Airworthiness Directives; Airbus Model A330-200, A340-200, and A340-300 Airplanes, 61639-61642 [E6-17426]

Download as PDF Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations 61639 Actions Compliance Procedures (5) For Model N24A airplanes: (i) Fabricate a placard that incorporates the following words (using at least 1⁄8-inch letters) and install this placard on the instrument panel within the pilot’s clear view: ‘‘USE 10° FLAP FOR TAKE-OFF AND LANDING—WARNING—DO NOT EXCEED 10° FLAP EXTENSION DURING FLIGHT, LANDING GEAR UP WARNING WILL INITIATE FOR A TORQUE PRESSURE OF LESS THAN 30 PSI’’; and (ii) Incorporate the following information into the Limitations section of the AFM: (A) Limit the maximum flap extension to 10 degrees; and (B) Limit flaps down operations for landing to 10° flap. Within the next 50 hours TIS after December 23, 2003 (the effective date of AD 2003– 22–13), unless already done following Nomad Alert Service Bulletin ANMD–57–18, dated December 19, 2002. Following Nomad Alert Service Bulletin ANMD–57–18, Rev 1, dated August 14, 2006. To show compliance with paragraphs (e)(5)(ii)(A) and (e)(5)(ii)(B) of this AD, a copy of this AD may be inserted into the Limitations section of the AFM. The owner/ operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may do the AFM insertion and the placard requirement of paragraph (e)(5)(i) of this AD. Make an entry into the aircraft records showing compliance with these portions of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). Alternative Methods of Compliance (AMOCs) (f) The Manager, Standards Staff, FAA, ATTN: Doug Rudolph, Aerospace Engineer, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; fax: (816) 329– 4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (g) AMOCs approved for AD 2003–22–13 are not approved for this AD. Related Information (h) This AD relates to Australian AD/GAF– N22/69, Amendment 5, dated September 14, 2006, which references Nomad Alert Service Bulletin ANMD–57–18, Rev 1, dated August 14, 2006. PWALKER on PRODPC60 with RULES Material Incorporated by Reference (i) You must use Nomad Alert Service Bulletin ANMD–57–18, Rev 1, dated August 14, 2006, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Nomad Operations, Aerospace Support Division, Boeing Australia, PO Box 767, Brisbane, QLD 4000 Australia; telephone 61 7 3306 3366; fax 61 7 3306 3111. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Kansas City, Missouri, on October 13, 2006. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–17425 Filed 10–18–06; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 20:58 Oct 18, 2006 Jkt 211001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26083; Directorate Identifier 2006–NM–185–AD; Amendment 39–14793; AD 2006–21–08] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–200, A340–200, and A340–300 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330–200, A340–200, and A340–300 airplanes. This AD requires the installation of heatshields in the belly fairing of the center fuselage. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent exposing any fuel leaked from the center fuel tank to the hot temperature areas of the air conditioning packs, which could result in a fire and consequent fuel tank explosion. DATES: This AD becomes effective November 3, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of November 3, 2006. We must receive comments on this AD by December 18, 2006. ADDRESSES: Use one of the following addresses to submit comments on this AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 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 AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: 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 E:\FR\FM\19OCR1.SGM 19OCR1 61640 Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations 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), which is the airworthiness authority for the European Union, notified us that an unsafe condition may exist on certain Airbus Model A330– 200, A340–200, and A340–300 airplanes. The EASA advises that there could be temperatures in excess of 200 degrees Celsius on surfaces in the belly fairing of the center fuselage. Therefore, any fuel leaked from the center fuel tank would be exposed to the hot temperature areas of the air conditioning packs. This condition, if not corrected, could result in a fire and consequent fuel tank explosion. 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 issuing this AD to prevent exposing any fuel leaked from the center fuel tank to the hot temperature areas of the air conditioning packs, which could result in a fire and consequent fuel tank explosion. This AD requires accomplishing the actions specified in the service information described previously, except as discussed in ‘‘Difference Between EASA Airworthiness Directive and This AD.’’ Relevant Service Information Airbus has issued Service Bulletins A330–21–3096 and A340–21–4107, both Revision 01, both dated October 10, 2005. The service bulletins describe procedures for the installation of heatshields in the belly fairing of the center fuselage. The installation includes the following actions: • Replacing existing heatshields with new heatshields fitted with edges and draining tapping. • Adding draining systems. • Adding two heatshields. • Adding two tight insulation sleeves on the ozone reducer and on the trim pipe. • Replacing and adding brackets. • Modifying a heatshield panel. The EASA mandated the service information and issued airworthiness directive 2006–0191, dated July 10, 2006, to ensure the continued airworthiness of these airplanes in the European Union. Difference Between EASA Airworthiness Directive and This AD FAA’s Determination and Requirements of this 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 The applicability of EASA airworthiness directive 2006–0191 excludes airplanes on which Airbus Service Bulletin A330–21–3096, Revision 01; or Airbus Service Bulletin A340–21–4107, Revision 01; have been accomplished in service. However, we have not excluded those airplanes in the applicability of this AD; rather, this AD includes a requirement to accomplish the actions specified in Revision 01 of those service bulletins, as applicable. This requirement would ensure that the actions specified in the service bulletins and required by this AD are accomplished on all affected airplanes. Operators must continue to operate the airplane in the configuration required by this AD unless an alternative method of compliance is approved. Costs of Compliance None of the airplanes affected by this action are on the U.S. Register. All airplanes affected by this AD are currently operated by non-U.S. operators under foreign registry; therefore, they are not directly affected by this AD action. However, we consider this AD necessary to ensure that the unsafe condition is addressed if any affected airplane is imported and placed on the U.S. Register in the future. The following table provides the estimated costs to comply with this AD for any affected airplane that might be imported and placed on the U.S. Register in the future. PWALKER on PRODPC60 with RULES ESTIMATED COSTS Action Work hours Average labor rate per hour Parts cost Cost per airplane Installation ........................................................................................................ 65 $80 $17,290 $22,490 VerDate Aug<31>2005 20:58 Oct 18, 2006 Jkt 211001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\19OCR1.SGM 19OCR1 Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations FAA’s Determination of the Effective Date No airplane affected by this AD is currently on the U.S. Register. Therefore, providing notice and opportunity for public comment is unnecessary before this AD is issued, and this AD may be made effective in less than 30 days after it is published in the Federal Register. Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any relevant written data, views, or arguments regarding this AD. Send your comments to an address listed in the ADDRESSES section. Include ‘‘Docket No. FAA–2006–26083; Directorate Identifier 2006–NM–185–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD that might suggest a need to modify it. 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 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. PWALKER on PRODPC60 with RULES 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. 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 VerDate Aug<31>2005 20:58 Oct 18, 2006 Jkt 211001 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 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 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, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I 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): I PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 61641 2006–21–08 Airbus: Amendment 39–14793. Docket No. FAA–2006–26083; Directorate Identifier 2006–NM–185–AD. Effective Date (a) This AD becomes effective November 3, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A330– 200, A340–200, and A340–300 airplanes, certificated in any category; except airplanes on which Airbus Modification 49520 has been done in production. Unsafe Condition (d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent exposing any fuel leaked from the center fuel tank to the hot temperature areas of the air conditioning packs, which could result in a fire and consequent fuel tank explosion. 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. Installation of Heatshields (f) Within 27 months after the effective date of this AD, install heatshields in the belly fairing of the center fuselage in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 21–3096, Revision 01, dated October 10, 2005 (for Model A330–200 airplanes); or Airbus Service Bulletin A340–21–4107, Revision 01, dated October 10, 2005 (for Model A340–200 and A340–300 airplanes); as applicable. 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. Related Information (h) European Aviation Safety Agency (EASA) airworthiness directive 2006–0191, dated July 10, 2006, also addresses the subject of this AD. Material Incorporated by Reference (i) You must use Airbus Service Bulletin A330–21–3096, Revision 01, dated October 10, 2005; or Airbus Service Bulletin A340– 21–4107, Revision 01, dated October 10, 2005; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point E:\FR\FM\19OCR1.SGM 19OCR1 61642 Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on October 10, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–17426 Filed 10–18–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25730; Directorate Identifier 2006–NE–31–AD; Amendment 39– 14796; AD 2006–21–11] RIN 2120–AA64 Airworthiness Directives; Turbomeca Turmo IV A and IV C Series Turboshaft Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. PWALKER on PRODPC60 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Turmo IV A and IV C series turboshaft engines. This AD requires identifying, inspecting and replacing flexible lubrication pipes manufactured after April 1, 2003. If both engines on the same helicopter each have an affected pipe, then this AD requires replacing one of the affected pipes before further flight. This AD also requires initial and repetitive borescope inspections of affected pipes, visual inspections for oil leakage, and visual inspections of the oil filter, on engines that are not required to have an affected pipe replaced before further flight by this AD. This AD results from 7 reports of oil leakage due to the deterioration of flexible lubrication pipes manufactured after April 1, 2003. We are issuing this AD to prevent dual-engine failure on a twin-engine helicopter. DATES: Effective November 3, 2006. We must receive any comments on this AD by December 18, 2006. VerDate Aug<31>2005 20:58 Oct 18, 2006 Jkt 211001 Use one of the following addresses to comment on this 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– 0001. • 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 Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15 for the service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7175; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The European Aviation Safety Agency (EASA), which is the airworthiness authority for the European Community, recently notified us that an unsafe condition may exist on certain Turbomeca Turmo IV A and IV C series turboshaft engines. EASA advises that 7 reports were received of oil leakage due to the deterioration of flexible lubrication pipes, part number (P/N) 0 249 92 813 0, installed on Turbomeca Turmo III C4 (military version) turboshaft engines. Turbomeca is still investigating the cause of the deterioration, but links a manufacturing process change, applied by the pipe manufacturer, in 2003. The same process was used to manufacture flexible lubrication pipes, P/N 0 249 92 916 0. Either P/N pipe could be installed on Turmo IV A and IV C series turboshaft engines. ADDRESSES: Relevant Service Information We have reviewed and approved the technical contents of Turbomeca Alert Mandatory Service Bulletin (MSB) No. A249 72 0802, Update No. 1, dated August 3, 2006. That Alert MSB describes procedures for identifying affected flexible lubrication pipes by their curing batch number, and replacing one of the affected pipes on a twin-engine helicopter to prevent dualengine failure. That Alert MSB also PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 describes procedures for performing repetitive borescope inspections of all other affected pipes and visual inspections of the oil filter. EASA classified this service bulletin as mandatory and issued AD 2006–0240–E in order to ensure the airworthiness of these Turbomeca Turmo IV A and IV C series turboshaft engines in Europe. Bilateral Airworthiness Agreement These Turbomeca Turmo IV A and IV C series turboshaft engines 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. Under this bilateral airworthiness agreement, EASA kept the FAA informed of the situation described above. We have examined the findings of EASA, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. FAA’s Determination and Requirements of This AD The unsafe condition described previously is likely to exist or develop on other Turbomeca Turmo IV A and IV C series turboshaft engines of the same type design. We are issuing this AD to prevent dual-engine failure on a twinengine helicopter. This AD requires identifying affected flexible lubrication pipes by their curing batch number, and replacing the affected pipe before further flight, on one engine if both engines on the same helicopter each have an affected pipe. This AD also requires initial and repetitive borescope inspections of flexible lubrication pipes and visual inspections of the oil filter, on engines that do not have the affected pipe replaced before further flight. FAA’s Determination of the Effective Date Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in less than 30 days. Interim Action These actions are interim actions and we may take further rulemaking actions in the future. Comments Invited This AD is a final rule that involves requirements affecting flight safety and E:\FR\FM\19OCR1.SGM 19OCR1

Agencies

[Federal Register Volume 71, Number 202 (Thursday, October 19, 2006)]
[Rules and Regulations]
[Pages 61639-61642]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-1]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26083; Directorate Identifier 2006-NM-185-AD; 
Amendment 39-14793; AD 2006-21-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-200, A340-200, and 
A340-300 Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A330-200, A340-200, and A340-300 airplanes. This 
AD requires the installation of heatshields in the belly fairing of the 
center fuselage. This AD results from fuel system reviews conducted by 
the manufacturer. We are issuing this AD to prevent exposing any fuel 
leaked from the center fuel tank to the hot temperature areas of the 
air conditioning packs, which could result in a fire and consequent 
fuel tank explosion.

DATES: This AD becomes effective November 3, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of November 3, 
2006.
    We must receive comments on this AD by December 18, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this 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 AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

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

[[Page 61640]]

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), which is the 
airworthiness authority for the European Union, notified us that an 
unsafe condition may exist on certain Airbus Model A330-200, A340-200, 
and A340-300 airplanes. The EASA advises that there could be 
temperatures in excess of 200 degrees Celsius on surfaces in the belly 
fairing of the center fuselage. Therefore, any fuel leaked from the 
center fuel tank would be exposed to the hot temperature areas of the 
air conditioning packs. This condition, if not corrected, could result 
in a fire and consequent fuel tank explosion.

Relevant Service Information

    Airbus has issued Service Bulletins A330-21-3096 and A340-21-4107, 
both Revision 01, both dated October 10, 2005. The service bulletins 
describe procedures for the installation of heatshields in the belly 
fairing of the center fuselage. The installation includes the following 
actions:
     Replacing existing heatshields with new heatshields fitted 
with edges and draining tapping.
     Adding draining systems.
     Adding two heatshields.
     Adding two tight insulation sleeves on the ozone reducer 
and on the trim pipe.
     Replacing and adding brackets.
     Modifying a heatshield panel.
    The EASA mandated the service information and issued airworthiness 
directive 2006-0191, dated July 10, 2006, to ensure the continued 
airworthiness of these airplanes in the European Union.

FAA's Determination and Requirements of this 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 issuing this AD to prevent exposing any fuel 
leaked from the center fuel tank to the hot temperature areas of the 
air conditioning packs, which could result in a fire and consequent 
fuel tank explosion. This AD requires accomplishing the actions 
specified in the service information described previously, except as 
discussed in ``Difference Between EASA Airworthiness Directive and This 
AD.''

Difference Between EASA Airworthiness Directive and This AD

    The applicability of EASA airworthiness directive 2006-0191 
excludes airplanes on which Airbus Service Bulletin A330-21-3096, 
Revision 01; or Airbus Service Bulletin A340-21-4107, Revision 01; have 
been accomplished in service. However, we have not excluded those 
airplanes in the applicability of this AD; rather, this AD includes a 
requirement to accomplish the actions specified in Revision 01 of those 
service bulletins, as applicable. This requirement would ensure that 
the actions specified in the service bulletins and required by this AD 
are accomplished on all affected airplanes. Operators must continue to 
operate the airplane in the configuration required by this AD unless an 
alternative method of compliance is approved.

Costs of Compliance

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes affected by this AD are currently operated by 
non-U.S. operators under foreign registry; therefore, they are not 
directly affected by this AD action. However, we consider this AD 
necessary to ensure that the unsafe condition is addressed if any 
affected airplane is imported and placed on the U.S. Register in the 
future.
    The following table provides the estimated costs to comply with 
this AD for any affected airplane that might be imported and placed on 
the U.S. Register in the future.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                Average labor                        Cost per
                   Action                        Work hours     rate per hour      Parts cost        airplane
----------------------------------------------------------------------------------------------------------------
Installation................................              65              $80          $17,290          $22,490
----------------------------------------------------------------------------------------------------------------


[[Page 61641]]

FAA's Determination of the Effective Date

    No airplane affected by this AD is currently on the U.S. Register. 
Therefore, providing notice and opportunity for public comment is 
unnecessary before this AD is issued, and this AD may be made effective 
in less than 30 days after it is published in the Federal Register.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to an 
address listed in the ADDRESSES section. Include ``Docket No. FAA-2006-
26083; Directorate Identifier 2006-NM-185-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD that might 
suggest a need to modify it.
    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 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.

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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 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 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2006-21-08 Airbus: Amendment 39-14793. Docket No. FAA-2006-26083; 
Directorate Identifier 2006-NM-185-AD.

Effective Date

    (a) This AD becomes effective November 3, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A330-200, A340-200, and 
A340-300 airplanes, certificated in any category; except airplanes 
on which Airbus Modification 49520 has been done in production.

Unsafe Condition

    (d) This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD to prevent exposing any fuel 
leaked from the center fuel tank to the hot temperature areas of the 
air conditioning packs, which could result in a fire and consequent 
fuel tank explosion.

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.

Installation of Heatshields

    (f) Within 27 months after the effective date of this AD, 
install heatshields in the belly fairing of the center fuselage in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-21-3096, Revision 01, dated October 10, 2005 (for 
Model A330-200 airplanes); or Airbus Service Bulletin A340-21-4107, 
Revision 01, dated October 10, 2005 (for Model A340-200 and A340-300 
airplanes); as applicable.

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 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

    (h) European Aviation Safety Agency (EASA) airworthiness 
directive 2006-0191, dated July 10, 2006, also addresses the subject 
of this AD.

Material Incorporated by Reference

    (i) You must use Airbus Service Bulletin A330-21-3096, Revision 
01, dated October 10, 2005; or Airbus Service Bulletin A340-21-4107, 
Revision 01, dated October 10, 2005; as applicable, to perform the 
actions that are required by this AD, unless the AD specifies 
otherwise. The Director of the Federal Register approved the 
incorporation by reference of these documents in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point

[[Page 61642]]

Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this 
service information. You may review copies at the Docket Management 
Facility, U.S. Department of Transportation, 400 Seventh Street, 
SW., Room PL-401, Nassif Building, Washington, DC; on the Internet 
at https://dms.dot.gov; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at the NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

    Issued in Renton, Washington, on October 10, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-17426 Filed 10-18-06; 8:45 am]
BILLING CODE 4910-13-P