2016-08253. Airworthiness Directives; Airbus Airplanes

AGENCY:

Federal Aviation Administration (FAA), DOT.

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, -200, and -300 series airplanes. This proposed AD was prompted by a report of a manufacturing defect that affects the durability of affected parts in the cargo and cabin compartment. This proposed AD would require an inspection of affected structural parts in the cargo and cabin compartments to determine if proper heat-treatment has been done, and replacement if necessary. We are proposing this AD to prevent crack initiation and propagation, which could result in reduced structural integrity of the fuselage.

DATES:

We must receive comments on this proposed AD by May 27, 2016.

ADDRESSES:

You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
• Fax: [phone].
• Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this NPRM, contact Airbus SAS, Airworthiness Office-EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: [phone]; fax: [phone]; email: [e-mail]; 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.

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-2016-5460; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone [phone]) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT:

Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: [phone]; fax: [phone].

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include “Docket No. FAA-2016-5460; Directorate Identifier 2015-NM-188-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.

We will post all comments we receive, without change, to http://www.regulations.gov,, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued European Airworthiness Directive 2015-0212, dated November 4, 2015, to correct an unsafe condition for all Airbus Model A330-200 Freighter, -200, and -300 series airplanes. The MCAI states:

Airbus quality controls identified that several structural parts, intended for cargo or cabin compartment installation, were manufactured from improperly heat-treated materials. Subsequent review identified that some of those parts were installed on airplanes manufactured between November 2011 and February 2013. From February 2013, Airbus implemented measures into manufacturing processes to ensure detection and to prevent installation of such non-conforming parts.

A detailed safety assessment was accomplished to identify the possible impact of affected parts on the airplane structure. The result of this structural analysis demonstrated the capability of the affected structure to sustain static limit loads, but failed to confirm that the affected structures met the certified fatigue life.

This condition, if not detected and corrected, could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the fuselage.

To address this potentially unsafe condition, Airbus issued [Mandatory] Service Bulletin (SB) SB A330-53-3227 and SB A330-53-3228 to provide inspection instructions for affected cargo and cabin structural parts respectively.

For the reasons described above, this [EASA] AD requires a one-time Special Detailed Inspection (SDI) [eddy current inspection] to measure the electrical conductivity of affected structural parts, to identify the presence or absence of heat treatment, and, depending on findings, corrective action [replacement].

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-2016-5460.

Related Service Information Under 1 CFR Part 51

Airbus has issued the following service information:

• Airbus Mandatory Service Bulletin A330-53-3227, dated August 18, 2015. The service information describes procedures to inspect affected structural parts in the cargo compartment to determine if proper heat-treatment has been done, and replacement of parts; and
• Airbus Mandatory Service Bulletin A330-53-3228, dated August 18, 2015. The service information describes procedures to inspect affected structural parts in the cabin compartment to determine if proper heat-treatment has been done, and replacement of parts.

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.

FAA's Determination and Requirements of This Proposed AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design.

Differences Between This Proposed AD and the Service Information

Figure A-GFAAA, Sheet 01, “Inspection Flowchart,” of Airbus Mandatory Service Bulletin A330-53-3227, dated August 18, 2015; and Figure A-GFAAA, Sheet 01, “Inspection Flowchart” of Airbus Mandatory Service Bulletin A330-53-3228, dated August 18, 2015, note that if any other measured (conductivity) value is found, to check the non-destructive test (NDT) tool and perform a new measurement; and if that measured value is confirmed, contact Airbus for further instructions. This proposed AD would require that if a measured value is confirmed that is outside the measurements specified in the service information, a repair must be done using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA Design Organization Approval (DOA).

Costs of Compliance

We estimate that this proposed AD affects 20 airplanes of U.S. registry.

We also estimate that it will take about 11 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $18,700, or $935 per product.

In addition, we estimate that any necessary follow-on actions would take about 45 work-hours for a cost of $3,825 per product. We have received no definitive data that would enable us to provide cost of the parts for the on-condition actions specified in this proposed AD. We have no way of determining the number of aircraft that might need this action.

According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate.

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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:

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

The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39—AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13

[Amended]

2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2016-5460; Directorate Identifier 2015-NM-188-AD.

(a) Comments Due Date

We must receive comments by May 27, 2016.

(b) Affected ADs

None.

(c) Applicability

This AD applies to Airbus Model A330-223F and -243F airplanes; A330-201, -202, -203, -223, and -243 airplanes; A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes, certificated in any category, manufacturer serial numbers 1175, 1180, 1287 through 1475 inclusive, 1478, 1480, 1483, and 1506.

(d) Subject

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

(e) Reason

This AD was prompted by a report of a manufacturing defect (i.e. improperly heat-treated materials) that affects the durability of affected parts in the cargo and cabin compartment. We are issuing this AD to prevent crack initiation and propagation, which could result in reduced structural integrity of the fuselage.

(f) Compliance

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

(g) Inspection of Affected Structure in the Cargo Compartment

Within 72 months since first flight of the airplane, do an eddy current inspection (i.e., conductivity measurement) of affected structural parts in the cargo compartment to determine if proper heat treatment has been done as identified in, and in accordance with, the Accomplishment Instructions of Airbus Service Bulletin A330-53-3227, dated August 18, 2015.

(h) Replacement of Non-Conforming Parts in the Cargo Compartment

If, during the inspection required by paragraph (g) of this AD, an affected structural part in the cargo compartment is identified to have a measured value greater than 26 megasiemens per meter (MS/m) or greater than 44.8% International Annealed Copper Standard (IACS), before further flight, replace the affected structural part with a serviceable part, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-53-3227, dated August 18, 2015.

(i) Repair of Non-Conforming Parts in the Cargo Compartment

If, during the inspection required by paragraph (g) of this AD, an affected structural part in the cargo compartment is identified to have a measured value other than those specified in Figure A-GFAAA, Sheet 01, “Inspection Flowchart,” of Airbus Mandatory Service Bulletin A320-53-3227, dated August 18, 2015, 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).

(j) Inspection of Affected Structure in the Cabin Compartment

Within 72 months since first flight of the airplane, do an eddy current inspection of affected structural parts in the cargo compartment to determine if proper heat treatment has been done as identified in, and in accordance with, the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-53-3228, dated August 18, 2015.

(k) Replacement of Non-Conforming Parts in the Cabin Compartment

If, during the inspection required by paragraph (j) of this AD, an affected structural part in the cabin compartment is identified to have a measured value greater than 26 MS/m or greater than 44.8% IACS, before further flight, replace the affected structural part with a serviceable part, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-53-3228, dated August 18, 2015.

(l) Repair of Non-Conforming Parts in the Cargo Compartment

If, during the inspection required by paragraph (j) of this AD, an affected structural part in the cargo compartment is identified to have a measured value other than those specified in Figure A-GFAAA, Sheet 01, “Inspection Flowchart,” of Airbus Service Bulletin A320-53-3228, dated August 18, 2015, 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).

(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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: [phone]; fax: [phone]. Information may be emailed to: [e-mail]. 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.

(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 European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.

(3) Required for Compliance (RC): 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 AD 2015-0212, dated November 4, 2015, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-5460.

(2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office-EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: [phone]; fax: [phone]; email: [e-mail]; Internet: http://www.airbus.com. 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.

Issued in Renton, Washington, on March 30, 2016.

Victor Wicklund,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.