Airworthiness Directives; Airbus Model A300 Airplanes; and Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes), 19818-19823 [E7-7516]

Download as PDF 19818 Federal Register / Vol. 72, No. 76 / Friday, April 20, 2007 / Proposed Rules Development. Written instructions will be provided to the applicant or grantee by USDA Rural Development when review or appeal rights are applicable in accordance with 7 CFR part 11. §§ 4284.195–4284.200 [Reserved] Dated: March 29, 2007. Thomas C. Dorr, Under Secretary, Rural Development. [FR Doc. 07–1922 Filed 4–19–07; 8:45 am] BILLING CODE 3410–XY–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27926; Directorate Identifier 2006–NM–050–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 Airplanes; and Airbus 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). cprice-sewell on PRODPC61 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all Airbus Model A300 B2 and B4 series airplanes; and Model A300 B4–600, B4–600R, and F4–600R (collectively called A300–600) series airplanes. The existing AD currently requires repetitive inspections to detect cracking of the upper radius of the forward fitting of frame 47, and repair if necessary. This proposed AD would reduce inspection thresholds and repetitive intervals, and add related investigative and corrective actions. This proposed AD also would provide an optional terminating action for the repetitive inspections only for airplanes with cracking that is within certain limits. This proposed AD results from reports of additional cracking in airplanes that were inspected in accordance with the existing AD. We are proposing this AD to detect and correct fatigue cracking of the left and right upper radius at frame 47, which could propagate and result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by May 21, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. VerDate Aug<31>2005 15:15 Apr 19, 2007 Jkt 211001 • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Thomas Stafford, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; 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–2007–27926; Directorate Identifier 2006–NM–050– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion On March 18, 2003, we issued AD 2003–06–04, amendment 39–13091 (68 FR 14894, March 27, 2003), for all Airbus Model A300 B2 and B4 series airplanes, and Model A300 B4–600, B4– 600R, and F4–600R (collectively called A300–600) series airplanes. That AD requires repetitive inspections to detect cracking of the upper radius of the forward fitting of frame 47, and repair if necessary. That AD resulted from issuance of mandatory continuing airworthiness information by a civil airworthiness authority. We issued that AD to detect and correct such fatigue cracking, which could result in propagation of the cracking to the rear fitting and reduced structural integrity of fuselage frame 47. Actions Since Existing AD Was Issued Since we issued AD 2003–06–04, cracks were found on the left and right upper radius at frame 47 at 48,000 simulated flights, and at 18,000 total flights on an in-service airplane. Inservice experience up to 2001 showed there was no propagation of cracking between 30 millimeters (mm) and 40 mm in size. In mid-2001, a crack of 110 mm in size was found on a scrapped Model A300 B4–200 airplane with 23,700 total flights. Further sampling inspections revealed two Model A300 airplanes with cracks greater in size than the defined limit of 50 mm. Based on these last investigation results, Airbus established a revised inspection program that: • Redefines the threshold and repetitive interval values; and • Introduces corrective measures in the event of abnormal load events (e.g., hard landing and flight with turbulence). Definitions of abnormal load events are in the applicable airplane maintenance manual. Relevant Service Information Airbus has issued the service bulletins described in the following table. E:\FR\FM\20APP1.SGM 20APP1 19819 Federal Register / Vol. 72, No. 76 / Friday, April 20, 2007 / Proposed Rules AIRBUS SERVICE BULLETINS Service bulletin type For model A300 airplanes For model A300–600 series airplanes Inspection service bulletins ................................ A300–53–0246, Revision 06, including Appendix 01, dated October 19, 2005. A300–53–0370, including Appendix 01, dated July 16, 2004. A300–53–6029, Revision 08, including Appendix 01, dated October 19, 2005. A300–53–6144, including Appendix 01, dated July 16, 2004. results from Airbus, described above, and establish a revised inspection program. The inspection service bulletins specify reporting all inspection results to Airbus. The inspection service bulletins describe procedures for repetitive eddy current inspections to detect cracking of the upper radius of the forward fitting of frame 47, and applicable related investigative and corrective actions, as described in the following table. Optional terminating service bulletins ................ The inspection service bulletins are newer revisions of the service bulletins that were referenced as the appropriate sources of service information for accomplishing the actions required by AD 2003–06–04. The newer revisions take into account the latest investigation RELATED INVESTIGATIVE AND CORRECTIVE ACTIONS FOLLOWING EDDY CURRENT INSPECTION Finding or occurrence Corrective action Related investigative action No crack ............................................................. Modify the fairing attachment profile by cutting and removing the fairing attachment profile between frame 47 and frame 48, and trimming the keel beam at frame 47. This action is specified only after the first eddy current inspection. Contact Airbus for repair instructions .............. Eddy current inspection for cracking of the upper radius (after the keel beam has been trimmed and while the attachment profile is removed). More than one crack .......................................... Crack less than or equal to 8 mm in size .......... Crack greater than 8 mm in size, but less than or equal to 20 mm in size. Crack greater than 20 mm in size, but less than or equal to 50 mm in size. Crack greater than 50 mm in size ...................... Abnormal load event on an airplane with any crack finding. As noted in the table above, the repetitive intervals for the special detailed inspection vary according to Do the repetitive eddy current inspection at a reduced interval. Remove, modify, and reinstall the sealing fitting and sealing shim. This action is specified only after the first eddy current inspection with a crack finding of this size. Do the repetitive eddy current inspection at a reduced interval. Contact Airbus for repair instructions if any crack is found during the detailed visual inspection; if no further cracking is found, do the repetitive eddy current inspection at a reduced interval. Repair in accordance with the optional terminating service bulletins and contact Airbus for repair instructions. Report the event to Airbus and do the next repetitive eddy current inspection within 3 months after the event; or, if the first eddy current inspection has not yet been done, contact Airbus before further flight. the crack finding. The following table is a summary of the repetitive intervals Detailed visual inspection for cracking of the aft fitting around the fasteners. None. Ultrasonic inspection for cracking of the forward fitting. Detailed visual inspection for cracking of the aft fitting around the fasteners. None. None. given in Figure 1, Sheet 1, of the inspection service bulletins. REPETITIVE INTERVALS BASED ON CRACK FINDING Finding Repetitive interval cprice-sewell on PRODPC61 with PROPOSALS No crack ................................................................................................................................................................................... Crack less than or equal to 30 mm ......................................................................................................................................... Crack greater than 30 mm but less than or equal to 40 mm ................................................................................................. Crack greater than 40 mm but less than or equal to 50 mm ................................................................................................. The optional terminating service bulletins apply only if a crack is greater than 30 mm but less than or equal to 50 mm in size. The optional terminating service bulletins specify contacting VerDate Aug<31>2005 15:15 Apr 19, 2007 Jkt 211001 Airbus for repair instructions, special tooling, and the use of trained personnel for accomplishing the repair because of the high risk of serious damage to the frame 47 forward fitting, which could PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 4,150 flight cycles. 1,400 flight cycles. 750 flight cycles. 250 flight cycles. lead to a repair beyond the economical limit. Accomplishing the actions specified in the service information is intended to adequately address the unsafe E:\FR\FM\20APP1.SGM 20APP1 19820 Federal Register / Vol. 72, No. 76 / Friday, April 20, 2007 / Proposed Rules ´ ´ condition. The Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, mandated the service information and issued French airworthiness directive F–2006–016, dated January 18, 2006, 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 2003–06–04, and would continue to require repetitive inspections to detect cracking of the upper radius of the forward fitting of frame 47, and repair if necessary. This proposed AD would also continue to require the report to Airbus that was required by the existing AD. This proposed AD would reduce inspection thresholds and repetitive intervals, and add related investigative and corrective actions. This proposed AD also would provide an optional terminating action for the repetitive inspections only for airplanes with cracking that is within certain limits. This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Among the Proposed AD, the Service Information, and the French Airworthiness Directive.’’ cprice-sewell on PRODPC61 with PROPOSALS Differences Among the Proposed AD, the Service Information, and the French Airworthiness Directive The inspection service bulletins referenced by the French airworthiness directive specify contacting Airbus for certain instructions. This proposed AD would require doing those actions according to a method that we or the European Aviation Safety Agency (EASA) (or its delegated agent) approve. In light of the actions that would be required to address the unsafe condition, and consistent with existing bilateral airworthiness agreements, we have determined that, for this proposed AD, a method we or the EASA approve would be acceptable for compliance with this proposed AD. The French airworthiness directive does not specify repair instructions for crack findings of greater than 50 mm, and the inspection service bulletins specify doing actions in the optional terminating service bulletins and contacting Airbus for repair instructions. This proposed AD would instead require repairing those conditions using a method that we approve. Where the optional terminating service bulletins specify sending a geometrical plan to Airbus after doing the repair, this proposed AD would require providing a post-repair inspection program to us for approval within 6 months after doing the repair. These differences have been coordinated with EASA. Flight With Cracking Operators should note that this proposed AD permits further flight with cracking within certain limits. While it is not the FAA’s policy to allow flight with known cracking, we have determined that, for the purposes of this proposed AD, repair may be deferred for certain crack lengths. In making this determination, we considered that longterm continued operational safety in this case will be adequately ensured by repetitive inspections to detect cracking before it represents a hazard to the airplane, and by repair if the crack exceeds the specified limit. We also considered that cracks that are less than 30 mm in size are not physically accessible and would require removing frame 47 to repair, which is not economically viable. The proposed inspection program will mitigate any safety concerns for cracks of this size. Cracks of 30 mm to 50 mm in size are also acceptable for flight, but this proposed AD would require a more rigorous inspection program for cracks of this size. If operators strictly observe the crack size limits and perform repetitive inspections at required intervals, operators can detect any cracks that grow beyond the limits and take corrective action before the crack size creates an unacceptable risk of structural failure. The DGAC concurs with these findings. In consideration of these findings and the FAA’s criteria for flight with known cracking, further flight with cracking within certain limits is permissible for an interim period in this case. Changes to Existing AD This proposed AD would retain certain requirements of AD 2003–06–04. Since AD 2003–06–04 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 in this proposed AD Requirement in AD 2003–06–04 Paragraph Paragraph Paragraph Paragraph Paragraph (a) (b) (c) (d) (e) ............ ............ ............ ............ ............ paragraph paragraph paragraph paragraph paragraph (f). (g). (h). (i). (q). We have also clarified the applicability of the proposed AD in the following ways: • To match more closely the applicability of the parallel French airworthiness directive. • To identify model designations as published in the most recent type certificate data sheet for the affected models. We have revised this proposed AD to clarify the appropriate procedure for notifying the principal inspector before using any approved alternative method of compliance (AMOC) on any airplane to which the AMOC applies. Costs of Compliance There are about 163 U.S.-registered airplanes that would be affected by this proposed AD. The following table provides the estimated costs for U.S. operators to comply with this proposed AD. The average labor rate is $80 per work hour. ESTIMATED COSTS Work hours Action Actions required by AD 2003–06–04 .. Inspection (new proposed action) ....... VerDate Aug<31>2005 15:15 Apr 19, 2007 Jkt 211001 Parts 9 1 PO 00000 $0 0 Frm 00014 Cost per airplane $720, per inspection cycle .................. $80, per inspection cycle .................... Fmt 4702 Sfmt 4702 E:\FR\FM\20APP1.SGM Fleet cost $117,360, per inspection cycle. $13,040, per inspection cycle. 20APP1 Federal Register / Vol. 72, No. 76 / Friday, April 20, 2007 / Proposed 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 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. cprice-sewell on PRODPC61 with PROPOSALS 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: VerDate Aug<31>2005 15:15 Apr 19, 2007 Jkt 211001 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–13091 (68 FR 14894, March 27, 2003) and adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2007–27926; Directorate Identifier 2006–NM–050–AD. Comments Due Date (a) The FAA must receive comments on this AD action by May 21, 2007. Affected ADs (b) This AD supersedes AD 2003–06–04. Applicability (c) This AD applies to all Airbus Model A300 airplanes; and all Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 622R, F4–605R, F4–622R, and C4–605R Variant F airplanes; certificated in any category. Unsafe Condition (d) This AD results from reports of additional cracking in airplanes that were inspected in accordance with AD 2003–06– 04. We are issuing this AD to detect and correct fatigue cracking of the left and right upper radius at frame 47, which could propagate and result in reduced structural integrity 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. Requirements of AD 2003–06–04 Model A300–600: Inspection (f) For Model A300–600 series airplanes: At the earlier of the times specified by paragraphs (f)(1) and (f)(2) of this AD, perform an eddy current inspection to detect cracking of the upper radius of the left and right forward fitting of frame 47, in accordance with Airbus Service Bulletin A300–53–6029, Revision 02, dated November 7, 1994; Revision 05, dated April 11, 2001; or Revision 08, including Appendix 01, dated October 19, 2005. After the effective date of this AD, only Revision 08 of the service bulletin may be used. (1) Before the accumulation of 17,300 total flight cycles, or within one year after October 16, 1996 (the effective date of AD 96–18–18, amendment 39–9744), whichever occurs later. (2) At the later of the times specified by paragraphs (f)(2)(i) and (f)(2)(ii) of this AD. (i) Before the accumulation of 10,000 total flight cycles or 26,000 total flight hours, whichever occurs first. (ii) Within 750 flight cycles or 1,900 flight hours, whichever occurs first after May 1, 2003 (the effective date of AD 2003–06–04). Model A300–600: Follow-On (Repetitive) Inspections (g) For Model A300–600 series airplanes on which no cracking is found during any PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 19821 inspection required by paragraph (f) of this AD, repeat the inspection required by paragraph (f) of this AD at the applicable times specified in paragraphs (g)(1) and (g)(2) of this AD until the inspection required by paragraph (j) of this AD is done. (1) If the initial inspection was accomplished before May 1, 2003, repeat the inspection at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. Thereafter, repeat the inspection at intervals not to exceed 6,100 flight cycles or 15,600 flight hours, whichever occurs first. (i) Re-inspect within 6,100 flight cycles after the initial inspection. (ii) Re-inspect within 750 flight cycles or 1,900 flight hours, whichever occurs first after May 1, 2003. (2) If the initial inspection was not accomplished before May 1, 2003, repeat the inspection thereafter at intervals not to exceed 6,100 flight cycles or 15,600 flight hours, whichever occurs first. Model A300–600: Corrective Action (h) For Model A300–600 series airplanes on which any cracking is found during any inspection required by paragraph (f) of this AD: Before further flight, contact the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate; or the ´ ´ Direction Generale de l’Aviation Civile (DGAC) (or its delegated representative), or the European Aviation Safety Agency (EASA) (or its delegated agent); for instructions regarding repair or for an applicable reinspection interval, in accordance with Airbus Service Bulletin A300–52–6029, Revision 05, dated April 11, 2001; or Revision 08, including Appendix 01, dated October 19, 2005. After the effective date of this AD, only Revision 08 may be used. Repair and/or re-inspection accomplished before May 1, 2003, in accordance with a method approved by the Manager, International Branch, ANM–116, is acceptable for compliance with the requirements of paragraph (h) of this AD. Model A300 B2 and B4: Repetitive Inspections and Follow-On Actions (i) For Model A300 B2 and B4 series airplanes: At the applicable time specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, perform repetitive eddy current inspections to detect cracking of the upper radius of the forward fitting of frame 47, left and right sides, per Airbus Service Bulletin A300–53– 0246, Revision 03, dated April 11, 2001; or Revision 06, including Appendix 01, dated October 19, 2005. After the effective date of this AD, only Revision 06 may be used. Accomplishing this requirement terminates the corresponding inspection requirement of the A300 Supplemental Structural Inspection Document (SSID) for Model A300 B2 and B4 series airplanes. (That SSID is mandated by AD 96–13–11, amendment 39–9679.) (1) For Model A300 B2 series airplanes: Perform the initial inspection at the later of the times specified by paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. Repeat the inspection thereafter at intervals not to exceed 10,400 flight cycles or 13,300 flight hours, whichever occurs first, until the inspection in paragraph (j) of this AD is done. E:\FR\FM\20APP1.SGM 20APP1 19822 Federal Register / Vol. 72, No. 76 / Friday, April 20, 2007 / Proposed Rules (i) Before the accumulation of 16,500 total flight cycles or 21,000 total flight hours, whichever occurs first. (ii) Within 1,000 flight cycles or 1,300 flight hours after May 1, 2003, whichever occurs first. (2) For Model A300 B4–100 series airplanes: Perform the initial inspection at the later of the times specified by paragraphs (i)(2)(i) and (i)(2)(ii) of this AD. Repeat the inspection thereafter at intervals not to exceed 8,500 flight cycles or 16,400 flight hours, whichever occurs first, until the inspection in paragraph (j) of this AD is done. (i) Before the accumulation of 10,300 total flight cycles or 19,800 total flight hours, whichever occurs first. (ii) Within 750 flight cycles or 1,500 flight hours after May 1, 2003, whichever occurs first. (3) For Model A300 B4–200 series airplanes: Perform the initial inspection at the later of the times specified by paragraphs (i)(3)(i) and (i)(3)(ii) of this AD. Repeat the inspection thereafter at intervals not to exceed 7,000 flight cycles or 13,600 flight hours, whichever occurs first, until the inspection in paragraph (j) of this AD is done. (i) Before the accumulation of 11,000 total flight cycles or 21,200 total flight hours, whichever occurs first. (ii) Within 750 flight cycles or 1,500 flight hours after May 1, 2003, whichever occurs first. cprice-sewell on PRODPC61 with PROPOSALS New Requirements of This AD Inspections and Corrective Actions (j) At the applicable time in paragraph (k) or (l) of this AD: Except as provided by paragraphs (n) and (p) of this AD, do an eddy current inspection to detect cracking of the upper radius of the forward fitting of frame 47, and do all applicable related investigative and corrective actions, by accomplishing all the applicable actions specified in the Accomplishment Instructions of the applicable service bulletin specified in paragraph (j)(1) or (j)(2) of this AD. Do all applicable investigative and corrective actions before further flight. Where the service bulletins specify to contact Airbus for repair instructions: Before further flight, repair using a method approved by either the Manager, International Branch, ANM–116; or the EASA (or its delegated agent). Doing the inspections required by this paragraph terminates the inspections required by paragraphs (f), (g), and (i) of this AD. (1) For Airbus Model A300 airplanes: Airbus Service Bulletin A300–53–0246, Revision 06, including Appendix 01, dated October 19, 2005. (2) For Airbus Model A300 B4–601, B4– 603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and C4–605R Variant F airplanes: Airbus Service Bulletin A300–53– 6029, Revision 08, including Appendix 01, dated October 19, 2005. (k) For airplanes on which the inspection required by paragraph (f), (g), or (i) of this AD, as applicable, has not been done prior to the effective date of this AD: Do the initial inspection required by paragraph (j) of this VerDate Aug<31>2005 15:15 Apr 19, 2007 Jkt 211001 AD before the accumulation of 10,000 total flight cycles, or within 1,400 flight cycles after the effective date of this AD, whichever occurs later. Repeat the inspection thereafter at the applicable interval specified in Figure 1, Sheet 1, of the Accomplishment Instructions of the applicable service bulletin. (l) For airplanes on which the inspection required by paragraph (f), (g), or (i) of this AD, as applicable, has been done prior to the effective date of this AD: Inspect at the applicable times specified in paragraph (l)(1) or (l)(2) of this AD. Repeat the inspection thereafter at the applicable interval specified in Figure 1, Sheet 1, of the Accomplishment Instructions of the applicable service bulletin. (1) For airplanes on which no cracking was found during any inspection required by this AD: Do the next inspection at the earlier of the times specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD. (i) At the next repetitive interval specified in the applicable service bulletin specified in paragraph (j)(1) or (j)(2) of this AD, or within 1,400 flight cycles after the effective date of this AD, whichever occurs later. (ii) At the next repetitive interval specified in paragraph (g) or (i) of this AD, as applicable. (2) For airplanes on which any crack was found during any inspection required by this AD, and the crack is 30 millimeters (mm) (1.181 inch) or less in length: Do the next inspection at the applicable times specified in paragraph (l)(2)(i) or (l)(2)(ii) of this AD. (i) For Airbus Model A300 airplanes: At the next repetitive interval specified in the service bulletin specified in paragraph (j)(1) of this AD, or within 500 flight cycles after the effective date of this AD, whichever occurs later. (ii) Airbus Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4– 605R, F4–622R, and C4–605R Variant F airplanes: At the next repetitive interval specified in the service bulletin specified in paragraph (j)(2) of this AD. Abnormal Load Events (m) For airplanes on which any abnormal load event occurs after the effective date of this AD, do the actions in paragraph (m)(1), (m)(2), or (m)(3) of this AD, as applicable, at the time specified in the applicable paragraph. (1) Within 3 months after the event, or at the next applicable repetitive interval required by paragraph (k) or (l) of this AD, whichever occurs first: Do the next repetitive inspection required by paragraph (j) of this AD. (2) Before further flight following any additional abnormal load event that occurs following the first event but before the next repetitive inspection required by paragraph (k) or (l) of this AD: Contact the Manager, International Branch, ANM–116, or the EASA (or its delegated agent) for further instructions. (3) Within 3 months after any abnormal load event: Report the event to Airbus in accordance with the requirements of paragraph (q) of this AD. PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 Optional Terminating Action (Repair) for Certain Cracks (n) Repairing any crack greater than 30 mm but less than or equal to 50 mm in size in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–0370, including Appendix 01, dated July 16, 2004; or Airbus Service Bulletin A300– 53–6144, including Appendix 01, dated July 16, 2004; as applicable; terminates the repetitive inspection requirements of paragraph (k) or (l) of this AD for that area only. Where the service bulletins specify to contact Airbus for repair instructions: Repair the crack using a method approved by either the Manager, International Branch, ANM– 116; or the EASA (or its delegated agent). Repetitive Inspections Following Optional Terminating Action (o) Within 6 months after repair in accordance with paragraph (n) of this AD: Submit a post-repair inspection program for monitoring the repair to the Manager, International Branch, ANM–116, for approval. Repair of Any Crack Greater than 50 mm in Size (p) If any crack that is greater than 50 mm in size is found during any inspection required by paragraph (j), (k), or (l) of this AD: Before further flight, repair according to a method approved by the Manager, International Branch, ANM–116. Reporting Requirement (q) At the applicable time specified in paragraph (q)(1) or (q)(2) of this AD: Submit a report of all results of each inspection required by this AD to Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, Attention: Jacques Leborgne, fax 33– 5–61–93–36–14. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. Information collection requirements contained in this AD have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120–0056. (1) For airplanes on which the inspection is accomplished after the effective date of this AD: Submit the report within 30 days after performing the inspection. (2) For airplanes on which the inspection has been accomplished before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. Actions Accomplished in Accordance With Previous Issues of Service Bulletins (r) Actions done before the effective date of this AD in accordance with the service bulletins listed in Table 1 of this AD are acceptable for compliance with the corresponding requirements of paragraphs (i) and (j) of this AD. E:\FR\FM\20APP1.SGM 20APP1 19823 Federal Register / Vol. 72, No. 76 / Friday, April 20, 2007 / Proposed Rules TABLE 1.—PREVIOUS ISSUES OF SERVICE BULLETINS Airbus Service Bulletin Model A300 airplanes ...................................................................................... Revision level Date Alternative Methods of Compliance (AMOCs) (s)(1) The Manager, International Branch, ANM–116, 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 2003–06–04 are approved as AMOCs with this AD until paragraph (j) of this AD is accomplished. Related Information (t) French airworthiness directive F–2006– 016, dated January 18, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on April 12, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–7516 Filed 4–19–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27927; Directorate Identifier 2006–NM–182–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for all Airbus A300 series airplanes. This proposed AD would require revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This proposed AD results from fuel system cprice-sewell on PRODPC61 with PROPOSALS SUMMARY: VerDate Aug<31>2005 15:15 Apr 19, 2007 Jkt 211001 03 04 05 05 April 11, 2001. November 12, 2002. January 19, 2004. April 11, 2001. A300–53–6029 A300–53–6029 A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4– 605R, F4–622R, and C4–605R Variant F airplanes. A300–53–0246 A300–53–0246 A300–53–0246 A300–53–6029 06 07 November 12, 2002. January 19, 2004. reviews conducted by the manufacturer. We are proposing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors caused by latent failures, alterations, repairs, or maintenance actions, could result in fuel tank explosions and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by May 21, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2007–27927; Directorate Identifier 2006–NM–182–AD’’ at the beginning of your comments. We specifically invite comments on the PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection E:\FR\FM\20APP1.SGM 20APP1

Agencies

[Federal Register Volume 72, Number 76 (Friday, April 20, 2007)]
[Proposed Rules]
[Pages 19818-19823]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-7516]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27926; Directorate Identifier 2006-NM-050-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 Airplanes; and Airbus
Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-
605R Variant F Airplanes (Collectively Called A300-600 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 all Airbus Model A300 B2 and B4 series
airplanes; and Model A300 B4-600, B4-600R, and F4-600R (collectively
called A300-600) series airplanes. The existing AD currently requires
repetitive inspections to detect cracking of the upper radius of the
forward fitting of frame 47, and repair if necessary. This proposed AD
would reduce inspection thresholds and repetitive intervals, and add
related investigative and corrective actions. This proposed AD also
would provide an optional terminating action for the repetitive
inspections only for airplanes with cracking that is within certain
limits. This proposed AD results from reports of additional cracking in
airplanes that were inspected in accordance with the existing AD. We
are proposing this AD to detect and correct fatigue cracking of the
left and right upper radius at frame 47, which could propagate and
result in reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by May 21, 2007.

ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Thomas Stafford, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; 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-2007-27926; Directorate Identifier 2006-NM-050-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit https://dms.dot.gov.

Examining the Docket

You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.

Discussion

On March 18, 2003, we issued AD 2003-06-04, amendment 39-13091 (68
FR 14894, March 27, 2003), for all Airbus Model A300 B2 and B4 series
airplanes, and Model A300 B4-600, B4-600R, and F4-600R (collectively
called A300-600) series airplanes. That AD requires repetitive
inspections to detect cracking of the upper radius of the forward
fitting of frame 47, and repair if necessary. That AD resulted from
issuance of mandatory continuing airworthiness information by a civil
airworthiness authority. We issued that AD to detect and correct such
fatigue cracking, which could result in propagation of the cracking to
the rear fitting and reduced structural integrity of fuselage frame 47.

Actions Since Existing AD Was Issued

Since we issued AD 2003-06-04, cracks were found on the left and
right upper radius at frame 47 at 48,000 simulated flights, and at
18,000 total flights on an in-service airplane. In-service experience
up to 2001 showed there was no propagation of cracking between 30
millimeters (mm) and 40 mm in size. In mid-2001, a crack of 110 mm in
size was found on a scrapped Model A300 B4-200 airplane with 23,700
total flights. Further sampling inspections revealed two Model A300
airplanes with cracks greater in size than the defined limit of 50 mm.
Based on these last investigation results, Airbus established a revised
inspection program that:
Redefines the threshold and repetitive interval values;
and
Introduces corrective measures in the event of abnormal
load events (e.g., hard landing and flight with turbulence).
Definitions of abnormal load events are in the applicable airplane
maintenance manual.

Relevant Service Information

Airbus has issued the service bulletins described in the following
table.

[[Page 19819]]

Airbus Service Bulletins
------------------------------------------------------------------------
For model A300 For model A300-600
Service bulletin type airplanes series airplanes
------------------------------------------------------------------------
Inspection service bulletins A300-53-0246, A300-53-6029,
Revision 06, Revision 08,
including Appendix including Appendix
01, dated October 01, dated October
19, 2005. 19, 2005.
Optional terminating service A300-53-0370, A300-53-6144,
bulletins. including Appendix including Appendix
01, dated July 16, 01, dated July 16,
2004. 2004.
------------------------------------------------------------------------

The inspection service bulletins are newer revisions of the service
bulletins that were referenced as the appropriate sources of service
information for accomplishing the actions required by AD 2003-06-04.
The newer revisions take into account the latest investigation results
from Airbus, described above, and establish a revised inspection
program. The inspection service bulletins specify reporting all
inspection results to Airbus.
The inspection service bulletins describe procedures for repetitive
eddy current inspections to detect cracking of the upper radius of the
forward fitting of frame 47, and applicable related investigative and
corrective actions, as described in the following table.

Related Investigative and Corrective Actions Following Eddy Current
Inspection
------------------------------------------------------------------------
Related
Finding or occurrence Corrective action investigative action
------------------------------------------------------------------------
No crack.................... Modify the fairing Eddy current
attachment profile inspection for
by cutting and cracking of the
removing the upper radius (after
fairing attachment the keel beam has
profile between been trimmed and
frame 47 and frame while the
48, and trimming attachment profile
the keel beam at is removed).
frame 47. This
action is specified
only after the
first eddy current
inspection.
More than one crack......... Contact Airbus for Detailed visual
repair instructions. inspection for
cracking of the aft
fitting around the
fasteners.
Crack less than or equal to Do the repetitive None.
8 mm in size. eddy current
inspection at a
reduced interval.
Crack greater than 8 mm in Remove, modify, and Ultrasonic
size, but less than or reinstall the inspection for
equal to 20 mm in size. sealing fitting and cracking of the
sealing shim. This forward fitting.
action is specified
only after the
first eddy current
inspection with a
crack finding of
this size. Do the
repetitive eddy
current inspection
at a reduced
interval.
Crack greater than 20 mm in Contact Airbus for Detailed visual
size, but less than or repair instructions inspection for
equal to 50 mm in size. if any crack is cracking of the aft
found during the fitting around the
detailed visual fasteners.
inspection; if no
further cracking is
found, do the
repetitive eddy
current inspection
at a reduced
interval.
Crack greater than 50 mm in Repair in accordance None.
size. with the optional
terminating service
bulletins and
contact Airbus for
repair instructions.
Abnormal load event on an Report the event to None.
airplane with any crack Airbus and do the
finding. next repetitive
eddy current
inspection within 3
months after the
event; or, if the
first eddy current
inspection has not
yet been done,
contact Airbus
before further
flight.
------------------------------------------------------------------------

As noted in the table above, the repetitive intervals for the
special detailed inspection vary according to the crack finding. The
following table is a summary of the repetitive intervals given in
Figure 1, Sheet 1, of the inspection service bulletins.

Repetitive Intervals Based on Crack Finding
------------------------------------------------------------------------
Finding Repetitive interval
------------------------------------------------------------------------
No crack............................ 4,150 flight cycles.
Crack less than or equal to 30 mm... 1,400 flight cycles.
Crack greater than 30 mm but less 750 flight cycles.
than or equal to 40 mm.
Crack greater than 40 mm but less 250 flight cycles.
than or equal to 50 mm.
------------------------------------------------------------------------

The optional terminating service bulletins apply only if a crack is
greater than 30 mm but less than or equal to 50 mm in size. The
optional terminating service bulletins specify contacting Airbus for
repair instructions, special tooling, and the use of trained personnel
for accomplishing the repair because of the high risk of serious damage
to the frame 47 forward fitting, which could lead to a repair beyond
the economical limit.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe

[[Page 19820]]

condition. The Direction G[eacute]n[eacute]rale de l'Aviation Civile
(DGAC), which is the airworthiness authority for France, mandated the
service information and issued French airworthiness directive F-2006-
016, dated January 18, 2006, 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 2003-06-04, and would continue
to require repetitive inspections to detect cracking of the upper
radius of the forward fitting of frame 47, and repair if necessary.
This proposed AD would also continue to require the report to Airbus
that was required by the existing AD.
This proposed AD would reduce inspection thresholds and repetitive
intervals, and add related investigative and corrective actions. This
proposed AD also would provide an optional terminating action for the
repetitive inspections only for airplanes with cracking that is within
certain limits. This proposed AD would require accomplishing the
actions specified in the service information described previously,
except as discussed under ``Differences Among the Proposed AD, the
Service Information, and the French Airworthiness Directive.''

Differences Among the Proposed AD, the Service Information, and the
French Airworthiness Directive

The inspection service bulletins referenced by the French
airworthiness directive specify contacting Airbus for certain
instructions. This proposed AD would require doing those actions
according to a method that we or the European Aviation Safety Agency
(EASA) (or its delegated agent) approve. In light of the actions that
would be required to address the unsafe condition, and consistent with
existing bilateral airworthiness agreements, we have determined that,
for this proposed AD, a method we or the EASA approve would be
acceptable for compliance with this proposed AD.
The French airworthiness directive does not specify repair
instructions for crack findings of greater than 50 mm, and the
inspection service bulletins specify doing actions in the optional
terminating service bulletins and contacting Airbus for repair
instructions. This proposed AD would instead require repairing those
conditions using a method that we approve.
Where the optional terminating service bulletins specify sending a
geometrical plan to Airbus after doing the repair, this proposed AD
would require providing a post-repair inspection program to us for
approval within 6 months after doing the repair.
These differences have been coordinated with EASA.

Flight With Cracking

Operators should note that this proposed AD permits further flight
with cracking within certain limits. While it is not the FAA's policy
to allow flight with known cracking, we have determined that, for the
purposes of this proposed AD, repair may be deferred for certain crack
lengths. In making this determination, we considered that long-term
continued operational safety in this case will be adequately ensured by
repetitive inspections to detect cracking before it represents a hazard
to the airplane, and by repair if the crack exceeds the specified
limit.
We also considered that cracks that are less than 30 mm in size are
not physically accessible and would require removing frame 47 to
repair, which is not economically viable. The proposed inspection
program will mitigate any safety concerns for cracks of this size.
Cracks of 30 mm to 50 mm in size are also acceptable for flight,
but this proposed AD would require a more rigorous inspection program
for cracks of this size. If operators strictly observe the crack size
limits and perform repetitive inspections at required intervals,
operators can detect any cracks that grow beyond the limits and take
corrective action before the crack size creates an unacceptable risk of
structural failure.
The DGAC concurs with these findings. In consideration of these
findings and the FAA's criteria for flight with known cracking, further
flight with cracking within certain limits is permissible for an
interim period in this case.

Changes to Existing AD

This proposed AD would retain certain requirements of AD 2003-06-
04. Since AD 2003-06-04 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 2003-06-04 in this proposed AD
------------------------------------------------------------------------
Paragraph (a).............................. paragraph (f).
Paragraph (b).............................. paragraph (g).
Paragraph (c).............................. paragraph (h).
Paragraph (d).............................. paragraph (i).
Paragraph (e).............................. paragraph (q).
------------------------------------------------------------------------

We have also clarified the applicability of the proposed AD in the
following ways:
To match more closely the applicability of the parallel
French airworthiness directive.
To identify model designations as published in the most
recent type certificate data sheet for the affected models.
We have revised this proposed AD to clarify the appropriate
procedure for notifying the principal inspector before using any
approved alternative method of compliance (AMOC) on any airplane to
which the AMOC applies.

Costs of Compliance

There are about 163 U.S.-registered airplanes that would be
affected by this proposed AD. The following table provides the
estimated costs for U.S. operators to comply with this proposed AD. The
average labor rate is $80 per work hour.

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Work
Action hours Parts Cost per airplane Fleet cost
----------------------------------------------------------------------------------------------------------------
Actions required by AD 2003-06-04..... 9 $0 $720, per inspection $117,360, per inspection
cycle. cycle.
Inspection (new proposed action)...... 1 0 $80, per inspection $13,040, per inspection
cycle. cycle.
----------------------------------------------------------------------------------------------------------------

[[Page 19821]]

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 39-13091 (68 FR 14894, March 27, 2003) and adding
the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2007-27926; Directorate Identifier 2006-NM-
050-AD.

Comments Due Date

(a) The FAA must receive comments on this AD action by May 21,
2007.

Affected ADs

(b) This AD supersedes AD 2003-06-04.

Applicability

(c) This AD applies to all Airbus Model A300 airplanes; and all
Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-
605R, F4-622R, and C4-605R Variant F airplanes; certificated in any
category.

Unsafe Condition

(d) This AD results from reports of additional cracking in
airplanes that were inspected in accordance with AD 2003-06-04. We
are issuing this AD to detect and correct fatigue cracking of the
left and right upper radius at frame 47, which could propagate and
result in reduced structural integrity 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.

Requirements of AD 2003-06-04

Model A300-600: Inspection

(f) For Model A300-600 series airplanes: At the earlier of the
times specified by paragraphs (f)(1) and (f)(2) of this AD, perform
an eddy current inspection to detect cracking of the upper radius of
the left and right forward fitting of frame 47, in accordance with
Airbus Service Bulletin A300-53-6029, Revision 02, dated November 7,
1994; Revision 05, dated April 11, 2001; or Revision 08, including
Appendix 01, dated October 19, 2005. After the effective date of
this AD, only Revision 08 of the service bulletin may be used.
(1) Before the accumulation of 17,300 total flight cycles, or
within one year after October 16, 1996 (the effective date of AD 96-
18-18, amendment 39-9744), whichever occurs later.
(2) At the later of the times specified by paragraphs (f)(2)(i)
and (f)(2)(ii) of this AD.
(i) Before the accumulation of 10,000 total flight cycles or
26,000 total flight hours, whichever occurs first.
(ii) Within 750 flight cycles or 1,900 flight hours, whichever
occurs first after May 1, 2003 (the effective date of AD 2003-06-
04).

Model A300-600: Follow-On (Repetitive) Inspections

(g) For Model A300-600 series airplanes on which no cracking is
found during any inspection required by paragraph (f) of this AD,
repeat the inspection required by paragraph (f) of this AD at the
applicable times specified in paragraphs (g)(1) and (g)(2) of this
AD until the inspection required by paragraph (j) of this AD is
done.
(1) If the initial inspection was accomplished before May 1,
2003, repeat the inspection at the later of the times specified in
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. Thereafter, repeat
the inspection at intervals not to exceed 6,100 flight cycles or
15,600 flight hours, whichever occurs first.
(i) Re-inspect within 6,100 flight cycles after the initial
inspection.
(ii) Re-inspect within 750 flight cycles or 1,900 flight hours,
whichever occurs first after May 1, 2003.
(2) If the initial inspection was not accomplished before May 1,
2003, repeat the inspection thereafter at intervals not to exceed
6,100 flight cycles or 15,600 flight hours, whichever occurs first.

Model A300-600: Corrective Action

(h) For Model A300-600 series airplanes on which any cracking is
found during any inspection required by paragraph (f) of this AD:
Before further flight, contact the Manager, International Branch,
ANM-116, FAA, Transport Airplane Directorate; or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated
representative), or the European Aviation Safety Agency (EASA) (or
its delegated agent); for instructions regarding repair or for an
applicable re-inspection interval, in accordance with Airbus Service
Bulletin A300-52-6029, Revision 05, dated April 11, 2001; or
Revision 08, including Appendix 01, dated October 19, 2005. After
the effective date of this AD, only Revision 08 may be used. Repair
and/or re-inspection accomplished before May 1, 2003, in accordance
with a method approved by the Manager, International Branch, ANM-
116, is acceptable for compliance with the requirements of paragraph
(h) of this AD.

Model A300 B2 and B4: Repetitive Inspections and Follow-On Actions

(i) For Model A300 B2 and B4 series airplanes: At the applicable
time specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD,
perform repetitive eddy current inspections to detect cracking of
the upper radius of the forward fitting of frame 47, left and right
sides, per Airbus Service Bulletin A300-53-0246, Revision 03, dated
April 11, 2001; or Revision 06, including Appendix 01, dated October
19, 2005. After the effective date of this AD, only Revision 06 may
be used. Accomplishing this requirement terminates the corresponding
inspection requirement of the A300 Supplemental Structural
Inspection Document (SSID) for Model A300 B2 and B4 series
airplanes. (That SSID is mandated by AD 96-13-11, amendment 39-
9679.)
(1) For Model A300 B2 series airplanes: Perform the initial
inspection at the later of the times specified by paragraphs
(i)(1)(i) and (i)(1)(ii) of this AD. Repeat the inspection
thereafter at intervals not to exceed 10,400 flight cycles or 13,300
flight hours, whichever occurs first, until the inspection in
paragraph (j) of this AD is done.

[[Page 19822]]

(i) Before the accumulation of 16,500 total flight cycles or
21,000 total flight hours, whichever occurs first.
(ii) Within 1,000 flight cycles or 1,300 flight hours after May
1, 2003, whichever occurs first.
(2) For Model A300 B4-100 series airplanes: Perform the initial
inspection at the later of the times specified by paragraphs
(i)(2)(i) and (i)(2)(ii) of this AD. Repeat the inspection
thereafter at intervals not to exceed 8,500 flight cycles or 16,400
flight hours, whichever occurs first, until the inspection in
paragraph (j) of this AD is done.
(i) Before the accumulation of 10,300 total flight cycles or
19,800 total flight hours, whichever occurs first.
(ii) Within 750 flight cycles or 1,500 flight hours after May 1,
2003, whichever occurs first.
(3) For Model A300 B4-200 series airplanes: Perform the initial
inspection at the later of the times specified by paragraphs
(i)(3)(i) and (i)(3)(ii) of this AD. Repeat the inspection
thereafter at intervals not to exceed 7,000 flight cycles or 13,600
flight hours, whichever occurs first, until the inspection in
paragraph (j) of this AD is done.
(i) Before the accumulation of 11,000 total flight cycles or
21,200 total flight hours, whichever occurs first.
(ii) Within 750 flight cycles or 1,500 flight hours after May 1,
2003, whichever occurs first.

New Requirements of This AD

Inspections and Corrective Actions

(j) At the applicable time in paragraph (k) or (l) of this AD:
Except as provided by paragraphs (n) and (p) of this AD, do an eddy
current inspection to detect cracking of the upper radius of the
forward fitting of frame 47, and do all applicable related
investigative and corrective actions, by accomplishing all the
applicable actions specified in the Accomplishment Instructions of
the applicable service bulletin specified in paragraph (j)(1) or
(j)(2) of this AD. Do all applicable investigative and corrective
actions before further flight. Where the service bulletins specify
to contact Airbus for repair instructions: Before further flight,
repair using a method approved by either the Manager, International
Branch, ANM-116; or the EASA (or its delegated agent). Doing the
inspections required by this paragraph terminates the inspections
required by paragraphs (f), (g), and (i) of this AD.
(1) For Airbus Model A300 airplanes: Airbus Service Bulletin
A300-53-0246, Revision 06, including Appendix 01, dated October 19,
2005.
(2) For Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes:
Airbus Service Bulletin A300-53-6029, Revision 08, including
Appendix 01, dated October 19, 2005.
(k) For airplanes on which the inspection required by paragraph
(f), (g), or (i) of this AD, as applicable, has not been done prior
to the effective date of this AD: Do the initial inspection required
by paragraph (j) of this AD before the accumulation of 10,000 total
flight cycles, or within 1,400 flight cycles after the effective
date of this AD, whichever occurs later. Repeat the inspection
thereafter at the applicable interval specified in Figure 1, Sheet
1, of the Accomplishment Instructions of the applicable service
bulletin.
(l) For airplanes on which the inspection required by paragraph
(f), (g), or (i) of this AD, as applicable, has been done prior to
the effective date of this AD: Inspect at the applicable times
specified in paragraph (l)(1) or (l)(2) of this AD. Repeat the
inspection thereafter at the applicable interval specified in Figure
1, Sheet 1, of the Accomplishment Instructions of the applicable
service bulletin.
(1) For airplanes on which no cracking was found during any
inspection required by this AD: Do the next inspection at the
earlier of the times specified in paragraphs (l)(1)(i) and
(l)(1)(ii) of this AD.
(i) At the next repetitive interval specified in the applicable
service bulletin specified in paragraph (j)(1) or (j)(2) of this AD,
or within 1,400 flight cycles after the effective date of this AD,
whichever occurs later.
(ii) At the next repetitive interval specified in paragraph (g)
or (i) of this AD, as applicable.
(2) For airplanes on which any crack was found during any
inspection required by this AD, and the crack is 30 millimeters (mm)
(1.181 inch) or less in length: Do the next inspection at the
applicable times specified in paragraph (l)(2)(i) or (l)(2)(ii) of
this AD.
(i) For Airbus Model A300 airplanes: At the next repetitive
interval specified in the service bulletin specified in paragraph
(j)(1) of this AD, or within 500 flight cycles after the effective
date of this AD, whichever occurs later.
(ii) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R,
B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: At the
next repetitive interval specified in the service bulletin specified
in paragraph (j)(2) of this AD.

Abnormal Load Events

(m) For airplanes on which any abnormal load event occurs after
the effective date of this AD, do the actions in paragraph (m)(1),
(m)(2), or (m)(3) of this AD, as applicable, at the time specified
in the applicable paragraph.
(1) Within 3 months after the event, or at the next applicable
repetitive interval required by paragraph (k) or (l) of this AD,
whichever occurs first: Do the next repetitive inspection required
by paragraph (j) of this AD.
(2) Before further flight following any additional abnormal load
event that occurs following the first event but before the next
repetitive inspection required by paragraph (k) or (l) of this AD:
Contact the Manager, International Branch, ANM-116, or the EASA (or
its delegated agent) for further instructions.
(3) Within 3 months after any abnormal load event: Report the
event to Airbus in accordance with the requirements of paragraph (q)
of this AD.

Optional Terminating Action (Repair) for Certain Cracks

(n) Repairing any crack greater than 30 mm but less than or
equal to 50 mm in size in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-0370, including
Appendix 01, dated July 16, 2004; or Airbus Service Bulletin A300-
53-6144, including Appendix 01, dated July 16, 2004; as applicable;
terminates the repetitive inspection requirements of paragraph (k)
or (l) of this AD for that area only. Where the service bulletins
specify to contact Airbus for repair instructions: Repair the crack
using a method approved by either the Manager, International Branch,
ANM-116; or the EASA (or its delegated agent).

Repetitive Inspections Following Optional Terminating Action

(o) Within 6 months after repair in accordance with paragraph
(n) of this AD: Submit a post-repair inspection program for
monitoring the repair to the Manager, International Branch, ANM-116,
for approval.

Repair of Any Crack Greater than 50 mm in Size

(p) If any crack that is greater than 50 mm in size is found
during any inspection required by paragraph (j), (k), or (l) of this
AD: Before further flight, repair according to a method approved by
the Manager, International Branch, ANM-116.

Reporting Requirement

(q) At the applicable time specified in paragraph (q)(1) or
(q)(2) of this AD: Submit a report of all results of each inspection
required by this AD to Airbus, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France, Attention: Jacques Leborgne, fax 33-5-61-93-
36-14. The report must include the inspection results, a description
of any discrepancies found, the airplane serial number, and the
number of landings and flight hours on the airplane. Information
collection requirements contained in this AD have been approved by
the Office of Management and Budget (OMB) under the provisions of
the Paperwork Reduction Act (44 U.S.C. 3501 et seq.) and have been
assigned OMB Control Number 2120-0056.
(1) For airplanes on which the inspection is accomplished after
the effective date of this AD: Submit the report within 30 days
after performing the inspection.
(2) For airplanes on which the inspection has been accomplished
before the effective date of this AD: Submit the report within 30
days after the effective date of this AD.

Actions Accomplished in Accordance With Previous Issues of Service
Bulletins

(r) Actions done before the effective date of this AD in
accordance with the service bulletins listed in Table 1 of this AD
are acceptable for compliance with the corresponding requirements of
paragraphs (i) and (j) of this AD.

[[Page 19823]]

Table 1.--Previous Issues of Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300 airplanes.............................. A300-53-0246 03 April 11, 2001.
A300-53-0246 04 November 12, 2002.
A300-53-0246 05 January 19, 2004.
A300 B4-601, B4-603, B4-620, B4-622, B4- A300-53-6029 05 April 11, 2001.
605R, B4-622R, F4-605R, F4-622R, and C4-
605R Variant F airplanes.
A300-53-6029 06 November 12, 2002.
A300-53-6029 07 January 19, 2004.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

(s)(1) The Manager, International Branch, ANM-116, 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 2003-06-04
are approved as AMOCs with this AD until paragraph (j) of this AD is
accomplished.

Related Information

(t) French airworthiness directive F-2006-016, dated January 18,
2006, also addresses the subject of this AD.

Issued in Renton, Washington, on April 12, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-7516 Filed 4-19-07; 8:45 am]
BILLING CODE 4910-13-P

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