N739DH

Part: ENGINE — VIBRATION · airframe 89,575 hrs · 17,686 cycles

DURING TAKEOFF AS NOSE GEAR LIFTED OFF SIGNIFICANT NOSE GEAR VIBRATION FELT. REMOVED NOSE WHEEL ASSYS IAW B767-300 AMM 32-45-02. PERFORMED WHEEL EXAMINATION IAW B767-300 AMM 32-45-03. NO DEFECT FOUND. PERFORMED INSPECTION/CHECK OF NLG TIRES IAW B767-300 AMM 32-45-04. ALL CHECKS GOOD. REINSTALLED NLG WHEEL ASSYS IAW B767-300 AMM 32-45-02. DURING NOSE/MAIN LANDING RETRACTION, LANDING GEAR DOOR LIGHT STAYED ILLUMINATED FOR EXTENDED PERIOD OF TIME- NO EICAS. PERFORMED OPS CHECK OF NLG RETRACTION IAW AMM 32-34-00 AND PERFORMED OPS TEST OF NLG RETRACTION IAW AMM 32-32-00, ALL CHECKED GOOD, NO DEFECTS NOTED. DURING CLIMB OUT HIGH ENGINE VIB INDICATION. LEFT ENGINE VIB 3.8 RIGHT ENGINE VIB 4.8. ACCOMPLISHED TRIM BALANCE PROCEDURE ON LT AND RT ENGINES IAW AMM 72-31- 00 WITHIN LIMITS, ALL CHECKS GOOD. POSSIBLE BIRD STRIKE DURING TAKEOFF MULTIPLE BIRDS NOTED ON FLIGHT PATH DURING LIFTOFF. PERFORMED CONDITIONAL BIRD STRIKE INSPECTION IAW AMM 05-51-00. NO DEFECT NOTED. PERFORMED VISUAL CONDITIONS INSPECTION IAW AMM 78-00-00. NO MAJOR FINDINGS. NR 1 AND 2 ENGINES OK FOR SERVICE.

Part: CONNECTOR — DIRTY (AC MOTOR) · airframe 89,470 hrs · 17,604 cycles

MASTER MESSAGE: CABIN ALTITUDE MASTER CAUTION MESSAGE: CABIN AUTO INOP STATUS MESSAGE: CABIN ALT AUTO 1 + 2. PERFORMED BITE TEST ON CABIN ALT AUTO 1 IAW FIM 21-31 FAULT TREE 804. OPS CHECK GOOD. INSPECTED, CLEANED AND SECURED ELECTRICAL CONNECTOR ON AC MOTOR 2 IAW AMM 21-31-00, C/W FIM 21-31 FT 803 NO FAULTS AT THIS TIME.

Part: EADI — FAILED (CAPTAIN'S) · airframe 89,434 hrs · 17,570 cycles

CA ADI TURNED BRIGHT, THEN FUZZY, THEN OFF. ACRID BURNING WIRE SMELL ASSOCIATED. REMOVED AND REPLACED CAPT EADI IN ACCORDANCE WITH B767-300 AMM 34-22-03. ALL CHECKS GOOD. PERFORMED SMOKE/FUMES CONDITIONAL INSPECTION IN ACCORDANCE WITH B767-300 AMM 05-51-56. ALL CHECKS GOOD. NO DEFECTS NOTED.

Part: EADI — FAILED (CAPTAIN'S) · airframe 89,390 hrs · 17,536 cycles

ADI INOP LIGHT SMOKE AND FUMES OBSERVED. REMOVED AND REPLACED CAPTAINS EADI IAW B767 AMM 34-22-03 OPS CHECK GOOD. PERFORMED AIRCRAFT SYSTEM OIL SMOKE/FUME CONTAMINATION MAINTENANCE PRACTICES IAW B767 AMM 21-00-21. NO FURTHER DEFECTS NOTED.

Part: EADI — FAILED (CAPTAIN'S) · airframe 88,785 hrs · 16,880 cycles

CAPTAIN ATTITUDE DIRECTIONAL INDICATOR WENT BLANK ON THE ARRIVAL WITH THE SMELL OF ELECTRICAL SMOKE AND A POPPING SOUND. LEFT ATTITUDE DIRECTIONAL INDICATOR CIRCUIT BREAKER POPPED. CHECK WIRES FROM CBC593 THROUGH LEFT ATTITUDE DIRECTIONAL INDICATOR CONNECTION D107 PER B767 WDM 34-22-16 PAGE 8, NO DEFECTS NOTED. TERMINATING SERVICE IAW B767 FIM 34-22-F.T. 804. REMOVED AND REPLACED LEFT ATTITUDE DIRECTIONAL INDICATOR IAW B767 AMM 34-22-03, OPS CHECK NORMAL AT THIS TIME.

Part: SYMBOL GENERATOR — FAILED (CAPTAIN'S) · airframe 88,773 hrs · 16,870 cycles

CAPTAINS SIDE EXPERIENCED ELECTRICAL BURNING SMELL AFTER ELECTRONIC FLIGHT INSTRUMENT SWITCH WAS SELECTED DUE TO POSSIBLE SYMBOL GENERATOR FAILURE. REMOVED AND REPLACED CENTER GENERATOR IAW B767-300 AMM 34-22-01. ALL CHECKS GOOD. PERFORMED AUTOPILOT FLIGHT DIRECTOR SYSTEM TEST IAW B767-300 AMM 22-10-00. ALL CHECKS GOOD. AIRCRAFT REMAINS CAT III.

Part: CIRCUIT BREAKER — FAILED (BUSS TIE) · airframe 88,608 hrs · 16,764 cycles

DECLARED EMERGENCY DURING LANDING, DUE TO LOSS OF LEFT AC BUSS INFLIGHT. REMOVED AND REPLACED LEFT BUSS TIE CIRCUIT BREAKER.

Part: CONTROL VALVE — MALFUNCTIONED (APU) · airframe 88,608 hrs · 16,764 cycles

AT 1800 FT ON FINAL APPROACH INTO CVG, WHEN SELECTING FLAPS 30, THE LEFT AL BUS FAILED. REMOVED AND REPLACED APU SURGE CONTROL VALVE IAW AMM 49-53-01 ALL CHECKS GOOD.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 88,411 hrs · 16,564 cycles

FWD PIT PALLET SUPPORT HAS AREAS OF CORROSION AND POSSIBLE CRACK STA 538 - 595 RBL 38 APPROX.

Part: STRINGER CLIP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

RT MAIN DECK INTERIOR GROUNDING STUD STATION 1285, STRINGER APPROX 12 IS CORRODED (NOTE: CORROSION FOUND TO BE ON STRINGER CLIP)

Part: FILL PORT — CORRODED (LT WING) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

L/W OVERWING FILLPORT HAS EVIDENCE OF CORROSION.

Part: SUPPORT BEAM — CORRODED (TE FLAP) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

RIGHT I/B FLAP, O/B SUPPORT BEAM AFT I/B BOLT HOLE PITTED.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

FWD PIT AT STA 485 RBL APPROX 24" FLOOR SUPPORT HAS EVIDENCE OF CORROSION ON TOP SURFACE.

Part: SUPPORT BEAM — CORRODED (TE FLAP) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

RIGHT INBOARD FLAP, OUTBOARD SUPPORT BEAM, AFT OUTBOARD BOLT HOLE IS PITTED.

Part: STRUCTURE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

FWD PIT AT STA 654 LBL APPROX 48" TOP OF CHORD & UNDERNEATH FLANGE AROUND NUT PLATE HAS EVIDENCE OF CORROSION.

Part: TORQUE BOX — CORRODED (FUSELAGE) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

FORWARD CARGO COMPARTMENT RIGHT HAND TORQUE BOX WEB HAS EVIDENCE OF CORROSION FS 478 TO 495 RBL 40 TO 65.

Part: SHEAR TIE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

FWD PIT AT STA 610 LBL APPROX 1" SHEAR TIE HAS EVIDENCE OF CORROSION.

Part: BULKHEAD WEB — CORRODED (NR 2 PYLON) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

NR 2 PYLON FWD TORQUE BOX WEB CUTOUT FOR HYDRAULIC LINE HAS CORROSION ON AFT SIDE OF HOLE.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 88,411 hrs · 16,564 cycles

PILOTS O/B FWD SEAT TRACK HAS EVIDENCE OF CORROSION ON AFT END OF TRACK. UPON FURTHER INVESTIGATION FOUND TRACK CRACKED, NO CORROSION NOTED.

Part: SKIN PANEL — CORRODED (TE FLAP) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

LEFT INBOARD MAIN FLAP PANEL 555 EB IS CORRODED ON THE AFT EDGE NEAR THE OUTBOARD FITTING.

Part: HINGE FITTING — CRACKED (TE FLAP) · airframe 88,411 hrs · 16,564 cycles

RIGHT INBOARD MAIN FLAP INBOARD HINGE FITTING, OUTBOARD TAB IS CRACKED.

Part: STRINGER CLIP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

EVIDENCE OF CORROSION ON STRINGER CLIP IN MAIN CARGO COMPARTMENT LT SIDE @ APPROX STA 1219 S19 L.

Part: STRINGER CLIP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

CORRODED STRINGER CLIP IN MAIN CARGO COMPARTMENT LT SIDE @ APPROX STA 1153, S12 L.

Part: SKIN — CRACKED (RT WING) · airframe 88,411 hrs · 16,564 cycles

RT WING LWR SKIN AT STA 995 STR R 9.5 HAS 2 CRACKS COMING FROM FASTENERS. END OF CRACKS MARKED.

Part: WEB — CRACKED (LT WING) · airframe 88,411 hrs · 16,564 cycles

LT L/E CAVITY WEB CRACKED ON AFT SIDE NEAR WS 668.2.

Part: STRINGER CLIP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

EVIDENCE OF CORROSION ON STRINGER CLIP IN MAIN CARGO COMPARTMENT LT SIDE @ APPROX STA 1241 S18 L.

Part: SKIN — CORRODED (TE FLAP) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

RIGHT WING INBD FLAP AT INBD HINGE ON AFT SPAR OF FLAP ON LOWER SURFACE, APPROX. 66 INCHES - 78 INCHES OUTBD OF FLAP INBD END, (W. BL 164 - 176) SKIN IS BULGED FROM CORROSION.

Part: STRUCTURE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

EVIDENCE OF CORROSION ON LT OVERWING EMERGENCY EXIT CUTOUT @ APPROX STA 933 S17 L.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

RT MAIN DECK STRINGER TO FRAME CLIP HAS AREA OF CORROSION AT STRINGER 11 AND STATION 1197 + 22.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 88,411 hrs · 16,564 cycles

RT MAIN DECK STATION 1153, STRINGER 10, HAS STRINGER TO FRAME CLIP WITH CORROSION.