COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Fokker F27 Series Aeroplanes
AD/F27/144 Emergency Lighting 12/97
Applicability: All Fokker Aircraft B.V. Model F.27 Mk.050, Mk0502, and Mk.0604 if Emergency Battery Power Supply Unit, Part Number 60-4915-1 is installed.
Requirement: Fabricate a placard, with the following words in letters at least 2.5mm (0.10 inches) in height and install the placard in clear view of the pilot adjacent to the Emergency Lighting Selector Switch:
CAUTION
WHEN CYCLING EMERGENCY LIGHTING SELECTOR, SWITCH MUST BE LEFT IN “OFF” POSITION FOR AT LEAST 60 SECONDS.
Note: Netherlands AD 1997-060 (A) refers.
Compliance: By the 11 February 1998.
This airworthiness directive becomes effective on 6 November 1997.
Background: Pre delivery testing on a Fokker Model F.27 Mk 050 aircraft has shown that, if the flight crew cycles the Emergency Lighting Selector Switch, within a short time period, to OFF, either from ARMED or ON, and subsequently back to ARMED, the system will actually not be armed. If this switching sequence has occurred, the system will not react either in the event of an electrical power failure, nor when the switch is moved to the ON position. The affected circuitry, which needs a certain time to reset, is only installed in the Emergency Battery Power Supply units identified above.
Overview
The Civil Aviation Regulations 1998, enacted by the Parliament of Australia, represent a comprehensive set of rules aimed at ensuring the safety and efficiency of civil aviation within Australia. Specifically, Part 39 - 105 of the Civil Aviation (Airworthiness) Regulations focuses on the issuance of airworthiness directives to maintain the safety of aircraft. One such directive, AD/F27/144, addresses a critical safety issue related to the emergency lighting system of Fokker F27 Series Aeroplanes. This directive was introduced to rectify a problem where improper cycling of the Emergency Lighting Selector Switch could render the emergency lighting system inoperative during critical situations, such as electrical power failure. The policy objective behind this directive is to ensure that pilots are adequately informed and that the emergency lighting system remains functional, thereby enhancing overall flight safety.
Scope and Application
The Civil Aviation Regulations 1998, as amended, apply to all Fokker Aircraft B.V. Model F.27 Mk.050, Mk.0502, and Mk.0604 aircraft if equipped with an Emergency Battery Power Supply Unit, Part Number 60-4915-1. This legislation mandates the fabrication and installation of a placard with specific cautionary instructions in clear view of the pilot, adjacent to the Emergency Lighting Selector Switch. The directive is aimed at ensuring that when the emergency lighting selector is cycled, the switch must be left in the "OFF" position for at least 60 seconds to allow the system to reset properly. This requirement is to prevent the emergency lighting system from failing to activate during an electrical power failure or when the switch is moved to the "ON" position. The directive applies nationally and became effective on 6 November 1997, with compliance required by 11 February 1998. This legislation is part of the broader civil aviation safety framework in Australia, ensuring that all relevant aircraft meet specific safety standards to maintain operational airworthiness.
Key Provisions
The key provisions of the airworthiness directive AD/F27/144 as it applies to Fokker F27 Series Aeroplanes are detailed under Part 39 - 105 of the Civil Aviation Regulations 1998. Specifically, Section 39.105 addresses the requirements for maintaining the airworthiness of aircraft, which includes adherence to specific Airworthiness Directives (ADs) issued by the Civil Aviation Safety Authority (CASA). The directive AD/F27/144 pertains to Fokker Aircraft B.V. Model F.27 Mk.050, Mk0502, and Mk.0604 if they are equipped with an Emergency Battery Power Supply Unit, Part Number 60-4915-1. This directive mandates that a placard with specific wording must be fabricated and installed in a clear view of the pilot adjacent to the Emergency Lighting Selector Switch. The placard must have the words "CAUTION WHEN CYCLING EMERGENCY LIGHTING SELECTOR, SWITCH MUST BE LEFT IN 'OFF' POSITION FOR AT LEAST 60 SECONDS" in letters at least 2.5mm (0.10 inches) in height.
The obligations imposed by AD/F27/144 are straightforward but critical for ensuring the safety and proper functioning of the emergency lighting system on the specified Fokker aircraft. Operators and owners of affected aircraft must ensure that the required placard is fabricated and installed as stipulated. This involves creating a clear, visible warning that instructs pilots on the correct procedure for cycling the Emergency Lighting Selector Switch to avoid system failure. Failure to comply with these requirements can result in the aircraft being deemed unairworthy, thereby rendering it ineligible for flight operations until the necessary modifications are made.
Breach of the requirements outlined in AD/F27/144 can lead to serious consequences. Although the specific penalties are not detailed in the text, non-compliance with airworthiness directives generally carries significant legal and operational repercussions. CASA has the authority to enforce compliance through various measures, including fines, operational restrictions, and potential grounding of the aircraft. Such non-compliance not only poses a risk to the safety of the aircraft and its occupants but can also result in civil or criminal liability for the aircraft operator or owner. It is crucial for all parties governed by this directive to adhere strictly to the specified requirements to avoid these potential consequences.