COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
DH 104 (Dove) Series Aeroplanes
AD/DH 104/1 Fire Protection Modifications - Engine Nacelles 8/71
Applicability: All models in transport category.
Requirement: 1. Modify the existing nacelle fire detection system as follows:
1.1 Replace the existing pyrotechnic cord type detector with a minimum of eight (8) unit detectors in approved locations in each engine bay or, alternatively, with an approved continuous type detector. All fire detectors shall be of an approved type.
1.2 Detector Circuits:
(a) Provide separate independent detector circuits for each nacelle.
(b) Install a test switch adjacent to the warning lights for each nacelle and arrange the detector circuit so that the test switch checks the circuit protection, the indicator lamps and the continuity of the detector wiring.
1.3 Indicators:
In addition to the existing warning lights for each nacelle install in the cockpit an audible fire-warning device common to both detector circuits.
2. Oil System:
Rework the following flexible oil lines to ensure that they are rendered fully fireproof:
(a) Hoses from oil tank to engine-driven oil pump.
(b) Hose from oil tank to propeller feathering pump.
3. Electric Cables:
3.1 Ensure that wiring forward of the firewall is PVC insulated glass braided cable to Specification AN-J-C-48a or other cable approved as fire-resistant class 11 for the following circuits:
(a) Fire detectors.
(b) Propeller feathering.
(c) Those sections of the starter motor circuit in which a fault could adversely affect propeller feathering.
3.2 Protect cable with glass outer-braiding from abrasion by wrapping with PVC tape, shrouding with PVC tubing, or by other approved means.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
3.3 Ensure that cable and cable runs forward of the firewall are installed in the cooler parts of the engine nacelle. Cable runs shall also be arranged so that they are not exposed to mechanical damage during normal engine operation or during ground maintenance.
4. Firewall Sealing:
4.1 Install a steel slide forward of the present bakelite slides on the engine control rods.
4.2 Install a fire-proofing tube over the slow running cut-out control cable where it enters the engine bay.
4.3 Install a steel cover over the end of the fuel filter that protrudes into the engine bay.
4.4 Install steel covers over all light alloy electrical connectors; or
5. Part 100, Appendix “A” Notice No. 4/21 Issue 2; or
6. De Havilland Drawing DHZ-101A; or 7. ANO 105.1.14.13.5.2.
Compliance: Before 1 September 1971.
Overview
The Civil Aviation Regulations 1998, enacted by the Parliament of Australia, form the primary legislative framework governing civil aviation within the country, addressing the need for stringent safety standards in air travel. This legislative instrument, specifically PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES DH 104 (Dove) Series Aeroplanes AD/DH 104/1, was introduced to enhance the safety of aircraft by mandating specific modifications to the fire protection systems and other critical components of the Dove Series Aeroplanes. The policy objective underpinning these regulations is to ensure that all aircraft meet rigorous safety standards, thereby protecting passengers, crew, and the general public from aviation-related hazards. The regulations demand compliance with the outlined modifications before 1 September 1971, underscoring the urgency and importance of these safety measures.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105 of the Civil Aviation Safety Authority Schedule of Airworthiness Directives, mandates fire protection modifications for the De Havilland DH 104 (Dove) series aeroplanes in the transport category. The legislation requires the replacement of the existing pyrotechnic cord type detector in each engine bay with a minimum of eight unit detectors or an approved continuous type detector, all of which must be of an approved type. Additionally, the regulations mandate separate independent detector circuits for each nacelle, installation of test switches for each nacelle, and installation of an audible fire-warning device in the cockpit. Furthermore, the flexible oil lines from the oil tank to the engine-driven oil pump and propeller feathering pump must be reworked to ensure they are fully fireproof, while electric cables forward of the firewall must be PVC insulated glass braided cable, protected from abrasion, and installed in cooler parts of the engine nacelle. Compliance with these modifications is required before 1 September 1971.
The applicability of these regulations is limited to De Havilland DH 104 (Dove) series aeroplanes in the transport category, with no stated exclusions or exemptions in the provided text. However, the scope of application might be extended or restricted through subordinate instruments not detailed in the provided text. The regulations are part of the Civil Aviation Regulations 1998, which have a national reach within Australia, thereby affecting all civil aviation entities operating within the country.
Key Provisions
The Civil Aviation Regulations 1998, under Part 39, include specific airworthiness directives concerning the Dove series aeroplanes, identified as DH 104. The primary focus of these directives (AD/DH 104/1) is on fire protection modifications for the engine nacelles. The modifications are applicable to all Dove series aeroplanes in the transport category. Section 1 of the directive mandates several specific modifications to the fire detection system within the engine nacelles, including replacing the existing pyrotechnic cord type detector with a minimum of eight unit detectors in approved locations in each engine bay or an approved continuous type detector (section 1.1). Each nacelle must have separate independent detector circuits, with a test switch adjacent to the warning lights to check the circuit protection, indicator lamps, and continuity of the detector wiring (section 1.2). Additionally, an audible fire-warning device must be installed in the cockpit, common to both detector circuits (section 1.3).
These regulations impose several obligations on the operators and maintainers of Dove series aeroplanes. Firstly, they must ensure that the modifications to the fire detection system are completed as per the specified requirements, including the replacement or installation of new detectors, circuits, and warning devices (section 1). Secondly, the flexible oil lines connecting the oil tank to the engine-driven oil pump and the propeller feathering pump must be reworked to ensure they are fully fireproof (section 2). Thirdly, wiring forward of the firewall must be made of PVC insulated glass braided cable to Specification AN-J-C-48a or an approved fire-resistant class 11 cable, specifically for fire detectors, propeller feathering, and sections of the starter motor circuit that could affect propeller feathering (section 3). The wiring must be protected from abrasion and installed in cooler parts of the engine nacelle, ensuring it is not exposed to mechanical damage (section 3.2 and 3.3). Furthermore, firewall sealing improvements are required, including the installation of steel slides, fire-proofing tubes, and steel covers over specific components (section 4).
Failure to comply with these airworthiness directives can result in significant consequences. While specific penalties are not detailed in the excerpt provided, non-compliance with Civil Aviation Regulations can generally lead to enforcement actions by the Civil Aviation Safety Authority (CASA). Potential outcomes may include fines, suspension or revocation of airworthiness certificates, and other regulatory sanctions. The exact penalties would depend on the severity of the breach and could be substantial, reflecting the critical nature of ensuring fire safety in aircraft operations.