AD 2018-17-10

We are superseding Airworthiness Directive (AD) 2017-15-17, which applied to certain Airbus Model A300 B4-600R series airplanes, Model A300 C4-605R Variant F airplanes, and Model A300 F4-600R series airplanes. AD 2017-15-17 required an inspection of the lower area of a certain frame (FR) radius for cracking, and corrective action if necessary. This AD requires new repetitive inspections of the forward fitting lower radius of a certain frame for cracking, and corrective actions if necessary. This AD was prompted by a determination that repetitive inspections and applicable corrective actions are necessary. We are issuing this AD to address the unsafe condition on these products.

Final rule.

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) 2017-15-17, Amendment 39-18977 (82 FR 35644, August 1, 2017), and adding the following new AD:

2018-17-10 Airbus SAS: Amendment 39-19364; Docket No. FAA-2018-0277; Product Identifier 2017-NM-124-AD.

(a) Effective Date

This AD is effective September 24, 2018.

(b) Affected ADs

This AD replaces AD 2017-15-17, Amendment 39-18977 (82 FR 35644, August 1, 2017) (``AD 2017-15-17'').

(c) Applicability

This AD applies to Airbus SAS airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, on which AirbusSAS Modification 10221 was embodied in production.
(1) Airbus SAS Model A300 B4-605R and B4-622R airplanes.
(2) Airbus SAS Model A300 C4-605R Variant F airplanes.
(3) Airbus SAS Model A300 F4-605R and F4-622R airplanes.

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(d) Subject

Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

This AD was prompted by the detection of cracking that originated from the fastener holes in the forward fitting lower radius of frame (FR) 40. We are issuing this AD to detect and correct cracking in the forward fitting lower radius of FR 40. Such cracking could reduce the structural integrity of the fuselage.

(f) Compliance

Comply with this AD within the compliance times specified, unless already done.

(g) Definitions

(1) For the purpose of this AD, the average flight time (AFT) can be established by dividing the flight hours (FHs) by the flight cycles (FCs) counted:
(i) From first flight, for selecting the inspection threshold of the non-repaired area.
(ii) From repair, for selecting the inspection threshold of the repaired area.
(iii) From the last inspection, for selecting the inspection interval.
(2) For the purpose of this AD, Group 1 airplanes are those airplanes already inspected in accordance with paragraph 4.2.2 in Alert Operators Transmission (AOT) A57W009-16, Revision 01, dated July 13, 2016, before the effective date of this AD. Group 2 airplanes are those airplanes not inspected in accordance with paragraph 4.2.2 in AOT A57W009-16, Revision 01, dated July 13, 2016, as of the effective date of this AD.
(3) For the purpose of this AD, inspection method A is a high frequency eddy current (HFEC) inspection of the radius and fastener area. Inspection method B is a HFEC inspection of the radius and fastener area and a rototest of the fastener hole. Both are defined as a special detailed inspection (SDI) in this AD.

(h) Repetitive Inspections for Non-Repaired AreasWithin the compliance time values specified in table 1 to paragraph (h) of this AD (Group 1 airplanes) or table 2 to paragraph (h) of this AD (Group 2 airplanes), as applicable, and, thereafter, at intervals not exceeding the values specified in table 3 to paragraph (h) of this AD: Do a SDI for cracking of any non-repaired radius, fastener areas, and fastener holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6120, dated April 28, 2017; except where Airbus Service Bulletin A300-57- 6120, dated April 28, 2017, specifies contacting Airbus SAS for appropriate action, before further flight, obtain instructions using the procedures specified in paragraph (m)(2) of this AD and accomplish those instructions.

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(i) Repetitive Inspections for RepairedAreas

Within the compliance time values specified in table 4 to paragraph (i) of this AD, and, thereafter, at intervals not exceeding those same values, do a SDI for cracking of the repaired radius, fastener areas, and fastener holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6120, dated April 28, 2017; except where Airbus Service Bulletin A300-57- 6120, dated April 28, 2017, specifies contacting Airbus SAS for appropriate action, before further flight, obtain instructions using the procedures specified in paragraph (m)(2) of this AD and accomplish those instructions. [GRAPHIC] [TIFF OMITTED] TR20AU18.004

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(j) Corrective Action

If any crack is found during any inspection required by paragraph (h) or (i) of this AD: Before further flight, repair in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6120, dated April 28, 2017.

(k) Reporting

Submit a report ofthe findings (both positive and negative) of each inspection required by paragraphs (h) and (i) of this AD to Airbus SAS, in accordance with the instructions of Airbus Service Bulletin A300-57-6120, dated April 28, 2017, at the applicable time specified in paragraph (k)(1) or (k)(2) of this AD.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.

(l) Paperwork Reduction Act Burden Statement

A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this informationcollection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 1 hour per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200.

(m) Other FAA AD Provisions

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (n)(2) of this AD. 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

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the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by paragraphs (h) and (i) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC.

(n) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2017-0158, dated August 25, 2017, 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-2018-0277.
(2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3225.

(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.
(3) The following service information was approved for IBR on September 5, 2017 (82 FR 35644, August 1, 2017).
(i) Airbus Service Bulletin A300-57-6120, dated April 28, 2017.
(ii) Reserved.
(4) 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 account.airworth-eas@airbus.com; internet http://www.airbus.com.
(5) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195.
(6) 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.

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2017-15-17, Amendment 39-18977 (82 FR 35644, August 1, 2017) (``AD 2017-15-17''). AD 2017-15-17 applied to certain Airbus Model A300 B4-600R series airplanes, Model A300 C4-605R Variant F airplanes, and Model A300 F4-600R series airplanes. The NPRM published in the Federal Register on April 17, 2018 (83 FR 16787). The NPRM was prompted by a determination that new repetitive inspections of the lower area of a certain frame radius for cracking, and corrective actions are necessary. The NPRM proposed to require an inspection of the lower area of a certain frame radius for cracking, and corrective action if necessary. The NPRM also proposed to add new repetitive inspections of the lower area of a certain frame radius for cracking, and corrective actions if necessary. We are issuing this AD to detect and correct cracking in the forward fitting lower radius of a certain frame. Such cracking could reduce the structural integrity of the fuselage.
The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017-0158, dated August 25, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus SAS Model A300 B4-600R series airplanes, Model A300 C4-605R Variant F airplanes, and Model A300 F4-600R series airplanes. The MCAI states:

Following a full stress analysis of the Frame (FR) 40 lower area, supported by a Finite Element Model (FEM), of the post-mod [modification] 10221 configuration, it was demonstrated that, for the FR40 forward fitting lower radius, a crack could occur after a certain number of flight cycles (FC).
This condition, if not detected and corrected, could reduce the structural integrity of the fuselage.
To address this potential unsafe condition, Airbus established that crack detection could be achieved through a special detailed inspection (SDI) using a high frequency eddy current (HFEC) method, and issued Alert Operators Transmission (AOT) A57W009-16 to provide those inspection instructions.
Consequently, EASA issued AD 2016-0085 to require a one-time SDI of the FR40 lower area and, depending on findings, accomplishment of applicable corrective action(s). After that [EASA] AD was issued, further cracks were detected, originating from the fastener hole, and, based on these findings, it was determined that the inspection area must be enlarged, and Airbus issued AOT A57W009-16 Revision (Rev.) 01 accordingly. Consequently, EASA issued AD 2016-0179 [which corresponds to FAA AD 2017-15-17], retaining the requirements of EASA AD 2016-0085, which was superseded, to extend the area of inspection, and to require an additional inspection for aeroplanes that were previously inspected.
The one-time SDI for high cycle A300-600 aeroplanes was intended to mitigate the highest risks within the fleet, pending development of instructions for repetitive inspections.
Since EASA AD 2016-0179 was issued, Airbus published SB A300-57- 6120 * * * [for] the inspection programme for A300-600 * * * post- mod 10221 * * * [airplanes]. The AOT one-time inspection is superseded by these repetitive inspection SBs. These SBs include alternative inspection methods and repair solutions in case of findings together with the associated inspection programme.
For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2016-0179, which is superseded, * * * and defines new inspections methods with

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new compliance times, including repetitive inspections, depending on the aeroplane inspection status.

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-2018- 0277.

Comments

We gave the publicthe opportunity to participate in developing this final rule. We received no comments on the NPRM or on the determination of the cost to the public.

Conclusion

We reviewed the relevant data and determined that air safety and the public interest require adopting this final rule 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 for addressing the unsafe condition; and
Do not add any additional burden upon the public than was already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

Airbus SAS has issued Service Bulletin A300-57-6120, dated April 28, 2017. This service information describes procedures for repetitive inspections of the forward fitting lower radius of FR 40 for cracking, and corrective action. 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 94 airplanes of U.S. registry.
The actions required by AD 2017-15-17, and retained in this AD, take about 4 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2017-15-17 is $340 per product.
We also estimate that it takes about 4 work-hours per product to comply with the new requirements of this AD, including 1 work-hour per product for reporting. 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 $39,950, or $425 per product.
We have received no definitive data that enables us to provide cost estimates for the on-condition actions specified in this AD.

Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120- 0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200.

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.
This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transitionperiod, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division.

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.