|BOMBARDIER CL600 2B16 – ATA 4900 AIRBORNE AUX POWER UNIT (APU) SYSTEM – APU – OVERTEMPERATURE. DR 611953516
APU Over-temp CAS message on APU shutdown accompanied by a loud bang and smoke. No sign of APU wind-down. Failure of internal component. Rectifications planned.
|AIRBUS A320 232 – ATA 2421 AC GENERATOR-ALTERNATOR – IDG – CONTAM-METAL. DR 611953506|
|Crew carried out an air return due to ELEC IDG 1 OIL LO PR ECAM after take-off. Engine 1 IDG filters were inspected, contamination was noted in both scavenge and charge filters. Engine 1 Fuel Cooled IDG Oil Cooler and the IDG were replaced and aircraft was release back to service. IDG PN: 772292 TSI: 2235 TSN: 44506 IDG Fuel Cooled Oil Cooler PN: 16844-000 TSI: 2235 TSN: 22754|
|BOEING 737 8FE – ATA 2710 AILERON CONTROL SYSTEM – AILERON CONTROL – INCORRECT RIGGED. DR 611953514|
|Pilot reported excessive R wing down deflection when getting airborne. Required approx. 2 units aileron (left) down to remain wings level. Root cause: Aileron control system and flight spoiler system out of rig. Extensive troubleshooting carried out per FIM 27-11 task 816, high aileron trim fault isolation. Aileron system adjustment check confirmed ailerons were out of rig consistent with captains detailed report. igging/adjustment/test of the aileron control system carried out. Flight spoiler system was also tested and adjusted. A test flight was carried out and confirmed no unusual inputs required. Aircraft returned to service.|
|BOEING 717 200 – ATA 2780 LEADING EDGE SLAT CONTROL SYSTEM – SLAT – STUCK. DR 611953530|
|Upon selection of slats, airplane started to roll. Left aileron applied to correct roll. Slats immediately retracted, “Slat Disagree Warning”. Rectifications are continuing.|
|ATR ATR72 212A – ATA 3246 WHEEL/SKI/FLOAT – WHEEL – CRACKED. DR 611953543|
|During dye penetrant Inspection per CMM 32-49-42 Rev 3, a crack indication, emanating from a corrosion pit, thought to be the stress raiser, was found extending partially across the mating face to the outer edge of the tie bolt hole bore in the outer wheel half (P/No A36559-3).|
|BOEING 737 838 – ATA 3520 PASSENGER OXYGEN SYSTEM – OXYGEN SYSTEM – FAILED TEST. DR 611953553|
|During function check of passenger Oxygen system automatic actuation, it fails to operate. Ref AMM 35-22-00-700-801, task T0038141. Cover of J23 box removed, revealed altitude pressure switch electrically disconnected (D2886P).|
|DE HAVILLAND DHC8 315 – ATA 2740 STABILIZER CONTROL SYSTEM – CABLE – CORRODED. DR 611953578|
|During replacement of an Elevator trim servo actuator (rectification of an auto pilot defect), trim actuator servo cables were found to have several areas with individual broken wires/cable wear or chafing out of AMM limits. Cables to be replaced before further flight.|
|BOEING 737 8FE – ATA 5710 WING , MAIN FRAME STRUCTURE – SPAR – CRACKED. DR 611953579|
|On daily inspection, crack (60mm in length) found in wing centre section rear spar vertical press deck web between RBL 40.0 + 45.64. Crack is located in a principal structure element (PSE) of the wing. Repair arranged.|
|BOEING 787 8 – ATA 5730 WING, PLATES/SKIN – ACCESS PANEL – DELAMINATED. DR 611953580|
|RHW fuel tank access Panel 633EB outer skin FWD edge found peeled up. Fuel tank panel replaced.|
|AIRBUS A320 232 – ATA 5322 FUSELAGE INTERNAL MOUNTING STRUCTURE – SUPPORT STRUCTURE – CORRODED. DR 611953582|
|Following an inspection of the rear cargo hold restraint attach points, extensive corrosion has been found on the floor panel support structure between FR56 to FR59 adjacent to STGR38LH and STGR38RH. Cause of corrosion unknown.
Initially, temporary repairs carried out IAW EO-XX issue 2 and followed by permanent repair requirements consisting of replacement of corroded parts.