N559FE

Part: CONTROL CABLE — BROKEN (L1 DOOR) · airframe 102,462 hrs · 34,301 cycles

L1 DOOR LOWER CABLE BROKEN. INSTALLED THE L1 DOOR LOWER AFT DOOR CONTROL CABLE. CABLE RIG AND OPS CHECKED GOOD IAW AMM 52-10-02-2.

Part: SPAR CAP — CRACKED (LT WING) · airframe 102,199 hrs · 34,185 cycles

L/W WING REAR SPAR AFT LOWER CAP HAS .400 IN. CRACK PROPAGATING AFT FROM FASTENER HOLE AT XORS 412. REPAIRED L/H REAR SPAR CAP REF EA 8-5710-T0336600 PARTS 1 - 4. REPAIR CLASSIFIED AS MAJOR.

Part: SKIN — CRACKED (RT ELEVATOR) · airframe 102,199 hrs · 34,185 cycles

RT HORIZ STAB DROOP ELEVATOR HAS A 1.5 CRACKED ON UPPER SKIN. CUT OUT DAMAGED AND INSTALLED REPAIR PER SRM 55-00-01 FIG 3 SHT 2 VOL 1.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 3 · airframe 102,199 hrs · 34,185 cycles

FWD CARGO COMP LT FLOORBEAM AT STA LBL 56 IS CORRODED. REPAIRED FLOOR BEAM IAW SRM 53-00-01 FIG 8 V1.

Part: SKIN — CORRODED (RT HORIZ STAB) · airframe 102,199 hrs · 34,185 cycles

RT HORIZONTAL STABILIZER CENTER LOWER FARING (AJC7412-2) HAS NUMEROUS AREAS OF CORROSION AT LOWER SECTION UNDER ATTACH AREA AND SEALANT (MARKED) REPAIRED AREA PER SRM 51-21-01 VOL II.

Part: SKIN — CORRODED (LT HORIZ STAB) · airframe 102,199 hrs · 34,185 cycles

LT HORIZONTAL STABILIZER LOWER FAIRING CORROSION ON SKIN AT LOWER AFT STABILIZER FAIRING (AJC7470-1) LOWER ATTACH AREA UNDER SEALANT TREATED AREA PER SRM 51-21-01 VOL II.

Part: ATTACH ANGLE — CORRODED (BS 1970) · corrosion level 2 · airframe 102,199 hrs · 34,185 cycles

AFT FUSELAGE WASTE TANK, BS 1970 UPPER PANEL ATTACH ANGLE CORRODED AT NUMEROUS FASTENERS AREA. REMOVED THE CORROSION IAW SRM 51-21-01, VOL 2. WITHIN LIMITS.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 102,199 hrs · 34,185 cycles

AFT CARGO COMPT, STA 1902, FLOOR SUPPORT CORROSION FROM APPROX LONGERON 45L TO 48R. CRACKED AND FLAKING METAL AROUND NUMEROUS NUTPLATES AT APPROX LONGERON 46R. (NOTE:PRIMARY STRUCTURE) REPAIR PER SRM 53-00-01 FIG 8 SHT 1 VOL 1

Part: STANCHION — CORRODED (BS 1970) · corrosion level 2 · airframe 102,199 hrs · 34,185 cycles

AFT FUSELAGE WASTE TANK BS 1970, CTR STANCHION AT THE BULKHEAD IS CORRODED. REMOVED AND REPLACE STANCHION SRM 51-31-01.

Part: STANCHION — CORRODED (FUSELAGE) · airframe 102,199 hrs · 34,185 cycles

AFT FUSELAGE WASTE TANK STA 1970 CTR STANCHION AT BULKHEAD IS CORRODED. REPAIRED PER 51-21-01 VOL II.

Part: FLAP — DENTED (TE FLAP) · airframe 102,199 hrs · 34,185 cycles

RT I/B FLAP TOP SURFACE HAS A DENTED CREASE. REPAIRED PER SRM 57-10-00 FIG 85 VOL 1.

Part: SKIN — CRACKED (RT WING) · airframe 102,199 hrs · 34,185 cycles

RIGHT LOWER WING SKIN AT THE FUEL ACCESS DOOR FWD INBOARD CORNER HAS A .400 INCH CRACK. REPAIRED THE SKIN IAW SRM 57-10-00, FIG 106, SHT 2.

Part: FRAME — CRACKED (BS 1721) · airframe 102,199 hrs · 34,185 cycles

BS 1721, LONGERON 13R, FUSELAGE FRAME CRACKED. REPLACED THE FRAME SECTION IAW SRM 53-30-00, VL 1, PAGES 15-16, FIG 5, SHEETS 1-2, AND DWG AFA0019.

Part: DOUBLER — DENTED (VERTICAL STAB) · airframe 102,199 hrs · 34,185 cycles

VERTICAL STAB LT SIDE DENTED JUST AFT OF ACCESS PANEL NR 373GL. REPAIRED VERTICAL STAB LT SIDE REF SRM 55-00-01 FIG 3 SHT 2 VOL I.

Part: DOUBLER — DENTED (RUDDER) · airframe 102,199 hrs · 34,185 cycles

UPPER AT RUDDER, LT CENTER AREA GOUGED APX 1 INCH. REPAIRED UPPER AFT RUDDER LT SIDE REF SRM 55-00-01 FIG 3 SHT 3 VOL I.

Part: HINGE — CORRODED (CARGO DOOR) · airframe 102,199 hrs · 34,185 cycles

FOUND THE CARGO DOOR HINGE AND BACK UP STRUCTURE CORRODED. REPAIRED IAW SRM 51-21-01, VOL II.

Part: DOUBLER — CRACKED (LT WING) · airframe 102,199 hrs · 34,185 cycles

L/H WING L/E LOWER SURFACE, CRACK NOTED AT FWD I/B CORNER OF FUEL ACCESS DOOR. MARKED DOT #1. CUT OUT CRACKED SKIN AND INSTALLED WING LEADING EDGE SKIN REPAIR REF. SRM 57-10-00 FIG.106 (SHEET 2) PAGE 509 VOL I.

Part: HINGE — CORRODED (CARGO DOOR) · airframe 102,199 hrs · 34,185 cycles

AFT CARGO DOOR HINGE CORRODE. REPAIRED IAW SRM 51-21-01, VOL II.

Part: SKIN — CORRODED (CARGO DOOR) · airframe 102,199 hrs · 34,185 cycles

AFT CARGO DOOR CORRODED ON THE EXTERIOR SURFACE, BELOW THE DOOR HINGE. REPAIRED IAW SRM 51-21-01, VOL II.

Part: CHANNEL — CORRODED (BS 1521) · airframe 102,199 hrs · 34,185 cycles

CENTER CARGO LT CHANNEL AT SIDEWALL BASE IS CORRODED AT BS 1521, LBL 72. REMOVED AND REPLACED THE CHANNEL IAW SRM 53-31-01 VOL II

Part: LINK — FAILED (NLG) · airframe 101,648 hrs · 33,809 cycles

DURING APPROACH, NLG INDICATION WENT FROM GREEN TO RED ON PRIMARY AND SECONDARY DISPLAY. FROM THAT POINT NLG DOWN INDICATION WAS INTERMITTENT. REMOVED AND REPLACED THE LOWER LOCK LINK ASSY IAW MM 32-00-01-4. REPLACED TARGET ASSY IAW MM 32-61-17-4. PERFORMED GEAR SWING 7 TIMES, OPS CHECKED NORMAL ALL INDICATIONS WERE NORMAL IAW MM 32-30-00-5-1.

Part: TARGET — DETACHED (MLG) · airframe 101,648 hrs · 33,809 cycles

AFTER INITIAL LANDING GEAR RETRACTION, NLG DID NOT RETRACT, RED LIGHT IN PRIMARY AND SECONDARY DISPLAY. CYCLED GEAR DOWN THEN UP AGAIN. LANDING GEAR RETRACTED NORMALLY IAW QRH, AS INDICATED ON PRIMARY & SECONDARY DISPLAY. HYDRAULIC PRESSURES NORMAL THROUGHOUT THIS PROCEDURE. REPLACED THE LOWER LOCK LINK ASSY AND THE TARGET ASSY. APPEARS TO BE AN INDICATION ISSUE AS THE TARGET WAS ABOUT TO FALL OFF AND WAS MOVING ALL OVER THE PLACE. THE GEAR OPS CHECKED NORMAL. OK FOR SERVICE IAW MM 32-22-01-4, 32-61-17-4, AND 32-30-00-5-1. ACFT OK FOR SERVICE.

Part: ACTUATOR — FAILED (NLG) · airframe 100,373 hrs · 33,119 cycles

NOSE GEAR DID NOT RETRACT ON INTIAL TAKE OFF. RAN QRH HAD RED UNSAFE NOSE GEAR INDICATION. ANOTHER AIRPLANE SAID NOSE GEAR WAS EXTENDED. WHEN GEAR HANDLE WAS PUT DOWN, NOSE GEAR IMMEDIATELY TURNED GREEN. FOUND NOSE GEAR UNLOCK CYLINDER BYPASSING. R & R NLG UNLOCK CYLINDER IAW MM 32-35-02-2. JACKED NOSE GEAR, SWUNG GEAR SEVERAL TIMES WITH NO DEFECTS IAW MM 32-20-00-5. LEAK AND OPS CK GOOD.

Part: BRACKET — LOOSE (MLG) · airframe 99,832 hrs · 32,846 cycles

AFTER TAKEOFF, MLG HANDLE WOULD NOT MOVE TO UP POSITION. RAN QRH & RAISED MLG HANDLE USING MLG HANDLE RELEASE BUTTON. NLG INDICATED UP, LT & RT MLG INDICATED, UNSAFE, RED ON MLG PANELS & CONFIG PAGE. RETURNED MLG DOWN, 3 GOOD INDICATIONS, CONTINUED TO DESTINATION. FOUND NLG GROUND SENSE BRACKET ON UPPER TORQUE LINK WORN & VERY LOOSE. R & R THE BRACKET. CONTROL MECHANISM RIGGED IAW MM 32-31-02-2, RIGGED NLG GND SENSING IAW WC 32T2701. OPS CHECKED GOOD. ADJUSTMENT TEST OF NLG & DOORS IAW MM 32-20-00-5, OPS CHECKED GOOD. PERFORMED MLG SWINGS IAW MM 32-30-00-5. OPS CHECKED GOOD. OK FOR SERVICE.

Part: STRUCTURE — TWISTED (FUSELAGE) · airframe 99,827 hrs · 32,841 cycles

DURING EMER STOP SITUATION WITH SIDE LOADS ON ACFT NOSE ENOUGH TWIST WAS APPLIED TO ACFT TO CAUSE THE RT ACFT ENTRY DOOR TO INDICATE OPEN, EVEN THOUGH IT WAS CLOSED & ARMED. PERFORMED GVI OF RT MAIN ENTRY DOOR INSPECTION & CHECK IAW AMM 52-10-01-6. PERFORMED OPERATIONS CHECK OF RT MAIN ENTRY DOOR IAW AMM 52-10-00-0. OPERATIONS CHECKED NORMAL.

Part: UNKNOWN — MALFUNCTIONED (LANDING GEAR) · airframe 99,753 hrs · 32,803 cycles

UNABLE TO RAISE LG AFTER TAKEOFF. SEVERAL TRIES UNSUCCESSFUL. RAN QRH USING HANDLE REL BUTTON, WAS ABLE TO RAISE GEAR HANDLE. ALL ACFT SYSTEMS SHIFTED TO FLIGHT MODE. CHECKED CABLE RUN FROM COCKPIT TO CRANK ASSEMBLY UNDER PILOT AT PRESS BULKHEAD. CABLE APPEARS INTACT. CHECKED CABLES FROM TORQUE LINK QUAD UP TO CRANK & ALL APPEARS FREE & NO BINDING NOTED AS REQ' IAW MM 32-31-02. MOVING THE CRANK BY HAND WOULD ALLOW THE HANDLE TO MOVE UP, BUT THE REQ'D MOVEMENT SEEMED EXCESSIVE AT ABOUT 1 INCH. OPERATIONS CHECKED GOOD IAW WRI 32-30-0626.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 99,521 hrs · 32,665 cycles

CAC STATION 1119, FRAME BETWEEN LONGERON 47 & 48, SHEAR CLIP IS EXFOLIATED. R & R SHEAR CLIP IAW DWG AAA7046.

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 99,521 hrs · 32,665 cycles

MAIN DECK SEAT TRACK DAMAGED AT STATION 1381, LBL 45.5. R & R SECTION OF SEAT TRACK IAW SRM 53-70-00 FIG 1.

Part: SKIN — CORRODED (FUSELAGE) · airframe 99,521 hrs · 32,665 cycles

EXTERIOR FUSELAGE, STATION 1119, BELOW LONGERON 47, SKIN HAS EXFOLIATION CORROSION, APPROX 2" IN DIAMETER, COMPLIED WITH EA 8-5310-T0322104.

Part: FRAME — CRACKED (FUSELAGE) · airframe 99,521 hrs · 32,665 cycles

LOWER BILGE STATION 595 RT, AT LONGERON 39, ACA6044-65 T CAP FRAME CRACKED .300" LONG. REPAIRED CRACKED T CAP CUTTING OUT CRACK & REINFORCING T CAP WITH STRAPS IAW EA 8-5310-T0321525. REPAIR HAS BEEN CLASSIFIED AS A MAJOR REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 99,521 hrs · 32,665 cycles

CAC RT STATION 1156, UPPER CORNER FRAME INNER VIEW ONE SHEARED 1/4" FASTENER & CRACK RUNNING THROUGH ANOTHER 1/4" FASTENER. CRACK RUNS ENTIRE LENGTH OF FRAME & IT APPEARS FRAME HAS BEEN SHIFTING. FRAME REPAIR HAS NOT BEEN ACCOMPLISHED IAW SRM 53-30-00, NO CUT OUTS & FILLERS AT CRACK LOCATIONS. REPAIRED FUSELAGE FRAME IAW EA 8-5310-T0321548.

Part: FRAME — CRACKED (FUSELAGE) · airframe 99,521 hrs · 32,665 cycles

INSIDE CAC COMPARTMENT, RT SIDE AT STATION 1156, PREVIOUS REPAIR FUSELAGE FRAME AEAO159 HAS AN ADDITIONAL CRACK AT THE TOP ROW FASTENERS. CRACK ALSO EXTENDS INTO THE RADIUS & OTBD OF T LEG OF FITTING, APPROX 1 INCH. REPAIRED FUSELAGE FRAME IAW EA 8-5310-T0321548.

Part: WEB — CRACKED (RT WING) · airframe 995 hrs · 32,665 cycles

RIGHT WING, INTERNAL WEB CRACKED AT STATION XORS 402 & APPROX STRINGER 39. REMOVED DOUBLER FROM RT WING INTERNAL WEB AT STATION XORS 402 & APPROX STRINGER 39 & REPAIRED IAW EA 8-5700-T0321488.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 995 hrs · 32,665 cycles

LEFT STATION 595, PRESS BULKHEAD WEB HAS A 1.4 INCH CRACK FROM THE EDGE OF THE WEB EXTENDING THROUGH ONE FASTENER AT STATION X=78 & Z=87. COMPLIED WITH EA 8-5310-T0321453.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 995 hrs · 32,665 cycles

LEFT STATION 595, PRESS BULKHEAD T CAP AT LONGERON 39L, HAS A CRACK THROUGH THE VERTICAL & HORIZONTAL LEGS. CUT & REMOVED SECTION OF THE 595 T CAP FROM LONGERON 35L - 44L. COMPLIED WITH EA 8-5310-T0321379.

Part: SKIN — CORRODED (FUSELAGE) · airframe 995 hrs · 32,665 cycles

CENTER ACCESSORY COMPARTMENT, CORROSION & EXFOLIATION ON & UNDER FINGER DOUBLER, BETWEEN LONGERONS 47L & 48L. COMPLIED WITH EA 8-5330-T0321798 PART 1.

Part: SKIN — DAMAGED (NR 2 COWLING) · airframe 995 hrs · 32,665 cycles

NUMBER 2 FAN COWL LAND, LT SIDE, SKIN HAS MINOR DAMAGE. R & R SKIN IAW DWG AJC7415.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 99,520 hrs · 32,665 cycles

MAIN DECK, SEAT TRACK DAMAGED, STATION 1386, LBL 45.50. R & R SECTION OF SEAT TRACK AS REQUIRED.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 99,520 hrs · 32,665 cycles

MAIN CABIN, STATION 765, LBL 47 SEAT TRACK DAMAGED & NEEDS TO BE REPLACED. REPLACED SECTION OF SEAT TRACK IAW SRM 53-70-0-0 FIG 1 SHT 3.

Part: STRIP — DAMAGED (CARGO BAY) · airframe 993 hrs · 32,586 cycles

RAMP OFF LOAD CREW REPORTED, DAMAGE TO THE LOWER FWD CARGO COMPARTMENT CEILING STRUCTURE, AT THE AFT INBD SIDE OF THE DOOR MOTOR. R & R METAL TRIM STRIP ATTACHMENT TO LINER IAW SRM 51-31-01 VOLUME II.

Part: SKIN — CRACKED (LT WING) · airframe 993 hrs · 32,545 cycles

EVIDENCE OF A SKIN CRACK ON LT WING INBD FWD RADIUS OF SLAT DRIVE MECHANISM DOOR CUT OUT CONFIRMED BY NDT HFEC. VERIFIED CRACK TO BE 3/4 - 1". COMPLIED WITH NTM REF 20-30-00-PT6 WILL BE REQUIRED TO RE-CHECK AFTER S/M REMOVES METAL PRIOR TO INSTALLING FILLER. REMOVED SLAT DRIVE ACCESS DOOR, ADJACENT UNDERWING PANEL & INTERIOR COVER AT SLAT DRIVE DOOR FWD INBD CORNER IAW SRM 51-31-01. REMOVED CRACK DAMAGED AT NOTED LOCATION IAW REPAIR DWG SG11570012. VERIFIED DAMAGE REMOVAL AT NOTED LOCATION IAW NTSPM 06-10-01.010. FABRICATED REPAIR DOUBLER .063 6AL-4V MPO MP2933043 & FILLER .090 2024-T3 MPO MP2747228. DOUBLER & FILLER HAS BEEN PRIMED & READY FOR INSTALL IAW DWG SG11570012. INSTALLED REPAIR IAW REPAIR DWG SG11570012.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 992 hrs · 32,480 cycles

EMERGENCY LIGHT PREFLIGHT TEST LEVEL 1 ALERT, EMERGENCY LIGHT BATTERY LOW. RELEASED FOR SERVICE IAW MEL 33-50-02, CATEGORY C EXPIRATION 13 AUG 15. EMERGENCY LIGHTS INOPERATIVE. ITEM PLACED ON MEL.

Part: WARNING MESSAGE — FALSE ACTIVATION (ZONE 200) · airframe 991 hrs · 32,457 cycles

ON EMER LIGHTS TEST MSG DISPLAYED, EMER BAT 1 LOW. PERFORMED OPERATIONAL CHECK OF EMER LIGHT & POWER SYS. OPERATIONS CHECKED GOOD.

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 985 hrs · 32,131 cycles

DURING EMER LIGHTS TEST, EMER LT BATT 1 LOW, MSG DISPLAYED. REPLACED EMER LIGHTING BATTERY POWER SUPPLY IAW MM 33-51-01-4. OPERATIONS CHECKED GOOD.

Part: WARNING LIGHT — FALSE ACTIVATION (EMERGENCY LIGHTS) · airframe 985 hrs · 32,124 cycles

EMERGENCY LIGHTS WOULD NOT TEST. RECEIVED AN EMERGENCY LIGHT NR 1 BATTERY LOW INDICATION. PERFORMED SEVERAL EMERGENCY LIGHTING BATTERY POWER SUPPLY TESTS. NOFAULTS NOTED. OKAY FOR SERVICE.

Part: UNKNOWN — ODOR (CABIN) · airframe 98,365 hrs · 32,014 cycles

COCKPIT SMELLED LIKE SOMEONE HAD BEEN SMOKING IN THE ACFT FROM PREFLIGHT THROUGH POST FLIGHT. RAN NR 1 ENGINE. OPERATED NR 1, 2 & 3 AIR CONDITIONING UNITS. NO ABNORMAL ODOR OF SMOKE WAS NOTED.

Part: COALESCER BAG — DIRTY · airframe 97,426 hrs · 31,499 cycles

PASSING FL 310, CARGO FIRE FLASHING, DISCHARGE SWITCH TURNED ON AFT SIDE. EMERGENCY RETURN TO DEPARTURE. APU OIL SUSPECTED OF CONTAMINATING NR 2 BLEED AIR DUCT. PERFORMED PACK & DISTRIBUTION ODOR CLEARING PROCEDURE IAW MM 21-53-00-7. RAN NR 2 ENG & USED NR 2 BLEED AIR TO SUPPLY NR 2 PACK. BLEED AIR DUCT REACHED 100 C WITH NO SMOKE OR ODOR DETECTED. REPLACED 1 & 3 COALECER BAGS IAW MM 21-54-03-2.

Part: WIRE HARNESS — BURNED (BOOST PUMP) · airframe 97,312 hrs · 31,438 cycles

NR 1 FUEL TANK, FWD PUMP FAILS FUEL SYS CONTROLLER, PUMP STAYS AMBER WHEN SELECTED ON. AFTER REMOVAL OF FUEL PUMP, PUMP SHOWED SIGNS OF OVERHEATING & PUMP IMPELLER WAS SEIZED. WIRE HARNESS GROMMET AT CONNECTOR FOUND STUCK IN PUMP CONNECTOR END. R & R NR 1 TANK FWD BOOST PUMP WIRE HARNESS IAW MM 28-22-01-2. AFTER REPLACED NR 1 TANK BOOSTER PUMP WIRE HARNESS, REINSTALLED STRING 3 - 368 TERMINAL & 502A GND WIRE TERMINAL IAW WDM 28-22-01. R & R NR 1 FWD BOOST PUMP IAW MM 28-22-01-2. PERFORMED OPERATIONS CHECK MAN 28-22-01-2.

Part: PRESSURE SWITCH — FAILED (PNEUMATIC SYS) · airframe 97,174 hrs · 31,376 cycles

AT FL 340, AIR MANIFOLD FAIL LEVEL 3. DIVERTED & LANDED WITHOUT INCIDENT. NR 1 MANIFOLD PRESSURE SENSOR INOPERATIVE. NR 1 PNEUMATIC SUPPLY SYS INOPERATIVE. INTERROGATED PNUE FAULT INDICATOR PANEL, FOUND LT WING MANIFOLD PRESSURE SWITCH FAILED. DECAY CHECK WAS GOOD. CONFIRMED FAULT BALL ON LEFT WING MANIFOLD PRESSURE SWITCH. REMOVED AND REPLACED NR 1 MANIFOLD FAIL DETECTOR PRESSURE SWITCH IAW AMM36-23-03-4. PERFORMED OPS CHECK, NO DEFECTS NOTED. RAN NR 1 ENGINE IAW JRH, OPS CHECKED GOOD.

Part: TEE FITTING — CRACKED (MLG WW) · airframe 95,551 hrs · 30,486 cycles

CENTER WHEEL WELL RT FWD SIDEWALL TO AFT WING SPAR ATTACH TEE ANGLE CRACKED BS 1381, 1.5 IN BELLOW UPPER SPAR CAP. CENTER WHEEL WELL RT FWD SIDEWALL TO AFT SPAR ATTACH TEE ANGLE CRACKED.

Part: BULKHEAD WEB — CRACKED (ZONE 700) · airframe 95,551 hrs · 30,486 cycles

NLG WW, TWO CRACKS ON RT SIDEWALL APPROX 22" FORWARD OF AFT BULKHEAD, 1ST CRACK 4 .8750" LONG END OF CRACKS MKD, 2ND CRACK APPOX 1.5" LONG FORWARD OF 1ST CRACK ENDS OF CRACK MARKED. REPAIRED CRACKS IN NLG WW RT SIDEWALL APPROX 22" FWD OF AFT BULKHEAD REF SRM 53-00-01.

Part: UNKNOWN — UNKNOWN (ELECTRICAL POWER) · airframe 94,894 hrs · 30,097 cycles

DURING EMERGENCY POWER TEST AND EXTERNAL POWER AND APU POWER SELECTED, UNABLE TO GET A GOOD TEST UNTIL DESELECTING EXTERNAL POWER. DURING TEST DISPLAY UNITS 1, 2, & 3, BLANK AS NORMAL BUT WHILE EXT POWER CONNECTED WOULD NOT REINSTATE. TESTED EMERGENCY POWER SYS IAW AMM 24-00-00-5. NO DEFECTS NOTED. OK TO CONTINUE.

Part: FITTING — GOUGED (RT WING TE FLAP) · airframe 94,808 hrs · 30,039 cycles

RT INBD FLAP STRUCTURE SUPPORT FITTING FOR INBD FLAP ROLLERS AND INBD TRANSMITTER GOUGED BY INBD FLAP TRACK. UPON DISASSEMBLY, FOUND FLAP SIDE LOAD FITTING DAMAGED AND WORN AROUND ATTACH BARREL NUT. DAMAGE TO FITTING MADE SIDE ROLLERS FAIL AND ALLOW FOR GOUGING WHEN THE FLAP WAS ACTUATED. COMPLIED WITH HFEC INSPECTION IAW NDTSPM CHAP C6. FOUND NO INDICATION OF CRACKING. R & R FLAP STRUCTURE SUPPORT FITTING IAW DWG ABN7393. R & R RT INBD FLAP TRANSMITTER ON NR928. BLENDED WEAR MARK IN THE FLAP STRUCTURE SUPPORT ASSY. PERFORMED HFEC OF THE BLENDED AREA IAW SPM 93K0393, NO CRACK INDICATION NOTED. REINSTALLED FLAP, PREVIOUSLY REMOVED AND RIGGED FLAP SYS IAW 27-50-00-5. OPS CHECKED GOOD.

Part: HINGE FITTING — CRACKED (LT WING TE FLAP) · airframe 94,808 hrs · 30,039 cycles

LEFT OTBD FLAP, INBD FWD HINGE FITTING, FWD SECTION (INBD HALF), SUSPECT CRACK EMANATING FROM FASTENER. INSTALLED NEW HINGE FITTING IAW DWG 6013.

Part: HINGE FITTING — CRACKED (ZONE 500) · airframe 94,808 hrs · 30,039 cycles

LT WING, OTBD FLAP, INBD FWD HINGE FITTING (OTBD HALF), SUSPECT CRACK. INSTALLED NEW HINGE FITTING IAW DWG NR 6013.

Part: HINGE FITTING — CRACKED (LT WING TE FLAP) · airframe 94,808 hrs · 30,039 cycles

LEFT OTBD FLAP, INBD FWD HINGE FITTING, FWD SECTION (INBD HALF), SUSPECT CRACK EMANATING FROM FASTENER. INSTALLED NEW HINGE FITTING IAW DWG NR 6013.

Part: BULKHEAD WEB — CRACKED (NLG WW) · airframe 94,808 hrs · 30,039 cycles

NOSE GEAR WHEEL WELL LEFT BULKHEAD WEB CRACKED. REMOVED DAMAGE, FABRICATED AND INSTALLED DOUBLER IAW SRM 53-00-01, VOL 1. HFEC AREA OF REMOVED MATERIAL IAW NDT SPMTP-MDC-93K0393.

Part: WIRE HARNESS — DEFECTIVE (ESCAPE SLIDE) · airframe 94,521 hrs · 29,888 cycles

DOOR SLIDE LIGHT WILL NOT TEST OR ILLUMINATE WHEN PRESSED. TRIED NEW BATTERIES AND BLUBS NO HELP. SLIDE LIGHT ASSY HARNESS DEFECTIVE. REPLACED SLIDE LIGHT HARNESS ASSY IAW WDM 25-61-01. CHECKED GOOD IAW AMM 25-61-02-5. R & R R1 SLIDE IAW MM 25-61-02-4 PRIOR TO HARNESS CHANGE, SLIDE PRESS TO TEST PRESSURE CHECKED SATISFACTORY. OK FOR SERVICE.

Part: COVER — MISSING (DISARM INDICATOR) · airframe 93,495 hrs · 29,343 cycles

DOOR DISARM LIGHT BULB COVER IS MISSING ON LT MAIN CABIN DOOR. INSTALLED NEW DISARM INDICATOR COVER, REF AMM 52-11-00. OK FOR SERVICE. FINAL CLOSED.

Part: BATTERY PACK — DISCHARGED (EMERGENCY LIGHTS) · airframe 93,237 hrs · 29,204 cycles

EMERGENCY LIGHT TEST BATTERY 1 LOW MESSAGE APPEARED. RELEASED FOR SERVICE IAW MEL: 33-50-01 CATEGORY: C EXPIRATION: 31OCT10 "MEL 33-50-01: EMERGENCY LIGHT TEST FUNCTION - INOP." PART(S) IDENTIFIED ARE THE MOST PROBABLE CAUSE. TROUBLESHOOTING IS REQUIRED PRIOR TO INSTALLING PART(S) ITEM PLACED ON MEL AT THIS TIME. C/W FIM 33-50-01 NO DEFECTS NOTED, C/W ADJ/TEST AMM 33-51-01/501 ALL TEST PASS MEL CLEARED, PLACARD REMOVED.

Part: FITTING — CRACKED (ZONE 200) · airframe 92,360 hrs · 28,763 cycles

FOUND CRACK INDICATION ON MAIN CARGO DOOR NR 3 SPOOL BOLT HOLE FITTING IN HOLE D. ORIGINATED SNRM SEQ N00734. R & R NR 7 FITTING IAW SRM 51-00-01 VOL 1.

Part: FITTING — CRACKED (ZONE 200) · airframe 92,360 hrs · 28,763 cycles

FOUND CRACK INDICATION ON MAIN CARGO DOOR NR 3 SPOOL BOLT FITTING IN HOLE D. R & R NR 3 FITTING IAW SRM 51-00-01 PG 2 VOLUME 1.

Part: ANGLE — CORRODED (RT MLG WW) · airframe 92,360 hrs · 28,763 cycles

RT WHEEL WELL, THERE IS A CORRODED ANGLE (APB7080-2) AT THE OTBD LOWER CORNER THAT SUPPORTS THE SLANT PANEL. DAMAGED AREA IS APPROX (6 IN) LONG AND HAS ATTACKED THE SPAR UPPER CAP OR SKIN. REMOVED DAMAGED SECTION OF ANGLE, REF SRM 53-40-00. ACCOMPLISHED DYE PENETRANT INSP IAW DACDPS4.707 & MDCSPM 93K0393, CH 8. NO DEFECTS NOTED. FABRICATED NEW SECTION OF ANGLE, REF SRM 53-40-00. INSTALLED NEW SECTION OF ANGLE, REF SRM 53-40-00, FIG 11.

Part: ATTACH FITTING — CRACKED (HORIZONTAL STAB) · airframe 92,360 hrs · 28,763 cycles

VISUAL CRACK INDICATION ON THE LT HORIZ STABILIZER L/E INTERIOR AREA AT THE FWD ATTACHED FITTING OF THE LOWER CHORD, VIEWED THRU ACCESS PANEL 331-AZ (INBD SIDE). R & R FITTING AT LT HORIZONTAL STABILIZER L/E REF. SRM 51-00-01 VOLUME 1.

Part: WATER SEPARATOR — DIRTY · airframe 86,044 hrs · 25,834 cycles

AIRCRAFT ON GROUND HAD ODOR OF DIRTY WATER SEPARATOR. IMMEDIATELY AFTER T/O ODOR GREW STRONG AND ACRID. SLIGHT BURNING OF EYES. DONNED O2 MASK AND LANDED DEW. NO VISIBLE SIGN OF SMOKE. REPLACED ALL 3 WATER SEPARATOR BAGS PER AM 21-54-03-2. OPS CAKES GOOD PER 21-00-01-5. OK FOR SERVICE.

Part: SKIN — DAMAGED (FUSELAGE) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND RT AFT FUSELAGE - LATERAL SKIN B/T LONG 36-48 STA 1754-1997 WITH SEVERAL EXISTING REPAIR: DENTS, NICK, CORROSION, AND MISSING MATERIAL AROUND JAMB CTR DOOR CARGO. REPLACE SKIN PER SRM 51-35-01 PAGE 1-12 SRM 51-35-02 PAGE 3- 9, SRM 51-33-01 PAGE 34-47. P/N AGA3102-504, AGA3071-505.

Part: SKIN — CRACKED (FUSELAGE) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF DURING REMOVAL INLET DUCT IS NOTED EXFOLATION ON EXTERNAL SKIN STA 2160 RT SIDE B/T LONG 10-12 AND CRACK ON DOUBLER AJC7057-5. REPLACE INTERNAL DOUBLER P/N AJC7057-5 PER SRM 53-00-01 FIG 4 SHEET 2.

Part: RIB — DAMAGED (L/E SLAT) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND AT LT SLAT NR 5 OUTBOARD SIDE, RIB WITH HOLES IN RADIUS ANGLE. REPLACE RIB ASSY PER SRM 51-35-01 PAGE 1-12 SRM 51-35-02 PAGE 3-9. P/N ARB1766-501.

Part: STRUCTURE — BROKEN (RT WING) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND ON RT WING LWR SIDE XORS 309, B/T REAR SPAR AND HINGE FLAP, 5 EA TL WITH HEAD BROKEN AND 1 EA WITH HIGH SUSPECT CORROSION BELOW SKIN. REMOVE EAS TL WITH HEAD BROKEN PER SRM 51-34-01 PAG 1-7. PERFORM ULTRASONIC INSPECTION PER DPS 4.713 ON BELOW SKIN. REPAIR WING LWR SKIN PER EA 8-5710-701131, REPLACE SUPPORT ARB 2259-2 ARB 2259-502. INSTALLED HINGE FLAP PER MM 57-41-01 P/N: ARB 2259-2, ARB 2259-502, TLV110-5-24.

Part: SKIN — CORRODED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND PITTING CORROSION ON SIDE SKIN BETWEEN LONG 48 RT - 41 RT, STA 1531 - 1754. EXISTING REPAIR WITH BULGING AND CRACK AROUND JAMB DOOR. REPLACE PANEL PER SRM 51-33-02 PAGE 34-47, SRM 51-35-01 PAGE 1-12 AND DWG NFA 6013. P/N AFA 3076-501, AFA 6014-5.

Part: ACCESS PANEL — DAMAGED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND EXISTING REPAIR FWD OF MID LAVATORY ACCESS PANEL AT 6 O'CLOCK APPROX STA 770. STRAP INSTALLED PER SRM 53-00-01 FIG 4 SHEET 2.

Part: FITTING — CORRODED (LT WING) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF REF NRC NF 11565, FOUND AFTER NUT REMOVAL, CORROSION AROUND FASTENERS HOLES ON MLG TRUNNION FITTING LT WING AND ON SPLICE ANGLE P/N ARB 0634-1. REPLACE SPLICE ANGLE PER SRM 51-34-01, P/N ARB0634-1, TLU 980-9-47, TLN 1000L9, ARB 1997-501, 2431218-9C18E, AN960C916L. REMOVE FASTENERS PER SRM 51-34-01, REMOVE CORROSION PER SRM 51-21-01, REWORKED AREA PER EA 8-55710-70140.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND EXISTING REPAIR BTW STA 959-STA 979 ON BOTTOM SKIN AT 6 O' CLOCK FOR SUMP DRAIN VALVE. NO ACTION REQUIRED, THE DOUBLER IS INSTALLED PER SB 53-86.

Part: BULKHEAD — DAMAGED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND AT STA 1701 X = 32.0 EXISTING REPAIR ON BULKHEAD AND DAMAGED CAUSE CHAIN. REMOVE EXISTING REPAIRS AT X=30 AND DISCART THEN. PERFORM VISUAL INSP FOR CRACKS AND DAMAGED AREA. IF GAUGES ARE FOUND, BLEND OUT AREAS IAW SRM 53-00-01 FIG 18. REPORT BACK WITH FINDING. REPLACE P/N: AFA0043-3 QTY:1.

Part: SKIN — DENTED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND DENT ON EXTERNAL SKIN BETWEEN STA 304 TO STA 330 RT SIDE LONG 33 TO LONG 36. REPLACE PANEL SKIN ABA 7049U4 PER DWG ABA7049/SRM 51-35-01 GAG 1/13 51-33-01 PAGE 34/47. REPLACE P/N: ABA 7049U4 , BN 330-428-4.

Part: SLAT TRACK — WORN (LT WING) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND AT LT WING FIX L/E NR 6 SLAT TRACK RIB WITH SEVERAL WEAR. REPLACE RIB PER SRM 51-33-01 PAGE 34/47. REPLACED P/N: ARB 1188-1 QTY: 8 ARB 1141-1 QTY: 1 ARB 1143-503 QTY:1 ARB 1147-503 QTY:1.

Part: SKIN — DENTED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND AT EXT LWR FUSELAGE RT SIDE - SKIN B/T STA 765 - 890 WITH SEVERAL DENT BEYOND LIMITS. NICKS, GAUGES AND EXISTING REPAIRS WITH PULLED HEAD FASTENERS B/T LONG 36-48. REPLACE SIDE SKIN ADA 3139-501 PER DWG NDA 6013 AND LONG 43. REPLACE SCUFF PLATE PER MM 20-50-02. REINSTALL DBLL RAM 1470-31 PER DWG RAM1470- 7009. WORK IN IAW NRC NF 10376. REPLACE P/N: ADA 3139-501 QTY:1 ADA 3483-1 QTY: 1 ADA 3968-29 QTY:1 ADA 3483-501 QTY 1.

Part: BUSHING — WORN (NR 3 PYLON) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND ON PYLON NR 3 BUSHING AFT WITH WEAR. REPLACE BUSHING PER MM 54-00-02-4, P/N AUB 7281-1. SPHERICAL BEARING PER MM 54-40-02. PERFORM DIMENSIONAL CHECK OF HOLE TO DETERTMINE WHICH O/S BEARING TO ORDERED.

Part: RIB — DAMAGED (LT L/E SLAT) · airframe 84,271 hrs · 25,024 cycles

DURING AIRPLANE`S CONVERSION FROM P-F/ACF FOUND AT LT SLAT NR 5 OUTBOARD SIDE RIB WITH HOLE IN RADIUS ANGLE. REPLACE RIB ASSY PER SRM 51-35-01 PG 1-12 SRM 51-35-02 PG 3-9. P/N ARB1766-501.

Part: ANGLE — CRACKED (NR 2 INLET DUCT) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND ON NR 2 ENGINE INLET DUCT, INBOARD PANEL 361 HL, ANGLE BROKEN. REMOVE NOSE COWL PER MM 20-50-02, REPLACE CRACKED SHIELDS PER DWG AJC7151, P/N AJC 7151-27, AJC 7151-29, INSTALL NOSE COWL PER MM 20-50-02.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE CONVERSION FROM P-F/ACF FOUND RT LONGERON 33 CRACKED AT STA 555 / STA 575. P/N 3849-19. REPLACE LONGERON PER SRM 51-35-01 PAGE 1-13 P/N ACA 3849-19, REINSTALL SKIN PER SRM 51-33-01 PAGE 34-47, SRM 51-35-01 PAGE 1-13.

Part: PANEL — CRACKED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND, BY ULTRASONIC INSPECTION, EA 3 PANELS CRACKED (NR 14 POSITION) P/N ALC7436-1. REPLACE PANELS PER SB 55-16, FIG 15 GROUP I, EA-8-5510-70126 P/N: SB10550016-7 KIT, SB10550016-117 KIT, 62525-7-16-7, 113LH7940T070. (OPEN)

Part: HINGE — CORRODED (RT WING FLAP) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND RT WING OUTBD HINGE SECTION OF OUTBD FLAP STA XW 638 RUST NEAR HOLES FOR STUDBOLTS. ACCOMPLISH CORROSION REWORK OF ATTACH HOLES (NR 3) FWD/OUTB HINGE OUTBD FLAP IAW CMM 57-44-09 AT HOLES MARKED 7. ACCOMPLISH CORROSION REWORK IAW CMM 57-44-09 CONT PG 301 TO 414 AT HOLES MARKED 2 HOLES REMAIN AT ORIGINAL SIZE DIA. REPROTECT IAW CMM 57-44-09 REV 30. EVERY SINGLE REWORK AREA MUST BE PROTECTED AND PAINTED IAW CMM 57-44-09.

Part: HINGE — CORRODED (TE FLAP) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND RT WING FWD INSIDE HINGE SECTION OF OUTBOARD FLAP STA XW 486 FOUND RUST NEAR HOLES FOR STUD BOLT AND IN THE HOLES OF THE LATERAL BRACE. ACCOMPLISH CORROSION REWORK OF RT FWD INBOARD HINGE OF RT OUTBOARD FLAP IAW CMM 57-44-08.

Part: LONGERON — MISMANUFACTURED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND ON STR 46 RT THE LONGERON SUPPLIED HAS BEEN FORMED INCORRECTLY. INSTALL A NEW LONGERON.

Part: FITTING — CORRODED (LONGERON) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND, AFTER REMOVAL BELLY SKIN, END FITTING WITH CORROSION AND REPAIR NOT CONFORMED TO SRM, BETWEEN STA 1521 TO STA 1581 LONGERON 52. REPLACE LONGERON 52 PER SRM 51-33-01 PAGE 34-47 MM 20-50-02.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND CRACK ON FLOORBEAM DIM 3 INCH AT STA 1293 X= -107. REPLACE FLOORBEAM IAW DWG AEA 0361.

Part: HINGE — CORRODED (RT TE FLAP) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND RT OUTBOARD FLAP FWD HINGE SECTION STA XW 638 WITH CORROSION IN THE BORE OF BUSHINGS ACTUATOR ATTACH POINTS. ACCOMPLISH CORROSION REWORK AT RT OUTBD FLAP OUTBD FWD HINGE HOLE BORES (5A), (5B) IAW CMM 57-44-09 REV 30.

Part: SKIN — DENTED (FUSLEAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE CONVERSION FROM P-F/ACF FOUND IN LWR FUSELAGE DENT 1 X 1 INCH ON EXTERNAL SKIN STA 330 LT SIDE LONG 28. PERFORMED NDI, FOUND CRACK. INSTALLED EXTERNAL REPAIR DOUBLER X SRM 53-00-02 FIG 5 SHT 1.

Part: HINGE — CORRODED (TE FLAP) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND RT OUTBOARD FLAP, FWD HINGE SECTION, STA XW 486 WITH CORROSION IN THE BORE OF BUSHINGS ACTUATOR ATTACH POINTS. ACCOMPLISH CORROSION REWORK AT RT OUTBOARD FLAP INBOARD FWD HINGE HOLES BORES (5A), (5B) IAW CMM 57-44-08 REV 30.

Part: RIB — CRACKED (LT WING) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND 2 INCH LONGERON CRACK RIB 402 LT WING AFT OF FUEL TANK FLAPPER DOOR. INSTALL REPAIR DOUBLER -3 PER SRM 57-20-00 FIG 33.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND AT AFT CARGO AT STA 1801 STR 45 RT EXFOLIATION. REMOVED CORROSION PER SRM 51-21-01 PAGE 28. CHECK LIMIT PER SRM 53-00-01. REPLACED LONGERON 45 RT PER SRM 51-33-01, P/N AGA 3083-505.

Part: HINGE — CORRODED (TE FLAPS) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND ON LT OUTBOARD FLAP HINGE SECTION STA XW 638 WITH OXIDATION WHERE CONTACT STUD BOLTS. ACCOMPLISH CORROSION REWORK AT LT OUTBOARD FLAP FWD OUTB'D HINGE SECTION IAW CMM 51-44-09.

Part: SKIN — CORRODED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND CORROSION ON LWR SKIN BTW FRAMES 1168/1334 AND STRG 46L/49R. REMOVE CORROSION PER SRM 52-21-01 PAGE 28. CHECK LIMIT PER SRM 53-40-00 FIG 14 (OUT LIMITS). REPLACE SKIN PER DWG NYB 6008 P/N 6008-27.

Part: SKIN — WORN (T/E FLAP) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE CONVERSION FROM P-F/ACF, FOUND RT WING OUTBD FLAP UPPER SIDE. LEADING EDGE B/T STA XOF 775-759 HAVE SKIN WITH WEAR DEEP. REPLACED SKIN PANEL X SRM 51-33-01 PG 34-47 DWG ARC1560.

Part: SKIN — DAMAGED (AILERONS) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND LT OUTBD AILERON UPPER SKIN STA XOA 907 TO XOA 912. REPLACE SKIN PER SRM 51-35-01 PAG 1-12. REBALANCE AILERON WILL BE PERFORMED PER NRC NF10454.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND AFT FUS VAST COMP STA 1986 FOUND EXISTING REPAIRED AND CORROSION ON FRAME P/N AGA3787-3. REPLACE FRAME PER SRM 51-35-01 PAGE 1-12 AND SRM 51-33-01 PAGE 34-47.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND AFT FUSELAGE COMPT STA 1975 FOUND FRAME P/N AGA 3183-3 WITH CORROSION. REPLACE FRAME PER SRM 51-35-01 PAGE 1-12 AND SRM 51-33-01 PAGE 34-47.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND AFT CARGO AT STA 187. FOUND STR 44 RT WITH CORROSION. REPLACE LONG 44 PER SRM 51-33-01 PAGE 34-47 AND SRM 51-35-01 PAGE 1-12.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND FWD AVIONIC COMPT AT STA 401 FRAME P/N ABA7104-67 AND ANGLE P/N 7104-69 WITH CORROSION. REPLACE FRAME AND ANGLE PER SRM 51-35-01 PAGE 1-12 AND SRM 51- 33-01 PAGE 33-47.

Part: SKIN — DAMAGED (RT WING) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND RT WING OUTBD AILERON B/T STA XOA1006/1023 FOUND LOWER SIDE FASTENERS PULLED THROUGH IN THE SKIN AND 1EA WITH HEAD BROKEN. REPLACE SKIN PER SRM 51-35-01 PG 1-12 AND REBALANCE PER SRM 57-50-00.

Part: FRAME — CRACKED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND FWD ACC COMP AT STA 469 RT SIDE. FOUND 1 CRACK OF 5 INCHES ON FRAME AND 1 CRACK ON LWR FLANGE OF 0.90 INCHES. REPLACED FRAME PER SRM 51-33-01 PAGE 34-47 AND SRM 51-35-01 PAGE 1- 12.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND AFT CARGO LOWER BELLY SKIN B/L LONG 48 RT - 48 LT STA 1531-1741 WITH CORROSION INTERNAL AND EXTERNAL SIDE. REPLACE SKIN PER SRM 51-35-01 PAGE 1-12 AND SRM 51-33-01 PAGE 34- 47 (REF DWG NFA 6014)

Part: SKIN — DELAMINATED (LT WING) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND LT WING INBOARD ISLAND UPPER SKIN WITH FINGER DOUBLER DELAMINATED. REPLACE UPPER SKIN PER SRM 51-35-01 PG 1-12 AND SRM 51-35-01 PG 34-47.

Part: FITTING — CORRODED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND AFT FUSELAGE VAST COMPT STA 1986-2007 3EA END FITTING LONGERON CORRODED. REPLACED END FITTING PER SRM 51-33-01 PAGE 34-47.

Part: FASTENER — WRONG PART (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND AT INSP HEAD MARKINGS OF FASTENERS ON THE VERTICAL TAIL IS INSTALLED FASTENER P/N HL221-8. REMOVE EXISTING FASTNERS AND REPAIR BY SB 55-023 GROUP 1.

Part: ADAPTER — CRACKED (NR 2 PYLON) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND NR 2 PYLON JOINT PANEL INTERAL SIDE WITH CRACK. REPLACED ADAPTER RING: ATL7029-91, ATL7029-87, ATL7029-89.

Part: NOSE COWL — DAMAGED (NR 3 ENGINE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND ENG NR 3 NOSE COWL BORDER ENTRY, WITH NR 6 HOLE APPROX .125 INCH PLUS NICK. REPLACE ENG NR 3 NOSE COWL IAW MM 71-11-00-2: P/N NSL 6051-511.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND DURING INSP, LWR FUS EXT STRUC EXISTING REPAIR (40 INCHES X 19 INCHES) STA 1781 TO STA 1821 RT SIDE BETWEEN L34 TO L38. SCRAP EXISTING REPAIR, DUE TO REPLACEMENT OF SKIN BELOW LONG 36, PERFORM A NEW REPAIR ON SKIN OVER LONG 36 PER SRM 53-20-00 FIG 6 SH 5, 6.

Part: LONGERON — DENTED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND AT STA 959, FWD CARGO COMPT, STR 40 LT WITH DENT. CUT DAMAGED LONGERON BETWEEN STA 939/959 - 959/979 AND INSTALL TWO LONGERON SPLICE PER SRM 53-10-10 FIG 1, 2 VOL I (TYPE I), P/N S2929835, S2613996.

Part: PANEL — CRACKED (EMPENNAGE) · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF FOUND BY ULTRASONIC INSPECTION 1 PANEL P/N ALC7438-2 (19 POSITION) CRACKED. REPLACED PANEL PER SB 55-16 FIG 20 GROUP 1 (KIT SB10550016-57).

Part: SKIN — WORN (LT WING) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION FROM P-F/ACF, FOUND ON LT WING FIX TE LWR SKIN WORN STA XORS 270 . REPLACE SKIN PER SRM 513501 PAGE 1-12.

Part: SKIN — DAMAGED (FUSELAGE) · corrosion level 2 · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE CONVERSION FROM P-F/CF IN AFT CARGO AT STA 1821-1841 FOUND STR 36 RT WITH EXISTING REPAIR. REPLACE LONGERON'S AND SPLICE PER SRM 51-33-01 PG 34-47.

Part: SUPPORT — CORRODED (MLG) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE'S CONVERSION TO P-F/ACF RT WING INTERNAL T-EDGE STRUCTURE STA XORS 264 ON MAIN LANDING GEAR SUPPORT FOUND SEVERAL AREA WITH CORROSION. REMOVE CORROSION PER SRM 51-21-01 PAGE 28, NDI CHECK PROTECT AND INSTALLED NEW FASTENERS.

Part: SKIN — DAMAGED (FUSELAGE) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING AIRPLANE CONVERSION FROM P-F/ACF HAVING REPLACE SKIN P/N AGA3108-1 FRAME AND SHEAR TIE AT STA 1986 ,PN AGA3783-3/-25 FRAME ,SHEAR TIE AT STA 1975 P/N, AGA3183-3/-23. REWORK INVOLVED AREA IAW EA 8-5310-77036.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING PAX TO FREIGHT CONVERSION FOUND INTERNAL FUSELAGE STA 791-808, STR 27, RT VANE DOOR WITH CORROSION AND EXFOLATION. REMOVE SCUFF PLATE FOR ACCESS OPEN SKIN, REPLACE DAMAGE SECTION OF LONGERON 27 AND REINSTALL SKIN IAW SRM 51-33-01 PAG 34-47;AND SCUFF PLATE.

Part: SPLICE — DAMAGED (ZONE 100) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING TO MODIFICATION AND TRANSITION CHECK, AFT CARGO COMPT FOUND AT STA 1821-1841 STR 36 RT WITH EXISTING REPAIR. REPLACE LONGERONS AND SPLICES PER SRM 51-33-01 PAGE 34-47, PART REPLACED:AGA3068-1, AGA3068-501, AFA3114-503, AFA3114-504.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING PAX TO FREIGHT CONVERSION FOUND INTERNAL FUSELAGE STA 791-808, STR 27, RT VANE DOOR WITH CORROSION AND EXFOLATION REMOVED SCUFF PLATE FOR ACCESS OPEN SKIN, REPLACE DAMAGE SECTION OF LONG 27 AND REINSTALL SKIN IAW SRM 51-33-01 PAGE 34-47; AND SCUFF PLATE.

Part: PANEL — CRACKED (ZONE 300) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

N12347, DURING PASSENGER TO FREIGHT COVERSION: ON PANEL 7208-1 RT SIDE, FOUND BY ULTRASONIC INSPECTION NR 1 HOLE WITH CRACK L .2500 INCH AT 1INCH FROM BOTTOM. POSITION NR 3, SHORE AIRCRAFT AS REQUIRED IAW SB 55-16, REPLACE CRACKED PANEL IAW SB 55-16 FIG 4 GRUP 1 AND EA 8-510-70126.

Part: FRAME — CRACKED (N/A) · corrosion level 2 · airframe 83,782 hrs · 24,798 cycles

DURING PASSENGER TO FRIGHTER CONVERSATION FOUND ON FWD ACCESSORY COMPARTMENT AT STA 459 RT SIDE, 1 CRACK 5 INCHES LONG ON FRAME AND 1 CRACK ON LOWER FLANGE OF THE .90 INCH. REPLACED FRAME PER SRM 51-33-01 PAGE 34-47 AND SRM 51-35-01 PAGE 1-12.

Part: SKIN — CRACKED (FUSELAGE) · corrosion level 2 · airframe 83,782 hrs · 24,798 cycles

DURING PASSENGER TO FREIGHTER CONVERSION FOUND ON PANEL 7205 -1 LT SIDE FOUND BY ULTRASONIC INSPECTION NR 1 HOLE WITH CRACK L= 1.25 - 1.65 INCH ON BOTTOM NR 6 POSITION. COSTANT SKIN SECTION REPLACEMENT PER EA 8-5510-70126.

Part: HINGE — CORRODED (TE FLAP) · corrosion level 2 · airframe 83,782 hrs · 24,798 cycles

DURING P TO F MODIFICATION AND TRANSATION CHECK FOUND LEFT OUTBOARD FLAP HINGE FWD SECTION STA XW 486 WITH OXIDATION WHERE CONTACT STUD BOLTS. REMOVED CORROSION AT BARREL NUT CORRESPONDING SIDE LOAD FITTING BOLT HOLE IAW CMM 57-44-08, INSTALLED BUSHING IAW CMM 57-44-08FIG 404.

Part: HINGE — CORRODED (TE FLAPS) · airframe 83,782 hrs · 24,798 cycles

N-12476 DURING PASSENGER TO FREIGHTER MODIFICATION AND TRANSITION CHECK LT OUTBOARD FLAP, FWD HINGE SECTION STA XW 486 WITH CORROSION IN THE BORES OF BUSHINGS ACTUATOR ATTACH POINTS. REMOVED CORROSION AND CHECK LIMITS IAW CMM 57-44-08 AND INSTALLED BUSHING REPAIR HOLE BORE (5A), (5B).

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING P TO F MODIFICATION AND TRANSITION CHECK, AFT FUSELAGE COMPT FOUND STA 1877-1951 STR 51 RT WITH CORROSION. REPLACED LONG 51 RT IAW SRM 51-35-01 PAGE 1-12 AND SRM 51-33-01 PAGE 34-47.

Part: SEAT TRACK — DAMAGED (FUSLEAGE) · airframe 83,782 hrs · 24,798 cycles

DURING P TO F MODIFICATION AND TRANSITION CHECK, FOUND DRILLED ADA3203-33 FLOOR PANEL STA 879-824 AT X /- 75.25 PROCURE DAMAGED HOLES .440 INCH Q/TA 5 HOLE ON EXISTING SEAT TRACK. PERFORM REPAIR IAW SRM 57-70-00 FIG 1A VOL I. INSTALL P/N WSP0414-7, ACA7414-3.

Part: HINGE — CORRODED (TE FLAP) · corrosion level 2 · airframe 83,782 hrs · 24,798 cycles

DURING PAX TO FREIGHTER MODIFICATION AND TRANSITION CHECK, FOUND LT OUTBOARD FLAP FWD HINGE SECTION STA XW 486 WITH CORROSION AT THE FACE OF BORE FOR BEARING. CORROSION REWORK FWD INNER HINGE NR 4 LUG FACE IAW CMM 57-44-08 IN LIMIT REF FIG 401 SH 1 CMM 57-44-08, INSTALL SHIM IAW CMM 57-44-08.

Part: TEAR STRIP — CRACKED (FUSELAGE) · airframe 83,782 hrs · 24,798 cycles

DURING P TO F MODIFICATION TRANSITION CHECK, AFTER REMOVAL SKIN IS NOTED 2EA TEAR STRIP WITH CRACK .50 INCH LONG STA 879 AND 899 BETWEEN L46 TO L48 RIGHT SIDE. FABRICATE A NEW TEAR STRIP (INCREASE LENGTH .10 INCH TO ENSURE 2DE MARGINE) IAW SRM 51-35-01.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING PAX TO FREIGHTER CONVERSION, AFT CARGO AREA, STA 1877 TO STA 1951, STRINGER 51 LT, FOUND CORRISION INNER EXTRUSION LONGERON. REPLACED LONGERON 51 IAW SRM 51-33-01 FIG 34, 47 AND SRM 51-35-01.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING PAX TO FREIGHTER MODIFICATION AND TRANSITION CHECK, FOUND FWD AVIONICS COMPARTMENT AT STA 421, FRAME CORRODED. REMOVED AND REPLACED FRAME IAW SRM 51-31-01 PAGE 1-12 AND SRM 51-33-01.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 3 · airframe 83,782 hrs · 24,798 cycles

DURING P TO F MODIFICATION AND TRANSITION CHECK, AFT CGO AT STA 1801-1821, 1887-1902-1921. FOUND STRINGER 52 WITH CORROSION. REMOVED AND REPLACED STRINGER IAW SRM 51-33-01 PAGE 34, 47 AND SRM 51-35-01 PAGE 1-12.

Part: RIB — CRACKED (CENTER WING) · airframe 83,782 hrs · 24,798 cycles

MAJOR REPAIR DURING C-CHECK, PASSENGER TO FREIGHTER CONFIG, FOUND RIB XCW/81 BETWEEN LONGERON 21 AND 22, UPPER CORD RADIUS HAS .5 INCH CRACK CENTER WING RIB. REPAIRED AREA WITH A FAB ANGLE, PER EA 8-5710-70141.

Part: PANEL — CRACKED (HORIZ STAB) · airframe 83,782 hrs · 24,798 cycles

MAJOR REPAIR DURING C-CHECK, AND PASSENGER TO FREIGHTER CONFIG BY ULTRASONIC INSPECTION, FOUND 1 PANEL CRACKED ON THE HORIZONTAL STABILIZER. P/N REMOVED ALC7204-1. REMOVE AND REPLACE PANEL WITH P/N ALC7204-501N PER EA 8-5510-70126.

Part: PANEL — CRACKED (ZONE 300) · airframe 83,782 hrs · 24,798 cycles

ON PANEL 7208-1 RT SIDE FOUND BY ULTRASONIC INSPECTION 1 HOLE WITH CRACK, L= .25 INCH AT 1 INCH FROM BOTTOM. REPLACED PANELS PER SB 55-16 FIG 3 GROUP 1 (EA -8-5510-70126) FEDEX P/N: SB10550016-17KIT, SB10550016-93KIT. THE P/N ITEM 5 IS A REPLACEMENT KIT. THE CORRECT P/N DEFECTED IS 7208-1.

Part: SKIN — DENTED (ZONE 200) · airframe 83,782 hrs · 24,798 cycles

LOWER FUSELAGE EXTERNAL INSPECTION, FOUND MANY DENTS (MAX DENT .044 EA) ON EXTERNAL SKIN STA 295 TO STA 330 SIDE AREA BETWEEN L33 TO L36. REMOVED AND REPLACED SKIN PANEL PER ABA 7050 AND SRM.