Swearingen SA227DC Rudder control system—rod end damaged.
Pilot reported binding of rudder pedals during brake application with right rudder activated. Rod end on rudder pedal interconnect found bent. P/No: MS211518.
Lycoming IO540K1B5 engine fuel pump—pump failed.
Engine decelerated during cruise. Aux fuel pump turned on, engine rpm increased, aircraft returned to base, on ground noted, fuel was spraying from engine driven pump case drain line. On shutdown found oil level two quarts higher. Engine driven pump found failed, with broken vanes and signs of excessive overheating, causing cracks of pump body. Shaft had signs of blueish metal indicating high heat and shaft seal had disintegrated allowing aux fuel pump fuel pressure to enter engine accessory case. Pump replaced, oil drained, flushed and oil replenished. Found debris in FCU filter, filter cleaned and reinstalled. Engine oil filter inspected as precaution found OK, no contaminants. Engine runs c/out all parameters normal. P/No: 201F5003. TSN: 502 hours
Beech B200C air conditioning system—filter contaminated metal.
FWD aircon blower accessed to check brushes, numerous metallic debris found in filter.
Filter replaced. P/No: 1015553090005
Beech B200C service doors—seal missing.
Panel removed to access FWD aircon blower fan assembly. Seal on panel underside missing. Seal replaced with new item. P/No: 10141006425.
Beech B200C air conditioning system—bearing unserviceable.
Pilot reported aircon U/S. Engineer found pulley drive assembly U/S due to collapsed bearing caused by lack of lubrication. Pulley, quick shaft and bearing replaced. Assembly cleaned; checked serviceable after replacement. P/No: 1179100593
Beech B200C air conditioning system—bearing unserviceable.
Pilot reported aircon U/S. Engineer found pulley drive assembly U/S due to collapsed bearing caused by lack of lubrication. Pulley, quick shaft and bearing replaced. Assembly cleaned; checked serviceable after replacement. P/No: 1179100593
Cessna 208 control column section—control mechanism unserviceable.
Pilot reported during taxi for take-off, while the elevator trim was being set, the cockpit elevator trim wheel became detached from the control pedestal. Engineering was dispatched to rectify the problem. On investigation it was determined that the shaft that holds the elevator trim wheel to the control pedestal had broken, causing the wheel to become detached and the elevator trim to become unserviceable. P/No: C2995140105. TSN: 4159 hours/14768 cycles
Cessna 208B landing gear brake system—line failed.
The RH MLG brake line running from the fuselage to the brake calliper came away from the swage terminal at the calliper connection. The aircraft was taxiing at the time of failure and which caused the pilot to lose control of the aircraft resulting in a collision with another stationary aircraft. The flexible brake line being completely unserviceable is to be replaced with a new assembly. The pilot completed the daily inspection for that day, would not have been aware that the line was close to failure if it was still located within the swage terminal and without physically trying to pull the line from the swage terminal, particularly if there was no hydraulic fluid present. P/No: 264102717. TSN: 60 hours
Piper PA31350 wheel—wheel fractured.
Pilot reported to make a normal landing, during the landing roll once the brakes were applied the L/H main wheel assembly suffered a wheel lock up. Inspection found a failure of the L/H MLG wheel half. The failure resulted in a portion of the bead fracturing and becoming lodged between the brake calliper and wheel assembly. Following disassembly and further inspection the fracture had appeared to develop over a short time discernible by the ageing of the initial fracture. P/No: 16119.
Jabiru 4A482POD propeller blade section—propeller cracked.
On carrying out engine related work, propeller blade was found to be cracked in two places. Flexing blade allowed crack to open up. Propeller removed from A/C. P/No: 4A482TOD. TSN: 330 hours
Piper PA32300 stabiliser control system—terminal damaged.
While carrying out a periodic inspection, strange marks were found on the swaged cable fittings on the aft stabilator cables, cables were replaced as this is similar to the issues expressed in FAA AD 2013-02-13. P/No: 62701012AND62701013.
Cessna 177RG nose/tail landing gear—bolt broken.
During the inspection it was discovered that the nose-wheel front drag-brace bolt had failed and approximately half the bolt was missing. The remaining half was removed for inspection along with the pivot bolt (next bolt along aft of the nose wheel). MPI inspection revealed faults with the pivot bolt also, but it had not yet broken. Both bolts were replaced with new parts and the aircraft returned to service.
Cessna 182P elevator tab control system—cable broken.
Elevator trim cable found 90 per cent broken during SIDs inspection. P/No: 051010187. TSN: 4786 hours
Eurocopter EC130B4 empennage structure—fitting cracked.
During inspection the stabiliser attach fitting was inspected closely due to the manufacturer issuing a recommended SB showing similar damage to the lower right fitting. A faint visual indication was noted and an eddy current inspection showed that further cracking was present below the painted area. The manufacturer was informed and a Level D repair through modification was carried out. P/No: 350A23422320. TSN: 1200 hours
Bombardier CL604 DC generation system—IDG faulty.
At cruise level the GEN 1 OFF CAS message was posted. Initial visual inspection of the LH integrated drive generator found the generator had lost oil and was had produced a lot of heat. There was delamination on the adjacent cowl, also bubbled paint. After removing the IDG it was observed the shaft was not sheared, but had no resistance if turned. It seemed there was an internal failure in the IDG. The failure may have been caused by a loss of oil, which then caused the IDG to overheat and fail; or something inside the IDG failed which caused an oil leak, and the IDG then overheated. P/No: 731579C
Lycoming IO360M1A engine reciprocating—filter split.
Engine air filter discovered split around 180 degrees. Two similar defects reported. P/No: FR08504. TSN: 139 hours
