21 April – 20 May

510
Boeing 787 8 - ATA 2421 AC generator-alternator - connector - burnt. DR 611953613
BOEING 787 8 – ATA 2421 AC GENERATOR-ALTERNATOR – CONNECTOR – BURNT. DR 611953613

During removal of VFSG P/N 7001330H03, a severely burned VFSG feeder cable terminal was discovered at the terminal block on the VFSG. No reported VFSG faults prior to engine removal.

Root cause: Terminal attachment nut was found to be partially loose which likely allowed a high resistance to build up and overheating to occur.

Cause of the nut being loose could not be determined however it might have been due to an under torqued condition or loosening due to vibration. The retention torque on the nut could not be tested accurately as the nut had been severely overheated.

BAE BAE146 300 – ATA 2750 TRAILING EDGE FLAP CONTROL SYSTEM – FLAP SYSTEM – STUCK. DR 611953610

Flaps became inoperative at position 18. BITE check carried out on flap ECU, 4 LEDs found annunciated. Initial flap test reset procedure, (MM 27-50-00 Page 104 para D) satisfactory. Flaps operated numerous times across all ranges, found satisfactory. Nil further faults.
AIRBUS A320 232 – ATA 2720 RUDDER CONTROL SYSTEM – Rudder pedals – JAMMED. DR 611953611
During flare, R rudder pedal felt jammed. Extra rudder pedal pressure applied, jam was released, a small audible click noise was heard.

Initial inspection carried out IAW TSM 27-20-00-810-801-A, satisfactory. Additional inspection of the rudder servos have been called up and Airbus has been advised of this event.

AIRBUS A320 232 – ATA 2730 ELEVATOR CONTROL SYSTEM – SERVO CONTROL – SUSPECT FAULTY. DR 611953612
Passing FL350 on climb, aircraft abruptly pitched down approx. 2.5 degrees. A F/CTL ELAC 2 PITCH FAULT ECAM followed. No further issues were noted, flight continued safely to destination.

Rectifications: Elevator servo control , Green servo control valve , ELAC2 replaced . Additional wiring checks were carried out as per TSM 27-93-00-810-866-A with nil findings. Aircraft was released to service.

 
ATR ATR72 212A – ATA 2510 CREW STATION EQUIPMENT SYSTEM – SPRING – BROKEN. DR 611953622
During 750 FH repetitive inspection of the first officer crew seat track lock tension springs, outboard spring was found broken. Vendor SB 063-25-09 and EASA AD 2018-0262 refers. Spring were replaced with post modification parts and aircraft released to service.
DE HAVILLAND DHC8 102 – ATA 2210 AUTOPILOT SYSTEM – PUSHBUTTONSWITCH – STUCK. DR 611953623
Shortly after take-off, unable to achieve selection of any AFCS mode. Fault finding identified LAFCS button found stuck on captains ID-802. LAFCS button cleaned and lubricated. System tested; aircraft returned to service.
AIRBUS A320 232 – ATA 3240 LANDING GEAR BRAKE SYSTEM – HOSE – BURST. DR 611953627
After landing, engine was shutdown, crew noted “PARK BRK LO PR ECAM”. Root cause: Hydraulic hose failure (IPC 32-11-12-04G Item # 30 refers). Hydraulic hose was replaced. Operational checks satisfactory.
AIRBUS A330 202 – ATA 2720 RUDDER CONTROL SYSTEM – HOSE – BURST. DR 611953639
During walk around check, substantial hydraulic fluid leakage observed running down L/H & R/H sides of aft fuselage from the vertical stabiliser / rudder areas. Moreover, Green hydraulic system noted with low quantity. Root cause: Rudder centre servo hydraulic pressure flex line [5458JM] found at fault with failure beneath braid. Failed line replaced The type certificate holder/OEM has been notified. The occurrence is not considered a systemic issue and the corrective action as described is considered adequate.
AIRBUS A321 231 – ATA 3610 PNEUMATIC DISTRIBUTION SYSTEM – BLEED AIR – FAULT MESSAGE. DR 611953652
ATB due AIR ENG 1 + 2 BLEED FAULT.
CBs for BMC 1 and 2 were opened. BMCs were removed to inspect any water ingress. No water ingress was noted. BMCs were refitted. Operational test of BMCs were carried out, no faults were noted.
A check of Airman Web showed no PFR was triggered for this event. With no further reports, 14 sectors completed, event is considered to be an isolated event.
BOEING 737 8FE – ATA 5711 WING SPAR – Pressure deck – CORRODED. DR 611953675
During daily inspection, a crack was found on Centre Wing section rear spar vertical pressure deck web located between RBL40.00 and RBL45.64 approx. 4.5″ long.

During repair of the Crack a 2nd crack was found in deck web approx. 1.2″ Long, located 4″ down from top of wing box, between RBL31.83 and 40.00, 2.5″ outboard of RBL31.83.

Engineering Order EO 737-57-XX was issued for Temporary Repair and Terminating Action.
Subject maintenance and repairs will be completed in due course.

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