
SDR 510021862 | Cessna 402C wing frame structure—fitting corroded. The R/H upper wing fitting found corroded at the wing type B inspection, this is a 1200 hr inspection. (R/H upper rear wing fitting). This was caused by exfoliation corrosion. The corrosion had started on the inner top surface, this surface butts up with the top spar cap and is not visible at normal inspection. The corrosion then progressed to the front top surface where it was visible. P/No: 50110232. TSN: 16268 hours

SDR 510021821 | Robinson R22BETA fuselage structure—frame cracked. While disassembling the aircraft in accordance with Robinson R22 2200 hourly inspection, the upper welded frame was found to be cracked/broken all the way through in one place. The break was located on the central support for the aft right hand main rotor transmission mount. It was found that the location of the wiring loom may have increased the difficulty to inspect this part of the frame during scheduled inspections. P/No: A0202. TSN: 4399 hours TSO: 2200 hours.

SDR 510021804 | Cessna A152 horizontal stabiliser structure—bracket cracked. Upper surface cracked at two locations adjacent to o/b vertical fin attach bracket anchor nuts. Cracks approx. 25mm long. P/No: 04320049. TSN: 21708 hours

SDR 510021790 | IAE V2533A5 engine (turbine/turboprop)—plug broken. During open up for engine HPT blade BSI, the BSI plug T1/2L inner plug was found broken off and detached from the external cover. The broken inner plug was located and retrieved from the turbine casing inter layer cavity. No obvious damage was found on the turbine casing. A new plug assembly was installed after the completion of the BSI inspection. P/No: 2A2351.

SDR 510021776 | Cessna 172RG landing gear retract/extension system—actuator cracked. L/H main gear failed to fully retract. Investigation showed that a foreign object (possible a washer) has jammed the gear drive causing the actuator housing to crack and damaged the gear sector (part number 9882002-2). P/No: 12810012. TSN: 7258 hours

SDR 510021746 | Beech 200BEECH Air conditioning wiring—terminal loose. During routine fault finding for an intermittent air conditioning system it was found that the main terminal post attachment screw and nut had loosened causing localised heating and material failure of the support structure of the contactor terminal support post. P/No: MS24166D1.

SDR 510021736 | Piper PA31350 horizontal stabiliser plates/skin—skin damaged. Left and right horizontal stabilizer leading edge skins had several large dents and holes/splits. Damage had not been repaired, just filled over with body filler and leading edge tape. Larger holes had fiberglass mat repairs. P/No: 4015514AND4015515. TSN: 19923 hours/450 months

SDR 510021676 | Cessna 208B Wing spar—fitting cracked. Crack found on rear upper attachment of R/H wing strut. This is the second time this inspection has been carried out on this fitting, the first being at approximately 5000 hours with nil defects evident. P/No: 26210082. TSN: 8395 hours/11508 cycles/13927 landings/164 months