AD 98-05-09 Airworthiness Directives; Israel Aircraft Industries (IAI), Ltd., Model 1121, 1121A, 1121B, 1123, 1124, and 1124A Series Airplanes

Models named: 1121, 1121A, 1121B, 1123, 1124, 1124A series. Read the applicability below — it usually turns on serial or part numbers too.

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 (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 ensure that the trim actuator of the horizontal stabilizer operates properly, accomplish the following: (a) Perform an inspection of the trim actuator of the horizontal stabilizer to verify jackscrew integrity and to detect excessive wear of the tie rod, in accordance with Commodore Jet Service Bulletin SB 1121-27-023, dated August 14, 1996, or Revision 1, dated May 28, 1997 (for Model 1121,1121A, and 1121B series airplanes); Westwind Service Bulletin SB 1123-27-046, dated August 14, 1996, or Revision 1, dated May 28, 1997 (for Model 1123 series airplanes); or Westwind Service Bulletin 1124-27-133, dated August 14, 1996, or Revision 1, dated May 28, 1997 (for Model 1124 and 1124A series airplanes), as applicable; at the time specified in paragraph (a)(1) or (a)(2) of this AD, as applicable. (1) For airplanes that have accumulated 6,000 or more total flight cycles, or on which the horizontal trim actuator has accumulated 2,000 or more flight cycles as of the effective date of this AD: Inspect within 50 flight hours after the effective date of this AD. Repeat the inspection thereafter at intervals not to exceed 300 flight hours (for Model 1121, 1121A, 1121B, and 1123 series airplanes); or 400 flight hours (for Model 1124 and 1124A series airplanes); as applicable. (2) For airplanes that have accumulated less than 6,000 total flight cycles, and on which the horizontal trim actuator has [[Page 11108]] accumulated less than 2,000 total flight cycles as of the effective date of this AD: Inspect at the times specified in paragraph (a)(2)(i) or (a)(2)(ii) of this AD, as applicable. (i) For Model 1121, 1121A, 1121B, and 1123 series airplanes: Inspect within 300 flight hours after the effective date of this AD. Repeat the inspection thereafter at intervals not to exceed 300 flight hours. (ii) For Model 1124 and 1124A series airplanes: Inspect within 400 flight hours after the effective date of this AD. Repeat the inspection thereafter at intervals not to exceed 400 flight hours. (b) If any discrepancy is found during any inspection required by paragraph (a) of this AD, prior to further flight, replace the actuator or tie rod, as applicable, in accordance with Commodore Jet Service Bulletin SB 1121-27-023, dated August 14, 1996, or Revision 1, dated May 28, 1997 (for Model 1121, 1121A, and 1121B series airplanes); Westwind Service Bulletin SB 1123-27-046, dated August 14, 1996, or Revision 1, dated May 28, 1997 (for Model 1123 series airplanes); or Westwind Service Bulletin 1124-27-133, dated August 14, 1996, or Revision 1, dated May 28, 1997 (for Model 1124 and 1124A series airplanes); as applicable. (c) As of the effective date of this AD, no horizontal stabilizer trim actuator shall be installed on any airplane unless that trim actuator has been inspected in accordance with the requirements of paragraph (a) of this AD. (d) Replacement of the trim actuator of the horizontal stabilizer with a modified trim actuator with modified jackscrew assemblies in accordance with Commodore Jet Service Bulletin SB 1121-27-025, dated December 22, 1997 (for Model 1121, 1121A, and 1121B series airplanes); Westwind Service Bulletin SB 1123-27-047, dated September 1, 1997 (for Model 1123 series airplanes); or Westwind Service Bulletin 1124-27-136, dated September 1, 1997 (for Model 1124 and 1124A series airplanes), as applicable; constitutes terminating action for the requirements of this AD. (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, International Branch, ANM-116, 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, International Branch, ANM-116. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (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. (g) The actions shall be done in accordance with the following service bulletins, which contain the specified effective pages: ---------------------------------------------------------------------------------------------------------------- Page number Service bulletin referenced and shown on Revision level shown on page Date shown on page date page ---------------------------------------------------------------------------------------------------------------- Westwind, SB 1124-27-133, August 1-6 Original......................... Aug. 14, 1996. 14, 1996. Westwind, SB 1124-27-133, Revision 1-4 1................................ May 28, 1997. 1, May 28, 1997. 5, 6 Original......................... Aug. 14, 1996. Westwind, SB 1123-27-046, August 1-6 Original......................... Aug. 14, 1996. 14, 1996. Westwind, SB 1124-27-046, Revision 1-4 1................................ May 28, 1997. 1, May 28, 1997. 5, 6 Original......................... Aug. 14, 1996. Westwind, SB 1124-27-136, September 1-3 Original......................... Sept. 1, 1997. 1, 1997. Westwind, SB 1123-27-047, September 1-3 Original......................... Sept. 1, 1997. 1, 1997. Commodore Jet, SB 1121-27-025, 1-3 Original......................... Dec. 22, 1997. December 22, 1997. Commodore Jet, SB 1121-27-023, 1-6 Original......................... Aug. 14, 1996. August 14, 1996. Commodore Jet, SB 1121-27-023, 1-4 1................................ May 28, 1997. Revision 1, May 28, 1997. 5, 6 Original......................... Aug. 14, 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 Galaxy Aerospace Corporation, One Galaxy Way, Fort Worth Alliance Airport, Fort Worth, Texas 76177. 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 3: The subject of this AD is addressed in Israeli airworthiness directive 96-92, dated September 1, 1996. (h) This amendment becomes effective on April 10, 1998. Issued in Renton, Washington, on February 24, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-5348 Filed 3-5-98; 8:45 am] BILLING CODE 4910-13-U