Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes, 2200-2204 [E8-383]

Download as PDF 2200 Federal Register / Vol. 73, No. 9 / Monday, January 14, 2008 / Proposed Rules TABLE 1.—SERVICE BULLETINS Required Airbus Service Bulletin Approved Airbus Service Bulletin version for actions done before the effective date of this AD A300–27–6044, Revision 04, dated September 10, 2001. A300–27–6044, Revision 02, dated August 26, 2000; or Revision 03, dated June 28, 2001. A310–27–2089, Revision 02, dated June 28, 2001. A310–27–2089, Revision 01, dated August 25, 2000. rmajette on PROD1PC64 with PROPOSALS Inspection (l) At the applicable time specified in paragraph (l)(1) or (l)(2) of this AD, do a detailed inspection of specified components of the THSA in accordance with paragraph 1.E.(2)(a) and the Accomplishment Instructions of the applicable service bulletin. Repair any discrepancy before further flight in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). TRW Aeronautical Systems/Lucas Aerospace Component Maintenance Manual 27–44–13, dated September 14, 2001, is one acceptable method for the repair. Doing an inspection in accordance with paragraph (o) or (p) of this AD terminates the requirements of this paragraph. (1) If the flight hours accumulated on the THSA can be positively determined: Inspect at the earlier of: (i) Before the accumulation of 47,000 total flight hours on the THSA, or within 600 flight hours after August 29, 2006 (the effective date of AD 2006–15–10), whichever occurs later. (ii) Within 25 years since the THSA was new or within 600 flight hours after August 29, 2006, whichever occurs later. (2) If the flight hours accumulated on the THSA cannot be positively determined: Inspect before the accumulation of 47,000 total flight hours on the airplane, or within 600 flight hours after August 29, 2006, whichever occurs later. Note 5: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Follow-on Repetitive Tasks (m) After the inspection required by paragraph (l) of this AD: Do the repetitive tasks in accordance with the Accomplishment Instructions and at the times specified in paragraph 1.E.(2)(b) of the service bulletin, as applicable, except as provided by paragraph (n) of this AD. The repetitive tasks are valid only until the THSA operational life exceeds 65,000 flight hours, 40,000 flight cycles, or 25 years, whichever occurs first. Before the THSA is operated VerDate Aug<31>2005 15:19 Jan 11, 2008 Jkt 214001 beyond these extended life goals, it must be replaced with a new THSA, except as required by paragraph (n) of this AD. Doing an inspection in accordance with paragraph (o) or (p) of this AD terminates the requirements of this paragraph. THSA Replacement (n) For any THSA, whether discrepant or not, that is replaced with a new THSA: Within 47,000 flight hours or 25 years, whichever occurs first, after the THSA is replaced, do the applicable tasks specified in paragraph 1.E.(2)(a) and the Accomplishment Instructions of the applicable service bulletin. Thereafter repeat the tasks within the repetitive intervals specified in paragraph 1.E.(2)(b) of the applicable service bulletin. Doing the corresponding tasks in accordance with paragraph (o) or (p) of this AD terminates the requirements of this paragraph. New Requirements of This AD Revise Airworthiness Limitations Section (ALS) to Incorporate Limitations and Maintenance Tasks for Aging Systems Maintenance (o) Within 3 months after the effective date of this AD, revise the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate Airbus A310 ALS Part 4—Aging Systems Maintenance, Revision 01, dated December 21, 2006; and A300–600 ALS Part 4—Aging Systems Maintenance, Revision 01, dated December 21, 2006; as applicable. For all tasks identified in Airbus A310 ALS Part 4— Aging Systems Maintenance, Revision 01; and A300–600 ALS Part 4—Aging Systems Maintenance, Revision 01; the initial compliance times start from the effective date of this AD, except as provided by paragraph (p) of this AD. The repetitive inspections must be accomplished thereafter at the interval specified in Airbus A310 ALS Part 4—Aging Systems Maintenance, Revision 01; and A300–600 ALS Part 4—Aging Systems Maintenance, Revision 01. (p) For airplanes on which any life limitation/maintenance task has been complied with in accordance with the requirements of AD 2006–10–11 or AD 2006– 15–10, the last accomplishment of each limitation/task must be retained as a starting point for the accomplishment of each corresponding limitation/task interval now introduced in Airbus A310 ALS Part 4— Aging Systems Maintenance, Revision 01, dated December 21, 2006; and A300–600 ALS Part 4—Aging Systems Maintenance, PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 Airbus airplane model A300 B4–601, B4–603, B4–620, and B4–622. A300 B4–605R and B4–622R. A300 F4–605R and F4–622R. A300 C4–605R Variant F. A310–203, –204, –221, and –222. A310–304, –322, –324, and –325. Revision 01, dated December 21, 2006; as applicable. (q) Except as provided by paragraph (r) of this AD: After accomplishing the actions specified in paragraphs (o) and (p) of this AD, no alternative inspection, inspection intervals, or limitations may be used. Alternative Methods of Compliance (AMOCs) (r)(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) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (3) AMOCs approved previously in accordance with AD 2006–10–11 are not approved as AMOCs with this AD. (4) AMOCs approved previously in accordance with AD 2006–15–10 are not approved as AMOCs with this AD. Related Information (s) EASA airworthiness directive 2007– 0092, dated April 10, 2007, also addresses the subject of this AD. Issued in Renton, Washington, on January 3, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–380 Filed 1–11–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0014; Directorate Identifier 2007–NM–249–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: E:\FR\FM\14JAP1.SGM 14JAP1 Federal Register / Vol. 73, No. 9 / Monday, January 14, 2008 / Proposed Rules Notice of proposed rulemaking (NPRM). ACTION: rmajette on PROD1PC64 with PROPOSALS SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Airbus Model A318, A319, A320, and A321 airplanes. The existing AD currently requires repetitive inspections for cracking in the forward lug of the support rib 5 fitting of both main landing gear (MLG), and repair if necessary. The existing AD also provides optional terminating actions for certain airplanes, as well as other optional methods for complying with the inspection requirements of the existing AD. This proposed AD would continue to require repetitive inspections for cracking in the forward lug of the support rib 5 fitting of the left and right MLG at new repetitive intervals in accordance with new service information, and repair or replacement of any cracked MLG fitting if necessary. This proposed AD would also require modification of the rib bushings of the left and right MLG, which would end the repetitive inspections. This proposed AD results from cracks found in the forward lug of the MLG support rib 5 fitting. We are proposing this AD to prevent cracking in the forward lug of the MLG, which could result in failure of the lug and consequent collapse of the MLG during takeoff or landing. DATES: We must receive comments on this proposed AD by February 13, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD VerDate Aug<31>2005 15:19 Jan 11, 2008 Jkt 214001 docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2008–0014; Directorate Identifier 2007–NM–249–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On May 15, 2006, we issued AD 2006–11–04, amendment 39–14608 (71 FR 29578, May 23, 2006), for certain Airbus Model A318, A319, A320, and A321 airplanes. AD 2006–11–04 requires repetitive detailed inspections for cracking in the forward lug of the support rib 5 fitting of both main landing gear (MLG), and repair if necessary. AD 2006–11–04 also provides optional terminating actions for certain airplanes, as well as other optional methods for complying with the inspection requirements of the existing AD. That AD resulted from a new crack that was found in the forward lug of the MLG support rib 5 fitting. We issued that AD to detect and correct cracking in the forward lug of the MLG, which could result in failure of the lug and consequent collapse of the MLG during takeoff or landing. Actions Since Existing AD Was Issued Since we issued AD 2006–11–04, the European Aviation Safety Agency (EASA), which is the technical agent for PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 2201 the Member States of the European Union, notified us that the repetitive inspection intervals must be adjusted and that the optional terminating action, which would end the repetitive inspections, must be mandated for all airplanes. In the preamble to AD 2006– 11–04, we indicated that the actions required by that AD were considered ‘‘interim action,’’ and that we were considering further rulemaking to require the modification of the lugs of the support rib 5 fitting of both MLG, which would terminate the repetitive inspections required by AD 2006–11– 04. We have now determined that further rulemaking action is indeed necessary, and this proposed AD follows from that determination. Relevant Service Information Airbus has issued Service Bulletin A320–57–1138, Revision 01, dated October 27, 2006. The service bulletin describes procedures for (1) doing repetitive visual inspections or repetitive ultrasonic inspections for cracking in the forward lug of the support rib 5 fitting of the left and right MLG, (2) doing repetitive visual inspections for cracking in the forward lug of the support rib 5 fitting if any cracking is found during an ultrasonic inspection, and (3) contacting the manufacturer for instructions if any cracking is found during a visual inspection. The service bulletin also specifies that accomplishing Airbus Service Bulletin A320–57–1118 eliminates the need for the repetitive inspections. Airbus has also issued Service Bulletin A320–57–1118, Revision 03, dated April 23, 2007. The service bulletin describes procedures for modifying the rib bushings of the left and right MLG. The modification includes removing the existing bushings, doing a visual inspection for corrosion and damage to the bores and spotfaces, repairing any corrosion or damage found during the detailed inspection, and installing new improved bushings and applying a certain protective sealant to the bores and spotfaces of the lugs for the pintle-pin bushings of gear rib 5. Accomplishing the modification eliminates the need for the repetitive inspections specified in Airbus Service Bulletin A320–57–1138. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The EASA mandated the service information and issued airworthiness directive 2007–0213, dated August 7, 2007, to ensure the continued airworthiness of these airplanes in the European Union. E:\FR\FM\14JAP1.SGM 14JAP1 2202 Federal Register / Vol. 73, No. 9 / Monday, January 14, 2008 / Proposed Rules FAA’s Determination and Requirements of the Proposed AD These airplanes are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. As described in FAA Order 8100.14A, ‘‘Interim Procedures for Working with the European Community on Airworthiness Certification and Continued Airworthiness,’’ dated August 12, 2005, the EASA has kept the FAA informed of the situation described above. We have examined the EASA’s findings, evaluated all pertinent information, and determined that 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 2006–11–04 and would retain the requirements of the existing AD, until the new inspections have been initiated. This proposed AD would also require accomplishing the actions specified in service information described previously, except as discussed under ‘‘Differences between Proposed AD and Service Bulletin.’’ rmajette on PROD1PC64 with PROPOSALS Differences Between Proposed AD and Service Bulletin Although EASA airworthiness directive 2007–0213 specifies repeating the inspections at the intervals defined in Airbus Service Bulletin A320–57– 1138, the intent is to require the repetitive inspections at those intervals, or before further flight after a hard landing, whichever is first. We have coordinated this difference with the EASA. EASA airworthiness directive 2007– 0213 and Airbus Service Bulletin A320– 57–1138 permit further flight if cracking is found during the ultrasonic inspection but is not detected by a visual inspection. This proposed AD, however, would require repair or replacement of any cracked MLG fitting before further flight. We have determined that because of the safety implications and consequences associated with cracking in the subject area, the MLG fitting must be repaired or replaced before further flight regardless of how the crack is detected. We note that cracking found during the ultrasonic inspection may be repaired with oversized bushings, whereas cracking detected during the visual inspection would require extensive repair or replacement of the MLG fitting. Airbus Service Bulletin A320–57– 1138 specifies to contact the VerDate Aug<31>2005 15:19 Jan 11, 2008 Jkt 214001 manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions using a method approved by the FAA or the EASA (or its delegated agent). In light of the type of repair 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 repair approved by the FAA or the EASA would be acceptable for compliance with this proposed AD. Costs of Compliance This proposed AD would affect about 466 airplanes of U.S. registry. The actions that are required by AD 2006–11–04 and retained in this proposed AD take about 2 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the currently required actions is $160 per airplane, per inspection cycle. The new proposed inspections would take between 3 and 4 work hours per airplane, depending on the type of inspection accomplished, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the new inspections specified in this proposed AD for U.S. operators is between $111,840 and $149,120, or between $240 and $320 per airplane, per inspection cycle. The new proposed modification would take about 73 work hours per airplane, at an average labor rate of $80 per work hour. Required parts would cost $3,850 per airplane. Based on these figures, the estimated cost of the new modification specified in this proposed AD for U.S. operators is $4,515,540, or $9,690 per airplane. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 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. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–14608 (71 FR 29578, May 23, 2006) and adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2008–0014; Directorate Identifier 2007–NM–249–AD. Comments Due Date (a) The FAA must receive comments on this AD action by February 13, 2008. Affected ADs (b) This AD supersedes AD 2006–11–04. Applicability (c) This AD applies to Airbus Model A318, A319, A320, and A321 airplanes, certificated in any category, except airplanes on which E:\FR\FM\14JAP1.SGM 14JAP1 Federal Register / Vol. 73, No. 9 / Monday, January 14, 2008 / Proposed Rules Airbus Modification 32025 has been accomplished in production. Unsafe Condition (d) This AD results from cracks found in the forward lug of the main landing gear (MLG) support rib 5 fitting. We are issuing this AD to prevent cracking in the forward lug of the MLG, which could result in failure of the lug and consequent collapse of the MLG during takeoff or landing. 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 Certain Requirements of AD 2006–11–04 Repetitive Detailed Inspections (f) Within 8 days after June 7, 2006 (the effective date of AD 2006–11–04), or before further flight after a hard landing, whichever is first: Perform a detailed inspection for cracking in the forward lug of the support rib 5 fitting of the left- and right-hand MLG, and, if any crack is found, replace the MLG fitting with a new fitting before further flight, in accordance with a method approved by either the Manager, International Branch, ANM–116, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Accomplishing the actions specified in the Airbus A318/A319/A320/A321 Nondestructive Testing Manual, Chapter 51– 90–00, revision dated February 1, 2003, is one approved method for performing the detailed inspection. Repeat the inspection thereafter at intervals not to exceed 8 days, or before further flight after a hard landing, whichever is first. As of the effective date of this AD, the repetitive inspections required by paragraph (i) of this AD must be accomplished in lieu of the repetitive inspections required by this paragraph. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ 2203 Optional Terminating Action (h) For Model A319, A320, and A321 airplanes: Repair of the forward lugs of the support rib 5 fitting of the left- and righthand MLG in accordance with a method approved by the Manager, International Branch, ANM–116; or the EASA (or its delegated agent); constitutes terminating action for the requirements of this AD. Doing the repair in accordance with Airbus A319 Structural Repair Manual (SRM), Chapter 5.C., 57–26–13, revision dated November 1, 2004; Airbus A320 SRM, Chapter 5.D., 57– 26–13, revision dated November 1, 2004; or Airbus A321 SRM, Chapter 5.D., 57–26–13, revision dated February 1, 2005; as applicable; is one approved method. New Requirements of This AD Optional Inspection Method (g) Performing an ultrasonic inspection for cracking in the forward lug of the support rib 5 fitting of the left- and right-hand MLG in accordance with a method approved by the Manager, International Branch, ANM–116; or the EASA (or its delegated agent); is an acceptable alternative method of compliance for the initial and repetitive inspections required by paragraph (f) of this AD. Doing the actions specified in the A318/A319/ A320/A321 Nondestructive Testing Manual, Chapter 57–29–03, revision dated February 1, 2005 (for Model A318, A319, and A320 airplanes), or Chapter 57–29–04, revision dated May 1, 2005 (for Model A321 airplanes), as applicable, is one approved method for performing the ultrasonic inspection. New Repetitive Inspections (i) At the applicable time specified in Table 1 of this AD, or before further flight after a hard landing, whichever is first: Do a visual inspection or ultrasonic inspection for cracking in the forward lug of the support rib 5 fitting of the left and right MLG, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 57–1138, Revision 01, dated October 27, 2006. Repeat the inspection thereafter at the applicable interval specified in Table 1 of this AD or before further flight after a hard landing, whichever is first, until the modification required by paragraph (k) of this AD has been accomplished. Accomplishing the initial inspection terminates the requirements of paragraph (f) of this AD. TABLE 1.—COMPLIANCE TIMES Airplanes Model A318, A319, and A320 airplanes. Model A321 airplanes .......... Initial inspection If the most recent inspection is a detailed inspection done in accordance with paragraph (f) of this AD, inspect within 150 flight cycles after the most recent detailed inspection. If the most recent inspection is an ultrasonic inspection done in accordance with paragraph (g) of this AD, inspect within 940 flight cycles after the most recent ultrasonic inspection. If the most recent inspection is a detailed inspection done in accordance with paragraph (f) of this AD, inspect within 100 flight cycles after the most recent detailed inspection. If the most recent inspection is an ultrasonic inspection done in accordance with paragraph (g) of this AD, inspect within 630 flight cycles after the most recent ultrasonic inspection. rmajette on PROD1PC64 with PROPOSALS Corrective Action (j) If any cracking is found during any inspection required by paragraph (i) of this AD: Before further flight, repair or replace the cracked MLG fitting using a method approved by either the Manager, International Branch, ANM–116, or the EASA (or its delegated agent). Terminating Action (k) Within 60 months after the effective date of this AD, modify the rib bushings of the left and right MLG, by accomplishing all VerDate Aug<31>2005 15:19 Jan 11, 2008 Repetitive interval Jkt 214001 Within 150 flight cycles after a visual inspection. Within 940 flight cycles after an ultrasonic inspection. Within 100 flight cycles after a visual inspection. Within 630 flight cycles after an ultrasonic inspection. of the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A320–57–1118, Revision 03, dated April 23, 2007. Accomplishing the modification terminates the requirements of this AD. Credit for Actions Done According to Previous Issue of Service Bulletin (l) For Model A319, A320, and A321 airplanes, modifying the lugs of the support rib 5 fitting of the left and right MLG is acceptable for compliance with the PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 requirements of paragraph (k) of this AD if done before the effective date of this AD in accordance with one of the following service bulletins: Airbus Service Bulletin A320–57– 1118, dated September 5, 2002; Revision 01, dated August 28, 2003; or Revision 02, dated August 2, 2006. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested in E:\FR\FM\14JAP1.SGM 14JAP1 2204 Federal Register / Vol. 73, No. 9 / Monday, January 14, 2008 / Proposed Rules accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (3) AMOCs approved previously in accordance with AD 2006–11–04 are approved as AMOCs for the corresponding provisions of this AD. Related Information (n) EASA airworthiness directive 2007– 0213, dated August 7, 2007, also addresses the subject of this AD. Issued in Renton, Washington, on December 26, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–383 Filed 1–11–08; 8:45 am] We must receive comments on this proposed AD by February 28, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. DATES: AGENCY: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Jeff Janusz, Aerospace Engineer, Systems and Propulsion Branch, ACE–116W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946–4148; fax (316) 946–4107. SUPPLEMENTARY INFORMATION: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 727–200 series airplanes. This proposed AD would require deactivation of auxiliary fuel tank systems installed in accordance with Supplemental Type Certificate (STC) SA1350NM. This proposed AD results from fuel tank system reviews conducted by the manufacturer that identified potential unsafe conditions for which the manufacturer has not provided corrective actions. We are proposing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2008–0013; Directorate Identifier 2007–NM–230–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0013; Directorate Identifier 2007–NM–230–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 727–200 Series Airplanes Equipped With an Auxiliary Fuel Tank System Installed in Accordance With Supplemental Type Certificate SA1350NM rmajette on PROD1PC64 with PROPOSALS Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). VerDate Aug<31>2005 15:19 Jan 11, 2008 Jkt 214001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 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 Requirements’’ (67 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (‘‘SFAR 88,’’ Amendment 21–78, and subsequent Amendments 21–82 and 21–83). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC) design approval) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to design approval holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: Single failures, single failures in combination with another latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. We have determined that the actions identified in this AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. E:\FR\FM\14JAP1.SGM 14JAP1

Agencies

[Federal Register Volume 73, Number 9 (Monday, January 14, 2008)]
[Proposed Rules]
[Pages 2200-2204]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-383]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0014; Directorate Identifier 2007-NM-249-AD]
RIN 2120-AA64


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

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

[[Page 2201]]


ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Airbus Model A318, A319, A320, 
and A321 airplanes. The existing AD currently requires repetitive 
inspections for cracking in the forward lug of the support rib 5 
fitting of both main landing gear (MLG), and repair if necessary. The 
existing AD also provides optional terminating actions for certain 
airplanes, as well as other optional methods for complying with the 
inspection requirements of the existing AD. This proposed AD would 
continue to require repetitive inspections for cracking in the forward 
lug of the support rib 5 fitting of the left and right MLG at new 
repetitive intervals in accordance with new service information, and 
repair or replacement of any cracked MLG fitting if necessary. This 
proposed AD would also require modification of the rib bushings of the 
left and right MLG, which would end the repetitive inspections. This 
proposed AD results from cracks found in the forward lug of the MLG 
support rib 5 fitting. We are proposing this AD to prevent cracking in 
the forward lug of the MLG, which could result in failure of the lug 
and consequent collapse of the MLG during takeoff or landing.

DATES: We must receive comments on this proposed AD by February 13, 
2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Airbus, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0014; 
Directorate Identifier 2007-NM-249-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On May 15, 2006, we issued AD 2006-11-04, amendment 39-14608 (71 FR 
29578, May 23, 2006), for certain Airbus Model A318, A319, A320, and 
A321 airplanes. AD 2006-11-04 requires repetitive detailed inspections 
for cracking in the forward lug of the support rib 5 fitting of both 
main landing gear (MLG), and repair if necessary. AD 2006-11-04 also 
provides optional terminating actions for certain airplanes, as well as 
other optional methods for complying with the inspection requirements 
of the existing AD. That AD resulted from a new crack that was found in 
the forward lug of the MLG support rib 5 fitting. We issued that AD to 
detect and correct cracking in the forward lug of the MLG, which could 
result in failure of the lug and consequent collapse of the MLG during 
takeoff or landing.

Actions Since Existing AD Was Issued

    Since we issued AD 2006-11-04, the European Aviation Safety Agency 
(EASA), which is the technical agent for the Member States of the 
European Union, notified us that the repetitive inspection intervals 
must be adjusted and that the optional terminating action, which would 
end the repetitive inspections, must be mandated for all airplanes. In 
the preamble to AD 2006-11-04, we indicated that the actions required 
by that AD were considered ``interim action,'' and that we were 
considering further rulemaking to require the modification of the lugs 
of the support rib 5 fitting of both MLG, which would terminate the 
repetitive inspections required by AD 2006-11-04. We have now 
determined that further rulemaking action is indeed necessary, and this 
proposed AD follows from that determination.

Relevant Service Information

    Airbus has issued Service Bulletin A320-57-1138, Revision 01, dated 
October 27, 2006. The service bulletin describes procedures for (1) 
doing repetitive visual inspections or repetitive ultrasonic 
inspections for cracking in the forward lug of the support rib 5 
fitting of the left and right MLG, (2) doing repetitive visual 
inspections for cracking in the forward lug of the support rib 5 
fitting if any cracking is found during an ultrasonic inspection, and 
(3) contacting the manufacturer for instructions if any cracking is 
found during a visual inspection. The service bulletin also specifies 
that accomplishing Airbus Service Bulletin A320-57-1118 eliminates the 
need for the repetitive inspections.
    Airbus has also issued Service Bulletin A320-57-1118, Revision 03, 
dated April 23, 2007. The service bulletin describes procedures for 
modifying the rib bushings of the left and right MLG. The modification 
includes removing the existing bushings, doing a visual inspection for 
corrosion and damage to the bores and spotfaces, repairing any 
corrosion or damage found during the detailed inspection, and 
installing new improved bushings and applying a certain protective 
sealant to the bores and spotfaces of the lugs for the pintle-pin 
bushings of gear rib 5. Accomplishing the modification eliminates the 
need for the repetitive inspections specified in Airbus Service 
Bulletin A320-57-1138.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The EASA mandated 
the service information and issued airworthiness directive 2007-0213, 
dated August 7, 2007, to ensure the continued airworthiness of these 
airplanes in the European Union.

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FAA's Determination and Requirements of the Proposed AD

    These airplanes are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. As described in FAA 
Order 8100.14A, ``Interim Procedures for Working with the European 
Community on Airworthiness Certification and Continued Airworthiness,'' 
dated August 12, 2005, the EASA has kept the FAA informed of the 
situation described above. We have examined the EASA's findings, 
evaluated all pertinent information, and determined that 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 2006-11-04 and would retain the 
requirements of the existing AD, until the new inspections have been 
initiated. This proposed AD would also require accomplishing the 
actions specified in service information described previously, except 
as discussed under ``Differences between Proposed AD and Service 
Bulletin.''

Differences Between Proposed AD and Service Bulletin

    Although EASA airworthiness directive 2007-0213 specifies repeating 
the inspections at the intervals defined in Airbus Service Bulletin 
A320-57-1138, the intent is to require the repetitive inspections at 
those intervals, or before further flight after a hard landing, 
whichever is first. We have coordinated this difference with the EASA.
    EASA airworthiness directive 2007-0213 and Airbus Service Bulletin 
A320-57-1138 permit further flight if cracking is found during the 
ultrasonic inspection but is not detected by a visual inspection. This 
proposed AD, however, would require repair or replacement of any 
cracked MLG fitting before further flight. We have determined that 
because of the safety implications and consequences associated with 
cracking in the subject area, the MLG fitting must be repaired or 
replaced before further flight regardless of how the crack is detected. 
We note that cracking found during the ultrasonic inspection may be 
repaired with oversized bushings, whereas cracking detected during the 
visual inspection would require extensive repair or replacement of the 
MLG fitting.
    Airbus Service Bulletin A320-57-1138 specifies to contact the 
manufacturer for instructions on how to repair certain conditions, but 
this proposed AD would require repairing those conditions using a 
method approved by the FAA or the EASA (or its delegated agent). In 
light of the type of repair 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 repair 
approved by the FAA or the EASA would be acceptable for compliance with 
this proposed AD.

Costs of Compliance

    This proposed AD would affect about 466 airplanes of U.S. registry.
    The actions that are required by AD 2006-11-04 and retained in this 
proposed AD take about 2 work hours per airplane, at an average labor 
rate of $80 per work hour. Based on these figures, the estimated cost 
of the currently required actions is $160 per airplane, per inspection 
cycle.
    The new proposed inspections would take between 3 and 4 work hours 
per airplane, depending on the type of inspection accomplished, at an 
average labor rate of $80 per work hour. Based on these figures, the 
estimated cost of the new inspections specified in this proposed AD for 
U.S. operators is between $111,840 and $149,120, or between $240 and 
$320 per airplane, per inspection cycle.
    The new proposed modification would take about 73 work hours per 
airplane, at an average labor rate of $80 per work hour. Required parts 
would cost $3,850 per airplane. Based on these figures, the estimated 
cost of the new modification specified in this proposed AD for U.S. 
operators is $4,515,540, or $9,690 per airplane.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14608 (71 FR 29578, May 23, 2006) and adding the 
following new airworthiness directive (AD):

Airbus: Docket No. FAA-2008-0014; Directorate Identifier 2007-NM-
249-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by February 
13, 2008.

Affected ADs

    (b) This AD supersedes AD 2006-11-04.

Applicability

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

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Airbus Modification 32025 has been accomplished in production.

Unsafe Condition

    (d) This AD results from cracks found in the forward lug of the 
main landing gear (MLG) support rib 5 fitting. We are issuing this 
AD to prevent cracking in the forward lug of the MLG, which could 
result in failure of the lug and consequent collapse of the MLG 
during takeoff or landing.

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 Certain Requirements of AD 2006-11-04

Repetitive Detailed Inspections

    (f) Within 8 days after June 7, 2006 (the effective date of AD 
2006-11-04), or before further flight after a hard landing, 
whichever is first: Perform a detailed inspection for cracking in 
the forward lug of the support rib 5 fitting of the left- and right-
hand MLG, and, if any crack is found, replace the MLG fitting with a 
new fitting before further flight, in accordance with a method 
approved by either the Manager, International Branch, ANM-116, FAA; 
or the European Aviation Safety Agency (EASA) (or its delegated 
agent). Accomplishing the actions specified in the Airbus A318/A319/
A320/A321 Nondestructive Testing Manual, Chapter 51-90-00, revision 
dated February 1, 2003, is one approved method for performing the 
detailed inspection. Repeat the inspection thereafter at intervals 
not to exceed 8 days, or before further flight after a hard landing, 
whichever is first. As of the effective date of this AD, the 
repetitive inspections required by paragraph (i) of this AD must be 
accomplished in lieu of the repetitive inspections required by this 
paragraph.

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

Optional Inspection Method

    (g) Performing an ultrasonic inspection for cracking in the 
forward lug of the support rib 5 fitting of the left- and right-hand 
MLG in accordance with a method approved by the Manager, 
International Branch, ANM-116; or the EASA (or its delegated agent); 
is an acceptable alternative method of compliance for the initial 
and repetitive inspections required by paragraph (f) of this AD. 
Doing the actions specified in the A318/A319/A320/A321 
Nondestructive Testing Manual, Chapter 57-29-03, revision dated 
February 1, 2005 (for Model A318, A319, and A320 airplanes), or 
Chapter 57-29-04, revision dated May 1, 2005 (for Model A321 
airplanes), as applicable, is one approved method for performing the 
ultrasonic inspection.

Optional Terminating Action

    (h) For Model A319, A320, and A321 airplanes: Repair of the 
forward lugs of the support rib 5 fitting of the left- and right-
hand MLG in accordance with a method approved by the Manager, 
International Branch, ANM-116; or the EASA (or its delegated agent); 
constitutes terminating action for the requirements of this AD. 
Doing the repair in accordance with Airbus A319 Structural Repair 
Manual (SRM), Chapter 5.C., 57-26-13, revision dated November 1, 
2004; Airbus A320 SRM, Chapter 5.D., 57-26-13, revision dated 
November 1, 2004; or Airbus A321 SRM, Chapter 5.D., 57-26-13, 
revision dated February 1, 2005; as applicable; is one approved 
method.

New Requirements of This AD

New Repetitive Inspections

    (i) At the applicable time specified in Table 1 of this AD, or 
before further flight after a hard landing, whichever is first: Do a 
visual inspection or ultrasonic inspection for cracking in the 
forward lug of the support rib 5 fitting of the left and right MLG, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-57-1138, Revision 01, dated October 27, 2006. Repeat 
the inspection thereafter at the applicable interval specified in 
Table 1 of this AD or before further flight after a hard landing, 
whichever is first, until the modification required by paragraph (k) 
of this AD has been accomplished. Accomplishing the initial 
inspection terminates the requirements of paragraph (f) of this AD.

                       Table 1.--Compliance Times
------------------------------------------------------------------------
          Airplanes            Initial inspection    Repetitive interval
------------------------------------------------------------------------
Model A318, A319, and A320    If the most recent    Within 150 flight
 airplanes.                    inspection is a       cycles after a
                               detailed inspection   visual inspection.
                               done in accordance
                               with paragraph (f)
                               of this AD, inspect
                               within 150 flight
                               cycles after the
                               most recent
                               detailed inspection.
                              If the most recent    Within 940 flight
                               inspection is an      cycles after an
                               ultrasonic            ultrasonic
                               inspection done in    inspection.
                               accordance with
                               paragraph (g) of
                               this AD, inspect
                               within 940 flight
                               cycles after the
                               most recent
                               ultrasonic
                               inspection.
Model A321 airplanes........  If the most recent    Within 100 flight
                               inspection is a       cycles after a
                               detailed inspection   visual inspection.
                               done in accordance
                               with paragraph (f)
                               of this AD, inspect
                               within 100 flight
                               cycles after the
                               most recent
                               detailed inspection.
                              If the most recent    Within 630 flight
                               inspection is an      cycles after an
                               ultrasonic            ultrasonic
                               inspection done in    inspection.
                               accordance with
                               paragraph (g) of
                               this AD, inspect
                               within 630 flight
                               cycles after the
                               most recent
                               ultrasonic
                               inspection.
------------------------------------------------------------------------

Corrective Action

    (j) If any cracking is found during any inspection required by 
paragraph (i) of this AD: Before further flight, repair or replace 
the cracked MLG fitting using a method approved by either the 
Manager, International Branch, ANM-116, or the EASA (or its 
delegated agent).

Terminating Action

    (k) Within 60 months after the effective date of this AD, modify 
the rib bushings of the left and right MLG, by accomplishing all of 
the applicable actions specified in the Accomplishment Instructions 
of Airbus Service Bulletin A320-57-1118, Revision 03, dated April 
23, 2007. Accomplishing the modification terminates the requirements 
of this AD.

Credit for Actions Done According to Previous Issue of Service Bulletin

    (l) For Model A319, A320, and A321 airplanes, modifying the lugs 
of the support rib 5 fitting of the left and right MLG is acceptable 
for compliance with the requirements of paragraph (k) of this AD if 
done before the effective date of this AD in accordance with one of 
the following service bulletins: Airbus Service Bulletin A320-57-
1118, dated September 5, 2002; Revision 01, dated August 28, 2003; 
or Revision 02, dated August 2, 2006.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, International Branch, ANM-116, FAA, has the 
authority to approve AMOCs for this AD, if requested in

[[Page 2204]]

accordance with the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (3) AMOCs approved previously in accordance with AD 2006-11-04 
are approved as AMOCs for the corresponding provisions of this AD.

Related Information

    (n) EASA airworthiness directive 2007-0213, dated August 7, 
2007, also addresses the subject of this AD.

    Issued in Renton, Washington, on December 26, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-383 Filed 1-11-08; 8:45 am]
BILLING CODE 4910-13-P
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