Airworthiness Directive · Amendment 39-14102 · AeroSpace Technologies of Australia Pty Ltd. Models N22B, N22S, and N24A Airplanes

AD 2005-10-24

AeroSpace Technologies of Australia Pty Ltd. Models N22B, N22S, and N24A Airplanes

Mentions a repeat actionAirplane

Published: May 23, 2005
Effective: June 30, 2005
Maker: Aerospace Technologies of Australia Pty Ltd.
Supersedes: 2003-14-20

Applies to

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

The FAA's summary

The FAA adopts a new airworthiness directive (AD) to supersede AD 2003-14-20, which applies to all AeroSpace Technologies of Australia Pty Ltd. (ASTA) Models N22B and N24A airplanes. AD 2003-14-20 requires you to repetitively inspect, using either dye penetrant or magnetic particle methods, the rudder control lever shafts for cracks; inspect (one-time) all lever shaft side plates by measuring the thickness; and if cracks or discrepancies in thickness are found, replace unserviceable parts with new or serviceable parts. Since AD 2003-14-20 was issued, we determined that the AD should also affect Model N22S airplanes. The manufacturer has also revised the service information to include a rudder control lever shaft part number (P/N) that was not part of AD 2003-14-20. Consequently, this AD retains the actions of AD 2003-14-20, adds Model N22S airplanes to the applicability, and adds rudder control lever shaft P/N 1/N-45-1102 to the inspection requirements. We are issuing this AD 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.

What it requires

What Must I Do To Address This Problem?

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.

Official sources

The Federal Register document · document 05-9976, the legal text
FAA Dynamic Regulatory System (DRS) · search 2005-10-24 for its current status and any corrections

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.