AIRCRAFT BELOW 5700 kg

BEECH B300C–ATA 2731 ELEVATOR TAB CONTROL SYSTEM–CABLE–FOULED. DR 611852065
During cables inspection, elevator trim cable was noted to be fouling with rudder cables at FS 280.750. Here it passed through holes in a rubber flange on the fuselage frame. There are three holes in the flange very close together and the two elevator cables had migrated into the same hole as the rudder cable and were rubbing together. The three holes are connected by a slit in the rubber flange. It was thought initially that the cause was low tension in the elevator trim cables, but they were only 1 lb below required tension. Rubber flange will now be replaced which should hold the cables in their correct position. OEM notified, awaiting response.

BEECH B300C–ATA 3260 LANDING GEAR POSITION AND WARNING SYSTEM–circuit card–UNSERVICEABLE. DR 611852094
Landing gear was selected down, gear travelled and locked down but with no green annunciators illuminating. Annunciator Control Circuit Card A125 replaced with serviceable item and tested serviceable.

CESSNA 402 C–ATA 5740 WING, ATTACH FITTINGS–FITTING–CORRODED. DR 611852097
While performing scheduled operations, engineers discovered exfoliation corrosion on the top side of LH aft upper wing carry through attachment fitting P/N 5011023-1. When removed, small visible area of corrosion extended to approximately 3/4″ by 3/4″ to 0.025″ deep. With no allowable tolerance for corrosion in the inspection criteria, fitting is being replaced with a new item.

PIPER PA28 161–ATA 2730 ELEVATOR CONTROL SYSTEM–CABLE–BROKEN. DR 611852098
Broken stabilator cable at turn barrel. Corrosion on cable end fitting caused complete separation of cable at turn barrel. Lock wire on cable prevented loss of control.

GIPPSLAND GA8–ATA 5740 WING, ATTACH FITTINGS–FITTING–SERVICEABLE. DR 611852103
Inspection IAW AD/GA8/9 Amdt 1 and SB-GA8-2017-174 Issue 2. All potentially affected parts were inspected. Serial numbers could not be confirmed by physical inspection, however nil defects evident at the time of inspection.

CESSNA 210 N–ATA 3230 LANDING GEAR RETRACT/EXTENSION SYSTEM–LANDING GEAR–FAILED-RETRACT. DR 611852135
Inflight hydraulic loss resulting in cycling of the hydraulic power pack. Aircraft suffered an inflight loss of hydraulic fluid from the up side of the aircraft’s hydraulic system. Leak was traced to the outboard union on the R/H under carriage down lock actuator. The seal in this union, an MS28778-4, was found compressed and unserviceable. Seal replaced. Gear swings satisfactory.

CESSNA 208 B–ATA 2435 STARTER-GENERATOR–STARTERGENERATOR–ARCED. DR 611852136
During an engine start sequence, pilot observed an electrical arcing smell which corresponded to abnormal starting indications.

BEECH 200 B200C–ATA 5311 FUSELAGE MAIN, FRAME–FRAME–CRACKED. DR 611852139
Crack found in the intersection of stringer #10 and frame at STA 337.75. Repair scheme arranged.

CESSNA 208 B–ATA 3244 TIRE–TYRE TUBE–PUNCTURED. DR 611852146
Inner tube has been cut and deflated the tyre. This is the second similar case of a very unusual cut pattern on the inner tube. The cut pattern appears to be in the same area as the tyre manufactures affixes sticker on the inside of the tyre. The cut pattern is like crazing in toughened glass. OEM advised that these were quality control stickers, and these could be removed before fitment.

CESSNA 305 F–ATA 5740 WING, ATTACH FITTINGS–FITTING–CRACKED. DR 611852181
While SIDs inspection, of 57-11-01 wing structure & 57-40-01 strut & strut wing attachment, crack indication detected on LH strut lower strut fitting.