AD 2007-21-14 R1

The FAA is revising an existing airworthiness directive (AD), which applies to all Airbus Model A310 airplanes. That AD currently requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors caused by latent failures, alterations, repairs, or maintenance actions, could result in fuel tank explosions and consequent loss of the airplane.

Final rule; request for comments.

2007-21-14 R1 Airbus: Amendment 39-16061. Docket No. FAA-2009-0996; Directorate Identifier 2009-NM-156-AD.

Effective Date

(a) This airworthiness directive (AD) is effective November 12, 2009.

Affected ADs

(b) This AD revises AD 2007-21-14.

Applicability

(c) This AD applies to all Airbus Model A310-203, -204, -221, - 222, -304, -322, -324, and -325 airplanes, certificated in any category.

Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections and critical design configuration control limitations (CDCCLs). Compliance with the operator maintenance documents is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections and CDCCLs, the operator may not be able to accomplish the inspections and CDCCLs described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (j) of this AD. The request should include a description of changes to the required inspections and CDCCLs that will preserve the critical ignition source prevention feature of the affected fuel system.

Unsafe Condition

(d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors caused by latent failures, alterations, repairs, or maintenance actions, could result in fuel tank explosions and consequent loss of the airplane.

Compliance

(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Restatement of AD 2007-21-14, With No Changes

Revise Airworthiness Limitations Section (ALS) To Incorporate Fuel Maintenance and Inspection Tasks

(f) Within 3 months after November 20, 2007 (the effective date of AD 2007-21-14), revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A310 ALS Part 5--Fuel Airworthiness Limitations, dated May 31, 2006, as defined in Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007 (approved by the European Aviation Safety Agency (EASA) on July 6, 2007), Section 1, "Maintenance/Inspection Tasks.'' For all tasks identified in Section 1 of Document 95A.1930/ 05, the initial compliance times start from the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD, and the repetitive inspections must be accomplished thereafter at the intervals specified in Section 1 of Document 95A.1930/05, except as provided by paragraph (g) of this AD.

(1) November 20, 2007.

(2) The date of issuance of the original French standard airworthiness certificate or the date of issuance of the original French export certificate of airworthiness.Note 2: Airbus Operator Information Telex SE 999.0079/07, Revision 01, dated August 14, 2007, identifies the applicable sections of the Airbus A310 Airplane Maintenance Manual necessary for accomplishing the tasks specified in Section 1 of Document 95A.1930/05.

Initial Compliance Time for Task 28-18-00-03-1

(g) For Task 28-18-00-03-1 identified in Section 1 of Document 95A.1930/05, "Maintenance/Inspection Tasks,'' of Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007 (approved by the EASA on July 6, 2007): The initial compliance time is the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD. Thereafter, Task 28-18-00-03-1 must be accomplished at the repetitive interval specified in Section 1 of Document 95A.1930/05.

(1) Prior to the accumulation of 40,000 total flight hours.

(2) Within 72 months or 20,000 flight hours after November 20, 2007, whichever occurs first.

Revise ALS To Incorporate CDCCLs

(h) Within 12 months after November 20, 2007, revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A310 ALS Part 5--Fuel Airworthiness Limitations, dated May 31, 2006, as defined in Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007 (approved by the EASA on July 6, 2007), Section 2, "Critical Design Configuration Control Limitations.''

No Alternative Inspections, Inspection Intervals, or CDCCLs

(i) Except as provided by paragraph (j) of this AD: After accomplishing the actions specified in paragraphs (f) and (h) of this AD, no alternative inspections, inspection intervals, or CDCCLs may be used.

New Information

Explanation of CDCCL Requirements

Note 3: Notwithstanding any other maintenance or operational requirements, components that have been identified as airworthy or installed on the affected airplanes before the revision of the ALS, as required by paragraph (f) of this AD, do not need to be reworked in accordance with the CDCCLs. However, once the ALS has been revised, future maintenance actions on these components must be done in accordance with the CDCCLs.

Alternative Methods of Compliance (AMOCs)

(j)(1) 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. Send information to ATTN: Tom Stafford, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149.

(2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office.

Related Information

(k) EASA airworthiness directive 2007-0096 R1, dated May 2, 2007, also addresses the subject of this AD.

Material Incorporated by Reference

(l) You must use Airbus A310 ALS Part 5--Fuel Airworthiness Limitations, dated May 31, 2006; and Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007; to do the actions required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register previously approved the incorporation by reference of Airbus A310 ALS Part 5--Fuel Airworthiness Limitations, dated May 31, 2006; and Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007; on November 20, 2007 (72 FR 58499, October 16, 2007).

(2) For service information identified in this AD, contact Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +335 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; Internet http://www.airbus.com.

(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152.

(4) You may also review copies of the 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/code_of_federal_regulations/ ibr_locations.html.

Discussion

On October 5, 2007, we issued AD 2007-21-14, amendment 39-15232 (72 FR 58499, October 16, 2007). That AD applied to all Airbus Model A310 airplanes. That AD required revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems.

Critical design configuration control limitations (CDCCLs) are limitation requirements to preserve a critical ignition source prevention feature of the fuel tank system design that is necessary to prevent the occurrence of an unsafe condition. The purpose of a CDCCL is to provide instruction to retain the critical ignition source prevention feature during configuration change that may be caused by alterations, repairs, or maintenance actions. A CDCCL is not a periodic inspection.

Actions Since AD Was Issued

Since we issued that AD, we have determined that it is necessary to clarify the AD's intended effect on spare and on-airplane fuel tank system components, regarding the use of maintenance manuals and instructions for continued airworthiness.

Section 91.403(c) of the Federal Aviation Regulations (14 CFR 91.403(c) specifies the following:

No person may operate an aircraft for which a manufacturer's maintenance manual or instructions for continued airworthiness has been issued that contains an airworthiness limitation section unless the mandatory * * * procedures * * * have been complied with.

Some operators have questioned whether existing components affected by the new CDCCLs must be reworked. We did not intend for the AD to retroactively require rework of components that had been maintained using acceptable methods before the effective date of the AD. Owners and operators of the affected airplanes therefore are not required to rework affected components identified as airworthy or installed on the affected airplanes before the required revisions of the Airworthiness Limitations Section of the Instructions for Continued Airworthiness. But once the CDCCLs are incorporated into the Airworthiness Limitations Section of the Instructions for Continued Airworthiness, future maintenance actions on components must be done in accordance with those CDCCLs.

FAA's Determination and Requirements of This AD

The affected product(s) have been approved by the aviation authority of another country, and are approved for operation in the United States. 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. This new AD retains the requirements of the existing AD, and adds a new note to clarify the intended effect of the AD on spare and on-airplane fuel tank system components.

Costs of Compliance

This revision imposes no additional economic burden. The current costs for this AD are repeated for the convenience of affected operators, as follows:

This AD affects about 69 airplanes of U.S. registry. The required actions take about 2 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $11,040, or $160 per airplane.

FAA's Justification and Determination of the Effective Date

This revision merely clarifies the intended effect on spare and on- airplane fuel tank system components, and makes no substantive change to the AD's requirements. For this reason, it is found that notice and opportunity for prior public comment for this action are unnecessary, and good cause exists for making this amendment effective in less than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include "Docket No. FAA-2009-0996; Directorate Identifier 2009-NM-156-AD'' at the beginning of your comments. We 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:// www.regulations.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 theauthority 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 have 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 the regulation:

1. Is not a "significant regulatory action'' under ExecutiveOrder 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. See the ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends part 39 of the Federal Aviation Regulations (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.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by removing amendment 39-15232 (72 FR 58499, October 16, 2007) and adding the following new AD: