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Airworthiness Directives; Airbus Model A318, A319, A320 and A321 Airplanes

Document Details

Information about this document as published in the Federal Register.

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This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

Start Preamble

AGENCY:

Federal Aviation Administration (FAA), Department of Transportation (DOT).

ACTION:

Final rule; request for comments.

SUMMARY:

We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

* * * * *

* * * updates [to the airplane maintenance manual (AMM), engine service manual (ESM), and quick engine change kit instruction manual (QECKIM)] have inadvertently introduced torque value errors for the bolts that attach the forward engine mount to the engine. * * *

* * * * *
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Application of the incorrect torque to the forward engine mount bolts during maintenance could result in failure of the forward engine mount and possible separation of the engine from the airplane and damage to the wing or loss of control of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.

DATES:

This AD becomes effective March 30, 2007.

The Director of the Federal Register approved the incorporation by reference of certain publications, listed in the AD, as of March 30, 2007.

We must receive comments on this AD by April 16, 2007.

ADDRESSES:

You may send comments by any of the following methods:

  • DOT Docket Web Site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically.
  • Fax: (202) 493-2251.
  • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001.
  • Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
  • Federal eRulemaking Portal: http://www.regulations.gov. Follow the instructions for submitting comments.

Examining the AD Docket

You may examine the AD docket on the Internet at http://dms.dot.gov;​ 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647-5227) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Tim Dulin, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2141; fax (425) 227-1149.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

Streamlined Issuance of AD

The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. This streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products.

This AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The AD contains text copied from the MCAI and for this reason might not follow our plain language principles.

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2007-0036R1, dated February 27, 2007 (referred to after this as “the MCAI”), to correct an unsafe condition for the specified products. The MCAI states:

From May 2006, the forward engine mount removal and installation procedures (AMM, ESM, QECKIM) have been updated to add removal and installation of the support assemblies.

These updates have inadvertently introduced torque value errors for the bolts that attach the forward engine mount to the engine. This condition, if not corrected, may have the following consequences:

—rupture of bolts and failure of the support assembly due to overtorqued bolts;

—reduced safe life of the secondary thrust load path due to low torque on monoball housing bolts.

Application of the incorrect torque to the forward engine mount bolts during maintenance could result in failure of the forward engine mount and possible separation of the engine from the airplane and damage to the wing or loss of control of the airplane. The MCAI requires inspection, replacement, and re-torque of the affected bolts and adjustment of the torque values. You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Airbus has issued All Operators Telex A320-71A1042, Revision 01, dated February 12, 2007. Goodrich has issued All Operators Letter CFM56-074, Revision 1, dated February 1, 2007. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This 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 issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.

Differences Between the AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.

We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the AD.

FAA's Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because application of the incorrect torque to the engine mount primary and secondary load path bolts during maintenance could result in failure of the forward engine mount and possible separation of the engine from the airplane and damage to the wing or loss of control of the airplane. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include “Docket No. FAA-2007-27360; Directorate Identifier 2007-NM-026-AD” at the beginning of your comments. Start Printed Page 12079We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments.

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

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 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 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); 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.

We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket.

Start List of Subjects

List of Subjects in 14 CFR Part 39

End List of Subjects

Adoption of the Amendment

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Accordingly, under the authority delegated to me by the Administrator, the FAA amends

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PART 39—AIRWORTHINESS DIRECTIVES

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

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

End Authority
[Amended]
Start Amendment Part

2. The FAA amends § 39.13 by adding the following new AD:

End Amendment Part

2007-06-05 Airbus: Amendment 39-14986. Docket No. FAA-2007-27360; Directorate Identifier 2007-NM-026-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective March 30, 2007.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Airbus Model A318-111 and -112; A319-111, -112, -113, -114, and -115; A320-111, -211, -212, and -214; and A321-111, -112, -211, -212, and -213 airplanes; certificated in any category; all serial numbers, which have CFM International CFM56-5A or CFM56-5B series engines installed.

Subject

(d) Powerplant.

Reason

(e) The mandatory continued airworthiness information (MCAI) states:

From May 2006, the forward engine mount removal and installation procedures (airplane maintenance manual (AMM), engine service manual (ESM), quick engine change kit instruction manual (QECKIM)) have been updated to add removal and installation of the support assemblies.

These updates have inadvertently introduced torque value errors for the bolts that attach the forward engine mount to the engine. This condition, if not corrected, may have the following consequences:

—rupture of bolts and failure of the support assembly due to overtorqued bolts;

—reduced safe life of the secondary thrust load path due to low torque on monoball housing bolts.

Application of the incorrect torque to the forward engine mount bolts during maintenance could result in failure of the forward engine mount and possible separation of the engine from the airplane and damage to the wing or loss of control of the airplane. The MCAI requires inspection, replacement, and re-torque of the affected bolts and adjustment of the torque values.

Actions and Compliance

(f) Unless already done, do the following actions.

(1) As of the effective date of this AD:

(i) Any maintenance on the engine mounts must be performed in accordance with correct instructions as identified in the Airbus All Operators Telex (AOT) A320-71A1042, Revision 01, dated February 12, 2007; or Goodrich All Operators Letter (AOL) CFM56-074, Revision 1, dated February 1, 2007; and

(ii) Any forward engine mount support assemblies fitted on an engine which is used as replacement must be fitted in accordance with correct instructions as identified in Airbus AOT A320-71A1042, Revision 01, dated February 12, 2007; or Goodrich AOL CFM56-074, Revision 1, dated February 1, 2007.

(2) For aircraft on which any forward engine mount support assembly has been installed or maintained since May 2006 using erroneous torque values given in the maintenance data identified in paragraph 1. of the Airbus AOT A320-71A1042, Revision 01, dated February 12, 2007, or where the use of correct torque values cannot be established: Within 20 days after the effective date of this AD, accomplish the actions in paragraphs (f)(2)(i), (f)(2)(ii), (f)(2)(iii), and (f)(2)(iv) of this AD, as applicable, in accordance with the instructions of Airbus AOT A320-71A1042, Revision 01, dated February 12, 2007. Aircraft on which no engine removal has been performed since aircraft delivery are not affected by this paragraph. The alternative procedure given in paragraph 4.2.3 of the AOT is acceptable, provided that the nominal torque values specified in paragraphs 4.2.1 and 4.2.2 are restored within 120 flight cycles after accomplishing paragraph 4.2.3 of the AOT.

(i) Remove and inspect the following forward engine mount bolts: 77710-5H6 (AMM item 90) and NAS2815C15H (AMM item 85).

(ii) If any bolts, 77710-5H6 (AMM item 90), are found broken during the above inspection, before further flight, replace the affected forward engine mount support assembly (AMM item 75).

(iii) Replace bolts, 77710-5H6 (AMM item 90) and NAS2815C15H (AMM item 85), with new items and torque them to the correct value.

(iv) Re-torque 77458-7H21 bolts (AMM item 95) and NAS2816C7H (AMM item 50) to the correct value.

(3) Actions done before the effective date of this AD in accordance with Airbus AOT A320-71A1042, dated February 5, 2007, are acceptable for compliance with the corresponding provisions of paragraph (f)(2) of this AD.

(4) Within 7 days after the inspection, report all findings to Airbus Customer Services, Engineering and Technical Support, Attention: Mr. J-P Pourtau SEE11; telephone +33 (0) 5 62 11 04 48; fax +33 (0) 5 61 93 36 14.

FAA AD Differences

Note:

This AD differs from the MCAI and/ or service information as follows: No differences.

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Other FAA AD Provisions

(g) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tim Dulin, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2141; fax (425) 227-1149. Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056.

Related Information

(h) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2007-0036R1, dated February 27, 2007; Airbus All Operators Telex A320-71A1042, Revision 01, dated February 12, 2007; and Goodrich All Operators Letter CFM56-074, Revision 1, dated February 1, 2007, for related information.

Material Incorporated by Reference

(i) You must use Airbus All Operators Telex A320-71A1042, Revision 01, dated February 12, 2007; or Goodrich All Operators Letter CFM56-074, Revision 1, dated February 1, 2007; as applicable; to do the actions required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

(3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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.

Start Signature

Issued in Renton, Washington, on March 7, 2007.

Ali Bahrami,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. E7-4535 Filed 3-14-07; 8:45 am]

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