AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
Beechcraft 400 Series Aeroplanes
AD/BEECH 400/23 Engine Mount 4/2002 DM
Applicability: Model 400 series aircraft, serial numbers RJ-1 through RJ-65.
Model 400A series aircraft, serial numbers RK-1 and subsequent. Model 400T series aircraft, serial numbers TT-1 through TT-180. Model 400T-1 series aircraft, serial numbers TX-1 through TX-11.
Requirement: Perform a fluorescent penetrant inspection to detect cracking in the radius of the cutout of the aft flange of the left engine forward carry-through mount bracket, in accordance with Raytheon Safety Communique No. 189, Revision 1, dated January 2002.
If any cracking is detected, before further flight, replace the cracked part with a new bracket and fitting in accordance with Raytheon Maintenance Manual, Chapter 54-40-
00. The replacement parts are identified in the Requirement document.
Note: FAA AD 2002-01-23 Amdt 39-12617 refers.
Compliance: At the later of the following times:
Before the accumulation of 1,500 total flight hours, or;
Within 25 flight hours or 14 days after 27 February 2002, whichever occurs first. Repeat thereafter at intervals not to exceed 200 flight hours.
This Airworthiness Directive becomes effective on 27 February 2002.
Beechcraft 400 Series Aeroplanes
AD/BEECH 400/23 (continued)
Background: A report was received of cracking found on the aft flange of the left engine forward carry-through mount bracket during routine inspection. Inspection of other aircraft revealed similar cracking, and all aircraft had accumulated between 2,000 and 3,000 total flight hours.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 20 February 2002
The above AD is notified in the Commonwealth of Australia Gazette on 27 February 2002.
Overview
The Airworthiness Directive (AD) F2006B03926 was enacted by the Civil Aviation Safety Authority (CASA) in 2002 to address a safety issue identified in the Beechcraft 400 series aeroplanes. This directive was issued under subregulation 39.1 (1) of the Civil Aviation Regulations 1998 to mandate specific actions to correct an unsafe condition relating to the engine mount of the mentioned aircraft models. The directive applies to specific serial numbers of Model 400, Model 400A, Model 400T, and Model 400T-1 series aircraft. The directive requires a fluorescent penetrant inspection to detect potential cracking in the aft flange of the left engine forward carry-through mount bracket, with subsequent replacement of any cracked parts to prevent further risk. The compliance deadline mandates these inspections and actions before the accumulation of 1,500 total flight hours or within 25 flight hours or 14 days after 27 February 2002, whichever occurs first, and then at regular intervals not exceeding 200 flight hours. The policy objective behind this directive is to ensure the continued airworthiness and safety of the affected aircraft by proactively addressing the identified structural issue.
Scope and Application
The Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) under subregulation 39.1 (1) of the Civil Aviation Regulations 1998 applies to specific models of the Beechcraft 400 series aeroplanes. Specifically, the directive pertains to Model 400 series aircraft with serial numbers RJ-1 through RJ-65, Model 400A series aircraft with serial numbers RK-1 and subsequent, Model 400T series aircraft with serial numbers TT-1 through TT-180, and Model 400T-1 series aircraft with serial numbers TX-1 through TX-11. The AD mandates a fluorescent penetrant inspection to detect cracking in the radius of the cutout of the aft flange of the left engine forward carry-through mount bracket, as outlined in Raytheon Safety Communique No. 189, Revision 1, dated January 2002. If any cracking is detected, the cracked part must be replaced with a new bracket and fitting in accordance with the Raytheon Maintenance Manual, Chapter 54-40-00. The compliance timeline requires the inspection to be conducted before the accumulation of 1,500 total flight hours or within 25 flight hours or 14 days after 27 February 2002, whichever occurs first, and repeated thereafter at intervals not exceeding 200 flight hours. This directive applies throughout the Commonwealth of Australia and is published in the Commonwealth of Australia Gazette on 27 February 2002.
Key Provisions
The Airworthiness Directive (AD) issued under section 39.1 (1) of the Civil Aviation Regulations 1998 (CAR 1998) applies to specific models of Beechcraft 400 series aeroplanes, including Model 400 series aircraft (serial numbers RJ-1 through RJ-65), Model 400A series aircraft (serial numbers RK-1 and subsequent), Model 400T series aircraft (serial numbers TT-1 through TT-180), and Model 400T-1 series aircraft (serial numbers TX-1 through TX-11). This AD mandates a fluorescent penetrant inspection to detect any cracking in the radius of the cutout of the aft flange of the left engine forward carry-through mount bracket, as detailed in Raytheon Safety Communique No. 189, Revision 1, dated January 2002. If any cracking is detected, the cracked part must be replaced with a new bracket and fitting in accordance with the Raytheon Maintenance Manual, Chapter 54-40-00. The replacement parts are clearly identified in the AD. This inspection must be completed at the later of the following times: before the aircraft accumulates 1,500 total flight hours, or within 25 flight hours or 14 days after 27 February 2002, whichever occurs first. The inspection must then be repeated at intervals not exceeding 200 flight hours. The AD became effective on 27 February 2002.
The AD imposes specific obligations on the owners and operators of the affected aircraft models. They must ensure that the fluorescent penetrant inspection is conducted as required, and that any identified cracking is addressed by replacing the affected parts with new ones, as specified in the Raytheon Maintenance Manual. These obligations are crucial to maintaining the airworthiness of the aircraft and ensuring the safety of all those on board. The AD also requires that these actions be documented and maintained in the aircraft's maintenance records.
Failure to comply with the AD may result in severe civil or criminal consequences. The AD outlines specific penalties for non-compliance, although the exact penalties are not specified in the text provided. The AD references FAA AD 2002-01-23 Amdt 39-12617, which may provide further details on the penalties associated with non-compliance. In general, non-compliance with airworthiness directives can lead to fines, aircraft grounding, or even criminal charges in cases of gross negligence or wilful disregard for safety regulations. The seriousness of these consequences underscores the importance of adhering to the AD's requirements.