AD 2019-19-17

The FAA is superseding Airworthiness Directive (AD) 2000-03-20 R1, which applied to all Airbus SAS Model A300 B4-601, B4-603, and B4- 620, Model A300 B4-600R series, and Model A300 F4-605R airplanes. AD 2000-03-20 R1 required repetitive inspections to detect cracks on the forward fittings in the radius of a certain frame, adjacent to the tension bolts in the center section of the wings, and various follow-on actions. This AD retains the requirements of AD 2000-03-20 R1, adds new airplanes to the applicability, and introduces new compliance times for the required inspections, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of cracking due to fatigue-related stress in the radius of frame 40, adjacent to the tension bolts at the center/ outer wing junction. The FAA is 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) 2000-03-20 R1, Amendment 39-12298 (66 FR 34530, June 29, 2001), and adding the following new AD:

2019-19-17 Airbus SAS: Amendment 39-19753; Docket No. FAA-2019-0441; Product Identifier 2019-NM-036-AD.

(a) Effective Date

This AD is effective November 14, 2019.

(b) Affected ADs

This AD replaces AD 2000-03-20 R1, Amendment 39-12298 (66 FR 34530, June 29, 2001) (``AD 2000-03-20 R1'').

(c) Applicability

This AD applies to Airbus SAS airplanes identified in paragraphs (c)(1) through (4) of this AD, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2019- 0044, dated March 7, 2019 (``EASA AD 2019-0044'').
(1) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(2) Model A300 B4-605R and B4-622R airplanes.
(3) Model A300 F4-605R airplanes.
(4) Model A300 C4-605R Variant F airplanes.

(d) Subject

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

(e) Reason

This AD was prompted by reports of cracking due to fatigue- related stress in the radius of frame 40, adjacent to the tension bolts at the center/outer wing junction. The FAA is issuing this AD to address fatigue cracking on the forward fittings in the radius of frame 40, adjacent to the tension bolts in the center section of the wings, which could result in reduced structural integrity of the wings.

(f) Compliance

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

(g) Requirements

Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2019-0044.

(h) Exceptions to EASA AD 2019-0044

(1) For purposes of determining compliance with the requirements of this AD: Where EASA AD 2019-0044 refers to its effective date, this AD requires using the effective date of this AD.
(2) The ``Remarks'' section of EASA AD 2019-0044 does not apply to this AD.
(3) Paragraph (5) of EASA AD 2019-0044 specifies to report all inspection results to Airbus. For this AD, report all inspection results to Airbus Service Bulletin Reporting Online Application on Airbus World (https://w3.airbus.com/) at the applicable time specified in paragraph (h)(3)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(ii) 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.(4) For Model A300 B4-622 and A300 C4-605R Variant F airplanes: The initial compliance time for the inspections required by EASA AD 2019-0044 is at the applicable time specified in EASA AD 2019-0044, or within 12 months after the effective date of this AD, whichever occurs later.

(i) Other FAA AD Provisions

The following provisions also apply to this AD:
(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 (j) 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: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or 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): For any service information referenced in EASA AD 2019-0044 that contains RC procedures and tests: Except as required by paragraph (i)(2) of this AD, RC 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.
(4) 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 information collection 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.

(j) Related Information

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.

(k) 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 November 14, 2019.
(i) European Union Aviation Safety Agency (EASA) AD 2019-0044, dated March 7, 2019.
(ii) [Reserved]
(4) For information about EASA AD 2019-0044, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 89990 6017; email

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ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https://ad.easa.europa.eu.
(5) You may view this material 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. This material may be found in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA- 2019-0441.
(6) You may view this material that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@nara.gov, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2000-03-20 R1, Amendment 39-12298 (66 FR 34530, June 29, 2001) (``AD 2000-03-20 R1''). AD 2000-03-20 R1 applied to all Airbus SAS Model A300 B4-601, B4-603, and B4-620, Model A300 B4- 600R series, and Model A300 F4-605R airplanes. The NPRM published in the Federal Register on June 17, 2019 (84 FR 27990). The NPRM was prompted by reports of cracking due to fatigue-related stress in the radius of frame 40, adjacent to the tension bolts at the center/outer wing junction. The NPRM proposed to require initial and repetitive ultrasonic (UT) and high frequency eddy current (HFEC) inspections and applicable corrective actions. The FAA is issuing this AD to address fatigue cracking on the forward fittings in the radius of frame 40, adjacent to the tension bolts in the center section of the wings, which could result in reduced structural integrity of thewings.
The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2019-0044, dated March 7, 2019 (``EASA AD 2019-0044'') (also referred to as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus SAS Model A300 B4-600 series, Model A300 B4-600R series, Model A300 F4-605R, and Model A300 C4-605R Variant F airplanes. See the MCAI for additional background information.

Comment

The FAA gave the public the opportunity to participate in developing this final rule. The FAA has considered the comment received. Patrick Imperatrice indicated support for the NPRM.

Conclusion

The FAA reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. The FAA has determined that these minor changes:
Are consistent with the intent thatwas 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 IBR Material Under 1 CFR Part 51

EASA AD 2019-0044 describes procedures for initial and repetitive UT and HFEC inspections and applicable corrective actions. Corrective actions include reworking the fuselage lateral panel at frame 40, blending out around cracks, and repair. This material 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

The FAA estimates that this AD affects 65 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD:

Estimated Costs for Required Actions * ----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
ActionLabor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Retained actions from AD 2000-03-20 R1 2 work-hours x $85 per $0 $170 $11,050
hour = $170. New actions........................... 161 work-hours x $85 per 0 13,685 889,525
hour = $13,685. ----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.

The FAA estimates that it would take about 1 work-hour per product to comply with the reporting requirement in this AD. The average labor rate is $85 per hour. Based on these figures, the FAA estimates the cost of reporting the inspection results on U.S. operators to be $5,525, or $85 per product.
The FAA has received no definitive data that would enable the agency 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.
The FAA is 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 transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division.

Regulatory Findings

The FAA has determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect

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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) Will not affect intrastate aviation in Alaska, and
(3) 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.