COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-34 (Seneca) Series Aeroplanes
AD/PA-34/48 Flap Handle Attach Bolt 9/96
Applicability: Models Serial Numbers
PA-34-200 34-7250001 through 34-7450220
PA-34-200T 34-7570001 through 34-8170092
PA-34-220T 34-8133001 through 34-8233088
Requirement: a) Measure the cable mounting attach hole diameter and enlarge the hole to .316 of an inch diameter. If the diameter of the cable mount attach hole is larger than
.316 of an inch, replace the flap lever handle (refer to the illustrated parts catalogue for the part number), in accordance with the Instructions section of Piper SB 965.
b) Install a new bushing (using only Piper part number (P/N) 63900-174) into the cable mounting attach hole, in accordance with the Instructions section of Piper SB 965.
c) Replace the flap lever handle attach bolt with a new clevis bolt (Piper P/N 400 673 or standard P/N AN23-11) in accordance with the Instructions section of Piper SB 965.
d) Inspect the washer, nut, and cotter pin, and if damaged, replace washer (Piper P/N 407-564 or standard P/N AN960-10), nut (Piper P/N 404-392 or standard P/N AN320-3), and cotter pin (Piper P/N 424-051 or standard P/N MS24665- 132) in accordance with the Instructions section of Piper SB 965.
Note 1: FAA AD 96-10-03 Amdt 39-9608 refers.
Note 2: The Requirement instructions of this Directive do not mirror the instructions in Piper SB 965. This Directive requires installing the clevis bolt, regardless of the condition of the current part.
Compliance: Upon the accumulation of 2,000 hours time in service or within the next 100 hours time in service after 15 August 1996, whichever occurs later.
Background: The FAA received reports of worn flap handle attach bolts and elongated holes in the flap lever to cable mounting attach point. Failure of the flap handle attach bolt could cause a sudden retraction of the flaps, and result in loss of control.
Overview
The Civil Aviation Regulations 1998, specifically within Part 39, addresses the safety requirements for civil aircraft and includes the Airworthiness Directive AD/PA-34/48 pertaining to Piper PA-34 (Seneca) Series Aeroplanes. Enacted by the Australian Government, this legislation was introduced to ensure the safety and reliability of civil aviation, particularly in response to issues identified with the flap handle attach bolts on the specified Piper models. The overarching policy objective is to mitigate the risk of accidents caused by mechanical failures in aircraft, ensuring that all aircraft meet stringent safety standards. The directive requires specific modifications to the flap handle attach bolt and related components to prevent potential failures that could lead to loss of control, thereby protecting the safety of passengers and crew.
This legislative instrument, issued under the authority of the Civil Aviation Act 1988, mandates compliance with the specified maintenance and inspection requirements for the affected Piper PA-34 models. The directive requires that certain actions be taken within a specified timeframe, either after the aircraft accumulates 2,000 hours of flight time or within 100 hours after 15 August 1996, whichever is later. The directive references FAA AD 96-10-03 and requires the installation of a clevis bolt regardless of the condition of the current part, aligning with the instructions provided in Piper SB 965 to ensure safety and uniformity in maintenance procedures.
Scope and Application
The Civil Aviation Safety Authority (CASA) has issued an Airworthiness Directive (AD) under the Civil Aviation Regulations 1998, specifically targeting the Piper PA-34 (Seneca) series aeroplanes, with serial numbers falling within certain ranges for models PA-34-200, PA-34-200T, and PA-34-220T. This legislation applies to the specified aircraft models to ensure they meet critical safety standards concerning the flap handle attach bolt and associated components. The AD mandates the measurement and adjustment of the cable mounting attach hole diameter, installation of a new bushing, replacement of the attach bolt, and inspection of the washer, nut, and cotter pin, with replacements as necessary. The directive applies regardless of the condition of the current parts and must be complied with either after the aeroplane accumulates 2,000 hours of time in service or within 100 hours of time in service following 15 August 1996, whichever is later. This AD aims to prevent the failure of the flap handle attach bolt, which could lead to a sudden retraction of the flaps and loss of control. The AD extends its application nationally, ensuring compliance across all relevant aircraft within the Commonwealth of Australia.
Key Provisions
The key operative sections of the Civil Aviation Regulations 1998 (Cth), specifically Part 39 - 105, require modifications to the flap handle attach bolt on Piper PA-34 (Seneca) Series aeroplanes. Section 39 - 105 mandates that certain models of the Piper PA-34 aeroplanes must adhere to specific safety directives. For instance, the AD/PA-34/48 addresses the flap handle attach bolt, detailing precise modifications that must be made to ensure the safety of the aircraft. These modifications include measuring the cable mounting attach hole diameter, enlarging the hole to.316 of an inch if necessary, and replacing the flap lever handle if the hole is larger than this specified diameter (section 39 - 105, subparagraph a).
The obligations imposed by this legislation are clear and precise. Operators of the affected Piper PA-34 aeroplanes must ensure that the specified modifications to the flap handle attach bolt are carried out. This includes measuring and potentially enlarging the cable mounting attach hole, installing a new bushing, replacing the attach bolt with a new clevis bolt, and inspecting and replacing any damaged washers, nuts, and cotter pins (section 39 - 105, subparagraphs b, c, and d). Compliance with these requirements must occur upon the accumulation of 2,000 hours of time in service or within the next 100 hours of time in service after 15 August 1996, whichever is later (section 39 - 105).
Failure to comply with these requirements can result in serious consequences. The Civil Aviation Safety Authority (CASA) has the authority to enforce compliance, and non-compliance could lead to safety risks that may result in accidents or loss of control. While the specific penalties for non-compliance are not detailed in the excerpt, they could include fines, enforcement actions, or other regulatory penalties as prescribed by the Civil Aviation Act 1988 (Cth). These penalties underscore the importance of adhering to the safety directives to maintain the airworthiness of the aircraft.