COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Beechcraft 90 and 65-90 (King Air) Series Aeroplanes
AD/BEECH 90/94 Elevator Control Cable 7/99 DM
Applicability: All Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90,
C90, C90A, E90, F90, and H90 aircraft.
Requirement: 1. Accomplish the following:
- Remove the pilot’s seat and floor panels in the cockpit area on the pilot’s side of the aircraft and inspect the entire area for interference or damage between the elevator control cable and equipment under the cockpit floor panels (wire harnesses, stainless steel clamps, etc).
b. Run a cloth wrap around the control cable to detect broken strands of the control cable (refer 90 Series Maintenance Manual, Sections 5-20-00, 5-20-01, if applicable, and 20-04-00).
2. Accomplish the following:
- Replace or repair any damaged items found during the inspection and cloth wrap procedure specified in Requirement 1 of this Directive. This would include chafing damage and nicks, cuts, and broken strands on the control cable (refer 90 Series Maintenance Manual, Section 20-04-00, for criteria to determine if the cable needs to be replaced).
b. Secure any component that is interfering with the elevator control cable and install additional supports and clamps as necessary to prevent sagging or further interference between the elevator control cables and equipment under the cockpit floor panels. Use best shop practices and Advisory Circular 43.13-1B as guides for installing the additional supports.
c. Reinspect the elevator control cables in accordance with the procedures specified in Requirement 1 upon completion of any rework or replacement to assure that there is no interference.
d. Re-install floor panels and pilot’s seat.
Note 1: Raytheon Safety Communique No. 143, dated October 1997, is not considered an alternative method of compliance to this Directive.
Note 2: FAA Priority Letter AD 99-10-07 refers.
Compliance: 1. Upon accumulating 600 hours total time in service on the aircraft or within 10 hours’ time in service after 9 June 1999, whichever occurs later.
2. Before further flight after accomplishment of the Requirement 1 actions. This Airworthiness Directive becomes effective on 9 June 1999.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Background: The FAA has received numerous reports of reduced or loss of elevator control on Beech Model 90 series aircraft. In one incident where elevator up control was only available, investigation revealed that the down elevator cable was severed due to chafing between the cable and the windshield de-ice circuit electrical wire. In another incident, the elevator down cable separated because of interference between the cable and the stainless steel clamp that joined two bleed air supply ducts. Several other reports were received of incidents of reduced/loss of elevator control.
Overview
The Civil Aviation Regulations 1998, enacted by the Commonwealth of Australia, aim to ensure the safety of civil aviation operations within the country. This legislation is overseen by the Civil Aviation Safety Authority (CASA) and is designed to address gaps in aviation safety by establishing comprehensive regulations and directives. The specific legislative instrument referenced here, AD/BEECH 90/94, was introduced to address issues of elevator control cable interference and damage in Beechcraft 90 and 65-90 (King Air) series aeroplanes, as reported by the Federal Aviation Administration (FAA). The policy objective of this directive is to enhance the safety of these aircraft by ensuring that any interference or damage to the elevator control cables is identified and rectified promptly. This is achieved by mandating regular inspections and necessary repairs to prevent potential loss of elevator control, thereby protecting both the aircraft and those on board.
Scope and Application
The Civil Aviation Safety Authority (CASA) has issued Airworthiness Directive AD/BEECH 90/94 concerning the elevator control cable of Beechcraft 90 and 65-90 (King Air) series aeroplanes. This directive applies to all specified Beech models, including the 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, F90, and H90 aircraft. It mandates the inspection and maintenance of the elevator control cable to prevent any potential loss of elevator control, which has been reported in several incidents. The directive requires the removal of cockpit floor panels to inspect for interference or damage, wrapping the control cable with cloth to detect broken strands, and repairing or replacing any damaged components. Furthermore, it specifies that additional supports and clamps must be installed to prevent future interference, with all work to be performed in accordance with the 90 Series Maintenance Manual and best shop practices. This Airworthiness Directive must be adhered to upon the aircraft reaching 600 hours of total time in service or within 10 hours of service after 9 June 1999, whichever comes later, and before any subsequent flight following maintenance actions.
Key Provisions
The main operative sections of the Civil Aviation Regulations 1998, specifically Part 39 - 105, outline the Civil Aviation Safety Authority's Schedule of Airworthiness Directives for the Beechcraft 90 and 65-90 (King Air) series aeroplanes. Section AD/BEECH 90/94 addresses the Elevator Control Cable, detailing specific requirements and procedures for maintaining and inspecting the elevator control cables on these aircraft models. The directive applies to all Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, F90, and H90 aircraft.
The requirements under this directive include removing the pilot’s seat and floor panels in the cockpit area on the pilot’s side of the aircraft to inspect for any interference or damage between the elevator control cable and equipment under the cockpit floor panels (section 1a). Additionally, a cloth wrap must be run around the control cable to detect any broken strands (section 1b). If any damaged items are found during the inspection and cloth wrap procedure, they must be replaced or repaired (section 2a). Components that are interfering with the elevator control cable should be secured, and additional supports and clamps must be installed as necessary (section 2b). After any rework or replacement, the elevator control cables must be reinspected to ensure there is no interference (section 2c). Finally, the floor panels and pilot’s seat must be reinstalled (section 2d).
The obligations imposed on the parties governed by this Act include ensuring that the inspection and maintenance procedures are carried out meticulously. Aircraft operators must ensure that the elevator control cables are inspected and maintained according to the specified requirements within the stipulated timeframes. The compliance deadlines include completing the actions within 600 hours total time in service on the aircraft or within 10 hours’ time in service after 9 June 1999, whichever occurs later, and before further flight after the completion of the requirement actions (section Compliance 1 and 2). Additionally, operators must adhere to the maintenance manual sections and best shop practices as outlined in Advisory Circular 43.13-1B.
Any failure to comply with the Airworthiness Directive could result in severe consequences. The Civil Aviation Safety Authority can impose penalties for non-compliance with these regulations, which may include fines and potential grounding of the aircraft. Additionally, operators may face civil or criminal liabilities if non-compliance results in accidents or incidents. The specific maximum penalties are not detailed within the text, but they can be significant given the potential safety risks associated with non-compliance.