The relevant tasks in the trouble shooting manual did not specifically identify the pitot probe as a potential source of airspeed indication failure.
The Civil Aviation Safety Authority did not require builders of amateur‑built experimental aircraft to produce a flight manual, or equivalent, for their aircraft following flight testing. Without a flight manual the builder, other pilots and subsequent owners do not have reference to operational and performance data necessary to safely operate the aircraft.
The maintenance program for the aircraft’s landing gear did not adequately provide for the detection of corrosion and cracking in the yoke lug bore.
The Civil Aviation Safety Authority did not have a defined process for a robust, systematic approach to the assessment and approval of alternative non-destructive inspection procedures to ensure that the proposed method provided an equivalent, or better, level of safety than the original procedure.
The eddy current inspection used on VH-TZJ, and other M18 aircraft, had not been approved by the Civil Aviation Safety Authority as an alternate means of compliance to airworthiness directive AD/PZL/5. This exposed those aircraft to an inspection method that was potentially ineffective at detecting cracks in the wing attachment fittings.
Although wing removal was necessary to provide adequate access for effective visual and magnetic particle inspections of M18 wing attachment fittings, the aircraft manufacturer’s service bulletin E/02.170/2000 allowed the wings to remain attached during these inspections.
The engineering justification supporting Australian supplemental type certificate SVA521 did not contain consideration of the effect an increase in the average operating speed could have on the rate of fatigue damage accumulation.
Important information relating to Civil Aviation Safety Authority (CASA) airworthiness directive AD/PZL/5 was not contained in CASA’s airworthiness directive file, but on other CASA files with no cross-referencing between those files. This impacted CASA’s future ability to reliably discover that information and make appropriately‑informed decisions regarding the airworthiness directive.
Operators of some Australian M18 Dromaders, particularly those fitted with turbine engines and enlarged hoppers and those operating under Australian supplemental type certificate (STC) SVA521, have probably conducted flights at weights for which airframe life factoring was required but not applied. The result is that some of these aircraft could be close to or have exceeded their prescribed airframe life, increasing the risk of an in-flight failure of the aircraft’s structure.
Operation of M18 aircraft with a more severe flight load spectrum results in greater fatigue damage than anticipated by the manufacturer when determining the service life of the M18. If not properly accounted for, the existing service life limit, and particular inspection intervals, may not provide the intended level of safety.
The documented procedure for eddy current inspection of M18 wing attachment fittings did not assure repeatable, reliable inspections.
The spin recovery methods taught by the flying school were inconsistent across instructors and training material, and were not always appropriate for the Chipmunk aircraft type used by the school.
It was likely that, because of the Civil Aviation Safety Authority’s policy at the time, their engineering assessment of the tie rod design for inclusion in the manufacturer’s Australian Parts Manufacturer Approval did not consider the service history of the original tie rods or identify that they were subject to airworthiness directive AD/DH 82/10. Consequently, the assessment team was likely unaware that the original tie rods were subject to a life limitation, and did not require the life limits for the replacement tie rods to be established.
The JRA-776-1 fuselage lateral tie rods that were inspected by the ATSB were not appropriately marked with part and serial numbers, affecting the traceability and service history of the parts in a number of aircraft.
The manufacturer’s quality system did not prevent non-conforming tie rods from being released for use on aircraft.
Although a number of aerobatic manoeuvres were permitted in Tiger Moth aircraft, there was no limitation on the amount of aerobatic operations that was considered to be safe. As a result, operators may be unaware that a high aerobatic usage may exceed the original design assumptions for the aircraft.
Over 1,000 parts were approved by the Civil Aviation Safety Authority for Australian Parts Manufacturer Approval using a policy that accepted existing design approvals without the authority confirming that important service factors, such as service history and life‑limits, were appropriately considered.
Together with a number of other Australian Tiger Moths, VH-TSG was fitted with non‑standard Joint H attachment bolts that did not conform to the original design with the result that the integrity of the Joint H could not be assured.
When approving the change in material for the manufacture of the replacement tie rods, the design engineer did not identify that the original parts had a life limitation, or that they had shown susceptibility to fatigue cracking. As a result, the engineer did not compare the fatigue performance of the alternative design to the original, and the replacement tie rods were manufactured to that design and released into service with an unknown fatigue life.
Debris originating from the starter failure was not contained by the starter casing and severed the number one engine B-sump oil scavenge pipe.
