AD 00-5331

12077 Federal Register / Vol. 65, No. 46 / Wednesday, March 8, 2000 / Rules and Regulations airplane centerline and stringer 56R in the area of the VHF2 antenna, in accordance with the applicable service bulletin, at the applicable time specified by paragraph (b)(1) or (b)(2) of this AD. Accomplishment of this inspection terminates the requirements of paragraph (a) of this AD. (1) For airplanes on which the interim repair specified by paragraph 2.C.(4) of the applicable service bulletin has not been accomplished: Prior to the accumulation of 900 total flight hours on the airplane, or within 500 flight hours after the effective date of this AD, whichever occurs later. Thereafter, accomplish the follow-on actions of paragraph (c) or (d) of this AD, as applicable. (2) For airplanes on which the interim repair specified by paragraph 2.C.(4) of the applicable service bulletin has been accomplished: Within 1,250 flight hours after accomplishment of the interim repair, or within 500 flight hours after the effective date of this AD, whichever occurs later. Repetitive Inspections (c) If no crack is detected during the HFEC inspection required by paragraph (b) of this AD, accomplish the repetitive inspections required by paragraph (c)(1) or (c)(2) of this AD, as applicable. (1) For airplanes on which the interim repair specified by paragraph 2.C.(4) of the applicable service bulletin has not been accomplished, accomplish the actions specified by paragraphs (c)(1)(i) and (c)(1)(ii) of this AD. (i) Repeat the HFEC inspection specified by paragraph (b) at intervals not to exceed 500 flight hours. (ii) Within 300 flight hours after each HFEC inspection required by this AD: Perform a detailed visual inspection (without removal of the VHF2 antenna) of the fuselage skin aft of frame 54, between the airplane centerline and stringer 56R in the area of the VHF2 antenna to detect cracks, in accordance with the applicable service bulletin. Thereafter, if no cracks are detected, repeat the detailed visual inspection every 36 flight hours until accomplishment of the next HFEC inspection required by paragraph (c)(1)(i) of this AD. (2) For airplanes on which the interim repair specified by paragraph 2.C.(4) of the applicable service bulletin has been accomplished, repeat the HFEC inspection specified by paragraph (b) of this AD at intervals not to exceed 1,250 flight hours. Corrective Actions (d) If any crack is detected during any inspection required by paragraph (a), (b), or (c) of this AD, and the interim repair specified by paragraph 2.C.(4) of the applicable service bulletin has not been accomplished: Prior to further flight, accomplish the actions specified by paragraph (d)(1) or (d)(2) of this AD, as applicable. (1) If only one crack is detected and that crack is 9.45 inches or less, and is within the limits specified by the applicable service bulletin: Install the interim repair specified in paragraph 2.C.(4) of the applicable service bulletin. Thereafter, repeat the HFEC inspection specified by paragraph (b) of this AD at intervals not to exceed 1,250 flight hours. Note 3: The interim repair referenced by this AD consists of cutting out the cracked portion of the fuselage skin, and installing a filler plate in the skin cutout, two doublers, and shims, as described in paragraph 2.C.(4) of the applicable service bulletin. Note 4: Accomplishment of the interim repair in accordance with paragraph 4.3 of Airbus Industrie All Operator Telex (AOT) 53–10, dated September 24, 1997, is acceptable for compliance with the requirements of paragraph (d)(1) of this AD. (2) If any crack is detected that is longer than 9.45 inches, or is outside the limits specified by the service bulletin, or if more than one crack is detected: Repair in accordance with a method approved by the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate; or the Direction Ge ´ ne ´ rale de l’Aviation Civile (DGAC) (or its delegated agent). For a repair method to be approved by the Manager, International Branch, ANM–116, as required by this paragraph, the Manager’s approval letter must specifically reference this AD. (e) If any crack is detected during any inspection required by paragraph (a), (b), or (c) of this AD and the interim repair specified by paragraph 2.C.(4) of the applicable service bulletin has been accomplished: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM–116; or the DGAC (or its delegated agent). For a repair method to be approved by the Manager, International Branch, ANM–116, as required by this paragraph, the Manager’s approval letter must specifically reference this AD. (f) Accomplishment of the modification as described in Airbus Service Bulletin A330– 53–3097, Revision 01, dated May 21, 1999 (for Model A330 series airplanes), or Service Bulletin A340–53–4108, Revision 01, dated May 21, 1999 (for Model A340 series airplanes), terminates the repetitive inspections required by paragraphs (a), (b), and (c) of this AD. Note 5: Accomplishment of Airbus production modification 46025, or the modification as described in Airbus Service Bulletin A330–53–3097, dated July 29, 1998 (for Model A330 series airplanes), or Service Bulletin A340–53–4108, dated July 31, 1998 (for Model A340 series airplanes), also constitutes terminating action for the repetitive inspections required by paragraphs (a), (b), and (c) of this AD. Alternative Methods of Compliance (g) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM–116. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM–116. Note 6: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM–116. Special Flight Permits (h) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (i) Except as provided by paragraphs (d)(2) and (e) of this AD, the actions shall be done in accordance with Airbus Service Bulletin A330–53–3094, Revision 02, dated May 28, 1998; or Airbus Service Bulletin A340–53– 4105, Revision 02, dated May 25, 1998; as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Note 7: The subject of this AD is addressed in French airworthiness directives 1998– 192–071(B)R1 (for Model A330 series airplanes) and 1998–193–089(B)R1 (for Model A340 series airplanes), both dated March 24, 1999. (j) This amendment becomes effective on April 12, 2000. Issued in Renton, Washington, on February 29, 2000. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 00–5332 Filed 3–7–00; 8:45 am] BILLING CODE 4910–13–U DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 99–NM–337–AD; Amendment 39–11616; AD 2000–05–07] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 and A300–600 Series Airplanes AGENCY : Federal Aviation Administration, DOT. ACTION : Final rule. SUMMARY : This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 and A300–600 series airplanes, that currently requires repetitive inspections to detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings at the lower flange, and repair, if necessary. That AD also VerDate 07<MAR>2000 21:27 Mar 07, 2000 Jkt 190000 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\08MRR1.SGM pfrm08 PsN: 08MRR1

12078 Federal Register / Vol. 65, No. 46 / Wednesday, March 8, 2000 / Rules and Regulations requires modification of Gear Rib 5 of the MLG attachment fittings, which constitutes terminating action for the repetitive inspections. This amendment expands the current inspection area for certain airplanes. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking of the MLG attachment fittings, which could result in reduced structural integrity of the airplane. DATES : Effective April 12, 2000. The incorporation by reference of certain publications, as listed in the regulations, is approved by the Director of the Federal Register as of April 12, 2000. The incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of October 20, 1999 (64 FR 49966, September 15, 1999). ADDRESSES : The service information referenced in this AD may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT : Norman B. Martenson, Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2110; fax (425) 227–1149. SUPPLEMENTARY INFORMATION : A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 99–19–26, amendment 39–11313 (64 FR 49966, September 15, 1999), which is applicable to certain Airbus Model A300 and A300–600 series airplanes, was published in the Federal Register on December 30, 1999 (64 FR 73439). The action proposed to continue to require repetitive inspections to detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings at the lower flange, and repair, if necessary; and modification of Gear Rib 5 of the MLG attachment fittings, which would constitute terminating action for the repetitive inspections. That action also proposed to expand the current inspection area for certain airplanes. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA’s determination of the cost to the public. Conclusion The FAA has determined that air safety and the public interest require the adoption of the rule as proposed. Cost Impact There are approximately 164 airplanes of U.S. registry that will be affected by this AD. The modification that is currently required by AD 99–19–26, and retained in this AD, takes approximately 62 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Required parts cost approximately $10,270 per airplane. Based on these figures, the cost impact of the currently required inspections on U.S. operators is estimated to be $2,294,360, or $13,990 per airplane. The new expanded inspections that are required in this AD action will take approximately 6 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the requirements of this AD on U.S. operators is estimated to be $59,040, or $360 per airplane. The cost impact figures discussed above are based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. Regulatory Impact The regulations adopted herein will 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132. For the reasons discussed above, I certify that this action (1) is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) is not a ‘‘significant rule’’ under 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. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES . List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by removing amendment 39–11313 (64 FR 49966, September 15, 1999), and by adding a new airworthiness directive (AD), amendment 39–11616, to read as follows: 2000–05–07 Airbus Industrie: Amendment 39–11616. Docket 99–NM–337–AD. Supersedes AD 99–19–26, Amendment 39–11313. Applicability: Model A300 series airplanes, as listed in Airbus Service Bulletin A300–57– 0234, Revision 01, dated March 11, 1998; and Model A300–600 series airplanes, as listed in Airbus Service Bulletin A300–57–6087, Revision 01, dated March 11, 1998; except airplanes on which Airbus Modification 11912 has been installed in production, or on which Airbus Modification 11932 has been accomplished; certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d)(1) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue cracking of the main landing gear (MLG) attachment fittings, which could result in reduced structural integrity of the airplane, accomplish the following: VerDate 07<MAR>2000 21:27 Mar 07, 2000 Jkt 190000 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 E:\FR\FM\08MRR1.SGM pfrm08 PsN: 08MRR1

12079 Federal Register / Vol. 65, No. 46 / Wednesday, March 8, 2000 / Rules and Regulations Repetitive Inspections (a) Perform a detailed visual and a high frequency eddy current (HFEC) inspection to detect cracks in Gear Rib 5 of the MLG attachment fittings at the lower flange, in accordance with Airbus Service Bulletin A300–57–6087, Revision 01, dated March 11, 1998 (for Model A300–600 series airplanes); or A300–57–0234, Revision 01, dated March 11, 1998 (for Model A300 series airplanes); as applicable; at the time specified in paragraph (a)(1) or (a)(2) of this AD, as applicable. After the effective date of this AD, only Airbus Service Bulletin A300–57A0234, Revision 02, dated June 24, 1999, or Revision 03, including Appendix 01, dated September 2, 1999 (for Model A300 series airplanes); or A300–57A6087, Revision 02, including Appendix 01, dated June 24, 1999 (for Model A300–600 series airplanes); as applicable; shall be used. Repeat the inspections thereafter at intervals not to exceed 1,500 flight cycles. Detailed Visual Inspection Note 2: For the purposes of this AD, a detailed visual 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.’’ (1) For airplanes that have accumulated 20,000 or more total flight cycles as of March 9, 1998: Inspect within 500 flight cycles after March 9, 1998. (2) For airplanes that have accumulated less than 20,000 total flight cycles as of March 9, 1998: Inspect prior to the accumulation of 18,000 total flight cycles, or within 1,500 flight cycles after March 9, 1998, whichever occurs later. Note 3: Accomplishment of the initial detailed visual and HFEC inspections in accordance with Airbus Service Bulletin A300–57A0234 or A300–57A6057, both dated August 1, 1997, as applicable, is considered acceptable for compliance with the initial inspections required by paragraph (a) of this AD. Repair (b) If any crack is detected during any inspection required by this AD, prior to further flight, accomplish the requirements of paragraphs (b)(1) or (b)(2) of this AD, as applicable. (1) If a crack is detected at one hole only, and the crack does not extend out of the spotface of the hole, repair in accordance with Airbus Service Bulletin A300-57A0234, Revision 02, dated June 24, 1999, or Revision 03, including Appendix 01, dated September 2, 1999 (for Model A300 series airplanes); or A300–57A6087, Revision 02, including Appendix 01, dated June 24, 1999 (for Model A300–600 series airplanes); as applicable. (2) If a crack is detected at more than one hole, or if any crack at any hole extends out of the spotface of the hole, repair in accordance with a method approved by the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate, or the Direction Ge ´ ne ´ rale de l’Aviation Civile (or its delegated agent). Terminating Modification (c) Prior to the accumulation of 21,000 total flight cycles, or within 2 years after October 20, 1999 (the effective date of AD 99–19–26, amendment 39–11313), whichever occurs later: Modify Gear Rib 5 of the MLG attachment fittings at the lower flange in accordance with Airbus Service Bulletin A300–57–6088, Revision 01, including Appendix 01 (for Model A300–600 series airplanes), or A300–57–0235, Revision 01, including Appendix 01 (for Model A300 series airplanes), all dated February 1, 1999, as applicable. Accomplishment of this modification constitutes terminating action for the repetitive inspection requirements of this AD. Note 4: Accomplishment of the modification required by paragraph (d) of this AD prior to the effective date of this AD in accordance with Airbus Service Bulletin A300–57–6088 or A300–57–0235, both dated August 1, 1998; as applicable; is acceptable for compliance with the requirements of that paragraph. Alternative Methods of Compliance (d)(1) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM–116. (2) Alternative methods of compliance, approved previously in accordance with AD 99–19–26, amendment 39–11313, are approved as alternative methods of compliance with this AD. Note 5: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM–116. Special Flight Permits (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (f) Except as provided by paragraph (b)(2) of this AD, the actions shall be done in accordance with Airbus Service Bulletin A300–57–6087, Revision 01, dated March 11, 1998; Airbus Service Bulletin A300– 57A6087, Revision 02, including Appendix 01, dated June 24, 1999; Airbus Service Bulletin A300–57–0234, Revision 01, dated March 11, 1998; Airbus Service Bulletin A300–57A0234, Revision 02, dated June 24, 1999; Airbus Service Bulletin A300– 57A0234, Revision 03, including Appendix 01, dated September 2, 1999; Airbus Service Bulletin A300–57–6088, Revision 01, including Appendix 01, dated February 1, 1999; and Airbus Service Bulletin A300–57– 0235, Revision 01, including Appendix 01, dated February 1, 1999; as applicable. (1) The incorporation by reference of Airbus Service Bulletin A300–57A6087, Revision 02, including Appendix 01, dated June 24, 1999; Airbus Service Bulletin A300– 57A0234, Revision 02, dated June 24, 1999; and Airbus Service Bulletin A300–57A0234, Revision 03, including Appendix 01, dated September 2, 1999; is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) The incorporation by reference of Airbus Service Bulletin A300–57–6087, Revision 01, dated March 11, 1998; Airbus Service Bulletin A300–57–0234, Revision 01, dated March 11, 1998; Airbus Service Bulletin A300–57–6088, Revision 01, including Appendix 01, dated February 1, 1999; and Airbus Service Bulletin A300–57– 0235, Revision 01, including Appendix 01, dated February 1, 1999; was approved previously by the Director of the Federal Register as of October 20, 1999 (64 FR 49966, September 15, 1999). (3) Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Note 6: The subject of this AD is addressed in French airworthiness directive 1998–151– 247(B), dated June 16, 1999. (g) This amendment becomes effective on April 12, 2000. VerDate 07<MAR>2000 21:27 Mar 07, 2000 Jkt 190000 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 E:\FR\FM\08MRR1.SGM pfrm08 PsN: 08MRR1

12080 Federal Register / Vol. 65, No. 46 / Wednesday, March 8, 2000 / Rules and Regulations Issued in Renton, Washington, on February 29, 2000. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 00–5331 Filed 3–7–00; 8:45 am] BILLING CODE 4910–13–U DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 99–NM–353–AD; Amendment 39–11617; AD 2000–05–08] RIN 2120–AA64 Airworthiness Directives; Airbus Model A319 and A321 Series Airplanes AGENCY : Federal Aviation Administration, DOT. ACTION : Final rule. SUMMARY : This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319 and A321 series airplanes, that requires replacement of the actuator of the ram air turbine (RAT) with a new actuator. This amendment also requires modification of the actuator wiring. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the RAT to deploy in an emergency situation, and consequent loss of electrical and hydraulic systems. DATES : Effective April 12, 2000. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of April 12, 2000. ADDRESSES : The service information referenced in this AD may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT : Norman B. Martenson, Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2110; fax (425) 227–1149. SUPPLEMENTARY INFORMATION : A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Airbus Model A319 and A321 series airplanes was published in the Federal Register on December 30, 1999 (64 FR 73438). That action proposed to require replacement of the actuator of the ram air turbine (RAT) with a new actuator. That action also proposed to require modification of the actuator wiring. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA’s determination of the cost to the public. Conclusion The FAA has determined that air safety and the public interest require the adoption of the rule as proposed. Cost Impact The FAA estimates that 18 airplanes of U.S. registry will be affected by this AD, that it will take approximately 4 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Required parts will be supplied by the parts manufacturer at no cost to the operators. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $4,320, or $240 per airplane. The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the proposed requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. Regulatory Impact The regulations adopted herein will 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132. For the reasons discussed above, I certify that this action (1) is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) is not a ‘‘significant rule’’ under 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. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES . List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new airworthiness directive: 2000–05–08 Airbus Industrie: Amendment 39–11617. Docket 99–NM–353–AD. Applicability: Model A319 and A321 series airplanes, certificated in any category; except those on which Airbus Modification 27015 or Airbus Service Bulletin A320–29–1088, dated February 23, 1999, has been accomplished. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the ram air turbine (RAT) to deploy in an emergency situation, and consequent loss of electrical and hydraulic systems, accomplish the following: Modification (a) Within 18 months after the effective date of this AD: Replace the RAT actuator with an improved actuator, and modify the wiring of the RAT actuator; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–29–1088, dated February 23, 1999. VerDate 07<MAR>2000 21:27 Mar 07, 2000 Jkt 190000 PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 E:\FR\FM\08MRR1.SGM pfrm08 PsN: 08MRR1