Airworthiness Directives; Airbus Model A300 B4-600R and A300 F4-600R Series Airplanes, 5620-5623 [E6-1418]

Download as PDF 5620 Proposed Rules Federal Register Vol. 71, No. 22 Thursday, February 2, 2006 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. Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6450; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20691; Directorate Identifier 2004–NM–249–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 757–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Proposed rule; withdrawal. hsrobinson on PROD1PC71 with PROPOSALS AGENCY: SUMMARY: The FAA withdraws a notice of proposed rulemaking (NPRM) that proposed a new airworthiness directive (AD) for certain Boeing Model 757–200 and –300 series airplanes. The proposed AD would have required inspecting for the part number, the serial number, and the mark ‘‘RETESTED’’ on the reaction link of the main landing gear (MLG), and replacing the reaction link of the MLG with a retested reaction link if necessary. Since the proposed AD was issued, we have received new data that all suspect reaction links of the MLG have been replaced with acceptable reaction links, and the suspect reaction links have been sent back to the reaction link manufacturer. Accordingly, the proposed AD is withdrawn. ADDRESSES: 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 U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Washington, DC. This docket number is FAA–2005–20691; the directorate identifier for this docket is 2004–NM– 249–AD. FOR FURTHER INFORMATION CONTACT: Dennis Stremick, Aerospace Engineer, VerDate Aug<31>2005 15:25 Feb 01, 2006 Jkt 208001 We proposed to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) with a notice of proposed rulemaking (NPRM) for a new AD for certain Boeing Model 757–200 and –300 series airplanes. That NPRM was published in the Federal Register on March 23, 2005 (70 FR 14585). The NPRM would have required inspecting for the part number, the serial number, and the mark ‘‘RETESTED’’ on the reaction link of the main landing gear (MLG), and replacing the reaction link of the MLG with a retested reaction link if necessary. The NPRM resulted from a report of faulty welds in certain reaction links. The proposed actions were intended to prevent failure of the reaction link, collapse of the MLG, and consequently, loss of control on the ground and possible damage to the airplane. Actions Since NPRM Was Issued Since we issued the NPRM, we have received confirmation that, world-wide, all suspect reaction links of the MLG have been replaced with acceptable reaction links, and the suspect reaction links have been sent back to the reaction link manufacturer. FAA’s Conclusions Upon further consideration, we have determined that the suspect reaction links are not installed on any airplane and have been altered in such a way as to be impossible to be reinstalled on an airplane. Accordingly, the NPRM is withdrawn. Withdrawal of the NPRM does not preclude the FAA from issuing another related action or commit the FAA to any course of action in the future. Regulatory Impact Since this action only withdraws an NPRM, it is neither a proposed nor a final rule and therefore is not covered under Executive Order 12866, the Regulatory Flexibility Act, or DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Withdrawal Accordingly, we withdraw the NPRM, Docket No. FAA–2005–20691, Directorate Identifier 2004–NM–249– AD, which was published in the Federal Register on March 23, 2005 (70 FR 14585). Issued in Renton, Washington, on January 24, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–1415 Filed 2–1–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23760; Directorate Identifier 2005–NM–211–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B4–600R and A300 F4–600R 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 certain Airbus Model A300 B4–600R and A300 F4–600R series airplanes. The existing AD requires repetitive inspections for damage of the center tank fuel pumps and fuel pump canisters and replacement of any damaged parts, and mandates modification of the canisters of the center tank fuel pumps, which terminates the repetitive inspections. For certain airplanes, this proposed AD would require a one-time inspection of the attachment bolts of the outlet flange of the canisters of the center tank fuel pumps for bolts that are too short and do not protrude through the nut, and replacement of the bolts if necessary. This proposed AD results from several reports that the attachment bolts for the canisters, modified by the requirements in the existing AD, are too short and do E:\FR\FM\02FEP1.SGM 02FEP1 Federal Register / Vol. 71, No. 22 / Thursday, February 2, 2006 / Proposed Rules not fully protrude from the nuts. We are proposing this AD to prevent damage to the fuel pump and fuel pump canister, which could result in loss of flame trap capability and could provide a fuel ignition source in the center fuel tank. DATES: We must receive comments on this proposed AD by March 6, 2006. 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: Thomas Stafford, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: hsrobinson on PROD1PC71 with PROPOSALS 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–2006–23760; Directorate Identifier 2005–NM–211– 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, VerDate Aug<31>2005 15:25 Feb 01, 2006 Jkt 208001 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 November 1, 2004, we issued AD 2004–23–08, amendment 39–13863 (69 FR 65528, November 15, 2004), for certain Airbus Model A300 B4–600R and A300 F4–600R series airplanes. That AD superseded AD 99–27–07, amendment 39–11488 (65 FR 213, January 4, 2000), to mandate modification of the canisters of the center tank fuel pumps, which would terminate the repetitive inspections required by AD 99–27–07. AD 2004–23– 08 resulted from the issuance of a new French airworthiness directive, 2002– 132(B), dated March 20, 2002, which mandated the modification. We issued that AD to prevent damage to the fuel pump and fuel pump canister, which could result in loss of flame trap capability and could provide a fuel ignition source in the center fuel tank. Actions Since Existing AD Was Issued Since we issued AD 2004–23–08, the Direction Gonorale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, advises that it has received several reports that the attachment bolts for the canisters, modified by the requirements in the existing French AD, are too short and do not fully protrude from the nuts. In light of these findings, the DGAC has issued French airworthiness directive F–2005– 147, dated August 17, 2005. French airworthiness directive F–2005–147 adds a one-time inspection for bolts that are too short and do not protrude from the nut, and replacement of the bolts if necessary. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 5621 Relevant Service Information Airbus has issued Service Bulletin A300–28–6069, Revision 02, dated October 17, 2003. For airplanes on which the modification specified in the original issue or Revision 01 of the service bulletin has been accomplished, Revision 02 includes additional work. That additional work involves a onetime inspection of the attachment bolts of the outlet flange of the canisters of the center tank fuel pumps for bolts that are too short and do not protrude from the nut, and replacement of the bolts if necessary. Airbus has also issued Service Bulletin A300–28–6087, dated April 8, 2005, for airplanes on which Airbus Service Bulletin A300–28–6069, dated September 4, 2001, or Revision 01, dated May 28, 2002, has been accomplished. The service bulletin describes procedures for a one-time inspection of the attachment bolts of the outlet flange of the canisters of the center tank fuel pumps for bolts that are too short and do not protrude from the nut, and replacement of the bolts if necessary. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DGAC mandated the service information and issued French airworthiness directive F–2005–147, dated August 17, 2005, to ensure the continued airworthiness of these airplanes in France. FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. We have examined the DGAC’s findings, evaluated all pertinent information, and determined that AD action is necessary for airplanes of this type design that are certificated for operation in the United States. This proposed AD would supersede AD 2004–23–08 and would continue to require repetitive inspections for damage of the center tank fuel pumps and fuel pump canisters and replacement of any damaged parts, and modification of the canisters of the center tank fuel pumps, which terminates the repetitive inspections. For certain airplanes, this proposed AD would also require a one-time E:\FR\FM\02FEP1.SGM 02FEP1 5622 Federal Register / Vol. 71, No. 22 / Thursday, February 2, 2006 / Proposed Rules inspection of the attachment bolts of the outlet flange of the canisters of the center tank fuel pumps for bolts that are too short and do not protrude through the nut, and replacement of the bolts if necessary. Difference Between Proposed AD and French Airworthiness Directive The applicability of the French airworthiness directive excludes airplanes on which Airbus Service Bulletin A300–28–6069, Revision 2, or A300–28–6087 were accomplished in service. However, we have not excluded those airplanes in the applicability of this proposed AD; rather, this proposed AD would include a requirement to accomplish the actions specified in those service bulletins. This proposed requirement would ensure that the actions specified in those service bulletins are accomplished on all affected airplanes. Operators must continue to operate the airplane in the configuration required by this proposed AD unless an alternative method of compliance is approved. Clarification of Inspection Terminology In this proposed AD, the ‘‘inspection’’ specified in the service bulletins is referred to as a ‘‘detailed inspection.’’ Change to Existing AD This proposed AD would retain the requirements of the existing AD. Since AD 2004–23–08 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: REVISED PARAGRAPH IDENTIFIERS Requirement in AD 2004–23–08 hsrobinson on PROD1PC71 with PROPOSALS Paragraph Paragraph Paragraph Paragraph (a) (b) (c) (d) ............ ............ ............ ............ Corresponding requirement in this proposed AD Paragraph Paragraph Paragraph Paragraph (f). (g). (h). (i). Clarification of Alternative Method of Compliance (AMOC) Paragraph We have revised this action to clarify the appropriate procedure for notifying the principal inspector before using any approved AMOC on any airplane to which the AMOC applies. Costs of Compliance This proposed AD would affect about 101 airplanes of U.S. registry. The inspections that are required by AD 99–27–07, and retained in this proposed AD, take about 2 work hours VerDate Aug<31>2005 15:25 Feb 01, 2006 Jkt 208001 per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the currently required inspections is $130 per airplane, per inspection cycle. The modification that is required by AD 2004–23–08, and retained in this proposed AD, takes about 2 work hours per airplane, at an average labor rate of $65 per work hour. Required parts will cost about $9,620 per airplane. Based on these figures, the estimated cost of the currently required modification is $9,750 per airplane. The new proposed one-time inspection would take about 1 work hour per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the new inspection specified in this proposed AD for U.S. operators is $6,565 or $65 per airplane. 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. 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. 1. The authority citation for part 39 continues to read as follows: 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 PO 00000 Frm 00003 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 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–13863 (69 FR 65528, November 15, 2004) and adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2006–23760; Directorate Identifier 2005–NM–211–AD. Comments Due Date (a) The FAA must receive comments on this AD action by March 6, 2006. Affected ADs (b) This AD supersedes AD 2004–23–08. Applicability (c) This AD applies to Airbus Model A300 B4–605R and B4–622R airplanes, and A300 F4–605R and F4–622R airplanes; certificated in any category; on which Airbus Modification 4801 has been accomplished; except airplanes on which Airbus Modification 12314 has been installed in production. Unsafe Condition (d) This AD results from several reports that the attachment bolts for the canisters, modified by the requirements in the existing AD, are too short and do not fully protrude from the nuts. We are issuing this AD to prevent damage to the fuel pump and fuel pump canister, which could result in loss of flame trap capability and could provide a fuel ignition source in the center fuel tank. 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. E:\FR\FM\02FEP1.SGM 02FEP1 Federal Register / Vol. 71, No. 22 / Thursday, February 2, 2006 / Proposed Rules 5623 Restatement of Requirements of AD 2004– 23–08 A300–28–6061, Revision 04, dated August 1, 2002. DEPARTMENT OF TRANSPORTATION Inspections (f) Prior to the accumulation of 5,000 total hours’ time-in-service or within 250 hours’ time-in-service after February 8, 2000 (the effective date of AD 99–27–07, (superseded by AD 2004–23–08) amendment 39–11488), whichever occurs later, perform a detailed inspection for damage of the center tank fuel pumps and fuel pump canisters, in accordance with Airbus All Operators Telex (AOT) 28–09, dated November 28, 1998. Repeat the inspection prior to the accumulation of 12,000 total hours’ time-inservice, or within 250 hours’ time-in-service after accomplishment of the initial inspection, whichever occurs later. Thereafter, repeat the inspection at intervals not to exceed 250 hours’ time-in-service, until accomplishment of the initial inspection required by paragraph (g) of this AD. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Modification Federal Aviation Administration (i) Within 18 months after December 20, 2004 (the effective date of AD 2004–23–08): Modify the canisters of the center tank fuel pumps (including an operational test) by doing all the actions in accordance with paragraphs 3.A., 3.B., 3.C., and 3.D. of the Accomplishment Instructions of Airbus Service Bulletin A300–28–6069, dated September 4, 2001; Revision 01, dated May 28, 2002; or Revision 02, dated October 17, 2003. After the effective date of this AD, Revision 02 of the service bulletin must be used for accomplishing the modification. Accomplishing this modification ends the repetitive inspections required by paragraph (g) of this AD. 14 CFR Part 39 hsrobinson on PROD1PC71 with PROPOSALS (g) At the applicable time specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD: Perform a detailed inspection to detect damage of the center tank fuel pumps and perform an eddy current inspection to detect damage of the fuel pump canisters, in accordance with Airbus Alert Service Bulletin A300–28A6061, dated February 19, 1999; or Airbus Service Bulletin A300–28– 6061, Revision 04, dated August 1, 2002. Repeat the inspections thereafter at intervals not to exceed 1,500 flight cycles, until accomplishment of paragraph (i) of this AD. Accomplishment of the inspection required by this paragraph constitutes terminating action for the requirements of paragraph (f) of this AD. (1) For airplanes that have accumulated 11,000 or more total flight cycles as of February 8, 2000: Inspect within 300 flight cycles after February 8, 2000. (2) For airplanes that have accumulated 8,500 or more total flight cycles, but fewer than 11,000 total flight cycles, as of February 8, 2000: Inspect within 750 flight cycles after February 8, 2000. (3) For airplanes that have accumulated fewer than 8,500 total flight cycles as of February 8, 2000: Inspect prior to the accumulation of 7,000 flight cycles, or within 1,500 flight cycles after February 8, 2000, whichever occurs later. Corrective Action (h) If any damage is detected during any inspection required by this AD, prior to further flight, replace the damaged fuel pump or fuel pump canister with a new or serviceable part in accordance with Airbus Alert Service Bulletin A300–28A6061, dated February 19, 1999; or Airbus Service Bulletin VerDate Aug<31>2005 15:25 Feb 01, 2006 Jkt 208001 New Requirements of This AD One-Time Inspection/Replacement if Necessary (j) For airplanes on which Airbus Service Bulletin A300–28–6069, dated September 4, 2001, or Revision 01, dated May 28, 2002, has been accomplished before the effective date of this AD: Within 18 months after the effective date of this AD, perform a one-time detailed inspection of the attachment bolts of the outlet flange of the canisters of the center tank fuel pumps for bolts that are too short and do not protrude through the nut, and replace the bolts as applicable, by doing all the actions in accordance with paragraphs 3.A., 3.B., 3.C., 3.D., and 3.E. of the Accomplishment Instructions of Airbus Service Bulletin A300–28–6087, dated April 8, 2005. Do any applicable bolt replacement before further flight. 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. (3) AMOCs approved previously in accordance with AD 2004–23–08 are approved as AMOCs for the corresponding provisions of this AD. Related Information (l) French airworthiness directive F–2005– 147, dated August 17, 2005, also addresses the subject of this AD. Issued in Renton, Washington, on January 25, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–1418 Filed 2–1–06; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 [Docket No. FAA–2006–23762; Directorate Identifier 2005–NM–226–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 767 airplanes. This proposed AD would require repetitive inspections for cracking in the skin, the bulkhead outer chord, and the strap of the bulkhead outer chord at station (STA) 1725.5; and repair if necessary. This proposed AD also provides for repairs, which are optional for airplanes on which no cracking is found, that terminate certain inspections. This proposed AD results from reports of cracking in the skin panel common to stringer 7R and aft of the STA 1725.5 butt splice, and in the strap of the bulkhead outer chord at STA 1725.5. We are proposing this AD to detect and correct cracking in the skin, the bulkhead outer chord, or the strap of the bulkhead outer chord in this area, which could progress into surrounding areas and result in reduced structural integrity of the support structure for the vertical or horizontal stabilizer and subsequent loss of control of the airplane. We must receive comments on this proposed AD by March 20, 2006. 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. DATES: E:\FR\FM\02FEP1.SGM 02FEP1

Agencies

[Federal Register Volume 71, Number 22 (Thursday, February 2, 2006)]
[Proposed Rules]
[Pages 5620-5623]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-1418]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23760; Directorate Identifier 2005-NM-211-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-600R and A300 F4-
600R Series 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 certain Airbus Model A300 B4-600R and 
A300 F4-600R series airplanes. The existing AD requires repetitive 
inspections for damage of the center tank fuel pumps and fuel pump 
canisters and replacement of any damaged parts, and mandates 
modification of the canisters of the center tank fuel pumps, which 
terminates the repetitive inspections. For certain airplanes, this 
proposed AD would require a one-time inspection of the attachment bolts 
of the outlet flange of the canisters of the center tank fuel pumps for 
bolts that are too short and do not protrude through the nut, and 
replacement of the bolts if necessary. This proposed AD results from 
several reports that the attachment bolts for the canisters, modified 
by the requirements in the existing AD, are too short and do

[[Page 5621]]

not fully protrude from the nuts. We are proposing this AD to prevent 
damage to the fuel pump and fuel pump canister, which could result in 
loss of flame trap capability and could provide a fuel ignition source 
in the center fuel tank.

DATES: We must receive comments on this proposed AD by March 6, 2006.

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: Thomas Stafford, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2006-23760; Directorate Identifier 2005-NM-211-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 November 1, 2004, we issued AD 2004-23-08, amendment 39-13863 
(69 FR 65528, November 15, 2004), for certain Airbus Model A300 B4-600R 
and A300 F4-600R series airplanes. That AD superseded AD 99-27-07, 
amendment 39-11488 (65 FR 213, January 4, 2000), to mandate 
modification of the canisters of the center tank fuel pumps, which 
would terminate the repetitive inspections required by AD 99-27-07. AD 
2004-23-08 resulted from the issuance of a new French airworthiness 
directive, 2002-132(B), dated March 20, 2002, which mandated the 
modification. We issued that AD to prevent damage to the fuel pump and 
fuel pump canister, which could result in loss of flame trap capability 
and could provide a fuel ignition source in the center fuel tank.

Actions Since Existing AD Was Issued

    Since we issued AD 2004-23-08, the Direction Gonorale de l'Aviation 
Civile (DGAC), which is the airworthiness authority for France, advises 
that it has received several reports that the attachment bolts for the 
canisters, modified by the requirements in the existing French AD, are 
too short and do not fully protrude from the nuts. In light of these 
findings, the DGAC has issued French airworthiness directive F-2005-
147, dated August 17, 2005. French airworthiness directive F-2005-147 
adds a one-time inspection for bolts that are too short and do not 
protrude from the nut, and replacement of the bolts if necessary.

Relevant Service Information

    Airbus has issued Service Bulletin A300-28-6069, Revision 02, dated 
October 17, 2003. For airplanes on which the modification specified in 
the original issue or Revision 01 of the service bulletin has been 
accomplished, Revision 02 includes additional work. That additional 
work involves a one-time inspection of the attachment bolts of the 
outlet flange of the canisters of the center tank fuel pumps for bolts 
that are too short and do not protrude from the nut, and replacement of 
the bolts if necessary.
    Airbus has also issued Service Bulletin A300-28-6087, dated April 
8, 2005, for airplanes on which Airbus Service Bulletin A300-28-6069, 
dated September 4, 2001, or Revision 01, dated May 28, 2002, has been 
accomplished. The service bulletin describes procedures for a one-time 
inspection of the attachment bolts of the outlet flange of the 
canisters of the center tank fuel pumps for bolts that are too short 
and do not protrude from the nut, and replacement of the bolts if 
necessary.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The DGAC mandated 
the service information and issued French airworthiness directive F-
2005-147, dated August 17, 2005, to ensure the continued airworthiness 
of these airplanes in France.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede AD 2004-23-08 and would continue 
to require repetitive inspections for damage of the center tank fuel 
pumps and fuel pump canisters and replacement of any damaged parts, and 
modification of the canisters of the center tank fuel pumps, which 
terminates the repetitive inspections. For certain airplanes, this 
proposed AD would also require a one-time

[[Page 5622]]

inspection of the attachment bolts of the outlet flange of the 
canisters of the center tank fuel pumps for bolts that are too short 
and do not protrude through the nut, and replacement of the bolts if 
necessary.

Difference Between Proposed AD and French Airworthiness Directive

    The applicability of the French airworthiness directive excludes 
airplanes on which Airbus Service Bulletin A300-28-6069, Revision 2, or 
A300-28-6087 were accomplished in service. However, we have not 
excluded those airplanes in the applicability of this proposed AD; 
rather, this proposed AD would include a requirement to accomplish the 
actions specified in those service bulletins. This proposed requirement 
would ensure that the actions specified in those service bulletins are 
accomplished on all affected airplanes. Operators must continue to 
operate the airplane in the configuration required by this proposed AD 
unless an alternative method of compliance is approved.

Clarification of Inspection Terminology

    In this proposed AD, the ``inspection'' specified in the service 
bulletins is referred to as a ``detailed inspection.''

Change to Existing AD

    This proposed AD would retain the requirements of the existing AD. 
Since AD 2004-23-08 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                             Corresponding  requirement
       Requirement in AD 2004-23-08             in this  proposed AD
------------------------------------------------------------------------
Paragraph (a).............................  Paragraph (f).
Paragraph (b).............................  Paragraph (g).
Paragraph (c).............................  Paragraph (h).
Paragraph (d).............................  Paragraph (i).
------------------------------------------------------------------------

Clarification of Alternative Method of Compliance (AMOC) Paragraph

    We have revised this action to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.

Costs of Compliance

    This proposed AD would affect about 101 airplanes of U.S. registry.
    The inspections that are required by AD 99-27-07, and retained in 
this proposed AD, take about 2 work hours per airplane, at an average 
labor rate of $65 per work hour. Based on these figures, the estimated 
cost of the currently required inspections is $130 per airplane, per 
inspection cycle.
    The modification that is required by AD 2004-23-08, and retained in 
this proposed AD, takes about 2 work hours per airplane, at an average 
labor rate of $65 per work hour. Required parts will cost about $9,620 
per airplane. Based on these figures, the estimated cost of the 
currently required modification is $9,750 per airplane.
    The new proposed one-time inspection would take about 1 work hour 
per airplane, at an average labor rate of $65 per work hour. Based on 
these figures, the estimated cost of the new inspection specified in 
this proposed AD for U.S. operators is $6,565 or $65 per airplane.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-13863 (69 FR 65528, November 15, 2004) and adding 
the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2006-23760; Directorate Identifier 2005-NM-
211-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by March 6, 
2006.

Affected ADs

    (b) This AD supersedes AD 2004-23-08.

Applicability

    (c) This AD applies to Airbus Model A300 B4-605R and B4-622R 
airplanes, and A300 F4-605R and F4-622R airplanes; certificated in 
any category; on which Airbus Modification 4801 has been 
accomplished; except airplanes on which Airbus Modification 12314 
has been installed in production.

Unsafe Condition

    (d) This AD results from several reports that the attachment 
bolts for the canisters, modified by the requirements in the 
existing AD, are too short and do not fully protrude from the nuts. 
We are issuing this AD to prevent damage to the fuel pump and fuel 
pump canister, which could result in loss of flame trap capability 
and could provide a fuel ignition source in the center fuel tank.

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.

[[Page 5623]]

Restatement of Requirements of AD 2004-23-08

Inspections

    (f) Prior to the accumulation of 5,000 total hours' time-in-
service or within 250 hours' time-in-service after February 8, 2000 
(the effective date of AD 99-27-07, (superseded by AD 2004-23-08) 
amendment 39-11488), whichever occurs later, perform a detailed 
inspection for damage of the center tank fuel pumps and fuel pump 
canisters, in accordance with Airbus All Operators Telex (AOT) 28-
09, dated November 28, 1998. Repeat the inspection prior to the 
accumulation of 12,000 total hours' time-in-service, or within 250 
hours' time-in-service after accomplishment of the initial 
inspection, whichever occurs later. Thereafter, repeat the 
inspection at intervals not to exceed 250 hours' time-in-service, 
until accomplishment of the initial inspection required by paragraph 
(g) of this AD.

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


    (g) At the applicable time specified in paragraph (g)(1), 
(g)(2), or (g)(3) of this AD: Perform a detailed inspection to 
detect damage of the center tank fuel pumps and perform an eddy 
current inspection to detect damage of the fuel pump canisters, in 
accordance with Airbus Alert Service Bulletin A300-28A6061, dated 
February 19, 1999; or Airbus Service Bulletin A300-28-6061, Revision 
04, dated August 1, 2002. Repeat the inspections thereafter at 
intervals not to exceed 1,500 flight cycles, until accomplishment of 
paragraph (i) of this AD. Accomplishment of the inspection required 
by this paragraph constitutes terminating action for the 
requirements of paragraph (f) of this AD.
    (1) For airplanes that have accumulated 11,000 or more total 
flight cycles as of February 8, 2000: Inspect within 300 flight 
cycles after February 8, 2000.
    (2) For airplanes that have accumulated 8,500 or more total 
flight cycles, but fewer than 11,000 total flight cycles, as of 
February 8, 2000: Inspect within 750 flight cycles after February 8, 
2000.
    (3) For airplanes that have accumulated fewer than 8,500 total 
flight cycles as of February 8, 2000: Inspect prior to the 
accumulation of 7,000 flight cycles, or within 1,500 flight cycles 
after February 8, 2000, whichever occurs later.

Corrective Action

    (h) If any damage is detected during any inspection required by 
this AD, prior to further flight, replace the damaged fuel pump or 
fuel pump canister with a new or serviceable part in accordance with 
Airbus Alert Service Bulletin A300-28A6061, dated February 19, 1999; 
or Airbus Service Bulletin A300-28-6061, Revision 04, dated August 
1, 2002.

Modification

    (i) Within 18 months after December 20, 2004 (the effective date 
of AD 2004-23-08): Modify the canisters of the center tank fuel 
pumps (including an operational test) by doing all the actions in 
accordance with paragraphs 3.A., 3.B., 3.C., and 3.D. of the 
Accomplishment Instructions of Airbus Service Bulletin A300-28-6069, 
dated September 4, 2001; Revision 01, dated May 28, 2002; or 
Revision 02, dated October 17, 2003. After the effective date of 
this AD, Revision 02 of the service bulletin must be used for 
accomplishing the modification. Accomplishing this modification ends 
the repetitive inspections required by paragraph (g) of this AD.

New Requirements of This AD

One-Time Inspection/Replacement if Necessary

    (j) For airplanes on which Airbus Service Bulletin A300-28-6069, 
dated September 4, 2001, or Revision 01, dated May 28, 2002, has 
been accomplished before the effective date of this AD: Within 18 
months after the effective date of this AD, perform a one-time 
detailed inspection of the attachment bolts of the outlet flange of 
the canisters of the center tank fuel pumps for bolts that are too 
short and do not protrude through the nut, and replace the bolts as 
applicable, by doing all the actions in accordance with paragraphs 
3.A., 3.B., 3.C., 3.D., and 3.E. of the Accomplishment Instructions 
of Airbus Service Bulletin A300-28-6087, dated April 8, 2005. Do any 
applicable bolt replacement before further flight.

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.
    (3) AMOCs approved previously in accordance with AD 2004-23-08 
are approved as AMOCs for the corresponding provisions of this AD.

Related Information

    (l) French airworthiness directive F-2005-147, dated August 17, 
2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on January 25, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-1418 Filed 2-1-06; 8:45 am]
BILLING CODE 4910-13-P