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Proposed Rule

Airworthiness Directives; Airbus Model A300 B4-600, A300 B4-600R, A300 C4-600R, and A300 F4-600R Series Airplanes

Document Details

Information about this document as published in the Federal Register.

Published Document

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

Start Preamble Start Printed Page 63503

AGENCY:

Federal Aviation Administration (FAA), DOT.

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed 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:

[T]he FAA has published SFAR 88 (Special Federal Aviation Regulation 88). * * *

Under this regulation, all holders of type certificates for passenger transport aircraft * * * are required to conduct a design review against explosion risks.

The replacement of some types of P-clips and improvement of the electrical bonding of the equipment in the fuel tanks are rendered mandatory by this AD.

The unsafe condition is damage to wiring in the wing, center, and trim fuel tanks, due to failed P-clips used for retaining the wiring and pipes, which could result in a possible fuel ignition source in the wing, center, or trim fuel tanks. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.

DATES:

We must receive comments on this proposed AD by December 10, 2007.

ADDRESSES:

You may send comments by any of the following methods:

  • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
  • Fax: (202) 493-2251.
  • 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 W12-40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov;​ or in person at the Docket Operations office 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 (800) 647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

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.

End Further Info End Preamble Start Supplemental Information

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-2007-0172; Directorate Identifier 2007-NM-225-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 Community, has issued EASA Airworthiness Directive 2007-0233, dated August 27, 2007 (referred to after this as “the MCAI”), to correct an unsafe condition for the specified products. The MCAI states:

[T]he FAA has published SFAR 88 (Special Federal Aviation Regulation 88). In their letters referenced 04/00/02/07/01-L296, dated March 4th, 2002 and 04/00/02/07/03-L024, dated February 3rd, 2003, the JAA (Joint Aviation Authorities) recommended the application of a similar regulation to the National Aviation Authorities (NAA).

Under this regulation, all holders of type certificates for passenger transport aircraft with either a passenger capacity of 30 or more, or a payload capacity of 7,500 pounds (3402 kg) or more, which have received their certification since January 1st, 1958, are required to conduct a design review against explosion risks.

The replacement of some types of P-clips and improvement of the electrical bonding of the equipment in the fuel tanks are rendered mandatory by this AD.

Note:

Initially, EASA AD 2006-0325, which addresses the same unsafe condition, also applied to A300-600 aircraft. The approval holder subsequently introduced additional work at revision 1 of SB (service bulletin) A300-28-6064 applicable to A300-600 aircraft. [On September 21, 2007, the FAA issued parallel AD 2007-20-04 for only Airbus Model A300 Airplanes and Model A310 Airplanes, which was published in the Federal Register (72 FR 56258, October 3, 2007).]

As a result, AD 2006-0325 has been revised to remove A300-600 aircraft from applicability, and this new AD applicable to A300-600 aircraft is issued.

The unsafe condition is damage to wiring in the wing, center, and trim fuel tanks, due to failed P-clips used for retaining the wiring and pipes, which could result in a possible fuel ignition source in the wing, center, or trim fuel tanks. The corrective action is checking the electrical bonding points of certain equipment in the center fuel tank for the presence of a blue coat and doing related investigative and corrective actions if necessary. The related investigative action is to measure the electrical resistance between the equipment and structure, if a blue coat is not present. The corrective action is Start Printed Page 63504to electrically bond the equipment, if the measured resistance is greater than 10 milliohms. The corrective action also includes installing new bonding leads and electrical bonding points on certain equipment in the left and right wing fuel tanks and center fuel tank. You may obtain further information by examining the MCAI in the AD docket.

The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled “Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements” (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (“SFAR 88,” Amendment 21-78, and subsequent Amendments 21-82 and 21-83).

Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews.

In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: Single failures, single failures in combination with a latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action.

The JAA has issued a regulation that is similar to SFAR 88. (The JAA is an associated body of the European Civil Aviation Conference (ECAC) representing the civil aviation regulatory authorities of a number of European States who have agreed to co-operate in developing and implementing common safety regulatory standards and procedures.) Under this regulation, the JAA stated that all members of the ECAC that hold type certificates for transport category airplanes are required to conduct a design review against explosion risks.

We have determined that the actions identified in this AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.

Relevant Service Information

Airbus has issued Service Bulletins A300-28-6064, Revision 01, dated April 3, 2007; A300-28-6068, dated July 20, 2005; and A300-28-6077, Revision 01, dated October 26, 2006. 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 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 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 proposed 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 proposed AD.

Costs of Compliance

Based on the service information, we estimate that this proposed AD would affect about 114 products of U.S. registry. We also estimate that it would take about 632 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Required parts would cost about $6,870 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $6,547,020, or $57,430 per product.

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); and

3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities Start Printed Page 63505under the criteria of the Regulatory Flexibility Act.

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

Start List of Subjects

List of Subjects in 14 CFR Part 39

End List of Subjects

The Proposed Amendment

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

Start Part

PART 39—AIRWORTHINESS DIRECTIVES

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

Start Authority

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

End Authority
[Amended]

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

Airbus: Docket No. FAA-2007-0172; Directorate Identifier 2007-NM-225-AD.

Comments Due Date

(a) We must receive comments by December 10, 2007.

Affected ADs

(b) None.

Applicability

(c) This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD.

(1) Airbus Model A300 B4-600 series airplanes (without trim tank), all serial numbers, certificated in any category, except airplanes on which Airbus Modifications 12226, 12365, 12490, and 12308 have been incorporated in production, or Airbus Service Bulletin A300-28-6064, Revision 01, dated April 3, 2007; and A300-28-6068, dated July 20, 2005; have been performed in service.

(2) Airbus Model A300 B4-600R, A300 C4-600R, and A300 F4-600R series airplanes (fitted with a trim tank), all serial numbers, certificated in any category, except airplanes on which Airbus Modifications 12226, 12365, 12490, 12308, 12294, and 12476 have been incorporated in production, or on which the service bulletins listed in paragraphs (c)(2)(i), (c)(2)(ii), and (c)(2)(iii) of this AD have been performed in service.

(i) Airbus Service Bulletin A300-28-6064, Revision 01, dated April 3, 2007.

(ii) Airbus Service Bulletin A300-28-6068, dated July 20, 2005.

(iii) Airbus Service Bulletin A300-28-6077, dated July 25, 2005; or A300-28-6077, Revision 01, dated October 26, 2006.

Subject

(d) Air Transport Association (ATA) of America Code 28: Fuel.

Reason

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

[T]he FAA has published SFAR 88 (Special Federal Aviation Regulation 88). In their letters referenced 04/00/02/07/01-L296, dated March 4th, 2002 and 04/00/02/07/03-L024, dated February 3rd, 2003, the JAA (Joint Aviation Authorities) recommended the application of a similar regulation to the National Aviation Authorities (NAA).

Under this regulation, all holders of type certificates for passenger transport aircraft with either a passenger capacity of 30 or more, or a payload capacity of 7,500 pounds (3402 kg) or more, which have received their certification since January 1st, 1958, are required to conduct a design review against explosion risks.

The replacement of some types of P-clips and improvement of the electrical bonding of the equipment in the fuel tanks are rendered mandatory by this AD.

Note:

Initially, EASA AD 2006-0325, which addresses the same unsafe condition, also applied to A300-600 aircraft. The approval holder subsequently introduced additional work at revision 1 of SB (service bulletin) A300-28-6064 applicable to A300-600 aircraft. [On September 21, 2007, the FAA issued parallel AD 2007-20-04 for only Airbus Model A300 Airplanes and Model A310 Airplanes, which was published in the Federal Register (72 FR 56258, October 3, 2007).]

As a result, AD 2006-0325 has been revised to remove A300-600 aircraft from applicability, and this new AD applicable to A300-600 aircraft is issued.

The unsafe condition is damage to wiring in the wing, center, and trim fuel tanks, due to failed P-clips used for retaining the wiring and pipes, which could result in a possible fuel ignition source in the wing, center, or trim fuel tanks. The corrective action is checking the electrical bonding points of certain equipment in the center fuel tank for the presence of a blue coat and doing related investigative and corrective actions if necessary. The related investigative action is to measure the electrical resistance between the equipment and structure, if a blue coat is not present. The corrective action is to electrically bond the equipment, if the measured resistance is greater than 10 milliohms. The corrective action also includes installing new bonding leads and electrical bonding points on certain equipment in the left and right wing fuel tanks and center fuel tank.

Actions and Compliance

(f) Within 40 months after the effective date of this AD, unless already done, do the following actions.

(1) Remove NSA5516-XXND or NSA5516-XXNJ type P-clips, used in the wing and center fuel tanks to retain wiring and pipes, and replace them by NSA5516-XXNF type P-clips in accordance with the instructions of Airbus Service Bulletin A300-28-6068, dated July 20, 2005.

(2) Check the electrical bonding points in the center tank and do all applicable related investigative and corrective actions, and install additional bonding leads and electrical bonding points in the wing and center fuel tanks in accordance with the instructions of Airbus Service Bulletin A300-28-6064, Revision 01, dated April 3, 2007. Do all applicable related investigative and corrective actions before further flight.

(3) For airplanes fitted with a trim tank, in addition to the actions defined in paragraphs (f)(1) and (f)(2) of this AD, install bonding leads and electrical bonding points in the trim tanks, in accordance with the instructions of Airbus Service Bulletin A300-28-6077, Revision 01, dated October 26, 2006.

(4) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A300-28-6064, dated July 28, 2005, for aircraft under configuration 05, as defined in the service bulletin, are considered acceptable for compliance with the requirements of paragraph (f)(2) of this AD.

(5) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A300-28-6077, dated July 25, 2005, for aircraft under configuration 05, as defined in the service bulletin, are considered acceptable for compliance with the requirements of paragraph (f)(3) of this AD.

FAA AD Differences

Note:

This AD differs from the MCAI and/or service information as follows: The applicability of the MCAI does not address Airbus Modification 12490. We have added this Modification number to the applicability of this AD, as requested by Airbus and coordinated with the European Aviation Safety Agency (EASA).

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, 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. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(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. Start Printed Page 63506

Related Information

(h) Refer to MCAI EASA Airworthiness Directive 2007-0233, dated August 27, 2007, and the service information listed in Table 1 of this AD, for related information.

Table 1.—Service Information

Airbus Service BulletinRevision levelDate
A300-28-606401April 3, 2007.
A300-28-6068OriginalJuly 20, 2005.
A300-28-607701October 26, 2006.
Start Signature

Issued in Renton, Washington, on November 2, 2007.

Ali Bahrami,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Part End Supplemental Information

[FR Doc. E7-21997 Filed 11-8-07; 8:45 am]

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