AD 00-5328

12082 Federal Register / Vol. 65, No. 46 / Wednesday, March 8, 2000 / Rules and Regulations § 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: 2000–05–05 Construcciones Aeronauticas, S.A. (CASA): Amendment 39–11614. Docket 99–NM–261–AD. Applicability: All Model CN–235–100 and CN–235–200 series airplanes, certificated in any category. 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 (c) 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 ice accumulation on the wings or tail of the airplane, which could result in reduced controllability of the airplane, accomplish the following: Replacement (a) Within 4 months after the effective date of this AD, replace the existing anti-icing distributor valves, having part number (P/N) AC960013, in the wing and tail areas of the airplane, with new, improved valves, having P/N AC911016, in accordance with CASA Service Bulletin SB–235–30–14, dated August 13, 1999. (b) As of the effective date of this AD, no person shall install a distributor valve having P/N AC960013 on any airplane. Alternative Methods of Compliance (c) 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. Note 2: 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 (d) 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 (e) The replacement shall be done in accordance with CASA Service Bulletin SB– 235–30–14, dated August 13, 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 Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain. 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 3: The subject of this AD is addressed in Spanish airworthiness directive 04/99, dated July 30, 1999. (f) 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. 00–5329 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–334–AD; Amendment 39–11615; AD 2000–05–06] RIN 2120–AA64 Airworthiness Directives; Raytheon (Beech) Model 400A and 400T Series Airplanes AGENCY : Federal Aviation Administration, DOT. ACTION : Final rule. SUMMARY : This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon (Beech) Model 400A and 400T series airplanes, that requires a one-time inspection to detect incorrect wiring of the engine fire extinguisher bottle squibs, and corrective action, if necessary. It also requires a modification to the wiring and the addition of wire harness and bottle labeling for future reference. This amendment is prompted by reports of incorrect wiring of the engine fire extinguisher bottle squibs. The actions specified by this AD are intended to prevent failure of the engine fire extinguisher bottle to discharge, or discharge of the wrong engine fire extinguisher bottle. 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 Raytheon Aircraft Company, Manager Service Engineering, Beechjet/ Premier Technical Support Department, P.O. Box 85, Wichita, Kansas 67201– 0085. 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 FAA, Small Airplane Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT : Todd Dixon, Aerospace Engineer, Systems and Propulsion Branch, ACE– 116W, FAA, Small Airplane Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid- Continent Airport, Wichita, Kansas 67209; telephone (316) 946–4152; fax (316) 946–4407. 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 Raytheon (Beech) Model 400A and 400T series airplanes was published in the Federal Register on December 6, 1999 (64 FR 68060). That action proposed to require a one-time inspection to detect incorrect wiring of the engine fire extinguisher bottle squibs, and corrective action, if necessary. It also proposed to require a modification to the wiring and the addition of wire harness and bottle labeling for future reference. 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 350 airplanes of the affected design in the worldwide fleet. The FAA estimates that 310 airplanes of U.S. registry will be affected by this AD. It is estimated that it will take approximately 1 work hour per airplane to accomplish the required inspection, VerDate 07<MAR>2000 21:27 Mar 07, 2000 Jkt 190000 PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 E:\FR\FM\08MRR1.SGM pfrm08 PsN: 08MRR1

12083 Federal Register / Vol. 65, No. 46 / Wednesday, March 8, 2000 / Rules and Regulations at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the inspection portion of the AD on U.S. operators is estimated to be $18,600, or $60 per airplane. It is estimated that it will take approximately 2 work hours per airplane to accomplish the required modification, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the modification portion of the required AD on U.S. operators is estimated to be $37,200, or $120 per airplane. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $55,800, or $180 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. However, the FAA has been advised that manufacturer warranty remedies are available for labor costs associated with accomplishing the actions required by this AD. Therefore, the future economic cost impact of this rule on U.S. operators may be less than the cost impact figure indicated above. 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 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: 2000–05–06 Raytheon Aircraft Company (Formerly Beech): Amendment 39– 11615. Docket 99–NM–334–AD. Applicability: Model 400A series airplanes, serial numbers RK–45 and RK–49 through RK–209 inclusive; Model 400T series airplanes (T–1A), serial numbers TT–01 through TT–180 inclusive; and Model 400T series airplanes (TX), serial numbers TX–01 through TX–09 inclusive; certificated in any category. 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 (c) 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 engine fire extinguisher bottle to discharge, or discharge of the wrong engine fire extinguisher bottle, accomplish the following: Inspection and Corrective Action (a) Within 50 flight hours after the effective date of this AD: Perform a one-time general visual inspection of the left and right engine fire extinguisher bottle squibs to detect wiring that is incorrect as specified by Raytheon Aircraft Service Bulletin SB 26– 3250, Revision 1, dated July 1999. Perform the inspection in accordance with the service bulletin. If any incorrect wiring is detected, prior to further flight, repair it in accordance with the service bulletin. Note 2: For the purposes of this AD, a general visual inspection is defined as: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or drop- light, and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ Modification (b) Within 200 flight hours after the effective date of this AD: Modify and re-label the wiring of the left and right engine fire extinguisher bottle squibs, in accordance with Raytheon Aircraft Service Bulletin SB 26–3250, Revision 1, dated July 1999. Alternative Methods of Compliance (c) 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, Wichita Aircraft Certification Office (ACO), FAA, Small 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, Wichita ACO. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. Special Flight Permits (d) 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 (e) The actions shall be done in accordance with Raytheon Aircraft Service Bulletin SB 26–3250, Revision 1, dated July 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 Raytheon Aircraft Company, Manager Service Engineering, Beechjet/Premier Technical Support Department, P.O. Box 85, Wichita, Kansas 67201–0085. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid- Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) 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. 00–5328 Filed 3–7–00; 8:45 am] BILLING CODE 4910–13–U VerDate 07<MAR>2000 21:27 Mar 07, 2000 Jkt 190000 PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 E:\FR\FM\08MRR1.SGM pfrm08 PsN: 08MRR1