AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BEECH 200/65 and issues the following AD under subregulation 39.1 (1) of CASR 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 200 (Super King Air) Series Aeroplanes
AD/BEECH 200/65
Amdt 1
Fuselage Frame 6/2003
Applicability: All Beech 200 aircraft.
Requirement: | 1. | Perform a detailed visual inspection of the right hand side fuselage frame at Fuselage Station 207, and adjacent frames, in the area between the lower longeron at Water Line 119 (below the windows) and the floor, for evidence of cracking. |
| 2. | Report to CASA on a Defect Report form if any cracks are found, specifying the number of cracks, exact location (include of diagram if possible), and crack |
| | length. |
Compliance: | 1. | Within 10 cycles after a threshold of 10,000 cycles (total cycles in service) and thereafter at 1,000 cycle intervals. |
| 2. | Within 48 hours after completion of the inspection. |
Note: The first inspection per this amendment is not required until 1,000 cycles has elapsed since the last inspection done per the original issue of this AD. If no inspection has been performed before in accordance with the original issue of this AD, then the compliance as stated in this amendment applies.
This Amendment becomes effe ctive on 12 June 2003.
Background: Significant cracking has been found in a fuselage frame at STA 207 on a local Model B200C aircraft during an investigation of a crack in the fuselage external skin. The fuselage frames in several other aircraft have also been found cracked, but to a lesser degree.
Items 6 and 7 of the B200 Maintenance Manual Rev B7, 31 January 2003, Chart 201, “Priority Area Inspection Guide” currently require inspections in the area where the cracks in frame STA 207 were located. The threshold for these inspections at the time this AD was originally effective was 15,000 hours total time in service. The threshold for these inspections has now been revised to 10,000 cycles, with subsequent repeat inspections at 1,000 cycle intervals.
Beechcraft 200 (Super King Air) Series Aeroplanes
AD/BEECH 200/65 Amdt 1 (continued)
This amendment alters the AD compliance to align the threshold and repeat interval with that specified in the latest revision of the maintenance manual. The reporting requirement has also been altered to require the submission of a CASA Major Defect Report form if cracks are found in the fuselage frame at STA 207.
The original issue of this Airworthiness Directive became effective on 3 February 2000.
David Villiers
Delegate of the Civil Aviation Safety Authority 2 May 2003
The above AD is notified in the Commonwealth of Australia Gazette on 21 May 2003.
Overview
The Civil Aviation Safety Authority (CASA) has enacted the Airworthiness Directive AD/BEECH 200/65 Amendment 1, effective from 12 June 2003, to address the issue of fuselage frame cracking in Beechcraft 200 (Super King Air) Series Aeroplanes. This amendment was introduced to rectify the unsafe condition identified in the fuselage frame at Station 207 and adjacent frames. The directive mandates a detailed visual inspection of the specified area for any evidence of cracking and requires reporting to CASA if any cracks are detected, providing specific details about the cracks found. The policy objective behind this directive is to ensure the continued airworthiness and safety of Beech 200 aircraft by implementing regular inspections and reporting requirements to mitigate the risk associated with fuselage frame cracking.
Scope and Application
This Airworthiness Directive issued under the Civil Aviation Safety Regulations 1998 applies specifically to all Beechcraft 200 (Super King Air) Series aeroplanes. The directive mandates a detailed visual inspection of the right-hand side fuselage frame at Fuselage Station 207 and adjacent frames, in the area between the lower longeron at Water Line 119 and the floor, for evidence of cracking. This inspection is required within 10 cycles after the aircraft reaches a threshold of 10,000 cycles in total service, and then at every 1,000 cycle interval thereafter. If any cracks are found during the inspection, the operator must report this to the Civil Aviation Safety Authority (CASA) on a Defect Report form, detailing the number of cracks, their exact location, and the length of each crack. The directive came into effect on 12 June 2003, superseding the previous AD/BEECH 200/65, with the first inspection under the new amendment not required until 1,000 cycles have elapsed since the last inspection conducted under the original AD, if such an inspection has previously been performed.
Key Provisions
This Airworthiness Directive (AD) applies to all Beech 200 series aircraft and mandates a detailed visual inspection of the right-hand side fuselage frame at Fuselage Station 207, and adjacent frames, for evidence of cracking. This inspection must be conducted in the area between the lower longeron at Water Line 119 (below the windows) and the floor (Section 1). If any cracks are found, they must be reported to the Civil Aviation Safety Authority (CASA) on a Defect Report form, including details such as the number of cracks, their exact location, and the crack length (Section 2). The AD specifies the timing for these inspections, requiring them to be carried out within 10 cycles after reaching a threshold of 10,000 cycles (total cycles in service), and thereafter at 1,000 cycle intervals (Section 3). Additionally, the report on any found defects must be submitted to CASA within 48 hours after completing the inspection (Section 4). Note that the first inspection under this amendment is not required until 1,000 cycles have elapsed since the last inspection under the original AD issue, and if no prior inspections have been performed according to the original AD, the compliance as stated in this amendment applies.
The AD imposes several obligations on the parties or entities it governs. Primarily, these entities must ensure that the specified inspections are performed meticulously and within the prescribed timeframes. Specifically, they must conduct a visual inspection of the designated fuselage frames at the required cycle intervals and report any findings to CASA. This includes gathering precise data about any discovered cracks, such as their number, exact location, and length, and submitting this information on a Defect Report form within 48 hours of the inspection. The AD also requires adherence to the compliance timeline, ensuring inspections are conducted at the correct intervals post the 10,000 cycle threshold.
The AD includes provisions for civil and criminal consequences for non-compliance. While the specific penalties are not detailed in the AD itself, it is reasonable to infer that breaches of ADs can lead to significant consequences under the Civil Aviation Safety Authority Act 1998 and associated regulations. These could include fines, enforcement actions, and potential criminal charges for more severe violations, depending on the nature and impact of the non-compliance. The exact penalties would be determined by the relevant aviation authorities and could vary based on the severity and circumstances of the breach.