COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Robinson R22 Series Helicopters
AD/R22/29 Main Rotor Pitch Link 8/87 TX
Applicability: All R22 helicopters S/N 0580 through S/N 0644. All R22 helicopters overhauled or repaired at RHC completed between 15 August 1986 and 7 May 1987. R22 helicopters fitted with pitch link parts A258-1 -2, or -3, received from RHC between 15 August 1986 and 7 May 1987.
Requirement: 1. Inspect main rotor pitch links for cracks in accordance with Part A of RHC S.B. No. 57.
2. Replace fittings in accordance with Part B of RHC S.B. No. 57.
Compliance: 1. Prior to next flight after 16 June 1987, and each flight thereafter until Part B is accomplished.
Note 1. If cracks are found, perform Part B of RHC S.B. No. 57 prior to any further flight.
Note 2. This inspection may be accomplished by the pilot in command in which case he shall enter and certify for this A.D. in col. 2 part 3 of the Maintenance Release on each occasion.
2. Within the next 10 flight hours or by 15 July 1987 whichever occurs first.
Background: Flaws have been found in the material used during a production run of the A258-2 and A258-3 pitch link components. These flaws produce lengthwise cracks in the parts and, if allowed to progress, these cracks could lead to failure of the pitch link and loss of control of the helicopter.
Overview
The Civil Aviation Regulations 1998, administered by the Civil Aviation Safety Authority (CASA), are a comprehensive set of rules governing aviation safety in Australia. Part 39 of these regulations includes various airworthiness directives designed to ensure the safety and reliability of aircraft. One such directive, AD/R22/29, pertains specifically to Robinson R22 Series Helicopters, addressing a critical issue identified in the main rotor pitch links. Enacted to rectify a gap in safety protocols, this directive responds to the discovery of material flaws in certain pitch link components (A258-1, -2, and -3) used in R22 helicopters, which could lead to catastrophic failure if left unaddressed. The policy objective behind this directive is to mitigate the risk of in-flight accidents by mandating rigorous inspection and, if necessary, replacement of these components to ensure the continued safe operation of the affected aircraft.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, under the Civil Aviation Safety Authority, governs the safety directives for aircraft including the Robinson R22 series helicopters. The regulation in question, AD/R22/29, pertains to the main rotor pitch link for all R22 helicopters with serial numbers ranging from 0580 to 0644, those that were overhauled or repaired at Robinson Helicopter Company (RHC) between 15 August 1986 and 7 May 1987, and those fitted with pitch link parts A258-1 to A258-3 sourced from RHC during the same period. The requirement necessitates that the main rotor pitch links be inspected for cracks as outlined in Part A of RHC S.B. No. 57, followed by the replacement of fittings as per Part B of RHC S.B. No. 57. Compliance must be achieved before the next flight after 16 June 1987 and each subsequent flight until the replacement is completed, with an additional requirement to complete the replacement within the next 10 flight hours or by 15 July 1987, whichever comes first. This directive is crucial to prevent the progression of cracks that could compromise the structural integrity of the pitch link, potentially leading to a loss of control over the helicopter.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, incorporates an airworthiness directive (AD/R22/29) concerning the Robinson R22 series helicopters. This directive applies to all R22 helicopters with serial numbers (S/N) ranging from 0580 to 0644, those overhauled or repaired at Robinson Helicopter Company (RHC) between 15 August 1986 and 7 May 1987, and those fitted with pitch link parts A258-1 through -3 received from RHC during the same period. The directive mandates two primary actions: inspecting the main rotor pitch links for cracks, and replacing fittings if necessary. These inspections and replacements must be carried out in accordance with Part A and Part B of RHC Service Bulletin No. 57.
In terms of compliance, the regulations require that the inspection of the main rotor pitch links for cracks be completed before the next flight after 16 June 1987 and before each subsequent flight until the replacement of fittings is completed. If any cracks are detected, the replacement procedures outlined in Part B of RHC Service Bulletin No. 57 must be performed before any further flights. Notably, the pilot in command is permitted to conduct the inspection and must enter and certify the inspection in column 2, part 3 of the Maintenance Release each time. Furthermore, the replacement of fittings must occur within the next 10 flight hours or by 15 July 1987, whichever comes first.
The directive also outlines the potential consequences of non-compliance. Failure to adhere to the specified inspection and replacement requirements could result in safety risks, as the identified flaws in the pitch link components can lead to lengthwise cracks that might compromise the structural integrity of the pitch link. Such a failure could ultimately result in the loss of control of the helicopter, posing a severe threat to the safety of all on board and potentially leading to criminal charges, civil penalties, or other regulatory actions under the Civil Aviation Act 1988 and related regulations. The exact penalties for non-compliance would depend on the severity and circumstances of the breach, but they could include significant fines and potential imprisonment.