N505MC

Part: PANEL — DELAMINATED (LWS 170-630) · airframe 96,641 hrs · 21,139 cycles

LT WING UPPER L/E FIXED PANEL BETWEEN AISLES 170.0 TO AISLES 630.72 HAS AN AREA DELAMINATION, AREA IS 58.0 INCH LONG BY 50.0 INCH WIDE. INTERIM REPAIR WAS ACCOMPLISHED AS PER B747-200 SRM 51-40-16 AND ATLAS AIR EO NR 4757A402 PART 4. PER FAA FORM 8110-3 REQUIRES DETAIL VISUAL INSPECTIONS AT EVERY "C" CHECK PER PART 5 OF EO NR 4757A402.

Part: PANEL — DELAMINATED (LT WING) · airframe 32,224 hrs · 5,447 cycles

UPPER SURFACE OF LEFT WING INBOARD NR 2 ENGINE FIBERGLASS HAS HOLE AND DENT. REPAIRED PER XEO 57-102607 TRANS TO NON MEL N07-126. REINSPECTED IN ORD AND ACCOMPLISHED XEO 57-102607 PART 3 IAW SRM 51-40-16. REPAIRED AND TO BE INSPECTED EVERY 10 FLIGHT CYCLES UNTIL PERM REPAIR IS ACCOMPLISHED AT THE NEXT "A" CHECK.

Part: SENSOR — FAILED (STALL WARNING) · airframe 96,396 hrs · 21,086 cycles

AIR TURN BACK, AT ROTATION STICK SHAKER CAME ON AND STAYED ON UNTIL LANDING. VR SPEED WAS 129 KNOTS. REMOVED AND REPLACED LEFT AOA SENSOR AND STALL WARNING COMPUTER IAW 27-30-01, OPS CHECKED NORMAL IAW 27-30-00.

Part: SKIN — DAMAGED (BS 2594-2604) · airframe 96,397 hrs · 21,048 cycles

LOWER AFT FUSELAGE EXTERIOR SKIN DOUBLER/TRIPLER AT FS 2594 TO 2604.0 PREVIOUS REPAIR DAMAGED WITH HEAVY ABRASION/SCRAPING DUE TO TAIL DRAG. REMOVED AND REPLACED DOUBLER/TRIPLER REPAIR AS PER 747-200 SRM 51-30-02 AND 51-30-03 FIG 1 SHEETS 1 THRU 6. REFERENCE ATLAS XEO 53-092807.

Part: FRAME — DAMAGED (BS 2638) · airframe 96,397 hrs · 21,048 cycles

AFT LOWER FUSELAGE AT FS 2638 FRAME LOWER SURFACE SCRAPED DUE TO TAIL DRAG. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-20-01 FIG 3, AND SRM 51-30-02. ALSO REFERENCE ATLAS AIR XEO NR 53-093007-1.

Part: FRAME — DAMAGED (BS 2658) · airframe 96,397 hrs · 21,048 cycles

AFT LOWER FUSELAGE AT FS 2658 FRAME LOWER SURFACE SCRAPED DUE TO TAIL DRAG. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 53-10-04 FIG 75 SHEETS 1 THRU 15. REFERENCE ATLAS AIR XEO 53-093007.

Part: SKIN — DAMAGED (BS 2613) · airframe 96,397 hrs · 21,048 cycles

LOWER AFT FUSELAGE EXTERIOR SKIN DOUBLER/TRIPLER AT FS 2613 PREVIOUS REPAIR DAMAGED WITH HEAVY ABRASION/SCRAPING DUE TO TAIL DRAG. REMOVED AND REPLACED DOUBLER/TRIPLER REPAIR AS PER 747-200 SRM 51-30-02 AND 51-30-03 FIG 1 SHEETS 1 THRU 6. REFERENCE ATLAS XEO 53-092807.

Part: SKIN — DAMAGED (BS 2742-2792) · airframe 96,397 hrs · 21,048 cycles

FUSELAGE TAIL CONE LOWER AREA FROM FS 2742 TO 2792 SKIN AND FRAMES SCRAPED AND DENTED DUE TO TAIL DRAG. REMOVE AND REPLACED LOWER SECTION OF CONE FROM STA 2742 TO 2792, ASSY P/N 65B02785-1 AND PERMANENT REPAIRS ACCOMPLISHED AS PER B747-200 SRM 51-20-01 FIG 3, SRM 51-30-02 AND 51-10-02. ALSO REF: ATLAS AIR XEO NR 53-092907.

Part: SKIN — TORN (ZONE 100) · airframe 96,397 hrs · 21,048 cycles

LT INBOARD ELEVATOR, TRAILING EDGE COMPOSITE SKIN TIP AREA HAD GROUND DAMAGE. PERMANENT REPAIR ACCOMPLISHED AS PER B747 SRM 51-40-09, FIG 1A, SHEET 1 AND FIG 8, SHEETS 1 AND 2. REFERENCE ATLAS AIR EO NR 4755A049.

Part: WIRE — CHAFED (NR 3 FIRE WARN) · airframe 94,930 hrs · 20,769 cycles

AFTER T/O FROM AMS, WHERE NR 3 ENGINE B LOOP WAS DEFERRED AS INOP. NR 3 ENGINE FIRE BELL AND LIGHT ILLUMINATED, NR 3 ENGINE A LOOP WAS ERRATIC AND WAS AT 10 ON THE SCALE FLUCTUATING. ENGINE SHUT DOWN AS PER ATLAS PROCEDURE USING FIRE CHECK LIST FIRE SWITCH AT 1602Z, WIND MILL OIL PRESSURE 7-9 PSI. FOUND WIRING AT CONNECTORS DM132A AND DM214A WITH WORN INSULATION AND CHAFING AGAINST CONNECTORS. REPLACED CONNECTORS PER SWPM 20-62-19. ALL CHECKS SATISFACTORY PER MM 26-11-00. NO FURTHER FAULT FOUND.

Part: STRAP — CRACKED (BS 800) · airframe 94,762 hrs · 20,738 cycles

CRACKS FOUND ON BS 800 LT STRAP AND INNER CHORD AT NR 2 MAIN ENTRY DOOR. REPAIRED ACCOMPLISHED IAW SR ID NR 1-289052431 AND FAA FORM 8100-9.

Part: BULKHEAD — CORRODED (BS 1250) · corrosion level 2 · airframe 94,762 hrs · 20,738 cycles

BS 1250, L WLG W/W CANTED PRESSURE BULKHEAD, NR 2 PACK COOLING DUCT CUTOUT FOUND CORROSION. REPAIRED ACCOMPLISHED AS PER BOEING SR ID NR 1-289645346-1 THRU -5 AND FAA FORM 8100-9.

Part: SKIN — CORRODED (BS 1241) · corrosion level 2 · airframe 94,762 hrs · 20,738 cycles

FOUND M/DECK STA1241 FRAME AND SKIN SPLICE AREA HAS HOLE, CRACKED AND CORRODED. REPAIRED ACCOMPLISHED AS PER BOEING MESSAGE NR 1-29020776-1 AND -6 AND FAA FORM 8100-9.

Part: SKIN — CORRODED (BS 1319) · corrosion level 2 · airframe 94,762 hrs · 20,738 cycles

M/DECK RT NR 3 MED CUTOUT AFT UPPER CORNER SKIN STA1319, STR 17R-18R FOUND CORRODED. REPAIRED ACCOMPLISHED AS PER BOEING MESSAGE NR 1-289657194-1, 747 SRM 53-30-03 FIG 44 AND FAA FORM 8100-9.

Part: DOUBLER — SEPARATED (RT WING) · airframe 94,762 hrs · 20,738 cycles

NR 3 PYLON FWD FIXED FAIRING LT EXTERIOR SURFACE AFT CORNER SKIN DOUBLER SEPARATED. FAIRING REPLACED BUT NUMEROUS FASTENERS HOLES FOUND MISALIGNED. TIME LIMIT REPAIRED ACCOMPLISHED AS PER BOEING MESSAGE NR 1-292185930-1 THRU -14, DWG 65B90813-52 AND FAA FORM 8100-9.

Part: INTERCOSTAL — CRACKED (BS 420) · airframe 94,762 hrs · 20,738 cycles

UPPER DECK FLOOR SUPPORT INTERCOSTAL CRACKED AT BS 420, LBL 50. U/DECK FLOOR SUPPORT INTERCOSTAL AT BS420, LBL 50 REPLACED AS PER SRM 51-30-02.

Part: STRINGER — CORRODED (BS 978 S47L) · corrosion level 2 · airframe 94,762 hrs · 20,738 cycles

FWD CARGO COMPARTMENT STA 978, STR 47L FOUND CORRODED. FWD CARGO COMPARTMENT STA978, STR47L REPLACED AS PER SRM 51-10-01.

Part: STRINGER — CRACKED (BS 905) · airframe 94,762 hrs · 20,738 cycles

M/DECK ZONE "C" LT SIDEWALL STRUCTURE STA 905, STR-10L FOUND CRACKED. REPAIRED ACCOMPLISHED AS PER SRM 53-10-03, FIG 4.

Part: KEELBEAM — BULGED (BS 1450) · airframe 94,762 hrs · 20,738 cycles

FOUND KEEL BEAM BOTH SIDES WEB BULGE FOUND AT BS 1450. REPAIRED ACCOMPLISHED AS PER BOEING SR ID NR 1-286690602-1 THRU -10.

Part: SHEAR TIE — CRACKED (BS 840) · airframe 94,762 hrs · 20,738 cycles

RT STA 840 FWD CHANNEL TENSION TIE AT 12 O'CLOCK FOUND CRACKED. REPAIRED ACCOMPLISHED AS PER BOEING SR ID 1-288425027-1 AND -6, 1-289012875-1, SB747-53-2502 AND FAA FORM 8100-9.

Part: STRINGER — CRACKED (BS 895 S7R) · airframe 94,762 hrs · 20,738 cycles

M/DECK STA 895 STR 7R FOUND CRACKED. STRINGER REPAIRED ACCOMPLISHED AS PER SRM 53-10-03 FIG 4.

Part: STRINGER — CRACKED (BS 875) · airframe 94,762 hrs · 20,738 cycles

M/DECK LT SIDE STA 875, STR9L FOUND CRACKED. STRINGER REPAIRED AS PER SRM 53-10-03, FIG.4

Part: CREASE BEAM — CRACKED (BS 940) · airframe 94,762 hrs · 20,738 cycles

M/DECK RTH SIDE STA 940, S-8R CREASE BEAM WEB FOUND CRACKED. CREASE BEAM WEB REPLACED AS PER SRM 51-10-01 AND 51-30-02.

Part: SKIN — PUNCTURED (TE FLAP) · airframe 94,762 hrs · 20,738 cycles

NR 20 VC FLAP FOLDING NOSE I/B END SKIN PUNCHED. REPAIRED ACCOMPLISHED AS PER BOEING SR ID NR 1-290202458-1 THRU -3 AND FAA FORM 8100-9.

Part: SKIN — CRACKED (NR 3 NACELLE) · airframe 94,762 hrs · 20,738 cycles

NR 3 ENGINE LT CORE COWL SKIN BOND DOUBLER CRACKED AT AIR EXHAUST DUCT AFT LOWER PORTION. REPAIRED ACCOMPLISHED AS PER BOEING SR ID NR 1-286833874-1 THRU -6, DWG 65B94280 AND FAA FORM 8100-9.

Part: CREASE BEAM — CRACKED (BS 960) · airframe 94,762 hrs · 20,738 cycles

FOUND M/DECK STA960, S-7R CREASE BEAM SUPPORT ANGLE FOUND CRACKED. CREASE BEAM SUPPORT WEB REPLACED AS PER SRM 51-10-01.

Part: STRINGER — CORRODED (BS 980) · corrosion level 2 · airframe 94,762 hrs · 20,738 cycles

FOUND FWD CARGO COMPT STA 980, STR 43R IS CORRODED. STRINGER REPAIRED AS PER SRM 53-10-03 FIG 1.

Part: SKIN — MISREPAIRED (BS 690) · airframe 94,762 hrs · 20,738 cycles

FUSELAGE BS 690 S31L HAS 14" BY 12" EXTERNAL DOUBLER TO LT UPPER STATIC PORT PREVIOUS REPAIRED PER SRM 51-70-00 PG 8E AND F FIG 3 SHEET 6 AND 7. THIS REPAIR IS BEYOND THE LIMIT. REPAIRED ACCOMPLISHED AS PER SRM 53-30-03 FIG 1 AND 51-70-00 FIG 3.

Part: SKIN — CRACKED (BS 240) · airframe 94,762 hrs · 20,738 cycles

FUSELAGE SKIN EXTERNAL DOUBLER FOUND CRACKED AT NLG LT FWD CORNER. REPAIRED ACCOMPLISHED AS PER BOEING SR ID NR 1-290193820-1 THRU -5 AND FAA FORM 8100-9.

Part: FAIRING — CRACKED (THRUST REVERSER) · airframe 94,762 hrs · 20,738 cycles

ENGINE NR 2 RT T/REV AFT UPPER BEAVER TAIL FAIRING ASSY INNER SKIN FOUND CRACKED. REPAIRED ACCOMPLISHED AS PER EO NR 4778A094 AND FAA FORM 8110-3.

Part: MOUNT — DAMAGED (NR 4 ENGINE) · airframe 94,762 hrs · 20,738 cycles

NR 4 PYLON FWD ENGINE MOUNT FITTING BOTH I/B AND O/B LUG BORE HOLES FOUND OVERSIZED. REPAIRED ACCOMPLISHED AS PER BOEING SR ID NR 1-290193672-1 THRU -3 AND FAA FORM 8100-9.

Part: SKIN — CRACKED (BS 570) · airframe 94,762 hrs · 20,738 cycles

FUSELAGE SKIN BS 570 EQUIPMENT COOLING OUTLET FOUND CRACKED. REPAIRED ACCOMPLISHED AS PER SB747-53-2386 FIG 5 AND 10.

Part: ACCESS DOOR — DAMAGED (THRUST REVERSER) · airframe 94,762 hrs · 20,738 cycles

NR 3 ENGINE RT FAN T/REV ACCESS DOOR ASSY SKIN DAMAGED. REPAIRED ACCOMPLISHED AS PER EO NR 4778A095 AND FAA FORM 8110-3.

Part: WEB — CORRODED (BS 1350) · airframe 94,762 hrs · 20,738 cycles

FOUND LT WLG BS 1350 HORIZONTAL WEB UPPER SURFACE FOUND CORROSION. CORROSION REMOVED AND AREA PROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (LT WING) · airframe 94,762 hrs · 20,738 cycles

LEFT WING UPPER WING SKIN AT WS320, STR 14L-14L FOUND CORROSION. CORROSION REMOVED AND PROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (LT WING) · airframe 94,762 hrs · 20,738 cycles

FOUND LEFT WING UPPER WING SKIN AT WS 1280 FOUND CORROSION. CORROSION REMOVED AND PROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (RT WING) · airframe 94,762 hrs · 20,738 cycles

RIGHT WING UPPER SURFACE WS 697, STR28R AT FRONT SPAR FOUND CORROSION. CORROSION REMOVED AND PROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (RT WING) · airframe 94,762 hrs · 20,738 cycles

FOUND RIGHT WING UPPER SURFACE RWS642 AT MID SPAR FOUND CORROSION. CORROSION REMOVED AND PROTECTED AS PER SRM51-10-01 AND 51-10-02.

Part: SKIN — DENTED (BS 1810) · airframe 94,762 hrs · 20,738 cycles

FUSELAGE SKIN DENT FOUND AT BS 1810, S51L-S51R. DENT AREA REWORKED AND PROTECTED AS PER SRM 51-40-01 AND 51-10-02.

Part: SKIN — SCRATCHED (BS 2310 S38-40L) · airframe 94,762 hrs · 20,738 cycles

FOUND FUSELAGE SKIN SCRATCH FOUND AT BS 2310, S38L-S40L. SCRATCH SLIGHTLY SMOOTHED AND PROTECTED AS PER SRM 51-10-02.

Part: SHEAR WEB — CRACKED (BS 840-860) · airframe 94,762 hrs · 20,738 cycles

TENSION TIE BS 840-BS 860, LT SLOPING SHEAR WEB FOUND CRACKED AT FWD I/B LOWER CORNER. LEFT SLOPING SHEAR WEB REPLACED AS PER SRM 51-10-01.

Part: BLOWOUT DOOR — CHAFED (NR 1 NACELLE) · airframe 94,762 hrs · 20,738 cycles

ENGINE NR 1 AND NR 2, RT C-DUCT BLOW OUT DOOR ASSEMBLY HAS MISSING MATERIAL AND CHAFE MARKED. REPAIRED ACCOMPLISHED AS PER EO NR 4778A093 AND FAA FORM 8110-3.

Part: SKIN — CORRODED (BS 1020) · corrosion level 2 · airframe 94,762 hrs · 20,738 cycles

FOUND CENTER TANK LOWER SKIN LOWER SURFACE FOUND CORROSION JUST ABOVE NR 1 ACM. CORROSION BLEND OUT AND HFEC INSPECTION PERFORMED AS PER BOEING SR ID NR 1-290707077-1 THRU -3 AND FAA FORM 8100-9.

Part: SKIN — CORRODED (LT WING) · corrosion level 2 · airframe 94,762 hrs · 20,738 cycles

LEFT WING LEADING EDGE BULLNOSE FOUND CORROSION OUTBOARD OF LANDING LIGHT. PERMANENT REPAIRED ACCOMPLISHED AS PER BOEING MESSAGE 1-286780848-2 DATED 13 FEB,2007 AND EO NR 4757A281.

Part: INTERCOSTAL — CRACKED (BS 395) · airframe 94,762 hrs · 20,738 cycles

FOUND UPPER DECK FLOOR SUPPORT INTERCOSTAL CRACKED AT BS 395 RBL 6. U/DECK FLOOR SUPPORT INTERCOSTAL REPLACED AS PER SRM 51-10-01.

Part: STIFFENER — CRACKED (BS 400) · airframe 94,762 hrs · 20,738 cycles

FOUND UPPER DECK FLOORBEAM ONE STIFFENER CRACKED AT BS 400 LBL15. UPPER DECK FLOORBEAM STIFFENER REPLACED AS PER SRM 51-10-01.

Part: FIRE WARNING — FALSE ACTIVATION (APU BAY) · airframe 93,730 hrs · 20,512 cycles

APU FIRE WARNING CAME ON IN FLT WITH BELL AND MASTER CAUTION LIGHT ON. APU FIRE HANDLE PULLED AND FIRE BOTTLE IAW FHB 3.26.5. PLACED APU, APU FIRE WARNING ON APU AND APU FIRE BOTTLE ON DMI. APU INSPECTED IAW 49-31-00 PG 601. NO EVIDENCE OF FIRE FOUND. (OPEN).

Part: CONTROL UNIT — MALFUNCTIONED (ANTI SKID SYS) · airframe 93,312 hrs · 20,408 cycles

(DIV) AFTER T/O GROUND SAFETY RELAY LIGHT REMAINED ON ALONG WITH G/S 1 ANT LIGHT, PROBE HEAT LIGHT AND ALL 4 ALTERNATE NOT TILTED LIGHTS WERE ILLUMINATED. NR 1 ENG OVER SPEED ON N2 110.2 FOR 15 SEC AT CRUISE ALL OTHER ENG INDICATIONS NORMAL. NR 3 ENG N1 OVER SPEED LIMIT 119.1 FOR 8 SEC AT CRUISE ALL OTHER ENG INDICATIONS NORMAL. NR 4 ENG OVER SPEED N1 AT 119.8 FOR 19 SECONDS, ALL OTHER ENG INDICATIONS NORMAL. AT TOUCHDOWN AUTO BRAKES KICKED OFF ON THERE OWN. RIGHT WING AND BODY GEAR BRAKE TEMPS CLIMBED TO 8.0 ON THE BRAKE TEMP GAUGE THE LEFT BODY AND WING GEAR TEMPS REMAINED AT LOW GREEN PRIOR TO BLOCK ALL ANTI SKID LIGHTS ILLUMINATED. REMOVED AND REPLACED LANDING GEAR LOGIC MODULE AS PER MM 32-61-14, OPS

Part: WARNING HORN — FALSE ACTIVATION · airframe 93,125 hrs · 20,372 cycles

RTO TAKEOFF REJECTED AT 110 KTS DUE TO TAKEOFF WARNING HORN. AFTER EXITING RUNWAY A/C CHECKED FOR CONFIGURATION DISCREPANCY. SUSPECT T/O WARNING, ENABLE BY FLAP TAKEOFF WARNING SWITCH, S339 FOUND STICKING, CLEANED SWITCH AND PERFORMED AURAL WARNING LOGIC CIRCUIT TEST IAW MM 31-26-00 ALL NORMAL. PERFORMED FLAPS SYS OPERATIONAL CHECK IAW MM 27-51-00, ALL NORMAL. PERFORMED AUTO STAB TRIM OPERATIONAL CHECK IAW MM 22-14-00, ALL NORMAL. HIGH ENERGY STOP DAMAGE CONDITION INSPECTION CARRIED OUT IAW MM 5-51-10, ALL NORMAL. TIRE PRESSURE OK. BRAKE CONDITION NORMAL.

Part: BOLT — SHEARED (THRUST REVERSER) · airframe 92,862 hrs · 20,318 cycles

NR 3 LT REVERSER, CENTER HINGE FITTING 2 EACH BOLTS FRACTURED. REMOVED AND REPLACED CENTER HINGE FITTING AND BOLTS AS PER 747 SRM 51-30-05 TABLE I PAGE 6 AND SRM 51-30-04 TO NEXT OVERSIZED BOLT P/N BACB30US6K13Y. FASTENER HOLES WERE INSPECTED AS PER NDT MANUAL PART 6, 51-00-00 FIG 9. NO DEFECTS NOTED.

Part: SKIN — CRACKED (NR 2 PYLON) · airframe 92,862 hrs · 20,318 cycles

PYLON NR 2 FORWARD ACCESS PANEL CUTOUT SKIN AND DOUBLER HAS A 1 1/16 INCH CRACK AT LOWER AFT CORNER. ACCOMPLISHED SKIN AND INNER DOUBLER REPAIR AS PER 747 SRM 54-31-03 FIG 6 AND REFERENCE ATLAS AIR XEO NR 54-070806-2.

Part: BRACE — CHAFED (PYLON) · airframe 92,862 hrs · 20,318 cycles

PYLON NR 4 DIAGONAL BRACE HAS A CHAFE ON OUTBOARD SIDE CAUSED BY HYDRAULIC COMPARTMENT DOOR ROD FOUND NOT SECURED. ACCOMPLISHED BLEND REPAIR ON BRACE P/N 321U2731-102, S/N MFR 16889 RP 06709322 AS PER 747 SRM 51-41-01 FIG 3 AND REFERENCE ATLAS AIR XEO NO. 54-070806-1. BLEND-OUT IS ON BRACE ZONE "5" AND IS 1.5 INCH BY 1.75 INCH WIDE AND 0.094 INCH DEEP. BLEND-OUT IS WITHIN LIMITS. AREA WAS FLAP PEENED, TREATED AND PRIMED AS PER 747 SRM 54-41-01 FIG 3. HFEC WAS ACCOMPLISHED AS PER NDT MANUAL PART 6 51-00-00 FIG 4.

Part: SKIN PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 92,243 hrs · 5,730 cycles

LT WING LE O/B OF O/B LANDING LT AT AREA OF LOOSE RIVETS THERE IS TWO SPOTS OF INNERGRANULAR CORROSION (MARKED). INTERIM REPAIR TO LEADING EDGE LT WING PER SRM 57-30-04 AND XEO57-041306 AND 8110-3. REPEAT INSP EVERY A CK AND PERMANENT REPAIR AT C-CK.

Part: SKIN — CRACKED (BS 1796) · airframe 91,552 hrs · 20,086 cycles

REFERENCE ENGINEERING ORDER XEO 53-021706, FOUND DENT CRACKED APPROXIMATELY 1 INCH LONG BS 1796 STRINGER 32 R

Part: SUPPORT — CRACKED (TE FLAPS) · airframe 91,552 hrs · 20,086 cycles

LEFT WING O/B MIDFLAP COVE PANEL CRACKED 18 INCHES LONG AT 3RD SUPPORT ARM I/B OF NR 1 CANOE.

Part: SUPPORT — CRACKED (ZONE 500) · airframe 91,552 hrs · 20,086 cycles

RIGHT WING OB MID FLAP COVE PANEL CRACKED AT 4TH SUPPORT ARM IB OB #8 CANOE APPROX 18" LONG

Part: PANEL — CRACKED (TE FLAP) · airframe 91,552 hrs · 20,086 cycles

L/W IB MIDFLAP COVE PANEL CRACKED AT PREVIOUS REPAIR- 4TH SUPPORT ARM FROM OB END.

Part: GEARBOX — SEIZED (NR 2 ENGINE)

DURING CRUISE ENGINE NR 2 FUEL FLOW BEGAN FLUCTUATING FOR 30 SECONDS, THEN THE ENGINE SHUTDOWN WITH THE FOLLOWING INDICATIONS. N1=26.1 PERCENT, EGT 0.0, N2 0.0, OIL PRESSURE 0.0, OIL QUANTITY 3.7 GALLONS, AND FUEL FLOW WAS 1.095. ENGINE WAS WINDMILLING 3 HOUR 45 MINUTES. REMOVED AND REPLACED NR 2 ENGINE IAW MM. PERFORMED TEST NR 3 AND 8. FOUND ALL PARAMETERS WITHIN LIMITS. (K)

Part: PANEL — CRACKED (NR 2 PYLON)

NR 2 PYLON OUTBOARD SIDE CUTOUT FOR PANEL 463CL HAS A .875 INCH CRACK AT AFT CORNER OF SKIN. CRACK WAS NDT INSPECTED TO VERIFY AREA OF CRACK AS PER B747 NDT MANUAL PART 6 51-00-00 FIG 23. STOP DRILLED CRACK IAW B747 SRM 51-10-01 PAGE 12. HFEC INSPECTED STOP DRILL HOLE AND FOUND NO CRACKS EXTENDING BEYOND STOP DRILL HOLE AS PER B747 NDT MANUAL PART 6-51-00-00 FIG 23. INSTALLED DOUBLER REPAIR IAW SRM 54-31-03 FIG 6. (M)

Part: RHEOSTAT — BURNED (LIGHTS)

HOT SMELL (ELECTRICAL) DETECTED IN CRUSE. C/B PILOT PANEL ENDER FLIGHT DECK LIGHTS WAS PULLED ON P6 PANEL. SMELL STOPPED, SHORTLY AFTER. PANEL BELOW CAPTAIN CUP HOLDER FELT HOT. ON T/S FOUND T77 DIMMER BURNED. REMOVED AND REPLACED DIMMER. OPS CHECK NORMAL. (K)

Part: SUPPORT — CRACKED (FUSELAGE)

DURING OVERNIGHT, EXTERNAL IMPACT BY A FOREIGN OBJECT CAUSED BY A TORNADO. AN INSPECTION OF THE AIRCRAFT WAS CARRIED OUT AND IT WAS OBSERVED THAT AT BS 1034 RBL 104, THE UNDERWING FAIRING SUPPORT LOWER CHORD WAS CRACKED AT THE OUTBOARD FLANGE. THE LONGITUDINAL CRACK IS APPROXIMATE 3 INCHES LONG. THERE WERE NO OTHER REPAIRS WITHIN 12 INCHES OF THIS DAMAGE. TRIMMED OFF THE CRACKED AREA. NDT INSPECTED TO CONFIRM NO CRACK OF DEFECT EXISTS AT THE TRIMMED EDGE AND REPAIRED AREA. FABRICATED REPAIR PART FROM REPAIR ANGLE 7075-0 AND HEAT TREATED TO T6 AFTER FORMING. PERFORMED ULTRASONIC INSPECTION OF THE ANGLE AFTER FORMING TO ENSURE DEFECT FREE CONDITION. BOEING CONCURRED THAT THE REPAIR IS STRUCTURALLY ACEPTAB

Part: PANEL — DELAMINATED (LT WING)

FOUND LER LEFT WING PANEL AT ILES 173.6 HAD DELAMINATION HEAT DAMAGE WHILE ON GROUND. THE PANELS WERE REPLACED IAW SRM 51-30-02 AND AMM 51-24-11. (M)

Part: SEQUENCE VALVE — FAILED (NLG)

AFTER TAKEOFF, ON GEAR RETRACTION NOSE LANDING GEAR DOORS KEPT CYCLING, ATTEMPTED RECYCLE NO EFFECT. REMOVED AND REPLACED NOSE GEAR, OPERATED DOOR SEQUENCE VALVE PER MM 32-34-08 PAGE 401-405, OPS AND LEAK CHECK NORMAL. UIEA (M)

Part: SEQUENCE VALVE — MALFUNCTIONED (NLG)

AFTER TAKEOFF, ON GEAR RETRACTION NOSE LANDING GEAR DOOR KEPT CYCLING. ATTEMPTED RE-CYCLE NO EFFECT. REMOVED AND REPLACED NOSE GEAR OPERATED DOOR SEQUENCE VALVE PER MM 32-34-08. PAGE 401-405 OPS AND LEAK CHECK NORMAL. (M)

Part: VALVE — MALFUNCTIONED (PYLON) · airframe 86,902 hrs · 19,062 cycles

AFTER ENGINE START NR 1 ENGINE HAD NO RESPONSE TO THROTTLE MOVEMENT. ALL INSTRUMENTS INDICATED ENGINE AT IDLE POWER. CLEANED CDP LINE, NO HELP, REPLACED CIT SENSOR, ENGINE NOW RUNS HIGH EGT, FOUND PYLON VALVE AT FAULT, OPENED DMI NR 36-5-2.

Part: VALVE — MALFUNCTIONED (NR 1 ENGINE) · airframe 86,682 hrs · 19,015 cycles

ON ENGINE START-UP NR 1 ENGINE PYLON VALVE WILL NOT OPEN DURING MANUAL ENGINE START. REPOSITIONED PYLON VALVE IN ORDER TO ACHIEVE ENGINE START, OPS CHECK GOOD IAW MM 36-11-04.

Part: VALVE — MALFUNCTIONED (NR 1 PYLON) · airframe 86,682 hrs · 19,015 cycles

DMI NR 32768, NR 1 PYLON VALVE INOPERATIVE, ALSO HIGH PRESSURE BLEED VALVE ON ENGINE NR 1. REMOVAL AND REPLACEMENT. REMOVED AND REPLACED PYLON VALVE DUE TO NOT CLOSING COMPLETELY , OPS CHECK AND LEAK CHECKS GOOD IAW MM 36-11-04.

Part: MANIFOLD — LEAKING (NR 3 ENG FUEL) · airframe 86,515 hrs · 18,974 cycles

FUEL DRAINING FROM DRAIN MAST NR 3 ENGINE PORT ON ENGINE START. REPLACED NR 3 ENGINE VBR FUEL MANIFOLD ASSY AS PER MM 75-32-00. OPS & LEAK CHECK OK AS PER MM 71-00-00 TEST NR 3.

Part: WEB — DAMAGED (FUSELAGE) · airframe 86,030 hrs · 18,873 cycles

ON POST FLIGHT INSPECTION, FOUND FAIRING OVER RIGHT WING ROOT OPEN AND FOUND WEB PANEL DAMAGED. ACCOMPLISHED REPAIR OF WEB PANEL PER SRM 51-40-02. SURROUNDING AREA CLEANED AND INSPECTED. NO FURTHER DAMAGE.

Part: TIRE — SEPARATED (MLG) · airframe 85,975 hrs · 18,861 cycles

TOWER REPORTED LOST TIRE ON LANDING. REPLACED NR 3 TIRE AND BRAKE, NR 4 TIRE.

Part: PANEL — DAMAGED (LT WING) · airframe 86,004 hrs · 18,867 cycles

LT WING ACCESS PANEL OB AND FWD OF NR 4 FLAP TRACK FIX FAIRING 3 X 3 INCH HOLE. REMOVED DAMAGED ACCESS PANEL FOR REPAIRS, INSTALLED SERVICEABLE PANEL IAW SRM.

Part: PROXIMITY SWITCH — FAILED (MLG) · airframe 86,004 hrs · 18,867 cycles

LEFT "WING GEAR" ELECTRICAL HARNESS INSPECTION. REPLACED LEFT WING O/B (PRIM) PROX SWITCH (TILT) AND REPLACED LEFT WING GEAR INBD (ALT) TILT SWITCH. SECURED INBD PROX SWITCH MOUNT. CLEARANCE OK ON GEAR SWING.

Part: DOOR — DAMAGED (LT WING) · airframe 86,004 hrs · 18,867 cycles

LT WING GEAR LWR O/B STRUT DOOR DAMAGED. REMOVED AND ROUTED TO SHOP, OK TO INSTALL. INSTALLED DOOR PER MM.

Part: RELIEF VALVE — ILLUMINATED (NR 4 ENGINE) · airframe 85,924 hrs · 18,850 cycles

AT APPROX 6,000 FT NR 4 ENG LOOP FAULT LT ILLUMINATED NACELLE TEMPS A&B OBSERVED RAPIDLY CLIMBING TO 9. REMOVED AND REPLACED HIGH PRESS VLV, HIGH PRESS BLEED VLV HARNESS. REMOVED AND REPLACED PRESSURE RELIEF VLV. ENG OPS CHECKED GOOD, NO DEFECTS NOTED PER MM 36-11-05 & MM 36-11-03.

Part: CONNECTOR — LOOSE (NR 1 BLEED VALVE) · airframe 85,909 hrs · 18,847 cycles

NR 1 ENG WILL NOT START. MANUAL START UNSUCCESSFUL. FOUND CONNECTOR LOOSE ON NR 1 ENG BLEED AIR VALVE. RECONNECTED PLUG, OPS CHECK OK PER MM 36-11-00.

Part: START VALVE — MALFUNCTIONED (NR 4 ENGINE) · airframe 85,652 hrs · 18,795 cycles

NR 4 ENG STARTER VALVE WOULD NOT CLOSE 50 PERCENT. REPLACED START VALVE, OPS CHECK OK PER MM 80-11-04.

Part: PANEL — CRACKED (LT WING) · airframe 85,652 hrs · 18,795 cycles

LT WING UPPER LE PANEL CRACKED ON UPPER SURFACE (APPROX 30 INCHES,) LWR OB SURFACE HAS A 25 INCHES CRACK AND IS DISBONDED. PANEL REPLACED DURING FA-06 CHECK - NON-ROUTINE WORKCARD (T-160) NR 0034 REF.

Part: CHECK VALVE — FAILED (8TH STAGE) · airframe 85,100 hrs · 18,689 cycles

NR 1 ENG AT TOP OF DESCENT, FL 380, ENG. STALLED. ENG. RECOVERED AT FL 330 AND STALLED AGAIN. ENGINE SHUT DOWN. REMOVED AND REPLACED 8TH STAGE CHECK VALVE RUN UPPER LEAK CHECK, OK IAW MM 36-11-02 AND 71-00-43.

Part: VALVE — MALFUNCTIONED (NR 4 FUEL TANK) · airframe 64,880 hrs · 18,120 cycles

NR 4 MAIN FUEL TANK - REFILL VALVE WILL NOT SHUT OFF. REMOVED AND REPLACED NR 4 MAIN FUEL TANK REFILL VALVE IAW AMM 28-21-13.

Part: ACTUATOR — FAILED (NLG STEERING) · airframe 83,865 hrs · 18,427 cycles

RT INBND BODY GEAR STEERING ACTUATOR FAILED, CAUSING LOSS OF NR 1 HYDRO SYS. REMOVED AND REPLACED RT INBND BODY GEAR STEERING ACTUATOR. LEAK CK AND GROUND OPS NORMAL IAW MM 32-51-05, SERVIVED NR 1 HYD SYS IAW 72-00.

Part: FUEL SYS — MALFUNCTIONED (SURGE TANK) · airframe 83,655 hrs · 18,381 cycles

REPORTED FUEL LEAK BY TOWER ON CLIMBOUT WITH SMELL OF FUEL IN UPPER CRG DECK. FOUND LT SURGE TANK WITH FUEL SUMPED SURGED TANK. FOUND VOLUMETRIC SYS INOP. OPENED DMI 28-20-1. MALFUNCTION OF VOLUMETRIC SYS.

Part: ACTUATOR — BROKEN (NLG STEERING) · airframe 83,597 hrs · 18,367 cycles

LEFT BODY GEAR LIGHT "UNLOCKED" WOULD NOT COME ON IN PRIMARY OR ALTERNATE ON TAXI BACK LIGHTS CAME ON. ITEM TRANSFERRED TO DMI NR 30932 IAW DDPG 32-17-C BODY GEAR STEERING ACTUATORS VERIFIED LOCKED. REQUIRES FURTHER TROUBLE SHOOTING

Part: SWITCH — MALFUNCTIONED (NLG STEERING) · airframe 83,597 hrs · 18,367 cycles

ON TOW OUT RT LANDING GEAR TURNED SIDEWAYS. OPS CHECKED BODY GEAR STEERING SYSTEM IAW MM 32-53-00. OPS CK OK A/C BACK TO CONFIGURATION. SUSPECT RT BODY GEAR UNLOCK SWITCHES MALFFUNCTIONED.

Part: CONTROL UNIT — INOPERATIVE (ANTI SKID SYS) · airframe 82,793 hrs · 18,191 cycles

ON PUSHBACK RT WING FRONT ANTI-SKID LIGHT ILLUMINATED. DE-ACTIVATED NR 14 BRAKE & DEFERRED ITEM. ONE DEFECTIVE CHANNEL WITHIN CONTROL UNIT.

Part: IGNITER — DEFECTIVE (NR 4 ENGINE) · airframe 82,766 hrs · 18,184 cycles

RETURN TO BLOCKS DUE TO NR 4 ENG FAILED TO START. REPLACED BOTH IGNITER PLUGS TESTED OK. DEFECTED IGNITER PLUG NR 2 POS NR 1 SYS PREV DEFERRED.

Part: INDICATOR — MALFUNCTIONED (COCKPIT) · airframe 81,956 hrs · 18,025 cycles

ON LANDING & AFTER T/R'S STOWED, NR 3 ENGINE FUEL FLOW SPIKED. PRECAUTIONARY ENGINE SHUTDOWN PERFORMED IMMEDIATELY. F/F INDICATION REMAINED AT 12000 PLUS. PERFORMED BITE CHECK OF F/F SYSTEM. OPERATED NR 3 ENGINE, ALL PARAMETERS NORMAL PER MM 71-00-00 & MM 78-31-00.

Part: COUPLING — LOOSE (SCAVENGE LINE) · airframe 81,623 hrs · 17,957 cycles

DURING CRUISE AT FL 310, #4 ENG OIL QTY WENT FROM 3.5 TO ZERO IN APPROX. 15 MIN. OIL PRESS STARTED FLUCTUATING; OIL TEMP IN GREEN BAND (PERFORMED PRECAUTIONARY SHUTDOWN) WINDMILL RPNM 26%, N2 23%, OIL TEMP BELOW GREEN, OIL PRESS 10 PSI. EMERGENCY DECLARED & FLT DIVERTED TO ANC. AT ANC INSPECTED #4 ENG INLET & EXHAUST. NO FAULTS FOUND. INSPECTED ENG CORE - FOUND LOOSE COUPLING ON AFT ENG BEARING SCAVENGE LINE. INSPECTED LINE & COUPLING - NO ABNORMALITIES. RESECURED COUPLING. PERFORMED LEAK CHK & ENG RUN. NO LEAKS EVIDENT.

Part: KEELBEAM — CORRODED (FUSELAGE)

DURING CURRENT C CHECK AT KLM FOUND KEEL BEAM BOX WEB UPPER SURFACE ON BOTH LEFT/RIGHT SIDES OF BL 0 CORRODED. CUT AND REMOVED WEB FROM BS 1265 TO 1273. PERFORMED OPEN HOLE HFEC INSPECTION OF REMOVED FASTENER HOLES IN REPAIR AREA. NO ADDITIONAL CRACKS/CORROSION FOUND. FABRICATED REPLACEMENT WEB AND TWO SPLICE DOUBLERS. INSTALLED PARTS IAW SRM STANDARD PRACTICES.

Part: SPAR — CORRODED (WING)

DURING CURRENT C CHECK, FOUND CENTER WING LOWER REAR SPAR WEB CORRODED AT LBBL66 TO 75. BLENDED CORROSION. PERFORMED HFEC OPEN HOLE INSPECTION AND SURFACE INSPECTION OF BLENDED AREAS. NO DEFECTS FOUND. MEASURED CORROSION DEPTH, MEASUREMENTS EXCEEDED SRM LIMITS. FABRICATED REPAIR DOUBLER AND FILLERS. INSTALLED DOUBLERS AND FILLERS .

Part: WEB — CRACKED (FUSELAGE)

DURING CURRENT C CHECK AT KLM FOUND SHEAR WEB FLANGE AT BS 340 TO 360 STR 26L WITH CRACKS ALONG THE SKIN FASTENER ROW. CUT AND REMOVED THE CRACKED FLANGE AT THE WEB RADIUS. HFEC INSPECTION PERFORMED ON EXTERNAL SKIN AND WEB CUT LINE. NO ADDITIONAL CRACKS FOUND. FABRICATED REPAIR ANGLE AND INSTALLED IAW SRM, SB.

Part: SKIN — CRACKED (NR 4 PYLON)

DURING CURRENT C CHECK, FOUND NR4 PYLON RIGHT HAND FORWARD ACCESS PLATE CUTOUT, BETWEEN NAC 211 AND 220, CRACKED. CRACKS INITIATED FROM THE CLIP NUT HOLES OF THE INNER LIP DOUBLER (4 PLACES). TRIMMED AWAY INNER DOUBLER AROUND THE ENTIRE CUTOUT. FABRICATED DOUBLER AND TRIPLER. INSTALLED DOUBLER AND TRIPLER IAW SRM.

Part: WEB — CRACKED (FUSELAGE)

DURING CURRENT C CHECK, FOUND SHEAR WEB FLANGE AT BS 340 TO 360 STR 26R WITH CRACKS ALONG THE SKIN FASTENER ROW. CUT AND REMOVED THE CRACKED FLANGE AT THE WEB RADIUS. HFEC INSPECTION PERFORMED ON EXTERNAL SKIN AND WEB CUT LINE. NO ADDITIONAL CRACKS FOUND. FABRICATED REPAIR ANGLE, RADIUS FILLER STRIP AND TAPERED SHIM. INSTALLED PARTS AND FASTENERS WET WITH BMS 5-95 SEALANT IAW SRM, SB.

Part: HARNESS — MISSING (NR 1 ENGINE)

DURING ROUTINE ENGINE INSPECTION FOUND NR 1 ENGINE LOWER EGT HARNESS MISSING. REPLACED NR 1 ENGINE EGT HARNESS AS PER MM 77-20-03. (M)

Part: FIRE LOOP — INOPERATIVE (NR 2 ENGINE) · airframe 86,515 hrs · 18,974 cycles

NR 2 ENGINE A-LOOP INOP IN FIRE TEST MODE. TRANSFERRED TO DMI 32697 AND PLACARD PER MEL 26-1.

Part: SKIN — CRACKED (FUSELAGE)

DURING HFEC INSPECTION PER SB 747-53A2488 FOUND LOWER LOBE CARGO COMPARTMENT AFT DOOR UPPER CUT OUT, FORWARD CORNER CRACKED UNDER 2 INCH. SHIMS OVER .055 THICK. TRIMMED OUT CRACK. FABRICATED FILLER AND REPAIR DOUBLER. INSTALLED IAW SRM 53-30-03 TYPE II. (M)

Part: SKIN — CRACKED (FUSELAGE)

DURING HFEC INSPECTION PER SB 747-53A2488 FOUND LOWER LOBE CARGO COMPARTMENT AFT DOOR UPPER CUT OUT, FORWARD CORNER CRACKED UNDER 2 INCHES. SHIMS OVER .055 THICK. TRIMMED OUT CRACK. FABRICATED FILLER AND REPAIR DOUBLER. INSTALLED IAW SRM 53-30-03 TYPE II DETAIL II. (M)

Part: SKIN PANEL — CRACKED (FUSELAGE)

DURING ACCOMPLISHMENT OF ATLAS EO 4753A099, INSPECTION REVEALED A 1 INCH SKIN CRACK AT BS 980, STRINGER 38L. FURTHER DISASSEMBLY REVEALED TWO ADDITIONAL CRACKS UNDER THE LOWER DRAG FITTING FORWARD HOLE, ONE WAS 1 INCH LONG AND THE OTHER WAS 3 INCH. THE 1 INCH LONG CRACKS RAN CIRCUMFERENTIALLY TO THE FUSELAGE, THE OTHER 3 INCH CRACK RAN AXIAL. REPLACED 2 STRINGER TIE FITTINGS DUE SMALL HOLE CRACKS. REPLACED 2 DRAG FITTINGS DUE CORROSION. CUT OUT CRACKED SKIN AND REPLACED PER SRM PRACTICES IAW BOEING TELEX. (M)

Part: BOLT — CRACKED (WS 1241)

LEFT WING REAR SPAR STATION 1241, LOWER SPLICE PLATE AND KICK FITTING INBOARD BOLT AND BOLT HOLE HAS CRACK INDICATIONS, VERIFIED WITH HFEC INSPECTION. OVERSIZED KICK FITTING AND REAR SPAR LOWER CHORD BOLT HOLE TO .975 INCH. VERIFIED HOLE IS CRACK FREE WITH HIGH FREQ EDDY CURRENT INSPECTION. REPLACED BOLT. (M)

Part: SKIN — CRACKED (WS 1241)

LEFT WING STATION 1241 SPLICE STRAP AND SKIN FOUND CRACKED IN FORWARD HOLE, VERIFIED WITH HFEC INSPECTION. FAIL/SAFE STRAP WAS REMOVED AND REPLACED AND CRACKED SKIN WAS TRIMMED OUT AND REPAIRED. THIS IS AN APPROVED ALTERNATE METHOD OF COMLIANCE REF 8110-3. (M)

Part: SPAR WEB — CORROSION (WS 1241)

WING CENTER SECTION, BS 1241 REAR SPAR WEB CORROSION. CORROSION REMOVED FROM WEB AND REWORKED, THIS IS AN APPROVED ALTERNATE METHOD OF COMPLIANCE REF 8110-3. (M)

Part: SPAR WEB — CRACKED (RT WING)

RIGHT WING MID SPAR UPPER CHORD FOUND WEB CRACKS. INDICATIONS VERIFIED USING HFEC INSPECTION, BETWEEN MSS 563.24 AND 592.45. AT MSS 575 THE WEB AT THE TWO CRACKED FASTENER HOLES WERE TRIMMED OUT AND A PERMANENT REPAIR WAS ACCOMPLISHED USING FILLERS, A DOUBLER AND A STIFFENER REF 8110-3. (M)

Part: COVER PLATE — SEAL LEAK (NR 2 GEARBOX)

LUX - AIRCRAFT DEPARTED, DURING CLIMB THE NR 2 ENGINE'S OIL QUANTITY DROPPED AND WAS SHUT DOWN. AIRCRAFT RETURNED TO LUX AND LANDED SAFELY. OIL SERVICED AND ENGINE MOTORED - NO LEAK, IDLE CHECK - NO LEAK, POWER LEVEL ADVANCED AND LEAK APPEARED AT THE GEARBOX MANUAL CRANK PAD. FOUND WASHER INSTALLED BEHIND CRANK PAD. WASHER REMOVED AND SEAL REPLACED, ENGINE RUN AND LEAK CHECK ACCOMPLISHED. AIRCRAFT RETURNED TO SERVICE. NOTE: THE GEARBOX MANUAL CRANK PAD WAS REMOVED FOR MAINTENANCE, SEAL REPLACED, NO LEAKS NOTED BY MOTORING. BOEING MM 72-00, PAGES 201-203, NO LEAK CHECK INDICATED, ESPECIALLY ADVANCED.