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Proposed Rule

Airworthiness Directives; Airbus Airplanes

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Start Preamble

AGENCY:

Federal Aviation Administration (FAA), DOT.

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

We propose to supersede Airworthiness Directive (AD) 2012-13-06, for all Airbus Model A300 series airplanes and all Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 2012-13-06 currently requires a one-time detailed inspection to determine the length of the fire shut-off valve (FSOV) bonding leads and for contact or chafing of the wires, and corrective actions if necessary. Since we issued AD 2012-13-06, a determination was made that the description of the inspection area specified in the service information was misleading; therefore, some operators might have inspected incorrect bonding leads. This proposed AD would instead require a new one-time detailed inspection of the FSOV bonding leads to ensure that the correct bonding leads are inspected, and corrective action if necessary. We are proposing this AD to detect and correct contact or chafing of wires and the bonding leads, which, if not detected, could be a source of sparks in the wing trailing edge, and could lead to an uncontrolled engine fire. May 5, 2015.

DATES:

We must receive comments on this proposed AD by May 15, 2015.

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 W12-140, 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 proposed AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 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-2015-0679; 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 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:

Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 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-2015-0679; Directorate Identifier 2013-NM-182-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

On June 21, 2012, we issued AD 2012-13-06, Amendment 39-17108 (77 FR 40485, July 10, 2012). AD 2012-13-06 requires actions intended to address an unsafe condition on all Airbus Model A300 series airplanes and all Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes).

Since we issued AD 2012-13-06, the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013-0204, dated September 6, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or “the MCAI”), to correct an unsafe condition for the specified products. The MCAI states:

During a scheduled maintenance check, one operator reported inoperative Fire Shut Off Valve (FSOV). Investigations showed damage at wire located between engine 2 hydraulic FSOV and wing rear spar, in the zones 575/675, and at bonding lead, located between wing rib 7A and rib 8 below hydraulic pressure lines.

Similar inspections on different aeroplanes have shown that one of the causes of damage is the contact between bonding lead and the harness, due to over length of the bonding lead.

This condition, if not detected and corrected, could lead to either:

—a potential explosive condition on-ground if the FSOV, that is installed in fuel vapor zone is commanded to close position, or

—a temporary uncontrolled engine fire, if combined with a fire event in the nacelle fed by an hydraulic leakage and not controlled by the fire extinguishing system.

As the affected wire is not powered during normal operation, no defect can be detected unless a test is performed on the FSOV during maintenance check.

EASA issued AD 2011-0084 [http://ad.easa.europa.eu/​blob/​easa_​ad_​2011_​0084.pdf/​AD_​2011-0084_​Superseded] which required a one-time [detailed] inspection of the wires [for contact or chafing] located between [LH/RH] engines hydraulic FSOV and wing rear spar in the zones 575/675, and the bonding lead [for length] that is located between rib 7A and rib 8 below hydraulic pressure lines, and corrective actions [repair of wires or replacement of bonding leads] depending on findings.

It appeared that the original issue of the Airbus inspection Service Bulletins (SB's) as Start Printed Page 17004well as EASA AD 2011-0084 might have caused possible misunderstandings on the exact bonding leads and wires that are required to be inspected.

For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2011-0084, which is superseded, and requires additional work on aeroplanes that have already been inspected in accordance with the instructions of the original issue of the SB's.

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-2015-0679.

Related Service Information Under 1 CFR Part 51

Airbus has issued Service Bulletin A300-24-0106, Revision 01, including Appendices 01, 02, 03, and 04, dated March 26, 2013 (for Model A300 series airplanes); and Service Bulletin A300-24-6108, Revision 01, including Appendices 01, 02, 03, and 04, dated March 26, 2013 (for Model A300-600 series airplanes. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available; see ADDRESSES for ways to access this service information.

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 these same type designs.

Costs of Compliance

We estimate that this proposed AD affects 123 airplanes of U.S. registry.

We estimate that it would take about 8 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $500 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $145,140, or $1,180 per product.

In addition, we estimate that any necessary follow-on actions would take about 1 work-hour and require parts costing $50, for a cost of $135 per product. We have no way of determining the number of products that may need these actions.

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.

Start List of Subjects

List of Subjects in 14 CFR Part 39

  • Air transportation
  • Aircraft
  • Aviation safety
  • Incorporation by reference
  • Safety
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

End Part Start Amendment Part

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

End Amendment Part Start Authority

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

End Authority
[Amended]
Start Amendment Part

2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2012-13-06, Amendment 39-17108 ( 77 FR 40485, July 10, 2012), and adding the following new AD:

End Amendment Part

Airbus: Docket No. FAA-2015-0679; Directorate Identifier 2013-NM-182-AD.

(a) Comments Due Date

We must receive comments by May 15, 2015.

(b) Affected ADs

This AD replaces AD 2012-13-06, Amendment 39-17108 (77 FR 40485, July 10, 2012).

(c) Applicability

This AD applies to the airplanes specified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all certificated models; all manufacturer serial numbers.

(1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes.

(2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-622R airplanes.

(3) Airbus Model A300 C4-605R Variant F airplanes.

(d) Subject

Air Transport Association (ATA) of America Code 24, Electrical Power.

(e) Reason

This AD was prompted by a determination that the description of the inspection area specified in the service information was misleading; therefore, some operators might have inspected incorrect bonding leads. We are issuing this AD to detect and correct contact or chafing of wires and the bonding leads, which, if not detected, could be a source of sparks in the wing trailing edge, and could lead to an uncontrolled engine fire.

(f) Compliance

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

(g) Inspection of the Fire Shut-off Valve (FSOV) Bonding Leads

At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD: Do a one-time detailed inspection to determine the length of the FSOV bonding leads, and to detect contact or chafing of the wires located on the left-hand (LH) and right-hand (RH) sides of the wing rear spar, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-24-0106, Revision 01, including Appendices 01, 02, 03, and 04, dated March 26, 2013 (for Model A300 series airplanes); or Airbus Service Bulletin A300-24-6108, Revision 01, including Appendices 01, 02, 03, and 04, dated March 26, 2013 (for Model A300-600 series airplanes); as applicable.

(1) For airplanes on which the inspection required by paragraph (g) of AD 2012-13-06, Start Printed Page 17005Amendment 39-17108 (77 FR 40485, July 10, 2012), has not been done as of the effective date of this AD: Inspect within 4,500 flight hours or 30 months after August 14, 2012 (the effective date of AD 2012-13-06), whichever occurs first.

(2) For airplanes on which the inspection required by paragraph (g) of AD 2012-13-06, Amendment 39-17108 (77 FR 40485, July 10, 2012), has been done as of the effective date of this AD: Inspect within 4,500 flight hours or 30 months after the effective date of this AD, whichever occurs first.

(h) Corrective Action for FSOV Bonding Leads

If, during the inspection required by paragraph (g) of this AD, the length of the bonding lead(s) is more than 80 millimeters (mm) (3.15 inches): Before further flight, replace the bonding lead(s) with a new bonding lead having a length equal to 80 mm ± 2 mm (3.15 inches) ± 0.08 inch, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD.

(i) Repair of the Wires of the LH and RH Sides

If, during the inspection required by paragraph (g) of this AD, any contact or chafing of the wires is found, repair the wires before further flight, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD.

(j) Parts Installation Prohibition

As of August 14, 2012 (the effective date of AD 2012-13-06, Amendment 39-17108 (77 FR 40485, July 10, 2012), no person may install any bonding lead longer than 80 mm ± 2 mm (3.15 inches) ± 0.08 inch, located between the LH/RH engine hydraulic FSOV and wing rear spar in zones 575/675 on any airplane.

(k) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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: As of the effective date of this AD, 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.

(l) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013-0204, dated September 6, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-0679.

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

Start Signature

Issued in Renton, Washington, on March 24, 2015.

Michael Kaszycki,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. 2015-07280 Filed 3-30-15; 8:45 am]

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