N620DL

Part: STRINGER — CORRODED · corrosion level 2 · airframe 81,981 hrs · 42,094 cycles

BS 1455, STRINGER 28L WAS CORRODED. REMOVED AND REPALCED THE STRINGER IAW SRM 53-00-003, FIG 201, AND REA 46971REA64,

Part: STRINGER — CORRODED (BS 1455) · corrosion level 2 · airframe 81,981 hrs · 42,094 cycles

STRINGER 27L WAS CORRODED, BS 1455. REMOVED AND REPLACED THE STRINGER IAW SRM 53-00-03, AND REA 46971REA64.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 80,568 hrs · 41,029 cycles

AIRCRAFT GROUNDED FOR HEAVY MAINTENANCE. FLOORBEAM LOWER HORIZONTAL FLANGE CORRODED AT STATION 740 LBL 18. REPAIR LOWER CHORD STATION 740 LBL 18 IN ACCORDANCE WITH SRM 53-00-51.

Part: WEB — CRACKED (LE SLAT) · airframe 80,568 hrs · 41,029 cycles

AIRCRAFT GROUNDED FOR HEAVY MAINTENANCE. NR 1 SLAT AFT SIDE COVE STRUCTURE HAS 2 CRACKS, LOCATED ABOVE THE INBOARD MAIN TRACK FITTING. ONE CRACK IS ABOUT 2 1/4" AND THE OTHER IS ABOUT 1 3/8" IN LENGTH, AT APPROXIMATELY OUTBOARD SLAT STATION 737. REMOVED AND REPLACED NR 1 SLAT COVER PANEL P/N 114N4075-19 IN ACCORDANCE WITH DRAWING 114N4075 AND SRM 51-40-02 PARAGRAPH 4, 5, 7, 9.

Part: WEB — CRACKED (LE SLAT) · airframe 80,568 hrs · 41,029 cycles

AIRCRAFT GROUNDED FOR HEAVY MAINTENANCE. NR 1 SLAT AFT SIDE COVE STRUCTURE HAS 2 CRACKS, LOCATED ABOVE THE INBOARD MAIN TRACK FITTING. ONE CRACK IS ABOUT 2 1/4" AND THE OTHER IS ABOUT 1 3/8" IN LENGTH, AT APPROXIMATELY OUTBOARD SLAT STATION 737. REMOVED AND REPLACED NR 1 SLAT COVER PANEL P/N 114N4075-19 IN ACCORDANCE WITH DRAWING 114N4075 AND SRM 51-40-02 PARAGRAPH 4, 5, 7, 9.

Part: ATTACH BRACKET — CRACKED (NR 1 PYLON) · airframe 80,568 hrs · 41,029 cycles

AIRCRAFT GROUNDED FOR HEAVY MAINTENANCE. NUMBER 1 PYLON, LINK AT FORWARD LEFT SIDE OF HYDRAULIC BAY, LOWER ATTACH BRACKET BROKEN.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 79,407 hrs · 40,169 cycles

DURING THE COURSE OF DAILY CHECK, EMERGENCY EXIT LIGHTING FOUND TO BE INOPERATIVE. R & R BATTERY POWER SUPPLY IAW AMM 33-51-07. OPERATIONAL CHECKED SATISFACTORY. ACFT RELEASED TO SERVICE.

Part: ROD — BENT (L1 DOOR) · airframe 84,840 hrs · 44,121 cycles

L1 ENTRY DOOR ROLLERS DO NOT ALWAYS ENGAGE, UPPER LOCK ROD BENT. R & R UPPER ROD IAW AMM 52-12-00. OPERATIONAL CHECKED SATISFACTORY. ACFT RELEASED TO SERVICE.

Part: ENGINE — MAKING METAL (RIGHT) · airframe 78,756 hrs · 39,773 cycles

DURING CLIMB OUT AT FL300, RT ENG OIL PRESS DROPPED INTO RED FOLLOWED BY EICAS MSG. PRECAUTIONARY SHUTDOWN OF NR 2 ENG. ACFT RETURNED, GNDED NO OPS. CHIP DETECTORS PULLED. MASTER CHIP DETECTOR & MAIN GEARBOX CHIP DETECTOR WERE CONTAMINATED WITH CHIPS. DETECTORS WERE CLEANED & SECOND ENG RUN ATTEMPT MADE WITH SAME RESULTS. POST ENG RUN INSPECTION REVEALED OIL PUDDLE WITH CHIPS IN THE TAILPIPE. WORK IN PROGRESS FOR THE REMOVAL OF NR 2 ENG SN-716429 & THE INSTALL OF SN-726727.

Part: VALVE — DEFECTIVE (CARGO DOOR) · airframe 78,513 hrs · 39,603 cycles

MAIN CARGO DOOR WARNING LIGHT DISPLAYED & CABIN PRESS NOT WITHIN PARAMETERS. CREW NOTED PRESSURIZATION AS DECREASING. BITE CHECK OF BOTH CABIN PRESS CONTROLLERS ACCOMPLISHED IAW FIM 21-30 FT 802. SYSTEMS CHECKED SATISFACTORY, NO FAULTS NOTED. HOLDING VLV ASSEMBLY REMOVED, REPLACED & FUNCTIONALLY TESTED IAW PRECISION CONVERSION MM 52-30-00 & MM 20-00-00. OPERATIONAL CHECK SATISFACTORY. ACFT PRESSURIZED TO 5.0 PSID FOR INTEGRITY CHECK OF VLV ASSEMBLY. OPERATIONS CHECKED SATISFACTORY. NO LEAKS NOTED.

Part: METERING UNIT — MALFUNCTIONED (BRAKE) · airframe 78,430 hrs · 39,532 cycles

DURING THE TAKE OFF, BEFORE COMPLETE RETRACTION OF THE FLAPS, EICAS MESSAGE DISPLAYED "L HYD PRESSURE" FOLLOWED BY FURTHER MESSAGES INDICATING A LEFT HYDRAULIC SYS PRESS. UPON EVALUATION OF SYSTEM FAULT WAS ISOLATED TO A SEPERATION OF AUTOBRAKE ACTUATOR FROM BRAKE METERING VALVE ASSY. IAW AMM 32-41-03/401 BRAKE METERING VALVE ASSY WAS REMOVED AND REPLACED. OPS CHECKED SATISFACTORY.

Part: MODULE — DEFECTIVE (CABIN) · airframe 78,410 hrs · 39,505 cycles

ON DAILY CHECK FOUND EMER LIGHT UNARMED. ANNUNCIATOR LIGHT INTERMITTENT. EMER LIGHT ANNUNCIATOR LIGHT LENS CAP MODULE R & R IAW AMM 33-16-02 201. OPERATIONAL CHECKED SATISFACTORY.

Part: SKIN PANEL — CORRODED (RT WING) · airframe 76,960 hrs · 38,364 cycles

CORROSION WAS DISCOVERED ON THE RT WING UPPER SKIN PANEL AT WS285.65. DAMAGE IS LOCATED NEAR THE AFT EDGE OF THE SKIN PANEL BETWEEN THE REAR SPAR AND STRINGER S-1. REMOVED CORROSION IAW SRM 57-20-01. PERFORMED HFEC INSPECTION OF BLENDED AREA IAW NDT MANUAL 51-00-19. NO DEFECTS NOTED. FABRICATED AND INSTALLED DOUBLER IAW DOCUMENT 470505REA06 AND FLIGHT VEHICLES CONSULTING DWG 57-13152-1, REV 1. FUEL LEAK CHECK GOOD IAW AMM 28-11-00.

Part: SKIN PANEL — CORRODED (RT WING) · airframe 76,960 hrs · 38,364 cycles

CORROSION WAS DISCOVERED ON THE RT WING UPPER SKIN PANEL AT FSS404 FWD OF FRONT SPAR. REMOVED CORROSION IAW SRM 57-20-01. PERFORMED HFEC INSP OF BLENDED AREA IAW NDT MANUAL 51-00-19. NO DEFECTS NOTED. FABRICATED REPAIR DOUBLER FROM .071" 7075-T6 AND INSTALLED DOUBLER IAW AMES DOCUMENT 47050REA02 AND FLIGHT VEHICLES CONSULTING DWG 57-13153-2. FUEL LEAK CHECK GOOD IAW AMM 28-11-00.

Part: FLOOR SUPPORT — CORRODED (BS 1075) · airframe 76,960 hrs · 38,364 cycles

CORROSION WAS DISCOVERED ON THE UPPER CARGO FLOOR SUPPORT BS 1075, LBL 47, FLOOR AREA INBD SURFACE. BLENDED AREA OF CORROSION IAW SRM 53-00-52. PERFORMED ULTRASONIC INSPECTION OF AREA IAW NDT MM PART 4, 51-00-10. MATERIAL REMOVED IS OUT OF LIMITS. FABRICATED NEW FLOOR SUPPORT FROM 7075-T611, ALUMINUM IAW BAC 1506-1108. INSTALLED NEW SECTION OF FLOOR SUPPORT IAW SRM 51-40-01.

Part: SEAT TRACK — CORRODED (BS 1180-1580) · airframe 76,960 hrs · 38,364 cycles

CORROSION WAS DISCOVERED ON THE UPPER CARGO SEAT TRACK UPPER CHORD AT STATION 1180-1580, RBL 24. DAMAGE CAUSED BY CORROSION IN SEVERAL AREAS ALONG THE UPPER SURFACE WERE FOUND TO BE BEYOND ALLOWABLE AND REPAIRABLE LIMITATIONS. FABRICATED NEW SEAT TRACK SECTION FROM BAC1520-792 7178-T6511 ALUMINUM USING REMOVED PART FOR A DIMENSIONAL SAMPLE. REPLACED SEAT TRACK IAW AMES DOCUMENT 47050REA09, REV A AND SRM 51-40-02.

Part: SEAT TRACK — CRACKED (BS 220) · airframe 76,960 hrs · 38,364 cycles

PILOTS AFT OTBD SEAT TRACK IS CRACKED AT THE AFT STOP. R & R THE CAPTAINS AFT OTBD SEAT TRACK IAW AMM 25-11-01.

Part: CARGO TRACK — BROKEN (BS 1100) · airframe 76,960 hrs · 38,364 cycles

UPPER CARGO TRACK AT BS 1100, RBL 24 IS BROKE OUT ON UPPER FLANGE AT NUTPLATE. ALSO 3 AREAS OF POSSIBLE CRACKS. REMOVED SEAT TRACK CROWN AT BS 1100 RBL 24 FOR REPLACEMENT. FABRICATED SEAT TRACK. INSTALLED SEAT TRACK IAW SRM 51-40-02.

Part: SKIN — CORRODED (BS 1401) · airframe 76,960 hrs · 38,364 cycles

FUSELAGE EXTERIOR SKIN CORRODED AT AFT LOWER CARGO DOOR CUTOUT THRESHOLD AT STATION 1401 S27R - S28R. CORROSION WAS REMOVED IAW SRM 53-00-01, FIG 101, EXCEEDING PUBLISHED LIMITS. THE DAMAGED SKIN WAS TRIMMED OUT AND A FILLER WAS FABRICATED. A HFEC OPEN HOLE AND SURFACE SCAN INSPECTION WAS ACCOMPLISHED REVEALING NO DEFECTS. AN EXTERNAL REPAIR DOUBLER WAS INSTALLED IAW SRM 53-00-01.

Part: SILL — CORRODED (BS 1340-1440) · airframe 76,960 hrs · 38,364 cycles

INNER CHORD OF AFT LOWER CARGO DOOR LOWER SILL CORRODED. THE DAMAGE WAS ISOLATED TO THE LOWER HORIZONTAL FLANGE OF THE CHORD SPANNING FROM STATION 1340 - 1440 AT S27R. CORROSION WAS REMOVED IAW SRM 53-60-15, FIG 101, EXCEEDING PUBLISHED LIMITS. A HFEC OPEN HOLE AND SURFACE SCAN INSPECTION WAS ACCOMPLISHED IAW NDT MANUAL PART 6 REVEALING A DAMAGE FREE CONDITION. FABRICATED A TAPERED FILLER FROM 7075-T6 ALUMINUM TO FIT THE BLENDED AREA AND INSTALLED IAW AMES DOCUMENT 47050REA04.

Part: STANCHION — CORRODED (BS 1440) · airframe 76,960 hrs · 38,364 cycles

LOWER SECTION OF STANCHION AT BS 1440, RBL 19 CORRODED. FABRICATED STANCHION IAW DWG 284N1695 USING EXTRUSION AND 10140-2002 7075-T6511. RT STANCHION IAW DWG 284N1695.

Part: SUPPORT ANGLE — CRACKED (BS 560) · airframe 76,960 hrs · 38,364 cycles

SUPPORT ANGLE CRACKED AT FORWARD LOWER CARGO FWD DOOR FRAME JUST INBD OF THE THIRD DOOR STOP DOWN AT BS 560. REMOVED CRACKED ANGLE AND FABRICATED NEW ANGLE. HEAT TREATED ANGLE IAW 5602, REV AF 28 DATED AUG 2001. TREATED, PRIMED AND PAINTED ANGLE IAW SRM 51-20-01. INSTALLED ANGLE IAW SRM 51-40-02.

Part: SKIN — CORRODED (RT WING) · airframe 76,960 hrs · 38,364 cycles

RT WING REAR SPAR AT WBL 95 HAS CORROSION ON WING SKIN. REMOVED CORROSION FROM WING SKIN IAW SRM 57-20-01. PERFORMED HFEC INSPECTION OF BLENDED AREA IAW NDT MANUAL 51-00-19. NO DEFECTS NOTED. PERFORMED THICKNESS CHECK OF BLENDED AREA IAW NDT MANUAL 51-00-10, PART 4. DAMAGE WAS FOUND TO BE OUT OF ALLOWABLE LIMITS AS DEFINED BY SRM. REPAIRED IAW DWG NR 57-13154-1.

Part: FRAME — CORRODED (BS 1480) · airframe 76,960 hrs · 38,364 cycles

CORROSION WAS FOUND IN THE AFT LOWER CARGO COMPARTMENT, ON THE FWD SIDE OF THE FRAME AT BS 1480 BETWEEN S26-27R. BLENDED AREA OF CORROSION IAW SRM 53-00-07, FIG 101. COMPLIED WITH HFEC SURFACE SCAN IAW NDT MM 51-00-19, PART 6. NO DEFECTS NOTED. FABRICATED THE REPAIR DOUBLER AND HEAT TREATED TO T6 CONDITION IAW BAC5602, REV AF. INSTALLED REPAIR DOUBLER IAW SRM 51-40-00.

Part: SKIN — DEBONDED (ZONE 500)

LT WING FIXED L/E UPPER SURFACE IS DISBONDED WS 231.0, REPAIRED BY REMOVED DAMAGE, CLEAN AND PREPPED LT WING FIXED L/E UPPER SURFACE, APPLIED REPAIR 23" X 18" AND RESTORED FINISH IAW SRM 51-70-07.

Part: WARNING LIGHT — FALSE ACTIVATION (SPOILERS) · airframe 75,211 hrs · 37,081 cycles

DURING TAKEOFF, SPOILER CAUTION LIGHT ILLUMINATED WITH THE TAKEOFF WARNING HORN AND THE SPOILER EICAS MESSAGE DISPLAYED. ACFT RETURNED TO THE BLOCKS WITHOUT INCIDENT. POST FLIGHT INSPECTION PERFORMED. CONDUCTED CONFIGURATION TAKE OFF TEST, UNABLE TO DUPLICATE PROBLEM. ACFT RETURNED TO SERVICE.

Part: PITOT TUBE — OBSTRUCTED · airframe 74,596 hrs · 36,801 cycles

DURING TAKEOFF ROLL IT WAS NOTED THAT THERE WAS NO AIRSPEED INDICATION ON THE CAPTAINS SIDE. THE TAKEOFF WAS ABORTED WITH LIGHT BRAKING. ACFT RETURNED TO THE BLOCKS WITHOUT INCIDENT. POST FLIGHT INSPECTION WAS PERFORMED NOTING THAT THE CAPTAINS PITOT TUBE WAS OBSTRUCTED WITH DEBRIS. THE DEBRIS WAS REMOVED, OPS CHECK WAS PERFORMED WITH NO DEFECTS. ACFT WAS RETURNED TO SERVICE.

Part: CONTROL VALVE — INOPERATIVE (A/C PACK) · airframe 74,142 hrs · 36,513 cycles

DURING CRUISE OPERATION AN EICAS MESSAGE APPEARED " R PACK OFF" & R ENG BLEED OFF" MESSAGES APPEARED. THE ACFT DIVERTED WHERE IT LANDED WITHOUT INCIDENT. POST FLIGHT INSP WAS PERFORMED AND WAS RELEASED TO SERVICE, FURTHER INVESTIGATION LEAD TO THE REMOVAL AND REPLACEMENT OF THE PACK TEMP CONTROL VALVE, OPS CHECKS GOOD. ACFT WAS RETURNED TO SERVICE WITH NO OTHER DEFECTS NOTED.

Part: UNKNOWN — UNKNOWN (THROTTLE) · airframe 73,289 hrs · 35,976 cycles

DURING TAKEOFF ROLL WITH THROTTLES ADVANCED AND EPR CALLED, THE THROTTLERS DID NOT ENGAGE FOR TAKEOFF. THE TAKEOFF WAS ABORTED. POST FLIGHT INSP WAS PERFORMED WITH NO DEFECTS NOTED. ACFT WAS RETURNED TO SERVICE.

Part: FLAP TRACK — CORRODED (LT TE FLAP) · corrosion level 2 · airframe 72,505 hrs · 35,565 cycles

DURING MX, THE LEFT OTBD FLAP, OTBD TRACK WAS BLEEDING RUST. UPON DISASSEMBLY, THE TRACK WAS FOUNDED CORRODED. THE CORROSION WENT BEYOND THE CMM LIMITS. MFG ENGINEERING ISSUED AN REA TO FURTHER CLEAN THE CORROSION WITH ADDITIONAL LIMITS ESTABLISHED. THE CORROSION WAS REMOVED, PART WAS INITAL ETCHED, FMPI INSPECTED, SHOT PEENED AND CAD PLATED. THE TRACK WAS REINSTALLED AND THE FLAPS RIGGED. THE ITEM WAS RETURNED TO SERVICE.

Part: FRAME — CORRODED (AILERON) · corrosion level 2 · airframe 72,505 hrs · 35,565 cycles

DURING MX, THE LT WING AILERON WAS FOUND DELAMINATED. REMOVED CONDUCTIVE FRAME. FABRICATED NEW FRAME FROM 6061 T4 0.020" AND INSTALLED FRAME IAW THE SRM. REMOVED FIBERGLASS ISOLATION PLY, NO FURTHER DAMAGE NOTED. REPLACED ISOLATION PLY. PREPPED AND PAINTED AILERON. BALANCED AILERON IAW THE SRM. ITEM RETURNED TO SERVICE.

Part: SKIN — DELAMINATED (NR 10 SLAT) · airframe 72,505 hrs · 35,565 cycles

DURING MX, THE BOTTOM WEDGE OF THE NR 10 SLAT WAS FOUND DELAMINATED ON INBD END. REPAIRED DELAMINATED AREA IAW THE SRM. REPAIR FOUND TO COMPLY WITH SB 757-57A0038, REV 6. ITEM RETURNED TO SERVICE.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 72,505 hrs · 35,565 cycles

DURING A MAINTENANCE INSPECTION EVENT, CORROSION WAS FOUND ON A FLOOR SUPPORT ANGLE AT FS 780 BL0. THE CORROSION WAS FOUND BEYOND LIMITS. FABRICATED A NEW SUPPORT ANGLE FROM 7075-0, 0.063". HEAT TREATED ANGLED. CORROSION TREATED ANGLE AND REINSTALLED. ITEM RETURNED TO SERVICE.

Part: SUPPORT FITTING — CORRODED (ZONE 200) · corrosion level 2 · airframe 72,505 hrs · 35,565 cycles

DURING MX, CORROSION WAS FOUND ON A SEAT TRACK SUPPORT FITTING (CHORD). CORROSION WAS FOUND OUT OF SRM LIMITS. ISSUED WITH GREATER CLEANUP ALLOWED. ITEM RETURNED TO SERVICE.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 72,505 hrs · 35,565 cycles

DURING MX, CORROSION WAS FOUND ON THE FLC AFT BULKHEAD LOWER CTR FRAME. CUTOUT CORROSION DAMAGE AND REPAIRED DAMAGE IAW THE SRM USING 7075 T6 0.050" AND 7075-T6 0.063". ITEM RETURNED TO SERVICE.

Part: ATTACH FITTING — CORRODED (ZONE 200) · corrosion level 2 · airframe 72,505 hrs · 35,565 cycles

DURING MX, CORROSION WAS FOUND ON A FLOOR PANEL ATTACH CHORD ADJACENT TO NUTPLATES. THE CORROSION WAS BEYOND MFG LIMITS AND THE DAMAGE CHORD REMOVED. FABRICATED NEW CHORD FROM EXTRUSION BAC 1506-1108 EXTRUSION. INSTALLED THE NEW CHORD SECTION IAW THE SRM. ITEM RETURNED TO SERVICE.

Part: INTERCOSTAL — CORRODED (ZONE 100) · corrosion level 2 · airframe 72,505 hrs · 35,565 cycles

DURING MX, INTERCOSTAL BETWEEN S29L-S30L STA 1400-1420 FOUND CORRODED. CORROSION OUTSIDE OF SRM LIMITS. REMOVED AND FABRICATED NEW INTERCOSTAL WITH 7075 T-6 0.032". REINSTALLED INTERCOSTAL IAW THE SRM. ITEM RETURNED TO SERVICE.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 72,505 hrs · 35,565 cycles

DURING MX, A FLOOR SUPPORT LBL 46-LBL 62 BS 1060 FOUND CRACKED. ISSUED FOR FABRICATION INSTRUCTIONS. FABRICATED THE CRACKED FLOOR SUPPORT/INTERCOSTAL FROM 7075-0 0.050" HAND HEAT TREATED. REINSTALLED INTERCOSTAL AND ITEM RETURNED TO SERVICE.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 72,505 hrs · 35,565 cycles

DURING A MX, CORROSION WAS FOUND ON A FLOOR SUPPORT ANGLE AT FS 780 LBL 6. THE CORROSION WAS FOUND BEYOND LIMITS. FABRICATED A NEW SUPPORT ANGLE FROM 7075-0, 0.063". HEAT TREATED ANGLED. CORROSION TREATED ANGLE AND REINSTALLED. ITEM RETURNED TO SERVICE.

Part: SKIN — CORRODED (ZONE 200) · airframe 72,505 hrs · 35,565 cycles

DURING A HEAVY MX INSP EVENT, THE FUSELAGE SKIN WAS FOUND BULGED AT STA 1460 BETWEEN STRINGERS 27L & 30L. DEFECT WAS FOUND TO BE CORROSION ON THE STRINGERS AND INTERCOSTAL. R & R STRINGERS, FABRICATED INTERCOSTAL AND INSTALLED IAW SRM. ITEM WAS RETURNED TO SERVICE.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 72,505 hrs · 35,565 cycles

DURING A HEAVY MX INSP EVENT CORROSION BETWEEN STR 29L AND THE FUSELAGE SKIN AT STA 1467. THE UNDERLYING SKIN WAS ALSO CORRODED RESULTING IN A 2.4"LONG X 1.0" WIDE CUT OUT LOCATED AT STA 1467, S29L. AN ADDITIONAL SKIN CUT OUT WAS REQUIRED AT STA 1484, S29L THAT MEASURED 8.0" LONG X 2.50" WIDE. NEW DOUBLER AND TRIPLER WAS FABRICATED FROM 2024-T3 X .063" AND INSTALLED. ITEM WAS RETURNED TO SERVICE. THE STRINGER PN WAS ADDRESSED ON THE SDR ABXR201006220004.

Part: STRINGER — CORRODED (BS 1466 S29L) · corrosion level 2 · airframe 72,505 hrs · 35,565 cycles

DURING A HEAVY MX INSP EVENT THE FUSELAGE SKIN WAS BULGED AT STATION 1466, STRINGER 29L. DEFECT WAS FOUND TO BE CORROSION OF THE STRINGER AND INTERCOSTAL BETWEEN STA 1400 AND STA 1420. R & R STRINGER, FABRICATED INTERCOSTAL AND INSTALLED. ITEM WAS RETURNED TO SERVICE.

Part: SHUTOFF VALVE — MALFUNCTIONED (ZONE 500) · airframe 70,518 hrs · 34,548 cycles

FLT 165 FROM MIA TO TOL WHILE CLIMBING THROUGH FL340 EICAS MSG "L" ENGINE BLEED OFF CAUTION APPEARED. WHILE PERFORMING APPROPRIATE PROCEDURES THE EICAS "R" ENGINE BLEED OFF CAUTION LIGHT APPEARED. APPROPRIATE PROCEDURES WERE PERFORMED AND AN EMERGENCY WAS DECLARED. THE AIRCRAFT DIVERTED TO MCO WHERE IT LANDED WITHOUT INCIDENT. POST FLIGHT INSPECTION WAS PERFORMED IN ACCORDANCE WITH THE B757 FIM MANUAL. OPERATIONAL CHECKS OF THE "R" ENGINE BLEED SYSTEM WAS PERFORMED WITH NO DEFECTS. PERFORMED INSPECTION OF THE "L" ENGINE BLEED SYSTEM AND FOUND THE LEFT HPSOV P/N 3214488-7 S/N 2032 NOT FULLY CLOSING. REMOVED AND REPLACED THE HPSOV PERFORMED OPS CHECKS, FOUND # 1 ENGINE PRSOV SENSE LINE LEAKING. REMOVED AND REPLACED PRSOV SENSE LINE, REMOVED AND REPLACED THE FAMV, REMOVE AND REPLACED THE FATS SENSOR, PERFORMED OPERATIONAL CHECKS WITH NO DEFECTS. AIRCRAFT WAS RETURNED TO SERVICE.

Part: BLEED VALVE — CRACKED (ZONE 600) · airframe 70,368 hrs · 34,509 cycles

DURING CLIMB OUT THE NR 2 ENG EXCEEDED THE EGT LIMIT OF 657 DEG FOR 16 SEC THIS DID NOT OCCUR DURING A SURGE. ACFT RETURNED TO DEPARTURE WHERE IT LANDED WITHOUT INCIDENT. POST FLIGHT INSP WAS PERFORMED. THE 14TH STAGE BLEED VALVE WAS REMOVED AND REPLACED PN 5840207 SN 0573 NO HELP, REMOVED AND REPLACED THE 14TH STAGED BLEED VALVE CONVERTER PN 322895-18 SN 2233. NO HELP, REMOVED AND REPLACED 2.5 BLEED VALVE ACTUATOR PN 3830041-109 SN 0498, NO HELP. REMOVED AND REPLACED DAMAGED FUEL MANIFOLD PSI LINE ON 2.5 BLEED VALVE PN 183622-01, NSN. REMOVED AND REPLACED FUEL CONTROL UNIT PN 779100-5 SN A4327 NO HELP. PERFORMED BORESCOPE INSP OF COMBUSTION CHAMBER, HPT AND LPT SECTIONS WITH NO DEFECTS. PERFORMED BORESCOPE INSPECTION OF THE 6-17TH COMPRESSOR SECTION, NO DEFECTS NOTED. FOUND 14TH STAGE BLEED VALVE MUSCLE PRESSURE MANIFOLD LINE WAS CRACKED REMOVED AND REPAIRED LINE. PERFORMED ENGINE RUN AND OPS CHECKS GOOD. NO OTHER DEFECTS WERE NOTED. ACFT WAS RETURNED TO SERVICE.

Part: ACOUSTIC PANEL — DELAMINATED (ENGINE INLET) · airframe 78,300 hrs · 38,269 cycles

DURING SHOP VISIT, LARGE DELAMINATIONS WERE FOUND ON THE PN 314N3011-170, ENGINE INLET ACOUSTIC PANEL, REQUIRING REPLACEMENT OF THE DELAMINATED SKINS. REPAIRED IAW ERA 474812-14.

Part: ENGINE — DAMAGED (NR 1) · airframe 68,721 hrs · 33,719 cycles

FLT 201 FROM MIA TO CCS - AFTER TAKEOFF WITH FLAPS RAISED APPROX 1800 FEET AND CLIMB THRUST SELECTED, 3 QUICK COMPRESSOR STALLS WERE HEARD AND FELT FROM THE NR 1 ENGINE. APPROPRIATE CHECKLIST WAS PERFORMED, EMERGENCY WAS DECLARED AND THE AIRCRAFT RETURNED TO MIA WHERE IT LANDED WITHOUT INCIDENT. POST FLIGHT BOROSCOPE INSPECTION REVEALED DAMAGE TO THE HIGH PRESSURE COMPRESSOR WHICH WAS DEEMED UNSERVICEABLE. THE NR 1 ENGINE WAS REMOVED AND REPLACE. OPERATIONAL AND LEAK CHECKS GOOD. NO OTHER DEFECTS WERE NOTED. AIRCRAFT WAS RETURNED TO SERVICE.

Part: HINGE — DAMAGED (PAX DOOR)

DURING CLIMB OPERATION THE FWD ENTRY DOOR EICAS MESSAGE APPEARED WITH THE ASSOCIATED OVERHEAD LIGHT. THE AC RETURNED TO DEPARTURE WHERE IT LANDED WITHOUT INCIDENT. POST FLIGHT INSPECTION REVEALED THAT THE FWD ENTRY DOOR WAS NOT CENTERED IN THE DOOR FRAME WHEN CLOSED. THE FWD ENTRY DOOR HINGE WAS REMOVED AND REPLACED. OPS AND LEAK CHECKS GOOD. NO OTHER DEFECTS WERE NOTED. AC WAS RETURNED TO SERVICE. (K)

Part: DOOR — OUT OF ADJUST (MAIN PAX)

DURING CLIMB OPERATION THE FWD ENTRY DOOR EICAS MESSAGE APPEARED WITH THE ASSOCIATED OVERHEAD LIGHT. THE ACFT RETURNED WHERE IT LANDED WITHOUT INCIDENT. POST FLIGHT INSP REVEALED THAT THE FWD ENTRY DOOR WAS NOT CENTERED IN THE DOOR FRAME WHEN CLOSED. THE FWD ENTRY DOOR HINGE WAS REMOVED AND REPLACED. OPS AND LEAK CHECK GOOD. NO OTHER DEFECTS WERE NOTED. AC WAS RETURNED TO SERVICE. (K)

Part: EEC — MALFUNCTIONED (ENGINE) · airframe 68,011 hrs · 33,405 cycles

FLT P0002 FROM PTY TO MFA. DURING CLIMB OPERATION OIL PSI WENT TO -4, N1=0, N2=0 ENG SHUTDOWN. ACFT RETURNED TO PTY WHERE IT LANDED WITHOUT INCIDENT. TROUBLESHOT SYSTEM AND FOUND EEC TO BE AT FAULT. REMOVED AND REPLACED EEC, OPS CHECKS GOOD. NO FURTHER DEFECTS NOTED. ACFT WAS RETURNED TO SERVICE. (S)

Part: EEC — INOPERATIVE (NR 2 ENGINE)

DURING CLIMB OPERATION, OIL PSI WENT TO -4, N1=0, N2=0, ENGINE SHUTDOWN. AC RETURNED TO DEPARTURE WHERE IT LANDED WITHOUT INCIDENT. TROUBLESHOT SYSTEM AND FOUND EEC TO BE AT FAULT. REMOVED AND REPLACED EEC, OPS AND LEAK CHECKS GOOD. NO OTHER DEFECTS NOTED. AC WAS RETURNED TO SERVICE. (K)

Part: PSEU — MALFUNCTIONED (MLG) · airframe 63,291 hrs · 31,447 cycles

AFTER RISING LDG GEAR HANDLE EICAS CAUTION GEAR DISAGREE AND ADVISORY MSG GEAR DOORS ANNUNCIATED WITH GEAR AND DOOR LIGHTS AT GEAR HANDLE. GEAR LOWERED NORMALLY WITH GOOD DOWN AND LOCKED INDICATIONS. PSEU BITE - 072, 069, 239, 241, 406, 171, 170, AND MORE SUSPECT FAULTY PSEU. REPLACED PSEU, BITE CHECKS OK. INSPECTED GEAR DOOR AND SWITCHES, ALL OK.

Part: SKIN — DAMAGED (BS 625 S7R) · airframe 63,175 hrs · 31,405 cycles

LIGHTNING STRIKE DAMAGE FOUND ON FUSELAGE SKIN AT STA 625 AT STR 7R. DAMAGED SKIN WAS REMOVED 1.5 X 1.0 IN. A REPAIR DOULBER WAS INSTALLED.

Part: BATTERY — OVERHEATED (E/E BAY) · airframe 60,862 hrs · 30,563 cycles

UNUSUAL ODOR IN COCKPIT NOTICED JUST PRIOR TO PUSH BACK . FOUND APU BATTERY AT ZERO VOLTS AND OVERHEATED. REPLACED APU BATTERY AND APU BATTERY CHARGER.

Part: SKIN — DENTED (FUSELAGE) · airframe 58,262 hrs · 29,645 cycles

FUSELAGE SKIN FROM STA 1701 - 1711 ABOVE STR 17L DENTED. REPAIRED IAW ERA 092423-14.

Part: FITTING — DAMAGED (NR 2 PYLON) · airframe 58,262 hrs · 29,645 cycles

NR 2 PYLON LOWER SPAR FITTING HAD FOUR OVERSIZED FASTENERS. REPAIRED IAW ERA 092712-14AD.

Part: SKIN — DENTED (FUSELAGE) · airframe 58,262 hrs · 29,645 cycles

FUSELAGE SKIN AT STATION 500 - 520 AND STR 27R - 28R SUFFERED MULTIPLE DAMAGE AREAS DUE TO GROUND DAMAGE. REPAIRED IAW ERA 092585-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 58,262 hrs · 29,645 cycles

FUSELAGE SKIN REPAIRED AT THE SKY RADIO ANTENNA CUTOUT AT STA 1320 AND BL 0. REPAIRED IAW ERA 092512-14.

Part: HOSE — FRAYED (RT WING SLIDE) · airframe 58,262 hrs · 29,645 cycles

RIGHT OFF WING SLIDE INFLATION HOSE FRAYED. REPLACED SAME.

Part: EEC — MALFUNCTIONED (NR 1 ENGINE) · airframe 56,611 hrs · 29,020 cycles

UPON LANDING WITH T/R DEPLOYED, COCKPIT LEFT OIL PRESS LIGHT ILLUMINATED AND SMOKE WAS SEEN TRAILING LEFT SIDE BY TOWER. ENGINE WAS SHUT DOWN DURING ROLLOUT. REMOVED AND CLEANED EEC CANNON PLUGS. INSP WIRING RUN THRU PEDESTAL FROM LT FUEL CONTROL SWITCH. WHILE MOVING T/R LEVER, NO CHAFING OR BINDING FOUND. CHECK CUTOFF CIRCUIT FOR 28VDC AT PIN 1 D41948P, 0 VOLTS FOUND NORMAL. REMOVED AND REPLACED ENG FIR CONTROL PANEL, RAN ENG, CHECK GOOD. REMOVED AND REPLACED FUEL CONTROL PER MM, OPS CHECK NORMAL. MEGGED CUTOFF WIRING CHECK NORMAL. VERIFIED 28VDC FOR 5 SEC TO FCU, RAN ENG AND T/R NO FAULTS FOUND. REMOVED AND REPLACED EEC.

Part: FUEL CONTROL — FAILED (NR 1 ENGINE) · airframe 55,799 hrs · 28,703 cycles

LT ENG FAILED TO ACHIEVE T/O EPR 1.43 SCHEDULED W/NORMAL PWR GOT TO 1.3, COMMAND SELECT SHOWING, THROTTLE AT FIRE-WALL. AFTER ABORTED GOT STATUS LT ENG CONT. REPLACED FUEL CONTROL.

Part: SLIDE — INOPERATIVE · airframe 55,155 hrs · 28,431 cycles

2L SLIDE DEPLOYED BY MAINT. SLIDE REPLACEMENT IN PROGRESS.

Part: BRAKE ASSY — FIRE (LT MLG) · airframe 50,503 hrs · 26,238 cycles

ON TAXI IN LT GEAR BRAKE FIRE, EXTINGUISHED NO DAMAGE. REPLACED NR 1-2 WHEEL ASSYS ALSO NR 1 BRAKE.

Part: FAN — SEIZED (E/E BAY) · airframe 48,543 hrs · 25,343 cycles

A/C 620 FLT 739 DECLARED AN EMERGENCY AND DIVERTED TO MEM DUE TO HOT ELECTRICAL ODOR IN COCKPIT. NO ABNORMAL INDI CATIONS OR EICAS MESSAGES. UPON ARRIVAL CONTRACT MTC FOUND THE FWD EQUIPMENT COOLING SUPPLY FAN NBR 1 DPN 216001013 SERIAL NBR 1997 AT FAULT (BEARING FAILURE AND SEIZING). REPLACED SAME

Part: INDICATOR — MALFUNCTIONED (NAVIGATION) · airframe 47,628 hrs · 24,921 cycles

LOST NAV ALIGNMENT ON TAKEOFF ROLL. IN ALIGN MODE AT RETURN TO GATE. T/S PER FIM, NO PROBLEMS FOUND. REPLACED INITIAL REF MODE PANEL AS PRECAUTION. PERFORMED IRS OPERATIONAL TEST PER M/M, ALL TESTS NORMAL.

Part: LIGHT — DAMAGED (CABIN) · airframe 46,354 hrs · 24,336 cycles

FOUND BY FLT CREW SEAT 26D AFT RED EMERGENCY LIGHT MODULE PULLED OUT. REPLACED SAME.

Part: OUTFLOW VALVE — MALFUNCTIONED (CABIN)

AFTER TAKEOFF, CABIN AUTO INOP EICAS MSG AND AUTO INOP ON PRESS PANEL. OK IN MANUAL. BITE CK ON NR 1 CONT FAULTS CONT AND BITE CK ON NR 2 CONT FAULTS NR 2 AC MOTOR. REPLACED NR 1 CONT AND OUTFLOW VALVE ASSY.

Part: OVEN — DIRTY (GALLEY)

PASSING 8K' ON DEPART. F/A REPORTED SMOKE IN AFT GALLEY CEILING AREA. OVENS TURNED OFF AND C/B'S PULLED, SMOKE DISSIPATED. CHKD OVENS AND COFFEEMAKERS IN AFT GALLEY AND ALL GOOD. CHKD AFT GALLEY LIGHTS AND GOOD. DROPPED OVHD CEILING PANEL AND AREA OK. AFT LAVS AND SMOKE DETECTORS GOOD. OK FOR SERVICE. SUSPECT SPILLED FOOD IN AFT OVENS.

Part: DRAG STRUT — BROKEN (NR 2 PYLON)

PYLON NR 2 ENGINE DIAGONAL DRAG BRACE. REPAIR FOR SEVERED LUG. THE DIAGONAL DRAG BRACE ON THE NR 2 ENGINE WAS FOUND WITH A SEVERED LUG. THE DRAG BRACE WAS REPLACED AND THE PYLON INSPECTED PER ER/A373001-14.

Part: BULB — FAILED (LT WING)

LT WING FWD EMERGENCY ESCAPE PATH LIGHT INOP. RELAMPED. OP CK GOOD.

Part: BULB — FAILED (RT WING)

RT WING AFT EMERGENCY ESCAPE PATH LIGHT INOP. RELAMPED. OP CK GOOD.

Part: HYD PUMP — LEAKING (LT ENGINE)

LEFT HYD QTY DECREASED IN FLT WITH BOTH LEFT ELEC AND ENG PUMPS OFF AND PTU CB. PULLED, LOSS WAS SLOWED CONSIDERABLY. FOUND LEFT ENG PUMP PRESSURE FILTER DIFFERENTIAL BUTTON ASSY LEAKING. REPLACED BUTTON ASSY, LEFT PRESSURE AND CASE DRAIN FILTERS. NO CONTAMINATION FOUND, LEAK CKS OK (P/N 291201356).

Part: SKIN — CRACKED (NR 1 PYLON)

THE O/B SKIN OF THE NR 1 ENGINE PYLON WAS FOUND TO HAVE A CRACK CONTINUING BEYOND A PREVIOUS STOP DRILL OUT OF THE UPPER, FWD CORNER OF THE FWD ACCESS OPENING AT NS 112.92. WHEN ROUTED OUT, THE TOTAL LENGTH WAS 1.50 INCH. THE SKIN AT THIS LOCATION IS FABRICATED FROM THREE BONDED 0.080 2024-T3 CLAD SHEETS. THIS CONDITION IS ADDRESSED BY B757 SRM SECTION 54-41-01, PG 210 AND FOLLOWING. IN ADDITION, THERE WAS A CRACK OUT OF THE FWD SIDE OF THE ACCESS OPENING CENTERED AT NS 122.3. AFTER ROUTING OUT, THIS MEASURED .50.

Part: PITOT TUBE — DIRTY (LT FUSELAGE)

DURING TAXI OUT AT APPROX 10 KTS, CA AIRSPD IND AND ADI WIND ARROW READ 133 KTS. CHECKED AND FOUND BOTH UPPER AND LWR PITOT TUBES ON CA SIDE BLOCKED WITH DIRT. REPLACED BOTH TUBES AND PURGED LINES. PUMPED SYS AND LEAK CKD OPS CK GOOD.

Part: BULB — FAILED (CABIN)

DURING INSPECTION, FOUND EMERGENCY LIGHT AT R-2 DOOR INOP. RELAMPED AND CHECKS GOOD.

Part: SCAV VALVE — MALFUNCTIONED (NR 1 ENGINE)

STATUS MSG CAME ON IN FLIGHT, L OIL SCAV CLOSE. REPLACED NR 4 BEARING SCAV VALVE PER MM 79-21-12, PERFORMED PFHB TEST 11. T/O PWR ACHIEVED, LEAK CK GOOD AND ALL CKS NORMAL.

Part: RADOME — DELAMINATED (NOSE)

HAIL DAMAGE TO TOP HALF OF RADOME. REPAIRED DAMAGE AT SHOP INSPECTION PER SRM 53-10-72.

Part: FLOOR BEAM — CORRODED (FS 324)

FWD GALLEY FLOOR BEAM BS 324 UPPER CHORD CORRODED NUMEROUS AREAS ON A 4 FOOT SECTION. SPLICED IN NEW SECTION FLOOR BEAM.

Part: FLOOR BEAM — CORRODED (FS 345)

FWD GALLEY FLOOR BEAM CORRODED STA 345 RBL 36 UPPER FLANGE AREA APPROX 1 INCH BY .75 INCH. REPAIRED PER SRM 53-30-51.

Part: SKIN — DENTED (NR 5 LE SLAT)

HAIL DAMAGE TO NUMBER 5 SLAT. REPLACED WEDGE PER SRM 57-43-02.

Part: SKIN — DENTED (NR 4 LE SLAT)

HAIL DAMAGE OCCURED, T/E WEDGE HAS MANY DENTS. REPLACED T/E WEDGE PER SRM 57-43-02, FOR NR 4 L/E SLAT.

Part: FLOOR BEAM — CORRODED (FS 345)

DURING INSPECTION, FOUND FS 345 CABIN FLOOR BEAM WITH CORROSION ON THE UPPER CAP. REPAIRS WERE ACCOMPLISHED PER SRM 53-30-51 PG 217-219.

Part: SKIN — DENTED (NR 1 LE SLAT)

DURING SHOP INSPECITON, NR 1 L/E SLAT, T/E WEDGE WAS REPAIRED FOR HAIL DAMAGE PER SRM 57-43-02.

Part: TE WEDGE — DENTS (NR 8 LE SLAT)

HAIL DAMAGE ON NR 8 SLAT T/E WEDGE. REPLACED T/E WEDGE PER SRM 57-43-02.

Part: SKIN — DENTED (NR 6 LE SLAT)

DURING SHOP VISIT, NR 6 L/E SLAT WAS REPAIRED FOR HAIL DAMAGE, PER SRM 57-43-02.

Part: TE WEDGE — DENTED (NR 10 SLAT)

HAIL DAMAGE ON NR 10 SLAT. REPLACED T/E WEDGE PER SRM 57-43-02.

Part: FLOORBEAM — CORRODED (FS 1640)

FLOORBEAM CORRODED STA 1640 UPPER FLANGE. REMOVED CORR FROM UPPER FLANGE FWD FLANGE, WITHIN LIMITS PER SRM 53-00-51 FIG 101. DRILLED UP REPAIR, APPLIED ALODINE AND EPOCART 15-11 TO DAMAGED AREA PAINTED AND INSTALLED REPAIR.

Part: FLOORBEAM — CORRODED (FS 1661)

FLOORBEAM CORRODED AT AFT GALLEY STA 1661 LBL 48 AND LBL 54C. REMOVED CORROSION FROM BEAM UPPER FLANGE .030 AT LBL 48 AND LBL 54. MANUF PARTS PER SRM, INSTALLED DOUBLERS.

Part: SKIN — DAMAGED (LT SPOILER)

NR 4 SPOILER PANEL, WAS FOUND WITH HAIL DAMAGE TO UPPER SKIN. REPAIRED PER SRM 51-70-17 AND ERA 270835-14.

Part: TE WEDGE — DAMAGED (NR 1 LE FLAP)

LEFT WING NR 1 L/E SLAT TRAILING EDGE WEDGE, WAS FOUND DAMAGED FROM HAIL. WEDGE WAS REPLACED PER SRM 57-43-02.

Part: SKIN — DAMAGED (LT SPOILER)

NR 1 SPOILER PANEL, WAS FOUND WITH HAIL DAMAGE TO UPPER SKIN. REPAIRED AREA PER SRM 51-70-17.

Part: SKIN — DAMAGED (LT SPOILER)

NR 5 SPOILER PANEL WAS FOUND WITH HAIL DAMAGE TO UPPER SKIN. REPAIRED PER SRM 51-70-17, 57-70-01 AND ERA 270835-14.

Part: SKIN — DAMAGED (NR 6 SPOILER)

NR 6 SPOILER PANEL, WAS FOUND WITH HAIL DAMAGE TO UPPER SKIN. REPAIRED PER SRM 57-70-01.

Part: TE WEDGE — DAMAGED (NR 9 LE SLAT)

RT WING NR 9 L/E SLAT TRAILING EDGE WEDGE, WAS FOUND WITH HAIL DAMAGE. REPLACED WEDGE PER SRM 57-43-02.

Part: TE WEDGE — DAMAGED (NR 3 LE FLAP)

LEFT WING NR 3 L/E SLAT TRAILING EDGE WEDGE, WAS DAMAGED BY HAIL. REPLACED WEDGE PER SRM 57-43-02.

Part: TE WEDGE — DAMAGED (NR 3 SLAT)

LEFT WING NR 5 SLAT PANEL TRAILING EDGE WEDGE WAS FOUND WITH DENTS FROM HAIL. REPLACED T/E WEDGE PER SRM 57-54-02.

Part: SKIN — DAMAGED (NR 8 SPOILER)

NR 8 SPOILER PANEL WAS FOUND WITH DAMAGE TO UPPER SURFACE FROM HAIL. REPAIRED SPOILER PER SRM 51-70-17.

Part: SKIN — DAMAGED (LT TE FLAP)

LEFT WING AFT FLAP PANEL SUSTAINED HAIL DAMAGE TO UPPER SURFACE. REPAIRS WERE ACCOMPLISHED PER SRM 57-53-01 WITH REF TO SRM 51-70-05.

Part: SKIN — DAMAGED (RT ELEVATOR)

RIGHT ELEVATOR SUSTAINED HAIL DAMAGE TO UPPER SURFACE. REPAIRS WERE ACCOMPLISHED PER SRM 55-20-01 PG 202 TABLE 1.

Part: SKIN — DAMAGED (RT AILERON)

RIGHT WING AILERON UPPER SURFACE WAS FOUND WITH HAIL DAMAGE. REPAIRS WERE ACCOMPLISHED PER SRM 57-60-01.

Part: TE WEDGE — HAIL DAMAGE (NR 2 LE SLAT)

THE BOEING 757 NR 2 LEADING EDGE SLAT RECEIVED CONSIDERABLE HAIL DAMAGE TO THE TRAILING EDGE WEDGE. THE SLAT WAS RECEIVED INTO THE SHOP AND THE WEDGE WAS REPLACED PER SRM 57-43-02 FIG 202.

Part: TE WEDGE — DENTED (NR 9 LE SLAT)

REPLACED TRAILING EDGE WEDGE ON NUMBER 9 LEADING EDGE SLAT AS PER SRM REF 57-43-02, DURING SHOP VISIT FOR HAIL DAMAGE.

Part: SLAT — DENTED (NR 7 SLAT)

NR 7 SLAT HAIL DAMAGE. REPLACED T/E WEDGE PER SRM 57-43-02, DURING SHOP VISIT.

Part: POWER SUPPLY — FAILED (CABIN EEL)

DURING INSPECTION, FIRST CLASS FLOOR TRACK LIGHTS FAILED TO TEST. REPLACED POWER SUPPLY, OPERATION NORMAL.

Part: GASKET — LEAKING (NR 2 IDG)

DURING CRUISE WITH NR 2 IDG ON MCO, APU FLAMED OUT, DIVERTED DFW. PEFORMED BITE CHECK ON APU CONTROLLER AND HAD SEVERAL SUCCESSFUL STARTS. NR 2 IDG HAD LEAKING GASKET, REPLACED GASKET, RETURNED TO SERVICE.

Part: STRUCTURE — CRACKED (NR 2 PYLON)

DURING L/O, NR 2 ENG WAS REMOVED FOR SCHEDULED MAINTENANCE, FOUND A 1.5 INCH CRACK IN THE INBOARD WEB OF PYLON STRUCTURE AT THE FWD INSPECTION HOLE. REPAIRED PER SRM 54-51-01 FIG 203.

Part: SKIN — DAMAGED (NR 3 FORE FLAP)

DURING LETTER CHECK, RIGHT WING NR 3 FWD FLAP WAS FOUND WITH A DENT IN THE LOWER SKIN AT STA 86. REPAIRED DAMAGE PER SRM 57-53-01.