N540MC

Part: LATCH — BROKEN (ACCESS DOOR) · airframe 108,575 hrs · 19,152 cycles

DURING MX WALKAROUND OF ACFT, REVEALED NR 1 ENGINE THRUST REVERSER LOWER AFT ACCESS DOOR AND BLOWOUT DOOR WERE FOUND OPENED. UPON FURTHER INSP, MX FOUND THE AFT TENSION LATCH BROKEN. (DISPOSITION IS TO ACCOMPLISH A TIME LIMITED REPAIR BY INSPECTING THE 2 OTHER TENSION LATCHES, REINSPECT AFTER EVERY FLIGHT CYCLE, AND PERMANENT REPAIR WITHIN 15 FLIGHT CYCLES.)

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 107,948 hrs · 19,016 cycles

DURING MX WALKAROUND, MX FOUND THE MAIN DECK - MDSCD AREA - BS1910 ROLL OUT GUIDE - DOUBLER CRACKED (REF FIG 1). THE DAMAGE EXCEEDS THE ALLOWABLE LIMITS IAW AMM 25-58-00. DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, DVI INSPECTIONS AFTER EVERY 5 FLIGHT CYCLES UNTIL ACCOMPLISHMENT OF PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 1,000 FH (FLIGHT HOURS) AFTER PART 1.

Part: SLEEVE — CRACKED (EXHAUST NOZZLE) · airframe 105,084 hrs · 18,436 cycles

DURING MX WALK AROUND, MX FOUND 2 EA CRACK ON THE EXHAUST NOZZLE OUTER SLEEVE, NR1 STARTING AT APPROX THE 7 O'CLOCK POSITION. THE CIRCUMFERENTIAL CRACK IS APPROX 3.0 IN LONG, THE NR2 CRACK IS LOCATED AT INBD SIDE AND AFT OF EXHAUST CONE AREA MEASURING 0.750 IN LONG. (SRM 54-41-30 THE LENGTH OF THE CRACK NR1 IS OUT OF LIMITS. DISPOSITION IS TO STOP DRILL THE ENDS OF THE CRACK WITH A 0.125 IN. DIAMETER HOLE (DRILL BIT); DVI EVERY 3 FLIGHT CYCLES; AND REMOVAL OF THE PART PRIOR TO THE ACCUMULATION OF 25 FC (FLT CYCLES) AFTER PART 1.)

Part: TIRE — FAILED (MLG) · airframe 107,606 hrs · 19,012 cycles

MLG WHEELS NR 2, 4, 6, 8 HAD THERMAL DISCHARGE AT GATE. (REPLACED NR 2, 4, 6, 8 WHEELS. SPIN AND LEAK CHECK OK. ANTI SKID TEST AND CHAPTER 5-51-26 INSP ACCOMPLISHED AND ALL NORMAL.)

Part: METERING VALVE — INOPERATIVE (MLG) · airframe 107,154 hrs · 18,924 cycles

WITH TAKEOFF POWER SET, ACFT PULLED RT. TAKEOFF ABANDONED AT 40 KNOTS, ENGINE POWER EVEN. (INSPECTED CABLE RUNS AND PULLEYS, CHECKED CABLE TENSIONS, NO DEFECTS NOTED. PERFORMED RIG CHECK, ALL OK. REPLACED METERING VALVE, ALL OPS NORMAL)

Part: BUSHING — MISSING (SUMMING LEVER) · airframe 106,972 hrs · 18,816 cycles

ON TAKEOFF ROLL, ACFT VEERED RT UNCOMMANDED. FULL LT RUDDER WAS APPLIED BUT HAD NO APPARENT EFFECT AS AIRSPEED INCREASED RATE OF TURN INCREASED. RTO INITIATED TO PREVENT RUNWAY DEPARTURE. NOTE: ALL ENGINE N1 AND N2 WERE OBSERVED TO BE EVEN. ADJ/TEST IAW MM 32-51-00. RIG CHECK IN LT DRUM AND ADJUSTED CABLE. RIG CHECK ON RT TILLER, OK. RIG CHECK IN CABLE COMPENSATOR, OUT OF LIMITS. ADJUSTED CABLE TENSION. FOUND BUSHING MISSING AT NOSE METERING VALVE SUMMING LEVER. INSTALLED OK IAW MM.

Part: SKIN — DELAMINATED (RT WING) · airframe 106,830 hrs · 18,788 cycles

DURING WALK AROUND INSP BEING PERFORMED, MX FOUND THE- LEADING EDGE PANEL - LOWER SURFACE EXTERNAL SKIN WITH DELAMINATION DAMAGE (AREA: MEASURES 33.0 IN. X 36 IN.) (REF FIGURE 1).(EO4757A497 DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS IAW THE SRM 51-40-16 FIG 1, REPEAT DETAIL VISUAL INSP AT EVERY 1,000 FH (FLIGHT HOURS) AND PERMANENT REPAIR IAW THE SRM 51-40-09 FIG 18 IAW 51-40-12 AT THE NEXT C CHECK AFTER PART 1.)

Part: SKIN — CRACKED (NR 3 PYLON) · airframe 106,156 hrs · 18,652 cycles

DURING C-CHECK, CRACKING WAS FOUND IN THE 65B94052-1, NR3 PYLON RT SKIN ASSY AT THE NAC STA 248 PRECOOLER EXHAUST. THE CRACK WAS REPAIRED BY TRIMMING OUT THE DAMAGE AND RESTORING THE SURFACE FINISH IAW RFTA 00664-0006, REV A AND REA MF00664R0006, REV A (FIG 1 AND 2). THIS EO DOCUMENTS THE REPAIR OF THE SKIN IAW IAI RFTA 00664-0006, REV A AND REA MF00664R0006, REV A. THE REPAIR IAW THIS EO AND RFTA 00664-0005, REV A AND REA MF00664R0005, REV A ARE FAA APPROVED BY A AR ON THE FAA FORM 8100-9 DATED 25MAR2010 (FIGURE 3). THE FAA FORM 8100-9 DATED 25MAR2010 REQUIRES CONTINUED INSP IAW SB 747-54A2223, REVISION 0 AT 18 MONTH INTERVALS AFTER THIS REPAIR. THE REQUIRED INSP IS ACCOMPLISHED IAW EO 4754A233 AND NO ADDITIONAL INSP ARE REQUIRED IAW THIS EO. THE REPAIR ACCOMPLISHED IAW THIS EO IS AR APPROVED IAW THE FAA FORM 8100-9 DATED 25MAR2010 (FIG 3).

Part: FRAME — CRACKED (BS 560) · airframe 106,156 hrs · 18,652 cycles

DURING C-CHECK, A CRACK WAS FOUND IN THE 65B06871-2 BS 560, RBL 35 LOWER LOBE FRAME INNER CHORD. THE DAMAGE WAS TRIMMED OUT AND NEW SECTION WAS SPLICED IAW NRC 305 AND SRM 51-40-04, FIG 2. 65B06871-2 CHORD IS MADE FROM BAC1505-100246 EXTRUSION IN 7075-0 ALUMINUM QQ-A-200/11 HEAT TREATED TO -T6 AFTER FORMING. THE REPAIR CONSISTS OF A 0.050 AND 0.063 INCH THICK ANGLES ON EACH SIDE OF THE INNER CHORD MADE FROM 7075-0 ALUMINUM SHEET HEAT TREATED TO T62 AFTER FORMING INSTALLED USING BACB30FM HI-LOKS. REPAIR IAW PART 1 AND SRM 51-40-04, FIG 2 IS INSTALLED ON FATIGUE CRITICAL BASELINE STRUCTURE (FCBS) AND A DAMAGE TOLERANCE EVALUATION (DTE) IS NECESSARY. A DAMAGE TOLERANCE INSP (DTI) INCLUDES AN INSPECTION THRESHOLD, INSPECTION INTERVALS, AND INSPECTION PROCEDURES AND METHODS. IF THE DTI IS NOT AVAILABLE WHEN THE AIRPLANE RETURNS TO SERVICE, THE REPAIR IS APPROVED FOR 24 MONTHS. THIS REPAIR HAS BEEN SUBMITTED TO FOR DTI ON SR 1-1555105500. THE REPAIR ACCOMPLISHED PART 1 IS FAA APPROVED SRM 51-40-04, FIG 2. THE PART 2 INSP WILL BE FAA APPROVED AT THE TIME IT IS PROVIDED BY MFG.

Part: FRAME — CRACKED (BS 1540) · airframe 106,156 hrs · 18,652 cycles

DURING C-CHECK, A CRACK WAS FOUND IN THE 65B07373-4 1540, LBL 15-17 LOWER LOBE FRAME INNER CHORD. THE DAMAGE WAS TRIMMED OUT AND NEW SECTION WAS SPLICED IAW NRC 727 AND SRM 51-40-04, FIG 2. THE 65B07373-4 CHORD IS MADE FROM BAC1505-100166 EXTRUSION IN 7075-T6511 ALUMINUM IAW QQ-A-200/11. THE REPAIR CONSISTS OF 0.040 AND 0.050 INCH THICK ANGLES ON EACH SIDE OF THE INNER CHORD MADE FROM 7075-0 ALUMINUM SHEET HEAT TREATED TO T62 AFTER FORMING INSTALLED USING BACB30FM HI-LOKS. THE REPAIR IAW PART 1 AND SRM 51-40-04, FIGURE 2 IS INSTALLED ON FATIGUE CRITICAL BASELINE STRUCTURE (FCBS) AND A DAMAGE TOLERANCE EVALUATION (DTE) IS NECESSARY. A DAMAGE TOLERANCE INSPECTION (DTI) INCLUDES AN INSP THRESHOLD, INSP INTERVALS, AND INSP PROCEDURES AND METHODS. IF THE DTI IS NOT AVAILABLE WHEN THE AIRPLANE RETURNS TO SERVICE, THE REPAIR IS APPROVED FOR 24 MONTHS. THIS REPAIR HAS BEEN SUBMITTED TO MFG FOR DTI ON SR 1-1554670691. THE REPAIR ACCOMPLISHED IAW PART 1 IS FAA APPROVED IAW SRM 51-40-04, FIGURE 2. THE PART 2 INSP WILL BE FAA APPROVED AT THE TIME IT IS PROVIDED BY MFG.

Part: BEAM — DAMAGED (CARGO DOORWAY) · airframe 106,156 hrs · 18,652 cycles

DURING C-CHECK, DAMAGE WAS FOUND IN THE 65B04721-2 AFT LOWER CARGO DOOR LOWER BEAM WEB BETWEEN BS 1840 TO 1852. DAMAGE WAS TRIMMED OUT AND REPAIRED IAW NRC 786 AND SRM 51-40-03, FIG 1. THE 65B04721-2 WEB IS MADE FROM 0.125 INCH THICK 7075-0 SHEET IAW QQ-A-250/12 HEAT TREATED TO T62 AFTER FORMING. THE REPAIR CONSISTS OF AN 0.125 INCH THICK DOUBLER THAT MEASURES 6.0 INCHES BY 16.0 INCHES MADE FROM 7075-0 ALUMINUM SHEET HEAT TREATED TO T6 AFTER FORMING INSTALLED USING HL18PB6-4 HI-LOKS WITH HL70-6 COLLARS. REPAIR IAW PART 1 AND SRM 51-40-03, FIG 1 IS INSTALLED ON FATIGUE CRITICAL BASELINE STRUCTURE (FCBS) AND A DAMAGE TOLERANCE EVALUATION (DTE) IS NECESSARY. A DAMAGE TOLERANCE INSP (DTI) INCLUDES AN INSP THRESHOLD, INSP INTERVALS, AND INSP PROCEDURES AND METHODS. IF THE DTI IS NOT AVAILABLE WHEN THE AIRPLANE RETURNS TO SERVICE, THE REPAIR IS APPROVED FOR 24 MONTHS. THIS REPAIR HAS BEEN SUBMITTED TO MFG FOR DTI ON SR 1-1554670751. THE REPAIR ACCOMPLISHED IAW PART 1 IS FAA APPROVED IAW SRM 51-40-03, FIGURE 1. THE PART 2 INSP WILL BE FAA APPROVED AT THE TIME IT IS PROVIDED BY MFG, EO 4752A163.

Part: SKIN — DAMAGED (BS 1790 S39R) · airframe 106,156 hrs · 18,652 cycles

DURING C-CHECK, DAMAGE WAS FOUND IN THE 65B04144-3 SKIN AT BS 1790, S-38R. THE DAMAGE WAS TRIMMED OUT AND REPAIRED IAW NRC 732 AND SRM 53-30-03, FIG 1. THE 65B04144-3 SKIN IS MADE FROM 0.100 INCH THICK 2024-T3 CLAD ALUMINUM SHEET IAW QQ-A-250/5. THE REPAIR CONSISTS OF AN 0.125 INCH THICK DOUBLER THAT MEASURES 14.0 INCH BY 11 INCH MADE FROM 2024-T3 CLAD ALUMINUM SHEET INSTALLED USING BACR15CE RIVETS AND BACB30FN BOLTS. PART 1 OF THIS EO DOCUMENTS THE FUSELAGE SKIN REPAIR IAW NRC 732 AND SRM 53-30-03, FIG 1. PART 2 OF THIS EO COMPLIES WITH THE REPETITIVE INSP REQUIREMENTS OF THE PART 1, CATEGORY B REPAIR. THE REPAIR ACCOMPLISHED IAW PART 1 AND THE INSP IAW PART 2 OF THIS EO ARE FAA APPROVED IAW SRM 53-30-03, FIG 1.

Part: SKIN — CRACKED (NR 2 PYLON) · airframe 106,156 hrs · 18,652 cycles

DURING C-CHECK, CRACKING WAS FOUND IN THE 65B94052-1 NR 2 PYLON RT SKIN ASSY AT THE NAC STA 248 PRECOOLER EXHAUST. CRACK WAS REPAIRED BY TRIMMING OUT THE DAMAGE AND RESTORING THE SURFACE FINISH IAW RFTA 00664-0005, REV A AND REA MF00664R0005, REV A (FIG 1 & 2). THIS EO DOCUMENTS THE REPAIR OF THE SKIN IAW RFTA 00664-0005, REV A AND REA MF00664R0005, REVISION A. THE REPAIR IAW THIS EO AND RFTA 00664-0005, REV A AND REA MF00664R0005, REVISION A ARE FAA APPROVED BY MFG AR ON THE FAA FORM 8100-9 DATED 25MAR2010 (FIGURE 3). THE FAA FORM 8100-9 DATED 25MAR2010 REQUIRES CONTINUED INSP IAW SB 747-54A2223, REV 0 AT 18 MONTH INTERVALS AFTER THIS REPAIR. THE REQUIRED INSP IS ACCOMPLISHED IAW EO 4754A233 AND NO ADDITIONAL INSP ARE REQUIRED IAW THIS EO. THE REPAIR ACCOMPLISHED IAW THIS EO IS MFG AR APPROVED IAW THE FAA FORM 8100-9 DATED 25MAR2010 (FIG 3).

Part: STRINGER — CRACKED (BS 2180-2200) · corrosion level 2 · airframe 106,156 hrs · 18,652 cycles

DURING C-CHECK, CORROSION AND CRACKING WAS FOUND IN THE 65B04161-17, STR 49L BETWEEN BS 2180 AND 2200. DAMAGE WAS TRIMMED OUT AND A NEW STR SECTION WAS INSTALLED IAW REA MF00664R0004. THE 65B04161-17 STRINGER IS MADE FROM BAC1498-144 EXTRUSION IN 7075-0 SHEET IAW QQ-A-250/12 HEAT TREATED TO T6 OR T62. PART 1 OF THIS EO DOCUMENTS THE REA MF00664R0004. THE REPAIR IAW PART 1 OF THIS EO AND REA MF00664R0004 IS APPROVED BY MFG VIA AN FAA FORM 8100-9 ISSUED ON 26 MARCH 2010 (FIGURE 4). PART 2 OF THIS EO IS TO BE DETERMINED BASED ON A STAGE 3 APPROVAL THAT WILL BE PROVIDED BY MFG. REPAIR ACCOMPLISHED IAW PART 1 OF THIS EO IS FAA APPROVED IAW FAA FORM 8100-9 DATED 26MAR2010 (FIGURE 4). PART 2 INSP WILL ALSO BE FAA APPROVED WHEN IT IS PROVIDED BY MFG.

Part: BULKHEAD — CRACKED (NR 1 PYLON) · airframe 106,156 hrs · 18,652 cycles

DURING C-CHECK, CRACKING WAS FOUND IN THE 65B94107-19 NAC STA 270 BULKHEAD UPPER WEB ASSY ON THE NR1 PYLON. THE WEB ASSY WAS REPLACED IAW DWG 65B94107 WITH MINOR DEVIATIONS IAW REA 00664R0002. THIS EO DOCUMENTS THE REPLACEMENT OF THE WEB IAW DWG 65B94107 AND REA MF00664R0002. THE DEVIATIONS TO THE 65B94107-19 WEB INSTALLATION IAW REA MF00664R0002 ARE MINOR AND HAVE BEEN APPROVED BY MFG, RDR DATED 24MAR2010 PROVIDED IN SR 1-1534747177 (FIGURE 5).

Part: SHEAR TIE — CRACKED (BS 780) · corrosion level 2 · airframe 106,156 hrs · 18,652 cycles

DURING C-CHECK, CORROSION AND CRACKING WAS FOUND IN THE 65B04175-1 BS 780 FRAME SHEAR TIE BETWEEN S-46L AND -47R. THE DAMAGE WAS TRIMMED OUT AND REPAIRED IAW NRC 699 AND SRM 53-10-04, FIG 4. THE 65B04175-1 FRAME SHEAR TIE IS MADE FROM 0.056 INCH THICK 7075-0 ALUMINUM SHEET IAW QQ-A-250/13 HEAT TREATED TO T6 AFTER FORMING. THE REPAIR CONSISTS OF AN 0.071 INCH THICK DOUBLER MADE FROM 7075-T6 ALUMINUM INSTALLED USING MS20470D6 RIVETS. PART 1 OF THIS EO DOCUMENTS THE FRAME REPAIR NRC 699 AND SRM 53-10-04, FIG 4 PART 2 OF THIS EO COMPLIES WITH THE REPETITIVE INSP REQUIREMENTS OF THE PART 1, CATEGORY B REPAIR. THE REPAIR ACCOMPLISHED IAW PART 1 AND THE INSP IAW PART 2 OF THIS EO ARE FAA APPROVED IAW SRM 53-10-04, FIG 4. EO 4753B278.

Part: CARGO TRACK — DAMAGED (BS 560-580) · airframe 106,156 hrs · 18,652 cycles

THIS EO DOCUMENTS A MAJOR REPAIR. DURING C-CHECK, DAMAGE WAS FOUND TO THE FWD CARGO COMPARTMENT - BS560 - BS580, RBL45.5 CARGO TRACK WITH A CRACK (REF FIG 1). IAW SRM 53-10-21, FIG 5 (ITEM 3) THE CARGO TRACK IS MADE OF BAC1520-1687 (7178-T6511) EXTRUSION. PERMANENT REPAIR WAS PERFORMED IAW NRC 514 IAW THE SRM 53-10-05, FIG 5. THIS REPAIR WILL NOT HAVE AN IMPACT ON THE SUPPLEMENTAL STRUCTURE INSPECTION DOCUMENT (SSID) INSPECTION PROGRAM OF STRUCTURAL SIGNIFICANT. ITEMS (SSI) GIVEN IN SRM 51-00-04, FIG 4. THE REPAIR ACCOMPLISHED IAW PART 1 IS APPROVED BY SRM 53-10-05, FIG 5.

Part: CARGO TRACK — DAMAGED (BS 1900-1920) · airframe 106,156 hrs · 18,652 cycles

THIS EO DOCUMENTS A MAJOR REPAIR. DURING C-CHECK, DAMAGE WAS FOUND TO THE AFT CARGO COMPARTMENT - BS1900 - BS1920, LBL24.75 CARGO TRACK WITH A CRACK (REF FIG 1) IAW SRM 53-10-23, FIG 5 (ITEM 3) THE CARGO TRACK IS MADE OF BAC1520-1682 (7178-T6511) EXTRUSION. PERMANENT REPAIR WAS PERFORMED IAW NRC 672 IAW THE SRM 53-10-05, FIG 5. THIS REPAIR WILL NOT HAVE AN IMPACT ON THE SUPPLEMENTAL STRUCTURE INSP DOCUMENT (SSID) INSP PROGRAM OF STRUCTURAL SIGNIFICANT. ITEMS (SSI) GIVEN IN SRM 51-00-04, FIG 4. THE REPAIR ACCOMPLISHED PART 1 IS APPROVED BY SRM 53-10-05, FIG 5.

Part: SEAT TRACK — CRACKED (BS 1980) · airframe 106,156 hrs · 18,652 cycles

THIS EO DOCUMENTS A MAJOR REPAIR. DURING C-CHECK, DAMAGE WAS FOUND TO THE MAIN DECK - BS1980, LBL98 - SEAT TRACK WITH A CRACK (REF FIG 1) IAW SRM 53-10-23, FIG 4C (ITEM 1) CARGO TRACK IS MADE OF BAC1520-1566 (7178-T6511) EXTRUSION. PERMANENT REPAIR WAS PERFORMED IAW NRC 199 IAW THE SRM 53-10-05, FIGURE 1A. THIS REPAIR WILL NOT HAVE AN IMPACT ON THE SUPPLEMENTAL STRUCTURE INSPECTION DOCUMENT (SSID) INSP PROGRAM OF STRUCTURAL SIGNIFICANT ITEMS (SSI) GIVEN IN SRM 51-00-04, FIG 4. THE REPAIR ACCOMPLISHED IAW PART 1 IS APPROVED BY SRM 53-10-05 FIG 1A.

Part: CARGO TRACK — CORRODED (BS 1480-1500) · corrosion level 2 · airframe 106,156 hrs · 18,652 cycles

MAJOR REPAIR. DURING C-CHECK, DAMAGE WAS FOUND TO AFT CARGO COMPARTMENT - BS1480 - BS1500, RBL45 SEAT TRACK WITH CORROSION (REF FIG 1) IAW SRM 53-11-25, FIG 7 (ITEM 2) CARGO TRACK IS MADE OF BAC1520-1682 (7178-T6511) EXTRUSION. PERMANENT REPAIR WAS PERFORMED IAW NRC 768 IAW THE SRM 53-10-05, FIG 5. THIS REPAIR WILL NOT HAVE AN IMPACT ON THE SUP STRUCTURE INSP DOCUMENT (SSID) INSP PROGRAM OF STRUCTURAL SIGNIFICANT ITEMS (SSI) GIVEN IN SRM 51-00-04, FIG 4. THE REPAIR ACCOMPLISHED IAW PART 1 IS APPROVED BY SRM 53-10-05 FIG 5, EO 4753B283.

Part: SKIN — DAMAGED (RT MLG DOOR) · airframe 106,156 hrs · 18,652 cycles

DOORS - RT AFT MLG BODY DOOR SKIN DAMAGE - REPAIR. APPLIED A CHEMICAL CONVERSION COATING TO THE BARE SURFACES OF THE SKIN. REFER TO SRM 51-10-02. APPLY ONE LAYER OF BMS 10-79, TYPE II PRIMER TO THE BARE SURFACES OF THE SKIN. REF TO SOPM 20-44-04. INSTALLED THE T01 REPAIR SPLICE DOUBLER. FORMED A FILLET SEAL OF BMS 5-95 SEALANT AROUND THE EDGE OF THE DOUBLER. USED THE SEALANT SQUEEZED OUT WHEN THE DOUBLER WAS INSTALLED. APPLY ADDITIONAL SEALANT WHERE NECESSARY. VERIFIED THAT ALL WORK AREA IS CLEAN OF FOD. PERFORMED FINAL INSP AND VERIFY THAT ALL ITEMS HAVE BEEN SIGNED OFF. EO 4752A160.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 105,378 hrs · 18,498 cycles

DURING JACKING OF DATUM AIRPLANE, MX DAMAGED THE FUSELAGE SKIN SECTION 48 - BS2594.5 AT S-26R (ABOVE THE TAIL JACK PAD). MEASURING 2.5 IN. D AND 0.437 IN DEPTH. THE DAMAGE IS LOCATED APPROX 3.5 IN FWD OF BS 2598 BUTT JOINT. "INTERIM REPAIR PERFORMED AS DESCRIBED IN PART 1 WORK INSTRUCTIONS IAW SRM 53-30-03 FIG 1. (SHEETS 1-9)" EO4753B233.

Part: RELAY — FAILED (ZONE 100) · airframe 105,350 hrs · 18,566 cycles

AFTER TAKEOFF FROUND SAFETY RELAY LIGHT ILLUMINATED. OTHER INDICATIONS WERE BOTH ATC TRANSPONDERS INOP, LOW SPEED BRAKE RELEASE LIGHT ILLUMINATED. PERFORMED ACTION PLAN SENT AND CHECKED OK PER AMM 32-09-02. REPLACED DEFECTIVE R226 RELAY REPLACED PRIMARY SQUAT SWITCH. OPS CHECKED NORMAL

Part: CONNECTOR — DIRTY · airframe 105,348 hrs · 18,565 cycles

AIR TURN BACK AFTER TAKEOFF GROUND SAFETY RELAY LIGHT ON. OTHER INDICATIONS WERE BOTH ATC TRANSPONDERS INOP, LOW SPEED BRAKE RELEASE LIGHT ILLUMINATED. AUTO THROTTLES/FRATTS DISENGAGED AUTO PRESSURIZATION INOP. WIRING CHECKED PER WDM 32-09-00. FOUND R952 ON P14 PIN 6 TO 12 SOCKET DIRTY. CLEANED BOTH SOCKETS. R229 FOUND PIN X1 AND X2 SOCKETS DIRTY CLEANED BOTH SOCKETS. ALL WIRING CHECKED ON ATC TRANSPONDERS CABIN PRESSURE CHECKED IN FLIGHT AND GROUND MODE OK. A/T FFRATS FUNCTION TEST OK

Part: RELAY — MISINSTALLED (ATC TRANSPONDER) · airframe 105,347 hrs · 18,564 cycles

AIR TURN BACK. ATC TRANSPONDER INOP. GROUND SAFETY RELAY LIGHT ON IN FLIGHT COULD NOT PRESSURIZE PAST 1.8 PSID. LOW SPEED BRAKE RELEASE LIGHT ILLUMINATED. RESET C/B BOTH TRANSPONDERS RERACKED, GROUND OPS CHECKED OK. SWAPPED RELAY BETWEEN R952 AND K3. FOUND R226 RELAY WAS INSTALLED INCORRECTLY. REINSTALLED BACK IN THE CORRECT POSITION. GROUND SAFETY RELAY TEST OK.

Part: SKIN PANEL — CORRODED (TE FLAP) · airframe 104,672 hrs · 18,345 cycles

RT WING INBOARD AFT FLAP UPPER EXTERNAL SURFACE PANEL HAS EVIDENCE OF CORROSION AT WBL 259.30 AND 12 INCHES FROM TRAILING EDGE. CUT OUT AREA OF CORROSION AND PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 57-50-02 FIG 5, SHEET 4 AND 10 AND SRM 51-40-06. ALSO, REFERENCE ATLAS EO 4757A482.

Part: PANEL — DELAMINATED (ZONE 500) · airframe 103,925 hrs · 18,194 cycles

LT WING UPPER SURFACE L/E FIXED PANEL AT ILES 664.97 HAS AN AREA OF 6.0 BY 18.0 INCHES OF DELAMINATION. PERMANENT REPAIR ACCOMPLISHED AS PER 747-200 SRM 51-40-09, FIG 18 SHEET 2 AND 5. PREPREG 250* F CURE PER SRM 51-40-12. REFERENCE ATLAS AIR EO 4757A477.

Part: BRACE — CHAFED (ZONE 400) · airframe 103,925 hrs · 18,194 cycles

PYLON NR 1 DIAGONAL BRACE IS CHAFED ON OTBD SIDE 11 O'CLOCK POSITION, ZONE 5, 29.5 INCHES FROM FORWARD END. CHAFE IS 2.0 INCH LONG BY 0.125 INCH WIDE. INTERIM REPAIR WAS ACCOMPLISHED AS PER 747-200 SRM 54-41-01, FIG 3 SHEETS 1 THRU 4. REFERENCE ATLAS AIR EO4754A298. REPEAT INSPECTIONS AS PER PART 2 OF EO TO BE ACCOMPLISHED EVERY C-CHECK.

Part: AMPLIFIER — FAILED (FIRE DETECTION) · airframe 103,493 hrs · 18,114 cycles

HIGH SPEED REJECTED TAKEOFF FOR CARGO FIRE INDICATION, NR 1 MAIN DECK WARNING ON TAKEOFF ROLL. REJECTED SPEED 146KTS. PERFORMED HIGH ENERGY STOP INSPECTION PER 5-31-10, ALL CHECKED OKAY. REMOVED AND REPLACED NR 1 SMOKE DETECTOR AMPLIFIER, ALL OPS CHECKED OK.

Part: BOLT — LOOSE (EMERGENCY EXIT) · airframe 103,190 hrs · 18,058 cycles

AIR TURNBACK AFTER TAKEOFF LOUD NOISE FROM OVERHEAD HATCH. CARRIED OUT HATCH SEAL CHECK AND DOOR CUTOUT CHECK FOR ABNORMALITIES ALL OKAY. FOUND HINGE BOLTS LOOSE. TIGHTENED SAME PER STANDARD PRACTICES. PRESSURIZED AIRCRAFT AND LEAK CHECKED, NO LEAKS NOTED.

Part: ELEMENT — FALSE ACTIVATION (NR 2 ENGINE) · airframe 103,190 hrs · 18,058 cycles

DURING CLIMBOUT AT 17000 FEET NR 2 ENGINE FIRE WARNING BELL AND LIGHT CAME ON. ACCOMPLISHED CHECKLIST, BOTH FIRE BOTTLES WERE DISCHARGED, HYD PUMP SUPPLY OFF FOR 1 HOUR AND 30 MINUTES NR 2 FIRE WARNING LIGHT AND NACELLE TEMP STAYED AT 7.9 AND 8.9 AFTER BLOCK IN. TROUBLESHOT TO HARD FAULTS ON STRUT AREA FORWARD DETECTOR ELEMENT, REPLACED ELEMENTS AND REPLACED FIRE BOTTLES. ALL OPS CHECKED NORMAL.

Part: BLEED VALVE — LEAKING (NR 1 ENGINE)

LT WING LEADING EDGE OVERHEAT LIGHT ILLUMINATED. LIGHT DID NOT GO OUT UNTIL THROTTLE WAS RETARDED. FOUND PYLON VALVE LEAKING. REPLACED VALVE, OPS CHECKED OK. (A)

Part: FRAME — CRACKED (BS 280 S26L) · airframe 102,518 hrs · 17,919 cycles

DURING C-CHECK FOUND FRAME CRACKED AT STATION 280 STRINGER 26L. FRAME REPAIRED AS PER SRM 53-10-04 FIGURE 10. (A)

Part: SKIN — CRACKED (NR 4 EXHAUST)

CARRY OUT NR 4 PYLON EXHAUST SKIN CRACK CONDITIONAL CHECK REF EO NR 4754A250. REPAIRED CRACK IAW MFG MESSAGE 1-299984882-19. (K)

Part: FRAME — CRACKED (BS 320 S25R) · airframe 102,518 hrs · 17,919 cycles

DURING C-CHECK FOUND FRAME CRACKED AT STATION 320 STRINGER 25R. FRAME REPAIRED AS PER SRM 53-10-04 FIGURE 10. (A)

Part: FRAME — CRACKED (BS 280 S26R) · airframe 102,518 hrs · 17,919 cycles

DURING C-CHECK FOUND FRAME CRACKED AT STATION 280 STRINGER 26R. FRAME REPAIRED AS PER SRM 53-10-04 FIGURE 10. (A)

Part: STRINGER — CRACKED (BS 396 S25L)

STA 396, STRINGER 25 L, FATIGUE CRACKED. REPLACED STRINGER IAW DWG 65B11089. (K)

Part: STRINGER — CRACKED (BS 320 S25L)

STA 320, STRINGER 25L HAS FATIGUE CRACK. FRAME REPAIRED AT STA 320 LT SIDE IAW SRM 53-10-04, FIG 10. (K)

Part: FASTENER — LOOSE (NR 4 PYLON)

NR 4 PYLON AFT BULKHEAD CHORD FOUND SEVERAL ATTACH FASTENERS LOOSE. REPLACED FASTENERS IAW MFG MESSAGE NR 1-875740529-4. (K)

Part: FASTENER — LOOSE (NR1 PYLON)

NR 1 PYLON AFT BULKHEAD CHORD FOUND SEVERAL ATTACH FASTENERS, LOOSE. REPLACED FASTENERS IAW MFG MESSAGE NR 1-875740529-4. (K)

Part: FRAME — CRACKED (BS 400)

FRAME CRACKED AT STATION 400, STRINGER 22R. REPLACED DAMAGED FRAME IAW SRM 51-10-01 AND SRM 51-30-02. (K)

Part: FRAME — CRACKED (BS 400 S22R)

FRAME CRACKED AT STATION 400 STRINGER 22R. REPLACED DAMAGED FRAME IAW SRM 51-10-01 AND SRM 51-30-02. (K)

Part: SKIN — DENTED (THRUST REVERSER)

NR 1 ENGINE LT "C" DUCT (REVERSER) EXTERIOR FOUND WITH 1 EACH DENT AT 7 O`CLOCK POSITION. NR 1 REVERSER EXTERIOR SURFACE DENT REPAIRED IAW CF650 ENGINE MANUAL 78-32-01, REPAIR NR 4. (K)

Part: STRUCTURE — DENTED (THRUST REVERSER)

NR 1 ENGINE LT "C" DUCT (REVERSER) EXTERIOR FOUND WITH 1 EACH DENT AT 7 O`CLOCK POSITION. NR 1 REVERSER EXTERIOR SURFACE DENT REPAIRED IAW ENGINE MANUAL 78-32-01, REPAIR NR 4. (K)

Part: SKIN — DENTED (THRUST REVERSER)

NR 3 ENGINE, RT SIDE ABOUT 4 O`CLOCK POSITION HAS 2 DENTS. NR 3 ENGINE REVERSER REPAIRED IAW ENGINE MANUAL 78-32-01, REPAIR NR 4. (K)

Part: STRUCTURE — DENTED (THRUST REVERSER)

NR 1 ENG IB THRUST REVERSER OUTER SURFACE FOUND LARGE DENT AT THE UPPER POSITION. NR 1 ENGINE IB THRUST REVERSER DENT REPAIRED IAW ENGINE MANUAL 78-32-01 REPAIR NR 4. (K)

Part: REVEAL — CRACKED (5R DOOR)

MAINE DECK R5 MAIN ENTRY DOOR CUTOUT FWD MIDDLE POSITION, DOOR OPENING LOCK RELEASE HANDLE CUTOUT REVEAL PANEL FOUND CRACKED. CRACKED AREA TRIMMED OUT AND REPAIRED IAW SRM 51-10-01. (K)

Part: SKIN — SCRATCHED (BS 770 S28-29L)

FORWARD CARGO STA 770 LT SIDE STRINGER 28L TO 29L, FUSELAGE SKIN FOUND SCRATCHED COMMON AT LOWER PAX RELIEF VALVE. (K)

Part: STRINGER — CRACKED (BS 300 S25R)

UPPER DECK STA 300 STRINGER 25R HAS FATIGUE CRACK. REPAIRED STRINGER CLIPS STRAP AND FRAME SPLICE FABRICATED IAW SRM 53-10-04 AND INSTALLED IAW SRM 51-30-02. (K)

Part: SMOKE DETECTOR — MALFUNCTIONED · airframe 102,139 hrs · 17,895 cycles

DIVERSION TO ICT DUE TO MAIN DECK CARGO SMOKE DETECTOR NR 1 FIRE WARNING CAME ON AFTER REACHING CRUISE ALTITUDE (FL410). INSPECTED AREA NO SIGNS OF SMOKE OR FUMES. DIVERTED TO ICT AT COMPANY REQUEST AS A PRECAUTION. LIGHT EXTINGUISHED AFTER LANDING. THE ABOVE ITEM HAS BEEN TRANSFERRED FROM LOG PAD 0159 PAGE NUMBER 367269.

Part: SMOKE DETECTOR — FAILED (CARGO BAY) · airframe 102,142 hrs · 17,896 cycles

NR 1 MAIN DECK CARGO SMOKE DETECTOR LIGHT CAME ON AGAIN AT CRUISE APPROXIMATELY 50 MINUTES INTO FLIGHT. REMAINED ON. REF DMI M08-058. REPLACED NR 1A SMOKE DETECTOR PER 26-14-01 SYSTEM. OPS CHECKED NORMAL PER MM 26-14-00. ALSO IN ITEM M3 REPLACED 1B SMOKE DETECTOR S/N 34151.

Part: SKIN — CRACKED (PAX DOORWAY) · corrosion level 2 · airframe 101,345 hrs · 17,658 cycles

MAIN ENTRY DOOR L-1, EXTERIOR LOWER HINGE CUT-OUT, PREVIOUS DOUBLER REPAIR, LOWER CORNER IS CRACKED AT STA 452.5 L. REMOVED CRACKED DOUBLER, FABRICATED NEW DOUBLER AS PER SB 747-52-2144 REV 2. VERIFIED STOP DRILLED ENDED CRACK USING HFEC INSP. AS PER 747 NDT MANUAL PART 6, 51-00-00 FIG 23. INSTALLED NEW DOUBLER AS PER SB 747-52-2144 REV 2 REF EO 4752A130.

Part: SKIN — CORRODED (TE FLAP) · corrosion level 2 · airframe 101,345 hrs · 17,658 cycles

LT WING O/B FLAP, AFT FLAP UPPER SKIN ON PANEL, AN AREA OF 5.0 INCH BY 2.0 INCH IS CORRODED AT WBL 625 LT. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09, FIG 5, SHEETS 7 AND 9, PREPREG LAYUP 250 DEGREES F CURE PER SRM 51-40-12. REF: ATLAS AIR EO 4757A416.

Part: PANEL — CRACKED (LT WING) · airframe 101,345 hrs · 17,658 cycles

LT WING UPPER FIXED T/E PANELS AT STA WBL 445, 11.0 INCHES FROM TRAILING EDGE AND WBL 515, 6.0 INCHES FROM TRAILING EDGE HAVE A 1.0 INCH CRACK. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09 FIG 2 SHEETS 3 AND 5, PREPREG LAYUP 250 DEGREES F CURE PER SRM 51-40-12. REF: ATLAS AIR EO 4757A415.

Part: STEERING SYS — INOPERATIVE (NLG) · airframe 100,932 hrs · 17,566 cycles

TAKEOFF REJECTED DUE TO T/O WARNING HORN BECAUSE RIGHT BODY GEAR UNLOCKED LIGHT ILLUMINATED ON T/O ROLL. SYSTEM SELECTED TO PRIMARY MODE. PERFORMED OPS CK OF BODY GEAR STEERING SYSTEM. FOUND RIGHT ALT BODY GEAR ACTUATOR SWITCH INOP. REMOVED AND REPLACED AS PER MM 32-53-16 AND PERFORMED OPS CK AS PER MM 32-53-00 FOUND SATISFACTORY.

Part: FLOORBEAM — DAMAGED (ZONE 200) · airframe 100,688 hrs · 17,518 cycles

ON REMOVAL OF MCD CEILING PANELS AROUND STA 600 FOUND UPPER FLOORBEAM LOWER CHORD AT BS 620 RBL 52 HAS SUSTAINED IMPACT DENT OF 5" LONG 1.5" WIDE 0.187" DEEP. STRUCTURAL DISCREPANCY RAM PART 1 COMPLETED. HFEC ACCOMPLISHED TO DAMAGED AREA PER NDT PARA 6 51-00-00 FIG 23. NO CRACK INDICATION FOUND. LOWER CHORD STA 620 RBL 52 WL 300.8 REPAIRED PER ATLAS AIR XEO 53-111607.

Part: FLOORBEAM — DAMAGED (BS 620) · airframe 100,688 hrs · 17,518 cycles

AFTER REMOVAL OF MCD CEILING PANEL AT STA 620 FOUND UPPER FLOORBEAM LOWER CHORD AT BS 620 LBL 52 WL 300.8 HAS IMPACT DENT. 4.5" LONG 1.5" WIDE. HFEC ACCOMPLISHED TO DAMAGED AREA PER NDT PARA 6 51-00-00 FIG 23. NO CRACK INDICATION FOUND. LOWER CHORD REPAIRED PER ATLAS AIR XEO 53-111607.

Part: TRANSMITTER — MALFUNCTIONED (CREW O2) · airframe 100,468 hrs · 17,468 cycles

DIVERSION, DUE TO LOSS OF CREW O2. REPLACED UPPER AND LOWER CREW O2 BOTTLES IAW AMM 12-15-08. REPLACED UPPER AND LOWER CREW O2 PRESS XMITTERS, LEAK CHECKED OKAY.

Part: STRUCTURE — DEBONDED (LT MLG DOOR) · airframe 99,979 hrs · 17,367 cycles

LT WING GEAR LOWER STRUT DOOR, AFT LOWER END, PREVIOUS REPAIR, EDGE IS SEPARATING. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09 FIG 12 SHEET 1, 2 AND 3. ALSO, REFERENCE ATLAS AIR XEO NR 52-082907.

Part: STRUCTURE — DENTED (THRUST REVERSER) · airframe 99,979 hrs · 17,367 cycles

NR 2 ENGINE OUTBOARD REVERSER EXTERIOR SKIN HAS A 7.5 INCH BY 6.0 INCH DENT IN UPPER AREA OF TRANSLATING COWL. PERMANENT REPAIR ACCOMPLISHED AS PER GE CF6-50 ENGINE MANUAL 78-32-01, REPAIR 003. ALSO, REFERENCE ATLAS AIR XEO NR 78-082907.

Part: STRUCTURE — DAMAGED (LT WING) · airframe 99,660 hrs · 117,298 cycles

AFTER LANDING LEFT WING UPPER SURFACE, INBOARD OF NR 2 ENG JUST AFT OF LEADING EDGE, PATCH MISSING. EXPOSED DAMAGE HONEYCOMB, MATERIAL EXPOSED WITH PORTIONS OF HONEY COMB MISSING AND BULGED UP FROM SURFACE AREA. INTERIM REPAIR WAS ACCOMPLISHED IAW XEO NR 57-072207 22 JUL 07. ATLAS AIR PART 1 INTERIM REPAIR. PART 2, 3, 4 AND 5.

Part: SKIN — CRACKED (BS 340) · airframe 99,304 hrs · 17,217 cycles

FLAT SIDED SKIN AT BS 340 STRINGERS 6-8L FOUND 9 EACH HOLES CRACKED AT SKIN. FLAT SKIN CRACKED HOLES REPAIRED AS PER BOEING MESSAGE 1-343396688-2 AND FAA 8100-9

Part: SHEAR TIE — CRACKED (BS 860) · airframe 99,304 hrs · 17,217 cycles

BS 860R FRAME TO TENSION TIE CONNECTION FOUND HOLE NR 9 HOLE CRACKED AT FORWARD CHANNEL. BS 860 FRAME TO TENSION TIE CONNECTION CRACKED FORWARD CHANNEL REPAIRED AS PER BOEING MESSAGE 1-339630379-21-1 AND FAA 8100-9.

Part: SKIN — CRACKED (NR 3 NACELLE) · airframe 99,304 hrs · 17,217 cycles

NR 3 PYLON ACCESS PANEL 473BL CUTOUT CRACKED AT FORWARD UPPER CORNER. NR 3 PYLON ACCESS PANEL 473BL CUTOUT SKIN REPAIR AS PER BOEING MESSAGE 1-351455345-3 AND FAA FORM 8100-9.

Part: SHEAR TIE — CRACKED (BS 880) · airframe 99,304 hrs · 17,217 cycles

BS 880R FRAME TO TENSION TIE CONNECTION FOUND CRACKED HOLE NR 5 AT FRAME. BS 880R FRAME TO TENSION TIE CONNECTION CRACKED FRAME REPAIRED AS PER BOEING MESSAGE 1-339629649-2 AND FAA FORM 8100-9.

Part: SHEAR TIE — CRACKED (BS 900) · airframe 99,304 hrs · 17,217 cycles

BS 900R FRAME TO TENSION TIE CONNECTION FOUND CRACKED HOLE NR 9 AT FORWARD CHANNEL. BS 900R FRAME TO TENSION TIE CONNECTION REPAIRED AS PER BOEING MESSAGE 1-343193942-4 AND FAA FORM 8100-9.

Part: SHEAR TIE — CRACKED (BS 920) · airframe 99,304 hrs · 17,217 cycles

BS 920R FRAME TO TENSION TIE CONNECTION FOUND HOLE NR 4 CRACKED. BS 920R FRAME TO TENSION TIE CONNECTION REPAIRED AS PER BOEING MESSAGE 1-340126164-4 AND 8100-9.

Part: SHEAR TIE — CRACKED (BS 840) · airframe 99,304 hrs · 17,217 cycles

BS 840R FRAME TO TENSION TIE CONNECTION FOUND NR 14 AND 19 HOLE CRACKED. BS 840 FRAME TO TENSION TIE CONNECTION REPAIRED AS PER BOEING MESSAGE 1-340418286-2 AND FAA FORM 8100-9.

Part: SKIN — CRACKED (NR 3 NACELLE) · airframe 99,304 hrs · 17,217 cycles

NR 3 PYLON OVAL PANEL 473AR CUTOUT CRACKED LOWER AFT SKIN. NR 3 PYLON OVAL PANEL 473AR CRACKED SKIN REPAIRED AS PER BOEING MESSAGE 1-351859671-9 AND FAA FORM 8100-9.

Part: SKIN — CRACKED (BS 2605) · airframe 99,304 hrs · 17,217 cycles

BS 2605 FOUND DENT AND CRACK BETWEEN STRINGER 46R AND 49R AREA JUST BETWEEN 2 PREVIOUS DOUBLERS. SKIN REPAIRED AS PER BOEING MESSAGE 1-343200877-4 AND FAA FORM 8100-9.

Part: ANGLE — CRACKED (RT WING) · airframe 98,608 hrs · 17,063 cycles

VERTICAL "L" EXTRUSION ANGLE CRACKED AT RIGHT WING UPPER SURFACE, BELOW GAP PANEL 611CT FOR NR 3 PYLON AT INBOARD SIDE, FORWARD CORNER, WING STATION 670.25. REMOVED AND REPLACED "L" ANGLE EXTRUSION P/N 221738-3-1 AS PER 747-200 SRM 51-30-02 AND SRM 51-10-02. ALSO, REFERENCE ATLAS AIR XEO NR 57-030107-1.

Part: SKIN — CRACKED (NR 3 NACELLE) · airframe 98,608 hrs · 17,063 cycles

NR 3 PYLON TOP SKIN, AFT EDGE, ABOVE LINK FITTING HAS A 0.375 INCH CRACK. TRIMMED OUT SKIN TO REMOVE CRACK AS PER 747 SRM 51-10-01. ACCOMPLISHED HFEC INSPECTION TO VERIFY REMOVAL OF CRACK AS PER 747 NDT MANUAL PAR 6 SECTION 51-00-00 FIG 4. ALSO, REFERENCE ATLAS AIR XEO NR 54-022807.

Part: PANEL — CRACKED (RT WING) · airframe 98,608 hrs · 17,063 cycles

RIGHT WING, UPPER TRAILING EDGE PANEL, OUTBOARD OF NR 8 SPOILER HAS A 7.0 INCH LONG BY 1.5 INCH WIDE CRACK. PERMANENT REPAIR WAS ACCOMPLISHED AS PER 747-200 SRM 51-40-09, FIG 2, TABLE 1 AND SRM 51-40-12. ALSO, REFERENCE ATLAS AIR XEO NR 57-030107.

Part: FRAME — CRACKED (NR 1 NACELLE) · airframe 98,608 hrs · 17,063 cycles

NR 1 PYLON AFT UPPER BULKHEAD "T" FRAME HAS A CRACK AT AFT FLANGE AND A SECOND CRACK AT FORWARD FLANGE, OUTBOARD OF NR 1 PYLON FRONT SPAR CHORD ASSEMBLY. AFT FLANGE CRACK IS 0.750 INCH LONG. FORWARD FLANGE CRACK IS 0.375 INCH LONG AT NACELLE STATION 270.00. ACCOMPLISHED INTERIM REPAIR AS PER 747-200 SRM 51-30-02 AND ATLAS AIR XEO NR 54-030107, FAA FORM 8110-3 ISSUED AND APPROVED. PERMANENT REPAIR TO BE ACCOMPLISH AT NEXT "C" CHECK.

Part: SKIN — CRACKED (NR 4 NACELLE) · airframe 98,608 hrs · 17,063 cycles

NR 4 PYLON CUT-OUT FOR PRE-COOLER EXHAUST AIR, RT SIDE OF PYLON AT NACELLE STATION 248.0 HAS A 2.625 INCH CRACK AT AFT, LOWER CORNER. ACCOMPLISHED INTERIM REPAIR, LOCATED CRACK AS PER NDT 747 MANUAL 51-00-00 PAR 6 AND STOP DRILLED BY REAMING EXISTING HI-LOCK HOLE TO .312 INCH DIAMETER AS PER 747 SRM 51-10-01 AND SRM 51-30-02. VERIFIED CRACK HIT HOLE AND INSTALLED HI-LOCK AS PER 747 SRM 51-30-02. REFERENCE ATLAS AIR XEO 54-030207.

Part: SEAT TRACK — CRACKED (BS 1816) · airframe 98,608 hrs · 17,063 cycles

FOUND MAIN CARGO COMPARTMENT SEAT TRACK AT STATION 1816, LBL 99 HAS CRACK CROWN LUGS. ACCOMPLISHED PERMANENT REPAIR AS PER 747-200 SRM 53-10-05 FIG 1A, ALSO, REFERENCE ATLAS AIR EO 4753A921.

Part: SKIN PANEL — DELAMINATED (RT WING) · airframe 98,018 hrs · 16,898 cycles

RT WING UPPER SURFACE T/E PANEL HAS 4.0 IN. BY 2.0 IN. AREA OF DELAMINATION LOCATED 30 INCHES I/B OF I/B AILERON. ACCOMPLISHED PERMANENT REPAIR AS PER B747 SRM 51-40-09 FIG 2 AND B747 SRM 51-40-12. ALSO, REFERENCE ATLAS AIR EO 4757A334.

Part: FIREWALL — CRACKED (APU BAY) · airframe 98,018 hrs · 16,898 cycles

APU COMPARTMENT TITANIUM FIREWALL, LOWER LT WEB IS CRACKED. ACCOMPLISHED PERMANENT REPAIR AS PER B747 SRM 53-10-04 FIG 30. ALSO, REFERENCE ATLAS EO 4753A866.

Part: PANEL — TORN (RT WING) · airframe 98,018 hrs · 16,898 cycles

RT WING LOWER PANEL 671AB INBOARD CORNER IS TORN, 2.0 INCH BY 2.0 INCH AREA. ACCOMPLISHED PERMANENT REPAIR AS PER B747 SRM 51-40-09 FIG 1 AND B747 SRM 51-40-12. ALSO REFERENCE ATLAS AIR EO 4757A334.

Part: SKIN PANEL — DELAMINATED (LT WING) · airframe 98,018 hrs · 16,898 cycles

LT WING UPPER L/E PANEL HAS A PREVIOUS REPAIR DELAMINATED AND CRACKED, 8.0 IN. BY 5.0 IN. ACCOMPLISHED PERMANENT REPAIR AS PER B747 SRM 51-40-09 FIG 1 AND B747 SRM 51-40-12. ALSO, REFERENCE ATLAS AIR EO 4757A335.

Part: SKIN PANEL — DAMAGED (TE FLAP) · airframe 98,018 hrs · 16,898 cycles

LT WING OUTBOARD MID-FLAP L/E DAMAGE AT OUTBOARD TRACK CUT-OUT. PERMANENT COMPOSITE REPAIR TO L/E WAS ACCOMPLISHED AS PER B747 SRM 51-40-14 AND PERMANENT REPAIR TO RIB SECTION LOCATED AT WBL 794, AS PER B747 SRM 51-40-03 FIG 1. ALSO, REFERENCE ATLAS AIR EO 4757A336.

Part: WARNING LIGHT — MALFUNCTIONED (MLG) · airframe 97,609 hrs · 16,793 cycles

AFTER PUTTING GEAR DOWN, WE HAD A GREEN GEAR LIGHT MOMENTARILY ON FOLLOWED BY A MOMENTARILY RED LIGHT, ALL GEAR LIGHTS WENT OUT. ENGINEER PANEL LIGHTS FOR GEAR CHECKED NORMAL. RESET C/B C613 PANEL. CARRIED OUT OPERATIONAL CHECK OF LANDING GEAR INDICATION LIGHTS IAW MM 32-61-00. OPERATION CHECKS OK.

Part: RIB — CRACKED (RT WING) · airframe 97,368 hrs · 16,737 cycles

RT WING SUPPORT RIB FOR FLYING PANEL, IB OF NR 7 SPOILER AT WBL253.0 HAS A CRACK. ACCOMPLISHED PERMANENT REPAIR IAW SRM 51-40-02 FIG. 1.

Part: RELIEF VALVE — FAILED (NR 1 ENGINE) · airframe 197,365 hrs · 16,733 cycles

NR 1 ENGINE FIRE INDICATION, FL330 2135Z, NACELLE TEMP INDICATIONS ON "B" LOOP OVER 5.0. "B" LOOP WAS DEFERRRED. FHB SECTION 3 PROCEDURES ACCOMPLISHED. FOUND OVERPRESSURE RELIEF VALVE LEAKING EXCESSIVELY AT 40-PSI. REPLACED VALVE PER AMM 36-11-00 ADJ TEST. ACCOMPLISHED PNEUMATIC LEAK TEST NR 1 AND FOUND OK.

Part: VALVE — INOPERATIVE (PYLON) · airframe 97,194 hrs · 16,699 cycles

DURING CRUISE, COULD NOT CLOSE NR 1 PYLON VALVE WITH ASSOCIATED SWITCH, VLV CLOSED. ON ENG SHUT DOWN (DIV). DURING CRUISE, COULD NOT CLOSE NR 3 PYLON VALVE WITH ASSOCIATED SWITCH, VLV CLOSED. ON ENG SHUT DOWN (DIV). DURING CRUISE, COULD NOT CLOSE NR 4 PYLON VALVE WITH ASSOCIATED SWITCH, VLV CLOSED. ON ENG SHUT DOWN (DIV). RAN NR 1 ENGINE & CHECKED OPERATION OF NR 1 PYLON VALVE GROUND CHECK OK PER 36-11-04. RAN NR 3 ENGINE & CHECKED OPERATION OF NR 3 PYLON VALVE GROUND CHECK OK PER 36-11-04. REMOVED AND REPLACED NR 4 PYLON VLV AS PER MM 36-11-04, OPS CHECK NORMAL.

Part: CHECK VALVE — RUPTURED (ENGINE) · airframe 97,068 hrs · 16,673 cycles

AFTER V1, NR 1 ENGINE LOOP FAULT FORWARD AND LIGHT ILLUMINATED, B-LOOP AT ENGINE PANEL AT 9.0 A-LOOP AT 6.5, VISUAL INSPECTION, LOWER BLOW DOOR OPEN. CHAPTER 5 DUCT SEPARATION INSPECTION REQUIRED ON NR 1 ENGINE. FOUND 8TH STAGE CHECK VALVE RUPTURED, REMOVED AND REPLACED VALVE AND MANIFOLD COMPARTMENTS PER AMM 36-11-01. LEAK CHECKED GOOD, PWR ASSURANCE RUN PER 71-00-00 SATISFACTORY. ENGINE NR 1 INSPECTED PER AMM 5-51-86 FOUND SATISFACTORY.

Part: CONTROLLER — DEFECTIVE (COCKPIT) · airframe 96,989 hrs · 16,657 cycles

R1-OVERHEAT CAME ON, WOULD NOT RESET. HAD ELECTRICAL ODOR AND C/B OPENED. REMOVED AND REPLACED R1 WINDOW HEAT CONTROLLER, R1 WINDOW OPS NORMAL PER MM 30-41-00.

Part: PANEL — CRACKED (ZONE 500) · airframe 96,730 hrs · 16,602 cycles

DURING REGULAR INSPECTION, LT WING OB MID FLAP COVE PANEL DISCOVERED CRACKED ON UNDERSIDE APPROX 22 IN ADJACENT TO SUPPORT ARMS LOCATED AT STA 1100/1122. REPAIRED IAW SRM 51-40-12 AND EO 4757A301.

Part: PANEL — CRACKED (ZONE 600) · airframe 96,730 hrs · 16,602 cycles

DURING REGULAR INSPECTION, RT WING OB MID FLAP COVER PANEL DISCOVERED CRACKED ON UNDERSIDE APPROX 4 INCH ADJACENT TO SUPPORT ARMS AT STA 862/866. REPAIRED IAW SRM 51-40-14 AND EO 4757A300.

Part: INU — INOPERATIVE · airframe 96,185 hrs · 16,494 cycles

ON CLIMB, BOTH ATT LIGHTS (WARNING) ILLUMINATED WITH CAPTS ADI FROZEN, W/ATT FLAG IN VIEW, ACCOMPLISHED CK LIST PROCEDURES. SWITCHING TO ALT, NO HELP. NR 1 INS FAILED WITH WARNING LIGHT AND BLACK SCREEN. NR 3 INS DISPLAYED A WARNING LIGHT WITH ERRONEOUS G/S INDICATION AND ATTITUDE INDICATION ACTION. CODE REMOVE INU NO MALF CODE. HEAVY WEIGHT LANDING LDW 344.6KGS. REMOVED AND REPLACED NR 1 INU PER AMM 34-41-03. ALIGNMENT CHK PERFORMED SATIS. REMOVED AND REPLACED NR 3 INU PER AMM 34-41-03. ALIGNMENT CK PERFORMED SATIS. ACCOMPLISHED OVERWEIGHT LDG CONDITIONAL INS PER 5-51-39, STEP 2A (PHASE 1) NIL DAMAGE NOTED, A/C OK FOR SVC.

Part: BUSHING — CORRODED (FLAP TRACK) · airframe 96,049 hrs · 16,466 cycles

CORROSION FOUND IN BUSHING BORES OF INBD FLAP TRACK ASSY NR 4 BY SIAGE WORKSHOP DURING REPAIR (SHOP VISIT) P/N 65B17064-13, S/N 0039. REPAIR CARRIED OUT IAW BOEING REPAIR NR 1-171550575 BY W/SHOP. REFER TO SWJC NR MS 130382145 AND SWJC NR E-W3LG000130382145 FOR REPAIR CERTIFICATION.

Part: ACCESS PANEL — CRACKED (NR 2 PYLON) · airframe 96,049 hrs · 16,466 cycles

NR 2 PYLON FWD ACCESS CUT OUT FOUND CRACKED AT TOP FWD AND AFT BOTTOM AREA BETWEEN NAC STA 211.42 TO NAC STA 222.50, (LHS) (ACCESS PANEL #462AL). INTERIM REPAIRED AS PER BOEING MSG 1-168393318-4. PERFORM REPEAT DV. INSP OF SUBJECT REPAIRED AREA AT EVERY C-CHECK OR 18 MONTHS.

Part: SUPPORT FITTING — CORRODED (TE FLAP BEARING) · airframe 96,049 hrs · 16,466 cycles

CORROSION FOUND ON NR 4 BEARING SUPPORT FITTING, P/N 65B08410-5 BY SIAGE W/SHOP DURING LT INBD TE MID FLAP SHOP VISIT. POS 002, P/N 65B02025-35, S/N 000388. BEARING SUPPORT FITTING P/N 65B08410-5 REPAIR CARRIED OUT IAW BOEING REPAIR NR 1-168327827 BY W/SHOP. REFER TO SWJC NR MS 130376958 FOR REPAIR CERTIFICATION.

Part: SKIN — CRACKED (NR 1 PYLON) · airframe 96,049 hrs · 16,466 cycles

NR 1 PYLON FOUND INTERIOR SKIN CRACKED AT RT SIDE BETWEEN NAC STA 248 TO NAC STA 259, BELOW RHS PRE-COOLER ACCESS CUT OUT LOWER HORIZONTAL STIFFENER. A/F INSP CARRIED OUT AS REQUIRED A/F. S/M REPAIR CARRIED OUT AS PER BOEING MESSAGE NR1-168393257-11, -16,-18 AND FAA 8100-9 DATED 04 APR 2006. CONDUCT REPEAT DV INSPECTION EVERY C-CHK OR 18 MONTHS, WHICHEVER EARLIER.

Part: PYLON — WRINKLED (NR 2) · airframe 96,049 hrs · 16,466 cycles

NR 2 PYLON FOUND WITH WRINKLE SKIN ON RHS FWD OF PYLON VALVE MANUAL CRANK AREA. WRINKLE SKIN INSPECTION CARRIED OUT IAW BOE MSG NUMBER: 1-167645228-9, FOUND SATISFACTORY. REPEAT DETAIL VISUAL INSP EVERY C-CHK, NOT TO EXCCED 18 MONTHS.

Part: STRUCTURE — CRACKED (KRUEGER FLAP) · airframe 96,049 hrs · 16,466 cycles

NR 15 KRUEGER FLAP DEFECTS, P/N 65B39250-2, S/N 000292, ALL "P" SEAL AND MOLDING SEAL WORN. OUTBD ARM PIVOT BEARING MIGRATED. STIFFENER CRACK AT EX-REPAIR AREA. BULL NOSE CRACK AT MID SECTION. REPAIR CARRIED OUT AS PER SWSC MSO 66/02/06, CS/020/03/06, TPAFT 06/0067, P52-1303794370050. INSTALLATION CARRIED OUT IAW AMM 27-81-01.

Part: SKIN — CRACKED (KRUEGER FLAP) · airframe 96,049 hrs · 16,466 cycles

NR 16 KRUEGER FLAT DEFECTS, P/N 65B39200-10, S/N 000296. STIFFENER CRACKS AT RTS EDGE. ALL "P" SEAL AND MOLDING SEAL WORN. MICA STRIPE CRACK. 1 LOCATION DELAMINATED AS MARKED. EXTERNAL PAINT WORK DETERIORATED. REPAIRED CARRIED OUT AS PER SWJC, MSG 63/02/06. CS021- MAR-02. PS2-1303810950060 ATTACHMENT AND INSTALLATION OF NR 16 KRUEGER FLAP CARRIED OUT IAW AMM 27-81-01.2) FUNCTIONAL/ADJUSTMENT CHECKED.

Part: REPAIR — UNKNOWN (BS 1718 S17-19R) · airframe 96,049 hrs · 16,466 cycles

FOUND FUSELAGE SKIN, SECTION 46 NON-STANDARD REPAIR INSTALLED AT AFT UPPER EDGE OF MED 4R CUT OUT, BETWEEN STR 17R & 19R. C/OUT HFEC ON TRIM LINE AND EXISTING FASTENER HOLES WITH DOUBLER REMOVED, NIL FINDING. C/OUT HFEC ON FUSELAGE SKIN WITH DOUBLER AREA, NIL CRACK INDICATION. NEW DOUBLER AND FILLER INSTALLED IAW BOEING MSG NR 1-173448781-2 DATED 23 MARCH 06.

Part: BULKHEAD — CRACKED (BS 400) · airframe 96,049 hrs · 16,466 cycles

FOUND 01 OFF CRACK AT STA 400 WHEEL WELL BULKHEAD PAN ASSY LOWER RT CORNER CUT OUT RBL.15.0. CARRIED OUT EDDY CURRENT INSP, AS PER MTM PT-6 51-00-00 FIG 16 AND 23, NIL CRACK INDICATION AT THIS LINE AND FASTENER HOLES. PAN ASSY REMOVED, FOUND CRACK ON BULKHEAD WEB. WEB REPAIRED IAW BOEING MSG NR 1-166123230-2 DATED 01 MAR 06.

Part: ATTACH FITTING — CRACKED (BS 340) · airframe 96,049 hrs · 16,466 cycles

UPPER DECK FLOORBEAM TO FRAME CONNECTOR AT STA 340 LHS FOUND 1 OFF HOLE CRACK 3MM LONG ON FRAME WEB. CRACKED FRAME WEB REPAIRED IAW, BOEING MSG NR 1-167357676-7 DATED 10 MARCH 06. FABRICATED DOUBLER MATERIAL 2024-T3 0.080", 2 OFF FILLERS MATERIAL 2024-T3 0.080", 2 OFF FILLERS MATERIAL 2024-T3 0.040", 1 OFF STRAP MATERIAL 2024T3 0.080",1 OFF FLANGE DOUBLER MATERIAL 2024-T3 0.050".

Part: BEARING — WORN (KRUEGER HINGE) · airframe 96,049 hrs · 16,466 cycles

NR 12 KRUEGER FOUND WITH FOLLOWING: 5 OUTBD HINGE BEARING FOUND WORN. SEAL FOUND TORN AT TOP AND BOTH SIDES. REPAIRED CARRIED OUT AS PER SWJC:MSG 61/02/06.

Part: SEAL — CRACKED (KRUEGER FLAP) · airframe 96,049 hrs · 16,466 cycles

NR 11 KRUEGER FOUND WITH FOLLOWING DEFECTS, UPPER STIFFENER FOUND CRACKED AT INBD SIDE. BULLNOSE MICA STRIP MISSING. OUTBD CURVE SEAL EDGE ON FLAP FOUND CRACKED. TORN SEAL AT TOP, AND BOTH SIDES, PN=65B39200-9, SN=000302. REPAIRED CARRIED OUT AS PER SWJC: MSO 59/02-06, CSO 19/MAR 06. 752-1303-820260060 ATTACHED.

Part: FRAME — CRACKED (BS 480 S11R) · airframe 96,049 hrs · 16,466 cycles

FUSELAGE FRAME BS 480 RT FOUND WITH 1 CRACKS AT STRINGER 11 CUT OUT. CRACKED FRAME REPAIRED IAW BOEING MSG NR 1-166738303-4, DATED 03 MARCH 06. FABRICATED 2 OFF DOUBLERS MATERIAL 2024-T3 0.063" & 0.063". FABRICATED 1 OFF CUP MATERIAL 2024-T42 0.050".

Part: FRAME — CRACKED (BS 500 S11L) · airframe 96,049 hrs · 16,466 cycles

FUSELAGE FRAME BS 500 LT FOUND WITH 1 CRACKS AT STRINGER 11 CUT OUT. CRACKED FRAME REPAIRED IAW BOEING MSG NR 1-166738303-4, DATED 06 MARCH 06. FABRICATED 2 OFF DOUBLERS MATERIAL 2024-T3 0.63" & 0.032" RESPECTIVELY. FABRICATED 1 OFF CUP MATERIAL 2024-T42 0.050.

Part: FRAME — CRACKED (BS 520 S11R) · airframe 96,049 hrs · 16,466 cycles

FUSELAGE FRAME BS 520 RT FOUND WITH 2 CRACKS AT STRINGER 11 CUT OUT. CRACKED FRAME REPAIRED IAW BOEING MSG NR 1-166738303-4. DATE 06 MARCH 2006. FABRICATED 03 OFF DOUBLERS MATERIAL 2024-T3.(0.063",0.032",0.063" RESPECTIVELY). FAB 1 OFF CUP MATERIAL 2024-T3 0.050.

Part: FRAME — CRACKED (BS 500 S11R) · airframe 96,049 hrs · 16,466 cycles

FUSELAGE FRAME BS 500 RT FOUND WITH 2 CRACKS AT STINGER 11 CUT OUT AND 1 CRACK AT STRINGER 10A. CRACKED FRAME REPAIRED IAW BOEING MSG NR 1-1667383034 DATE 06 MARCH 06. FABRICATED 3 OFF DOUBLERS MATERIAL 2024-T3, 0.063", 0.032", 0.063" RESPECTIVELY. FABRICATED 2 OFF CUPS MATERIAL 2024-T42 0.050".

Part: FRAME — CRACKED (BS 480 S12L) · airframe 96,049 hrs · 16,466 cycles

FUSELAGE FRAME BS 480 LT FOUND WITH 1 CRACKS AT STRINGER 12 CUT OUT. CRACKED FRAME REPAIRED IAW BOEING MSG NR 1-166738303-4 DATED 03 MARCH 06. FABRICATED 2 OFF DOUBLERS MATERIAL 2024-T3 0.063" & 0.032" RESPECTIVELY. FABRICATED 1 OFF CUP MATERIAL 2024-T42 0.050".

Part: BEAM — CRACKED (LT WING LE) · airframe 96,049 hrs · 16,466 cycles

LT WING FIXED LEADING EDGE NOSE BEAM CAP LOWER SKIN FOUND CRACKED AROUND FASTENERS AT ILES 630. LHW FIXED LEADING EDGE SKIN AT ILES 630. CRACKED REPAIRED AS PER BOEING MSG 1-166123104-2,FAA FORM 8100-9 DATED 24 MARCH 2006.

Part: PANEL — CRACKED (RUDDER) · airframe 96,049 hrs · 16,466 cycles

LWR RUDDER SENT TO W/SHOP FOR THE FOLLOWING REPAIRS, LOWER CLOSURE PANEL BONDED STIFFENER FOUND BADLY WORN AT SEVERAL LOCATION. LOWER MOST FWD RIB FOUND CRACKED. LOWEST HINGE BEARING COVER MISSING PART NR 65B05501-1 S/N NSN. REPAIRED RUDDER INSTALLED IAW AMM 27-21-01/401.

Part: MOUNT — CRACKED (KRUEGER FLAP) · airframe 96,049 hrs · 16,466 cycles

RHW NR 15 KRUEGER FLAP TOP MOUNTING POINT (O/B) CUT OUT AT LEADING EDGE CAP, FOUND WITH HEARLINE CRACK PROPAGATING FROM FASTENER HOLE (LWR BEAM), ILES 514. RHW LOWER BEAM CRACK REPAIRED AS PER BOEING MSG 1-168482122-2, AND FAA 8100-9 DATED 20 MARCH 2006.

Part: SKIN — CRACKED (LE FLAP) · airframe 96,049 hrs · 16,466 cycles

LT WING LEADING EDGE FIXED BULLNOSE, FOUND CRACKED AT BOTTOM CUT-OUT, AT NR 12 KRUEGER INBD LINKAGE MOUNTING AREA. ILES 445 LOWER BEAM. LHW LOWER BEAM CRACK REPAIRED AS PER BOEING MSG. 1-168482122-2 AND FAA 8100-9 DATED 20 MARCH 2006.

Part: ACCESS PANEL — CRACKED (NR 1 PYLON) · airframe 96,049 hrs · 16,466 cycles

NR 1 PYLON ACCESS PANEL CUT-OUT FOUND CRACKED AT LOWER AFT SIDE FWD OF NAC STA 291.5. (ACCESS PANEL 453AL). ACCESS PANEL 453AL CUT-OUT CRACK REPAIRED AS PER BOEING MSG, NR 1-167526498-2 AND FAA FORM 8100-9 DATED 15 MARCH 2006, TO CONDUCT DETAIL VISUAL INSPECTIONS EVERY C-CHECK OR 18 MONTHS, WHICHEVER EARLIER.

Part: ACCESS PANEL — CRACKED (NR 1 PYLON) · airframe 96,049 hrs · 16,466 cycles

NR 1 PYLON ACCESS PANEL CUT-OUT FOUND CRACKED AT LOWER AFT SIDE FWD OF NAC STA 291.5 (ACCESS PANEL 453AL). ACCESS PANEL 453AL CUT-OUT CRACK REPAIRED AS PER BOEING MSG, NR 1-167526498-2 AND FAA FORM 8100-9, DATED 15 MARCH 2006 TO CONDUCT DETAIL VISUAL INSPECTIONS EVERY C-CHECK OR 18 MONTHS, WHICHEVER EARLIER.

Part: ACCESS PANEL — CRACKED (NR 1 PYLON) · airframe 96,049 hrs · 16,466 cycles

NR 1 PYLON ACCESS PANEL CUT-OUT FOUND CRACKED AT LOWER AFT SIDE FWD OF NAC STA 248 (ACCESS PANEL 452DL). ACCESS PANEL 452DL CUT-OUT CRACK REPAIRED AS PER BOEING MSG, NR 1-167526498-2 AND FAA FORM 8100-9, DATED 15 MARCH 2006 TO CONDUCT DETAIL VISUAL INSPECTIONS EVERY C-CHECK OR 18 MONTHS, WHICHEVER EARLIER.

Part: SEAT TRACK — DAMAGED (CABIN)

MAINTENANCE PICK UP DURING DAILY CHECK, FOUND MAIN DECK SEAT TRACK DAMAGED AT STATION 1730. CUT OUT DAMAGED AREA AND REPAIRED PER SRM 53-10-05 FIG 1A. (M)

Part: SENSOR — FAILED (STALL WARNING)

IMMEDIATELY AFT T/O, STALL WARNING, STICK SHAKER ACTIVATED ASSOCIATED WITH STALL WARNING. (POWER OFF) LIGHT ILLUMINATION ON PILOTS OVERHEAD PANEL. REMOVED AND REPLACED LT ANGLE OF ATTACK SENSOR. OPS CHECK NORMAL IAW MM.

Part: ACTUATOR — MALFUNCTIONED (MLG)

ON TAKEOFF OUT OF BOG, A NOISE WAS HEARD RIGHT AT ROTATION. ALL SYSTEMS INDICATED NOTHING ABNORMAL. HOWEVER, WHEN THE GEAR WAS RETRACTED THE RIGHT BODY GEAR PRI AND ALT DOOR LIGHTS WERE ON ALONG WITH THE RED DOOR OPEN AND RED GEAR LIGHTS. THE LIGHTS EXTINGUISHED AFTER APPROX 2 MINUTES. (M)

Part: INDICATOR — FAILED (ADI)

CAPTAINS ADI FAILED. INSTRUMENT WARNING LIGHT AND ATTITUDE LIGHT, UNABLE OT SWITCH TO NR 3 INU DUE TO BEING INOPERATIVE. REMOVED AND REPLACED CAPTAINS ADI IAW MM 34-41-05, OPS NORMAL. REMOVED AND REPLACED NR 1 AND NR 3 INU IAW MM 34-41-03 CHECKS ALL SYSTEM OPERATE NORMAL. FUEL DUMPED 59.4 KGS. (M)

Part: ANTENNA — INOPERATIVE (RADAR)

ATB DUE TO BOTH RADARS INOPERATIVE: AFTER LEVEL OFF, BOTH RADAR SCREENS INOPERATIVE. SHOWED BLUE AZIMUTH LINES, BUT NO RANGE OR SWEEP. REPLACED RADAR ANTENNA. OPERATION CK IAW MM, ALL NORMAL. NOTE: NO FUEL DUMPED.

Part: CADC — INOPERATIVE (NR 1)

MIA-JFK - APPROXIMATELY 45 MINUTES DURING CRUISE, NR 1 CADC POWER C/B OPENED. C/B RESET PER FHB PROCEDURES. C/B OPENED AGAIN AND WAS LEFT OPENED FOR DURATIONOF FLIGHT. NY MAINTENANCE CONTROL DIVERT A/C TO MIA. REMOVED AND REPLACED NR 1 CADC OPERATION CHECKED FOUND TO BE SATISFACTORY IAW B747 MM 34-12-01. (M)

Part: CSD — MALFUNCTIONED (NR 1)

NR 1 GENERATOR FIELD TRIPPED CAUSING NR 2 GENERATOR TO TRIP ALSO. CHECKED EACH GENERATOR FREQUENCY AND VOLTS NR 2 OK. RETURNED TO NORMAL OPERATION WITH NR 3. NR 1 FREQUENCY WAS OVER 8000 THEN TRIPPED AGAIN. NR 1 CSD DISCONNECTED BY CHECKLIST PROCEDURES. REMOVED AND REPLACED NR 1 CSD IAW MM 24-11-01. OPERATION CHECK NORMAL NO LEAKS FOUND IAW MM 24-20-00. REMOVED AND REPLACED NR 1 GCU OPERATION CHECK NORMAL IAW MM 24-20-00. REMOVED AND REPLACED NR 2 GCU OPERATION CHECK NORMAL IAW MM 24-20-00. (M)

Part: STIFFENER — CRACKED (NR 3 PYLON)

DURING CURRENT C-CHECK AT SIAEC, FOUND NR 3 PYLON NR 3 LONGITUDINAL STIFFENER VERTICAL FLANGE, BELOW PRECOOLER EXHAUST VENT, CRACKED THREE PLACES AT NAC 245, 247 AND 257. PYLON PREVIOUSLY MODIFIED PER SB 747-54-2163 AND 747-54-2091 WHICH CONSISTS OF AN UPPER ANGLE INSTALLE DON THE STIFFENER FROM NAC 234 TO 272 ALONG WITH AN EXTERNAL SKIN DOUBLER. ADDITIONAL REPAIR CONSISTS OF A LOWER ANGLE INSTALLED FROM NAC 234 TO 252. CRACK AT NAC 257 MAY BE LEFT AS IS. HFEC INSPECTED ALL OPEN HOLES COMMON TO BOTH ANGLES AND HOLES IN THE REMAINING REPAIR. NO ADDITIONAL CRACKING FOUND ON STIFFENER OR ALUMINUM SKIN. REPAIR ANGLE INSTALLED PER STANDARD SRM PRACTICES IAW SB'S MENTIONED ABOVE. (M)

Part: STIFFENER — CRACKED (NR 3 NACELLE)

DURING CURRENT C-CHECK, AT SIAEC FOUND NR 2 PYLON (NR 3) LONGITUDINAL STIFFENER VERTICAL FLANGE, BELOW PRECOOLER EXHAUST VENT, CRACKED THREE PLACES AT NAC 245, 247 AND 257. PYLON PREVIOUSLY MODIFIED PER SB 747-54-2163 AND 747-54-2091 WHICH CONSISTS OF AN UPPER ANGLE INSTLALED ON THE STIFFENER FROM NAC 234 TO 272 ALONG WITH AN EXTERNAL SKIN DOUBLER. ADDITIONAL REPAIR CONSISTS OF A LOWER ANGLE INSTALLED FROM NAC 234-252. CRACK AT NAC 257 MAY BE LEFT AS IS. HFEC INSPECTED ALL OPEN HOLES COMMON TO BOTH ANGLES AND HOLES IN THE REMAINING REPAIR. NO ADDITIONAL CRACKING FOUND ON STIFFENER ON ALUMINUM SKIN. REPAIR ANGLE INSTALLED PER STANDARD SRM PRACTICES IAW S/B'S MENTIONED ABOVE. (M)

Part: STIFFENER — CRACKED (NR 3 PYLON)

DURING CURRENT C-CHECK AT SIAEC, FOUND NR 4 PYLON NR 3 LONGITUDINAL STIFFENER VERTICAL FLANGE, BELOW PRECOOLER EXHAUST VENT, CRACKED THREE PLACES AT NAC 245, 247 AND 257. PYLON PREVIOUSLY MODIFIED PER SB 747-54-2163 AND 747-54-2091 WHICH CONSISTS OF AN UPPER ANGLE INSTALLED ON THE STIFFENER FROM NAC 234 TO 272 ALONG WITH AN EXTERNAL SKIN DOUBLER. ADDITIONAL REPAIR CONSISTS OF A LOWER ANGLE INSTALLED FROM NAC 234-252. CRACK AT NAC 257 MAY BE LEFT AS IS. HFEC INSPECTED ALL OPEN HOLES COMMON TO BOTH ANGLES AND HOLES IN THE REMAINING REPAIR. NO ADDITIONAL CRACKING FOUND ON STIFFENER OF ALUMINUM SKIN. REPAIR ANGLE INSTALLED PER STANDARD SRM PRACTICES IAW S/B'S MENTIONED ABOVE. (M)

Part: SKIN — DELAMINATED (NR 3 NACELLE)

DURING CURRENT C-CHECK AT SIAEC, FOUND NR 3 ENGINE LEFT FAN COWL DELAMINTED APPROXIMATELY 8 INCHES BY 8 INCHES IN GENERAL REWORK AREA NOTED BY SB 78-2150 DURING TRAS LOCK MODIFICATION. THE OUTER DELAMINTED SKIN AND FILLER WERE STAGGER CUT TO REMOVE DELAMINATED AREA. PERFORMED HFEC OF SKIN CUT EDGES. NO CRACKING DETECTED. FABRICATED REPLACEMENT STAGGERED FILLER AND TWO ADDITIONAL STAGGERED REPAIR DOUBLERS WITH A 3 INCH AND 1.5 INCH OVERLAP. A STRUCTURAL HOT BOND METHOD WAS USED TO INSTALL REPAIR DOUBLERS AND FILLERS IAW SRM 51-40-06 PAR 3K. PART NUMBER BECAME 673U0032-39 AFTER MODIFICATION FROM 65B91241-38. (M)