AD 2003-04-20 Airworthiness Directives; Raytheon Model DH.125, HS.125, and BH.125 Series Airplanes; Model BAe.125 Series 800A, 800A (C-29A), 800A (U-125), 800B, 1000A, and 1000B Airplanes; and Model Hawker 800, 800 (including variant U-125A), 1000, and 800XP Airplanes

Makes named: raytheon. Models named: DH.125, HS.125, BH.125 series. Read the applicability below — it usually turns on serial or part numbers too.

Model DH.125, HS.125, and BH.125 series airplanes; Model BAe.125 series 800A, 800A (C-29A), 800A (U-125), 800B, 1000A, and 1000B airplanes; and Model Hawker 800, 800 (including variant U-125A), 1000, and 800XP airplanes; as listed in Raytheon Service Bulletin 32-3391, dated August 2000; 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 (e) 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, unless accomplished previously. To prevent separation of the cylinder head lugs, which could prevent the main landing gear (MLG) from extending and result in a partial gear-up landing, accomplish the following: Restatement of Certain Requirements of AD 2001-17-26 R1: Inspection (a) For Model DH.125, HS.125, and BH.125 series airplanes; BAe.125 series 800A, 800A (C-19A), 800A (U-125A), 1000A, and 1000B airplanes; and Model Hawker 800, 800 (including variant U-125A), 800XP, and 1000 airplanes: Perform an eddy current inspection of the actuator cylinder head lugs for cracking or corrosion per Raytheon Service Bulletin 32-3391, dated August 2000, at the time specified in paragraph (a)(1), (a)(2), (a)(3), or (a)(4) of this AD, as applicable. (1) For actuator cylinder heads that have 3,000 or less total landings as of October 3, 2001 (the effective date of AD 2001-17-26 R1, amendment 39-12619): Perform the eddy current inspection within 24 months after October 3, 2001. (2) For actuator cylinder heads that have 3,001 to 4,000 total landings as of October 3, 2001: Perform the eddy current inspection within 6 months after October 3, 2001. (3) For actuator cylinder heads that have been in service for more than 7 years as of October 3, 2001: Perform the eddy current inspection within 6 months after October 3, 2001. (4) For actuator cylinder heads that have 4,001 or more total landings as of October 3, 2001: Perform the eddy current inspection within 10 landings after October 3, 2001. New Requirements of this AD: (b) For Model BAe.125 series 800B airplanes: Perform an eddy current inspection of the actuator cylinder head lugs for cracking or corrosion per Raytheon Service Bulletin 32-3391, dated August 2000, at the time specified in paragraph (b)(1), (b)(2), or (b)(3) of this AD, as applicable. (1) For actuator cylinder heads that have 3,000 or less total landings as of the effective date of this AD: Perform the eddy current inspection within 24 months after the effective date of this AD. (2) For actuator cylinder heads that have 3,001 to 4,000 total landings as of the effective date of this AD: Perform the eddy current inspection within 6 months after the effective date of this AD. (3) For actuator cylinder heads that have been in service for more than 7 years or that have 4,001 or more total landings as of the effective date of this AD: Perform the eddy current inspection at the earlier of the times specified in paragraph (b)(3)(i) or (b)(3)(ii) of this AD. (i) Within 6 months after the effective date of this AD. (ii) Within 10 landings after the effective date of this AD. If No Cracking or Corrosion (c) If no cracking or corrosion is found during the inspection required by paragraph (a) or (b) of this AD, before further flight, accomplish follow-on actions ( e.g. , “vibro-etching” the MLG actuator data plate, painting a blue stripe on the actuator cylinder head to indicate 1 1/32 -inch oversize bushings, replacing bushings, and applying corrosion protection to the lug bores), per Raytheon Service Bulletin 32-3391, dated August 2000. If Any Cracking or Corrosion (d) If any cracking or corrosion is found during the inspection required by paragraph (a) or (b) of this AD, before further flight, accomplish either of the actions specified in paragraph (d)(1) or (d)(2) of this AD, per Raytheon Service Bulletin 32-3391, dated August 2000: (1) Replace the actuator of the MLG with a new or serviceable actuator; or (2) Replace the actuator cylinder head with a new cylinder head. Note 2: Raytheon Service Bulletin 32-3391, dated August 2000, references Precision Hydraulics Component Maintenance Manual 32-30-1105 as an additional source of service information. Alternative Methods of Compliance (e) 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. 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 (f) 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 (g) The actions shall be done in accordance with Raytheon Service Bulletin 32-3391, dated August 2000. This incorporation by reference of that document was approved previously by the Director of the Federal Register as of October 3, 2001 (66 FR 45575, August 29, 2001). Copies may be obtained from Raytheon Aircraft Company, Department 62, 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, 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. Effective Date (h) This amendment becomes effective on April 4, 2003. Issued in Renton, Washington, on February 19, 2003. Ali Bahrami, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-4586 Filed 2-27-03; 8:45 am] BILLING CODE 4910-13-P