AD 2006-15-16 Airworthiness Directives; Raytheon (Beech) Model 400 and 400A Series Airplanes

Makes named: beech, raytheon. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to the airplanes identified in Table 1 of this AD, certificated in any category. Table 1.—Applicability Raytheon (Beech) model— Serials— On which— (1) 400 series airplanes RJ-1 through RJ-65 inclusive Kit part number (P/N) 128-3004-1 P or 128-3004-3 P has been incorporated (Lucas Aerospace/Goodrich Direct Current (DC) Starter Generator). (2) 400A series airplanes RK-1 through RK-23 inclusive Kit P/N 128-3004-1 P or 128-3004-3 P has been incorporated (Lucas Aerospace/Goodrich DC Starter Generator).

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Service Bulletin (f) The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of Raytheon Service Bulletin SB 24-3713, dated November 2005. Review of Logbook (g) Within 200 flight hours or 6 months after the effective date of this AD, whichever occurs first, review the airplane logbook to determine whether GCU installation kit, P/N 128-3001-1 P or 128-3001-3 P, is installed, in accordance with the service bulletin. Installation Kit Not Found Installed: Replacement of Shinko GCUs (h) If no GCU installation kit, P/N 128-3001-1 P or 128-3001-3 P, is found installed or if the kit P/N cannot be conclusively determined during the review required by paragraph (g) of this AD: Within 200 flight hours or 6 months after the effective date of this AD, whichever occurs first, replace the Shinko GCUs with new Lucas Aerospace/Goodrich GCUs (installation kit P/N 128-3001-1 P or 128-3001-3 P), in accordance with the service bulletin. Installation Kit Found Installed: Inspections of GCUs and Current Sense Transformers and Replacement of Transformers as Applicable (i) If any GCU installation kit, P/N 128-3001-1 P or 128-3001-3 P is found installed during the review required by paragraph (g) of this AD: Within 200 flight hours or 6 months after the effective date of this AD, whichever occurs first, inspect to determine the P/N of both GCUs, in accordance with the service bulletin; and at the times specified in Table 2 of this AD, do the applicable action(s) in that table. Table 2.—Inspection and Replacement of Current Sense Transformers If— Then, within 200 flight hours or 6 months after the effective date of this AD, whichever occurs first— If— Then— (1) Both GCUs have P/N 45AS88801-19 or -25 Inspect to determine the P/N of both current sense transformers on the lower inboard quadrant of the left-hand and right-hand engine inlets, in accordance with the service bulletin Both current sense transformers have P/N 45AS88801-21 Either current sense transformer is not identified with P/N 45AS88801-21 No further action is required by this AD. Within 200 flight hours or 6 months after the effective date of this AD, whichever occurs first, replace the current sense transformer with a new transformer, P/N 45AS88801-21, in accordance with the service bulletin. (2) Either GCU does not have P/N 45AS88801-19 or -25 Replace the GCU with a new GCU, P/N 45AS88801-19 or -25, and inspect to determine the P/N of both current sense transformers on the lower inboard quadrant of the left-hand and right-hand engine inlets, in accordance with the service bulletin Both current sense transformers have P/N 45AS88801-21 Either current sense transformer is not identified with P/N 45AS88801-21 No further action is required by this AD. Within 200 flight hours or 6 months after the effective date of this AD, whichever occurs first, replace the current sense transformer with a new transformer, P/N 45AS88801-21, in accordance with the service bulletin. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Wichita Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Material Incorporated by Reference (k) You must use Raytheon Service Bulletin SB 24-3713, dated November 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Raytheon Aircraft Company, Department 62, P.O. Box 85, Wichita, Kansas 67201-0085, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Renton, Washington, on July 20, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-12107 Filed 7-28-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of over-voltage conditions of the DC starter generator. We are issuing this AD to prevent over-voltage conditions of the DC starter generator due to the incompatibility between certain generator control units (GCUs), which could result in the loss of normal electrical power, damage to some electrical components, or blown fuses during flight, and consequent unrecoverable loss of some or all essential equipment.