2018-28079. Airworthiness Directives; Airbus SAS 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 SAS Model A330-223, A330-223F, A330-321, A330-322, and A330-323 airplanes. This proposed AD was prompted by a report of fatigue cracking in the latch beam gussets on a certain thrust reverser (T/R). This proposed AD would require a one-time special detailed inspection of certain latch beam gussets of certain T/Rs for cracks, and modifying the latch beam gussets of the T/Rs, if necessary. We are proposing this AD to address the unsafe condition on these products.

DATES:

We must receive comments on this proposed AD by February 11, 2019.

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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For the incorporation by reference (IBR) material described in the “Related IBR material under 1 CFR part 51” section in SUPPLEMENTARY INFORMATION, contact European Aviation Safety Agency (EASA), Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone [phone]; email [e-mail]; internet www.easa.europa.eu. You may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may view this IBR 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. It is also available in the AD docket on the internet at http://www.regulations.gov.

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-2018-1063; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (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 Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax [phone].

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include “Docket No. FAA-2018-1063; Product Identifier 2018-NM-160-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM 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 NPRM.

Discussion

The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018-0227, dated October 22, 2018 (“EASA AD 2018-0227”) (also referred to as the Mandatory Continuing Airworthiness Information, or “the MCAI”), to correct an unsafe condition for all Airbus SAS Model A330-223, A330-223F, A330-321, A330-322, A330-323 airplanes. The MCAI states:

A report was received of an in-service occurrence where an operator found a crack in the latch beam gussets of an affected TR [thrust reverser], between the forward (L2) and middle (L3) latches, adjacent to the aft cascade frame attachment bracket in the 6 o'clock beam. Subsequent investigation revealed that the crack surface of the latch beam gusset showed indication of high fatigue cycle, leading to development of a design modification, reinforcing the latch beam gussets. This was introduced through Airbus production mod 48539 (improvement of 6 o'clock latch beam) and Airbus issued the modification SB [Airbus Service Bulletin A330-78-3014, dated May 9, 2001] as a recommendation for in-service aeroplanes. Since these measures were introduced, a new case was reported of finding a crack beyond prediction at the latch beam gusset of an affected TR, on which the recommended modification SB had not been accomplished.

This condition, if not detected and corrected, could lead to crack propagation until part failure and potentially departure of TR cascade during TR operation, which could create runway hazards for other aeroplanes [which could result in damage to the airplane and hazards to persons or property on the ground].

To address this potential unsafe condition, Airbus issued the inspection SB [Airbus Service Bulletin A330-78-3024, dated June 28, 2018] to provide instructions for special detailed inspection (SDI) of the latch beam gussets.

For the reasons described above, this [EASA] AD requires a one-time SDI of the latch beam gussets between the forward and middle latches of the affected TR [for cracks] and, depending on findings, replacement with improved (reinforced, modified) TR latch beam gussets.

Related IBR Material Under 1 CFR Part 51

EASA AD 2018-0227 describes procedures for a one-time special detailed inspection of the latch beam gussets between the forward and middle latches of the affected T/R for cracks and modifying the latch beam gussets. 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 and it is publicly available through the EASA website.

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 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.

Explanation of Required Compliance Information

In the FAA's ongoing efforts to improve the efficiency of the AD process, the FAA worked with Airbus and EASA to develop a process to use certain EASA ADs as the primary source of information for compliance with requirements for corresponding FAA ADs. As a result, EASA AD 2018-0227 will be incorporated by reference in the FAA final rule. This proposed AD would, therefore, require compliance with the provisions specified in EASA AD 2018-0227, except for any differences identified as exceptions in the regulatory text of this proposed AD. Service information specified in EASA AD 2018-0227 that is required for compliance with EASA AD 2018-0227 will be available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-1063 after the FAA final rule is published.

Costs of Compliance

We estimate that this proposed AD affects 9 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD:

Estimated Costs for Required Actions

Labor cost	Parts cost	Cost per product	Cost on U.S. operators
12 work-hours × $85 per hour = $1,020	$0	$1,020	$9,180

We estimate the following costs to do any necessary on-condition action that would be required based on the results of any required actions. We have no way of determining the number of aircraft that might need this on-condition action:

Estimated Costs of On-Condition Actions

Labor cost	Parts cost	Cost per product
26 work-hours × $85 per hour = $2,210	$0	$2,210

According to the manufacturer, some or all 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 known 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.

This proposed 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

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 SAS: Docket No. FAA-2018-1063; Product Identifier 2018-NM-160-AD.

(a) Comments Due Date

We must receive comments by February 11, 2019.

(b) Affected ADs

None.

(c) Applicability

This AD applies to all Airbus SAS Model A330-223, A330-223F, A330-321, A330-322, and A330-323 airplanes, certificated in any category, all manufacturer serial numbers.

(d) Subject

Air Transport Association (ATA) of America Code 78, Engine exhaust.

(e) Reason

This AD was prompted by a report of fatigue cracking in the latch beam gussets on a certain thrust reverser (T/R). We are issuing this AD to address this condition, which, if not detected and corrected, could lead to crack propagation until part failure and potential departure of the T/R cascade during T/R operation, which could result in damage to the airplane and hazards to persons or property on the ground.

(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, the European Aviation Safety Agency (EASA) AD 2018-0227, dated October 22, 2018 (“EASA AD 2018-0227”).

(h) Exceptions to EASA AD 2018-0227

(1) For purposes of determining compliance with the requirements of this AD: Where EASA AD 2018-0227 refers to its effective date, this AD requires using the effective date of this AD.

(2) The “Remarks” section of EASA AD 2018-0227 does not apply to this AD.

(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)(2) of this AD. 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.

(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 2018-0227 that contain 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.

(j) Related Information

(1) For information about EASA AD 2018-0227, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone [phone]; email [e-mail]; internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https://ad.easa.europa.eu. You may view this EASA AD 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. EASA AD 2018-0227 may be found in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-1063.

(2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax [phone].

Issued in Des Moines, Washington, on December 18, 2018.

Michael Kasychi,

Acting Director, System Oversight Division, Aircraft Certification Service.