AD 99-10-06 Airworthiness Directives; Raytheon Aircraft Corporation Model Beech 2000 Airplanes

Makes named: beech, raytheon. Models named: Beech 2000. Read the applicability below — it usually turns on serial or part numbers too.

Model Beech 2000 airplanes, serial numbers NC-4 through NC-53, certificated in any category, that do not have Raytheon Kit 122-4019, Rev. B, dated March 12, 1999, incorporated. 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 (g) 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.

Required as indicated in the body of this AD, unless already accomplished. To detect and correct delamination of the wing cove skin in the area of the support rib, which could result in the delamination propagating to the trailing edge of the wing with the wing cove skin panel possibly separating from the wing, accomplish the following: (a) Prior to further flight, incorporate Raytheon Temporary Changes to the FAA Approved Airplane Flight Manual (AFM), part number (P/N) 122-590013-37BTC3, Rev. 1, dated March 12, 1999, into the Limitations Section of the AFM. The requirements of the AFM temporary revisions include not allowing flap operation during takeoff and accomplishing preflight visual checks (referred to as visual inspections in the AFM temporary revisions) of the aft cove panel of the wing for delamination (debonding) prior to each flight and incorporating a repair scheme if delamination (debonding) is found. Note 2: The visual checks referenced in the AFM temporary revisions may be performed by the pilot. (b) Visually inspect the trailing edge of the wing by looking for delaminations (debonding) (also referred to as cracks in the service information) through the thickness of the trailing edge of the wing cove skin panel, in accordance with Raytheon Safety Communique No. 158, dated March 1999, at the compliance times specified in paragraphs (b)(1) and (b)(2) of this AD. (1) Initial Inspection: Within the next 10 hours time-in-service (TIS) after the effective date of this AD or prior to further flight after any delamination (debonding) is found during any preflight visual check specified in the AFM temporary revisions required by paragraph (a) of this AD, whichever occurs first; and (2) Repetitive Inspections: Thereafter (after each inspection) at intervals not to exceed 50 hours TIS or prior to further flight after any delamination (debonding) is found during any preflight check specified in the AFM temporary revisions required in paragraph (a) of this AD, whichever occurs first. (c) If any delamination (debonding) is found during any of the preflight checks or inspections of the aft cove panel of the wing required by paragraphs (a) and (b) of this AD, prior to further flight, accomplish the following: (1) Delamination (Debonding) Found During the Preflight Visual Checks Specified in the AFM Revisions Required by Paragraph (a) of This AD: In addition to the inspection required by paragraph (b) of this AD, incorporate one of the following: (i) Raytheon Field Repair drawing FR-SS-00010, Reinforcement of Aft cove panel of Flap Cove Assy P/N 122-100079-1/2, as referenced in Raytheon Safety Communique No. 158, dated March 1999; or (ii) Raytheon Kit 122-4019, Rev. B, dated March 12, 1999. This kit includes the procedures and parts necessary for modifying the attachment of the support rib at the center flap track. (2) Delamination (Debonding) Found During Any Inspection Required by Paragraph (b) of This AD: Incorporate Raytheon Kit 122- 4019, Rev. B, dated March 12, 1999. This kit includes the procedures and parts necessary for modifying the rib attachment center flap track. (d) Incorporating Raytheon Kit 122-4019, Rev. B, dated March 12, 1999, as specified in paragraphs (c)(1)(ii) and (c)(2) of this AD constitutes terminating action for the AFM and repetitive inspection requirements of paragraphs (a) and (b) of this AD, respectively. This kit may be incorporated at any time, but must be incorporated if any delamination is found during any inspection required by paragraph (b) of this AD. (e) Incorporating the AFM temporary revisions as required by paragraph (a) of this AD may be performed by the owner/operator holding at least a private pilot certificate as authorized by Sec. 43.7 of the Federal Aviation Regulations (14 CFR 43.7), and must be entered into the aircraft records showing compliance with this AD in accordance with Sec. 43.9 of the Federal Aviation Regulations (14 CFR 43.9). (f) Special flight permits may be issued in accordance with Secs. 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 inspections and modifications required by paragraphs (b) and (c) of this AD can be accomplished. The AFM temporary revisions required by paragraph (a) of this AD must be incorporated prior to this flight. (g) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, Mid- Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA 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. (h) The inspections required by this AD shall be done in accordance with Raytheon Safety Communique No. 158, dated March 1999. The modification required by this AD shall be done in accordance with Raytheon Field Repair drawing FR-SS-00010, Revision A, dated February 24, 1999, as referenced in Raytheon Safety Communique No. 158, dated March 1999; or Raytheon Field Service Kit 122-4019, Revision B, dated March 12, 1999. [[Page 24510]] (1) 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 the Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085. (2) Copies may be inspected at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (i) This amendment becomes effective on June 3, 1999. Issued in Kansas City, Missouri, on April 29, 1999. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 99-11320 Filed 5-6-99; 8:45 am] BILLING CODE 4910-13-U