COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Beechcraft 1900 Series Aeroplanes
AD/BEECH 1900/23 Radio Switching Panel 7/98
Applicability: Model 1900D aeroplanes with serial numbers UE-1 through UE-160 inclusive.
Requirement: 1. Inspect the radio switching panel, the electrical connectors and the relay printed circuit board (PCB) for moisture or corrosion in accordance with the Accomplishment Instructions of Raytheon Service Bulletin (SB) 2643 dated August 1996.
2. If moisture and/or corrosion is found during the Requirement 1 inspection, carry out the following actions:
- moisture is found - clean and dry the component in accordance with SB 2643, then locate and eliminate the source of the moisture.
b. corrosion is found - either clean or replace the component in accordance with SB 2643, then locate and eliminate the cause of the corrosion.
3. Inspect the nose avionics wire harnesses for proper installation in accordance with SB 2643.
4. If any harness is found to be incorrectly installed during the Requirement 3 inspection, secure it with cable ties in accordance with SB 2643.
5. Remove the A017 component PCB part number (P/N) 101-342536-1 and replace it with a new A017 component PCB P/N 101-342536-5, in accordance with SB 2643.
Note: FAA AD 98-09-12 Amdt 39-10493 refers.
Compliance: 1. Within the next 1000 hours time in service after the effective date of this directive, but no later than 12 November 1998.
2. Prior to further flight, immediately after the Requirement 1 inspection.
3. Within the next 1000 hours time in service after the effective date of this directive, but no later than 12 November 1998.
4. Prior to further flight, immediately after the Requirement 3 inspection.
5. Within the next 1000 hours time in service after the effective date of this directive, but no later than 12 November 1998.
This airworthiness directive becomes effective on 18 June 1998.
Background: The FAA has received several reports of loss of the pilot/copilot intercom system, VHF communication system and passenger address system. This directive specifies actions which are designed to decrease the likelihood of failure of these systems, which could result in loss of all communication during critical phases of flight.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Overview
The Civil Aviation Regulations 1998, administered by the Civil Aviation Safety Authority (CASA), were enacted to ensure the safety of civil aviation in Australia. Part 39 of these regulations outlines specific airworthiness directives for various aircraft, including the Beechcraft 1900 Series Aeroplanes. One such directive, AD/BEECH 1900/23, was introduced in response to reports of failures in the pilot/copilot intercom system, VHF communication system, and passenger address system. This airworthiness directive aims to mitigate the risk of system failures that could lead to a complete loss of communication during critical flight phases. The directive mandates inspections, repairs, and replacements to address moisture, corrosion, and improper installations in specified components of the aircraft, ensuring ongoing airworthiness and passenger safety.
The enactment of the Civil Aviation Regulations 1998 by the Australian Parliament established a comprehensive framework for regulating civil aviation safety, placing responsibility on CASA to issue and enforce airworthiness directives. The specific directive AD/BEECH 1900/23 was issued to address the identified risk of communication system failures in Beechcraft 1900 Series aeroplanes, with the primary policy objective of enhancing flight safety by ensuring that these critical systems remain operational. Compliance with this directive is mandatory for operators of Model 1900D aeroplanes within the specified serial number range, requiring timely inspections, repairs, and replacements to maintain the integrity of the radio switching panel, electrical connectors, and other relevant components.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, includes a directive under the Civil Aviation Safety Authority's schedule of airworthiness directives concerning Beechcraft 1900 Series aeroplanes. This directive, identified as AD/BEECH 1900/23, applies exclusively to Model 1900D aeroplanes with serial numbers UE-1 through UE-160 inclusive. The directive mandates a comprehensive inspection and corrective actions for the radio switching panel, electrical connectors, relay printed circuit board (PCB), and nose avionics wire harnesses to ensure the integrity and reliability of critical communication systems, aiming to prevent potential failures that could compromise flight safety. The directive requires compliance within specific timeframes relative to the directive's effective date and mandates corrective actions to be completed prior to further flight following inspections. This directive is a part of the overarching framework of the Civil Aviation Regulations 1998, and its application is strictly limited to the specified aircraft models, ensuring adherence to stringent safety standards in the aviation industry.
Key Provisions
The Civil Aviation Regulations 1998, particularly under PART 39 - 105, mandate specific actions for the maintenance and inspection of the Beechcraft 1900 Series aeroplanes, as outlined in AD/BEECH 1900/23 concerning the radio switching panel. This directive applies to Model 1900D aeroplanes with serial numbers UE-1 through UE-160 inclusive (Section 1). The primary requirements (Section 1) involve inspecting the radio switching panel, electrical connectors, and relay printed circuit board (PCB) for moisture or corrosion as per Raytheon Service Bulletin (SB) 2643 dated August 1996. If moisture or corrosion is detected, the directive mandates cleaning, drying, or replacing the affected components, and addressing the source of moisture or corrosion (Section 1b). Additionally, it requires inspecting the nose avionics wire harnesses for proper installation and securing them if necessary (Sections 3 and 4). The directive also specifies the replacement of a particular PCB component (Section 5).
The obligations imposed by this Act include conducting thorough inspections and corrective actions on the specified parts of the aeroplanes to ensure they are free from moisture, corrosion, and improper installations. Operators must adhere to the inspection and maintenance protocols outlined in the Raytheon Service Bulletin 2643 to maintain airworthiness (Sections 1-5). The directive demands immediate action upon detecting issues during inspections and mandates these tasks be completed within the next 1000 hours of time in service after the directive's effective date, which was 18 June 1998, but no later than 12 November 1998. It also requires these actions to be performed before further flights following the inspections (Sections 1-5).
Failure to comply with the provisions of this airworthiness directive may lead to serious safety risks, including the potential loss of communication systems critical during flight. Although the Civil Aviation Regulations 1998 do not explicitly state penalties for non-compliance with this specific directive, general non-compliance with Civil Aviation Regulations can result in severe consequences. These include fines, imprisonment, or both, depending on the severity of the breach. The specific maximum penalties are not detailed in the text but typically align with the general enforcement provisions of the Civil Aviation Act 1988, where significant non-compliance can lead to substantial penalties. Operators are expected to ensure strict adherence to maintain the safety and airworthiness of the aircraft.