Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes, 34814-34817 [06-5425]

Download as PDF 34814 Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations 2000, are considered acceptable for compliance with the initial inspections required by paragraph (f) of this AD. (g) Within 4,500 flight cycles or 6,000 flight hours, whichever comes first, after doing the initial inspections required by paragraph (f) of this AD: Do the free-play inspections of the elevator tab assembly on the left and right sides of the airplane to find any damage or discrepancy per Work Package III of Boeing Service Bulletin 737–55A1070, Revision 1, dated May 10, 2001. Repeat the inspections after that at intervals not to exceed 4,500 flight cycles or 6,000 flight hours, whichever comes first, until paragraph (i) of this AD has been accomplished. Corrective Actions (h) If any damage or discrepancy is found after doing any inspection required by paragraph (f) or (g) of this AD, before further flight, do the applicable corrective action per the Accomplishment Instructions of Boeing Service Bulletin 737–55A1070, Revision 1, dated May 10, 2001. New Requirements of This AD jlentini on PROD1PC65 with RULES Initial/Repetitive Inspections/Corrective Actions (i) Do the applicable inspections of the elevator tab assembly on the left and right sides of the airplane to find any damage or discrepancy by doing all the actions, including rework and all corrective actions, as specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737–55A1070, Revision 2, dated April 20, 2006, except as provided by paragraphs (j) and (k) of this AD. Do the applicable actions at the applicable time specified in Table 1, Table 2, or Table 3 of paragraph 1.E., ‘‘Compliance,’’ of the service bulletin; except that where the service bulletin specifies a time frame ‘‘after the release date’’ of the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. All corrective actions must be done before further flight. Repeat the inspections specified in Table 3 of paragraph 1.E., ‘‘Compliance,’’ of the service bulletin at the applicable time specified in the table. Accomplishing the actions required by paragraph (i) of this AD ends the requirements of paragraphs (f), (g), and (h) of this AD. (j) If any damage or discrepancy is found during any inspection required by paragraph (i) of this AD, and the service bulletin specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph of (m) of this AD. (k) Where Boeing Alert Service Bulletin 737–55A1070, Revision 1, dated May 10, 2001, or Revision 2, dated April 20, 2006, specifies reporting the inspection results to the manufacturer, this AD does not require such reporting. Actions Done in Accordance With Revision 1 of Service Bulletin (l) Footnote (a) in Table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–55A1070, Revision 2, specifies the following: ‘‘For airplanes on which the VerDate Aug<31>2005 16:11 Jun 15, 2006 Jkt 208001 initial actions required by Table 1 are due within 30 days after the release date of Service Bulletin 737–55A1070, Revision 2, the inspections and corrective actions defined by Service Bulletin 737–55A1070 Rev. 1 may be used.’’ This paragraph of this AD provides a corresponding 30-day deferral before Revision 2 must be used to do the initial actions, except that the 30-day time frame begins at the effective date of this AD. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) AMOCs approved previously in accordance with AD 2002–01–01, are approved as AMOCs for the corresponding provisions of paragraphs (f), (g), and (h) of this AD. (3) 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. (4) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane. Material Incorporated by Reference (n) You must use Boeing Service Bulletin 737–55A1070, Revision 1, including appendices A, B, and C, dated May 10, 2001; or Boeing Alert Service Bulletin 737– 55A1070, Revision 2, dated April 20, 2006; as applicable; to perform the actions that are required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 737–55A1070, Revision 2, dated April 20, 2006, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On February 19, 2002 (67 FR 1603, January 14, 2002), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 737– 55A1070, Revision 1, including appendices A, B, and C, dated May 10, 2001. (3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124– 2207, 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 http://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 http:// www.archives.gov/federal_register/code_of_ federal_regulations/ibr_locations.html. PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 Issued in Renton, Washington, on June 7, 2006. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–5430 Filed 6–15–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24949; Directorate Identifier 2006–NM–110–AD; Amendment 39–14626; AD 2006–12–02] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 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 all Airbus Model A318, A319, A320, and A321 airplanes. This AD requires inspecting to determine the part number and serial number of the fuel tank boost pumps and, for airplanes with affected pumps, revising the Airplane Flight Manual (AFM) and the FAA-approved maintenance program. This AD also provides for optional terminating action for compliance with the revisions to the AFM and the maintenance program. This AD results from a report that a fuel tank boost pump failed in service, due to a detached screw of the boost pump housing that created a short circuit between the stator and rotor of the boost pump motor and tripped a circuit breaker. We are issuing this AD to ensure that the flightcrew is aware of procedures to prevent the presence of a combustible air-fuel mixture in the fuel tank boost pump, which, in the event of electrical arcing in the pump motor, could result in an explosion and loss of the airplane. DATES: This AD becomes effective July 3, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of July 3, 2006. We must receive comments on this AD by August 15, 2006. ADDRESSES: Use one of the following addresses to submit comments on this AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the E:\FR\FM\16JNR1.SGM 16JNR1 Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://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 Dulin, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2141; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: could result in an explosion and loss of the airplane. compliance with the revisions to the AFM and the maintenance program. Relevant Service Information Differences Between the EASA Emergency Airworthiness Directive and This AD The EASA emergency airworthiness directive specifies to revise the AFM ‘‘from the effective date of this AD;’’ however, this AD requires revising the AFM within 10 days after the effective date of this AD. The EASA emergency airworthiness directive applies to Airbus Model A318, A319, A320, and A321 airplanes equipped with Eaton Aerospace Limited fuel pumps, having part number (P/N) 568–1–27202–005 with serial number (S/N) 6137 and subsequent. However, this AD applies to all Model A318, A319, A320, and A321 airplanes, and requires that operators perform an inspection to determine the P/N and S/ N of the fuel tank boost pumps within 10 days after the effective date of this AD. In addition, the EASA emergency airworthiness directive does not specify a terminating action; however, this AD specifies that replacing all subject fuel tank boost pumps with boost pumps not having the identified P/N and S/N is acceptable as an optional terminating action for compliance with the revisions specified for the AFM and maintenance program revisions. Airbus has issued Temporary Revision (TR) 4.03.00/28, dated May 4, 2006. The TR describes a revision to the Airbus A318/A319/A320/A321 AFM. The revision specifies conditions under which the center tank fuel boost pumps must be turned off to ensure that the center tank fuel boost pumps remain immersed in fuel during flight. The EASA mandated the TR to ensure that the center fuel tank boost pumps are immersed in fuel at all times during flight. The EASA also mandated ‘‘AFM and Airworthiness limitations’’ to ensure that the pumps are turned off during refueling and that the pumps are immersed in fuel at all times during ground fuel transfer and defueling. The EASA issued emergency airworthiness directive 2006–0106–E, dated May 2, 2006, to ensure the continued airworthiness of these airplanes in the European Union. jlentini on PROD1PC65 with RULES Discussion FAA’s Determination and Requirements of This AD The European Aviation Safety Agency (EASA) notified us that an unsafe condition may exist on certain Airbus Model A318, A319, A320, and A321 airplanes. The EASA advises that an operator reported the failure of a fuel tank boost pump in service. Subsequent investigation revealed that one of two screws that hold the gas return connector to the top of the boost pump housing had become unscrewed. The screw fell into the boost pump motor and created a short circuit between the stator and rotor, which caused a circuit breaker to trip. It was determined from further investigation that the screw came loose because of an inadequate screw locking mechanism and because the screw had not been tightened to the correct torque value. This failure mode was not identified during the design review conducted by the manufacturer in accordance with Special Federal Aviation Regulation No. 88 (‘‘SFAR 88,’’ Amendment 21–78, and subsequent Amendments 21–82 and 21–83). This condition, if not corrected, could lead to a screw becoming detached, which could compromise the integrity of the explosion-proof housing of the boost pump motor and create a potential ignition source. We are issuing this AD to ensure that the flightcrew is aware of procedures to prevent the presence of a combustible air-fuel mixture in the fuel tank boost pump, which, in the event of electrical arcing in the pump motor, 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 ensure that the flightcrew is aware of procedures to prevent the presence of a combustible air-fuel mixture in the fuel tank boost pump, which, in the event of electrical arcing in the pump motor, could result in an explosion and loss of the airplane. This AD requires inspecting to determine the part number and serial number of the fuel tank boost pumps and, for airplanes with affected pumps, revising the AFM to require including the information in the TR, and revising the AFM and the FAAapproved maintenance program to mandate the limitations described earlier. This AD also provides for optional terminating action for VerDate Aug<31>2005 16:11 Jun 15, 2006 Jkt 208001 34815 PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 Interim Action We consider this AD interim action. If final action is later identified, we may consider further rulemaking then. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD; therefore, providing notice and opportunity for public comment before the AD is issued is impracticable, and good cause exists to make this AD effective in less than 30 days. 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–2006–24949; Directorate Identifier 2006–NM–110–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. E:\FR\FM\16JNR1.SGM 16JNR1 34816 Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations We will post all comments we receive, without change, to http:// 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 http://dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at http://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. jlentini on PROD1PC65 with RULES 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. VerDate Aug<31>2005 16:11 Jun 15, 2006 Jkt 208001 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 2006–12–02 Airbus: Amendment 39–14626. Docket No. FAA–2006–24949; Directorate Identifier 2006–NM–110–AD. Effective Date (a) This AD becomes effective July 3, 2006. Affected ADs (b) None. Applicability (c) This AD applies to all Airbus Model A318, A319, A320, and A321 airplanes, certificated in any category. Unsafe Condition (d) This AD results from a report that a fuel tank boost pump failed in service, due to a detached screw of the boost pump housing that created a short circuit between the stator and rotor of the boost pump motor and tripped a circuit breaker. We are issuing this AD to ensure that the flightcrew is aware of procedures to prevent the presence of a combustible air-fuel mixture in the fuel tank boost pump, which, in the event of electrical arcing in the pump motor, could result in an explosion and loss of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 the compliance times specified, unless the actions have already been done. Part and Serial Number Inspection (f) Within 10 days after the effective date of this AD, inspect to determine the part number (P/N) and serial number (S/N) of each fuel tank boost pump installed in the wing and center fuel tanks. A review of maintenance records may be performed instead of the required inspection if the P/N and S/N of the fuel boost pump can be conclusively determined from that review. For any airplane not equipped with any Eaton Aerospace Limited (formerly FR– HITEMP Limited) fuel pump having P/N 568–1–27202–005 with S/N 6137 and subsequent: No further action is required by this AD for that airplane except as described in paragraph (i) of this AD. Revisions to the Airplane Flight Manual (AFM) and the Maintenance Program (g) For airplanes equipped with one or more Eaton Aerospace Limited (formerly FR– HITEMP Limited) fuel boost pumps, having P/N 568–1–27202–005 with S/N 6137 and subsequent: Prior to further flight after accomplishing the inspection required by paragraph (f) of this AD, do the actions specified in paragraphs (g)(1) and (g)(2) of this AD. (1) Revise the Limitations section of the Airbus A318/A319/A320/A321 AFM and the FAA-approved maintenance program by incorporating the following. This may be accomplished by inserting copies of this AD into the AFM and the maintenance program. ‘‘Apply the following procedure at each fuel loading: Refueling: Before refueling, all pumps must be turned off, in order to prevent them from automatically starting during the refueling process. Ground fuel transfer: For all aircraft, do not start a fuel transfer from any wing tank, if it contains less than 700 kg (1550 lb) of fuel. For A318, A319, and A320 aircraft with a center tank, do not start a fuel transfer from the center tank, if it contains less than 2,000 kg (4,500 lb) of fuel. If a tank has less than the required quantity, it is necessary to add fuel (via a transfer from another tank or refueling) to enable a transfer to take place. Defueling: For all aircraft, when defueling the wings, do not start the fuel pumps if the fuel quantity in the inner tank (wing tank for A321) is below 700 kg (1,550 lb). If the fuel on the aircraft is not sufficient to achieve the required fuel distribution, then transfer fuel or refuel the aircraft to obtain the required fuel quantity in the wing tank. For A318, A319, and A320 aircraft with a center tank, when performing a pressure defuel of the center tank, make sure that the center tank contains at least 2,000 kg (4,500 lb) of fuel. If it has less than the required quantity, then transfer fuel to the center tank. Defuel the aircraft normally, and turn OFF the center tank pumps immediately after the FAULT light on the corresponding pushbutton-switch comes on.’’ E:\FR\FM\16JNR1.SGM 16JNR1 Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations (2) Revise the Limitations section of the AFM to incorporate the changes specified in Airbus Temporary Revision (TR) 4.03.00/28, dated May 4, 2006. This may be accomplished by inserting a copy of the TR into the AFM. When general revisions of the AFM have been issued that incorporate the revisions specified in the TR, the copy of the TR may be removed from the AFM, provided the relevant information in the general revision is identical to that in TR 4.03.00/28. Optional Terminating Action Parts Installation Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (k) The European Aviation Safety Agency (EASA) emergency airworthiness directive 2006–0106–E, dated May 2, 2006, also addresses the subject of this AD. jlentini on PROD1PC65 with RULES DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 [Docket No. FAA–2006–24431; Directorate Identifier 2006–NM–011–AD; Amendment 39–14648; AD 2006–12–22] RIN 2120–AA64 Airworthiness Directives; Airbus Model A319, A320, and A321 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: (i) As of the effective date of this AD, no person may install a boost pump, P/N 568– 1–27202–005, having S/N 6137 and subsequent, on any airplane. Material Incorporated by Reference (l) You must use Airbus Temporary Revision 4.03.00/28, dated May 4, 2006, to perform the actions that are required by this AD, unless the AD specifies otherwise. (The approval date of Airbus Temporary Revision 4.03.00/28 is only indicated on page one of the document.) The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point 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 http://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 http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. 16:11 Jun 15, 2006 BILLING CODE 4910–13–P Federal Aviation Administration (h) Replacement of all subject fuel boost pumps on any airplane with boost pumps having a P/N other than P/N 568–1–27202– 005; or with boost pumps, P/N 568–1–27202– 005, having a S/N other than 6137 and subsequent; constitutes terminating action for this AD, and the limitations required by paragraph (g) of this AD may be removed from the AFM and the maintenance program for that airplane. VerDate Aug<31>2005 Issued in Renton, Washington, on June 7, 2006. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–5425 Filed 6–15–06; 8:45 am] Jkt 208001 SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 airplanes. This AD requires a detailed inspection for cracks and marks on the carbon blades of the ram air turbine (RAT), and replacement of the RAT with a new or serviceable RAT if necessary. This AD results from a report of three chord-wise cracks on the aft side of one carbon blade of a certain RAT. We are issuing this AD to detect and correct cracks and/or marks on the RAT carbon blades, which could result in reduced structural integrity of the carbon blade, and consequent loss of the RAT as a source of hydraulic and electrical power in an emergency. DATES: This AD becomes effective July 21, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of July 21, 2006. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2141; fax (425) 227–1149. PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 34817 SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://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 street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Airbus Model A319, A320, and A321 airplanes. That NPRM was published in the Federal Register on April 13, 2006 (71 FR 19136). That NPRM proposed to require a detailed inspection for cracks and marks on the carbon blades of the ram air turbine (RAT), and replacement of the RAT with a new or serviceable RAT if necessary. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the one comment received. The commenter, Airbus, supports the NPRM. Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance This AD will affect about 34 airplanes of U.S. registry. The required inspection will take about 1 work hour per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of this AD for U.S. operators is $2,720, or $80 per airplane. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations E:\FR\FM\16JNR1.SGM 16JNR1

Agencies

[Federal Register Volume 71, Number 116 (Friday, June 16, 2006)]
[Rules and Regulations]
[Pages 34814-34817]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5425]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24949; Directorate Identifier 2006-NM-110-AD; 
Amendment 39-14626; AD 2006-12-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318, A319, A320, and A321 
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 all 
Airbus Model A318, A319, A320, and A321 airplanes. This AD requires 
inspecting to determine the part number and serial number of the fuel 
tank boost pumps and, for airplanes with affected pumps, revising the 
Airplane Flight Manual (AFM) and the FAA-approved maintenance program. 
This AD also provides for optional terminating action for compliance 
with the revisions to the AFM and the maintenance program. This AD 
results from a report that a fuel tank boost pump failed in service, 
due to a detached screw of the boost pump housing that created a short 
circuit between the stator and rotor of the boost pump motor and 
tripped a circuit breaker. We are issuing this AD to ensure that the 
flightcrew is aware of procedures to prevent the presence of a 
combustible air-fuel mixture in the fuel tank boost pump, which, in the 
event of electrical arcing in the pump motor, could result in an 
explosion and loss of the airplane.

DATES: This AD becomes effective July 3, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of July 3, 2006.
    We must receive comments on this AD by August 15, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the

[[Page 34815]]

instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
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 Dulin, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA) notified us that an 
unsafe condition may exist on certain Airbus Model A318, A319, A320, 
and A321 airplanes. The EASA advises that an operator reported the 
failure of a fuel tank boost pump in service. Subsequent investigation 
revealed that one of two screws that hold the gas return connector to 
the top of the boost pump housing had become unscrewed. The screw fell 
into the boost pump motor and created a short circuit between the 
stator and rotor, which caused a circuit breaker to trip.
    It was determined from further investigation that the screw came 
loose because of an inadequate screw locking mechanism and because the 
screw had not been tightened to the correct torque value. This failure 
mode was not identified during the design review conducted by the 
manufacturer in accordance with Special Federal Aviation Regulation No. 
88 (``SFAR 88,'' Amendment 21-78, and subsequent Amendments 21-82 and 
21-83). This condition, if not corrected, could lead to a screw 
becoming detached, which could compromise the integrity of the 
explosion-proof housing of the boost pump motor and create a potential 
ignition source. We are issuing this AD to ensure that the flightcrew 
is aware of procedures to prevent the presence of a combustible air-
fuel mixture in the fuel tank boost pump, which, in the event of 
electrical arcing in the pump motor, could result in an explosion and 
loss of the airplane.

Relevant Service Information

    Airbus has issued Temporary Revision (TR) 4.03.00/28, dated May 4, 
2006. The TR describes a revision to the Airbus A318/A319/A320/A321 
AFM. The revision specifies conditions under which the center tank fuel 
boost pumps must be turned off to ensure that the center tank fuel 
boost pumps remain immersed in fuel during flight.
    The EASA mandated the TR to ensure that the center fuel tank boost 
pumps are immersed in fuel at all times during flight. The EASA also 
mandated ``AFM and Airworthiness limitations'' to ensure that the pumps 
are turned off during refueling and that the pumps are immersed in fuel 
at all times during ground fuel transfer and defueling. The EASA issued 
emergency airworthiness directive 2006-0106-E, dated May 2, 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 ensure that the flightcrew is 
aware of procedures to prevent the presence of a combustible air-fuel 
mixture in the fuel tank boost pump, which, in the event of electrical 
arcing in the pump motor, could result in an explosion and loss of the 
airplane. This AD requires inspecting to determine the part number and 
serial number of the fuel tank boost pumps and, for airplanes with 
affected pumps, revising the AFM to require including the information 
in the TR, and revising the AFM and the FAA-approved maintenance 
program to mandate the limitations described earlier. This AD also 
provides for optional terminating action for compliance with the 
revisions to the AFM and the maintenance program.

Differences Between the EASA Emergency Airworthiness Directive and This 
AD

    The EASA emergency airworthiness directive specifies to revise the 
AFM ``from the effective date of this AD;'' however, this AD requires 
revising the AFM within 10 days after the effective date of this AD.
    The EASA emergency airworthiness directive applies to Airbus Model 
A318, A319, A320, and A321 airplanes equipped with Eaton Aerospace 
Limited fuel pumps, having part number (P/N) 568-1-27202-005 with 
serial number (S/N) 6137 and subsequent. However, this AD applies to 
all Model A318, A319, A320, and A321 airplanes, and requires that 
operators perform an inspection to determine the P/N and S/N of the 
fuel tank boost pumps within 10 days after the effective date of this 
AD.
    In addition, the EASA emergency airworthiness directive does not 
specify a terminating action; however, this AD specifies that replacing 
all subject fuel tank boost pumps with boost pumps not having the 
identified P/N and S/N is acceptable as an optional terminating action 
for compliance with the revisions specified for the AFM and maintenance 
program revisions.

Interim Action

    We consider this AD interim action. If final action is later 
identified, we may consider further rulemaking then.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD; therefore, providing notice and opportunity for public comment 
before the AD is issued is impracticable, and good cause exists to make 
this AD effective in less than 30 days.

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-
24949; Directorate Identifier 2006-NM-110-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.

[[Page 34816]]

    We will post all comments we receive, without change, to http://
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 
http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://
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):

2006-12-02 Airbus: Amendment 39-14626. Docket No. FAA-2006-24949; 
Directorate Identifier 2006-NM-110-AD.

Effective Date

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

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A318, A319, A320, and 
A321 airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from a report that a fuel tank boost pump 
failed in service, due to a detached screw of the boost pump housing 
that created a short circuit between the stator and rotor of the 
boost pump motor and tripped a circuit breaker. We are issuing this 
AD to ensure that the flightcrew is aware of procedures to prevent 
the presence of a combustible air-fuel mixture in the fuel tank 
boost pump, which, in the event of electrical arcing in the pump 
motor, could result in an explosion and 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.

Part and Serial Number Inspection

    (f) Within 10 days after the effective date of this AD, inspect 
to determine the part number (P/N) and serial number (S/N) of each 
fuel tank boost pump installed in the wing and center fuel tanks. A 
review of maintenance records may be performed instead of the 
required inspection if the P/N and S/N of the fuel boost pump can be 
conclusively determined from that review. For any airplane not 
equipped with any Eaton Aerospace Limited (formerly FR-HITEMP 
Limited) fuel pump having P/N 568-1-27202-005 with S/N 6137 and 
subsequent: No further action is required by this AD for that 
airplane except as described in paragraph (i) of this AD.

Revisions to the Airplane Flight Manual (AFM) and the Maintenance 
Program

    (g) For airplanes equipped with one or more Eaton Aerospace 
Limited (formerly FR-HITEMP Limited) fuel boost pumps, having P/N 
568-1-27202-005 with S/N 6137 and subsequent: Prior to further 
flight after accomplishing the inspection required by paragraph (f) 
of this AD, do the actions specified in paragraphs (g)(1) and (g)(2) 
of this AD.
    (1) Revise the Limitations section of the Airbus A318/A319/A320/
A321 AFM and the FAA-approved maintenance program by incorporating 
the following. This may be accomplished by inserting copies of this 
AD into the AFM and the maintenance program.
    ``Apply the following procedure at each fuel loading:

Refueling:
    Before refueling, all pumps must be turned off, in order to 
prevent them from automatically starting during the refueling 
process.

Ground fuel transfer:
    For all aircraft, do not start a fuel transfer from any wing 
tank, if it contains less than 700 kg (1550 lb) of fuel.
    For A318, A319, and A320 aircraft with a center tank, do not 
start a fuel transfer from the center tank, if it contains less than 
2,000 kg (4,500 lb) of fuel.
    If a tank has less than the required quantity, it is necessary 
to add fuel (via a transfer from another tank or refueling) to 
enable a transfer to take place.

Defueling:
    For all aircraft, when defueling the wings, do not start the 
fuel pumps if the fuel quantity in the inner tank (wing tank for 
A321) is below 700 kg (1,550 lb). If the fuel on the aircraft is not 
sufficient to achieve the required fuel distribution, then transfer 
fuel or refuel the aircraft to obtain the required fuel quantity in 
the wing tank.
    For A318, A319, and A320 aircraft with a center tank, when 
performing a pressure defuel of the center tank, make sure that the 
center tank contains at least 2,000 kg (4,500 lb) of fuel. If it has 
less than the required quantity, then transfer fuel to the center 
tank. Defuel the aircraft normally, and turn OFF the center tank 
pumps immediately after the FAULT light on the corresponding 
pushbutton-switch comes on.''

[[Page 34817]]

    (2) Revise the Limitations section of the AFM to incorporate the 
changes specified in Airbus Temporary Revision (TR) 4.03.00/28, 
dated May 4, 2006. This may be accomplished by inserting a copy of 
the TR into the AFM. When general revisions of the AFM have been 
issued that incorporate the revisions specified in the TR, the copy 
of the TR may be removed from the AFM, provided the relevant 
information in the general revision is identical to that in TR 
4.03.00/28.

Optional Terminating Action

    (h) Replacement of all subject fuel boost pumps on any airplane 
with boost pumps having a P/N other than P/N 568-1-27202-005; or 
with boost pumps, P/N 568-1-27202-005, having a S/N other than 6137 
and subsequent; constitutes terminating action for this AD, and the 
limitations required by paragraph (g) of this AD may be removed from 
the AFM and the maintenance program for that airplane.

Parts Installation

    (i) As of the effective date of this AD, no person may install a 
boost pump, P/N 568-1-27202-005, having S/N 6137 and subsequent, on 
any airplane.

Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (k) The European Aviation Safety Agency (EASA) emergency 
airworthiness directive 2006-0106-E, dated May 2, 2006, also 
addresses the subject of this AD.

Material Incorporated by Reference

    (l) You must use Airbus Temporary Revision 4.03.00/28, dated May 
4, 2006, to perform the actions that are required by this AD, unless 
the AD specifies otherwise. (The approval date of Airbus Temporary 
Revision 4.03.00/28 is only indicated on page one of the document.) 
The Director of the Federal Register approved the incorporation by 
reference of this document in accordance with 5 U.S.C. 552(a) and 1 
CFR part 51. Contact Airbus, 1 Rond Point 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 http://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 http://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on June 7, 2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-5425 Filed 6-15-06; 8:45 am]
BILLING CODE 4910-13-P