AD 89-18-07 Airworthiness Directives; Raytheon Model BAe.125, DH.125, BH.125, and HS.125 Series Airplanes

Makes named: raytheon. Models named: BAe.125, DH.125, BH.125, HS.125 series, DH.125-400B, BH.125-400B, - 600B, HS.125-600B, -700B, BAe 125-800B series. Read the applicability below — it usually turns on serial or part numbers too.

Model BAe.125, DH.125, BH.125, and HS.125 series airplanes; up to and including series 700; 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 (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. Note 2: Raytheon (Beech) Model DH.125-400B, BH.125-400B and - 600B, HS.125-600B and -700B, and BAe 125-800B series airplanes are similar in design to the airplanes that are subject to the requirements of this AD, and, therefore, also may be subject to the unsafe condition addressed by this AD. However, as of the effective date of this AD, those models are not type certificated for operation in the United States. Airworthiness authorities of countries in which those models are approved for operation should consider adopting corrective action, applicable to these models, that is similar to the corrective action required by this AD.

Required as indicated, unless accomplished previously. To prevent control surface interference and jamming of flight controls, accomplish the following: (a) Within 3 years since the date of airplane manufacture, or within 60 days after September 21, 1989 (the effective date of AD 89-18-07, amendment 39-6297), whichever occurs later, accomplish the following: (1) Inspect the elevator mass balance weight side plate assembly and balance weight spigot for corrosion, in accordance with British Aerospace Service Bulletin 27-142, Revision 2, dated June 10, 1987, or Revision 3, dated November 13, 1989. Any corrosion detected during this inspection must be repaired prior to further flight, in accordance with the service bulletin. (2) Apply corrosion protection treatment and install Monel rivets, part number MS9318-052, or British Standard Specification SP88-304 rivets, in the elevator balance weight structure, in accordance with British Aerospace Service Bulletin 27-142, Revision 2, dated June 10, 1987, or Revision 3, dated November 13, 1989. (b) 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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) 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. (d) The actions shall be done in accordance with British Aerospace Service Bulletin 27-142, Revision 2, dated June 10, 1987, or British Aerospace Service Bulletin 27-142, Revision 3, dated November 13, 1989, which contains the following list of effective pages: ------------------------------------------------------------------------ Revision Page No. level shown Date shown on page on page ------------------------------------------------------------------------ 1............................. 3............ November 13, 1989. 2............................. Original..... May 15, 1987. 3............................. 2............ June 10, 1987. 4............................. 1............ May 21, 1987. ------------------------------------------------------------------------ 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, Hawker Customer 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 Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on December 18, 1998. Issued in Renton, Washington, on November 3, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-30050 Filed 11-12-98; 8:45 am] BILLING CODE 4910-13-U