17 July – 8 August 2018

196

AIRBUS A330 202–ATA 5350 AERODYNAMIC FAIRING–RADOME–CONTAM-WATER. DR 611852255
During initial climb, weather radar system 2 selected, ND radar displayed an area of significant weather in front of the aircraft. The area initially displayed a wide expanse of green with embedded yellow, however the environmental conditions were sky clear. During the turn the radar paint stayed immediately ahead of the aircraft on the ND and over a short time increased in intensity to show areas of red and magenta. The aircraft however remained in clear sky. System 1 was selected with no significant change to the erroneous weather display. Suspected, it was water ingress in composite structure, radome replaced. Engineering investigation in progress.

AIRBUS A320 232–ATA 7321 FUEL CONTROL/TURBINE ENGINES–FMU–LEAKING. DR 611852282
Number 1 ENG FMU was found to be leaking fuel from the electrical plug socket 4000KC-B. FMU was replaced. This is the first unscheduled removal of this component. OEM engaged.

BOEING 737 8FE–ATA 3510 CREW OXYGEN SYSTEM–SHUTOFF VALVE–LEAKING. DR 611852258
During daily inspection, crew oxygen system pressure found 900 PSI. Cylinder serviced per AMM 35-00-XX. Upon installation, it was found that the cylinder was leaking at the shut-off valve. Cylinder removed and replaced.

BOEING 787 8–ATA 2100 AIR CONDITIONING SYSTEM–BLEED AIR–CONTAMINATED. DR 611852288
After take-off, cabin crew reported burning smell of rubber lasting for two minutes. All indications were normal. No further smell reported for remainder of flight. Info noted.

SAAB 340 B–ATA 2730 ELEVATOR CONTROL SYSTEM–trim actuator–SUSPECT FAULTY. DR 611852294
Capt. & FO’s pitch trim controls failed numerous time on finals. Capt. actuated the STBY trim and then re-synced pitch trim. Both sides then worked normally. Relevant maintenance completed. Unable to reproduce defect. LH pitch trim actuator 3CC replaced with serviceable item IAW 27-32-XX as a precautionary measure.

AIRBUS A320 232–ATA 3260 LANDING GEAR POSITION AND WARNING SYSTEM–PROXIMITY SENSOR–Out of Adjustment. DR 611852304
During L/G retraction, ECAM ‘L/G doors not closed’ warning presented. ECAM actions acknowledged. Suspected L/G doors proximity sensors issue as revealed in post-flight report. TSM 32-31-00-810-859A was used for fault isolation, defect not reproduced. Functional tests of the NLG normal extension and retraction carried out, satisfactory. Post rectification, aircraft had operated 18 sectors with nil re-occurrence of this fault.

BAE JETSTREAM 3100 3200–ATA 5751 AILERONS–HINGE–WORN. DR 611852309
RH Aileron hinges have movement. Multiple bushes and bearings on all three hinges required replacement, replaced. Rigging checks carried out, satisfactory.

DE HAVILLAND DHC8 315–ATA 3230 LANDING GEAR RETRACT/EXTENSION SYSTEM–LANDING GEAR–FAILED-RETRACT. DR 611852319
After take-off, when landing gear selected up, all three amber gear door caution lights illuminated and remained on. Red nose gear unsafe light also illuminated and remained on. Emergency landing gear extension carried out. Landing gear showed down and locked. Air turn back conducted to departing base. It was noted that the nose gear ground lock was already extended/engaged. This is suspected to be the cause of the nose gear not retracting post take-off. Precautionary extension and retraction carried out multiple times satisfactory.

FOKKER F28 0100–ATA 2720 RUDDER CONTROL SYSTEM–PRESSURE SWITCH–LEAKING. DR 611852320
During flight, crew encountered #2 hydraulic low quantity alert. ATB initiated to departing base for a safe landing. Leak was emanating from relief hole of active rudder manifold, high pressure switch. Pressure switch was replaced. Fokker Services published Service Experience Digest (SED) number 2722/ 003, ‘High Scrap Rate of the Rudder Active or Standby Manifold Pressure Switches’. Fokker identified switches were predominantly subject to electrical failures, due to fluid ingress, with no details of hydraulic failures. Fokker Services will be contacted for advice, with the intention of forwarding the failed pressure switch for investigation.

BOEING 737 3H6–ATA 7600 ENGINE CONTROLS–Throttle Cable–JAMMED. DR 611852327
Post engine replacement, auto throttle test failed. Subsequent inspection found throttle friction was close to allowable limits. On removing the cable, it was found that the Teflon cover fitted over the cable for protection had deteriorated and broken up into various pieces within the cable channel. Thrust control cable was replaced IAW AMM 76-11-XX. Subsequent testing on the A/T Bit and PLA synchro were satisfactory IAW AMM 22-31-11.

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