COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Bell Helicopter Textron Canada (BHTC) 206 and Agusta Bell 206 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/BELL 206/146 Engine RPM Sensor - Limitations 7/2001 DM
Applicability: All Model 206B and Series 206L helicopters equipped with Allison 250-C20R engine and Soloy engine power-out warning sensors, part number 206-075-545-001, in accordance with Supplemental Type Certificate (STC) SH 95-46 (FAA STC SH4179NM, applicable to Model 206B) and SH 95-45 (FAA STC SH4169NM, applicable to Model 206L).
Note 1: This Directive is not applicable to helicopters with a part number (P/N) 680- 2551-1 engine out sensor.
Requirement: If not previously accomplished, revise the Limitations Section of the applicable approved STC Rotorcraft Flight Manual Supplement by adding the following Warning Statement and Note:
WARNING: For aircraft with an engine-out sensor other than P/N 680- 2551-1 only. To prevent false engine-out signals, the following procedure must be followed during practice auto-rotations. When entering a practice auto-rotation, avoid a pausing or creeping movement of any throttle decrease or increase between full open and idle. If movement is not made at a firm and continuous rate, N1 RPM undershoot and/or oscillation may occur causing a momentary false engine-out warning light and audio indication.
NOTE: Ensure N1 RPM idle speed is set at 62-64%.
The Amendment may be accomplished by inserting a copy of this Directive into the Flight Manual Supplement.
Note 2: Transport Canada AD CF-2001-13 refers.
Note 3: The above amendment may have been previously accomplished in accordance with either FAA AD 95-24-06 Amdt 39-9438 which required a warning to be inserted in accordance with Soloy Corporation Service Bulletin (SB) 02-680 revised 8 December 1992 or Soloy Corporation SB 02-680R2 dated 25 May 2000 (this SB was approved by the FAA as an Alternate Method of Compliance to AD 95- 24-06 by FAA Transport Airplane Directorate Letter 140S-00-215 dated 16 May 2000).
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Compliance: Within 15 days after the effective date of this Directive.
This Airworthiness Directive becomes effective on 30 May 2001.
Background: This Directive requires the addition of a warning and a note to the Rotorcraft Flight Manual to alert the pilot of a potential false engine-out warning from the engine-out sensor when practicing autorotations.
Eugene Paul Holzapfel
Delegate of the Civil Aviation Safety Authority 17 May 2001
The above AD is notified in the Commonwealth of Australia Gazette on 30 May 2001.
Overview
The Civil Aviation Regulations 1998, enacted by the Commonwealth of Australia, form a critical framework for ensuring the safety and regulation of civil aviation within the country. This legislation, overseen by the Civil Aviation Safety Authority (CASA), addresses gaps and problems related to aircraft airworthiness, maintenance, and operational safety. A specific focus of the Civil Aviation Regulations 1998 is the issuance of Airworthiness Directives (ADs) to address identified safety issues. The policy objective behind these ADs is to ensure that all civil aircraft are maintained in a safe and airworthy condition, thereby protecting the public and enhancing the overall safety of the aviation industry. One such directive, AD/BELL 206/146, was introduced to address an issue with the engine RPM sensor in certain Bell Helicopter models, specifically to prevent false engine-out warnings during practice auto-rotations.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105 and Schedule of Airworthiness Directives, addresses the maintenance and operation standards for certain types of helicopters within Australian jurisdiction. This particular Airworthiness Directive, AD/BELL 206/146, applies to all Model 206B and Series 206L helicopters equipped with Allison 250-C20R engine and Soloy engine power-out warning sensors part number 206-075-545-001, as per the Supplemental Type Certificate (STC) SH 95-46 and SH 95-45. It excludes helicopters with a part number (P/N) 680- 2551-1 engine out sensor. The directive mandates that operators must revise the Limitations Section of their applicable approved STC Rotorcraft Flight Manual Supplement by adding a specific warning statement and note to prevent false engine-out signals during practice auto-rotations. Compliance with this directive is required within 15 days of its effective date of 30 May 2001. The directive aims to ensure safety and operational integrity of the specified helicopters within Australia's airspace.
Key Provisions
The Civil Aviation Regulations 1998, under Part 39, Section 105, establish the authority of the Civil Aviation Safety Authority (CASA) to issue airworthiness directives (AD). Section 39.1 (1) specifically allows the CASA delegate to issue these directives when there is a need to ensure the safe operation of aircraft. In this particular case, AD/BELL 206/146 focuses on Bell Helicopter Textron Canada (BHTC) 206 and Agusta Bell 206 Series Helicopters equipped with specific engine models. The directive mandates changes to the Rotorcraft Flight Manual Supplement to include a warning statement and a note concerning the operation of engine RPM sensors to prevent false engine-out signals during practice auto-rotations (section applicability and requirement).
Entities governed by this AD, including operators of the specified helicopters, must ensure that the mandated changes to the Rotorcraft Flight Manual Supplement are made within 15 days of the directive's effective date. This requirement underscores the necessity for operators to keep their documentation updated with the latest safety information to ensure the continued airworthiness of the aircraft. The compliance period is explicitly stated, leaving no ambiguity regarding the timeframe within which the directive must be adhered to.
Failure to comply with the airworthiness directive may result in serious safety implications and potential legal repercussions. While the specific penalties for non-compliance are not detailed within this text, breaches of airworthiness directives generally carry significant penalties under the Civil Aviation Act 1988 and the Civil Aviation Regulations 1988. These penalties can include fines, suspension of airworthiness certificates, and other enforcement actions that could impede the operation of non-compliant aircraft. The severity of these penalties highlights the importance of strict adherence to the AD by all affected parties.