COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
McDonnell Douglas (Hughes) and Kawasaki 369 Series Helicopters
AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
AD/HU 369/103 Turbine Outlet Temperature Wire Harness 7/2000
DM
Applicability: Model 369D, 369E and 500N series helicopters with analogue/digital turbine outlet temperature (TOT) indicator, part number (P/N) 369D24513-1, installed; and Model 600N helicopters, with analogue/digital TOT indicator, P/N 9A3420 installed.
Requirement: 1. For Model 369E, 369D, and 500N helicopters -
- Test the TOT indicating system to verify correct calibration in accordance with the Accomplishment Instructions, Part I, of MD Helicopters, Inc. (MDHI) Service Bulletin SB369D-199, SB369E-093, SB500N-019, dated 11 January 2000, as applicable.
b. If, during any test required by Requirement 1.a., the TOT indicator readings for the tester setting temperatures in Table 1, Part I, of the SB are not within the indicator reading range, perform the actions specified in the Accomplishment Instructions, Part I, paragraph (6)(b) of the applicable SB.
2. For Model 600N helicopters -
- Test the TOT indicating system, including the electronic control unit (ECU) TOT sensing system, to verify correct calibration in accordance with the Accomplishment Instructions, Part I, of MDHI SB600N-026, dated 11 January 2000.
b. If, during any calibration test required by Requirement 2.a., the TOT indicator readings for the tester setting temperatures in Table 1, Part I, of the SB are not within the indicator reading range, perform the actions specified in the Accomplishment Instructions, Part I, paragraph (7)(b) of the SB.
c. If, during any test required by Requirement 2.a., the Full Authority Digital Electronic Control (FADEC) maintenance lap-top terminal does not indicate ECU TOT within ± 5 degrees Celsius of the tester setting in Table 1, Part I, of the SB, perform the actions specified in the Accomplishment Instructions, Part III, of the SB.
Note: FAA AD 2000-08-22 Amdt 39-11708 refers.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Compliance: For Requirement 1.a. - Within the next 50 hours time-in-service (TIS) after the effective date of this Directive or on or before 15 June 2000, whichever occurs first; thereafter, repeat the test at intervals not to exceed 300 hours TIS.
For Requirement 1.b. - Before further flight.
For Requirement 2.a. - Within the next 50 hours TIS after the effective date of this Directive or on or before 15 June 2000, whichever occurs first; thereafter, repeat the test at intervals not to exceed 300 hours TIS.
For Requirement 2.b. - Before further flight. For Requirement 2.c. - Before further flight.
This Airworthiness Directive becomes effective on 24 May 2000.
Background: The United States Federal Aviation Administration has received seven reports of erroneous TOT readings and two reports of incorrect wiring harness terminal lugs on the thermocouple wiring in Model 369D, 369E, 500N, and 600N helicopters with certain analogue/digital TOT indicators. The reports indicated that some of the TOT readings did not agree with the engine ECU and some readings were found to be 4 degrees Celsius to 17 degrees Celsius low.
This Directive requires repetitive calibration testing of the TOT indicating system and necessary corrective actions, these measures are intended to prevent erroneous TOT indications which could prevent the flight crew from detecting that an engine temperature limitation has been exceeded. This condition, if not corrected, could result in damage to critical engine components, loss of engine power, and a subsequent forced landing.
Eugene Paul Holzapfel
Delegate of the Civil Aviation Safety Authority 17 May 2000
The above AD is notified in the Commonwealth of Australia Gazette on 24 May 2000.
Overview
The Civil Aviation Regulations 1998 were enacted to ensure the safety and efficiency of civil aviation in Australia. This legislation was introduced to address the need for comprehensive regulations governing the airworthiness of aircraft, maintenance standards, and operational safety. Enacted by the Parliament of Australia, the Civil Aviation Regulations 1998 aim to uphold the highest safety standards in civil aviation by establishing stringent requirements for aircraft design, maintenance, and operation. This Airworthiness Directive (AD) is issued under the authority of the Civil Aviation Safety Authority (CASA) to address specific safety concerns identified in certain McDonnell Douglas (Hughes) and Kawasaki helicopters. The directive mandates corrective actions to prevent erroneous turbine outlet temperature (TOT) readings, which could potentially lead to engine overheating and subsequent failure. The objective of this AD is to ensure the continued airworthiness of the affected helicopter models by requiring regular calibration tests and corrective measures as specified.
Scope and Application
This legislative instrument, part of the Civil Aviation Regulations 1998, applies to the maintenance and operational standards of certain McDonnell Douglas (Hughes) and Kawasaki helicopter models specifically the 369D, 369E, 500N, and 600N series, where the helicopters are equipped with specific analogue/digital turbine outlet temperature (TOT) indicators. The geographic and jurisdictional reach of this Airworthiness Directive (AD) is nationwide, as it is issued by the Civil Aviation Safety Authority (CASA) under the Commonwealth of Australia. The directive applies to any person or entity operating or maintaining these specified helicopter models within Australia, ensuring adherence to the safety standards set forth to prevent erroneous TOT indications which could lead to severe operational hazards. The AD does not explicitly mention any exclusions or exemptions, implying that all operators of the specified helicopter models must comply with the outlined requirements. The AD can extend its application through subordinate instruments, such as specific service bulletins referenced in the directive, which provide detailed instructions on the required actions and tests.
Key Provisions
This Airworthiness Directive (AD), as specified in Section 39.1 (1) of the Civil Aviation Regulations 1998, applies to specific McDonnell Douglas (Hughes) and Kawasaki helicopter models, namely the 369D, 369E, 500N, and 600N series. The directive mandates that specific actions must be taken to address issues with the turbine outlet temperature (TOT) indicating system. For the 369D, 369E, and 500N models, the TOT indicating system must be tested for correct calibration as per MD Helicopters, Inc. (MDHI) Service Bulletins SB369D-199, SB369E-093, and SB500N-019 dated 11 January 2000. If the test results are outside the acceptable range, corrective actions as specified in these bulletins must be implemented before further flight. For the 600N model, the test must include the electronic control unit (ECU) TOT sensing system, and the same calibration test procedures as mentioned for the other models apply. If the ECU TOT does not match the tester setting within ± 5 degrees Celsius, corrective actions must be undertaken as specified in MDHI Service Bulletin SB600N-026 dated 11 January 2000.
The AD imposes several obligations on the operators and maintainers of the affected helicopters. Operators must ensure that the specified calibration tests are conducted within the stipulated timeframes: within the next 50 hours time-in-service (TIS) after the effective date of this Directive or before 15 June 2000, whichever comes first, and then at intervals not exceeding 300 hours TIS. Corrective actions must be completed before further flight if the test results are not within the acceptable range. These obligations are essential to ensure the safety and reliability of the helicopter’s TOT indicating system, thereby preventing potential engine damage and ensuring the safety of the flight crew and passengers.
Failure to comply with the requirements of this AD can result in significant consequences. While the specific penalties are not detailed within the text, non-compliance with ADs can generally lead to severe repercussions under the Civil Aviation Regulations 1998. These can include fines, penalties, or even the grounding of the aircraft until the required actions are taken. The seriousness of the potential outcomes underscores the importance of adhering to these safety directives to maintain the airworthiness of the aircraft and ensure safe operations.