Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes), 28615-28619 [E6-7477]

Download as PDF Federal Register / Vol. 71, No. 95 / Wednesday, May 17, 2006 / Proposed Rules Service Bulletin References (f) The term ‘‘service bulletin,’’ as used in this AD, means the Accomplishment 28615 Instructions of the service bulletin identified in Table 1 of this AD, as applicable. TABLE 1.—SERVICE BULLETIN REFERENCES For Airbus— And the actions specified in— Model A300 airplanes ....................................................................... paragraph paragraph paragraph paragraph paragraph paragraph Airbus service bulletin— Dated— Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes; Model A300 B4–605R and B4–622R airplanes; Model A300 F4– 605R and F4–622R airplanes; and Model A300 C4–605R Variant F airplanes. mstockstill on PROD1PC61 with PROPOSALS Inspection and Corrective Actions (g) Within 59 months after the effective date of this AD: Do a general visual inspection of the right and left wing fuel tanks and center fuel tank, if applicable, to determine if any NSA5516–XXND and NSA5516–XXNJ type P-clips are installed for retaining wiring and pipes in any tank, and do all applicable corrective actions before further flight after the inspection, by accomplishing all the actions specified in the service bulletin. Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ Installation of Bonding Leads and Points for Wing and Center Fuel Tanks (h) Within 59 months after the effective date of this AD: Do the actions specified in paragraphs (h)(1) and (h)(2) of this AD, by accomplishing all the actions specified in the service bulletin. (1) In the center fuel tank, if applicable, do a general visual inspection of the electrical bonding points of the equipment identified in the service bulletin for the presence of a blue coat, and do all related investigative and corrective actions before further flight after the inspection. (2) In the left and right wing fuel tanks and center fuel tank, if applicable, install bonding leads and electrical bonding points on the equipment identified in the service bulletin. Installation of Bonding Leads and Points for the Trim Fuel Tank (i) For Model A310 airplanes; Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes; Model A300 B4–605R and B4– VerDate Aug<31>2005 15:07 May 16, 2006 Jkt 208001 A300–28–0081 A300–28–0079 A310–28–2143 A310–28–2142 A310–28–2153 A300–28–6068 July 20, 2005. September 29, 2005. July 20, 2005. August 26, 2005. July 20, 2005. July 20, 2005. paragraph (h) of this AD ............. paragraph (i) of this AD .............. Model A310 airplanes ....................................................................... (g) of this AD ............. (h) of this AD ............. (g) of this AD ............. (h) of this AD ............. (i) of this AD .............. (g) of this AD ............. A300–28–6064 A300–28–6077 July 28, 2005. July 25, 2005. 622R airplanes; Model A300 F4–605R and F4–622R airplanes; and Model A300 C4– 605R Variant F airplanes; equipped with a trim fuel tank: Within 59 months after the effective date of this AD, install a new bonding lead(s) on the water drain system of the trim fuel tank and install electrical bonding points on the equipment identified in the service bulletin in the trim fuel tank, by accomplishing all the actions specified in the service bulletin, as applicable. Parts Installation (j) As of the effective date of this AD, no person may install any NSA5516–XXND or NSA5516–XXNJ type P-clip for retaining wiring and pipes in any wing, center, or trim fuel tank, on any airplane. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (l) French airworthiness directive F–2006– 031, dated February 1, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on May 8, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–7481 Filed 5–16–06; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00026 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23690; Directorate Identifier 2004–NM–133–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes; and Model A300 B4–600, B4–600R, and F4– 600R Series Airplanes, and Model C4– 605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes) Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: SUMMARY: The FAA is revising an earlier NPRM for an airworthiness directive (AD) that applies to certain Airbus Model A300 B2, A300 B4, and A300– 600 series airplanes. The original NPRM would have superseded two existing ADs. One AD currently requires an inspection for cracks of the lower outboard flange of gantry No. 4 in the main landing gear (MLG) bay area, and repair if necessary. The other AD currently requires, among other actions, repetitive inspections of the gantry lower flanges, and repair if necessary. The original NPRM proposed to require new repetitive inspections for cracks in the lower flange of certain gantries, and repair if necessary, which ends the existing inspection requirements. The original NPRM also provided for optional terminating actions for the new repetitive inspections. This new action revises the original NPRM by including additional airplanes that were excluded from the applicability. We are proposing E:\FR\FM\17MYP1.SGM 17MYP1 28616 Federal Register / Vol. 71, No. 95 / Wednesday, May 17, 2006 / Proposed Rules mstockstill on PROD1PC61 with PROPOSALS this supplemental NPRM to detect and correct fatigue cracks in the lower flanges of gantries 1 through 5 inclusive in the MLG bay area, which could result in reduced structural integrity of the fuselage, and consequent rapid decompression of the airplane. DATES: We must receive comments on this supplemental NPRM by June 12, 2006. 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. • Governmentwide 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, 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 proposal. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2006–23690; Directorate Identifier 2004–NM–133– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this supplemental NPRM. We will consider all comments received by the closing date and may amend this supplemental NPRM in light of those comments. We will post all comments submitted, 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 VerDate Aug<31>2005 15:07 May 16, 2006 Jkt 208001 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 ADDRESSES. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion The FAA issued a notice of proposed rulemaking (NPRM) (the ‘‘original NPRM’’) to amend 14 CFR part 39 to include an AD that supersedes AD 2003–26–10, amendment 39–13408 (69 FR 867, January 7, 2004), and AD 2004– 18–13, amendment 39–13792 (69 FR 55329, September 14, 2004). The original NPRM applied to certain Airbus Model A300 B2 and A300 B4 series airplanes; and Model A300 B4–600, B4– 600R, and F4–600R series airplanes, and Model C4–605R Variant F airplanes (collectively called A300–600 series airplanes). The original NPRM was published in the Federal Register on January 26, 2006 (71 FR 4313). The original NPRM proposed to continue to require an inspection for cracks of the lower outboard flange of gantry No. 4 in the main landing gear (MLG) bay area, and repair if necessary. The original NPRM also proposed to continue to require repetitive inspections of the gantry lower flanges, and repair if necessary. In addition, the original NPRM proposed to require new repetitive inspections for cracks in the lower flange of certain gantries, and repair if necessary, which ends the existing inspection requirements. The original NPRM also proposed optional terminating actions for the new repetitive inspections. Comments We have considered the following comment on the original NPRM. PO 00000 Frm 00027 Fmt 4702 Sfmt 4702 Request To Revise the Applicability Airbus requests that airplanes on which Airbus Modifications 13037 (Airbus Service Bulletins A300–53– 0380 and A300–53–6153) and 12413 (Airbus Service Bulletins A300–53– 0360 and A300–53–6132), as applicable, have been installed in service, and airplanes on which Airbus Modification 12924 has been incorporated in production be excluded from Table 1— Applicability of the original NPRM. The commenter states that the effectivity of French airworthiness directive F–2005– 091 R1, issued September 28, 2005, takes these modification into account, except for Airbus Modification 12924. The commenter states that the Direction ´ ´ Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, plans to revise French airworthiness directive F–2005–091 R1 to address Airbus Modification 12924. We do not agree with Airbus to exclude airplanes on which a particular modification or service bulletin has been accomplished in service. Paragraph (m) of this supplemental NPRM includes an optional terminating action for accomplishing the actions specified in Airbus Service Bulletin A300–53–0380, dated August 5, 2005; Airbus Service Bulletin A300–53–0360, dated May 3, 2002; Airbus Service Bulleitn A300–53–6132, dated February 5, 2002; or Airbus Service Bulletin A300–53–6153, dated August 24, 2005; as applicable. If an operator chooses to accomplish this optional terminating action, it must continue to operate the airplane in that configuration unless an alternative method of compliance is approved. Therefore, we have determined that excluding those airplanes from the applicability of this supplemental NPRM is not appropriate. This difference between French airworthiness directive F–2005–091 R1 and this supplemental NPRM has been coordinated with the DGAC. We also do not agree with the commenter to exclude airplanes on which Airbus Modification 12924 has been incorporated in production. We have confirmed with the DGAC that the omission of this modification in French airworthiness directive F–2005–091 R1 was an oversight. However, since the issuance of the original NPRM, we have determined that all combinations of the Airbus modifications specified in the effectivity of French airworthiness directive F–2005–091 R1 include an inservice service bulletin. Therefore, we have revised Table 1 of the applicability of this supplemental NPRM to not include any exceptions for E:\FR\FM\17MYP1.SGM 17MYP1 28617 Federal Register / Vol. 71, No. 95 / Wednesday, May 17, 2006 / Proposed Rules accomplishing those Airbus modifications. $80 per work hour. The cost impact information, below, reflects this increase in the specified hourly labor rate. FAA’s Determination and Proposed Requirements of the Supplemental NPRM The change to the applicability discussed above expands the scope of the original NPRM; therefore, we have determined that it is necessary to reopen Change to Labor Rate After the original NPRM was issued, we reviewed the figures we have used over the past several years to calculate AD costs to operators. To account for various inflationary costs in the airline industry, we find it necessary to increase the labor rate used in these calculations from $65 per work hour to the comment period to provide additional opportunity for public comment on this supplemental NPRM. This proposed AD would affect about 165 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this proposed AD. Not all actions must be completed on all airplanes. Costs of Compliance ESTIMATED COSTS FOR REQUIRED ACTIONS Average labor rate per hour Number of U.S.registered airplanes Parts Cost per airplane $80 None ................ $80 .................. 23 $1,840. 4 ............................ 80 None ................ $320 ................ 43 $13,760. 12 .......................... 80 None ................ 78 $74,880, per inspection cycle. 16 .......................... 80 None ................ $960, per inspection cycle. $1,280, per inspection cycle. 78 $99,840, per inspection cycle. Action Work hours One-time inspection (required by AD 2003–26–10). One-time inspection (required by AD 2004–18–13). Repetitive inspections (required by AD 2004–18–13). 1 ............................ Repetitive inspections (new proposed actions). Fleet cost ESTIMATED COSTS FOR OPTIONAL ACTIONS Average labor rate per hour Optional action Work hours Reinforcement specified in Airbus Service Bulletin A300–53–0380, dated August 5, 2005. 807 .......................... Reinforcement specified in Airbus Service Bulletin A300–53–6153, dated August 24, 2005. Reinforcement specified in Airbus Service Bulletin A300–53–0360, dated May 3, 2002. Reinforcement specified in Airbus Service Bulletin A300–53–6132, dated February 5, 2002. Parts Cost per airplane $80 Between $87,100 and $121,560 depending on kit purchased. 807 .......................... 80 Between $82,460 and $87,070 depending on kit purchased. Between 24 and 128 depending on airplane configuration. 109 .......................... 80 Between $250 and $1,000 depending on kit purchased. 80 Between $260 and $950 depending on kit purchased. Between $151,660 and $186,120 depending on airplane configuration. Between $147,020 and $151,630 depending on airplane configuration. Between $2,170 and $11,240 depending on airplane configuration. Between $8,980 and $9,670 depending on airplane configuration. mstockstill on PROD1PC61 with PROPOSALS 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 VerDate Aug<31>2005 15:07 May 16, 2006 Jkt 208001 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 PO 00000 Frm 00028 Fmt 4702 Sfmt 4702 Number of U.S.registered airplanes 23 120 23 120 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; E:\FR\FM\17MYP1.SGM 17MYP1 28618 Federal Register / Vol. 71, No. 95 / Wednesday, May 17, 2006 / Proposed Rules 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 supplemental NPRM 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. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendments 39–13408 (69 FR 867, January 7, 2004) and 39–13792 (69 FR 55329, September 14, 2004) and adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2006–23690; Directorate Identifier 2004–NM–133–AD. Comments Due Date (a) The FAA must receive comments on this AD action by June 12, 2006. Affected ADs (b) This AD supersedes ADs 2003–26–10 and 2004–18–13. Applicability (c) This AD applies to Airbus airplanes identified in Table 1 of this AD, certificated in any category. TABLE 1.—APPLICABILITY mstockstill on PROD1PC61 with PROPOSALS Affected Airbus airplanes (1) All Model A300 B2–1A, B2–1C, B2K–3C, and B2–203 airplanes (2) All Model A300 B4–2C, B4–103, and B4– 203 airplanes (3) All Model A300 B4–601, B4–603, B4– 620, and B4–622 airplanes (4) All Model A300 B4–605R and B4–622R airplanes (5) All Model A300 F4–605R and F4–622R airplanes (6) All Model A300 C4–605R Variant F airplanes VerDate Aug<31>2005 15:07 May 16, 2006 Jkt 208001 Unsafe Condition (d) This AD results from a report of a large fatigue crack along the outboard flange of beam No. 4. We are issuing this AD to detect and correct fatigue cracks in the lower flanges of the left and right gantries 1 through 5 inclusive in the main landing gear (MLG) bay area, which could result in reduced structural integrity of the fuselage, and consequent rapid decompression of the airplane. one-time ultrasonic inspection for cracking of the gantry lower flanges in the MLG bay area, in accordance with Airbus AOT 53–11, dated October 13, 1997. (1) If any cracking is detected, prior to further flight, repair in accordance with the AOT. (2) If no cracking is detected, no further action is required by this paragraph. 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. Repair (g) Repair any cracking found during the inspection required by paragraph (f) of this AD before further flight, per a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the Direction ´ ´ Generale de l’Aviation Civile (DGAC) (or its delegated agent). (i) For Model A300 B4–601, B4–603, B4– 605R, B4–620, B4–622R, C4–605R Variant F airplanes, and F4–605R airplanes, on which Airbus Modification 12169 has not been done in production: Perform the requirements of paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of this AD, in accordance with Airbus Service Bulletin A300–53–6128, dated March 5, 2001. (1) At the later of the times specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD, perform initial ultrasonic inspections or high frequency eddy current inspections (HFEC) for cracks of the lower flanges of gantries 3, 4, and 5 between fuselage frames FR47 and FR54, in accordance with the Accomplishment Instructions, including the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin. (i) In accordance with the thresholds specified in the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin; or (ii) Within 200 flight cycles after October 19, 2004 (the effective date AD 2004–18–13). (2) Perform repetitive ultrasonic inspections or high-frequency eddy current inspections for cracks of the lower flanges of gantries 3, 4, and 5 between fuselage frames FR47 and FR54, in accordance with the thresholds and Accomplishment Instructions, including the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin. (3) Perform repairs and reinforcements, in accordance with the thresholds and the Accomplishment Instructions, including the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin, except as specified in paragraph (i)(4) of this AD. (4) If a new crack is found during any action required by paragraph (i)(1), (i)(2), or (i)(3) of this AD and the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin specifies to contact Airbus for appropriate action: Prior to further flight, repair per a method approved by the Manager, International Branch, ANM– 116, or the DGAC (or its delegated agent). Restatement of Requirements of AD 2004– 18–13 Credit for Inspections Accomplished in Accordance with AOT One-Time Inspection and Corrective Action (h) For Model A300 B2–1A, B2–1C, B2K– 3C, and B2–203 airplanes, and Model A300 B4–2C, B4–103, and B4–203 airplanes, on which Airbus Modification 3474 has been done: Prior to the accumulation of 16,300 total flight cycles, or within 500 flight cycles after July 30, 1998 (the effective date of AD 98–13–37), whichever occurs later, perform a (j) Any inspection accomplished before October 19, 2004, in accordance with Airbus AOT 53–11, dated October 13, 1997, is acceptable for compliance with the corresponding inspection specified in paragraph (i)(1) of this AD, for that inspection area only. Operators must do the applicable inspections in paragraph (i)(1) of this AD for the remaining inspection areas. Restatement of Requirements of AD 2003– 26–10 One-Time Inspection (f) For airplanes on which Airbus Modification 10147 has not been done: At the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD: Do a one-time detailed inspection for cracking of the lower outboard flange of gantry No. 4 in the MLG bay area per paragraph 4.2.1 of Airbus All Operators Telex (AOT) A300–53A0371, Revision 01 (for Model A300 B2 and B4 series airplanes); or AOT A300–53A6145, Revision 01 (for Model A300–600 series airplanes); both dated September 10, 2003; as applicable. (1) Before the accumulation of 8,000 total flight cycles since the date of issuance of the original Airworthiness Certificate or the date of issuance of the Export Certificate of Airworthiness, whichever is first. (2) Within 30 days after January 22, 2004 (the effective date AD 2003–26–10). Note 1: For the purposes of this AD, a detailed inspection is defined as: ‘‘An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.’’ PO 00000 Frm 00029 Fmt 4702 Sfmt 4702 Repetitive Inspections and Corrective Actions E:\FR\FM\17MYP1.SGM 17MYP1 Federal Register / Vol. 71, No. 95 / Wednesday, May 17, 2006 / Proposed Rules New Requirements of This AD Repetitive Inspections (k) At the later of the applicable times specified in the ‘‘Threshold (FC)’’ and ‘‘Grace Period’’ columns of Tables 1 and 2 in paragraph 1.E of the applicable service bulletin specified in Table 2 of this AD: Do an ultrasonic inspection or HFEC inspection, including rework of the pressure diaphragm, for cracks in the lower flanges of the left and right gantries 1 through 5 inclusive between FR47 and FR54, in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 2 of this 28619 AD. Repeat the inspection at the applicable times specified in the ‘‘Interval (FC)’’ column of Tables 1 and 2 in paragraph 1.E of the applicable service bulletin in Table 2 of this AD. Accomplishment of the initial inspection ends the inspections required by paragraphs (f), (h), and (i) of this AD. TABLE 2.—SERVICE BULLETINS Airbus service bulletin— For airplanes identified in— (1) A300–53–0379, Revision 01, dated October 4, 2005 ........................ (2) A300–53–6152, Revision 01, dated October 4, 2005 ........................ Paragraphs (c)(1) and (c)(2) of this AD. Paragraphs (c)(3) through (c)(6) of this AD inclusive. Corrective Action (l) If any crack is detected during any ultrasonic or HFEC inspection required by paragraph (k) of this AD, before further flight, repair the crack in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 2 of this AD, except as provided by paragraph (n) of this AD. Optional Terminating Actions (m) Accomplishment of the actions specified in Table 3 of this AD ends the repetitive inspections required by paragraph (k) of this AD. TABLE 3.—OPTIONAL TERMINATING ACTIONS By doing all the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin— Before or at the same time with— Reinforce— (1) The actions required by paragraph (k) of this AD and the action specified in paragraph (m)(2) of this AD. The flanges of the left and right portals 1 through 5 inclusive between FR47 and FR54 of the landing gear, including a rotating probe inspection for cracks of holes and repair if necessary. Portals 3, 4, and 5 of the plates/ skin. (2) The actions required by paragraph (k) of this AD. Repair of Certain Cracks A300–53–0380, dated August 5, 2005, except as provided by paragraph (n) of this AD. A300–53–6153, dated August 24, 2005, except as provided by paragraph (n) of this AD. A300–53–0360, dated May 3, 2002, except as provided by paragraph (n) of this AD. A300–53–6132, dated February 5, 2002, except as provided by paragraph (n) of this AD. (n) Where the applicable service bulletin recommends contacting Airbus for appropriate action: Before further flight, repair the crack in accordance with a method approved by the Manager, International Branch, ANM–116; or the DGAC (or its delegated agent). 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. Credit for Original Service Bulletins Related Information (o) Accomplishing the inspections and repair before the effective date of this AD in accordance with Airbus Service Bulletin A300–53–0379, dated May 9, 2005, or Airbus Service Bulletin A300–53–6152, dated May 9, 2005, as applicable, is acceptable for compliance with the corresponding requirements of paragraphs (k) and (l) of this AD. (r) French airworthiness directive F–2005– 091 R1, issued September 28, 2005, also addresses the subject of this AD. mstockstill on PROD1PC61 with PROPOSALS No Inspection Report (p) Although the service bulletins in this AD specify to submit certain information to the manufacturer, this AD does not include that requirement. Issued in Renton, Washington, on May 8, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–7477 Filed 5–16–06; 8:45 am] BILLING CODE 4910–13–P Jkt 208001 PO 00000 Paragraphs (c)(3) through (c)(6) of this AD inclusive. Paragraphs (c)(1) and (c)(2) of this AD Paragraphs (c)(3) through (c)(6) of this AD inclusive DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24780; Directorate Identifier 2006–NM–069–AD] Airworthiness Directives; McDonnell Douglas Model DC–10–10, DC–10–10F, DC–10–15, DC–10–30, DC–10–30F (KC– 10A and KDC–10), DC–10–40, and DC– 10–40F 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 certain McDonnell Douglas airplanes, identified above. This proposed AD would require installing or replacing with improved parts, as applicable, the bonding straps between the metallic (q)(1) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in 16:32 May 16, 2006 Paragraphs (c)(1) and (c)(2) of this AD. RIN 2120–AA64 Alternative Methods of Compliance (AMOCs) VerDate Aug<31>2005 For airplanes identified in— Frm 00030 Fmt 4702 Sfmt 4702 E:\FR\FM\17MYP1.SGM 17MYP1

Agencies

[Federal Register Volume 71, Number 95 (Wednesday, May 17, 2006)]
[Proposed Rules]
[Pages 28615-28619]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-7477]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23690; Directorate Identifier 2004-NM-133-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 B2 and B4 Series
Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series
Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called
A300-600 Series Airplanes)

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

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.

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

SUMMARY: The FAA is revising an earlier NPRM for an airworthiness
directive (AD) that applies to certain Airbus Model A300 B2, A300 B4,
and A300-600 series airplanes. The original NPRM would have superseded
two existing ADs. One AD currently requires an inspection for cracks of
the lower outboard flange of gantry No. 4 in the main landing gear
(MLG) bay area, and repair if necessary. The other AD currently
requires, among other actions, repetitive inspections of the gantry
lower flanges, and repair if necessary. The original NPRM proposed to
require new repetitive inspections for cracks in the lower flange of
certain gantries, and repair if necessary, which ends the existing
inspection requirements. The original NPRM also provided for optional
terminating actions for the new repetitive inspections. This new action
revises the original NPRM by including additional airplanes that were
excluded from the applicability. We are proposing

[[Page 28616]]

this supplemental NPRM to detect and correct fatigue cracks in the
lower flanges of gantries 1 through 5 inclusive in the MLG bay area,
which could result in reduced structural integrity of the fuselage, and
consequent rapid decompression of the airplane.

DATES: We must receive comments on this supplemental NPRM by June 12,
2006.

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.
Governmentwide 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, 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 proposal. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2006-23690; Directorate Identifier 2004-NM-133-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
supplemental NPRM. We will consider all comments received by the
closing date and may amend this supplemental NPRM in light of those
comments.
We will post all comments submitted, 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 ADDRESSES. Comments will be available in the
AD docket shortly after the Docket Management System receives them.

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) (the
``original NPRM'') to amend 14 CFR part 39 to include an AD that
supersedes AD 2003-26-10, amendment 39-13408 (69 FR 867, January 7,
2004), and AD 2004-18-13, amendment 39-13792 (69 FR 55329, September
14, 2004). The original NPRM applied to certain Airbus Model A300 B2
and A300 B4 series airplanes; and Model A300 B4-600, B4-600R, and F4-
600R series airplanes, and Model C4-605R Variant F airplanes
(collectively called A300-600 series airplanes). The original NPRM was
published in the Federal Register on January 26, 2006 (71 FR 4313). The
original NPRM proposed to continue to require an inspection for cracks
of the lower outboard flange of gantry No. 4 in the main landing gear
(MLG) bay area, and repair if necessary. The original NPRM also
proposed to continue to require repetitive inspections of the gantry
lower flanges, and repair if necessary. In addition, the original NPRM
proposed to require new repetitive inspections for cracks in the lower
flange of certain gantries, and repair if necessary, which ends the
existing inspection requirements. The original NPRM also proposed
optional terminating actions for the new repetitive inspections.

Comments

We have considered the following comment on the original NPRM.

Request To Revise the Applicability

Airbus requests that airplanes on which Airbus Modifications 13037
(Airbus Service Bulletins A300-53-0380 and A300-53-6153) and 12413
(Airbus Service Bulletins A300-53-0360 and A300-53-6132), as
applicable, have been installed in service, and airplanes on which
Airbus Modification 12924 has been incorporated in production be
excluded from Table 1--Applicability of the original NPRM. The
commenter states that the effectivity of French airworthiness directive
F-2005-091 R1, issued September 28, 2005, takes these modification into
account, except for Airbus Modification 12924. The commenter states
that the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, plans to revise French
airworthiness directive F-2005-091 R1 to address Airbus Modification
12924.
We do not agree with Airbus to exclude airplanes on which a
particular modification or service bulletin has been accomplished in
service. Paragraph (m) of this supplemental NPRM includes an optional
terminating action for accomplishing the actions specified in Airbus
Service Bulletin A300-53-0380, dated August 5, 2005; Airbus Service
Bulletin A300-53-0360, dated May 3, 2002; Airbus Service Bulleitn A300-
53-6132, dated February 5, 2002; or Airbus Service Bulletin A300-53-
6153, dated August 24, 2005; as applicable. If an operator chooses to
accomplish this optional terminating action, it must continue to
operate the airplane in that configuration unless an alternative method
of compliance is approved. Therefore, we have determined that excluding
those airplanes from the applicability of this supplemental NPRM is not
appropriate. This difference between French airworthiness directive F-
2005-091 R1 and this supplemental NPRM has been coordinated with the
DGAC.
We also do not agree with the commenter to exclude airplanes on
which Airbus Modification 12924 has been incorporated in production. We
have confirmed with the DGAC that the omission of this modification in
French airworthiness directive F-2005-091 R1 was an oversight. However,
since the issuance of the original NPRM, we have determined that all
combinations of the Airbus modifications specified in the effectivity
of French airworthiness directive F-2005-091 R1 include an in-service
service bulletin. Therefore, we have revised Table 1 of the
applicability of this supplemental NPRM to not include any exceptions
for

[[Page 28617]]

accomplishing those Airbus modifications.

Change to Labor Rate

After the original NPRM was issued, we reviewed the figures we have
used over the past several years to calculate AD costs to operators. To
account for various inflationary costs in the airline industry, we find
it necessary to increase the labor rate used in these calculations from
$65 per work hour to $80 per work hour. The cost impact information,
below, reflects this increase in the specified hourly labor rate.

FAA's Determination and Proposed Requirements of the Supplemental NPRM

The change to the applicability discussed above expands the scope
of the original NPRM; therefore, we have determined that it is
necessary to reopen the comment period to provide additional
opportunity for public comment on this supplemental NPRM.

Costs of Compliance

This proposed AD would affect about 165 airplanes of U.S. registry.
The following table provides the estimated costs for U.S. operators to
comply with this proposed AD. Not all actions must be completed on all
airplanes.

Estimated Costs for Required Actions
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Average U.S.-
Action Work hours labor rate Parts Cost per airplane registered Fleet cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
One-time inspection (required by 1.......................... $80 None............... $80................ 23 $1,840.
AD 2003-26-10).
One-time inspection (required by 4.......................... 80 None............... $320............... 43 $13,760.
AD 2004-18-13).
Repetitive inspections (required 12......................... 80 None............... $960, per 78 $74,880, per
by AD 2004-18-13). inspection cycle. inspection cycle.
Repetitive inspections (new 16......................... 80 None............... $1,280, per 78 $99,840, per
proposed actions). inspection cycle. inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
Number of
Average Cost per U.S.-
Optional action Work hours labor rate Parts airplane registered
per hour airplanes
----------------------------------------------------------------------------------------------------------------
Reinforcement specified in 807............. $80 Between $87,100 Between $151,660 23
Airbus Service Bulletin A300- and $121,560 and $186,120
53-0380, dated August 5, 2005. depending on depending on
kit purchased. airplane
configuration.
Reinforcement specified in 807............. 80 Between $82,460 Between $147,020 120
Airbus Service Bulletin A300- and $87,070 and $151,630
53-6153, dated August 24, depending on depending on
2005. kit purchased. airplane
configuration.
Reinforcement specified in Between 24 and 80 Between $250 and Between $2,170 23
Airbus Service Bulletin A300- 128 depending $1,000 and $11,240
53-0360, dated May 3, 2002. on airplane depending on depending on
configuration. kit purchased. airplane
configuration.
Reinforcement specified in 109............. 80 Between $260 and Between $8,980 120
Airbus Service Bulletin A300- $950 depending and $9,670
53-6132, dated February 5, on kit depending on
2002. purchased. airplane
configuration.
----------------------------------------------------------------------------------------------------------------

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;

[[Page 28618]]

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 supplemental NPRM 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 amendments 39-13408 (69 FR 867, January 7, 2004) and 39-13792
(69 FR 55329, September 14, 2004) and adding the following new
airworthiness directive (AD):

Airbus: Docket No. FAA-2006-23690; Directorate Identifier 2004-NM-
133-AD.

Comments Due Date

(a) The FAA must receive comments on this AD action by June 12,
2006.

Affected ADs

(b) This AD supersedes ADs 2003-26-10 and 2004-18-13.

Applicability

Table 1.--Applicability
------------------------------------------------------------------------
Affected Airbus airplanes
-------------------------------------------------------------------------
(1) All Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes
(2) All Model A300 B4-2C, B4-103, and B4-203 airplanes
(3) All Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes
(4) All Model A300 B4-605R and B4-622R airplanes
(5) All Model A300 F4-605R and F4-622R airplanes
(6) All Model A300 C4-605R Variant F airplanes
------------------------------------------------------------------------

Unsafe Condition

(d) This AD results from a report of a large fatigue crack along
the outboard flange of beam No. 4. We are issuing this AD to detect
and correct fatigue cracks in the lower flanges of the left and
right gantries 1 through 5 inclusive in the main landing gear (MLG)
bay area, which could result in reduced structural integrity of the
fuselage, and consequent rapid decompression of the airplane.

Compliance

(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.

Restatement of Requirements of AD 2003-26-10

One-Time Inspection

(f) For airplanes on which Airbus Modification 10147 has not
been done: At the later of the times specified in paragraphs (f)(1)
and (f)(2) of this AD: Do a one-time detailed inspection for
cracking of the lower outboard flange of gantry No. 4 in the MLG bay
area per paragraph 4.2.1 of Airbus All Operators Telex (AOT) A300-
53A0371, Revision 01 (for Model A300 B2 and B4 series airplanes); or
AOT A300-53A6145, Revision 01 (for Model A300-600 series airplanes);
both dated September 10, 2003; as applicable.
(1) Before the accumulation of 8,000 total flight cycles since
the date of issuance of the original Airworthiness Certificate or
the date of issuance of the Export Certificate of Airworthiness,
whichever is first.
(2) Within 30 days after January 22, 2004 (the effective date AD
2003-26-10).

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

Repair

(g) Repair any cracking found during the inspection required by
paragraph (f) of this AD before further flight, per a method
approved by either the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated
agent).

Restatement of Requirements of AD 2004-18-13

One-Time Inspection and Corrective Action

(h) For Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes,
and Model A300 B4-2C, B4-103, and B4-203 airplanes, on which Airbus
Modification 3474 has been done: Prior to the accumulation of 16,300
total flight cycles, or within 500 flight cycles after July 30, 1998
(the effective date of AD 98-13-37), whichever occurs later, perform
a one-time ultrasonic inspection for cracking of the gantry lower
flanges in the MLG bay area, in accordance with Airbus AOT 53-11,
dated October 13, 1997.
(1) If any cracking is detected, prior to further flight, repair
in accordance with the AOT.
(2) If no cracking is detected, no further action is required by
this paragraph.

Repetitive Inspections and Corrective Actions

(i) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622R, C4-
605R Variant F airplanes, and F4-605R airplanes, on which Airbus
Modification 12169 has not been done in production: Perform the
requirements of paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of
this AD, in accordance with Airbus Service Bulletin A300-53-6128,
dated March 5, 2001.
(1) At the later of the times specified in paragraphs (i)(1)(i)
and (i)(1)(ii) of this AD, perform initial ultrasonic inspections or
high frequency eddy current inspections (HFEC) for cracks of the
lower flanges of gantries 3, 4, and 5 between fuselage frames FR47
and FR54, in accordance with the Accomplishment Instructions,
including the Synoptic Chart contained in Figure 2, sheets 1 through
5 inclusive, of the service bulletin.
(i) In accordance with the thresholds specified in the Synoptic
Chart contained in Figure 2, sheets 1 through 5 inclusive, of the
service bulletin; or
(ii) Within 200 flight cycles after October 19, 2004 (the
effective date AD 2004-18-13).
(2) Perform repetitive ultrasonic inspections or high-frequency
eddy current inspections for cracks of the lower flanges of gantries
3, 4, and 5 between fuselage frames FR47 and FR54, in accordance
with the thresholds and Accomplishment Instructions, including the
Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive,
of the service bulletin.
(3) Perform repairs and reinforcements, in accordance with the
thresholds and the Accomplishment Instructions, including the
Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive,
of the service bulletin, except as specified in paragraph (i)(4) of
this AD.
(4) If a new crack is found during any action required by
paragraph (i)(1), (i)(2), or (i)(3) of this AD and the Synoptic
Chart contained in Figure 2, sheets 1 through 5 inclusive, of the
service bulletin specifies to contact Airbus for appropriate action:
Prior to further flight, repair per a method approved by the
Manager, International Branch, ANM-116, or the DGAC (or its
delegated agent).

Credit for Inspections Accomplished in Accordance with AOT

(j) Any inspection accomplished before October 19, 2004, in
accordance with Airbus AOT 53-11, dated October 13, 1997, is
acceptable for compliance with the corresponding inspection
specified in paragraph (i)(1) of this AD, for that inspection area
only. Operators must do the applicable inspections in paragraph
(i)(1) of this AD for the remaining inspection areas.

[[Page 28619]]

New Requirements of This AD

Repetitive Inspections

(k) At the later of the applicable times specified in the
``Threshold (FC)'' and ``Grace Period'' columns of Tables 1 and 2 in
paragraph 1.E of the applicable service bulletin specified in Table
2 of this AD: Do an ultrasonic inspection or HFEC inspection,
including rework of the pressure diaphragm, for cracks in the lower
flanges of the left and right gantries 1 through 5 inclusive between
FR47 and FR54, in accordance with the Accomplishment Instructions of
the applicable service bulletin in Table 2 of this AD. Repeat the
inspection at the applicable times specified in the ``Interval
(FC)'' column of Tables 1 and 2 in paragraph 1.E of the applicable
service bulletin in Table 2 of this AD. Accomplishment of the
initial inspection ends the inspections required by paragraphs (f),
(h), and (i) of this AD.

Table 2.--Service Bulletins
------------------------------------------------------------------------
Airbus service bulletin-- For airplanes identified in--
------------------------------------------------------------------------
(1) A300-53-0379, Revision 01, dated Paragraphs (c)(1) and (c)(2) of
October 4, 2005. this AD.
(2) A300-53-6152, Revision 01, dated Paragraphs (c)(3) through
October 4, 2005. (c)(6) of this AD inclusive.
------------------------------------------------------------------------

Corrective Action

(l) If any crack is detected during any ultrasonic or HFEC
inspection required by paragraph (k) of this AD, before further
flight, repair the crack in accordance with the Accomplishment
Instructions of the applicable service bulletin in Table 2 of this
AD, except as provided by paragraph (n) of this AD.

Optional Terminating Actions

(m) Accomplishment of the actions specified in Table 3 of this
AD ends the repetitive inspections required by paragraph (k) of this
AD.

Table 3.--Optional Terminating Actions
----------------------------------------------------------------------------------------------------------------
By doing all the
actions in accordance
Before or at the same time with-- Reinforce-- with the Accomplishment For airplanes
Instructions of Airbus identified in--
Service Bulletin--
----------------------------------------------------------------------------------------------------------------
(1) The actions required by paragraph The flanges of the left A300-53-0380, dated Paragraphs (c)(1) and
(k) of this AD and the action and right portals 1 August 5, 2005, except (c)(2) of this AD.
specified in paragraph (m)(2) of through 5 inclusive as provided by .......................
this AD. between FR47 and FR54 paragraph (n) of this Paragraphs (c)(3)
of the landing gear, AD. through (c)(6) of this
including a rotating A300-53-6153, dated AD inclusive.
probe inspection for August 24, 2005,
cracks of holes and except as provided by
repair if necessary. paragraph (n) of this
AD.
(2) The actions required by paragraph Portals 3, 4, and 5 of A300-53-0360, dated May Paragraphs (c)(1) and
(k) of this AD. the plates/skin. 3, 2002, except as (c)(2) of this AD
provided by paragraph
(n) of this AD.
> A300-53-6132, dated Paragraphs (c)(3)
February 5, 2002, through (c)(6) of this
except as provided by AD inclusive
paragraph (n) of this
AD.
----------------------------------------------------------------------------------------------------------------

Repair of Certain Cracks

(n) Where the applicable service bulletin recommends contacting
Airbus for appropriate action: Before further flight, repair the
crack in accordance with a method approved by the Manager,
International Branch, ANM-116; or the DGAC (or its delegated agent).

Credit for Original Service Bulletins

(o) Accomplishing the inspections and repair before the
effective date of this AD in accordance with Airbus Service Bulletin
A300-53-0379, dated May 9, 2005, or Airbus Service Bulletin A300-53-
6152, dated May 9, 2005, as applicable, is acceptable for compliance
with the corresponding requirements of paragraphs (k) and (l) of
this AD.

No Inspection Report

(p) Although the service bulletins in this AD specify to submit
certain information to the manufacturer, this AD does not include
that requirement.

Alternative Methods of Compliance (AMOCs)

(q)(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.

Related Information

(r) French airworthiness directive F-2005-091 R1, issued
September 28, 2005, also addresses the subject of this AD.

Issued in Renton, Washington, on May 8, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-7477 Filed 5-16-06; 8:45 am]
BILLING CODE 4910-13-P

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.