SDR 510023944 | Gulfstream 500S Wing miscellaneous structure—wing strap cracked. During AD/AC/93 Inspection stage 1, R/H lower wing strap found with 3 cracks, as confirmed by FPI as well as eddy current. Requirement 2 of AD/AC/93 was then carried out with nil defects found. During AD/AC/93 requirement 3, R/H upper frame at F.S. 100.00 was found cracked , as confirmed by visual inspection. Confirmation by NDT not required. P/No: 1700368. TSN: 26437 hours
SDR 510023941 | Beech 76 Landing gear actuator—cylinder separated. During flight, pilot observed some mechanical issue with the under carriage . After verifying gear down through fly by inspection , safe landing was made. During ground checks it was learned that NLG actuating cylinder has separated causing the pressure to be released from the system thus causing the gear to gravity extend. Service data search indicated failed component has good reliability. Maintenance removed the Actuator and after inspection advised that the Cylinder failure was a clean break with no obvious pre-existing defect. A new Actuator was fitted. Gear swings carried out with nil defects and the aircraft returned to service. P/No: A2178A.
SDR 510023941 | Beech 76 Landing gear actuator—cylinder separated. During flight, pilot observed some mechanical issue with the under carriage . After verifying gear down through fly by inspection , safe landing was made. During ground checks it was learned that NLG actuating cylinder has separated causing the pressure to be released from the system thus causing the gear to gravity extend. Service data search indicated failed component has good reliability. Maintenance removed the Actuator and after inspection advised that the Cylinder failure was a clean break with no obvious pre-existing defect. A new Actuator was fitted. Gear swings carried out with nil defects and the aircraft returned to service. P/No: A2178A.
SDR 510023829 | Agusta Westland AW139 Fuselage plates/skin—skin corroded. During inspections, level 2/3 corrosion found behind upper sliding door rail. OEM notified and repair scheme requested. Frequency of repeat inspections increased targeting weak areas. P/No: NA. TSN: 2157 hours TSO: 2157 hours
SDR 510023891 | Cessna 441 Wing structure—wing damaged. Bird strike caused damage to the LH outer wing. P/No: 57226011. TSN: 6683 hours TSO: 6683 hours
SDR 510023883 | Eurocopter EC130B4 Rotorcraft tail boom—stiffener cracked. Structural member was discovered cracked beyond serviceable limits during scheduled maintenance. Five similar defect reported. P/No: 350A23404323. TSN: 4208 hours/17347 cycles/16202 landings
SDR 510023876 | Bombardier DHC8-202 Passenger compartment lighting—lamp holder burnt. During pre flight checks, crew reported burning smell in cabin and around the radar console. Smell was traced to X2 burnt cabin sidewall fluoro tube holders. Affected tubes removed from holders and MEL applied. During the course of rectifications, suspect lamp holders were replaced. One was found badly burnt where as the other was cracked. System tested serviceable. P/No: BV033021148BV033001248.
SDR 510023849 | Lycoming IO540AE1A5 Fuel control/reciprocating engines—rod end separated. Throttle forward rod end at FCU found separated. Removal of the cover revealed that the swage had failed. The R44 IPC shows an A141-17 large area washer, found not installed. Other R44 II aircraft of a similar age also did not have this washer installed. Installation of this washer would have prevented a complete disconnection of the rod after the failure. OEM notified. P/No: A1273.
SDR 510023840 | Lycoming LTS101700D2 Engine (turbine/turboprop)—idler gear damaged. Torque idler gear lock nuts found damaged during engine disassembly. Three of the eight nuts found damaged with fifteen segments broken off. P/No: 408116304. TSN: 8879 hours TSO: 722 hours
SDR 510023829 | Agusta Westland AW139 Fuselage plates/skin—skin corroded. During inspections, level 2/3 corrosion found behind upper sliding door rail. OEM notified and repair scheme requested. Frequency of repeat inspections increased targeting weak areas. P/No: NA. TSN: 2157 hours TSO: 2157 hours
SDR 510023811 | Gippsland Aeronautics GA8 Main landing gear strut/axle/truck—axle cracked. While doing an 100 hourly inspection of undercarriage axle assemblies, a crack was noticed in the welded transition area. Paint was removed and with the help of 10X magnifying glass, cracks on both LH and RH axle assemblies were noticed. Dye penetrant inspection confirmed the flaw. Four similar defects reported. P/No: GA8321023011. TSN: 8628 hours
SDR 510023811 | Gippsland Aeronautics GA8 Main landing gear strut/axle/truck—axle cracked. While doing an 100 hourly inspection of undercarriage axle assemblies, a crack was noticed in the welded transition area. Paint was removed and with the help of 10X magnifying glass, cracks on both LH and RH axle assemblies were noticed. Dye penetrant inspection confirmed the flaw. Four similar defects reported. P/No: GA8321023011. TSN: 8628 hours
SDR 510023810 | Gippsland Aeronautics GA8 Horizontal stabilizer spar/rib—stabilizer cracked. During inspection against mandatory service bulletin SB-GA8-2002-02, crack found in rear spar of horizontal stabilizer. Rectification carried out IAW mandatory service bulletin SB-GA8-2009-59. P/No: GA8551011011.
SDR 510023794 | Bell 429 Miscellaneous hardware—block melted. Engine oil cooler pipe holding clamp block found melted, probably from heated pipe. This resulted in chaffing damage to the pipe itself. Necessary rectifications planned. P/No: 429365230101. TSN: 2154 hours.
SDR 510023793 | VICTA 115 Wing spar corroded. While the wing was removed for AD/VAT/28 compliance, corrosion was discovered in the main spar web at the L/H forward wing attachment point.This area is not specifically mentioned for inspection for corrosion in AD. Inspection is only possible after removing the fuel tank.
SDR 510023773 | Diamond DA40 Autopilot system—clamp cracked. Aileron and elevator autopilot servo cable clamps found cracked (TTIS 42 hours/ 11 months) during first schedule inspection. No related PIREP defect. One similar defect reported P/No: D4122131054. TSN: 42 hours/11 months.
SDR 510023766 | Champion Spark Plug Co 4373 distributor gear failed. During an engine run, when magneto (4373) was selected, engine ran rough and backfired. The magneto was replaced with a serviceable unit and ground run serviceable. Within the suspect magneto, evidence of burning was found around the distributor assembly. Going forward, distributor and gear assembly was removed and opened for inspection. Inside the cap, was evidence of burning and copper deposits. The distributor gear (K3008) was found to have a loose and damaged finger that showed signs of electrical burning. The gear also had signs of burning. The loose finger combined with the carbon-copper deposits in the cap would have cause the HT to randomly track causing the rough running engine and back firing.The magneto will have a new distributor and gear assembly fitted. The problem with the distributor gears is known with Lycoming SB622 and Slick SB1-15 addressing the issue. P/No: K3008. TSN: 658 hours TSO: 658 hours
SDR 510023756 | Cessna 172P Crew station equipment system—repair kit incorrect fit. Secondary seat stop anchor point incorrectly installed with hole drilled to inaccurate dimensions. P/No: SK210174AINSTALLATION J.
SDR 510023724 | Gulfstream 690A Electrical power wiring—wire loose wiring. While undergoing major avionics upgrade, following discrepancies were observed. 1. CB’s terminals stripped of thread and blue tack used to secure screws. 2. CB panel dangerously wired (over time) with some wiring at loose ends and looms not secured. 3. Instrument panel as above – looms not secured and wiring found with loose ends and not secured. All wiring repaired and CB’s replaced.
SDR 510023724 | Gulfstream 690A Electrical power wiring—wire loose wiring. While undergoing major avionics upgrade, following discrepancies were observed. 1. CB’s terminals stripped of thread and blue tack used to secure screws. 2. CB panel dangerously wired (over time) with some wiring at loose ends and looms not secured. 3. Instrument panel as above – looms not secured and wiring found with loose ends and not secured. All wiring repaired and CB’s replaced.
SDR 510023702 | Saab SF340B Power lever—condition lever cracked. During start, when moving LH condition lever to the start gate detent, upper part of the lever separated from the lower half. A control quadrant replacement was carried out. P/No: 64198.
SDR 510023693 | Bombardier BD7001A10 Fuel wiring—cartridge broken. LH DC auxiliary fuel pump found with broken connector pin. Pin was found stuck in socket with arcing marks. P/No: F61003. TSN: 5800 hours/2234 cycles.
SDR 510023693 | Bombardier BD7001A10 Fuel wiring—cartridge broken. LH DC auxiliary fuel pump found with broken connector pin. Pin was found stuck in socket with arcing marks. P/No: F61003. TSN: 5800 hours/2234 cycles.
SDR 510023685 | Embraer EMB-500 Landing gear system—bracket cracked. Bracket found cracked during routine inspection. P/No: 23102111001. TSN: 3688 hours.
SDR 510023678 | Fokker F28 MK0100 Wing control surfaces—wing box corroded. During base checks, out of limit corrosion was found on the upper trailing edge shroud adjacent to #2 lift dumper. OEM technical services contacted.