Airworthiness Directives; Airbus Airplanes, 17003-17005 [2015-07280]

Download as PDF Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules 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. Issued in Renton, Washington, on March 19, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–07172 Filed 3–30–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0679; Directorate Identifier 2013–NM–182–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 18:18 Mar 30, 2015 Jkt 235001 • 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. 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. 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. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 17003 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 onground 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 E:\FR\FM\31MRP1.SGM 31MRP1 17004 Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules well 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. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS 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 VerDate Sep<11>2014 18:18 Mar 30, 2015 Jkt 235001 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. 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: ■ PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 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: ■ 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 onetime 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, E:\FR\FM\31MRP1.SGM 31MRP1 Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules Amendment 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. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (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-116AMOC-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 VerDate Sep<11>2014 18:18 Mar 30, 2015 Jkt 235001 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. Issued in Renton, Washington, on March 24, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–07280 Filed 3–30–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0677; Directorate Identifier 2013–NM–244–AD] RIN 2120–AA64 Airworthiness Directives; Gulfstream Aerospace Corporation Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation Model GVI airplanes. This proposed AD was prompted by reports of corrosion on in-service air non-return valves. This proposed AD would require a revision to the Emergency Procedures section of the airplane flight manual (AFM). This proposed AD would also require a revision to the maintenance or inspection program, as applicable, to incorporate airworthiness limitations for SUMMARY: PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 17005 the high pressure (HP) Stage 5 air nonreturn valves. We are proposing this AD to ensure the flightcrew is provided with procedures to mitigate the risks associated with failure of the HP Stage 5 air non-return valve. Failure of the HP Stage 5 air non-return valve in the open position could result in engine instability and uncommanded in-flight shutdown. DATES: We must receive comments on this proposed AD by May 15, 2015. 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: 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Gulfstream Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, GA 31402–2206; telephone 800–810–4853; fax 912–965–3520; email pubs@gulfstream.com; Internet http:// www.gulfstream.com/product_support/ technical_pubs/pubs/index.htm. 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. 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– 0677; 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 Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Eric Potter, Aerospace Engineer, Propulsion and Services Branch, ACE–118A, Atlanta Aircraft Certification Office, FAA, 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474–5583; E:\FR\FM\31MRP1.SGM 31MRP1

Agencies

[Federal Register Volume 80, Number 61 (Tuesday, March 31, 2015)]
[Proposed Rules]
[Pages 17003-17005]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-07280]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0679; Directorate Identifier 2013-NM-182-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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.

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.

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

[[Page 17004]]

well 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.

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

0
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]

0
2. The FAA amends Sec.  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:

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,

[[Page 17005]]

Amendment 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.

    Issued in Renton, Washington, on March 24, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-07280 Filed 3-30-15; 8:45 am]
 BILLING CODE 4910-13-P