PIPER PA31 350–ATA 2731 ELEVATOR TAB CONTROL SYSTEM–CABLE–INCORRECT ROUTED. DR 611751194
Elevator trim cables found to be twisted on each other on cable run below and aft of control pedestal in underfloor area. Elevator trim cable routing corrected.
CESSNA 172 R–ATA 5312 FUSELAGE MAIN, BULKHEAD–FIREWALL–CRACKED. DR 611751205 (photo above)
Crack formed in lower firewall skin. Crack located on L/H side under the middle engine cowl mount doubler. Location FS 0.00, Airplane Zone 123. Crack length approx 4 ½ inches. EO repair carried out.
CESSNA 172 R–ATA 5312 FUSELAGE MAIN, BULKHEAD–FIREWALL–CRACKED. DR 611751216 (photo above)
Crack formed in lower firewall skin. Crack located on L/H side under the middle engine cowl mount doubler. Location FS 0.00, Airplane Zone 123. Crack length approx 2 1/2 inches. Carry out crack repair IAW Structural Repair Manual.
CESSNA R172–ATA 5312 FUSELAGE MAIN, BULKHEAD–FIREWALL–CRACKED. DR 611851273
Crack formed in lower firewall skin. Crack located on L/H side under the middle engine cowl mount doubler. Location FS 0.00, Airplane Zone 123. Crack length approx 4 inches. Battery frame to engine frame angle support bracket found cracked, suspect excess vibration and firewall loading causing damage to the thin firewall skin. Carry out crack repair IAW Structural Repair Manual.
CESSNA 210 R–ATA 3213 MAIN LANDING GEAR STRUT/AXLE/TRUCK–SADDLE–MISSING. DR 611851274 (photo above)
Pilot reported gear down & locked annunciator failed to illuminate. Initial inspection found L/H MLG saddle pad is missing. A new saddle was installed with MLG rigging carried out IAW approved data.
CESSNA 182 P–ATA 2720 RUDDER CONTROL SYSTEM–CABLE–CORRODED. DR 611851305
Cables inspected IAW GEN 87 Am. 1. Pitting corrosion found on rudder cable PN 1260105-109. Cable replaced. Pitting associated with path of safety wiring and probably related to retained water and dust. Cable has accumulated 1475 since installation.
CESSNA 208–ATA 2561 LIFE JACKET–BATTERY PACK–Swollen. DR 611851310 (photo above)
AWB 25-02 regarding life jacket light batteries was received and subsequent inspection performed to two life jackets which were listed in AWB. Life jackets inspected were labelled as ‘Demo’ due to previous inspections revealing defective stitching however our operational aircraft also have life jackets which match the specified EAM part number defined in AWB; and subsequent to this finding will be inspected for similar defects as the two ‘demo’ jackets. The ‘demo’ jackets were still within their ‘serviceable life’ period.
CESSNA 150 M–ATA 2720 RUDDER CONTROL SYSTEM–CABLE–WORN. DR 611851335 (photo above)
Rudder cables found worn with broken strands. Moreover, cable fair lead incorrectly fitted. Cable replacement is required.
CESSNA 206 H–ATA 2701 CONTROL COLUMN SECTION–BEARING–SEIZED. DR 611851343 (photo above)
In flight, pilot observed an issue with the aircraft`s aileron control (unable to attain the desired deflection and that the aileron was unable to move). Air return initiated for a safe landing. During the course of troubleshooting, defect was traced to stiff bearing within block assembly. Block assembly replaced. Inspection task created to inspect block assembly within fleet system of maintenance to prevent further failures.
CESSNA 402 C–ATA 5740 WING, ATTACH FITTINGS–STRAP–NON COMPLIANT. DR 611851393
CASA released AWB 57-016 due potential anomalies in the installation of the Hawker Wing Spar Strap modification for the Cessna 402C aircraft. An inspection discovered four fasteners missing from the RH inboard engine beam. The fasteners were never installed at the time of the modification as no holes have been provided in the structure for them. The modification approval holder has been contacted for further advice.