AD 97-26-15 Airworthiness Directives; Raytheon Aircraft Company Models 1900, 1900C, and 1900D Airplanes

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

The following model and serial number airplanes, certificated in any category, that are equipped with at least one part number (P/N) 114-380041-11 (or FAA-approved equivalent part number) main landing gear actuator: ------------------------------------------------------------------------ Model Serial numbers ------------------------------------------------------------------------ 1900...................................... UA-2 and UA-3. 1900C..................................... UB-1 through UB-74, and UC-1 through UC-174. 1900C (C-12J)............................. UD-1 through UD-6. 1900D..................................... UE-1 through UE-249 and UE- 252. ------------------------------------------------------------------------ Note 1: The airplanes affected by this AD could have main landing gear actuators installed that have Parts Manufacturer Approval (PMA). For those airplanes having PMA parts that are equivalent (PMA by equivalency) to those referenced in this AD, the phrase ``or FAA-approved equivalent part number'' means that this AD applies to airplanes with PMA by equivalency main landing gear actuators installed. Note 2: 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 installation, 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 prevent actuator rod end failure caused by excessive friction in the rod end bearing, which could result in the inability to lower the main landing gear or result in landing gear collapse during landing, accomplish the following: (a) Upon accumulating 1,200 hours time-in-service (TIS) on each P/N 114-380041-11 (or FAA-approved equivalent part number) main landing gear actuator or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, lubricate the actuator rod ends in accordance with Raytheon Safety Communique 1900-128, dated October 25, 1996. (1) Installation of P/N M81935/1-8K (or FAA-approved equivalent part number) main landing gear actuator rod ends constitutes terminating action to the lubricating requirements of paragraph (a) of this AD. (2) Installing the P/N M81935/1-8K (or FAA-approved equivalent part number) main landing gear actuator rod ends may be accomplished at any time prior to the next 600 hours TIS, at which time they must be installed (see paragraph (b) of this AD). (b) Within the next 600 hours TIS after the effective date of this AD, install Teflon-lined main landing gear actuator rod ends, P/N M81935/1-8K (or FAA-approved equivalent part number), in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Raytheon Mandatory Service Bulletin No. 2730, Issued: November, 1996. (c) As of the effective date of this AD, no person may install a P/N 114-380041-11 (or FAA-approved equivalent part number) main landing gear actuator without replacing the rod ends with P/N M81935/1-8K (or FAA-approved equivalent part number). Installing these Teflon-lined rod ends re-identifies the main landing gear actuator as P/N 114-380041-13. (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. (e) An alternative method of compliance or adjustment of the compliance time 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. (f) The lubrication required by this AD shall be done in accordance with Raytheon Safety Communique 1900-128, dated October 25, 1996. The installation required by this AD shall be done in accordance with Raytheon Mandatory Service Bulletin No. 2730, Issued: November, 1996. 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. 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. (g) This amendment (39-10258) becomes effective on January 25, 1998. Issued in Kansas City, Missouri, on December 10, 1997. Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 97-32994 Filed 12-18-97; 8:45 am] BILLING CODE 4910-13-U