| AIRCRAFT BELOW 5700kg | ||
| CESSNA 152 – ATA 2750 TRAILING EDGE FLAP CONTROL SYSTEM – MOUNT – bent. DR 611953800 | ||
| Flap Binding on retraction. Root cause: Bent flap roller mount. Corrective action: Flap replaced. |
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| CESSNA 210 M – ATA 3260 LANDING GEAR POSITION AND WARNING SYSTEM – MICROSWITCH – Out of adjustment. DR 611953852 | ||
| Pilot reported no positive landing gear indication light.
Root cause: Nose landing gear micro switch out of rig. Rigging carried out. NLG and MLG down lock mechanisms inspected serviceable. Gear retractions satisfactory. |
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| CESSNA 402 C – ATA 2410 ALTERNATOR-GENERATOR DRIVE SYSTEM – BEARING – FAILED. DR 611953878 | ||
| LH Engine Alternator coupling (PN: 646655) bearing failure in flight. Engineers removed LH alternator and found crankshaft alternator drive gear (PN: 657984) had failed as well with subsequent metal contamination of the engine. Engine, alternator and coupling will be sent to an approved overhaul facility for investigation and report. |
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| CESSNA 402 C – ATA 3220 NOSE/TAIL LANDING GEAR – DRAG BRACE – CRACKED. DR 611953892 | ||
| During scheduled NDT inspection, drag brace found cracked. Drag brace replaced. | ||
| AVIONS PIERRE ROBIN HR100 – ATA 2710 AILERON CONTROL SYSTEM – CABLE – CORRODED. DR 611953900 | ||
| AD/GEN/87 was called for during the Annual Inspection. Cables are getting replaced. | ||
| CESSNA 402 C – ATA 5411 NACELLE/PYLON, FRAME/SPAR/RIB – SPAR STRAP – CRACKED. DR 611953905 | ||
| While carrying out cross beam replacement, cracks were found in the inner layer of both the inboard and outboard engine beam to Fwd spar straps.
Inboard beam has a single crack approximately 7mm in length extending from the relief cut out. The intermediate layer behind it appears unaffected. Outboard beam has 2 cracks approximately 5 and 10mm emanating from the inboard relief cut out and 2 cracks 5mm and 10mm emanating from the outboard relief cut out. The intermediate layer behind this also appears to be damaged. As this is an EO installation the design approval holder has been contacted for advice. |
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| CESSNA 210 M – ATA 5511 HORIZONTAL STABILIZER, SPAR/RIB – SPAR – CRACKED. DR 611953906 | ||
| Whilst performing an inspection of the Horizontal Stabiliser Fwd Spar IAW AD/C210/069 Amdt 2, engineers observed two cracks on the rear face of the FWD horizontal stabiliser spar.
Both cracks are in the rear laminate and originate from the Centre section cut out. |
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| CESSNA 210 L – ATA 5711 WING SPAR – SPAR – CORRODED. DR 611953920 | ||
| Corrosion evident on lower surface of carry thru spar Assy. Suggested cause is the adhesive that is used to attach the foam strip to the lower surface absorbing moisture. Investigation to be carried out IAW Cessna SEL 57-06. | ||
| CESSNA 402 C – ATA 3230 LANDING GEAR RETRACT/EXTENSION SYSTEM – HYDRAULIC LINE – FRACTURED. DR 611953938 | ||
| Hydraulic flow annunciators illuminated in flight. Hyd reservoir depleted. Root cause: Fractured rigid hydraulic pressure line, aft of firewall bulkhead. A new line PN 5100111-71 was installed. |
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