Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and A310-200 and -300 Series Airplanes, 16716-16721 [E6-4825]

Download as PDF 16716 Federal Register / Vol. 71, No. 64 / Tuesday, April 4, 2006 / Proposed Rules noxious weed, or plant pest in the State or political subdivision; (4) Specific information showing that the State or political subdivision has characteristics that make it particularly vulnerable to the biological control organism, noxious weed, or plant pest, such as unique plants, diversity of flora, historical concerns, or any other special basis for the request for additional restrictions or prohibitions; and (5) Information detailing the proposed additional prohibitions or restrictions and scientific data demonstrating that the proposed additional prohibitions or restrictions are necessary and adequate, and that there is no less drastic action that is feasible and that would be adequate, to prevent the introduction or spread of the biological control organism, noxious weed, or plant pest in the State or political subdivision. (b) All special need requests must be submitted to [Address to be added in final rule]. cchase on PROD1PC60 with PROPOSALS § 301.1–3 Action on special need requests. (a) Upon receipt of a complete special need request submitted in accordance with § 301.1–2, APHIS will publish a notice in the Federal Register to inform the public of the special need request and to make the request and its supporting information available for review and comment for at least 60 days. (b) Following the close of the comment period, APHIS will publish another notice announcing the Administrator’s decision to either grant or deny the special need request. The Administrator’s determination will be based upon the evaluation of the information submitted by the State or political subdivision of a State in support of its request and would take into account any comments received. (1) If the Administrator grants the special need request, the State or political subdivision of a State will be authorized to impose only the specific prohibitions or restrictions identified in the request and approved by APHIS. APHIS will coordinate with the State, or with the State on behalf of the political subdivision of the State, to ensure that the additional prohibitions or restrictions are in accord with the special need exception granted by the Administrator. (2) If the Administrator denies the special need request, the State or political subdivision of a State will be notified in writing of the reason for the denial and may submit any additional information the State or political subdivision of a State may have in order to request a reconsideration. VerDate Aug<31>2005 17:58 Apr 03, 2006 Jkt 208001 (c) If the Administrator determines that there is a need for the withdrawal of a special need exception, the reasons for the withdrawal would be communicated to the State or to the political subdivision of the State and APHIS will publish a notice in the Federal Register to inform the public of the withdrawal of the special need exception and to make the information supporting the withdrawal available for review and comment for at least 60 days. Reasons for withdrawal of approval of a special need exception may include, but are not limited to, the availability of new scientific data or changes in APHIS regulations. Following the close of the comment period, APHIS will publish another notice announcing the Administrator’s decision to either withdraw or uphold the special need exception. The Administrator’s determination will be based upon the evaluation of the information submitted in support of the withdrawal and would take into account any comments received. Done in Washington, DC, this 29th day of March 2006. Jeremy Stump, Acting Under Secretary for Marketing and Regulatory Programs. [FR Doc. E6–4840 Filed 4–3–06; 8:45 am] BILLING CODE 3410–34–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24289; Directorate Identifier 2005–NM–186–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series Airplanes; Model A300 B4–600, B4–600R, and F4– 600R Series Airplanes, and Model A300 C4–605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes); and A310–200 and –300 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 airplanes identified above. This proposed AD would require improving the routing of certain electrical wire bundles in certain airplane zones, as applicable to the airplane model. This proposed AD results from fuel system PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 reviews conducted by the manufacturer. We are proposing this AD 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. DATES: We must receive comments on this proposed AD by May 4, 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: Thomas Stafford, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; 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–2006–24289; Directorate Identifier 2005–NM–186–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 E:\FR\FM\04APP1.SGM 04APP1 Federal Register / Vol. 71, No. 64 / Tuesday, April 4, 2006 / Proposed Rules 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’’ (67 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 another 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 16717 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. ´ ´ The Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition may exist on certain Airbus Model A300 B2 and A300 B4, A300–600, A310–200, and A310–300 series airplanes. The DGAC recommends improving the routing of certain electrical wire bundles in certain airplane zones to minimize the risk of explosion. We have determined that the actions identified in this AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. Relevant Service Information Airbus has issued the service bulletins identified below. These service bulletins describe procedures for six different actions related to improving the routing of certain electrical wire bundles in certain airplane zones, as applicable to the airplane model. Each action is described in detail after the table. AIRBUS SERVICE BULLETINS Applicable to model— 2 .................................. Described in service bulletin— A300 B2 and A300 B4 series airplanes. A300–600 series airplanes .. Action A300–28–0057, Revision 02, dated January 8, 2001. A300–28–6018, Revision 1, dated September 15, 1988. A300–28–0070, Revision 01, dated March 18, 1999. A300–28–6048, dated September 19, 1996. A300 B2 and A300 B4 series airplanes. A300–600 series airplanes .. cchase on PROD1PC60 with PROPOSALS A310–200 and –300 Series Airplanes. VerDate Aug<31>2005 17:58 Apr 03, 2006 Jkt 208001 PO 00000 Prior or concurrent action— A310–28–2112, dated September 19, 1996. Frm 00007 Fmt 4702 Sfmt 4702 None. None. None. Do a visual inspection for damage (chafing and burn marks) of the protective conduits behind specified access doors, and replace or repair any damaged wires, in accordance with Airbus Service Bulletin A300–28– 6010, Revision 1, dated September 17, 1986. Do a visual inspection for damage (chafing and burn marks) of the protective conduits behind specified access doors, and replace or repair any damaged wires, in accordance with Airbus Service Bulletin A310–28– 2008, Revision 2, dated May 14, 1990. E:\FR\FM\04APP1.SGM 04APP1 16718 Federal Register / Vol. 71, No. 64 / Tuesday, April 4, 2006 / Proposed Rules AIRBUS SERVICE BULLETINS—Continued Action Described in service bulletin— Applicable to model— 3 .................................. A300 B2 and A300 B4 series airplanes. A300–24–0085, Revision 06, dated October 13, 2005. A300–600 series airplanes .. A300–24–6043, Revision 06, dated October 13, 2005. 4 .................................. A300–600 series airplanes .. 5 .................................. A300–600 series airplanes .. 6 .................................. A310–200 and –300 Series Airplanes. A300 B2 and A300 B4 series airplanes. A300–600 series airplanes .. A300–28–6056, dated February 18, 1998. A300–24–6004, Revision 03, dated June 30, 1998. A310–24–2009, Revision 03, dated June 30, 1998. A300–24–0100, dated April 7, 2005. A300–24–6084, Revision 01, dated June 28, 2005. A310–24–2091, dated March 4, 2005. cchase on PROD1PC60 with PROPOSALS A310–200 and –300 Series Airplanes. Action 1—Install a heat-shrinkable sleeve along the complete length of the electrical supply bundle of the fuel pumps. These electrical supply bundles are located in metallic protective conduits in zones 571 and 671. Action 2—Install a heat-shrinkable sleeve along the complete length of the electrical supply bundle of the fuel pumps. These electrical supply bundles are located in metallic protective conduits in zones 575 and 675. Action 3—Modify the retaining and protection system for the electrical bundles located at the wing-to-fuselage junctions, under the flap control screw jack. The modification involves installing a modified blanking plate and its related hardware, inspecting the bundles for damaged wires, repairing the wires if necessary, installing protective tape, and adding clamping to the bundles in order to improve their fastening capability. For some airplane models, Action 5 or Action 6 is necessary before or concurrently with this action. Action 4—Modify the electrical wiring of routes 1P and 2P (along the top panel of the shroud box and the rear spars of the wings) by extending the protective conduits up to the next support, and replace the two existing clamps on this support with new improved clamps. VerDate Aug<31>2005 17:58 Apr 03, 2006 Jkt 208001 Prior or concurrent action— Do repetitive inspections of the wire looms on the wing trailing edge for improperly held wires in the clamps, repair any damaged wires, restore the electrical bundles to good condition, and replace the affected nylon clamps with metallic clamps that have white silicone lining, in accordance with Airbus Service Bulletin A300–24–0073, Revision 04, dated June 30, 1998. Do repetitive inspections of the wire looms on the wing trailing edge for improperly held wires in the clamps, repair any damaged wires, restore the electrical bundles to good condition, and replace the affected nylon clamps with metallic clamps that have white silicone lining, in accordance with Airbus Service Bulletin A300–24–6004, Revision 03, dated June 30, 1998. None. None. None. None. None. None. Action 5—Do repetitive inspections of the wire looms on the wing trailing edge for improperly held wires in the clamps, repair any damaged wires, restore the electrical bundles to good condition, and replace the affected nylon clamps with metallic clamps that have white silicone lining. Action 6—Replace the nylon clamps of the electrical routes in the hydraulic compartment and in the shroud box with new metallic clamps that have white silicone lining (for Model A310– 200 and –300 series airplanes); or replace the nylon clamps and change the location of routes 1P and 2P to improve the retention of the wiring loom (for all other affected models). Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DGAC mandated the service information and issued French airworthiness directive F–2005–112 R1, dated September 14, 2005, to ensure the continued airworthiness of these airplanes in France. 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 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. We have examined the DGAC’s findings, evaluated all pertinent information, and determined that we need to issue an AD for airplanes 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. Clarification of Inspection Terminology In this proposed AD, the ‘‘inspection’’ specified in Airbus Service Bulletins A300–24–0073, A300–24–0085, A300– 24–6004, A300–24–6043, and A310–24– 2009; and the ‘‘visual inspection’’ specified in Airbus Service Bulletin A310–28–2008; are referred to as a ‘‘general visual inspection.’’ We have included the definition for a general visual inspection in a note in the proposed AD. Costs of Compliance This proposed AD would affect about 169 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this proposed AD. The average labor rate is $80 per work hour. E:\FR\FM\04APP1.SGM 04APP1 16719 Federal Register / Vol. 71, No. 64 / Tuesday, April 4, 2006 / Proposed Rules ESTIMATED COSTS For airplanes on which this action is required— Work hours Parts Cost per airplane Action 1, Install heat-shrinkable wrap (zones 571 and 671) ................................ Action 2, Install heat-shrinkable wrap (zones 575 and 675) ................................ Action 3, Modify the retaining and protection system .......................................... Action 4, Modify the electrical wiring of routes 1P and 2P .................................. Action 5, Inspect the wire looms on the wing trailing edge ................................. Action 6, Replace the nylon clamps of the electrical routes in the hydraulic compartment and in the shroud box. 10 .......................... 16 to 37 ................. 4 to 16 ................... 2 ............................ 8 ............................ 44 to 98 ................. Operator Supplied $1,533 to $1,790 ... $836 to $1,056 ...... $720 ...................... Operator Supplied $100 to $5,700 ...... $800. $2,813 to $4,750. $1,156 to $2,336. $880. $640. $3.620 to $13,540. Based on these figures, the estimated cost of the proposed AD for U.S. operators is up to $3,877,874, or up to $22,946 per airplane. The following table provides the estimated costs for U.S. operators to comply with the applicable prior or concurrent requirements in this proposed AD. ESTIMATED COSTS—PRIOR OR CONCURRENT REQUIREMENTS Action— Work hours Parts Inspect the wire looms on the wing trailing edge for improperly held wires, in accordance with Airbus Service Bulletin A300–24–6004. Inspect for damage of the protective conduits behind specified access doors in accordance with Airbus Service Bulletin A300–28–6010 or A310–28–2008, as applicable. Inspect the wire looms on the wing trailing edge for improperly held wires in accordance with Airbus Service Bulletin A300–24–0073. 8 ............................ None ...................... $640. 4 to 7 ..................... None ...................... $320 to $560. 8 ............................ None ...................... $640. 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. cchase on PROD1PC60 with PROPOSALS 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: VerDate Aug<31>2005 17:58 Apr 03, 2006 Jkt 208001 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): PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Cost per airplane Airbus: Docket No. FAA–2006–24289; Directorate Identifier 2005–NM–186–AD. Comments Due Date (a) The FAA must receive comments on this AD action by May 4, 2006. Affected ADs (b) None. Applicability (c) This AD applies to all Airbus Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4– 2C, B4–103, and B4–203 airplanes; Model A300 B4–601, B4–603, B4–620, B4–622, B4– 605R, B4–622R, F4–605R, F4–622R, and Model C4–605R Variant F airplanes; and A310–203, –204, –221, –222, –304, –322, –324, and –325 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 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. 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. Action 1—Install Heat-Shrinkable Sleeve, Zones 571 and 671 (f) For all airplanes identified in paragraphs (f)(1) and (f)(2) of this AD: Within 26 months after the effective date of this AD, install a heat-shrinkable sleeve along the complete length of the electrical supply bundles for the fuel pumps. These electrical E:\FR\FM\04APP1.SGM 04APP1 16720 Federal Register / Vol. 71, No. 64 / Tuesday, April 4, 2006 / Proposed Rules cchase on PROD1PC60 with PROPOSALS supply bundles are located in metallic protective conduits in zones 571 and 671. (1) For Model A300 B2–1A, B2–1C, B2K– 3C, B2–203, B4–2C, B4–103, and B4–203 airplanes: Do the action specified in paragraph (f) of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–28–0057, Revision 02, dated January 8, 2001. (2) For Model A300 B4–601, B4–603, B4– 620, B4–622, A300 B4–605R, B4–622R, F4– 605R, F4–622R, and A300 C4–605R Variant F airplanes; except those on which Airbus Modification 6803 has been done: Do the action specified in paragraph (f) of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 28–6018, Revision 1, dated September 15, 1988. Action 2—Install Heat-Shrinkable Sleeve, Zones 575 and 675 (g) For all airplanes identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Within 26 months after the effective date of this AD, install a heat-shrinkable sleeve along the complete length of the electrical supply bundles for the fuel pumps. These electrical supply bundles are located in metallic protective conduits in zones 575 and 675. For airplanes identified in paragraphs (g)(2) and (g)(3) of this AD: Prior to or concurrently with this installation, do a general visual inspection for damage of the protective conduits behind specified access doors, and do any applicable corrective action before further flight; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–28–6010, Revision 1, dated September 17, 1986; or Airbus Service Bulletin A310–28–2008, Revision 2, dated May 14, 1990; as applicable. (1) For Model A300 B2–1A, B2–1C, B2K– 3C, B2–203, B4–2C, B4–103, and B4–203 airplanes: Do the actions specified in paragraph (g) of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–28–0070, Revision 01, dated March 18, 1999. (2) For Model A300 B4–601, B4–603, B4– 620, B4–622, A300 B4–605R, B4–622R, F4– 605R, F4–622R, and A300 C4–605R Variant F airplanes; except those on which Airbus Modification 10505 has been done: Do the actions specified in paragraph (g) of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 28–6048, dated September 19, 1996. (3) For Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes, except those on which Airbus Modification 10505 has been done: Do the actions specified in paragraph (g) of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310–38–2112, dated September 19, 1996. Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally VerDate Aug<31>2005 17:58 Apr 03, 2006 Jkt 208001 available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ Action 3—Modify the Retaining and Protection System (h) For all airplanes identified in paragraphs (h)(1), and (h)(2) of this AD: Within 26 months after the effective date of this AD, modify the retaining and protection system for the electrical bundles located at the wing-to-fuselage junction, under the flap control screw jack. Prior to or concurrently with this action for airplanes identified in paragraphs (h)(1) and (h)(2) of this AD: Do a general visual inspection for improperly held wires of the wire looms on the wing trailing edge, restore the electrical bundles to good condition, and replace the affected nylon clamps with metallic clamps that have white silicone lining; and do any applicable corrective action before further flight; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 24–0073, Revision 04, dated June 30, 1998; or Airbus Service Bulletin A300–24–6004, Revision 03, dated June 30, 1998; as applicable. (1) For Model A300 B2–1A, B2–1C, B2K– 3C, B2–203, B4–2C, B4–103, and B4–203 airplanes: Do the actions specified in paragraph (h) of this AD in accordance with the Accomplishment Instructions Airbus Service Bulletin A300–24–0085, Revision 06, dated October 13, 2005. (2) For Model A300 B4–601, B4–603, B4– 620, B4–622, A300 B4–605R, B4–622R, F4– 605R, F4–622R, and A300 C4–605R Variant F airplanes, except those on which Airbus Modification 11276 has been done: Do the action specified in paragraph (h) of this AD in accordance with the Accomplishment Instructions Airbus Service Bulletin A300– 24–6043, Revision 06, dated October 13, 2005. Action 4—Modify the Electrical Wiring of Routes 1P and 2P (i) For Model A300 B4–601, B4–603, B4– 620, B4–622, A300 B4–605R, B4–622R, F4– 605R, F4–622R, and A300 C4–605R Variant F airplanes; except those on which Airbus Modification 11741 has been done: Within 26 months after the effective date of this AD, modify the electrical wiring of routes 1P and 2P (along the top panel of the shroud box and the rear spars of the wings) by extending the protective conduits up to the next support, and replace the two existing clamps on this support with new improved clamps. Do all actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–28–6056, dated February 18, 1998. Action 5—Inspect the Wire Looms (j) For all airplanes identified in paragraphs (j)(1) and (j)(2) of this AD: Within 24 months after the effective date of this AD, do a general visual inspection of the wire looms on the wing trailing edge for improperly held wires in the clamps, restore the electrical bundles to good condition, and PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 replace the affected nylon clamps with metallic clamps that have an elastometer lining. Do any applicable corrective action before further flight. Repeat the inspection thereafter at intervals not to exceed 24 months until all clamps have been replaced. (1) For Model A300 B4–601, B4–603, B4– 620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and A300 C4–605R Variant F airplanes; except those on which Airbus Modification 6478 has been done: Do the actions specified in paragraph (j) of this AD in accordance with the Accomplishment Instructions Airbus Service Bulletin A300– 24–6004, Revision 03, dated June 30, 1998. (2) For Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes, except those on which Airbus Modification 478 has been done: Do the actions specified in paragraph (j) of this AD in accordance with the Accomplishment Instructions Airbus Service Bulletin A310–24–2009, Revision 03, dated June 30, 1998. Action 6—Improve the Quality of the Electrical Routes (k) For all airplanes identified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD: Within 26 months after the effective date of this AD, replace the nylon clamps of the electrical routes in the hydraulic compartment and in the shroud box with new metallic clamps that have white silicone lining (for airplanes identified in paragraph (k)(1) of this AD); or replace the nylon clamps and change the location of routes 1P and 2P to improve the retention of the wiring loom (for airplanes identified in paragraphs (k)(2) and (k)(3) of this AD). (1) For Model A300 B2–1A, B2–1C, B2K– 3C, B2–203, B4–2C, B4–103, and B4–203 airplanes; except those on which Airbus Modification 11763 has been done: Do the action specified in paragraph (k) of this AD in accordance with the Accomplishment Instructions Airbus Service Bulletin A300– 24–0100, dated April 7, 2005. (2) For Model A300 B4–601, B4–603, B4– 620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and A300 C4–605R Variant F airplanes; except those on which Airbus Modifications 11763 and 12995 have been done: Do the action specified in paragraph (k) of this AD in accordance with the Accomplishment Instructions Airbus Service Bulletin A300–24–6084, Revision 01, dated June 28, 2005. (3) For Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes, except those on which Airbus Modification 11763 has been done: Do the action specified in paragraph (k) of this AD in accordance with the Accomplishment Instructions as identified in Airbus Service Bulletin A310– 24–2091, dated March 4, 2005. Parts Installation (l) After the effective date of this AD, no person may install on any airplane plate assemblies with part numbers A5351088000000 or A5351088000100 unless they have been modified in accordance with paragraph (h) of this AD. E:\FR\FM\04APP1.SGM 04APP1 Federal Register / Vol. 71, No. 64 / Tuesday, April 4, 2006 / Proposed Rules Actions Accomplished According to Previous Revisions of Service Bulletins (m) Actions done before the effective date of this AD in accordance with the service 16721 bulletins identified in Table 1 of this AD are acceptable for compliance with the corresponding requirement in this AD. TABLE 1.—PREVIOUS REVISIONS OF SERVICE BULLETINS Airbus service bulletin Revision level Date A300–28–0070 ................................................... A300–24–0073 ................................................... A300–24–0085 ................................................... A300–24–0085 ................................................... A300–24–0085 ................................................... A300–24–0085 ................................................... A300–28–057 ..................................................... A300–24–073 ..................................................... A300–24–073 ..................................................... A300–24–073 ..................................................... A300–24–6004 ................................................... A300–24–6004 ................................................... A300–28–6018 ................................................... A300–24–6043 ................................................... A300–24–6043 ................................................... A300–24–6043 ................................................... A300–24–6043 ................................................... A300–24–6043 ................................................... A300–24–6043 ................................................... A300–24–6084 ................................................... A310–24–2009 ................................................... A310–24–2009 ................................................... A310–24–2009 ................................................... Original ............................................................. 3 ....................................................................... Original ............................................................. 03 ..................................................................... 04 ..................................................................... 05 ..................................................................... 1 ....................................................................... Original ............................................................. 1 ....................................................................... 2 ....................................................................... 1 ....................................................................... 2 ....................................................................... Original ............................................................. Original ............................................................. 01 ..................................................................... 02 ..................................................................... 03 ..................................................................... 04 ..................................................................... 05 ..................................................................... Original ............................................................. Original ............................................................. 1 ....................................................................... 2 ....................................................................... Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (n)(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. Federal Aviation Administration Related Information (o) French airworthiness directive F–2005– 112 R1, dated September 14, 2005, also addresses the subject of this AD. Issued in Renton, Washington, on March 24, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–4825 Filed 4–3–06; 8:45 am] cchase on PROD1PC60 with PROPOSALS BILLING CODE 4910–13–P VerDate Aug<31>2005 17:58 Apr 03, 2006 Jkt 208001 14 CFR Part 39 [Docket No. FAA–2005–20689; Directorate Identifier 2004–NM–197–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 757 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: SUMMARY: The FAA is revising an earlier proposed airworthiness directive (AD) for certain Boeing Model 757 airplanes. The original NPRM would have required, for certain airplanes, reworking the spar bonding path and reapplying sealant; and, for certain other airplanes, testing the electrical bond between the engine fuel feed hose and the wing front spar and, if applicable, reworking the spar bonding path and reapplying sealant. The original NPRM also would have required, for all airplanes, an inspection to ensure the electrical bonding jumper is installed between the engine fuel feed tube and the adjacent wing station. The original NPRM resulted from fuel system PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 September 19, 1996. February 24, 1995. December 12, 1994. January 17, 1996. July 23, 1996. March 6, 2001. September 15, 1988. June 9, 1986. January 28, 1988. September 10, 1990. January 28, 1988. February 24, 1995. June 21, 1988. December 12, 1994. February 7, 1995. May 10, 1995. January 17, 1996. March 6, 2001. August 30, 2001. March 4, 2005. May 31, 1985. January 28, 1988. February 24, 1995. reviews conducted by the manufacturer. This action revises the original NPRM by requiring operators that may have installed an incorrect O-ring to install the correct part and do a re-test. We are proposing this supplemental NPRM to prevent arcing or sparking at the interface between the bulkhead fittings of the engine fuel feed tube and the front spar during a lightning strike, which could provide a possible ignition source for the fuel vapor inside the fuel tank and result in a fuel tank explosion. DATES: We must receive comments on this supplemental NPRM by May 1, 2006. ADDRESSES: Use one of the following addresses to submit comments on this supplemental NPRM. • 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. E:\FR\FM\04APP1.SGM 04APP1

Agencies

[Federal Register Volume 71, Number 64 (Tuesday, April 4, 2006)]
[Proposed Rules]
[Pages 16716-16721]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-4825]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24289; Directorate Identifier 2005-NM-186-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series
Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes,
and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-
600 Series Airplanes); and A310-200 and -300 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 airplanes identified above. This proposed AD would
require improving the routing of certain electrical wire bundles in
certain airplane zones, as applicable to the airplane model. This
proposed AD results from fuel system reviews conducted by the
manufacturer. We are proposing this AD 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.

DATES: We must receive comments on this proposed AD by May 4, 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: Thomas Stafford, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; 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-
24289; Directorate Identifier 2005-NM-186-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

[[Page 16717]]

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''
(67 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 another 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.
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified us that an
unsafe condition may exist on certain Airbus Model A300 B2 and A300 B4,
A300-600, A310-200, and A310-300 series airplanes. The DGAC recommends
improving the routing of certain electrical wire bundles in certain
airplane zones to minimize the risk of explosion. We have determined
that the actions identified in this AD are necessary to reduce the
potential of ignition sources inside fuel tanks, which, in combination
with flammable fuel vapors, could result in fuel tank explosions and
consequent loss of the airplane.

Relevant Service Information

Airbus has issued the service bulletins identified below. These
service bulletins describe procedures for six different actions related
to improving the routing of certain electrical wire bundles in certain
airplane zones, as applicable to the airplane model. Each action is
described in detail after the table.

Airbus Service Bulletins
----------------------------------------------------------------------------------------------------------------
Described in service Prior or concurrent action--
Action Applicable to model-- bulletin--
----------------------------------------------------------------------------------------------------------------
A300 B2 and A300 B4 A300-28-0057, Revision None.
series airplanes. 02, dated January 8,
2001.
A300-600 series A300-28-6018, Revision None.
airplanes. 1, dated September
15, 1988.
2.................................. A300 B2 and A300 B4 A300-28-0070, Revision None.
series airplanes. 01, dated March 18,
1999.
A300-600 series A300-28-6048, dated Do a visual inspection for
airplanes. September 19, 1996. damage (chafing and burn
marks) of the protective
conduits behind specified
access doors, and replace
or repair any damaged
wires, in accordance with
Airbus Service Bulletin
A300-28-6010, Revision 1,
dated September 17, 1986.
A310-200 and -300 A310-28-2112, dated Do a visual inspection for
Series Airplanes. September 19, 1996. damage (chafing and burn
marks) of the protective
conduits behind specified
access doors, and replace
or repair any damaged
wires, in accordance with
Airbus Service Bulletin
A310-28-2008, Revision 2,
dated May 14, 1990.

[[Page 16718]]

3.................................. A300 B2 and A300 B4 A300-24-0085, Revision Do repetitive inspections
series airplanes. 06, dated October 13, of the wire looms on the
2005. wing trailing edge for
improperly held wires in
the clamps, repair any
damaged wires, restore the
electrical bundles to good
condition, and replace the
affected nylon clamps with
metallic clamps that have
white silicone lining, in
accordance with Airbus
Service Bulletin A300-24-
0073, Revision 04, dated
June 30, 1998.
A300-600 series A300-24-6043, Revision Do repetitive inspections
airplanes. 06, dated October 13, of the wire looms on the
2005. wing trailing edge for
improperly held wires in
the clamps, repair any
damaged wires, restore the
electrical bundles to good
condition, and replace the
affected nylon clamps with
metallic clamps that have
white silicone lining, in
accordance with Airbus
Service Bulletin A300-24-
6004, Revision 03, dated
June 30, 1998.
4.................................. A300-600 series A300-28-6056, dated None.
airplanes. February 18, 1998.
5.................................. A300-600 series A300-24-6004, Revision None.
airplanes. 03, dated June 30,
1998.
A310-200 and -300 A310-24-2009, Revision None.
Series Airplanes. 03, dated June 30,
1998.
6.................................. A300 B2 and A300 B4 A300-24-0100, dated None.
series airplanes. April 7, 2005.
A300-600 series A300-24-6084, Revision None.
airplanes. 01, dated June 28,
2005.
A310-200 and -300 A310-24-2091, dated None.
Series Airplanes. March 4, 2005.
----------------------------------------------------------------------------------------------------------------

Action 1--Install a heat-shrinkable sleeve along the complete
length of the electrical supply bundle of the fuel pumps. These
electrical supply bundles are located in metallic protective conduits
in zones 571 and 671.
Action 2--Install a heat-shrinkable sleeve along the complete
length of the electrical supply bundle of the fuel pumps. These
electrical supply bundles are located in metallic protective conduits
in zones 575 and 675.
Action 3--Modify the retaining and protection system for the
electrical bundles located at the wing-to-fuselage junctions, under the
flap control screw jack. The modification involves installing a
modified blanking plate and its related hardware, inspecting the
bundles for damaged wires, repairing the wires if necessary, installing
protective tape, and adding clamping to the bundles in order to improve
their fastening capability. For some airplane models, Action 5 or
Action 6 is necessary before or concurrently with this action.
Action 4--Modify the electrical wiring of routes 1P and 2P (along
the top panel of the shroud box and the rear spars of the wings) by
extending the protective conduits up to the next support, and replace
the two existing clamps on this support with new improved clamps.
Action 5--Do repetitive inspections of the wire looms on the wing
trailing edge for improperly held wires in the clamps, repair any
damaged wires, restore the electrical bundles to good condition, and
replace the affected nylon clamps with metallic clamps that have white
silicone lining.
Action 6--Replace the nylon clamps of the electrical routes in the
hydraulic compartment and in the shroud box with new metallic clamps
that have white silicone lining (for Model A310-200 and -300 series
airplanes); or replace the nylon clamps and change the location of
routes 1P and 2P to improve the retention of the wiring loom (for all
other affected models).
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The DGAC mandated
the service information and issued French airworthiness directive F-
2005-112 R1, dated September 14, 2005, to ensure the continued
airworthiness of these airplanes in France.

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. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for airplanes 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.

Clarification of Inspection Terminology

In this proposed AD, the ``inspection'' specified in Airbus Service
Bulletins A300-24-0073, A300-24-0085, A300-24-6004, A300-24-6043, and
A310-24-2009; and the ``visual inspection'' specified in Airbus Service
Bulletin A310-28-2008; are referred to as a ``general visual
inspection.'' We have included the definition for a general visual
inspection in a note in the proposed AD.

Costs of Compliance

This proposed AD would affect about 169 airplanes of U.S. registry.
The following table provides the estimated costs for U.S. operators to
comply with this proposed AD. The average labor rate is $80 per work
hour.

[[Page 16719]]

Estimated Costs
----------------------------------------------------------------------------------------------------------------
For airplanes on which this action is
required-- Work hours Parts Cost per airplane
----------------------------------------------------------------------------------------------------------------
Action 1, Install heat-shrinkable 10..................... Operator Supplied...... $800.
wrap (zones 571 and 671).
Action 2, Install heat-shrinkable 16 to 37............... $1,533 to $1,790....... $2,813 to $4,750.
wrap (zones 575 and 675).
Action 3, Modify the retaining and 4 to 16................ $836 to $1,056......... $1,156 to $2,336.
protection system.
Action 4, Modify the electrical 2...................... $720................... $880.
wiring of routes 1P and 2P.
Action 5, Inspect the wire looms on 8...................... Operator Supplied...... $640.
the wing trailing edge.
Action 6, Replace the nylon clamps of 44 to 98............... $100 to $5,700......... $3.620 to $13,540.
the electrical routes in the
hydraulic compartment and in the
shroud box.
----------------------------------------------------------------------------------------------------------------

Based on these figures, the estimated cost of the proposed AD for
U.S. operators is up to $3,877,874, or up to $22,946 per airplane.
The following table provides the estimated costs for U.S. operators
to comply with the applicable prior or concurrent requirements in this
proposed AD.

Estimated Costs--Prior or Concurrent Requirements
----------------------------------------------------------------------------------------------------------------
Action-- Work hours Parts Cost per airplane
----------------------------------------------------------------------------------------------------------------
Inspect the wire looms on the wing 8...................... None................... $640.
trailing edge for improperly held
wires, in accordance with Airbus
Service Bulletin A300-24-6004.
Inspect for damage of the protective 4 to 7................. None................... $320 to $560.
conduits behind specified access
doors in accordance with Airbus
Service Bulletin A300-28-6010 or
A310-28-2008, as applicable.
Inspect the wire looms on the wing 8...................... None................... $640.
trailing edge for improperly held
wires in accordance with Airbus
Service Bulletin A300-24-0073.
----------------------------------------------------------------------------------------------------------------

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-2006-24289; Directorate Identifier 2005-NM-
186-AD.

Comments Due Date

(a) The FAA must receive comments on this AD action by May 4,
2006.

Affected ADs

(b) None.

Applicability

(c) This AD applies to all Airbus Model A300 B2-1A, B2-1C, B2K-
3C, B2-203, B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601,
B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and
Model C4-605R Variant F airplanes; and A310-203, -204, -221, -222, -
304, -322, -324, and -325 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 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.

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.

Action 1--Install Heat-Shrinkable Sleeve, Zones 571 and 671

(f) For all airplanes identified in paragraphs (f)(1) and (f)(2)
of this AD: Within 26 months after the effective date of this AD,
install a heat-shrinkable sleeve along the complete length of the
electrical supply bundles for the fuel pumps. These electrical

[[Page 16720]]

supply bundles are located in metallic protective conduits in zones
571 and 671.
(1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103,
and B4-203 airplanes: Do the action specified in paragraph (f) of
this AD in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A300-28-0057, Revision 02, dated January 8, 2001.
(2) For Model A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R,
B4-622R, F4-605R, F4-622R, and A300 C4-605R Variant F airplanes;
except those on which Airbus Modification 6803 has been done: Do the
action specified in paragraph (f) of this AD in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-28-6018,
Revision 1, dated September 15, 1988.

Action 2--Install Heat-Shrinkable Sleeve, Zones 575 and 675

(g) For all airplanes identified in paragraphs (g)(1), (g)(2),
and (g)(3) of this AD: Within 26 months after the effective date of
this AD, install a heat-shrinkable sleeve along the complete length
of the electrical supply bundles for the fuel pumps. These
electrical supply bundles are located in metallic protective
conduits in zones 575 and 675. For airplanes identified in
paragraphs (g)(2) and (g)(3) of this AD: Prior to or concurrently
with this installation, do a general visual inspection for damage of
the protective conduits behind specified access doors, and do any
applicable corrective action before further flight; in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A300-28-6010, Revision 1, dated September 17, 1986; or Airbus
Service Bulletin A310-28-2008, Revision 2, dated May 14, 1990; as
applicable.
(1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103,
and B4-203 airplanes: Do the actions specified in paragraph (g) of
this AD in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A300-28-0070, Revision 01, dated March 18, 1999.
(2) For Model A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R,
B4-622R, F4-605R, F4-622R, and A300 C4-605R Variant F airplanes;
except those on which Airbus Modification 10505 has been done: Do
the actions specified in paragraph (g) of this AD in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A300-28-
6048, dated September 19, 1996.
(3) For Model A310-203, -204, -221, -222, -304, -322, -324, and
-325 airplanes, except those on which Airbus Modification 10505 has
been done: Do the actions specified in paragraph (g) of this AD in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-38-2112, dated September 19, 1996.

Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''

Action 3--Modify the Retaining and Protection System

(h) For all airplanes identified in paragraphs (h)(1), and
(h)(2) of this AD: Within 26 months after the effective date of this
AD, modify the retaining and protection system for the electrical
bundles located at the wing-to-fuselage junction, under the flap
control screw jack. Prior to or concurrently with this action for
airplanes identified in paragraphs (h)(1) and (h)(2) of this AD: Do
a general visual inspection for improperly held wires of the wire
looms on the wing trailing edge, restore the electrical bundles to
good condition, and replace the affected nylon clamps with metallic
clamps that have white silicone lining; and do any applicable
corrective action before further flight; in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-24-0073,
Revision 04, dated June 30, 1998; or Airbus Service Bulletin A300-
24-6004, Revision 03, dated June 30, 1998; as applicable.
(1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103,
and B4-203 airplanes: Do the actions specified in paragraph (h) of
this AD in accordance with the Accomplishment Instructions Airbus
Service Bulletin A300-24-0085, Revision 06, dated October 13, 2005.
(2) For Model A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R,
B4-622R, F4-605R, F4-622R, and A300 C4-605R Variant F airplanes,
except those on which Airbus Modification 11276 has been done: Do
the action specified in paragraph (h) of this AD in accordance with
the Accomplishment Instructions Airbus Service Bulletin A300-24-
6043, Revision 06, dated October 13, 2005.

Action 4--Modify the Electrical Wiring of Routes 1P and 2P

(i) For Model A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R,
B4-622R, F4-605R, F4-622R, and A300 C4-605R Variant F airplanes;
except those on which Airbus Modification 11741 has been done:
Within 26 months after the effective date of this AD, modify the
electrical wiring of routes 1P and 2P (along the top panel of the
shroud box and the rear spars of the wings) by extending the
protective conduits up to the next support, and replace the two
existing clamps on this support with new improved clamps. Do all
actions in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A300-28-6056, dated February 18, 1998.

Action 5--Inspect the Wire Looms

(j) For all airplanes identified in paragraphs (j)(1) and (j)(2)
of this AD: Within 24 months after the effective date of this AD, do
a general visual inspection of the wire looms on the wing trailing
edge for improperly held wires in the clamps, restore the electrical
bundles to good condition, and replace the affected nylon clamps
with metallic clamps that have an elastometer lining. Do any
applicable corrective action before further flight. Repeat the
inspection thereafter at intervals not to exceed 24 months until all
clamps have been replaced.
(1) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, F4-622R, and A300 C4-605R Variant F airplanes; except
those on which Airbus Modification 6478 has been done: Do the
actions specified in paragraph (j) of this AD in accordance with the
Accomplishment Instructions Airbus Service Bulletin A300-24-6004,
Revision 03, dated June 30, 1998.
(2) For Model A310-203, -204, -221, -222, -304, -322, -324, and
-325 airplanes, except those on which Airbus Modification 478 has
been done: Do the actions specified in paragraph (j) of this AD in
accordance with the Accomplishment Instructions Airbus Service
Bulletin A310-24-2009, Revision 03, dated June 30, 1998.

Action 6--Improve the Quality of the Electrical Routes

(k) For all airplanes identified in paragraphs (k)(1), (k)(2),
and (k)(3) of this AD: Within 26 months after the effective date of
this AD, replace the nylon clamps of the electrical routes in the
hydraulic compartment and in the shroud box with new metallic clamps
that have white silicone lining (for airplanes identified in
paragraph (k)(1) of this AD); or replace the nylon clamps and change
the location of routes 1P and 2P to improve the retention of the
wiring loom (for airplanes identified in paragraphs (k)(2) and
(k)(3) of this AD).
(1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103,
and B4-203 airplanes; except those on which Airbus Modification
11763 has been done: Do the action specified in paragraph (k) of
this AD in accordance with the Accomplishment Instructions Airbus
Service Bulletin A300-24-0100, dated April 7, 2005.
(2) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, F4-622R, and A300 C4-605R Variant F airplanes; except
those on which Airbus Modifications 11763 and 12995 have been done:
Do the action specified in paragraph (k) of this AD in accordance
with the Accomplishment Instructions Airbus Service Bulletin A300-
24-6084, Revision 01, dated June 28, 2005.
(3) For Model A310-203, -204, -221, -222, -304, -322, -324, and
-325 airplanes, except those on which Airbus Modification 11763 has
been done: Do the action specified in paragraph (k) of this AD in
accordance with the Accomplishment Instructions as identified in
Airbus Service Bulletin A310-24-2091, dated March 4, 2005.

Parts Installation

(l) After the effective date of this AD, no person may install
on any airplane plate assemblies with part numbers A5351088000000 or
A5351088000100 unless they have been modified in accordance with
paragraph (h) of this AD.

[[Page 16721]]

Actions Accomplished According to Previous Revisions of Service
Bulletins

(m) Actions done before the effective date of this AD in
accordance with the service bulletins identified in Table 1 of this
AD are acceptable for compliance with the corresponding requirement
in this AD.

Table 1.--Previous Revisions of Service Bulletins
------------------------------------------------------------------------
Airbus service bulletin Revision level Date
------------------------------------------------------------------------
A300-28-0070................ Original............ September 19, 1996.
A300-24-0073................ 3................... February 24, 1995.
A300-24-0085................ Original............ December 12, 1994.
A300-24-0085................ 03.................. January 17, 1996.
A300-24-0085................ 04.................. July 23, 1996.
A300-24-0085................ 05.................. March 6, 2001.
A300-28-057................. 1................... September 15, 1988.
A300-24-073................. Original............ June 9, 1986.
A300-24-073................. 1................... January 28, 1988.
A300-24-073................. 2................... September 10, 1990.
A300-24-6004................ 1................... January 28, 1988.
A300-24-6004................ 2................... February 24, 1995.
A300-28-6018................ Original............ June 21, 1988.
A300-24-6043................ Original............ December 12, 1994.
A300-24-6043................ 01.................. February 7, 1995.
A300-24-6043................ 02.................. May 10, 1995.
A300-24-6043................ 03.................. January 17, 1996.
A300-24-6043................ 04.................. March 6, 2001.
A300-24-6043................ 05.................. August 30, 2001.
A300-24-6084................ Original............ March 4, 2005.
A310-24-2009................ Original............ May 31, 1985.
A310-24-2009................ 1................... January 28, 1988.
A310-24-2009................ 2................... February 24, 1995.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

(n)(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

(o) French airworthiness directive F-2005-112 R1, dated
September 14, 2005, also addresses the subject of this AD.

Issued in Renton, Washington, on March 24, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-4825 Filed 4-3-06; 8:45 am]
BILLING CODE 4910-13-P

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