COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Schweizer (Hughes) 269 Series Helicopters
AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/HU 269/28 Amdt 2 and issues the following 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 269/28
Amdt 3
Main Rotor Thrust Bearing P/N 269A5050-50 or
-51 Nut and Mast - Inspection and Modification
8/2000
Applicability: Model 269A helicopters, S/N 0011 to 1109, Model 269A-1 helicopters, S/N 0001 to 0041, Model 269B helicopters, S/N 0001 to 0444 and model TH-55A with main rotor thrust bearing P/No 269A5050-50, -51 or -73 installed.
Requirement: 1. Examine the helicopter records to determine P/N of main rotor thrust bearing.
(a) If bearing P/No 269A5050-50 or -51 is fitted, inspect in accordance with Step II, paragraph b. of Schweizer Service Notice (SSN) No N-59, dated October 9, 1968.
(b) If bearing P/No 269A5050-73 is fitted. Inspect for corrosion, rust, freedom of rotation, looseness, binding, nicks, burrs, cracks and lubrication. Repack the bearing cavity in accordance with Schweizer Aircraft Corporation CKP-C-41 “Installation Instructions for 269 Series Helicopters, SA-269K-057-1 Main Rotor Thrust Bearing Kit,” dated June 9, 1994.
Note 1: Bearing P/N 269A5050-50 and 269A5050-51 have a 300 hour retirement life while bearing P/N 269A5050-73 has a 3000 hour retirement life.
2. Inspect the thrust bearing nut P/N 269A1306-5 for corrosion and physical damage and confirm nut has been modified in accordance with Step III of SSN No 59. Replace any nut found damaged, corroded or not modified.
3. Inspect interior of main rotor mast for corrosion, damage, foreign material, moisture or inadequate drainage due to a build up of zinc chromate paste and determine whether the mast has been modified in accordance with Step II of SSN No 59. If mast has not been modified, modify mast in accordance with Step III of SSN No 59.
If corrosion or damage is found, replace mast with serviceable mast modified in accordance with Step III of SSN No 59. If mast interior has foreign material, moisture or inadequate drainage due to chromate build-up, then clean in accordance with Step II of SSN No59.
Note 2: FAA AD 97-05-06 Amendment 39-9950 supersedes FAA AD 68-21-05
Amendment 39-1055 and 39-672.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Compliance: 1 (a). Unless previously accomplished, within 25 hours time in service (TIS) from the effective date of this Directive. Re-inspect bearing after 150 hours TIS. Replace bearing before further flight if TIS equals or exceeds 300 hours. If bearing TIS equals or exceeds 275 hours and is less than 300 hours replace within next 25 hours. If bearing TIS is less than 275 hours replace on or before 300 hours.
(b) Unless previously accomplished, within 25 hours TIS from the effective date of this Directive. Thereafter, re-inspect at intervals not exceeding 600 hours TIS.
2. Unless previously accomplished within 25 hours time in service from the effective date of this Directive.
3. Unless previously accomplished within 25 hours time in service from the effective date of this Directive.
This Amendment becomes effective on 10 August 2000.
Background: This amendment has been raised to align the mast bearing inspection requirements with the country of origin Airworthiness Directive.
Eugene Paul Holzapfel
Delegate of the Civil Aviation Safety Authority 5 June 2000
The above AD is notified in the Commonwealth of Australia Gazette on 12 July 2000.
Overview
The Civil Aviation Regulations 1998, enacted by the Parliament of Australia, provide a regulatory framework for civil aviation in Australia, including the issuance of Airworthiness Directives (ADs) by the Civil Aviation Safety Authority (CASA). These ADs are designed to address specific safety concerns and ensure the airworthiness of aircraft. The AD in question, AD/HU 269/28 Amendment 3, specifically targets Schweizer (Hughes) 269 Series Helicopters to rectify unsafe conditions identified with their main rotor thrust bearings, thrust bearing nuts, and main rotor masts. This AD aims to enhance safety by mandating inspections, modifications, and replacements of these components, aligning with international standards set by the Federal Aviation Administration (FAA) in the United States. CASA’s policy objective, as evident in this AD, is to mitigate risks associated with mechanical failures in these critical helicopter components, ensuring continued safe operation within Australia's airspace.
Scope and Application
The Civil Aviation Regulations 1998, as amended, pertain to the safety standards and regulations governing civil aviation in Australia, with specific Airworthiness Directives (AD) issued under the authority of the Civil Aviation Safety Authority (CASA). One such AD, AD/HU 269/28 Amdt 3, applies to Schweizer (Hughes) 269 Series Helicopters, specifically models 269A, 269A-1, 269B and TH-55A within specified serial number ranges, and mandates rigorous inspections and modifications to the main rotor thrust bearing and related components. This directive requires inspections and modifications to ensure the continued airworthiness of these helicopters, addressing potential safety issues such as bearing degradation and mast corrosion. The compliance schedule stipulates that inspections must occur within 25 hours of the directive's effective date, with subsequent inspections and replacements at defined intervals to maintain safety standards. This AD extends its reach across the Commonwealth of Australia, necessitating adherence by operators, owners, and maintenance personnel of the affected helicopters.
Key Provisions
The Airworthiness Directive (AD) AD/HU 269/28 Amdt 3 issued under subregulation 39.1 (1) of the Civil Aviation Regulations 1998 (CAR 1998) outlines specific requirements for inspecting and modifying certain components of Schweizer (Hughes) 269 Series Helicopters. The AD applies to Model 269A, Model 269A-1, Model 269B helicopters, and the model TH-55A with specified main rotor thrust bearings. It requires helicopter operators to examine the main rotor thrust bearing, inspect the thrust bearing nut, and inspect and modify the main rotor mast according to specified procedures and intervals. The initial inspections and modifications must be completed within 25 hours of time in service from the AD's effective date.
The AD imposes several obligations on the parties governed by it. Operators must ensure that all specified inspections and modifications are carried out on their Schweizer (Hughes) 269 Series Helicopters within the stipulated timeframes. For the main rotor thrust bearing, inspections must be conducted at intervals not exceeding 150 hours of time in service (TIS), with replacements scheduled before reaching 300 hours TIS. The thrust bearing nut must be inspected and any damaged or unmodified nuts replaced within 25 hours TIS from the AD's effective date. Similarly, inspections of the main rotor mast and any required modifications or cleaning must be completed within 25 hours TIS from the AD's effective date. Failure to comply with these obligations may result in the aircraft not meeting the required airworthiness standards.
Non-compliance with the AD can result in serious consequences. Civil Aviation Safety Authority (CASA) may take enforcement actions against operators who fail to adhere to the AD's requirements. Potential penalties include fines and potential grounding of the aircraft until compliance is achieved. The exact penalties can vary based on the severity of the non-compliance and may be determined under relevant aviation safety laws and regulations. It is crucial for operators to meticulously follow the AD to ensure the continued airworthiness of their aircraft and to avoid legal repercussions.