AD 2005-10-24 Airworthiness Directives; AeroSpace Technologies of Australia Pty Ltd. Models N22B, N22S, and N24A Airplanes

Models named: N22B, N22S, N24A. Read the applicability below — it usually turns on serial or part numbers too.

(c) This AD affects Models N22B, N22S, and N24A airplanes, all serial numbers, that are certificated in any category.

(e) To address this problem, you must do the following:   Actions Compliance Procedures (1) Inspect the following: (i) The rudder control level shafts, part numbers (P/N) 1/N-45-1102, 2/N-45-1102, 1/N-45-1103, and 1/N-45-1104 (or FAA-approved equivalent part numbers) for cracks. Use dye penetrant inspection while the shaft is installed. Use either dye penetrant or magnetic particle inspection if the shaft is removed; and (ii) All lever shaft side plates on P/Ns 1/N-45-1102, 2/N-45-1102, 1/N-45-1103, and 1/N-45-1104 (or FAA-approved equivalent part numbers) by measuring the thickness for discrepancies. Initially inspect within the next 50 hours time-in-service (TIS) or 30 days after June 30, 2005 (the effective date of this AD), whichever occurs first, unless already done Following Nomad Alert Service Bulletin ANMD-27-51, Rev. 2, dated April 29, 2004, and the applicable maintenance manual. (2) If no cracks are found in the rudder control lever shafts during the inspection required in paragraph (e)(1)(i) of this AD, repetitively inspect rudder control lever shafts P/Ns 1/N-45-1102, 2/N-45-1102, 1/N-45-1103, ands 1/N-45-1104 (or FAA-approved equivalent part numbers) for cracks Repetitively inspect thereafter at intervals not to exceed 300 hours TIS after the initial inspection required in paragraph (e)(1) of this AD Following Nomad—Series N22 & N24 Inspection Requirements Manual, Temporary Revision 26, Fatigue Critical Areas, dated May 27, 2004. (3) If cracks or discrepancies are found during any inspection required by this AD, do the following: (i) For rudder control lever shafts found with crack damage, replace with new or serviceable parts. After replacement, continue with the repetitive inspections required in paragraph (e)(2) of this AD. (ii) If the thickness of the lever shaft side plates is less than 0.050 inches, replace the lever shaft side plate with a new plate that measures at least 0.050 inches in thickness. Before further flight after any inspection required by this AD in which cracks or discrepancies are found. Following Nomad Alert Service Bulletin ANMD-27-51, Rev. 2, dated April 29, 2004, and the applicable maintenance manual. (4) If at any time certain operating conditions occur that caused abnormal rudder pedal loads, inspect the rudder control lever shafts as specified in paragraph (e)(2) of this AD. Examples of such conditions are: heavy use of nosewheel steering over rough ground; excessive steering angle under towl; towing with rudder gust lock fitted; engine failure on takeoff; and aircraft left parked outside with rudder gust lock not fitted Before further flight Following Nomad—Series N22 & N24 Inspection Requirements Manual, Temporary Revision 26, Fatigue Critical Areas, dated May 27, 2004. (5) Do not install a new lever shaft side plate that is less than 0.050 inches in thickness As of June 30, 2005 (the effective date of this AD) As specified in Nomad Alert Service Bulletin ANMD-27-51, Rev. 2, dated April 29, 2004; and Nomad—Series N22 & N24 Inspection Requirements Manual, Temporary Revision 26, Fatigue Critical Areas, dated May 27, 2004.

(d) This AD is the result of continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. The actions specified in this AD are intended to detect and correct cracks in the rudder control lever torque shafts and discrepancies in the thickness of the lever shaft side plates, which could result in failure of the rudder control lever torque shaft. Such failure could lead to reduced controllability of the airplane.

(b) This AD supersedes AD 2003-14-20, Amendment 39-13239.