N102DA

Part: YAW DAMPER — MALFUNCTIONED (RUDDER) · airframe 69,291 hrs · 33,800 cycles

UNCOMMANDED RUDDER INPUT AT ROTATION, THOROUGHLY CHECKED SYSTEM. UNABLE TO DUPLICATE OR FIND FAULT.

Part: SHUTOFF VALVE — STICKS (BLEED AIR SYS) · airframe 68,811 hrs · 33,587 cycles

WHEN POWER INITIALLY REDUCED TO START INITIAL DESCENT A SMELL DEVELOPED IN THE AIRCRAFT. REPLACED NR 1 HPSOV.

Part: LINE — LEAKING (RT ENGINE) · airframe 68,178 hrs · 33,311 cycles

RT HYD SYS FAILURE. RT HYD SYS QTY DROPPED QUICKLY SUGGESTING A LEAK. FOUND RT ENGINE PRESSURE LINE CHAFED THROUGH, REPLACED SAME.

Part: PSEU — MALFUNCTIONED (LE FLAPS) · airframe 68,059 hrs · 33,268 cycles

ON FLAP RETRACTION GOT L/E FLAP DISAGREE. ON FINAL GOT L/E FLAP ASYM PLI WAS FLUCTUATING POS 5 DEG TO POS 12 DEG. T/S PER FIM 27-81-00. PSEU FAULTS CARD NR 10 AND SHOWS CODES 305 421 422 AND 301. REPLACED PSEU. FSEU SHOWS OUTBD SLAT RVDT MISSING AND 603 FLAP LVR RVDT MISRIG. RESET FSEU. RAN FLAPS AND SLATS NUMEROUS TIMES. OPS CK OK. NO FURTHER FAULTS.

Part: SKIN — GOUGED (HORIZ STAB) · airframe 65,233 hrs · 31,972 cycles

DENT/GOUGE FOUND ON LOWER SURFACE OF LT HORIZONTAL STAB, FORWARD TORQUE BOX, INBD SKIN PANEL. DENT WAS DUE TO GROUND DAMAGE. REPAIRED PER ERA 423716-14.

Part: SUPPORT FITTING — CORRODED (RT INBD FLAP) · airframe 65,233 hrs · 31,972 cycles

CORROSION WAS FOUND IN THE HOLE BORES OF THE 6 FASTENERS WHICH ATTACH THE INBOARD FLAP TO THE OUTBOARD SUPPORT FITTINGS. THE HOLES WERE OVERSIZED, HFEC INSPECTED, AND BUSHED. THE ASSEMBLY WAS REINSTALLED WITH ORIGINAL STYLE HARDWARE. THE REPAIR WAS ACCOMPLISHED PER ER/A 087692-14.

Part: WEB — CRACKED (FUSELAGE) · airframe 65,233 hrs · 31,972 cycles

HFEC INSPECTION OF THE AFT P-DOME WEB LAP JOINTS PER AD 88-19-03 REVEALED 26 CRACKS EMANATING FROM FASTENER HOLES ALONG THE LOWER ROW OF THE WEB LAP JOINT BETWEEN WL 190 & 230 (APPROX 210) ON THE RIGHT SIDE OF THE P-DOME.

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 64,842 hrs · 31,777 cycles

EMERGENCY LIGHTS STAY ON IN F/C GALLEY AND RT SIDE OF F/C SECTION. REPLACED POWER SUPPLY.

Part: SEAT BELT — DISCONNECTED (SEAT 36C) · airframe 64,143 hrs · 31,402 cycles

DURING TURBULENCE PASSENGER SEAT BELT AT 36C BECAME DISCONNECTED FROM SEAT, CAUSING A PASSENGER TO BE EJECTED FROM THE SEAT. THE SEAT BELT WAS REMOVED AND REPLACED. THEN BELT WAS SENT TO ATL.

Part: WEDGE — DEBONDED (L/E SLAT) · airframe 63,811 hrs · 31,216 cycles

LEFT SLAT T/E WEDGE DISBONDED. REPAIRED PER ER/A 422819-14.

Part: INDICATOR — OVERHEATED (CAPTAIN/LEFT) · airframe 62,032 hrs · 30,333 cycles

CAPTAIN EADI WENT BLANK. SELECTED ALT EFI AND INDICATOR REMAINED BLANK. ABOUT 5 MINUTES LATER SMOKE WAS SEEN COMINGFROM CAPTAIN EADI. PULLED C/B E3 AND SMOKE STOPPED. REMOVED LEFT ADI INSPECTED CONNECTORS NO DAMAGE FOUND. REPLA LEFT ADI WITH SEVISBLE UNIT PER MM 34-22-03-04. OPERATION NORMAL.

Part: SKIN — CORRODED (FUSELAGE) · airframe 60,728 hrs · 29,641 cycles

THE FUSELAGE SKIN WAS FOUND WITH A CRACK BETWEEN TWO STRINGER ATTACH FASTENERS AT FS 452 ALONG STRINGER 30R. THE UNDERLYING STRINGER WAS FOUND CORRODED. THE CORRODED AREA OF STRINGER WAS CUTOUT AND REPAIRED PER THE B767 SRM. THE SKIN CRACK WAS REMOVED WITH A CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER THE SRM. THE REPAIRS WERE DOCUMENTED PER ER/A 384438-14.

Part: BATTERY PACK — DISCHARGED (SEAT 03A WALL) · airframe 60,124 hrs · 29,285 cycles

ON L/O FOUND L-1DOOR AND 3 LT OVERWING EGRESS EMER LTS. INOPREPLACED M-736 BATTERY PACK, OPS CK GOOD

Part: FRAME — CRACKED (FUSELAGE) · airframe 58,969 hrs · 28,735 cycles

INSPECTION OF THE FS 1809.5 BULKHEAD CHORDS PER BAC S/B 767-53-0078 AND AD 2001-09-13 REVEALED A CRACK IN THE AFT CHORD, 2 FASTENER HOLE CRACKS IN THE FWD CHORD, AND A FASTENER HOLE CRACK IN THE MID CHORD. THE AFT CHORD WAS REPLACED, THE FWD CHORD CUT AND SPLICED PER THE S/B, AND THE MID CHORD HOLE OVERSIZED AND BUSHED. THE WORK WAS ACCOMPLISHED PER ER/A 380849-14AD, REV B.

Part: BOLT — DAMAGED (VERTICAL STAB)

WHILE PERFORMING OPN 5940 RC587 FOUND TENSION TIE BOLTS ROTATING AT FS 1702. UPON INSPECTION FOUND BOTH BARREL NUTS L/R AFT POSTION AT FS 1702 HAD FAILED. FOUND TO BE HEAVILY RUSTED. ENGRG ISSUED ERA 373376-14 TO C/W E0 1-74297-12. BOLT AND NUT REPLACEMENT.

Part: STRINGER — CORRODED (BS 1010)

FUSELAGE STRINGER S-21AR, BS 1010, RBL 97.42, CORROSION REPAIR. STRINGER 21AR WAS FOUND WITH EXTENSIVE CORROSION AT FS 1010 AND RBL 97.42. THE STRINGER FORMS AN END CAP FOR THE MLG HORIZONTAL PRESSURE BULKHEAD. THE CORROSION WAS REMOVED WITH A 5 INCH CUTOUT. THE CUTOUT WAS REPAIRED WITH TWO STEEL REPAIR ANGLES AND A REPAIR STRAP PER ER/A 368364-14, REV A.

Part: SWITCH — DIRTY (LT MLG)

LEFT MAIN GEAR GREEN LIGHTS DID NOT ILLUMINATE WHEN GEAR WAS LOWERED. THE LIGHTS DID NOT PRESS TO TEST WITH GEAR HANDLE UP OR DOWN. CLEANED SWITCH CONTACTS AND RELAMPED, OPERATION NORMAL.

Part: POWER SUPPLY — INOP (ROW 37)

ROW 37 AND BACK EMERGENCY LIGHTS INOP. REPLACED BATTERY SUPPLY PACK M9010, CKS GOOD.

Part: ACTUATOR — FAILED (LT MLG GEAR)

LEFT MAIN GEAR REMAINED DOWN ON DEPARTURE FROM LAX. LOWERD LANDING GEAR AND RECEIVED NORMAL INDICATION. RETURNED TO LAX. TROUBLESHOOTING REVEALED LT GEAR SIDE LOCK ACTUATOR BYPASSING. REMOVED ROD END AND FOUND UPPER PORTION OF ROD ATTACHED TO PISTON SHEARED OFF. REPLACED ACTUATOR PER M/M 32-32-02-4.

Part: LIGHT — INOPERATIVE (CABIN)

AFT EMERGENCY LIGHT ON SEAT 25F INOP. REPLACED LIGHT ASSY, CKS GOOD.

Part: WEDGE — DELAMINATION (NR 4 LE SLAT)

THE UPPER SKIN OF THE LT WING NR 4 SLAT TRAILING EDGE WEDGE WAS FOUND WITH 2 AREAS 2 INCH DIAMETER DELAMINATIONS. THE THE DAMAGE WAS REPAIRED PER THE B767 SRM AND DOCUMENTED PER ER/A 364074-14AD.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

SECTIONS OF SEAT MOUNTED EMERGENCY LIGHTING INOP. FOUND ON PREFLIGHT. REPLACED POWER SUPPLY, SYSTEM CKS GOOD.

Part: SEAT TRACK — CRACKED (BS 786)

THE FUSELAGE SEAT TRACKS LOCATED AT LBL 33, 55 AND RBL 54 WERE FOUND CRACKED IN THE VERTICAL WEB OF THE UPPER CHORD AT APPROX FS 786 AS DESCRIBED IN S/B 767-57-0029. IN ADDITION, PREVENTATIVE MODIFICATIONS TO THE LBL/RBL 33 AND LBL/RBL 54 FLOORBEAMS ARE BEING ACCOMPLISHED. REPAIRED PER ERA 330447-14.

Part: SKIN — CORROSION (WING CENTER SECT)

CORROSION DAMAGE TO THE WING CENTER SECTION UPPER SKIN WAS FOUND AT NUMEROUS LOCATIONS AT THE UPPER SKIN TO STRINGER ATTACH FASTENER HOLES ON STR 1 TO 8, 10 TO 12, 14 AND 15. ALSO, CORROSION WAS FOUND AROUND SEVERAL SKIN TO REAR SPAR ATTACH FASTENER HOLES. REPAIRED PER ERA 330443-14.

Part: SKIN — CORROSION (BS 1307)

CORROSION WAS FOUND JUST AFT OF STA 1307 UNDER THE UHF ANTENNA BOX. THE DAMAGE WAS CUTOUT AS SHOWN IN FIGURE 1. THE SKIN AT THIS LOCATION HAS A MAX THICKNESS OF .135 AND IS CHEM-MILLED FROM 2024-T3 CLAD SHEET. A PREVIOUS REPAIR IS LOCATED JUST FORWARD OF THE 1307 BUTT SPLICE AND REPAIRS A CUTOUT IN .100 2024-T3 CLAD. THEREFORE, BOTH CUTOUTS WILL BE INCORPORATED INTO ONE REPAIR ERA 330481-14.

Part: SKIN — CORROSION (WING CTR SECT)

CORROSION WAS DISCOVERED ON THE UPPER SURFACE OF THE WING CENTER SECTION UPPER SKIN PANELS AT BUTT SPLICE BETWEEN THE FORWARD AND AFT SKIN PANELS AT STRINGER 17, BETWEEN RBL 74.81 AND 97.42. THE SKIN WAS TRIMMED TO REMOVE THE CORROSION IN THE FORWARD AND AFT SKIN PANELS. ADDITIONAL CORROSION WAS FOUND ON THE TOP SURFACE OF THE AFT SKIN PANEL AROUND THE STRINGER 16 ATTACH FASTENERS. STRINGERS 16, 17, 18, AND 19 WERE TRIMMED TO FACILLITATE INSTALLATION OF THE REPAIR. REPAIRED PER ERA 330441-14.

Part: SLAT — DAMAGED (NR 8 LE SLAT)

A/C DIVERTED INTO MCO WITH FLAP/SLATS LOCKOUT. ON ARRIVAL, FOUND NR 8 SLAT DAMAGED. REPLACED NR 8 SLAT, OPS CHECK NORMAL.

Part: BATTERY PACK — DISCHARGED (CABIN)

RT OVERWING SLIDE AND LEFT SPOILER SQUIBS FAILED TEST ON THE MAINTENANCE PANEL. REPLACED THE BATTERY PACK.

Part: SKIN — CORROSION (BS 1540)

SKIN AND STRINGERS WERE FOUND CORRODED AT FS 1540 BETWEEN STR 34L AND 39L. A 3.75 BY 2.25 CUTOUT WAS MADE. STRS 34L TO 39L REQUIRED NEW SECTIONS TO BE SPLICED IN. ADDITIONAL DAMAGE WAS FOUND AFTER INITIAL RELEASE OF ER/A. A SECOND 2 BY 3 CUTOUT WAS MADE BETWEEN STR 37L TO 38L.

Part: SKIN — CORRODED (BS 1542)

NR 95 CORROSION THROUGH FUSELAGE SKIN AT STA 1542 STR 35. NR 177 THROUGH 182 WRITTEN FOR STRINGER DAMAGE STR 34L THROUGH 39L WILL REPAIR PER ERA 360836-14 AS OF 12/19/96 ERA PENDING FAA APPROVAL.

Part: FAN — SHORTED (E/E COMPT)

STRONG ELECTRICAL ODOR IN AIRCRAFT ON TAXI-OUT. FWD EXHAUST EQUIPMENT COOLING FAN POPPED C/B. FWD TO MCO AND PLAC PER MEL 21-58-04A, NEEDS FAN DAL 211002542.

Part: ACTUATOR — FAILED (RT AILERON CONTL)

DURING FLT CONTROL CHECK, AILERON AND ELEVATOR FELT VERY HEAVY. AIRCRAFT RETURNED TO BLOCK. REPLACED RT LCCA, RIGGED AND LEAK CHECKED, OPERATION NORMAL.

Part: LIGHT — INOPERATIVE (LT AFT)

ON LAYOVER, FOUND LEFT AFT EMERGENCY LIGHT INOP. RELAMPED, CKS OK.

Part: SENSOR — OUT OF ADJUST (LANDING GEAR)

ON TAKEOFF, GEAR COULD NOT BE RAISED WITHOUT USING LOCK OVERRIDE. AIRCRAFT WAS FERRIED ATL FOR REPAIRS. PSEU SHOWS 246 RT GEAR TILT TARGET SHOWS FAR RESET. ADJUSTED SENSOR PER MM, OPERATION NORMAL.

Part: FAN — FAILED (CARGO COMPT)

ELECTRICAL SMELL IN COCKPIT AT CRUISE. FORWARD EQ EXHAUST FAN EICAS MSG. SMELL DISSIPATED IN COCKPIT. F/A REPORTED SMELL DIRECTED AFT THROUGH CABIN. FOUND FAN AT FAULT. DEFERRED PER MEL, THEN REPLACED FAN, OPERATION NORMAL.

Part: FLAP — CAP DAMAGED (NBR 1 LE)

FOUND DURING O-2 CHECK, NR 1 FLAP L/E CAP DAMAGED 2 PLACES. INSTALLED PERMANENT REPAIR AS PER SRM 51-70-03 FIG 201.