N528MC

Part: NOZZLE — DENTED (NR 1 ENGINE) · airframe 80,646 hrs · 16,068 cycles

NR 1 ENGINE EXHAUST NOZZLE DENTED AT 0300. NDT CHECKED NIL CRACK DENT AREA WITHIN LIMITS AMM 78-11-01 PAGE 601.

Part: NOZZLE — DENTED (EXHAUST) · airframe 80,646 hrs · 16,068 cycles

NR 4 ENGINE EXHAUST NOZZLE EXTERIOR SKIN DENTED AT 0700 TO 0900. NDT CHECKED NIL CRACK DENT AREA WITHIN LIMIT AMM 78-11-01 PAGE 601.

Part: WEB — CORRODED (BS 1980-2030) · airframe 80,646 hrs · 16,068 cycles

BULK CARGO BS 1980-2030 DOOR LOWER SILL FLOOR WEB, CORRODED. CORROSION REMOVED AND REPROTECTED AS PER SRM 51-10-01 AND SRM 51-10-02 WITHIN ALLOWABLE LIMIT AS PER SRM 53-10-01.

Part: WEB — CRACKED (TE FLAP) · airframe 80,646 hrs · 16,068 cycles

UPON L/E CAP REMOVAL OLES 1522, NR 26VC FLAP UPPER STOP FTG FWD WEB DOUBLER FOUND CRACKED. DOUBLER REPLACED IAW SRM 51-10-01.

Part: PANEL — CONTAMINATED (RT WING TE FLAP) · airframe 80,646 hrs · 16,068 cycles

RT WING I/B T/E PANEL FOUND WATER. REPLACE RHW I/B T/E PANEL AS PER SRM 51-10-01 AND SRM 51-30-02.

Part: NOZZLE — DENTED (ZONE 400) · airframe 80,646 hrs · 16,068 cycles

NR 3 ENGINE EXHAUST NOZZLE EXTERIOR SKIN DENTED AT 0900. NDT CHECKED NIL CRACK DENT AREA WITHIN LIMIT AMM 78-11-01 PAGE 601.

Part: FRAME — CRACKED (ZONE 200) · airframe 80,646 hrs · 16,068 cycles

R1 MED LOWER AFT CORNER FRAME CRACKED AT STA 490 RT S-25R TO S-26R AREA. C/OUT AS PER SRM 52-10-02 FIG 10.

Part: DOOR FRAME — CRACKED (BS 1670) · airframe 80,646 hrs · 16,068 cycles

M/D R4 MED FWD UPPER CORNER FRAME CRACKED AT STA 1670 S-16R TO S-17R AREA. CARRY OUT REPAIR AS PER SRM 52-10-02, FIG 10.

Part: FRAME — CRACKED (ZONE 600) · airframe 80,646 hrs · 16,068 cycles

AFT REMOVAL OF L/E NOSE CAP FOUND THAT "D" SECTION CRACKED. CARRY OUT REPAIR AS PER SRM 57-20-03.

Part: WEB — CRACKED · airframe 80,646 hrs · 16,068 cycles

OLEO 1450 FWD CRACKED JUST FWD OF NR 25 V/C FLAP UPPER FITTING. CARRY OUT REPAIR AS PER SRM 51-40-03.

Part: DOOR FRAME — CRACKED (BS 1275) · airframe 80,646 hrs · 16,068 cycles

R3 DOOR FWD UPPER CORNER FRAME FOUND CRACKED. C/OUT AS PER SRM 52-10-02, FIG 10.

Part: PAN — CRACKED (COCKPIT SEAT) · airframe 80,646 hrs · 16,068 cycles

COCKPIT 2ND OBSERVER SEAT PAN CRACKED. REPAIRED IAW BOEING MESSAGE NR 1-497681686-1.

Part: PANEL — CONTAMINATED (ZONE 200) · airframe 80,646 hrs · 16,068 cycles

LT WING T/E I/B PANEL FOUND WATER. REPLACE LHW T/E I/B FIXED PAL AS PER SRM 51-10-01 AND SRM 51-30-02, AND PANEL REPAIR IAW BOEING MESSAGE 31-516595696-1 TO 1-516595696-4.

Part: SKIN — DENTED (RT ELEVATOR) · airframe 80,646 hrs · 16,068 cycles

HORIZONTAL STAB RT I/B ELEVATOR L/E UPPER SKIN DENTED. REPAIRED IAW BOEING MESSAGE SR 1-514407012.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 80,646 hrs · 16,068 cycles

FLOOR STRUCTURE BEAM WEB CRACKED. REPAIRED IAW BOEING MESSAGE NR 1-497681686-1.

Part: HINGE FITTING — CRACKED (HORIZONTAL STAB) · airframe 80,646 hrs · 16,068 cycles

BS 2598 H/S RT RBL 40" REAR SPAR UPPER I/B OF HINGE FITTING OPEN HOLE. OVERSIZE TO 0.403", USED BACB30 US6K21Y BOLT. CARRIED OUT NDT TEST OF THE OPEN OVERSIZE HOLE FOUND SATISFACTORY.

Part: FLOORBEAM — CRACKED (BS 1220) · airframe 80,646 hrs · 16,068 cycles

FLOOR STRUCTURE BEAM WEB CRACKED. C/OUT AS PER BOEING MESSAGE NR 1-497681686-1.

Part: FRAME — CRACKED (BS 800 S17L) · airframe 80,646 hrs · 16,068 cycles

BS 800 S17 LT ONE FASTENER HOLE FOUND CRACK ON FWD INNER CHORD ANGLE. REPLACEMENT PER BOEING CONTROL NO PO24708.

Part: ACCESS PANEL — ELONGATED (A/C BAY) · airframe 80,646 hrs · 16,068 cycles

AIR COND, BAY ACCESS PANEL 192ER EXT SURFACE FOUND SKIN ELONGATION. AIR COND BAY ACCESS PANEL 192ER REPAIRED WITH PRE-PRED FABRIC AS PER MESSAGE NR 1-497468248-2.

Part: SKIN — DENTED (BS 780) · airframe 80,646 hrs · 16,068 cycles

FX EXTERIOR SKIN DENT AS MARKED APPR, 1" SQ IN AT BS 780 S47-R. REINSTALLED A REPAIRED DOUBLER AS PER SRM 53-30-03 DETAILS AS PER SWS SHOWN.

Part: ACCESS PANEL — DELAMINATED (ZONE 100) · airframe 80,646 hrs · 16,068 cycles

AIR COND, BAY ACCESS PANEL 192HR EXT SURFACE FOUND SKIN DELAMINATION. AIR COND BAY ACCESS PANEL 192HR REPAIRED WITH PRE-PRED FABRIC AS PER MESSAGE NR 1-497468248-2.

Part: TORQUE LINK — CHAFED (NLG) · airframe 80,646 hrs · 16,068 cycles

NLG LOWER TORSION LINK FOUND CHAFING. BLEND OUT THE CHAFING AREA WITH MIN 20-1 BLEND-RATIO.

Part: ACCESS PANEL — ERODED (A/C BAY) · airframe 80,646 hrs · 16,068 cycles

AIR COND, BAY ACCESS PANEL 191HL EXT SURFACE FOUND ERODED. AIR COND BAY ACCESS PANEL 191HL REPAIRED WITH PRE-PRED FABRIC AS PER MESSAGE NR 1-497468248-2.

Part: UNKNOWN — ODOR (COCKPIT) · airframe 80,389 hrs · 16,014 cycles

AT DEPARTURE SMOKE AND BURNING ODOR IN COCKPIT, ELECTRICAL ODOR. PULLED C/BS FOR T/R UNITS, SMOKE AND ODOR STOPPED. WIRE BUNDLES AND AREA BELOW F/E PANEL (4) INSPECTED NO SIGN OF SHORTING OR CHAFING FOUND. PULLED T/R UNITS, PULLED AND INSPECTED FOUND NR 1 T/R UNIT VERY HOT AND WITH BURNED ODOR. NR 1 T/R TRANSFERRED TO DMI M07-134 IAW MEL 24-8. DDPG MAINT STEPS C/W ALL TEST PASS.

Part: SEAL — LOOSE (L3 WINDOW) · airframe 80,333 hrs · 16,000 cycles

L-3 WINDOW SEAL LIFTING IN THE WIND WITH EXCESSIVE COCKPIT NOISE. ALSO, DURING LEVEL FLIGHT APPROX TIME 1335Z FL 31.0 TEMP -09 TAT HEARD BANG AIRCRAFT SHOOK, POSSIBLE ENGINE STALL. AUTO THROTTLES TRIPPED OFF SEVERAL TIMES IN FLIGHT. RESECURED WINDOW SEAL IAW 56-11-00. INSPECTED INTAKES AND EXHAUST OF ALL ENGINES WITH NO FINDINGS. INSPECTED FUSELAGE IAW 5-51-00, NO FINDINGS.

Part: FAIRING — CRACKED (FLAP TRACK) · airframe 80,245 hrs · 15,985 cycles

RT WING NR 7 FLAP TRACK CANOE FAIRING DAMAGED AT LOWER SIDE, AFT OF ACCESS PANEL 667CB. ACCOMPLISHED PERMANENT REPAIR AS PER 747-200 SRM 51-40-09, FIG 6 TABLE I AND 747-200 SRM 51-40-12. ALSO REFERENCE ATLAS AIR XEO NR 57-061907.

Part: SKIN — DELAMINATED (THRUST REVERSER) · airframe 80,245 hrs · 15,985 cycles

NR 4 ENGINE RT REVERSER AT NAC STATION 206.10 UPPER SIDEWALL SKIN DELAMINATED. PERMANENT REPAIR WAS ACCOMPLISHED AS PER CF6-50 ENGINE MANUAL 78-32-03, REPAIR NR 13, REF: FIG 1. ALSO, REFERENCE ATLAS AIR XEO NR 78-062007.

Part: SUPPORT — CORRODED (BS 1112) · corrosion level 2 · airframe 80,245 hrs · 15,985 cycles

LOWER FUSELAGE AIR CONDITIONING ACCESS DOOR AREA, BELOW KEEL BEAM BOX, EXTERIOR CENTER PANEL SUPPORT EXTRUSION HAS CORROSION. PERMANENT REPAIR WAS ACCOMPLISHED AS PER 747-200 SRM 51-40-04, FIG 1. ALSO REFERENCE ATLAS AIR XEO NR 53-062007.

Part: PANEL — CORRODED (BS 1112) · corrosion level 2 · airframe 80,245 hrs · 15,985 cycles

LOWER FUSELAGE CENTER PANELS 191HH AND 191JJ BETWEEN NR 1 AND NR 3 ACM'S HAVE AREA OF CORROSION. PERMANENT REPAIR WAS ACCOMPLISHED AS PER 747-200 SRM 51-40-02 FIG 1. ALSO, REFERENCE ATLAS AIR XEO NR 53-062007.

Part: FAIRING — DAMAGED (FLAP TRACK) · airframe 80,245 hrs · 15,985 cycles

RT WING, NR 8 FLAPTRACK FORWARD FIXED FAIRING HAS SEVERAL SMALL HOLES AT LEADING EDGE AREA. ACCOMPLISHED PERMANENT REPAIR AS PER 747-200 SRM 51-40-09, FIG 6, TABLE I AND 747-200 SRM 51-40-12. ALSO, REFERENCE ATLAS AIR XEO NR 57-061907.

Part: SKIN — CRACKED (BS 2650-2658) · airframe 79,659 hrs · 15,864 cycles

FUSELAGE SKIN HAS 12" CRACK FROM STA 2650 TO 2658 ON RIGHT SIDE OF AIRCRAFT BETWEEN STRINGERS 11R AND 13R. FOUND CRACKED IN A SEMI-CIRCULAR SHAPE. REPAIRED PER SRM 53-30-03 FIG 1 DETAIL L AND XEO 53-04-06-07. (TIME LIMITED REPAIR)

Part: ALTIMETER — FAULTY (COCKPIT) · airframe 79,103 hrs · 15,749 cycles

CAPT ALT UNRESPONSIVE TO ALL CHANGE BOTH CADC/STBY MODES, PERFORMED CHECK DIFFERENCE BETWEEN ALT INDICATORS (3,34,7), CHANGE ALT LAGS IN DESCENT BY OVER 300' AND DIFFERS BY OVER 180' AT EL 290-310-MACH .84. T/S AND FOUND PIN NR 22 AT PLUG DN 101. CAPT ALT INDICATOR WIRE BROKEN, REPAIRED WIRING PER WDM 34-12-12. ALSO, R/R WITH NEW CAP ALT INDICATOR AS PRECAUTIONARY AS PER MM 34-13-04. PERFORMED PRIMARY ALT TEST AS PER AMM 34-13-04, ALL OPS CHECK NORMAL.

Part: CADC — STICKING (ALTIMETER) · airframe 79,072 hrs · 15,742 cycles

DURING CLIMB CAPT ALTIMETER NEEDLE WOULD STICK IN POSITION CAUSING PULL-UP TERRAIN WARNINGS, DON’T SINK WARNING AUDIBLES, ALTIMETER READ 37.0, ATC 36.8. PERFORMED STATIC SYSTEM LEAK CHECK NORMAL AS PER MM 34-11-00. FOUND NR 1 CADC DEFECTIVE. REMOVED AND REPLACED CADC PER MM 34-12-01. SYSTEM TEST NORMAL AND IAWS TEST NORMAL AS PER 34-11-00/34-46-01.

Part: ALTIMETER — STICKING (COCKPIT) · airframe 79,072 hrs · 15,742 cycles

DURING CLIMB CAPT'S ALTIMETER NEEDLE WOULD STICK IN POSITION CAUSING PULL-UP TERRAIN WARNING, DON'T SINK WARNING AUDIBLES. CAPT'S ALTIMETER REMOVED AND REPLACED, INDICATION AND LEAK CHECK CARRIED OUT, OK IAW MM 34-13-04.

Part: PANEL — CRACKED (LT WING) · airframe 79,038 hrs · 15,737 cycles

LT WING PYLON GAP PANEL AT ILES 640.47 HAS A 3.0 INCH CRACK. ACCOMPLISHED PERMANENT REPAIR AS PER 747 SRM 51-40-09 FIG 18 SHEET 5 AND SRM 51-40-12, ALSO REFERENCE ATLAS AIR EO 4757A342.

Part: PANEL — CRACKED (LT WING) · airframe 79,038 hrs · 15,737 cycles

LT WING UPPER FIXED PANEL, 12 INCHES FROM FORWARD EDGE OF NR 5 SPOILER, WBL 421.00 HAS A 6.0 INCH CRACK. ACCOMPLISHED PERMANENT REPAIR AS PER 747 SRM 51-40-09 FIG 2 SHEET 5 AND SRM 51-40-12 AND ATLAS AIR EO 4757A342.

Part: SKIN — PUNCTURED (SLATS) · airframe 78,406 hrs · 15,606 cycles

NR 21 LEADING EDGE DEVICE FOLDING NOSE FOUND DAMAGED ON ARRIVAL. NOSE HINGE ARM FOUND BROKEN AND SKIN PUNCTURED. UNABLE TO CONCLUSIVELY DETERMINE THE REASON FOR THE FAILURE AND SUBSEQUENT DAMAGE. REPLACED NR 21 LEADING EDGE DEVICE ASSY.

Part: DUCT — RUPTURED (NR 4 ENGINE) · airframe 77,188 hrs · 15,337 cycles

FOLLOWING TAKEOFF NR 4 ENG FIRE INDICATIONS NACELLE TEMPS A/B HIGH, THEN TO FIRE "F" AND FULL WARNING ENG NR 4 SHUTDOWN AS PER CHECKLIST. NR 4 ENG FIRE BOTTLE "A" DISCHARGED, FIRE WARNING EXTINGUISHED. FOUND 14TH STAGE BLEED AIR DUCT RUPTURE. REMOVED AND REPLACED DUCT AS PER MM 36-11-01. PFMD ENG TEST NR 4 AS PER MM 71-00-00. ALL INDICATION NML, DUCT LOCATION ENG RT SIDE. REMOVED AND REPLACED RT "A" FIRE EXTINGUISHER CONTAINER AS PER MM 26-21-03. ACCOMPLISHED EXTINGUISHER AGENT CONTAMINATION CHECK AS PER MM 72-00-00. CHECKS OK.

Part: SKIN — DENTED (THRUST REVERSER) · airframe 80,245 hrs · 15,985 cycles

NR 4 ENGINE LT REVERSER HAS DENT ON UPPER SIDE OF TRANSLATING COWL AT NAC STATION 224.6. PERMANENT REPAIR WAS ACCOMPLISHED AS PER CF6-50 ENGINE MANUAL 78-32-01, REPAIR 003. ALSO, REFERENCE ATLAS AIR XEO NR 78-062107.

Part: HYDRAULIC LINE — CRACKED (HYDRAULIC SYS) · airframe 77,051 hrs · 15,311 cycles

DURING CLIMB NR 4 HYD SYSTEM STARTED DECREASING AND LOW QUANTITY LIGHT CAME ON. FHB PROCEDURES C/W AND QUANTITY WAS STILL DECREASING. ENG PUMP SWITCH WAS POSITIONED TO "SUPPLY OFF" WITH ENGINE RUNNING. QUANTITY INDICATOR ZERO AT COMPLETION OF CHECKLIST. FOUND HYD FLEXLINE AT LEFT WING GEAR DOWNLOCK ACTUATOR ASSY UNLOCK LINE LEAKING. REMOVED AND REPLACED HYD FLEX LINES PER GMM 7.4.1. REMOVED AND REPLACED NR 4 HYD PUMP AND CASE DRAIN FILTER AS PER AMM 29-11-03/05.

Part: START VALVE — DAMAGED (NR 4 ENGINE) · airframe 77,050 hrs · 15,311 cycles

NR4 ENGINE SHUT DOWN AT 1945Z DUE TO NR 4 START VALVE ENGINE LIGHT FLICKERING AND THEN COMING ON. REMOVED AND REPLACED NR 4 START VALVE AS PER AMM 80-11-04. PERFORMED GROUND OPS BY MONITORING SATISFACTORY.

Part: SEAL — DAMAGED (NR 1 ENGINE) · airframe 76,886 hrs · 15,282 cycles

ACCOMPLISHED AIR TURNBACK DUE TO LOSS OF ALL OIL IN ENGINE NR 1, DURING CLIMBOUT. FOLLOWED SHORTLY BY A DROP IN OIL PRESSURE INTO THE MID TO LOWER AMBER BAND. FOUND NR 1 ENGINE HYD PUMP SHAFT SEAL CAVITY LEAKING OIL DURING IDLE RUN. HYD (EDP) PUMP SHAFT SEAL FOUND TO BE DAMAGED. REPLACED PER MM 29-11-05. NR 1 ENGINE SERVICED WITH 10 QTS.

Part: RELIEF VALVE — LEAKING (NR 1 ENIGNE) · airframe 76,886 hrs · 15,282 cycles

AT 3000 FT DURING CLIMBOUT FIRE DETECTION LIGHT ON PILOT'S CENTER ANNUNCIATOR PANEL ILLUMINATED, FOLLOWED SHORTLY BY A FIRE INDICATION ON NR 1 ENGINE. FIRE CAUSED SEVERE DAMAGE OR SEPARATION, CHECKLIST COMPLETE AS PER FHB 3.701. OVERWEIGHT LANDING AT 287.0 KG. FOUND NR 1 ENG PRESS RELIEF VLV AND PRESS REGULATING VLV, FOUND TO BE RELIEVING VIOLENTLY. (REFER PAD 250 LP 581351 ITEM 1 I.E. DAMAGED TO LT C-DUCT) AND LEAKING AT BODY. LP 101050 ITEM 1. ALL REPLACED. H1 POWER RUN C/OUT NAC. TEMP OK.

Part: PANEL — MISSING (NR 1 NACELLE) · airframe 75,906 hrs · 15,101 cycles

ON WALKAROUND FOUND NR 1 ENGINE LOWER ACCESS PANEL MISSING.

Part: CADC — FAILED (NR 2)

HKG/BEL - AFTER DEPARTURE NR 2 ALTIMETER BECAME ERRATIC WITH ALT ALERT SOUNDING ENTER FOLLOWED BY AIRSPEED MACH INDICATOR FLAG AND SAT IND OF .05, SUSPECT RN 2 CADC FAILED. CHANGED NR 2 CADC IAW MM 34-12-01/401. CADC NR 2 OPERATIONAL TEST IAW MM 34-12-00 SATISFACTORY. PITO/STATIC SYSTEM CHECK CARRIED OUT SATISFACTORY. NO LEAKAGE, AIRSPEED AND ALTIMETER READING AGREE WITH TESTER. (M)

Part: BULKHEAD — CORRODED (FUSELAGE)

DURING SCHEDULED MAINTENANCE, FS 1350 BULKHEAD WED FOUND CORRODED NEAR STRINGER 1L LEVEL OF CORROSION, LEVEL 1, MINOR. TRIMED OUT CORRODED AREA. REMOVED NICKS, SCRATCHES, GOUGES, BURRS AND SHARP EDGES FROM THE REPAIR PART. PERFORMED HFEC INSPECTION TO ENSURE CRACK FREE CONDITION. REPAIR DOUBLER WAS MADE FROM .063 INCH THICK 7075-T6 MATERIAL. (M)

Part: FRAME — CRACKED (BS 1265)

DURING CURRENT C-CHECK AT IAI, FOUND CRACK IN FRAME WEB AT BS 1265 WL 199 L/S CRITICAL HOLE. CRACK LENGTH IS 1MM. DURING CRACK REMOVAL BY REAMING THE FRAME WEB AND INNER CHORD WERE MISDRILLED. FRAME WEB ONLEY OVERSIZED TO .419 INCH. PERFORMED OPEN HOLE INSPECTION OF REMOVED FASTENERS AND SURFACE E/C INSPECTED THE EDGE OF THE WEB. NO OTHER CRACKING FOUND. FABRICATED FREEZE PLUGS AND ANGLES. PRIME PAINTED ANGLES. INSTALLED FREEZE PLUGS IAW SRM 51-10-08. INSTALLED REINFORCING ANGLES WET WITH SEALANT PER STANDARD SRM PRACTICES. REINSPECTION REQUIRED AT 2000 CYCLE INTERVALS WITH REPAIR LIMITED TO 4000 CYCLES. INSPECTION REQUIRES REMOVAL OF THE REINFORCING ANGLES AND FREEZE PLUGS. (M)

Part: FITTING — DAMAGED (NR 4 MID FLAP)

DURING CURRENT C-CHECK AT IAI, FOUND NR 4 INBOARD MID FLAP CARRIAGE SUPPORT RIB FITTING WITH ELONGATED MOUNT HOLES. HOLES OVERSIZED TO OBTAIN A CLEAN ROUND HOLE. PERFORMED OPEN HOLE E/C CHECK TO INSURE CRACK FREE CONDITION. NO CRACKS FOUND. FABRICATED REPAIR SLEEVES. INSTALLED INTERFERENCES SLEEVES PER STANDARD SRM PRACTICES AS REQUIRED. PRIME PAINTED AREA. REINSTALLED REMOVED PARTS WITH OVERSIZED FASTENERS PER APPLICABLE INSTRUCTIONS. FITTING P/N 65B02061-7. (M)

Part: SKIN — CRACKED (BS 1814)

DURING HFEC INSPECTION PER SB 747-53A2488 FOUND LOWER LOBE AFT CARGO COMPT DOOR UPPER FORWARD CUTOUT WITH TWO CRACK INDICATIONS, ONE FROM FASTENER HOLE TO RADIUS CUTOUT, THE OTHER 7MM LONG FROM FASTENER HOLE. AREA TRIMMED OUT. FILLER AND STACK DOUBLER FABRICATED AND INSTALLED PER STANDARD SRM PRACTICES WITH 300 CYCLE REPETITIVE THEREAFTER. (M)

Part: BULKHEAD — CRACKED (NR 4 PYLON)

DURING INSPECTION OF NR 4 PYLON, FOUND THE REAR ENGINE MOUNT BULKHEAD UPPER T-CHORD L/S CRACKED (R/S PREVIOUSLY REPAIRED). TRIMMED CRACK AREA AWAY. OVERSIZED HOLES IN AFFECTED AREA. HFEC INSPECTED HOLES TO ENSURE CRACK FREE AREA. NO CRACKS FOUND. INSTALLED OVERSIZED FASTENERS PER SRM 51-30-02 AND 51-30-05. REPAIR IS INTERIM REPAIR AND MUST BE VISUALLY INSPECTED EVERY C-CHECK NOT TO EXCEED 18 MONTHS. (M)

Part: FITTING — CORRODED

DURING INSPECTION OF REMOVED LANDING GEAR FOUND CORROSION PITTING ON THE INBOARD TRUNNION SUPPORT BUSHING CAP OF THE LEFT BODY LANDING GEAR EXCEEDING SRM LIMITS. CORROSION CLEANED UP BY BLENDING AFFECTED AREAS. AREAS PLOTTED, MEASURED AND TREATED PER STANDARD SRM PRACTICES. GEAR REINSTALLED. DATA SENT TO BOEING FOR APPROVAL. REWORK CONSIDERED A PERMANENT REPAIR PER BOEING WITH NO REPETITIVE INSPECTIONS REQUIRED. (M)

Part: DOUBLER — WORN

DURING INSPECTION OF NR 3 PYLON ACCESS PLATE CUTOUT (473AR) NAC STATION 290 WL 145, THE CONTACT AREA OF THE INNER SKIN TO LATCHES WAS FOUND WORN (THREE PLACES). AREAS TRIMMED OUT. HFEC INSPECTED AREAS FOR CRACKS, NONE FOUND. FABRICATED AND INSTALLED CRES-STEEL WEAR PLATES IN THE AREAS OF THE LATCH TO SKIN CONTACT SURFACES PER BOEING TELEX. AREA TO BE VISUALLY REINSPECTED AT SUBSEQUENCE C-CHECKS NOT TO EXCEED 18 MONTHS. (M)

Part: FITTING — CRACKED (FUSELAGE)

DURING HFEC INSPECTION PER SB 53A2390R1, FOUND BS 1480 L/S SPLICE PLATE FITTING HOLES NR 9 AND 10 WITH CRACK INDICATIONS. REMOVED LONGERON EXTENSION STRAP. REAMED HOLES TO REMOVE CRACKS. CONFIRMED NO CRACKS. FABRICATED BUSHINGS AND INSTALLED PER STANDARD PRACTICES IAW 747-53A2390R1 TO NOMINAL SIZE OF .5625 INCH DIAMETER. REINSTALLED LONGERON EXTENSION STRAP. REPEAT INSPECTION INTERVAL REDUCED BY 6000 CYCLES TO A THRESHOLD OF 12000 INITIAL AND 3500 REPETITIVE THEREAFTER. (M)

Part: FRAME — CRACKED (PAX)

DOOR L5 FRAME CRACK INDICATION ON LOWER FORWARD FRAME NEAR DOOR FITTING CUTOUT. CONFIRMED CRACK INDICATION WITH FPI.. REPLACED FRAME P/N 65B05000-263 PER SRM 51-10-01. (M)

Part: BOLT — LOOSE (NR 2 TE AFT FLAP)

INSPECTION OF NR 2 INBOARD AFT FLAP TRACK CARRIAGE BOGIE PIN ASSY REVEALED SAFETY BOLT MIGRATED OVER .50 INCH. NO PIN MIGRATION DUE PIN HELD IN PLACE BY ROLLER SUPPORT ROD. THIS CONFIGURATION DOES NOT REQUIRE SAFETY WIRE FROM BOLT TO PIN. REMOVED BOLT, INSPECTED, FOUND OK. RE-INSTALLED AND TORQUED TO 240 INCHES - 260 INCHES PER BOEING RECOMMENDATION. RE-TORQUED REMAINING SEVEN POSITIONS PRECAUTIONARY. ATLAS AIR IS CURRENTLY PROCESSING AN FCD TO INSPECT THE REMAINDER OF THE -200 FLEET. ATLAS WILL ALSO CREATE A TASK CARD TO ROUTINELY RE-TORQUE SAFETY BOLT DURING A-CHECKS UNTIL THE PIN AND BOLT COMBINATION CAN BE REPLACED WITH A DRILLED ASSEMBLY. (X)

Part: CARD — LOOSE (FIRE CONTROL)

FLT C1366 - ATO-AUH - AT APPROX 90 KNOTS, ENGINE FIRE BELL SOUNDED AND REJECTED TAKEOFF PROCEDURES ACCOMPLISHED. NO ENGINE OR APU FIRE LIGHTS 'ON'. COULD NOT SILENCE BELL USING NORMAL RESET. HIT COVER ON FIRE WARNING CONTROL MODULE AND BELL SILENCED. DURING TROUBLESHOOTING FOUND THAT FIRE WARNING CONTROL MODULE RECEPTACLE FOR CARDS A6, A8 AND A9 WERE NOT PROPERLY SECURED. REMOVED ALL CARDS, REPAIRED RECEPTACLES AND REINSERTED CARDS FROM APU POSITION IN ENGINE POSITION A8 AND A9. OPERATIONAL CHECK NOW NORMAL. DEFERRED APU FIRE WARNING UNIT CARD ARE REPLACED. (M)

Part: NLG — MALFUNCTIONED (NOSE)

ANC - DURING APPROACH, 'NOSE GEAR DID NOT EXTEND NORMALLY - MANUAL EXTENSION OK'. CHECKED RIGGING OF NOSE GEAR SEQUENCE VALVE LOCK MECHANISM AND ACTUATOR AND FOUND SAME TO BE NORMAL. PERFORMED GEAR EXTENSION/RETRACTION CHECK PER MM 32-34-00, AND NO DEFECTS FOUND, OPERATION NORMAL. (X)