BOEING 787 8 – ATA 2497 ELECTRICAL POWER WIRING – HARNESS – CHAFED WIRING. DR 611749683
During routine inspection on #2 engine during check C, following discrepancies were observed: 1. Chafing and possible arcing damage noted between VFSG power feeder (Red phase) harnesses and clamp / bracket hardware. 2. VFSG R2 power feeder harness block bracket at approximately 8 o’clock location has contacted adjacent block bracket on the R1 power feeder harness.
AIRBUS A320 232 – ATA 5730 WING, PLATES/SKIN – SKIN – CORRODED. DR 611749686
During inspection, corrosion damages were found outside SRM limit on bottom skin panel 1 & 2 lower surface, between Rib 6 – 7 at Stringer 8 on the RH wing. Affected fasteners were removed; corrosion damages were eliminated by smooth blend out. NDT inspections performed with nil findings and surface protection restored as per the Airbus Technical Disposition.
BOEING 787 8 – ATA 3242 BRAKE – PLUG – BURNT. DR 611749694
Flight was cancelled due to heat damage within the Brake Assembly #7 connector. Upon removal of harness, pins on brake assembly were found with ends burnt off.
AIRBUS A320 232 – ATA 2797 FLIGHT CONTROLS WIRING – WTB – Wire damaged. DR 611749697
Intermittent fault of slat wing tip brake system reported. After troubleshooting with extensive wiring checks, a damaged wire part no EN2267-008A006P was identified in the vicinity of the RH No 4 spoiler actuator. The wire was found partially cut through, connection was made through only a few strands and due to corrosion, these strands finally failed leaving an intermittent contact. Wire replaced, all functional checks satisfactory aircraft declared serviceable and returned to service.
BOEING 717 200 – ATA 2230 AUTOTHROTTLE SYSTEM – Throttle Module – FAULTY. DR 611749704
R/H throttle frequently non responsive or slow to respond to ATS commands . This could result in asymmetric condition and “CONF ENG OUT” fault. No faults shown in FCC #1 & #2, EEC #1 & #2. Throttle Control Module RTS carried out IAW AMM 22-31-XX. Throttle Module replaced due previous history of #2 AP disengagements. Later on, unit declared FF with the vendor. It was repaired and returned.
AIRBUS A320 232 – ATA 2797 FLIGHT CONTROLS WIRING – WIRE – DAMAGED. DR 611749723
Intermittent fault of flap wing tip brake reported. SFCC’s were swapped, WTB replaced, however intermittent fault remained. During detailed wiring checks, a damaged wire identification 2751-4531 PN EN2267-008A006P was identified. The wire was found partially cut through; connection was made through only a few strands. Due to corrosion, these strands finally failed leaving an intermittent contact. Wire replaced, defect cleared.
AIRBUS A321 231 – ATA 5730 WING, PLATES/SKIN – Skin panel – CORRODED. DR 611749736
During heavy check, corrosion found on top skin panel 2 lower surface between rib 6-8 adjacent to the outer jack rib between the trailing edge overhang and at the wing false rear spar attachment on the right hand wing. Major repair performed as per TD/XX issue X.
AIRBUS A380 842 – ATA 2565 ESCAPE SLIDE – SLIDERAFT – FAILED TO DEPLOY. DR 611749738
With all pre-testing carried out normal, slide failed to deploy and appeared caught up on door. Slide required some assistance to correctly fall out by the use of pressure applied by foot on the slide. Upon falling out and hanging in the correct position, the manual deploy button was used and the slide inflated correctly.
FOKKER F27 50 – ATA 2520 PASSENGER STATION EQUIPMENT SYSTEM – CROSS MEMBER – CRACKED. DR 611749741
Whilst carrying out scheduled AD inspection of the passenger seats, engineering staff identified that the central cross-member of the RH passenger seat assembly at R9 had fractured. Whilst carrying out scheduled AD inspection of the passenger seats, engineering staff identified that the central cross-member of the RH passenger seat assembly at R9 had fractured. Seat assembly was replaced. Repetitive inspection already scheduled in the AMP.
ATR ATR72 212A – ATA 2420 AC (ALTERNATING CURRENT) GENERATION SYSTEM – INVERTER – FAILED. DR 611749756
In flight, flight crew declared emergency due to smoke in the cockpit with multiple failures and associated “ELEC SMOKE WARNING” and “#1 INVERTER FAIL” indications. Crew donned Oxygen masks and a diversion was made. Defect was traced to failed static inverter. Static inverter was replaced and tested serviceable. Removed inverter FF with quality escape with C311 and C60X capacitors be the established root cause. In service units will be modified to Amd E status with testing and burn-in screening of both capacitors C311 and C60X at shop visit.
BOEING 737 8FE – ATA 2760 DRAG CONTROL SYSTEM – MICROSWITCH – Out of Adjustment. DR 611749759
Flight crew reported ‘TAKE-OFF CONFIG’ warning during take-off roll at about 92 Knots. RTO, aircraft returned to the gate with no further issues. Troubleshooting was unable to reproduce fault. However, maintenance message was found recorded for the ‘Speed Brake Lever Handle Up’. Defect traced to a speed brake lever micro switch out of adjustment. High Energy inspection carried out IAW AMM 05-51-XX with nil defects noted. Micro Switch adjusted IAW AMM 31-51-03 and tests satisfactory.
AIRBUS A320 232 – ATA 3250 LANDING GEAR STEERING SYSTEM – Electrovalve – FAULTY. DR 611749764
During descent, crew noticed Nose Wheel Steering Fault ECAM message. Referring to QRH procedures, possibility of NWS reset on ground only, crew decided to divert to nearby airport. After safe landing, successful reset was made. The fault re-appeared shortly and the aircraft veered left. The aircraft was shut down and towed to the gate without any incident. Engineering determined steering Electro-Hydraulic Module needed replacement. This component was replaced, all necessary checks conducted, and the aircraft returned to normal service.
BOEING 737 81D – ATA 2520 PASSENGER STATION EQUIPMENT SYSTEM – WATER BOILER – Defective. DR 611749778
Cabin crew reported burning smell from the AFT galley. Troubleshooting traced smell to the AFT Galley water boilers. In addition, wiring loom rear of water boilers showing signs of overheating at terminal strip TB3. Power isolated and MEL 25-32-XX applied for water boilers being inoperative. Aircraft released to service.
SAAB 340 A – ATA 2611 SMOKE DETECTION SYSTEM – SMOKE DETECTOR – Precautionary replacement. DR 611749779
At approximately 90 to 100 knots, Master Warning “Avionics Smoke” light on. Rejected take-off with zero brake application. At GND Idle, light extinguished/ cancel during de acceleration. Engineering was not able to find any evidence of smoke or fire. Detector was replaced as per AMM 26.13.05.XX. Smoke detector replaced and aircraft returned to service.
AIRBUS A330 303 – ATA 2900 HYDRAULIC POWER SYSTEM – HYDRAULIC LINE – LEAKING. DR 611749781
Blue hydraulic system gradually decreased in quantity on final approach with ECAM message ‘Hyd B sys LP PR’. ECAM actions carried out. Hyd leak was found in line having PN F3241083100200. Same replaced IAW AMM. No current reliability concerns for this part at present.
AIRBUS A330 303 – ATA 2720 RUDDER CONTROL SYSTEM – FCPC – SUSPECT FAULTY. DR 611749796
Lateral oscillations clearly evident on climb approximately from FL 250 until cruise at FL 320 @ 305 IAS. Also felt in cruise, descent at 260 k IAS but at lesser frequency. Oscillation check of ailerons, rudder, FCSC1 rudder servo loop test carried out per AMM. Visual inspection of rudder input controls, fuselage, wings and stabilisers, rudder and vertical fin as well as operational test of rudder trim actuation, completed. AMM 27-20-00-810-802-X rudder oscillation test states, if no oscillations were present during test then FCPC1 should be replaced. FCPC 1 replaced.
BOEING 717 200 – ATA 3241 BRAKE ANTISKID SECTION – ANTI SKID UNIT – FAILED. DR 611749802
On landing, level 2 alert “Antiskid L fail”. After parking on bay, #2 main wheel deflated. Later on, LH Inboard main wheel brake assembly found jammed with brake pressure off. LH O/B and LH I/B main wheels and brake assemblies replaced. Anti-skid system check and high energy stop inspection completed.
BOMBARDIER CL600 2B16 – ATA 2130 PRESSURE CONTROL SYSTEM – PRESSURISATION – FAULTY. DR 611749806
On closing aircraft door, cabin began pressurising, attempted to slow rate failed, manual control selected & cabin alt began to rise slowly. Packs were selected to OFF. Cabin alt reached less than -6000ft. EICAS CFAM FAIL message displayed. AUTOPRESS EICAS message displayed. Fault light on Press control panel ON. Bubble noted in the paint work on the LH just below the left AOA vane, cracks of paint work noted around the outside of the observer window (STC introduced). STC holder and OEM notified. CPAM, cabin pressure controller and cabin altitude indicator replaced. Functional and operational tests as called out in OEM instructions completed. Nil further defects. Aircraft RTS.
AIRBUS A320 232 – ATA 2730 ELEVATOR CONTROL SYSTEM – ELAC – FAULTY. DR 611749807
Crew reported airframe vibration accompanied with small sharp nose pitch changes along with LH elevator flutter on SD page. Engineering inspected elevator and determined that oscillations were well below AMM limits. Additional troubleshooting identified door L1 rub strips hanging loose and subsequently replaced. Aircraft was declared serviceable. On the next day, flight crew reported the same event and circumstances. Troubleshooting resulted in replacement of ELAC 2. Aircraft declared serviceable.
EMBRAER ERJ190100 – ATA 5320 FUSELAGE, MISCELLANEOUS STRUCTURE – FRAME – CORRODED. DR 611749816
During Heavy Maintenance Check, Corrosion Level 2 was found in the various locations classified as Primary Structure per the Embraer SRM.
AIRBUS A321 231 – ATA 5730 WING, PLATES/SKIN – Skin panel – CORRODED. DR 611749823
Corrosion was found on RH W top skin upper surface at multiple locations along panels. Corrosion areas were repaired IAW TD/XX/2017. Repairs classified as major cat B.
ATR ATR72 212A – ATA 3246 WHEEL/SKI/FLOAT – WHEEL – CRACKED. DR 611749848
Crack indication found during Eddy Current Inspection and confirmed via Dye Penetrant Inspection.
BOEING 737 8FE – ATA 2100 AIR CONDITIONING SYSTEM – BLEED AIR – CONTAMINATED. DR 611749852
After landing, when APU started, electrical burning smell was detected in the flight deck and cabin. Smell dissipated when the APU air was turned off. FIM 21-00 Task 806 carried out, unable to reproduce any odours using all combinations of Engine/APU bleed sources with L and R packs. Re-circulation fans checked individually with nil faults. Cabin equipment checked ok. Aircraft supplied with power from all generators without any fault. There is no history and there have been no repetitive occurrences. Considering it a transitory condition, event monitoring will continue.
AIRBUS A320 232 – ATA 3610 PNEUMATIC DISTRIBUTION SYSTEM – SENSE LINE – LEAKING. DR 611749857
On climb out, #1 bleed valve fault presented. Due #2 bleed already on MEL, an air return was planned and conducted. Rectification on #1 bleed found leaking PRV sense line, same replaced. Troubleshooting on Eng 2 HPV found nil faults, however as a precaution, HP control solenoid was replaced and operational test found satisfactory. Aircraft declared serviceable.
AIRBUS A320 232 – ATA 3500 OXYGEN SYSTEM – OXYGEN GENERATOR – safety pin installed. DR 611749858
Whilst carrying out SB 117042-35-001 G1 Rev004 (oxygen generator replacement), oxygen generator at location XX was found to still have the safety pin installed without safety streamer.
EMBRAER ERJ190100 – ATA 2150 CABIN COOLING SYSTEM – AIRCYCLE MACHINE – FAILED. DR 611749866
During climb out, Flight Crew reported heavy fumes and a light haze in the flight deck and cabin. Air Turn back conducted and, before landing, ‘Pack#2 Fail’ message annunciated. Troubleshooting confirmed, pack #2 Air Cycle Machine (ACM) had failed. MEL 21-51-XX applied and aircraft released to service with the Air Conditioning pack #2 inoperative. ACM replacement is underway. Investigation initiated.
BOEING 737 7FE – ATA 2100 AIR CONDITIONING SYSTEM – BLEED AIR – CONTAMINATED. DR 611749883
Fight crew reported fumes, oily smell through gasper vents on flight deck for about 1 minute. Also, FWD crew noticed haze from row 4 and forward. Gas was smelled near row 21-22 later in cruise, but nothing observed in flight deck during this time. No previous history and there have been no repetitive occurrences. Considered as transitory. Event monitoring to continue.
ATR ATR72 212A – ATA 3444 GROUND PROXIMITY SYSTEM – TAWS UNIT – transitory condition. DR 611749884
On climb out, spurious EGPWS alert was received. Possibly a transitory condition. TAWS extended self-test c/out with no faults as per local task card 34-XX.
AIRBUS A380 842 – ATA 2520 PASSENGER STATION EQUIPMENT SYSTEM – USB Port – BURNT. DR 611749893
Smoke emanating from USB socket as reported during pre-flight cabin preparation. Furthermore, remains of lead cleaned by cabin crew. Seat inspected by engineer and remaining FOD removed. Seat electrically deactivated and made non saleable by applying MEL.