COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Pitts S-1 and S-2 Series Aeroplanes
AD/PITTS S-2/16
Amdt 2
Upper Fuselage Longerons 4/98
Applicability: Models S-2A, S-2S, S-2E and S-2SE, all serial numbers, and model S-2B serial numbers 5000 to 5350 inclusive.
Requirement: 1. Inspect the fuselage longerons aft of the rear cabane strut attachments and forward of the instrument panel for cracks. Inspect, using a 10x magnifying glass, in accordance with paragraphs A.1 through A.4 and Figure 1 in the Accomplishment Instructions of Aviat Service Bulletin (SB) No. 24, revised November 22, 1996.
2. Either:
(a). Install an accelerometer and permanently mark the face with red marks (5 mm by 1.5 mm) at the +6g and -3g hash marks. Install a placard (Aviat part number 2-7604-47) stating the gravity (‘g’) force limitations within clear view of the pilot, in accordance with paragraph B.1 of the Accomplishment Instructions of Aviat SB No. 24, revised November 22, 1996; or,
(b). Install a placard within clear view of the pilot, using upper case letters at least
3.2 mm in height, which incorporates the words ‘AEROBATIC MANOEUVRES PROHIBITED’.
3. Repair the aircraft by incorporating Aviat Kit Number S-2-513, in accordance with the Installation Instructions section in Aviat Kit No S-2-513, dated August 26, 1996, revised May 9, 1997.
Note 1: Disregard the instructions in paragraph A.5 in the Accomplishment Instructions of Aviat SB No. 24, revised November 22, 1996. This AD takes precedence. Modification of the aircraft does not relieve the inspection requirement
Note 2: FAA AD 97-26-20 refers.
Compliance: 1. Inspect in accordance with Requirement 1 before further flight if unusual handling characteristics or airframe noises are noticed. Otherwise, inspect before 300 hours total time in service, or before 25 hours time in service after 26 March 1998, whichever occurs later. Thereafter inspect at intervals not to exceed 100 hours time in service.
2. Install either requirement 2(a) or 2(b) before 300 hours total time in service, or before 25 hours time in service after 26 March 1998, whichever occurs later. Compliance with requirement 2(a) at any later time cancels the aerobatic flight limitation of requirement 2(b).
3. Before further flight if damage is found as described by requirement 1. This amendment becomes effective on 26 March 1998.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Background: An unsafe condition may exist on certain Aviat (Pitts) aeroplanes. Four aircraft in the United States have reported cracking and failure of the longerons aft of the rear cabane strut attachments. In one incident, the cracked longeron made it very difficult to control the aeroplane. Investigation by the FAA has concluded that cracks are primarily caused by flight outside of the certificated ‘g’ limits of the aircraft.
Accordingly the requirements of this AD have been revised to incorporate measures to assist the pilot to fly within the aircraft’s approved limits.
Amendment 1 updated the FAA AD reference.
Amendment 2 aligns the requirements with those of the FAA.
Amendment 1 of this airworthiness directive became effective on 10 October 1996. The original issue of this airworthiness directive became effective on 31 May 1996.
Overview
The Civil Aviation Regulations 1998, amended by the PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Pitts S-1 and S-2 Series Aeroplanes AD/PITTS S-2/16 Amendment 2, was enacted to address the potential safety risks associated with the Pitts S-1 and S-2 series aeroplanes. This amendment specifically targets the issue of longeron cracking, which has been identified as a significant risk factor for these models. The problem of longeron cracking was highlighted by incidents in the United States, where the failure of these components has led to severe handling difficulties and safety hazards. The Civil Aviation Safety Authority (CASA) introduced these regulations to ensure the airworthiness of these aeroplanes by mandating specific inspections, modifications, and placarding to prevent accidents due to overstressing the aircraft beyond its design limits. The policy objective is to enhance flight safety by ensuring that pilots are aware of and adhere to the aircraft's structural limits, thereby mitigating the risk of accidents caused by exceeding those limits.
Scope and Application
The Civil Aviation Regulations 1998, specifically PART 39 - 105, addresses airworthiness directives concerning the Pitts S-1 and S-2 Series Aeroplanes, particularly focusing on the safety of the upper fuselage longerons. This regulation applies to the Pitts S-2A, S-2S, S-2E, and S-2SE models, as well as the S-2B model with serial numbers 5000 to 5350 inclusive. The geographic reach of this legislation is nationwide, as it is a Commonwealth regulation, thereby affecting all operators within Australia. The primary requirement of this directive is the inspection of the fuselage longerons for cracks, with specific instructions outlined for detailed visual and magnifying glass inspections. Operators are also required to either install an accelerometer with marked gravity force limitations or a placard prohibiting aerobatic manoeuvres, ensuring pilots are clearly informed of flight limitations. Repairs must be made using specific Aviat Kit Number S-2-513. Compliance with these requirements is mandatory, with initial inspections and installations to be completed within 300 hours of total time in service or 25 hours after 26 March 1998, whichever is later, and subsequent inspections must occur at intervals not exceeding 100 hours. The directive's amendments and updates reflect alignment with the Federal Aviation Administration's directives to ensure consistency and safety standards across international operations.
Key Provisions
The main operative sections of the Civil Aviation Regulations 1998, specifically Part 39 - 105, establish airworthiness directives for Pitts S-1 and S-2 Series Aeroplanes, focusing on the upper fuselage longerons. Section 1 of AD/PITTS S-2/16Amdt 2 mandates an inspection of the fuselage longerons for cracks, requiring the use of a 10x magnifying glass, in accordance with the specified service bulletin and its accomplishment instructions (section 1). Section 2 outlines two compliance options: either installing an accelerometer and marking it at the specified gravity force limits, along with a placard for pilot visibility, or installing a placard explicitly stating "AEROBATIC MANOEUVRES PROHIBITED" (section 2). Section 3 requires the aircraft to be repaired using the specific Aviat Kit Number S-2-513 as per its installation instructions, with a noted exception that certain instructions from the service bulletin are disregarded (section 3). The directive also sets forth compliance timelines and conditions, including inspection intervals and installation deadlines (section 4).
The obligations imposed by the Civil Aviation Regulations 1998, as detailed in the airworthiness directive, require aircraft operators to conduct thorough inspections of the fuselage longerons to identify any cracks or potential issues. Operators must either install the specified accelerometer with markings and placard or install a placard prohibiting aerobatic manoeuvres before reaching certain time-in-service thresholds. Compliance with these requirements is mandatory, and failure to adhere to the inspection and installation schedules can result in significant safety risks. The directive also mandates the use of a specific repair kit to address any identified issues, ensuring the aircraft remains airworthy.
Failure to comply with the provisions outlined in the airworthiness directive can lead to serious consequences. The regulations establish potential offences and penalties for non-compliance, although specific penalties are not detailed in the provided text. The overarching consequence of non-compliance is the risk of compromising the airworthiness of the aircraft, which can result in severe safety hazards, including potential aircraft failure during flight. The directive's purpose is to ensure the safety of the aircraft by mandating specific actions to address identified issues, and failure to do so can have dire implications for both the operator and the safety of the flight.