AD 2017-17-05

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 reports of cracks initiating at the upper radius of a certain frame and a determination that the current inspection procedure is not reliable in detecting certain cracking of the forward fitting of the frame. This AD requires repetitive inspections to detect cracking of the upper radius of the forward fitting of a certain frame, and related investigative actions and corrective actions if 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 adding the following new airworthiness directive (AD):

2017-17-05 Airbus: Amendment 39-18995; Docket No. FAA-2017-0520; Product Identifier 2016-NM-143-AD.

(a) Effective Date

This AD is effective September 25, 2017.

(b) Affected ADs

This AD affects AD 2007-26-14, Amendment 39-15316 (73 FR 2803, January 16, 2008) (``AD 2007-26-14'').

(c) Applicability

This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, except airplanes that have been repaired as specified in Airbus Service Bulletin A300-53-0370; or Airbus Service Bulletin A300-53- 6144, as applicable.
(1) 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, and B4-622 airplanes.
(3) Model A300 B4-605R and B4-622R airplanes.
(4) Model A300 F4-605R and F4-622R airplanes.
(5) Model A300 C4-605R Variant F airplanes.

(d) Subject

Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

This AD was prompted by reports of cracks initiating at the upper radius of frame (FR) 47 and a determination that the current inspection procedure is not reliable in detecting certain cracking of the forward fitting of FR 47. We are issuing this AD to detect and correct fatigue cracking of the FR 47 forward fitting upper radius on the left-hand and right-hand sides of the fuselage, which could propagate and result in reduced structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

Except as required by paragraph (h) of this AD: Before exceeding 10,000 flight cycles since first flight of the airplane or within 30 days after the effective date of this AD, whichever occurs later, do a special detailed inspection (SDI) for cracking of the FR 47 forward fitting upper radius on the left-hand and right-hand sides of the fuselage, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraphs (g)(1) and (g)(2) of this AD. Repeat the inspection thereafter at intervals not to exceed 4,150 flight cycles, except as required by paragraph (j) of this AD.
(1) Airbus Service Bulletin A300-53-0246, Revision 08, including Appendix 1, dated April 13, 2016.
(2) Airbus Service Bulletin A300-53-6029, Revision 12, including Appendix 1, dated April 13, 2016.

(h) Initial Inspection for Airplanes Previously Inspected

For airplanes previously inspected asspecified in the applicable Airbus service information specified in paragraphs (h)(1) through (h)(6) of this AD and on which no cracking was found: Within 4,150 flight cycles after the most recent inspection, do the inspection for cracking of the FR 47 forward fitting upper radius required by paragraph (g) of this AD.
(1) Airbus Service Bulletin A300-53-0246, Revision 06, dated October 19, 2005.
(2) Airbus Service Bulletin A300-53-0246, Revision 07, dated September 9, 2008.
(3) Airbus Service Bulletin A300-53-6029, Revision 08, dated October 19, 2005.
(4) Airbus Service Bulletin A300-53-6029, Revision 09, dated September 9, 2008.
(5) Airbus Service Bulletin A300-53-6029, Revision 10, dated July 9, 2009.
(6) Airbus Service Bulletin A300-53-6029, Revision 11, dated September 28, 2009.

(i) Inspections for Airplanes With Abnormal Load Events

For airplanes on which any crack was found during any inspection done as specified in Airbus Service Bulletin A300-53-0246 or Airbus Service Bulletin A300-53-6029, as applicable, and on which any abnormal load event, such as hard landing or flight in excessive turbulence, occurred within 3 months before the effective date of this AD or occurs on or after the effective date of this AD: Within 3 months after each event, accomplish an SDI for cracking of the FR 47 forward fitting upper radius, left-hand and right-hand sides of the fuselage, in accordance with the applicable Accomplishment Instructions of the Airbus service information specified in paragraphs (g)(1) or (g)(2) of this AD. If, during this 3-month period, another abnormal load event occurs, and if no SDI has yet been accomplished, before further flight after the second event, obtain corrective action instructions from the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA), and accomplish those instructions accordingly.

(j) Corrective Actions for Airplanes With Cracks

If, during any SDI as required by paragraph (g), (h), or (i) of this AD, any crack is found: Before further flight, do the applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraph (g)(1) or (g)(2) of this AD, and obtain additional corrective action instructions from the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA, and accomplish those instructions accordingly before further flight.

(k) Reporting

Submit a report of the findings (both positive and negative) of each SDI inspection required by paragraphs (g), (h), and (i) of this AD to Airbus Service Bulletin Reporting Online Application on Airbus World (https://w3.airbus.com/), 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 dateof 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) Terminating Action for AD 2007-26-14

Accomplishing any inspection required by paragraph (g) or (h) of this AD terminates all requirements of AD 2007-26-14 for the inspected airplane.

(m) 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

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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: 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 Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA- authorized signature.
(3) Reporting Requirements: 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 5 minutes 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.

(n) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0150, dated July 25, 2016, 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-2017-0520.
(2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425-227-1149.

(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 A300-53-0246, Revision 08, including Appendix 1, dated April 13, 2016.
(ii) Airbus Service Bulletin A300-53-6029, Revision 12, including Appendix 1, dated April 13, 2016.
(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: account.airworth-eas@airbus.com; Internet: http://www.airbus.com.
(4) You may view this service information at the FAA, Transport Standards Branch, 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.

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 May 31, 2017 (82 FR 24903) (``the NPRM''). The NPRM was prompted by reports of cracks initiating at the upper radius of frame (FR) 47 and a determination that the current inspection procedure is not reliable in detecting certain cracking of the forward fitting of FR 47. The NPRM proposed to require repetitive inspections to detect cracking of the upper radius of the forward fitting of FR 47, and related investigative actions and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking of the FR 47 forward fitting upper radius on the left-hand and right-hand sides of the fuselage, which could propagate and 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 AD 2016-0150, dated July 25, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on all. The MCAI states:

During scheduled maintenance inspections on the fuselage, cracks initiating at the upper radius of frame (FR) 47 have been reported on several aeroplanes. Similar damage was also discovered on the A300 fatigue test fuselage.
This condition, if not detected and corrected, could reduce the structural integrity of the fuselage.
Prompted by these findings, Airbus issued Service Bulletin (SB) A300-53-0246, SB A300-53-6029 and SB A300-53-9014 to provide inspection instructions and, consequently, DGAC France issued AD F- 2006-016 to require repetitive inspections and corrective action.
Since that [French] AD was issued, further investigation led to the conclusion that the current ultrasonic inspection performed in accordance with Airbus SB A300-53-0246 Revision 06, or SB A300-53- 6029 Revision 08, or SB A300-53-9014 Revision 01, as applicable, was not reliable to detect deep crack going downward.
Consequently, to ensure the crack depth is correctly measured whatever the crack direction, Airbus developed a new nondestructive testing method [eddy current]

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for this special detailed inspection (SDI) and revised the affected SBs accordingly.
For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD F-2006-016, which is superseded, but requires the accomplishment of repetitive SDI to replace the previously required ultrasonic inspections [and related investigative and corrective actions if necessary].

Related investigative actions include an ultrasonic inspection forcracking on the forward face of the forward fitting and a detailed inspection for cracking of the aft fitting around the fasteners. Corrective actions include crack repairs, and modification of the sealing fittings and sealing shims. This AD requires reporting of the inspection results to Airbus. 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-2017-0520.

Comments

We gave the public the opportunity to participate in developing this AD. 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 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 for correcting 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 has issued Airbus Service Bulletin A300-53-0246, Revision 08, including Appendix 1, dated April 13, 2016 (for Model A300 series airplanes); and Airbus Service Bulletin A300-53-6029, Revision 12, including Appendix 1, dated April 13, 2016 (for Model A300-600 series airplanes). The service information describes procedures for doing an SDI for cracking of the FR 47 forward fitting upper radius on the left- hand and right-hand sides of the fuselage, and related investigative and corrective actions. 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 will affect 132 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:

Estimated Costs ----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection................... 19 work-hours x $85 $0 $1,615 per $213,180 per
per hour = $1,615. inspection cycle. inspection cycle. Reporting.................... 1 work-hour x $85 per $0 $85 per inspection $11,220 per
hour = $85. cycle. inspection cycle. ----------------------------------------------------------------------------------------------------------------

We estimate the following costs to do any necessary related investigative and corrective actions that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these repairs:

On-Condition Costs ----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Related investigative and Corrective 21 work-hours x $85 per hour = $1,835 $3,620
actions. $1,785. ----------------------------------------------------------------------------------------------------------------

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 transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division.

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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.