N299SK

Part: ENGINE — ODOR (LEFT) · airframe 29,491 hrs · 26,184 cycles

DURING FLIGHT THERE WAS AN OIL BURNING ODOR IN THE COCKPIT WHILE USING BLEED SYSTEM 1 AND BOTH PACK SYSTEMS TURNED ON. THE ODOR WAS ONLY PRESENT IN THE COCKPIT AND CLEARED ON THE GROUND WHILE USING THE APU AS A BLEED SOURCE. LANDED WITHOUT INCIDENT. MX REPLACED THE NR 1 ENGINE. OPS CHECKED GOOD WITH NO FURTHER DEFECTS OR ODORS REPORTED.

Part: UNKNOWN — ODOR (CABIN) · airframe 29,489 hrs · 26,180 cycles

DURING ALL PHASES OF FLIGHT, A SLIGHT OIL BURNING ODOR WAS PRESENT. MX RAN BOTH ENGINES WITH THE ENGINE BLEED AND PACK SYS TURNED ON. NO ODORS OR DEFECTS WERE NOTED AND ACFT RETURNED TO SERVICE.

Part: BULB — INOPERATIVE (ZONE 100) · airframe 29,294 hrs · 25,937 cycles

DURING INSPECTION, THE OVERHEAD COCKPIT EMERGENCY LIGHT WAS FOUND TO BE INOPERATIVE. MX REPLACED THE COCKPIT EMERGENCY LIGHT BULB. OPS CHECKS WERE GOOD WITH NO FURTHER DEFECTS NOTED.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, A TOOLING MARK ON THE INTERIOR BELLY SKIN WAS FOUND ADJACENT TO STRINGER 21L AND BETWEEN FRAMES 10 AND 11. THE SKIN WAS REPAIRED IN ACCORDANCE WITH ETD 2013-145-008436.

Part: SUPPORT — DAMAGED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, A MISDRILLED RIVET HOLE ON THE RIGHT CONTROL CABLE QUADRANT SUPPORT. THE SUPPORT BRACKETS AND QUADRANT SUPPORT WERE REPLACED IN ACCORDANCE WITH SRM 51-40-02 AND 51-20-03.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, AN ELONGATED RIVET HOLE WAS FOUND ON FRAME 12 BETWEEN STRINGERS 21R AND 20R. THE FRAME WAS REPAIRED IN ACCORDANCE WITH ETD 2013-145-008257.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, CORROSION AND CRACKS WERE FOUND ON THE FLOORBOARD SUPPORT FLANGE OF THE LEFT OMEGA BEAM BETWEEN FRAME 24 AND FRAME 25. THE OMEGA BEAM WAS REPAIRED IN ACCORDANCE WITH SRM 53-00-10.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, CORROSION WAS FOUND ON STRINGER 21L BETWEEN FRAMES 13 AND 9. THE STRINGER WAS REPLACED IN ACCORDANCE WITH SRM 51-40-02.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, CORROSION WAS FOUND IN THE RIGHT AILERON QUADRANT SUPPORT WEB AT FRAME 12 AND 13 AND STRINGERS 20R AND 21R. THE RIGHT QUADRANT SUPPORT WAS REPAIRED IN ACCORDANCE WITH SRM 51-40-02.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, CORROSION WAS FOUND IN THE LEFT AILERON QUADRANT SUPPORT WEB AT FRAMES 12-13 AND STRINGERS 20L-21L. THE QUADRANT SUPPORT WAS REPLACED IN ACCORDANCE WITH SRM 51-40-02.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, CORROSION WAS FOUND ON STRINGER 21R BETWEEN FRAMES 13 AND 9. THE STRINGER WAS REPLACED IAW SRM 51-40-02.

Part: FITTING — CORRODED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, CORROSION WAS FOUND ON THE SHEAR CLIP AT FRAME 13 BETWEEN STRINGERS 21L AND 20L. THE SHEAR CLIP WAS REPLACED IN ACCORDANCE WITH SRM 51-40-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, CORROSION WAS FOUND ON THE CENTER OMEGA AT THE CARBON CROSS MEMBER FRAME 27. THE OMEGA BEAM WAS REPAIRED IN ACCORDANCE WITH SRM 53-00-10.

Part: BRACKET — CRACKED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, A CRACK WAS FOUND IN THE BRACKET BETWEEN FRAME 64 AND FRAME 65 AT STRINGER 5L. THE BRACKET WAS REPLACED IN ACCORDANCE WITH SRM 51-40-02, 51-30-01, AND 53-31-02.

Part: FITTING — CRACKED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, A CRACK WAS FOUND ON THE SHEAR CLIP AT FRAME 73 BETWEEN STRINGER 8L AND 9L. THE SHEAR CLIP WAS REPLACED IN ACCORDANCE WITH SRM 51-40-02.

Part: FITTING — CRACKED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, A CRACK WAS FOUND ON THE SHEAR CLIP AT FRAME 73 BETWEEN STRINGER 8R AND 9R. THE SHEAR CLIP WAS REPLACED IN ACCORDANCE WITH SRM 51-40-02.

Part: FITTING — CRACKED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, A CRACK WAS FOUND ON THE SHEAR CLIP AT FRAME 65 BETWEEN STRINGERS 7L AND 9L. THE SHEAR CLIP WAS REPLACED IN ACCORDANCE WITH SRM 51-40-02 AND 53-31-04.

Part: FITTING — CRACKED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, A CRACK WAS FOUND ON THE SHEAR CLIP ON FRAME 66 BETWEEN STRINGERS 6L AND 7L. THE SHEAR CLIP WAS REPLACED IN ACCORDANCE WITH SRM 51-40-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, CORROSION WAS FOUND AT THE SCREW HOLE ON THE CENTER OMEGA LEFT SIDE BETWEEN FRAMES 24 AND 25. THE CENTER OMEGA BEAM WAS REPAIRED IN ACCORDANCE WITH ETD 2013-145-008055.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 29,034 hrs · 25,560 cycles

DURING INSPECTION, CORROSION WAS FOUND ON THE REPAIR DOUBLER LEFT OMEGA FRAME 20. THE DOUBLER WAS REPLACED IN ACCORDANCE WITH SRM 53-00-10.

Part: SELECTOR SWITCH — FAULTY (BLEED AIR SYS) · airframe 27,064 hrs · 22,890 cycles

CREW REPORTED, RECEIVED A BLEED 2 VALVE CLOSED MESSAGE IN FLIGHT. THE CREW FOLLOWED THE QUICK-REFERENCE HANDBOOK BUT THE VALVE WOULD NOT INDICATE OPEN. THE AIRCRAFT RETURNED TO FIELD AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE BLEED 2 PUSHBUTTON SWITCH. OPERATIONAL CHECKS WERE GOOD WITH NO FURTHER DEFECTS NOTED.

Part: ENGINE — MAKING METAL (NR 2) · airframe 21,304 hrs · 15,796 cycles

FLIGHT 5356, JAX TO STL. ON DESCENT INTO STL, THE CREW HEARD A THUMP FROM THE REAR OF THE AIRCRAFT AS THRUST WAS DECREASED TO FLIGHT IDLE. A SHARP SPIKE IN E2 EGT WAS FOLLOWED BY AN E2 OUT MESSAGE ON EICAS. THE E2 OUT CHECKLIST WAS FOLLOWED ALONG WITH THE PRECAUTIONARY ENGINE SHUT-DOWN CHECK. THE AIRCRAFT THEN LANDED AT STL WITHOUT INCIDENT. MAINTENANCE INSPECTED THE ENGINE AND FOUND METAL ON THE CHIP DETECTOR FOR THE CENTER BEARING. THE ENGINE WAS THEN CHANGED AND NO FURTHER DEFECTS WERE NOTED.

Part: SMOKE DETECTOR — FAULTY (LAVATORY) · airframe 20,924 hrs · 15,510 cycles

DURING CLIMB OUT, THE CREW RECEIVED A LAV SMOKE WARNING MESSAGE ON THE EICAS DISPLAY. THIS WAS ACCOMPANIED BY A HAZE OR SMOKE WITH CONDENSATION COMING FROM THE LAVATORY AREA AND THE PACKS BY A DEAD HEADING CREW MEMBER. THE CREW RETURNED TO DEPARTURE AND DECLARED AN EMERGENCY AND PROCEEDED TO LAND WITHOUT INCIDENT. MX PERSONNEL ASSESSED THE ACFT AND REPLACED THE LAVATORY SMOKE DETECTOR. ALL OPS CHECKS PROVED SATISFACTORY AND NO OTHER ACTIONS WERE REQUIRED.

Part: LINE — LOOSE (NR 2 ENGINE OIL) · airframe 19,756 hrs · 14,660 cycles

DURING CRUISE, THE FLIGHT CREW NOTICED AN OIL BURN RATE OF (2) QUARTS PER HOUR AND THE OIL QUANTITY OF E2 HAD DROPPED BELOW 6 QTS. THE FLIGHT DIVERTED IN ORDER TO HAVE ENOUGH OIL TO CONTINUE TO OPERATE THE ENGINE UNTIL LANDING. THE AIRCRAFT LANDED WITHOUT INCIDENT. MX FOUND THE OIL LINE FROM THE SCAVENGE PUMP TO THE OIL TANK LOOSE AND LEAKING. THE LINE WAS SECURED, THE ENGINE SERVICED WITH OIL, AND THE ENGINE WAS RUN WITH NO OTHER LEAKS NOTED.

Part: WARNING LIGHT — ACTIVATED (AILERON CONTROL) · airframe 9,715 hrs · 7,819 cycles

DURING CLIMB AT FL210, RECEIVED "AILERON SYS 1 FAIL" EICAS MESSAGE. LEVELED OFF AT FL230 AND TOLD ATC TO STAND BY. FOLLOWED QRH AND TURNED OFF AILERON SYSTEM 1 AND SLOWED TO 250 KIAS. EMERGENCY DECLARED WITH ATC AND F/A PREPARED CABIN FOR EMERGENCY LANDING. LANDED WITHOUT FURTHER INCIDENT. MX TROUBLESHOT ACFT AND COULD NOT DUPLICATE FAULT. OPS CHECK GOOD IAW EMB AMM.