COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Beechcraft 200 (Super King Air) Series Aeroplanes
AD/BEECH 200/56 Landing Gear Actuator Pivot Mounting 2/95
Applicability: All Beechcraft 200 series aircraft.
Requirement: Jack the aircraft in accordance with the Manufacturers Maintenance Manual. With the aircraft on jacks partially retract the landing gear. Remove the fender assemblies to permit a thorough inspection of the actuator mounting area.
While supporting the undercarriage, for hydraulic actuated systems release all hydraulic pressure, inspect for movement (wear) of the actuator bearing supports on their mounting brackets. Inspect the 3 attaching bolts for correct torque. Refer item Section 32-31-00 page 211 figure 207 item 11. Inspect for movement (wear) of the mounting brackets to spar attachment. Inspect the 6 attachment bolts for correct torque. Inspect the actuator and down lock assembly for excessive wear. Refer Chapter 91 of the King Air Maintenance Manual for bolt torque requirements.
Inspect the actuator bearings for correct lubrication. After completing the inspection of the landing gear actuator mounts, select the landing gear down and refit the fender assemblies in the nacelles. Inspect all landing gear micro switches for correct functioning and adjustment. Carry out a full functional check of the undercarriage system. Lower aircraft and remove jacks. Ensure a certification detailing results of the inspection are recorded in the aircraft log book.
Note: Inspection through the spar cut-out is not adequate. Removal of fender assemblies is required to facilitate inspection of the area.
Compliance: At the next maintenance inspection or by 30 June 1995, whichever occur first.
Background: On landing the aircraft suffered extensive damage when the R/H undercarriage collapsed. Subsequent investigation confirmed the U/C collapse was due to failure of the down lock to correctly engage and this was caused by excessive movement in the undercarriage actuator mounting assembly and failure of the actuator pivot bearing.
Overview
The Civil Aviation Regulations 1998, administered by the Civil Aviation Safety Authority (CASA), were enacted to ensure the safety and airworthiness of aircraft in Australian airspace. Part 39, specifically addressing the Schedule of Airworthiness Directives, outlines mandatory safety measures and requirements for various aircraft types, including the Beechcraft 200 series. This legislation aims to mitigate risks and prevent incidents such as the collapse of the undercarriage experienced by a Beechcraft 200 series aircraft, which was attributed to excessive movement in the actuator mounting assembly and bearing failure. The policy objective is to maintain stringent safety standards and ensure the integrity of aircraft systems, thereby safeguarding passengers and crew. The directive mandates a thorough inspection and functional check of the landing gear actuator mounting area, including the removal of fender assemblies to facilitate a comprehensive assessment of wear and proper torque settings, with compliance required by a specified date to avert potential hazards.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, pertains to the airworthiness directives for civil aviation safety in Australia. This regulation applies to all Beechcraft 200 series aircraft operating within the Australian jurisdiction. It mandates that operators of these aircraft must ensure that their aircraft undergo a detailed inspection of the landing gear actuator pivot mounting as outlined in AD/BEECH 200/56. This includes tasks such as jacking the aircraft, partial retraction of the landing gear, removal of fender assemblies, and thorough inspection of various components including mounting brackets, bolts, and bearings. Compliance with these directives must be achieved at the next scheduled maintenance inspection or by 30 June 1995, whichever comes first. The directive aims to prevent failures such as the one experienced where the aircraft's right-hand undercarriage collapsed upon landing due to excessive movement in the actuator mounting assembly and bearing failure. The inspection must be comprehensive, with direct visual inspection of the mounting area being necessary, and any findings should be duly recorded in the aircraft logbook.
Key Provisions
The main operative sections of the Civil Aviation Regulations 1998 (Regulations), specifically Part 39 - 105, pertain to the Airworthiness Directives for the Beechcraft 200 (Super King Air) Series Aeroplanes. Section AD/BEECH 200/56 mandates a thorough inspection of the landing gear actuator pivot mounting to ensure aircraft safety. The directive requires the aircraft to be jacked up (Section 1) and partially retracted landing gear, followed by the removal of fender assemblies to inspect the actuator mounting area (Section 2). The directive specifies the need to inspect the actuator bearing supports, bolts, mounting brackets, and down lock assembly, as well as the actuator bearings and lubrication (Section 3-6). Post-inspection, the aircraft must undergo a full functional check of the undercarriage system and all landing gear micro switches (Section 7-8). The results of the inspection must be recorded in the aircraft logbook (Section 9). Notably, inspection through the spar cut-out is deemed inadequate; the removal of fender assemblies is required to facilitate the inspection (Section 10).
The Act imposes specific obligations and requirements on the operators of Beechcraft 200 series aircraft. Operators must ensure that the inspection of the landing gear actuator pivot mounting is conducted at the next scheduled maintenance inspection or by 30 June 1995, whichever comes first (Section 11). This inspection must be performed in accordance with the Manufacturers Maintenance Manual, including the removal of fender assemblies, thorough examination of the actuator mounting area, and verification of correct torque and lubrication of the components (Section 2-6). Operators are also required to perform a full functional check of the undercarriage system and ensure all landing gear micro switches are correctly functioning and adjusted (Section 7-8). The results of the inspection must be meticulously documented in the aircraft logbook (Section 9). Failure to adhere to these requirements could compromise the airworthiness of the aircraft.
Non-compliance with the provisions outlined in the Airworthiness Directive can result in significant civil and criminal consequences. The Regulations impose penalties for failure to adhere to the specified inspection requirements and documentation standards. The maximum penalties for breaches can include substantial fines and potential criminal charges. Operators found in breach of these regulations may face legal action, which could result in criminal penalties, including imprisonment for directors or senior management of the operating entity, and substantial financial penalties for the company. Such penalties underscore the critical importance of strict adherence to the stipulated safety directives to ensure the continued airworthiness of Beechcraft 200 series aircraft.