2000-23-13: Horizontal Stabilizer Trim Actuator

2000-23-13 ISRAEL AIRCRAFT INDUSTRIES, LTD.: Amendment 39-11985. Docket 2000-NM-364-AD. Applicability: All Model 1121, 1121A, 1121B, 1123, 1124, and 1124A series airplanes; 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 (c) 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. Compliance: Required as indicated, unless accomplished previously. To prevent jamming or disconnection of the horizontal stabilizer trim actuator, which could result in reduced pitch control of the airplane, accomplish the following: Inspection (a) Within 25 flight hours after the effective date of this AD: Perform a detailed visual inspection to determine whether the tie rod is installed correctly through the dust shield and both jackscrew assemblies of the horizontal stabilizer trim actuator. Do the inspection per Israel Aircraft Industries Alert Service Bulletins 1121-27A-028 (for 1121 JET COMMANDER series airplanes), 1123-27A-053 (for 1123 WESTWIND series airplanes), or 1124-27A-147 (for 1124 and 1124A WESTWIND series airplanes); all dated August 28, 2000; as applicable. Note 2: For the purposes of this AD, a detailed visual inspection is defined as: "An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required." (1) If both the tie rod and the dust shield are correctly assembled: No further action is required by this AD. (2) If either the tie rod or the dust shield is not correctly assembled: Prior to further flight, accomplish the actions specified by either paragraph (a)(2)(i) or (a)(2)(ii). (i) Replace the horizontal stabilizer trim actuator with a serviceable part in accordance with the airplane maintenance manual. Or (ii) Repair the horizontal stabilizer trim actuator in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Civil Aviation Administration of Israel (CAAI) (or its delegated agent). For a repair method to be approvedby the Manager, International Branch, ANM-116, as required by this paragraph, the Manager's approval letter must specifically reference this AD. Spares (b) As of the effective date of this AD, no person shall install a horizontal stabilizer trim actuator on any airplane, unless the actuator has been inspected and all applicable corrective actions have been performed in accordance with the requirements of this AD. Alternative Methods of Compliance (c) 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, International Branch, ANM-116. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the InternationalBranch, ANM-116. Special Flight Permits (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. Incorporation by Reference (e) Except as provided by paragraphs (a)(2)(i) and (a)(2)(ii) of this AD: The actions shall be done in accordance with the following alert service bulletins: Service Bulletin Date 1121 Commodore Jet Alert Service Bulletin 1121-27A-028 August 28, 2000 1123-Westwind Alert Service Bulletin 1123-27A-053 August 28, 2000 1124-Westwind Alert Service Bulletin 1124-27A-147 August 28, 2000 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 Galaxy Aerospace Corporation, One Galaxy Way, Fort Worth Alliance Airport, Fort Worth, Texas76177. 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. Note 4: The subject of this AD is addressed in Israeli airworthiness directive 27-00-09-01, dated September 24, 2000. Effective Date (f) This amendment becomes effective on December 4, 2000