AD 00-6162

14847 Federal Register / Vol. 65, No. 54 / Monday, March 20, 2000 / Rules and Regulations accomplished: Inspect prior to the accumulation of 11,600 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later. (v) For Model BAe 146–300 airplanes on which Modification HCM01000B has not been accomplished: Inspect prior to the accumulation of 17,200 total flight cycles, or within 1,400 flight cycles after the effective date of this AD, whichever occurs later. (b) Repeat the inspections required by paragraph (a) of this AD at the intervals defined in Significant Structural Item (SSI) Task No. 53–20–160 as detailed in Section 6 of the BAe 146 Maintenance Review Board Report, Revision 5, dated November 1998. Corrective Action (c) If any cracking is detected during any inspection required by paragraph (a) or (b) of this AD, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate; or the Civil Aviation Authority (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. Alternative Methods of Compliance (d) 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 4: 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 §§ 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) The inspections shall be done in accordance with British Aerospace Service Bulletin SB.53–144, dated April 27, 1998, or British Aerospace Service Bulletin SB.53– 144, Revision 1, May 21, 1999. Revision 1 of British Aerospace Service Bulletin 53–144 contains the following list of effective pages: Page No. Revision level shown on page Date shown on page 1–3, 7 .......... 1 .................. May 21, 1999. 4–6, 8–10 .... Original ........ April 27, 1998. (1) The incorporation by reference of British Aerospace Service Bulletin SB.53– 144, Revision 1, dated May 21, 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 British Aerospace Service Bulletin SB.53– 144, dated April 27, 1998, was approved previously by the Director of the Federal Register as of November 10, 1998 (63 FR 53550, October 6, 1998). (3) Copies may be obtained from British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171. 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 5: The subject of this AD is addressed in British airworthiness directive 005–04–98. (g) This amendment becomes effective on April 24, 2000. Issued in Renton, Washington, on March 9, 2000. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 00–6329 Filed 3–17–00; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 99–CE–57–AD; Amendment 39– 11633; AD 2000–05–23] RIN 2120–AA64 Airworthiness Directives; Ayres Corporation S2R Series Airplanes AGENCY : Federal Aviation Administration, DOT. ACTION : Final rule. SUMMARY : This amendment adopts a new airworthiness directive (AD) that applies to all Ayres Corporation (Ayres) S2R series airplanes that are equipped with at least one main landing gear fuselage attach bolt with a grease fitting installed through the shank. This AD requires replacing the main landing gear fuselage attach bolts that are drilled with a grease fitting with undrilled (no grease access) attach bolts. This AD is the result of a report of cracks found in all four main landing gear fuselage attach bolts on one of the affected airplanes. The actions specified by this AD are intended to prevent collapse of the main landing gear caused by cracked main landing gear fuselage attach bolts, which could result in main landing gear collapse with possible wing fuel tank rupture and consequent fire. DATES : Effective May 5, 2000. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 5, 2000. ADDRESSES : Service information that applies to this AD may be obtained from Ayres Corporation, P.O. Box 3090, One Ayres Way, Albany, Georgia 31706– 3090; telephone: (912) 883–1440; facsimile: (912) 439–9790. This information may also be examined at the Federal Aviation Administration (FAA), Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 99–CE–57–AD, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT : Satish Lall, Aerospace Engineer, FAA, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone: (770) 703–6082; facsimile: (770) 703–6097. SUPPLEMENTARY INFORMATION : Events Leading to the Issuance of This AD A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to all Ayres S2R series airplanes of the same type design, that are equipped with at least one main landing gear fuselage attach bolt with a grease fitting installed through the shank, was published in the Federal Register as a notice of proposed rulemaking (NPRM) on November 24, 1999 (64 FR 66116). The NPRM proposed to require replacing the main landing gear fuselage attach bolts that are drilled with a grease fitting with undrilled (no grease access) attach bolts. Accomplishment of the proposed action as specified in the NPRM would be required in accordance with both Ayres Service Bulletin No. SB-AG-42, dated June 16, 1999, and the applicable maintenance manual. The NPRM was the result of a report of cracks found in all four main landing gear fuselage attach bolts on one of the affected airplanes. Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposed rule or the FAA’s determination of the cost to the public. The FAA’s Determination After careful review of all available information related to the subject presented above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed except for minor VerDate 13<MAR>2000 20:03 Mar 17, 2000 Jkt 190000 PO 00000 Frm 00067 Fmt 4700 Sfmt 4700 E:\FR\FM\20MRR1.SGM pfrm01 PsN: 20MRR1

14848 Federal Register / Vol. 65, No. 54 / Monday, March 20, 2000 / Rules and Regulations editorial corrections. The FAA has determined that these minor corrections will not change the meaning of the AD and will not add any additional burden upon the public than was already proposed. Differences Between the Service Bulletin and this AD Ayres Service Bulletin No. SB-AG–42, dated June 16, 1999, specifies repetitive inspections and repetitive replacements of the main landing gear fuselage attach bolts. The FAA does not have justification to mandate the repetitive inspections and repetitive replacements. Based on all available information, the FAA has determined that initially replacing the main landing gear fuselage attach bolts with attach bolts of improved design will correct the unsafe condition on the affected airplanes. Cost Impact The FAA estimates that 1,000 airplanes in the U.S. registry will be affected by this AD, that it will take approximately 4 workhours per airplane to accomplish the replacement, and that the average labor rate is approximately $60 an hour. Parts cost approximately $88 per airplane (4 bolts per airplane at $22 each). Based on these figures, the total cost impact of this AD on U.S. operators is estimated to be $328,000, or $328 per airplane. 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 copy of the final evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting 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 a new airworthiness directive (AD) to read as follows: 2000 –05 –23 AYRES CORPORATION : Amendment 39–11633; Docket No. 99–CE–57–AD. Applicability: The following airplane models, all serial numbers, certificated in any category, that have at least one main landing gear fuselage attach bolt (that is drilled with a grease fitting), part number 21418T001 or 21418T005 (or FAA-approved equivalent part number): Models S–2R, S2R–G1, S2R–G5, S2R–G6, S2R– G10, S2R–R3S, S2R–T11, S2R–T15, S2R– T34, S2R–T45, S2R–T65, S2R–R1340, S2R– R1820, S2RHG–T34, and S2RHG–T65. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been 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) 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 in the body of this AD, unless already accomplished. To prevent collapse of the main landing gear caused by cracked main landing gear fuselage attach bolts, which could result in main landing gear collapse with possible wing fuel tank rupture and consequent fire, accomplish the following: (a) Within the next 100 hours time-in- service (TIS) after the effective date of this AD, replace each main landing gear fuselage attach bolt that is drilled with a grease fitting with an undrilled (no grease access) attach bolt, part number AN10–33 or NAS6610–42D (or FAA-approved equivalent part number). Accomplish this replacement in accordance with both Ayres Service Bulletin No. SB– AG–42, dated June 16, 1999, and the applicable maintenance manual. (b) As of the effective date of this AD, no person may install, on any affected airplane, a main landing gear fuselage attach bolt (that is drilled with a grease fitting), part number 21418T001 or 21418T005 (or FAA-approved equivalent part number). (c) Special flight permits may be issued in accordance with §§ 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. (d) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office (ACO), One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. (e) The replacements required by this AD shall be done in accordance with Ayres Service Bulletin No. SB–AG–42, dated June 16, 1999. 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 Ayres Corporation, P.O. Box 3090, One Ayres Way, Albany, Georgia 31706–3090. Copies may be inspected at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (f) This amendment becomes effective on May 5, 2000. Issued in Kansas City, Missouri, on March 7, 2000. Michael Gallagher, Manager, Small Airplane Directorate Aircraft Certification Service. [FR Doc. 00–6162 Filed 3–17–00; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 99–NM–73–AD; Amendment 39–11629; AD 2000–05–19] RIN 2120–AA64 Airworthiness Directives; Boeing Model 727 Series Airplanes AGENCY : Federal Aviation Administration, DOT. ACTION : Final rule. VerDate 13<MAR>2000 20:03 Mar 17, 2000 Jkt 190000 PO 00000 Frm 00068 Fmt 4700 Sfmt 4700 E:\FR\FM\20MRR1.SGM pfrm01 PsN: 20MRR1