Airbus modification 10599 has been incorporated,'' in paragraph (c)(2) of this AD. However, we disagree with moving the statement, ``As of the effective date of this AD, the actions specified in AD 98-21-34, Amendment 39-10842 (63 FR 55524, October 16, 1998) (``AD 98-21-34'') are no longer required'' from paragraph (g) of this AD to paragraph (c) of this AD because the Applicability should not include this type of information; it is appropriately included in other regulatory text such as paragraph (g) of this AD. Request To Clarify the Headings of Paragraphs (h) and (i) of the Proposed AD UPS requested that we revise the headings of paragraphs (h) and (i) of the proposed AD because the paragraph titles do not reflect what is contained within the respective paragraphs. UPS explained that paragraph (h) of the proposed AD does not contain any corrective actions, and paragraph (i) of the proposed AD contains fatigue inspection requirements. For the reasons stated by the commenter, we agree and have revised the headings of both paragraphs (h) and (i) of this AD. Request for Grace Period UPS stated that upon its review of the fatigue inspection requirements, it identified that there is not a transition/grace period for airplanes on which inspections are already being accomplished, but for which the new repetitive inspection intervals have already been exceeded due to the service bulletin interval reductions. We agree with the commenter's statement. We had erroneously specified Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011, in the compliance time in paragraph (i)(2)(ii)(B) of the proposed AD; the correct reference is Airbus Service Bulletin A300- 57-6047, Revision 05, dated May 27, 2008. We have changed paragraph (i)(2)(ii)(B) of this AD to include a grace period of 500 flight cycles or 1,050 flight hours (whichever occurs first), without exceeding the compliance time specified in Airbus Service Bulletin A300-57-6047, Revision 05, dated May 27, 2008. Request To Remove Paragraph (j) of the Proposed AD UPS requested that we delete paragraph (j) of the proposed AD. UPS explained that paragraphs (j)(1) and (j)(2) of the proposed AD identify differences between the service bulletin requirements specified by the original equipment manufacturer (OEM) and the proposed AD. UPS stated that in its review of paragraphs (j)(1) and (j)(2) of the proposed AD, it does not recognize a difference between contacting Airbus for corrective action, and using a method approved by the FAA for either situation. UPS reasoned that, as the discrepancy is located on primary structure and allowable/approved rework limits are exceeded, damage tolerance analysis is required as part of the repair definition process. UPS adds that the existing OEM process, the Repair Design Approval Sheet (RDAS), contains instructions for continued airworthiness and is approved by an EASA-designated airworthiness engineer. Based on the existing process and procedures in place, UPS does not believe that paragraph (j) of the proposed AD is necessary. We disagree with the request to delete paragraph (j) of this AD. Paragraph (j)(1) of this AD is required to address certain inspection findings. The service information specifies that Airbus be contacted for corrective action; however, paragraph (j)(1) of this AD requires that one of the specific organizations identified must approve those corrective actions. Likewise, paragraph (j)(2) of this AD specifies the appropriate organizations for compliance time determinations. Therefore, we have not changed this AD in this regard. Request To Define Average Flight Time (AFT) UPS requested that we revise paragraph (k) of the proposed AD to match paragraph (i) of AD 2016-07-20, Amendment 39-18465 (81 FR 21255, April 11, 2016). UPS reasoned that AD 2016-07-20 clearly defines when the AFT value is calculated in subsequent repetitive inspection interval determinations. UPS explained that recent FAA ADs have included using AFT to determine repetitive inspection intervals, but the definition of calculating the AFT value has varied among ADs, which further complicates compliance across several mandatory ADs. For the reasons stated by the commenter, we have added more specific criteria for establishing the AFT in paragraph (k) of this AD. Request To Include Approval for Previous Alternative Methods of Compliance (AMOCs) UPS requested that we revise paragraph (m) of the proposed AD to include approval for previous AMOCs. UPS explained that other final rules include approved AMOCs for prior or superseded ADs. UPS explained further that it received AMOC approval for AD 98-21-34 in which the intent is embodied within the proposed AD (i.e., no additional action for an airplane with modification 10599 embodied), and that there may be other AMOC approvals applicable to the previous AD. We agree for the reasons stated by the commenter. We added the previous AMOC approval information in paragraph (m)(1)(ii) of this final rule. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. [[Page 10257]] We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999; and Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011. This service information describes procedures for repetitive detailed inspections for corrosion of the rib 1 external lower surface splice between FR40 and FR47, repetitive fatigue inspections for cracking of the fasteners and on the surface of the forward and aft lower surface panels if necessary, and corrective actions (including application of new protective coating, removal of corrosion, and measurement of the reworked depth) if necessary. These documents are distinct since they apply to different airplane models. 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 29 airplanes of U.S. registry. We also estimate that it would take about 8 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $19,720, or $680 per product. In addition, we estimate that any necessary follow-on actions would take about 8 work-hours, for a cost of $680 per product. 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. 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 adding the following new airworthiness directive (AD): 2017-02-08 Airbus: Amendment 39-18787; Docket No. FAA-2016-5040; Directorate Identifier 2013-NM-192-AD. (a) Effective Date This AD is effective March 17, 2017. (b) Affected ADs This AD affects AD 98-21-34, Amendment 39-10842 (63 FR 55524, October 16, 1998) (``AD 98-21-34''). (c) Applicability This AD applies to Airbus airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD. (1) All Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes. (2) Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes, except those on which Airbus modification 10599 has been incorporated. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports of corrosion on the lower wing root joint located in the wing bottom skin inboard and outboard of the external lower surface splice, and the determination that certain existing inspection thresholds and intervals must be reduced. We are issuing this AD to detect and correct corrosion and cracking on the lower wing root joint, which could reduce the structural integrity of the airframe. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Airplanes Excluded From the Requirements of AD 98-21-34 and This AD For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes, on which Airbus modification 10599 has been incorporated: As of the effective date of this AD, the actions specified in AD 98-21-34 are no longer required. No action is required by this AD. (h) Repetitive Inspections Within 60 months since the airplane's first flight, or within 60 months since accomplishment of the last inspection specified in Airbus Service Bulletin A300-57-0204 or A300-57-6047, whichever occurs later: Do a detailed inspection for corrosion of the rib 1 external lower surface splice between frame (FR)40 and FR47, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; as applicable. Repeat the inspection thereafter at intervals not to exceed 60 months. Accomplishment of the initial inspection required by this paragraph terminates the requirements of AD 98-21-34 for Model A300 and A300-600 series airplanes. (i) Corrective Actions, Repetitive Fatigue Inspections, and Repair If any corrosion is found during any inspection required by paragraph (h) of this AD, do the actions specified in paragraph (i)(1) and (i)(2) of this AD. (1) Before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; as applicable; except as required by paragraph (j)(1) of this AD. (2) At the applicable time specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD, except as required by paragraph (j)(2) of this AD: Do fatigue inspections to detect cracks of [[Page 10258]] the fasteners and on the surface of the forward and aft lower surface panels, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; as applicable. Repeat the fatigue inspections thereafter at the applicable interval specified in paragraph B.(5) of Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Figure A-FBGAA, Sheet 01, of Airbus Service Bulletin A300- 57-6047, Revision 06, dated October 17, 2011; as applicable; except as required by paragraph (j)(2) of this AD. If any cracking is found during any fatigue inspection required by this paragraph: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (i) For Model A300 series airplanes: Do the initial inspection at the applicable time specified in paragraph B.(5) of Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999. (ii) For Model A300-600 series airplanes: Do the initial inspection at the later of the times specified in paragraphs (i)(2)(ii)(A) and (i)(2)(ii)(B) of this AD. (A) At the applicable time specified in Figure A-FBGAA, Sheet 01, of Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011. (B) Within 500 flight cycles or 1,050 flight hours after the effective date of this AD, whichever occurs first, without exceeding the compliance time specified in Airbus Service Bulletin A300-57- 6047, Revision 05, dated May 27, 2008. (j) Exceptions to Service Bulletin Specifications (1) Where Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; specifies to contact Airbus for appropriate corrective action, this AD requires repair before further flight using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (2) Where Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011, specifies to contact Airbus for the appropriate threshold or repetitive interval, this AD requires that the compliance time be determined using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (k) Calculating Average Flight Time (AFT) For the purposes of paragraph (i)(2) of this AD, the AFT must be established as specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD. (1) For the initial inspection, the AFT is the total accumulated flight hours, counted from take-off to touch-down, divided by the total accumulated flight cycles at the effective date of this AD. (2) For the first repeated inspection interval, the AFT is the total accumulated flight hours divided by the total accumulated flight cycles at the time of the inspection threshold. (3) For all inspection intervals onward, the AFT is the flight hours accumulated between the two most recent inspections divided by the flight cycles accumulated between the two most recent inspections. (l) Credit for Previous Actions This paragraph provides credit for the inspections and corrective actions required by paragraphs (h) and (i) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraphs (l)(1) through (l)(3) of this AD. (1) Airbus Service Bulletin A300-57-6047, Revision 02, dated April 2, 1999. (2) Airbus Service Bulletin A300-57-6047, Revision 03, dated September 28, 1999. (3) Airbus Service Bulletin A300-57-6047, Revision 05, dated May 27, 2008. (m) 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: 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 98-21-34 are approved as AMOCs for the corresponding provisions of paragraphs (h) and (i) of this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2013-0230, dated September 24, 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-2016-5040. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(4) of this AD. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999. (ii) Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011. (3) 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. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on January 18, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-01776 Filed 2-9-17; 8:45 am] BILLING CODE 4910-13-P
![10255
Rules and Regulations Federal Register
Vol. 82, No. 27
Friday, February 10, 2017
This section of the FEDERAL REGISTER referenced service information at the Model A300 C4–605R Variant F
contains regulatory documents having general FAA, Transport Airplane Directorate, airplanes (collectively called Model
applicability and legal effect, most of which 1601 Lind Avenue SW., Renton, WA. A300–600 series airplanes). The MCAI
are keyed to and codified in the Code of For information on the availability of states:
Federal Regulations, which is published under this material at the FAA, call 425–227–
50 titles pursuant to 44 U.S.C. 1510. Several cases of corrosion on the lower
1221. It is also available on the Internet wing root joint, located in the wing bottom
The Code of Federal Regulations is sold by at http://www.regulations.gov by skin inboard and outboard of the external
the Superintendent of Documents. Prices of searching for and locating Docket No. lower surface splice, have been reported by
new books are listed in the first FEDERAL FAA–2016–5040. operators.
REGISTER issue of each week. This condition, if not detected and
Examining the AD Docket corrected, could affect the structural integrity
You may examine the AD docket on of the airframe.
DEPARTMENT OF TRANSPORTATION Prompted by these findings, [Direction
the Internet at http:// Générale de l’Aviation Civile] (DGAC) France
www.regulations.gov by searching for issued AD 1997–006–210 [which
Federal Aviation Administration and locating Docket No. FAA–2016– corresponds to FAA AD 98–21–34,
5040; or in person at the Docket Amendment 39–10842 (63 FR 55524, October
14 CFR Part 39 Management Facility between 9 a.m. 16, 1998)] to require repetitive inspections to
[Docket No. FAA–2016–5040; Directorate and 5 p.m., Monday through Friday, detect the presence of corrosion and prevent
Identifier 2013–NM–192–AD; Amendment except Federal holidays. The AD docket crack propagation at the wing bottom skin,
39–18787; AD 2017–02–08] contains this AD, the regulatory inboard and outboard of the Rib 1 external
lower surface splice, between Frame (FR) 40
RIN 2120–AA64
evaluation, any comments received, and and FR47.
other information. The street address for DGAC France * * * issued [an AD] to
Airworthiness Directives; Airbus the Docket Office (telephone 800–647– expand the choice of applicable Service
Airplanes 5527) is Docket Management Facility, Bulletins (SB). [The] DGAC France AD * * *
U.S. Department of Transportation, was issued to allow A300–600 operators to
AGENCY: Federal Aviation Docket Operations, M–30, West use Revision 04 of Airbus SB A300–57–6047,
Administration (FAA), Department of Building Ground Floor, Room W12–140, converting flight cycles/’’Fatigue rating’’ into
Transportation (DOT). 1200 New Jersey Avenue SE., flight cycles (FC)/flight hours (FH).
Subsequently, Airbus modification 10599
ACTION: Final rule. Washington, DC 20590.
was developed to improve the corrosion
FOR FURTHER INFORMATION CONTACT: Dan behaviour of the area. This improvement
SUMMARY: We are adopting a new Rodina, Aerospace Engineer, allowed refining the inspection programme
airworthiness directive (AD) for certain International Branch, ANM–116, of the A300–600 aeroplane. For post-
Airbus Model A300 series airplanes; Transport Airplane Directorate, FAA, modification 10599 A300–600 aeroplanes,
and Model A300 B4–600, B4–600R, and 1601 Lind Avenue SW., Renton, WA the application of the Maintenance Review
F4–600R series airplanes, and Model 98057–3356; telephone (425) 227–2125; Board Report (MRBR) inspection tasks was
A300 C4–605R Variant F airplanes fax (425) 227–1149.
deemed sufficient for maintaining an
(collectively called Model A300–600 adequate level of safety on these aeroplanes.
SUPPLEMENTARY INFORMATION: Consequently, EASA issued AD 2008–0208
series airplanes). This AD was prompted
by a determination that certain (later revised), retaining the requirements of
Discussion [a] DGAC France AD * * *, which was
inspection thresholds and intervals We issued a notice of proposed superseded, to require the use of Airbus SB
must be reduced. This AD requires rulemaking (NPRM) to amend 14 CFR A300–57–6047 Revision 05 for the
repetitive detailed inspections for part 39 by adding an AD that would inspections and to exclude post-modification
corrosion of the lower wing root joint, apply to certain Airbus Model A300 10599 A300–600 aeroplanes from the
and related investigative and corrective series airplanes; and Model A300 B4–
Applicability.
actions if necessary. We are issuing this Since EASA AD 2008–0208R1 was issued,
600, B4–600R, and F4–600R series a fleet survey and updated Fatigue and
AD to address the unsafe condition on airplanes, and Model A300 C4–605R
these products. Damage Tolerance analyses have been
Variant F airplanes (collectively called performed in order to substantiate the second
DATES: This AD is effective March 17, Model A300–600 series airplanes). The A300–600 Extended Service Goal (ESG2)
2017. NPRM published in the Federal exercise. The results of these analyses
The Director of the Federal Register Register on April 5, 2016 (81 FR 19509) determined that the threshold and interval
approved the incorporation by reference (‘‘the NPRM’’). must be reduced to allow timely detection of
of certain publications listed in this AD these cracks and the accomplishment of an
The European Aviation Safety Agency
as of March 17, 2017. applicable corrective action.
(EASA), which is the Technical Agent For the reasons described above, this
ADDRESSES: For service information for the Member States of the European [EASA] AD takes over and retains the
identified in this final rule, contact Union, has issued EASA AD 2013–0230, requirements for A300 and A300–600
Airbus SAS, Airworthiness Office— dated September 24, 2013 (referred to
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aeroplanes from EASA AD 2008–0208R1
EAW, 1 Rond Point Maurice Bellonte, after this as the Mandatory Continuing (which has been revised, remaining
31707 Blagnac Cedex, France; telephone Airworthiness Information, or ‘‘the applicable only to A310 aeroplanes) and
+33 5 61 93 36 96; fax +33 5 61 93 44 MCAI’’), to correct an unsafe condition requires accomplishment of the inspections
51; email account.airworth-eas@ for certain Airbus Model A300 series within the new thresholds and intervals.
airbus.com; Internet http:// airplanes; and Model A300 B4–600, B4– Required actions include repetitive
www.airbus.com. You may view this 600R, and F4–600R series airplanes, and detailed inspections for corrosion of the
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![Federal Register / Vol. 82, No. 27 / Friday, February 10, 2017 / Rules and Regulations 10257
We also determined that these because it addresses an unsafe condition (2) Model A300 B4–601, B4–603, B4–620,
changes will not increase the economic that is likely to exist or develop on B4–622, B4–605R, B4–622R, F4–605R, F4–
burden on any operator or increase the products identified in this rulemaking 622R, and C4–605R Variant F airplanes,
except those on which Airbus modification
scope of this AD. action.
10599 has been incorporated.
Related Service Information Under 1 Regulatory Findings (d) Subject
CFR Part 51 We determined that this AD will not Air Transport Association (ATA) of
We reviewed Airbus Service Bulletin have federalism implications under America Code 57, Wings.
A300–57–0204, Revision 01, dated April Executive Order 13132. This AD will
(e) Reason
2, 1999; and Airbus Service Bulletin not have a substantial direct effect on
A300–57–6047, Revision 06, dated the States, on the relationship between This AD was prompted by reports of
October 17, 2011. This service corrosion on the lower wing root joint
the national government and the States, located in the wing bottom skin inboard and
information describes procedures for or on the distribution of power and outboard of the external lower surface splice,
repetitive detailed inspections for responsibilities among the various and the determination that certain existing
corrosion of the rib 1 external lower levels of government. inspection thresholds and intervals must be
surface splice between FR40 and FR47, For the reasons discussed above, I reduced. We are issuing this AD to detect and
repetitive fatigue inspections for certify that this AD: correct corrosion and cracking on the lower
cracking of the fasteners and on the 1. Is not a ‘‘significant regulatory wing root joint, which could reduce the
surface of the forward and aft lower action’’ under Executive Order 12866; structural integrity of the airframe.
surface panels if necessary, and 2. Is not a ‘‘significant rule’’ under the (f) Compliance
corrective actions (including application DOT Regulatory Policies and Procedures Comply with this AD within the
of new protective coating, removal of (44 FR 11034, February 26, 1979); compliance times specified, unless already
corrosion, and measurement of the 3. Will not affect intrastate aviation in done.
reworked depth) if necessary. These Alaska; and
4. Will not have a significant (g) Airplanes Excluded From the
documents are distinct since they apply Requirements of AD 98–21–34 and This AD
to different airplane models. This economic impact, positive or negative,
on a substantial number of small entities For Model A300 B4–601, B4–603, B4–620,
service information is reasonably
under the criteria of the Regulatory B4–622, B4–605R, B4–622R, F4–605R, F4–
available because the interested parties 622R, and C4–605R Variant F airplanes, on
have access to it through their normal Flexibility Act.
which Airbus modification 10599 has been
course of business or by the means List of Subjects in 14 CFR Part 39 incorporated: As of the effective date of this
identified in the ADDRESSES section. AD, the actions specified in AD 98–21–34 are
Air transportation, Aircraft, Aviation no longer required. No action is required by
Costs of Compliance safety, Incorporation by reference, this AD.
We estimate that this AD affects 29 Safety.
(h) Repetitive Inspections
airplanes of U.S. registry. We also Adoption of the Amendment Within 60 months since the airplane’s first
estimate that it would take about 8
Accordingly, under the authority flight, or within 60 months since
work-hours per product to comply with accomplishment of the last inspection
the basic requirements of this AD. The delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as specified in Airbus Service Bulletin A300–
average labor rate is $85 per work-hour. 57–0204 or A300–57–6047, whichever occurs
Based on these figures, we estimate the follows: later: Do a detailed inspection for corrosion
cost of this AD on U.S. operators to be of the rib 1 external lower surface splice
PART 39—AIRWORTHINESS between frame (FR)40 and FR47, in
$19,720, or $680 per product.
DIRECTIVES accordance with the Accomplishment
In addition, we estimate that any
necessary follow-on actions would take Instructions of Airbus Service Bulletin A300–
■ 1. The authority citation for part 39 57–0204, Revision 01, dated April 2, 1999; or
about 8 work-hours, for a cost of $680 continues to read as follows: Airbus Service Bulletin A300–57–6047,
per product. We have no way of Revision 06, dated October 17, 2011; as
Authority: 49 U.S.C. 106(g), 40113, 44701.
determining the number of aircraft that applicable. Repeat the inspection thereafter
might need these actions. § 39.13 [Amended] at intervals not to exceed 60 months.
Accomplishment of the initial inspection
Authority for This Rulemaking ■ 2. The FAA amends § 39.13 by adding required by this paragraph terminates the
Title 49 of the United States Code the following new airworthiness requirements of AD 98–21–34 for Model
specifies the FAA’s authority to issue directive (AD): A300 and A300–600 series airplanes.
rules on aviation safety. Subtitle I, 2017–02–08 Airbus: Amendment 39–18787; (i) Corrective Actions, Repetitive Fatigue
section 106, describes the authority of Docket No. FAA–2016–5040; Directorate Inspections, and Repair
the FAA Administrator. ‘‘Subtitle VII: Identifier 2013–NM–192–AD.
If any corrosion is found during any
Aviation Programs,’’ describes in more (a) Effective Date inspection required by paragraph (h) of this
detail the scope of the Agency’s This AD is effective March 17, 2017. AD, do the actions specified in paragraph
authority. (i)(1) and (i)(2) of this AD.
We are issuing this rulemaking under (b) Affected ADs (1) Before further flight, do all applicable
the authority described in ‘‘Subtitle VII, This AD affects AD 98–21–34, Amendment corrective actions, in accordance with the
Part A, Subpart III, Section 44701: 39–10842 (63 FR 55524, October 16, 1998) Accomplishment Instructions of Airbus
General requirements.’’ Under that (‘‘AD 98–21–34’’). Service Bulletin A300–57–0204, Revision 01,
section, Congress charges the FAA with dated April 2, 1999; or Airbus Service
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(c) Applicability Bulletin A300–57–6047, Revision 06, dated
promoting safe flight of civil aircraft in
This AD applies to Airbus airplanes, October 17, 2011; as applicable; except as
air commerce by prescribing regulations certificated in any category, identified in required by paragraph (j)(1) of this AD.
for practices, methods, and procedures paragraphs (c)(1) and (c)(2) of this AD. (2) At the applicable time specified in
the Administrator finds necessary for (1) All Model A300 B2–1A, B2–1C, B2K– paragraph (i)(2)(i) or (i)(2)(ii) of this AD,
safety in air commerce. This regulation 3C, B2–203, B4–2C, B4–103, and B4–203 except as required by paragraph (j)(2) of this
is within the scope of that authority airplanes. AD: Do fatigue inspections to detect cracks of
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![10258 Federal Register / Vol. 82, No. 27 / Friday, February 10, 2017 / Rules and Regulations
the fasteners and on the surface of the flight hours divided by the total accumulated available at the addresses specified in
forward and aft lower surface panels, in flight cycles at the time of the inspection paragraphs (o)(3) and (o)(4) of this AD.
accordance with the Accomplishment threshold.
Instructions of Airbus Service Bulletin A300– (o) Material Incorporated by Reference
(3) For all inspection intervals onward, the
57–0204, Revision 01, dated April 2, 1999; or AFT is the flight hours accumulated between (1) The Director of the Federal Register
Airbus Service Bulletin A300–57–6047, the two most recent inspections divided by approved the incorporation by reference
Revision 06, dated October 17, 2011; as the flight cycles accumulated between the (IBR) of the service information listed in this
applicable. Repeat the fatigue inspections two most recent inspections. paragraph under 5 U.S.C. 552(a) and 1 CFR
thereafter at the applicable interval specified part 51.
in paragraph B.(5) of Airbus Service Bulletin (l) Credit for Previous Actions (2) You must use this service information
A300–57–0204, Revision 01, dated April 2, This paragraph provides credit for the as applicable to do the actions required by
1999; or Figure A–FBGAA, Sheet 01, of inspections and corrective actions required this AD, unless this AD specifies otherwise.
Airbus Service Bulletin A300–57–6047, by paragraphs (h) and (i) of this AD, if those (i) Airbus Service Bulletin A300–57–0204,
Revision 06, dated October 17, 2011; as actions were performed before the effective Revision 01, dated April 2, 1999.
applicable; except as required by paragraph date of this AD using the applicable service (ii) Airbus Service Bulletin A300–57–6047,
(j)(2) of this AD. If any cracking is found information specified in paragraphs (l)(1) Revision 06, dated October 17, 2011.
during any fatigue inspection required by through (l)(3) of this AD. (3) For service information identified in
this paragraph: Before further flight, repair (1) Airbus Service Bulletin A300–57–6047, this AD, contact Airbus SAS, Airworthiness
using a method approved by the Manager, Revision 02, dated April 2, 1999. Office—EAW, 1 Rond Point Maurice
International Branch, ANM–116, Transport (2) Airbus Service Bulletin A300–57–6047, Bellonte, 31707 Blagnac Cedex, France;
Airplane Directorate, FAA; or the European Revision 03, dated September 28, 1999. telephone +33 5 61 93 36 96; fax +33 5 61
Aviation Safety Agency (EASA); or Airbus’s (3) Airbus Service Bulletin A300–57–6047, 93 44 51; email account.airworth-eas@
EASA Design Organization Approval (DOA). Revision 05, dated May 27, 2008. airbus.com; Internet http://www.airbus.com.
(i) For Model A300 series airplanes: Do the (4) You may view this service information
initial inspection at the applicable time (m) Other FAA AD Provisions at the FAA, Transport Airplane Directorate,
specified in paragraph B.(5) of Airbus Service The following provisions also apply to this 1601 Lind Avenue SW., Renton, WA. For
Bulletin A300–57–0204, Revision 01, dated AD: information on the availability of this
April 2, 1999. (1) Alternative Methods of Compliance material at the FAA, call 425–227–1221.
(ii) For Model A300–600 series airplanes: (AMOCs): The Manager, International (5) You may view this service information
Do the initial inspection at the later of the Branch, ANM–116, Transport Airplane that is incorporated by reference at the
times specified in paragraphs (i)(2)(ii)(A) and Directorate, FAA, has the authority to National Archives and Records
(i)(2)(ii)(B) of this AD. approve AMOCs for this AD, if requested Administration (NARA). For information on
(A) At the applicable time specified in using the procedures found in 14 CFR 39.19. the availability of this material at NARA, call
Figure A–FBGAA, Sheet 01, of Airbus In accordance with 14 CFR 39.19, send your 202–741–6030, or go to: http://
Service Bulletin A300–57–6047, Revision 06, request to your principal inspector or local www.archives.gov/federal-register/cfr/ibr-
dated October 17, 2011.
Flight Standards District Office, as locations.html.
(B) Within 500 flight cycles or 1,050 flight
appropriate. If sending information directly
hours after the effective date of this AD, Issued in Renton, Washington, on January
to the International Branch, send it to ATTN:
whichever occurs first, without exceeding the 18, 2017.
Dan Rodina, Aerospace Engineer,
compliance time specified in Airbus Service Michael Kaszycki,
International Branch, ANM–116, Transport
Bulletin A300–57–6047, Revision 05, dated Acting Manager, Transport Airplane
Airplane Directorate, FAA, 1601 Lind
May 27, 2008. Directorate, Aircraft Certification Service.
Avenue SW., Renton, WA 98057–3356;
(j) Exceptions to Service Bulletin telephone (425) 227–2125; fax (425) 227– [FR Doc. 2017–01776 Filed 2–9–17; 8:45 am]
Specifications 1149. Information may be emailed to: 9- BILLING CODE 4910–13–P
(1) Where Airbus Service Bulletin A300– ANM-116-AMOC-REQUESTS@faa.gov.
57–0204, Revision 01, dated April 2, 1999; or (i) Before using any approved AMOC,
Airbus Service Bulletin A300–57–6047, notify your appropriate principal inspector,
or lacking a principal inspector, the manager
DEPARTMENT OF TRANSPORTATION
Revision 06, dated October 17, 2011;
specifies to contact Airbus for appropriate of the local flight standards district office/
certificate holding district office. The AMOC
Federal Aviation Administration
corrective action, this AD requires repair
before further flight using a method approved approval letter must specifically reference
this AD. 14 CFR Part 39
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or (ii) AMOCs approved previously for AD [Docket No. FAA–2016–6670; Directorate
EASA; or Airbus’s EASA DOA. 98–21–34 are approved as AMOCs for the Identifier 2016–NM–006–AD; Amendment
(2) Where Airbus Service Bulletin A300– corresponding provisions of paragraphs (h) 39–18789; AD 2017–02–10]
57–6047, Revision 06, dated October 17, and (i) of this AD.
2011, specifies to contact Airbus for the (2) Contacting the Manufacturer: For any RIN 2120–AA64
appropriate threshold or repetitive interval, requirement in this AD to obtain corrective
this AD requires that the compliance time be actions from a manufacturer, the action must Airworthiness Directives; The Boeing
determined using a method approved by the be accomplished using a method approved Company Airplanes
Manager, International Branch, ANM–116, by the Manager, International Branch, ANM–
Transport Airplane Directorate, FAA; or 116, Transport Airplane Directorate, FAA; or AGENCY: Federal Aviation
EASA; or Airbus’s EASA DOA. the EASA; or Airbus’s EASA DOA. If Administration (FAA), DOT.
approved by the DOA, the approval must ACTION: Final rule.
(k) Calculating Average Flight Time (AFT) include the DOA-authorized signature.
For the purposes of paragraph (i)(2) of this SUMMARY: We are superseding
(n) Related Information
AD, the AFT must be established as specified Airworthiness Directive (AD) 2013–19–
in paragraphs (k)(1), (k)(2), and (k)(3) of this (1) Refer to Mandatory Continuing 04 for certain The Boeing Company
AD. Airworthiness Information (MCAI) EASA AD Model 737–600, –700, –700C, –800, and
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(1) For the initial inspection, the AFT is 2013–0230, dated September 24, 2013, for
–900 series airplanes. AD 2013–19–04
the total accumulated flight hours, counted related information. This MCAI may be
from take-off to touch-down, divided by the found in the AD docket on the Internet at required repetitive inspections for
total accumulated flight cycles at the http://www.regulations.gov by searching for cracking of the skin around the fasteners
effective date of this AD. and locating Docket No. FAA–2016–5040. common to the ends of certain bulkhead
(2) For the first repeated inspection (2) Service information identified in this chords, and related investigative actions
interval, the AFT is the total accumulated AD that is not incorporated by reference is and corrective actions if necessary; and
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Document Created: 2017-02-11 18:15:28
Document Modified: 2017-02-11 18:15:28
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective March 17, 2017. | |
| 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 | 82 FR 10255 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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