N304FL

Part: INLET — CRACKED (LT ENGINE)

DURING INSP OF LT ENGINE INLET, CRACKS WERE FOUND AT THE 9 AND 3 OCLOCK POSITIONS. DURING INSPECTION OF LH ENGINE INLET, CRACKS WERE FOUND AT THE 9 AND 3 OCLOCK POSITIONS. REPAIRED CRACKS ON INLET IN ACCORDANCE WITH ISR 8000027867R1.

Part: ADC — INTERMITTENT (RT) · airframe 238 hrs · 142 cycles

ON DESCENT FROM FL370, CREW RECEIVED (ADC 2 FAIL) CAS MESSAGE MULTIPLE TIMES COMBINED WITH LOSS OF AIRSPEED AND ALTITUDE INFORMATION ON THE RT PFD. CREW DECLARED EMERGENCY AND DIVERTED FOR UNSCHEDULED LANDING. MX REPLACED THE NR 2 (RT) SMART-PROBE.

Part: INLET — CRACKED (LT ENGINE) · airframe 183 hrs · 111 cycles

DURING ACCOMPLISHMENT OF REPETATIVE INLET INSP, REQUIRED BY SB SB505-71-0001, MX FOUND MULTIPLE CRACKS ON THE LT ENG INLET. DURING ACCOMPLISHMENT OF REPETATIVE INLET INSPECTION REQUIRED BY EMBRAER SERVICE BULLETIN SB505-71-0001, MAINTENANCE TECHNICIANS FOUND MULTIPLE CRACKS ON THE LH ENGINE INLET. INLET WAS REPAIRED IN ACCORDANCE WITH EMBRAER ISR 8000027793A.

Part: INLET — CRACKED (RT ENGINE)

DURING ACCOMPLISHMENT OF REPETATIVE INLET INSP, REQUIRED BY SB 505-71-0001, MX FOUND MULTIPLE CRACKS ON THE RT ENGINE INLET. MX REPLACED THE INLET.

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 22,282 hrs · 10,562 cycles

DURING C-7 CHECK, INSPECTION REPORTED L-2 DOOR FRAME MOP SILL CORRODED BETWEEN STA 947.5 AND STA 1006, STR 17L. REPLACED MOP SILL PER SRM 51-10-02 AND 51-40-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 22,282 hrs · 10,562 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON NUT PLATE HOLES ON FLOORBEAM UPPER CAP AT STA 947.5. REPAIRED DAMAGED SECTION OF FLOORBEAM UPPER CAP AT STA 947.5 PER EA B3-53R-10270.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 22,282 hrs · 10,562 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON FLOORBEAM CAP FROM L2 DOOR MOP SILL TO 20 INCHES INBOARD, STA 986.5. REPAIRED FLOORBEAM CAP PER EA B3-53R-10275.

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 22,282 hrs · 10,562 cycles

DURING C-7 CHECK, INSPECTION REPORTED R2 DOOR FRAME MOP SILL CORRODED FROM STA 947.5 TO 1000, STR 17R. REPLACED MOP SILL PER SRM 51-40-02 AND 53-60-15.

Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 18,961 hrs · 8,613 cycles

DURING C 6 CHECK, THE AFT CARGO PIT BULKHEAD LOWER SUPPORT ANGLE WAS FOUND TO BE CORRODED FROM LBL 20 TO RBL 20 ON THE TOP AND BOTTOM SURFACES. MAINTENANCE REMOVED THE AFT CARGO PIT AFT BULKHEAD LOWER SUPPORT ANGLE AND CORROSION WAS FOUND TO BE WITHIN LIMITS, IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-10-2. THE AREA WAS TREATED AND PRIMED IN ACCORDANCE WITH THE REQUIREMENTS OF SOPM 20-41-02 AND INSTALLED IN ACCORDANCE WITH SRM 51-40-02.

Part: STRAP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 18,962 hrs · 8,613 cycles

DURING C 6 CHECK, STRAP UNDER THE AFT CARGO PIT LOWER DOOR SILL WAS FOUND CORRODED AT STA 788 TO STA 791 AND RBL 18. MAINTENANCE REMOVED THE DAMAGED AFT CARGO COMPARTMENT DOOR SILL TAPERED STRAP BETWEEN STA 778 AND 799 AT RBL 18. A NEW PART WAS MATCH DRILLED IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-40-06 AND INSTALLED IN ACCORDANCE WITH SRM 51-40-02.

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 18,962 hrs · 8,613 cycles

DURING C 6 CHECK, THE AFT CARGO COMPARTMENT LOWER DOOR SILL WAS FOUND CORRODED FROM STA 787 TO STA 800, RBL 20. MAINTENANCE REMOVED THE AFT CARGO COMPARTMENT LOWER DOOR SILL BETWEEN STA 787 AND STA 800 AT RBL 20. THE NEW PART WAS MATCH DRILLED IN ACCORDANCE WITH SRM 51-40-06 AND INSTALLED IN ACCORDANCE WITH SRM 51-40-02.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 18,962 hrs · 8,613 cycles

DURING C 6 CHECK, CORROSION WAS FOUND IN THE AFT CARGO PIT, RIGHT HAND, TRANSITION PANEL FROM STA 767 TO 727 AT RBL 21. INSPECTION FOUND THE PANEL TO BE OUT OF LIMITS IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 63-60-53. A NEW PANEL WAS FABRICATED AND INSTALLED BETWEEN STA 727 AND STA 767 AT RBL 21 IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 57-40-02.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 18,962 hrs · 8,613 cycles

DURING C 6 CHECK, THE AFT CARGO PIT FLOOR TRANSITION PANEL, LEFT HAND, WAS FOUND CORRODED BETWEEN STA 727 TO STA 787, LBL 28. REMOVED DAMAGED PANEL AND FABRICATED REPLACEMENT. REPLACEMENT WAS PRIMED, PAINTED AND INSTALLED IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-40-02, 53-60-53, 51-40-05 AND 51-21-02.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 18,962 hrs · 8,613 cycles

DURING C 6 CHECK, CORROSION WAS FOUND IN THE AFT CARGO PIT FLOOR TRANSITION PANEL FROM STA 750 TO 754 AT RBL 20. REMOVED PANEL AND FABRICATED NEW PART IN ACCORDANCE WITH BOEING DRAWING 69-43477. PAINTED AND INSTALLED IN ACCORDANCE WITH SOPM 20-4602.

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 18,962 hrs · 8,613 cycles

DURING C 6 CHECK, CORROSION WAS FOUND ON THE WEB BETWEEN STA 787 AND 794 AT STR 25R. THE WEB WAS REMOVED IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-40-02. CORROSION WAS FOUND TO BE OUT OF LIMITS IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 53-60-15, FIGURE 101, DETAIL V. A NEW PART WAS FABRICATED IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-30-01. TREATED, PRIMED AND PAINTED IN ACCORDANCE WITH THE REQUIREMENTS OF SOPM 20-41-02. INSTALLED IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-40-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 18,962 hrs · 8,613 cycles

DURING C 6 CHECK, INSPECTION FOUND CORROSION IN THE AFT CARGO PIT FLOOR SUPPORT ANGLE AT STATION 750 TO 754. REPAIR WAS PERFOMED BETWEEN STA 767 AND 787 AND FOUND TO BE WITHIN THE LIMITS ESTABLISHED IN SRM 53-60-15, FIGURE 101, DETAIL V. THE PART WAS TREATED, PRIMED AND PAINTED IN ACCORDANCE WITH SOPM 20-41-02

Part: PANEL — CORRODED (FUSELAGE) · airframe 18,962 hrs · 8,613 cycles

DURING C 6 CHECK, INSPECTION FOUND CORROSION ON THE TRANSITION PANEL FROM STA 495 TO STA 500 AT STR 26R. CORROSION WAS REMOVED, IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 53-30-53, FIGURE 101, DETAIL V, BETWEEN STA 495 AND STA 500. AREA WAS TREATED, PRIMED AND PAINTED IN ACCORDANCE WITH THE REQUIREMENTS OF SOPM 20-41-02.

Part: LIGHT — INOPERATIVE (CABIN)

DEN - DURING C-3 CHECK, INSPECTION REPORTED FLOOR PROXIMITY LIGHT PATH STRIP AT ROW 21 INOPERATIVE. MAINTENANCE REPLACED LIGHT STRIP AND CHECKED OK. (M)

Part: TORQUE TUBE — DAMAGED (RUDDER)

DEN - DURING C-3 CHECK, INSPECTION REPORTED BOLT HOLES IN RUDDER CONTROL TORQUE TUBE ASSEMBLY OUT OF LIMITS. MAINTENANCE REPLACED RUDDER TORQUE TUBE AND BEARINGS PER BAC MM 27-21-71. (M)

Part: BEARING — FAILED (NR 2 ENGINE)

BHM - EN ROUTE FROM MCO TO DEN, FLIGHT CREW REPORTED TWO LOUD BANGS FROM NR 2 ENGINE AND EGT ROSE TO 900 DEGREES. THE NR 2 ENGINE WAS SHUTDOWN AND AN EMERGENCY WAS DECLARED. AIRCRAFT WAS DIVERTED TO BHM AND LANDED WITHOUT INCIDENT. FLIGHT CREW OBSERVED METAL IN THE TAILPIPE ON POST FLIGHT WALKAROUND. AIRCRAFT IS CURRENTLY IN BHM AWAITING INSTALLATION OF A REPLACEMENT ENGINE. CAUSE OF DAMAGE WS DUE TO NR 3 BEARING FAILURE. (M)

Part: ENGINE — FAILED (NR 1)

DEN - DURING A-CHECK, INSPECTION REPORTED MAGNETIC CHIP DETECTOR TEST OF FORWARD SUMP DETECTED LARGE PIECES OF METAL IN GEARBOX. MAINTENANCE REPLACED NR 1 ENGINE.

Part: COMPRESSOR — FAILED (NR 1 ENGINE)

EN ROUTE TO SEA, NR 1 ENG SPOOLING DOWN AND NR 1 ENG VIB AT 35,000 FT, SPARKS COMING FROM TAILPIPE. NO FIRE WARN OR O/H IND. NR 1 ENG WAS SHUTDOWN AND NR 1 ENG FIRE BOTTLE WAS DISCHARGED AS A PRECAUTION. DECLARED AN EMERG AND LANDED W/O INCIDENT. NO EMERG EQUIP WAS USED. MX FOUND INTERNAL TURBINE FAILURE AND REPLACED NR 1 ENG. THE FAILURE WAS CONTAINED WITHIN THE ENG, NO EXTERNAL DAMAGE. CAUSE OF DAMAGE WAS DUE TO NR 3 BEARING FAILURE (NO EVIDENCE OF OIL STARVATION). RESULTING BLADE TIP RUB WITH CASE CAUSED EXTENSIVE COMPRESSOR BLADE DAMAGE 6TH STAGE AFT. UNIQUE TO THE 8TH STAGE, 20 BLADES WERE MISSING FROM HUB AND TRAVELED AFT AND ENTERED THE HPT. KEEPER HARDWARD WAS INTACT FOR ALL COMPRESSOR STAGES

Part: SOLENOID — FAILED (LANDING GEAR)

DEN - FLT 55 - AIR TURN BACK. FLIGHT CREW REPORTED LANDING GEAR WOULD NOT RETRACT. AIRCRAFT RETURNED TO DEN AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED LANDING GEAR CONTROL LEVER LOCK SOLENOID. RETRACTED GEAR SEVERAL TIMES AND CHECKED OKAY. TOTAL CYCLES: 1,138. X)