Airworthiness Directives; Airbus Model A300 and A310 Airplanes; and Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes), 37512-37515 [06-5872]

Download as PDF 37512 Federal Register / Vol. 71, No. 126 / Friday, June 30, 2006 / Proposed Rules 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. Fokker Services B.V.: Docket No. FAA– 2006–25219; Directorate Identifier 2005– NM–259–AD. Regulatory Findings Unsafe Condition (d) This AD results from reports of findings of small cracks in the polyester assembly block in which the cotton escape rope is stored. A test revealed that the escape ropes had deteriorated over time, and the load capability was considerably reduced. We are issuing this AD to ensure that flightcrew members safely reach the ground after exiting the flight compartment window during an emergency evacuation. We have 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 that the 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 under 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. 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, 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 mstockstill on PROD1PC61 with PROPOSALS Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): VerDate Aug<31>2005 14:43 Jun 29, 2006 Jkt 208001 Affected ADs (b) None. Applicability (c) This AD applies to Fokker Model F27 Mark 050 and Model F.28 Mark 0070 and 0100 airplanes, certificated in any category; with escape rope assemblies in the flight compartment. 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. Replacement (f) Within 12 months after the effective date of this AD: Remove the two existing escape rope assemblies in the flight compartment and install new escape rope assemblies in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF50–25–59 (for Model F27 Mark 050 airplanes); and Fokker Service Bulletin SBF100–25–099 (for Model F.28 Mark 0070 and 0100 airplanes); both dated June 28, 2004. Repeat the removal and installation thereafter at intervals not to exceed 72 months. Alternative Methods of Compliance (AMOCs) (g)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Issued in Renton, Washington, on June 22, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–5873 Filed 6–29–06; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00006 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25221; Directorate Identifier 2006–NM–122–AD] RIN 2120–AA64 Related Information (h) Dutch airworthiness directive 2004– 159, dated December 24, 2004, also addresses the subject of this AD. 1. The authority citation for part 39 continues to read as follows: § 39.13 Comments Due Date (a) The FAA must receive comments on this AD action by July 31, 2006. DEPARTMENT OF TRANSPORTATION Fmt 4702 Sfmt 4702 Airworthiness Directives; Airbus Model A300 and A310 Airplanes; and Airbus Model A300 B4–600, B4–600R, and F4– 600R Series Airplanes, and Model C4– 605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes) Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Airbus Model A300 and A310 airplanes and A300–600 series airplanes. This proposed AD would require inspecting for discrepancies of all electrical bundles located in the leading and trailing edges of the wings, and performing corrective actions if necessary. This proposed AD results from fuel system reviews conducted by the manufacturer. We are proposing this AD to prevent an ignition source, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. We must receive comments on this proposed AD by July 31, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, DATES: E:\FR\FM\30JNP1.SGM 30JNP1 37513 Federal Register / Vol. 71, No. 126 / Friday, June 30, 2006 / Proposed Rules International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2006–25221; Directorate Identifier 2006–NM–122–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https://dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion 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 Joint Aviation Authorities (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. The European Aviation Safety Agency (EASA) notified us that an unsafe condition may exist on all Airbus Model A300 and A310 airplanes; and Airbus Model A300 B4–600, B4–600R, and F4– 600R series airplanes, and Model C4– 605R Variant F airplanes (collectively called A300–600 series airplanes). The EASA advises us of the potential for discrepancies, including but not limited to chafing, of all electrical bundles in the leading and trailing edges of the wings of these airplanes. This condition, if not corrected, could result in an ignition source, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. Relevant Service Information Airbus has issued the service bulletins listed in the table below. Airbus service bulletin, including appendix 01 A300 ...................................................................................... A310 ...................................................................................... A300–600 series ................................................................... mstockstill on PROD1PC61 with PROPOSALS Airplane model A300–24–0102 ..................................................................... A310–24–2095 ..................................................................... A300–24–6092 ..................................................................... These service bulletins describe procedures for performing detailed inspections for discrepancies of all electrical bundles located in the leading and trailing edges of the wings, and corrective actions if necessary. The VerDate Aug<31>2005 14:43 Jun 29, 2006 Jkt 208001 inspections include inspecting for the following: • Inadequate clearance between electrical wire harnesses and adjacent components or structure, including support structure, stringers, fasteners, pipes, bonding leads, or any metallic PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Date December 15, 2005. December 15, 2005. December 15, 2005. component which could create a conductive path to structure. • Evidence of chafing of electrical cable harnesses. • Discrepancies of clamps (including, but not limited to, unacceptable condition, unacceptable condition of E:\FR\FM\30JNP1.SGM 30JNP1 37514 Federal Register / Vol. 71, No. 126 / Friday, June 30, 2006 / Proposed Rules cushioning and anti-chafing devices, or evidence of chafing against electrical cable harnesses). • Discrepancies of cable ties (including, but not limited to, unacceptable condition, or evidence of chafing against electrical cable harnesses). • Discrepancies of convoluted conduits (including, but not limited to, unacceptable condition, evidence of chafing against electrical cable harnesses, and absence of drainage holes in the conduits). • Discrepancies of metallic conduits (including, but not limited to, unacceptable condition, evidence of chafing against electrical cable harnesses, and absence of or unacceptable condition of drainage holes in the conduits). Corrective actions include repairing any chafed electrical cable harnesses, replacing discrepant clamps with new clamps, repairing or replacing discrepant cable ties, installing drainage holes in convoluted or metallic conduits, and repairing any discrepant convoluted or metallic conduits. If clearance is not adequate between electrical wire harnesses and adjacent components or structure, the service bulletins specify contacting Airbus for corrective action. The service bulletins also specify to report all findings to Airbus. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The EASA mandated the service information and issued airworthiness directive 2006–0076, dated April 3, 2006, to ensure the continued airworthiness of these airplanes in the European Union. mstockstill on PROD1PC61 with PROPOSALS FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. As described in FAA Order 8100.14A, ‘‘Interim Procedures for Working with the European Community on Airworthiness Certification and Continued Airworthiness,’’ dated August 12, 2005, the EASA has kept the FAA informed of the situation described above. We have examined the EASA’s findings, evaluated all pertinent information, and determined that we need to issue an AD for products of this type design that are certificated for operation in the United States. VerDate Aug<31>2005 14:43 Jun 29, 2006 Jkt 208001 Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the Proposed AD and Service Information.’’ The proposed AD would also require sending the inspection results to Airbus. Differences Between the Proposed AD and Service Information The service bulletins specify to contact the manufacturer for instructions on how to correct inadequate clearance between electrical wire harnesses and adjacent components or structure and repair certain conditions, but this proposed AD would require correcting that condition using a method that we or the EASA (or its delegated agent) approve. In light of the type of corrective action that would be required to address the unsafe condition, and consistent with existing bilateral airworthiness agreements, we have determined that, for this proposed AD, a corrective action that we or the EASA approve would be acceptable for compliance with this proposed AD. Clarification of Inspection Terminology In this proposed AD, the ‘‘detailed visual inspection’’ specified in the EASA’s AD and the Airbus service bulletins is referred to as a ‘‘detailed inspection.’’ We have included the definition for a detailed inspection in a note in the proposed AD. Costs of Compliance This proposed AD would affect about 227 airplanes of U.S. registry. The proposed actions would take about 10 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the proposed AD for U.S. operators is $181,600, or $800 per airplane. 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 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 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 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 that the 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 under 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. 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, 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: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2006–25221; Directorate Identifier 2006–NM–122–AD. Comments Due Date (a) The FAA must receive comments on this AD action by July 31, 2006. Affected ADs (b) None. E:\FR\FM\30JNP1.SGM 30JNP1 Federal Register / Vol. 71, No. 126 / Friday, June 30, 2006 / Proposed Rules Applicability (c) This AD applies to all Airbus Model A300 and A310 airplanes; and all Airbus Model A300 B4–601, B4–603, B4–620, B4– 622, B4–605R, B4–622R, F4–605R, and F4– 622R airplanes, and A300 C4–605R Variant F airplanes; certificated in any category. Unsafe Condition (d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent an ignition source, which, in combination with flammable fuel vapors, could result in a fuel tank explosion 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. Service Bulletin Reference (f) The term ‘‘service bulletin,’’ as used in this AD, means the Accomplishment Instructions of the following service bulletins, as applicable: (1) For Model A300 airplanes: Airbus Service Bulletin A300–24–0102, including Appendix 01, dated December 15, 2005; (2) For Model A310 airplanes: Airbus Service Bulletin A310–24–2095, including Appendix 01, dated December 15, 2005; and (3) For Model A300 B4–601, B4–603, B4– 620, B4–622, B4–605R, B4–622R, F4–605R, and F4–622R airplanes, and A300 C4–605R Variant F airplanes: Airbus Service Bulletin A300–24–6092, including Appendix 01, dated December 15, 2005. days after the effective date of the AD, whichever is later: Submit a report of the findings (both positive and negative) of the inspections required by paragraph (g) of this AD to Airbus Engineering, c/o SE–E54, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. The report must include the airplane serial number or registration number, the number of flight cycles and flight hours on the airplane, the date of the inspection, the location of the defect, the conditions found, and the type of repair. Submitting Appendix 01 of the service bulletin to Airbus is acceptable for compliance with this requirement. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. 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 in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (k) EASA’s airworthiness directive 2006– 0076, dated April 3, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on June 22, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–5872 Filed 6–29–06; 8:45 am] Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ mstockstill on PROD1PC61 with PROPOSALS Inspections and Corrective Actions (g) Within 44 months after the effective date of this AD, perform detailed inspections for discrepancies of all electrical bundles located in the leading and trailing edges of the wings, and all applicable corrective actions, by doing all of the actions in the service bulletin, except as provided by paragraph (h) of this AD. All corrective actions must be done before further flight. DEPARTMENT OF TRANSPORTATION Exception to Corrective Action Instructions (h) If inadequate clearance is found between any electrical wire harness and adjacent components or structure: Before further flight, correct the inadequate clearance using a method approved by either the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Reporting (i) Within 30 days after doing the inspections required by this AD, or within 30 VerDate Aug<31>2005 14:43 Jun 29, 2006 Jkt 208001 BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25085; Directorate Identifier 2006–SW–02–AD] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, AS350D1, and AS355E Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes adopting a new airworthiness directive (AD) for the specified Eurocopter France PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 37515 (Eurocopter) model helicopters. This proposal would require replacing a certain hydraulic drive belt (drive belt). Also proposed is reducing the lubrication time interval for a certain hydraulic pump drive shaft (drive shaft). This proposal is prompted by inflight failures of the drive belt and the drive shaft. The actions specified by this proposed AD are intended to prevent inflight failure of the drive belt or drive shaft, loss of hydraulic power to the flight control system, and subsequent loss of control of the helicopter. DATES: Comments must be received on or before August 29, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically; • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590; • Fax: 202–493–2251; or • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this proposed AD from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. You may examine the comments to this proposed AD in the AD docket on the Internet at https://dms.dot.gov. FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5130, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2006–25085, Directorate Identifier 2006–SW–02–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date E:\FR\FM\30JNP1.SGM 30JNP1

Agencies

[Federal Register Volume 71, Number 126 (Friday, June 30, 2006)]
[Proposed Rules]
[Pages 37512-37515]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5872]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25221; Directorate Identifier 2006-NM-122-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 and A310 Airplanes; 
and Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, 
and Model C4-605R Variant F Airplanes (Collectively Called A300-600 
Series Airplanes)

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

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Airbus Model A300 and A310 airplanes and A300-600 series 
airplanes. This proposed AD would require inspecting for discrepancies 
of all electrical bundles located in the leading and trailing edges of 
the wings, and performing corrective actions if necessary. This 
proposed AD results from fuel system reviews conducted by the 
manufacturer. We are proposing this AD to prevent an ignition source, 
which, in combination with flammable fuel vapors, could result in a 
fuel tank explosion and consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by July 31, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer,

[[Page 37513]]

International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
25221; Directorate Identifier 2006-NM-122-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    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 Joint Aviation Authorities (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.
    The European Aviation Safety Agency (EASA) notified us that an 
unsafe condition may exist on all Airbus Model A300 and A310 airplanes; 
and Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, 
and Model C4-605R Variant F airplanes (collectively called A300-600 
series airplanes). The EASA advises us of the potential for 
discrepancies, including but not limited to chafing, of all electrical 
bundles in the leading and trailing edges of the wings of these 
airplanes. This condition, if not corrected, could result in an 
ignition source, which, in combination with flammable fuel vapors, 
could result in a fuel tank explosion and consequent loss of the 
airplane.

Relevant Service Information

    Airbus has issued the service bulletins listed in the table below.

----------------------------------------------------------------------------------------------------------------
                                             Airbus service bulletin,
              Airplane model                   including appendix 01                       Date
----------------------------------------------------------------------------------------------------------------
A300.....................................  A300-24-0102................  December 15, 2005.
A310.....................................  A310-24-2095................  December 15, 2005.
A300-600 series..........................  A300-24-6092................  December 15, 2005.
----------------------------------------------------------------------------------------------------------------

    These service bulletins describe procedures for performing detailed 
inspections for discrepancies of all electrical bundles located in the 
leading and trailing edges of the wings, and corrective actions if 
necessary. The inspections include inspecting for the following:
     Inadequate clearance between electrical wire harnesses and 
adjacent components or structure, including support structure, 
stringers, fasteners, pipes, bonding leads, or any metallic component 
which could create a conductive path to structure.
     Evidence of chafing of electrical cable harnesses.
     Discrepancies of clamps (including, but not limited to, 
unacceptable condition, unacceptable condition of

[[Page 37514]]

cushioning and anti-chafing devices, or evidence of chafing against 
electrical cable harnesses).
     Discrepancies of cable ties (including, but not limited 
to, unacceptable condition, or evidence of chafing against electrical 
cable harnesses).
     Discrepancies of convoluted conduits (including, but not 
limited to, unacceptable condition, evidence of chafing against 
electrical cable harnesses, and absence of drainage holes in the 
conduits).
     Discrepancies of metallic conduits (including, but not 
limited to, unacceptable condition, evidence of chafing against 
electrical cable harnesses, and absence of or unacceptable condition of 
drainage holes in the conduits).
    Corrective actions include repairing any chafed electrical cable 
harnesses, replacing discrepant clamps with new clamps, repairing or 
replacing discrepant cable ties, installing drainage holes in 
convoluted or metallic conduits, and repairing any discrepant 
convoluted or metallic conduits. If clearance is not adequate between 
electrical wire harnesses and adjacent components or structure, the 
service bulletins specify contacting Airbus for corrective action. The 
service bulletins also specify to report all findings to Airbus.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The EASA mandated 
the service information and issued airworthiness directive 2006-0076, 
dated April 3, 2006, to ensure the continued airworthiness of these 
airplanes in the European Union.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. As described in FAA 
Order 8100.14A, ``Interim Procedures for Working with the European 
Community on Airworthiness Certification and Continued Airworthiness,'' 
dated August 12, 2005, the EASA has kept the FAA informed of the 
situation described above. We have examined the EASA's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would require 
accomplishing the actions specified in the service information 
described previously, except as discussed under ``Differences Between 
the Proposed AD and Service Information.'' The proposed AD would also 
require sending the inspection results to Airbus.

Differences Between the Proposed AD and Service Information

    The service bulletins specify to contact the manufacturer for 
instructions on how to correct inadequate clearance between electrical 
wire harnesses and adjacent components or structure and repair certain 
conditions, but this proposed AD would require correcting that 
condition using a method that we or the EASA (or its delegated agent) 
approve. In light of the type of corrective action that would be 
required to address the unsafe condition, and consistent with existing 
bilateral airworthiness agreements, we have determined that, for this 
proposed AD, a corrective action that we or the EASA approve would be 
acceptable for compliance with this proposed AD.

Clarification of Inspection Terminology

    In this proposed AD, the ``detailed visual inspection'' specified 
in the EASA's AD and the Airbus service bulletins is referred to as a 
``detailed inspection.'' We have included the definition for a detailed 
inspection in a note in the proposed AD.

Costs of Compliance

    This proposed AD would affect about 227 airplanes of U.S. registry. 
The proposed actions would take about 10 work hours per airplane, at an 
average labor rate of $80 per work hour. Based on these figures, the 
estimated cost of the proposed AD for U.S. operators is $181,600, or 
$800 per airplane.

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 have 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 that the 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 under 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. 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, 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:

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

Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2006-25221; Directorate Identifier 2006-NM-
122-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 31, 
2006.

Affected ADs

    (b) None.

[[Page 37515]]

Applicability

    (c) This AD applies to all Airbus Model A300 and A310 airplanes; 
and all Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, 
B4-622R, F4-605R, and F4-622R airplanes, and A300 C4-605R Variant F 
airplanes; certificated in any category.

Unsafe Condition

    (d) This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD to prevent an ignition source, 
which, in combination with flammable fuel vapors, could result in a 
fuel tank explosion 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.

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of the following service bulletins, as 
applicable:
    (1) For Model A300 airplanes: Airbus Service Bulletin A300-24-
0102, including Appendix 01, dated December 15, 2005;
    (2) For Model A310 airplanes: Airbus Service Bulletin A310-24-
2095, including Appendix 01, dated December 15, 2005; and
    (3) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, and F4-622R airplanes, and A300 C4-605R Variant F 
airplanes: Airbus Service Bulletin A300-24-6092, including Appendix 
01, dated December 15, 2005.

Inspections and Corrective Actions

    (g) Within 44 months after the effective date of this AD, 
perform detailed inspections for discrepancies of all electrical 
bundles located in the leading and trailing edges of the wings, and 
all applicable corrective actions, by doing all of the actions in 
the service bulletin, except as provided by paragraph (h) of this 
AD. All corrective actions must be done before further flight.


    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Exception to Corrective Action Instructions

    (h) If inadequate clearance is found between any electrical wire 
harness and adjacent components or structure: Before further flight, 
correct the inadequate clearance using a method approved by either 
the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the European Aviation Safety Agency (EASA) (or 
its delegated agent).

Reporting

    (i) Within 30 days after doing the inspections required by this 
AD, or within 30 days after the effective date of the AD, whichever 
is later: Submit a report of the findings (both positive and 
negative) of the inspections required by paragraph (g) of this AD to 
Airbus Engineering, c/o SE-E54, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. The report must include the airplane serial 
number or registration number, the number of flight cycles and 
flight hours on the airplane, the date of the inspection, the 
location of the defect, the conditions found, and the type of 
repair. Submitting Appendix 01 of the service bulletin to Airbus is 
acceptable for compliance with this requirement. Under the 
provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), 
the Office of Management and Budget (OMB) has approved the 
information collection requirements contained in this AD and has 
assigned OMB Control Number 2120-0056.

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 in accordance with the procedures found in 14 
CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (k) EASA's airworthiness directive 2006-0076, dated April 3, 
2006, also addresses the subject of this AD.

    Issued in Renton, Washington, on June 22, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-5872 Filed 6-29-06; 8:45 am]
BILLING CODE 4910-13-P
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