Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes, 3371-3373 [E7-1093]

Download as PDF 3371 Proposed Rules Federal Register Vol. 72, No. 16 Thursday, January 25, 2007 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27011; Directorate Identifier 2006–NM–175–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). ycherry on PROD1PC64 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all Airbus Model A318, A319, A320, and A321 airplanes. The existing AD currently 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. The existing AD also provides for optional terminating action for compliance with the revisions to the AFM and the maintenance program. This proposed AD would require modifying or replacing the fuel tank boost pumps, which would allow removal of the limitations from the AFM and the maintenance program. This proposed 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 proposing this AD to prevent electrical arcing in the fuel tank boost pump motor, which, in the presence of a combustible air-fuel mixture in the pump, could result in an explosion and loss of the airplane. DATES: We must receive comments on this proposed AD by February 26, 2007. VerDate Aug<31>2005 13:34 Jan 24, 2007 Jkt 211001 Use one of the following addresses to submit comments on this proposed AD. • DOT Docket web site: Go to http:// dms.dot.gov and follow the 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 proposed 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: ADDRESSES: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2007–27011; Directorate Identifier 2006–NM–175– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to 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 proposed AD. Using the search function of that web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 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. Discussion On June 7, 2006, we issued AD 2006– 12–02, amendment 39–14626 (71 FR 34814, June 16, 2006), for all Airbus Model A318, A319, A320, and A321 airplanes. That 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. That AD also provides for optional terminating action for compliance with the revisions to the AFM and the maintenance program. That AD resulted 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 issued that 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. Actions Since Existing AD Was Issued We considered AD 2006–12–02 interim action and were considering further rulemaking if final action were later identified. We now have determined that further rulemaking is necessary, and this proposed AD follows from that determination. Airbus has developed a modification to prevent the screws from coming loose and E:\FR\FM\25JAP1.SGM 25JAP1 3372 Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Proposed Rules issued new service information that addresses the identified unsafe condition. Relevant Service Information Airbus has issued the following service bulletins: SERVICE BULLETINS Airbus Service Bulletin Revision A320–28–1152 Original 01 01 A320–28–1153 Date May 5, 2006. July 17, 2006. July 13, 2006. Service Bulletin A320–28–1152 describes procedures for determining the type, part number, and serial number of the fuel pumps of the wing and center tanks by either checking airplane records or inspecting the pump amendment label. The service bulletin recommends modifying affected fuel pumps in accordance with Service Bulletin A320–28–1153. Service Bulletin A320–28–1153 describes procedures for modifying the affected fuel pumps by replacing the nuts and bolts from the gas return outlet with new nuts and bolts, applying the correct torque to the nuts, and applying locktite adhesive, or replacing affected pumps with pumps having a serial number other than 6137 and subsequent. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The European Aviation Safety Agency (EASA), which is the aviation authority for the European Union, mandated the service information and issued airworthiness directive 2006–0222, dated July 20, 2006, to ensure the continued airworthiness of these airplanes in the European Union. Service Bulletin A320–28–1153 refers to Eaton Service Bulletin 8410–28–04, dated May 2, 2006, as an additional source of service information for the modification. FAA’s Determination and Requirements of the Proposed AD 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 airplanes of this type design that are certificated for operation in the United States. This proposed AD would supersede AD 2006–12–02 and would retain the requirements and provisions of the existing AD. This proposed AD would also require modifying affected fuel pumps, which would allow removal of the limitations from the AFM and the maintenance program. Costs of Compliance These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of § 21.29 of the Federal Aviation Regulations (14 The following table provides the estimated costs for U.S. operators to comply with this proposed AD. The parts manufacturer states that it will modify the pump free of charge. ESTIMATED COSTS Work hours Average labor rate per hour Parts Cost per airplane Number of U.S.-registered airplanes Fleet cost Identify boost pumps, as required by AD 2006–12–02 ... ycherry on PROD1PC64 with PROPOSALS Action 1 $80 None $80 727 $58,160 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism VerDate Aug<31>2005 13:34 Jan 24, 2007 Jkt 211001 implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–14626 (71 FR 34814, June 16, 2006) and adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2007–27011; Directorate Identifier 2006–NM–175–AD. E:\FR\FM\25JAP1.SGM 25JAP1 Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Proposed Rules Comments Due Date (a) The FAA must receive comments on this AD action by February 26, 2007. Affected ADs (b) This AD supersedes AD 2006–12–02. 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 prevent electrical arcing in the fuel tank boost pump motor, which in the presence of a combustible air-fuel mixture in the fuel tank boost pump, 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. Restatement of Requirements of AD 2006– 12–02 ycherry on PROD1PC64 with PROPOSALS Part and Serial Number Inspection (f) Within 10 days after July 3, 2006 (the effective date of AD 2006–12–02), 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. Accomplishment of the inspection or records review as specified in Airbus Service Bulletin A320–28–1152, dated May 5, 2006; or Revision 01, dated July 17, 2006; is one approved method for conducting this inspection or records 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 (j) 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 FRHITEMP 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, until the modification required by paragraph (h) of this AD has been done. (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: VerDate Aug<31>2005 13:34 Jan 24, 2007 Jkt 211001 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.’’ (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. 3373 Previous Accomplishment (i) Modification of a fuel pump before the effective date of this AD in accordance with Airbus Service Bulletin A320–28–1153, dated May 5, 2006, is acceptable for compliance with the requirements of paragraph (h) of this AD for that pump only. Parts Installation (j) As of the effective date of this AD, no person may install a boost pump, P/N 568– 1–27202–005, having any S/N 6137 and subsequent, on any airplane, unless the boost pump has been modified in accordance with this AD. Alternative Methods of Compliance (AMOCs) (k)(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 (l) European Aviation Safety Agency airworthiness directive 2006–0222, dated July 20, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on January 12, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–1093 Filed 1–24–07; 8:45 am] BILLING CODE 4910–13–P New Requirements of This AD Terminating Action (h) For airplanes equipped with one or more Eaton Aerospace Limited (formerly FRHITEMP Limited) fuel boost pumps, having P/N 568–1–27202–005 with S/N 6137 and subsequent: At the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, either modify or replace affected fuel boost pumps in accordance with Airbus Service Bulletin A320–28–1153, Revision 01, dated July 13, 2006. Modification or replacement of all affected fuel tank boost pumps on an airplane terminates the requirements of paragraph (g) of 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. (1) For the center tank fuel pumps: Within 1,000 flight hours or 3 months after the effective date of this AD, whichever occurs first. (2) For the wing tank fuel pumps: Within 2,000 flight hours or 6 months after the effective date of this AD, whichever occurs first. Note 1: Airbus Service Bulletin A320–28– 1153 refers to Eaton Service Bulletin 8410– 28–04, dated May 2, 2006, as an additional source of service information for the fuel pump modification. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27010; Directorate Identifier 2006–NM–259–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 Airplanes; Model A310 Airplanes; and Model A300 B4–600, B4–600R, and F4–600R Series Airplanes, and Model C4–605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes) Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all Airbus Model A300 airplanes and Model A310 airplanes, and certain Airbus Model E:\FR\FM\25JAP1.SGM 25JAP1

Agencies

[Federal Register Volume 72, Number 16 (Thursday, January 25, 2007)]
[Proposed Rules]
[Pages 3371-3373]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-1093]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / 
Proposed Rules

[[Page 3371]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27011; Directorate Identifier 2006-NM-175-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318, A319, A320, and A321 
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to all Airbus Model A318, A319, A320, and 
A321 airplanes. The existing AD currently 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. The 
existing AD also provides for optional terminating action for 
compliance with the revisions to the AFM and the maintenance program. 
This proposed AD would require modifying or replacing the fuel tank 
boost pumps, which would allow removal of the limitations from the AFM 
and the maintenance program. This proposed 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 proposing this AD to prevent electrical arcing in the fuel tank 
boost pump motor, which, in the presence of a combustible air-fuel 
mixture in the pump, could result in an explosion and loss of the 
airplane.

DATES: We must receive comments on this proposed AD by February 26, 
2007.

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

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2007-27011; Directorate Identifier 2006-NM-175-AD'' at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of the 
proposed AD. We will consider all comments received by the closing date 
and may amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to 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 proposed AD. Using the search function of 
that web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit 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.

Discussion

    On June 7, 2006, we issued AD 2006-12-02, amendment 39-14626 (71 FR 
34814, June 16, 2006), for all Airbus Model A318, A319, A320, and A321 
airplanes. That 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. That AD also provides for optional 
terminating action for compliance with the revisions to the AFM and the 
maintenance program. That AD resulted 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 issued that 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.

Actions Since Existing AD Was Issued

    We considered AD 2006-12-02 interim action and were considering 
further rulemaking if final action were later identified. We now have 
determined that further rulemaking is necessary, and this proposed AD 
follows from that determination. Airbus has developed a modification to 
prevent the screws from coming loose and

[[Page 3372]]

issued new service information that addresses the identified unsafe 
condition.

Relevant Service Information

    Airbus has issued the following service bulletins:

                            Service Bulletins
------------------------------------------------------------------------
      Airbus Service Bulletin        Revision             Date
------------------------------------------------------------------------
A320-28-1152......................   Original  May 5, 2006.
                                           01  July 17, 2006.
A320-28-1153......................         01  July 13, 2006.
------------------------------------------------------------------------

    Service Bulletin A320-28-1152 describes procedures for determining 
the type, part number, and serial number of the fuel pumps of the wing 
and center tanks by either checking airplane records or inspecting the 
pump amendment label. The service bulletin recommends modifying 
affected fuel pumps in accordance with Service Bulletin A320-28-1153. 
Service Bulletin A320-28-1153 describes procedures for modifying the 
affected fuel pumps by replacing the nuts and bolts from the gas return 
outlet with new nuts and bolts, applying the correct torque to the 
nuts, and applying locktite adhesive, or replacing affected pumps with 
pumps having a serial number other than 6137 and subsequent.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The European 
Aviation Safety Agency (EASA), which is the aviation authority for the 
European Union, mandated the service information and issued 
airworthiness directive 2006-0222, dated July 20, 2006, to ensure the 
continued airworthiness of these airplanes in the European Union.
    Service Bulletin A320-28-1153 refers to Eaton Service Bulletin 
8410-28-04, dated May 2, 2006, as an additional source of service 
information for the modification.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
Sec.  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 
airplanes of this type design that are certificated for operation in 
the United States.
    This proposed AD would supersede AD 2006-12-02 and would retain the 
requirements and provisions of the existing AD. This proposed AD would 
also require modifying affected fuel pumps, which would allow removal 
of the limitations from the AFM and the maintenance program.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD. The parts manufacturer states that it 
will modify the pump free of charge.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                        Number of
                                               Average                    Cost per        U.S.-
           Action              Work hours    labor rate       Parts       airplane     registered    Fleet cost
                                              per hour                                  airplanes
----------------------------------------------------------------------------------------------------------------
Identify boost pumps, as                1           $80          None           $80           727       $58,160
 required by AD 2006-12-02..
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14626 (71 FR 34814, June 16, 2006) and adding the 
following new airworthiness directive (AD):
Airbus: Docket No. FAA-2007-27011; Directorate Identifier 2006-NM-
175-AD.

[[Page 3373]]

Comments Due Date

    (a) The FAA must receive comments on this AD action by February 
26, 2007.

Affected ADs

    (b) This AD supersedes AD 2006-12-02.

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 prevent electrical arcing in the fuel tank boost pump motor, 
which in the presence of a combustible air-fuel mixture in the fuel 
tank boost pump, 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.

Restatement of Requirements of AD 2006-12-02

Part and Serial Number Inspection

    (f) Within 10 days after July 3, 2006 (the effective date of AD 
2006-12-02), 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. 
Accomplishment of the inspection or records review as specified in 
Airbus Service Bulletin A320-28-1152, dated May 5, 2006; or Revision 
01, dated July 17, 2006; is one approved method for conducting this 
inspection or records 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 (j) 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, until the modification required by paragraph (h) of this 
AD has been done.
    (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.''
    (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.

New Requirements of This AD

Terminating Action

    (h) 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: At the applicable time 
specified in paragraph (h)(1) or (h)(2) of this AD, either modify or 
replace affected fuel boost pumps in accordance with Airbus Service 
Bulletin A320-28-1153, Revision 01, dated July 13, 2006. 
Modification or replacement of all affected fuel tank boost pumps on 
an airplane terminates the requirements of paragraph (g) of 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.
    (1) For the center tank fuel pumps: Within 1,000 flight hours or 
3 months after the effective date of this AD, whichever occurs 
first.
    (2) For the wing tank fuel pumps: Within 2,000 flight hours or 6 
months after the effective date of this AD, whichever occurs first.

    Note 1: Airbus Service Bulletin A320-28-1153 refers to Eaton 
Service Bulletin 8410-28-04, dated May 2, 2006, as an additional 
source of service information for the fuel pump modification.

Previous Accomplishment

    (i) Modification of a fuel pump before the effective date of 
this AD in accordance with Airbus Service Bulletin A320-28-1153, 
dated May 5, 2006, is acceptable for compliance with the 
requirements of paragraph (h) of this AD for that pump only.

Parts Installation

    (j) As of the effective date of this AD, no person may install a 
boost pump, P/N 568-1-27202-005, having any S/N 6137 and subsequent, 
on any airplane, unless the boost pump has been modified in 
accordance with this AD.

Alternative Methods of Compliance (AMOCs)

    (k)(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

    (l) European Aviation Safety Agency airworthiness directive 
2006-0222, dated July 20, 2006, also addresses the subject of this 
AD.

    Issued in Renton, Washington, on January 12, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-1093 Filed 1-24-07; 8:45 am]
BILLING CODE 4910-13-P