N784NC

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 74,571 hrs · 68,711 cycles

LT AND RT OVERWING EMERGENCY LIGHTS COME ON WITH EMERGENCY LIGHT SWITCH IS SET TO ARM. TROUBLESHOT AND FOUND THE OVERWING EMERGENCY LIGHT BATTERY PACK IS BAD. R & R THE OVERWING EMERGENCY LIGHT BATTERY PACK AND PERFORMED OPS CHECK. OPS CHECKED GOOD REF WDM A-33-51-01-00A-051H-A, AMM A-33-53-00-401-926A-A AND AMM 33-45-00-501-927A.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 74,571 hrs · 68,711 cycles

LT AND RT OVERWING EMERGENCY LIGHTS COME ON WITH EMERGENCY LIGHT SWITCH IS SET TO ARM. TROUBLESHOT AND FOUND THE OVERWING EMERGENCY LIGHT BATTERY PACK IS BAD. R & R THE OVERWING EMERGENCY LIGHT BATTERY PACK AND PERFORMED OPS CHECK. OPS CHECK GOOD REF WDM A-33-51-01-00A-051H, AMM A-33-53-00-401-926A-A AND AMM 33-45-00-501-927A-A.

Part: LONGERON — CRACKED (BS 389) · airframe 74,571 hrs · 68,711 cycles

LONGERON CRACKED UNDER FRAME AT BS 389 AND L17R. ACCOMPLISHED PERMANENT REPAIR IAW SRM 53-02.

Part: LONGERON — CRACKED (BS 389) · airframe 74,571 hrs · 68,711 cycles

LONGERON CRACKED UNDER FRAME AT BS 389 & L17R. R & R LONGERON 17R IAW SRM 53-02, FIG 18. INSTALLED ID REPAIR TAG IAW DPS 900-5-1-NR 4.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 73,650 hrs · 67,654 cycles

DURING LINE CHECK, MAINTENANCE FOUND THE EMERGENCY LIGHT AT SEAT 7D TO BE INOPERATIVE. MAINTENANCE REPLACED THE LIGHT ASSEMBLY AND THE LIGHT RETURNED TO AN OPERATIONAL CONDITION AFTER A FUNCTIONAL CHECK OF THE SYSTEM.

Part: WIRE — BROKEN (EMERGENCY LIGHTS) · airframe 73,650 hrs · 67,654 cycles

DURING LINE CHECK, MAINTENANCE FOUND THE CENTER TAIL SECTION EMERGENCY LIGHT TO BE INOPERATIVE. UPON INSPECTION, MAINTENANCE FOUND THE LIGHT ASSEMBLY WIRE TO BE BROKEN. MAINTENANCE REPAIRED THE WIRE, REPLACED THE LIGHT ASSEMBLY, REMOVED AND REINSTALLED THE BLIND CHERRY RIVETS AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION. AIRCRAFT WAS RETURNED TO SERVICE AFTER A SUCCESSFUL CHECK OF THE SYSTEM.

Part: FUSE — BLOWN (CABIN) · airframe 3,675 hrs · 3,299 cycles

EMERGENCY EGRESS AISLE LIGHTING INOP, ROWS 5 THROUGH 8. REPLACED FUSE AT RIGHT OVERWING POWER SUPPLY, CHECKS NORMAL.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 3,519 hrs · 3,147 cycles

EMERGENCY EGRESS AISLE LIGHTS INOPERATIVE, ROWS 5 THROUGH 8, AND RIGHT FORWARD OVERWING EXIT SIGN. REPLACED POWER SUPPLY AND LIGHT ASSEMBLY, CHECKED GOOD.

Part: FUSE — BLOWN (CABIN) · airframe 3,426 hrs · 3,049 cycles

LEFT FORWARD OVERWING EXIT VERTICAL SIGN INOPERATIVE. REPLACED FUSE AND BATTERY SET. OPS CHECK GOOD.

Part: SKIN — DENTED (BS 239) · airframe 74,571 hrs · 68,711 cycles

RT FUSELAGE SKIN IS DENTED BETWEEN STA 239, 6 INCHES BELOW CUSP LINE. DENT MEASURES 1"X 8"X.025" DEEP. EDDY CURRENT DENT NO CRACKS FOUND. P

Part: BATTERY — DISCHARGED (CABIN) · airframe 72,259 hrs · 66,235 cycles

MAINTENANCE FOUND EMERGENCY ESCAPE PATH LIGHTING AT SEAT ROWS 5 - 8 AND RIGHT FORWARD EXIT SIGN INOPERATIVE. MAINTENANCE REPLACED BATTERIES AND FUSE ON RIGHT SIDE. LIGHTS RETURNED TO NORMAL OPERATION.

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 2,336 hrs · 2,007 cycles

MAINTENANCE FOUND THE RIGHT FORWARD EXIT AND ROWS 5 - 8 EMERGENCY EXIT LIGHTS INOPERATIVE. HOUSING WAS ALSO BROKEN ON RIGHT FORWARD EMERGENCY EXIT LIGHT. MAINTENANCE REPLACED THE RIGHT FORWARD EMERGENCY LIGHT POWER SUPPLY PER AMM. OPERATIONAL CHECK WAS OK. AIRCRAFT OK FOR SERVICE.

Part: FUSE — BLOWN (CABIN) · airframe 71,867 hrs · 65,878 cycles

MAINTENANCE FOUND EMERGENCY ESCAPE PATH LIGHTING FROM SEAT ROWS 5 THROUGH 8 DO NOT ILLUMINATE. MAINTENANCE REPLACED THE FUSE IN RIGHT FORWARD OVERWING EMERGENCY EXIT LIGHT PER AMM. AIRCRAFT OK FOR SERVICE.

Part: FAIRING — CORRODED (LWR FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

LWR FUSELAGE FROM STA Y851 TO STA Y927 BTWN L20 RT AND 30. FAIRING ATTACH POINTS WITH CORROSION AND MISSING STRAP. REMOVED CORROSION FROM BODY FAIRING ATTACH IAW SRM 51-10-3 IN LIMITS BTWN STA Y911-STA Y931 S21R -26R IN LIMITS BTWN STA Y891 - Y911 S26 DOUBLER OUT OF LIMITS FABRICATED AND INST DOUBLER SPLICE BTWN STA Y870-Y889 AND L26-L26R IAW SRM 51-30-2 INST 3 EA RUBSTRIPS FROM STA Y851-STA Y927 BTWN LONG L20R AND 30 IAW SRM 53-04.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 71,726 hrs · 65,746 cycles

MAINTENANCE FOUND LEFT AND RIGHT EXTERIOR OVERWING EMERGENCY EVACUATION LIGHTS INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE POWER SUPPLY B5-49 IN ACCORDANCE WITH WDM AND AMM. OPERATIONAL CHECK GOOD.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 71,726 hrs · 65,746 cycles

PASSENGER CABIN FLOOR PANEL NR 76-50 IS DELAMINATED. FABRICATED AND INSTALLED HAT CHANNELS AND SKIN, DOUBLER AND SUPPORT IAW SAA ERA 491550-14, REV ORIGINAL, FLOOR PANEL 76-50.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 71,726 hrs · 65,746 cycles

PASSENGER CABIN FLOOR PANEL NR 17-50 IS CRACKED AND EDGE DAMAGED. FABRICATED AND INSTALLED HAT CHANNELS AND SKIN IAW SAA ERA 491550-14 REV ORIGINAL INST ID TAG IAW PS 900-5-1 NR 4 COMPLETED.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

FWD CARGO COMPARTMENT RT ALT STATIC PORT INTERNAL DOUBLER WITH CORROSION. CORROSION REMOVAL WAS FOUND TO BE OUT OF LIMITS PER SRM 53-01 PG 1-4. REMOVED AND REPLACED T PER SRM 57-30-2 PG 24. AERODYNAMIC TEST FOR STATIC PORT MISMATCH PORT AND RIVETS WAS .001 INCH WITHIN LIMITS PER DC9 AMM 34-12-02-501-927A-A.

Part: SHEAR TIE — DAMAGED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

SHEAR TIE MISLOCATED AT FS 579 BETWEEN L29R AND L30. REMOVED DAMAGE AT FORMER SHEAR TIE SECTION PER SRM 53-03, FABRICATED NEW SHEAR TIE SECTION PER SRM 53-03, HEAT TREATED SHEAR TIE TRAVELER NR 87360810001 LOCATED AND DRILLED SHEAR TIE SECTION PER SRM 51-10-4. FABRICATED SPLICE SECT PER SRM 53-03 FIG 3,TREATED AND PRIMED SHEAR TIE SECT AND SPLICE SECT PER SRM 51-10-3. INSTALLED SHEAR TIE SECT AND SPLICE SECT PER SRM 53-03 AND SRM 51-30-5.

Part: SEAT TRACK — BROKEN (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

MAIN CABIN LT OTBD SEAT TRACK STA 440, HAS A SECTION OF LUG BROKEN OFF OF THE CROWN OF TRACK. FABRICATED SEAT TRACK IAW SRM 53-23-0 FIG 1, CUT OUT DAMAGED AREA LT OTBD SEAT TRACK STA 436-454 IAW SRM 53-05. LOCATED AND DRILLED HOLES 2 NEW SPLICE IAW SRM 51-10-4 PG 1, INSTALLED 1 SEAT TRACK AND 2 REPAIR SPLICE PER DC-9 SRM 51-30-5 AND SRM 53-05 FIG 4F.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

LWR FUSELAGE LT SIDE, STA Y 130.5,-Z22 EXTERNAL EXISTING REPAIR DOUBLER WITH CRACK. REMOVED AND REPLACED DAMAGED LATCH SKIN DOUBLER WITH DOUBLER P/N 09-5300-3-0925, BATCH NR 0002028806 REF SRM 53-04 FIG 24. IDENTIFIED REPAIR PER PS 900-5-1 NR 4.

Part: HINGE — WORN (RT WING TE FLAP) · airframe 71,726 hrs · 65,746 cycles

RT WING, STA XRS 353, T/E FLAP HINGE BUSHING WORN. REMOVED AND REPLACED RT WING FLAP HINGE IAW AMM 57-40-01-201-925A AND AMM 20-16-00-401-926A-A. REMOVED CABLE BLOCKS ON AILERON RT CTRL CABLES AND TRIM CABLES IAW AMM-57-40-01-201-925A AND AMM-27-10-00-501-927A-A, DISCONNECT RT AILERON CONTROL BUS CABLES AND AILERON TRIM CABLES AND RECONNECT IAW AMM-57-40-01-201-925A AND AMM -27-10-00-501-927A. RT WING AILERON CONTROL BUS CABLES AND AILERON TRIM CABLES.

Part: SKIN — DENTED (FUSELAGE) · airframe 717,726 hrs · 65,746 cycles

EXT SKIN DENT AT BS 180 AND L4L L=6", W=1", DEPTH = .064", D/X=15.625. OUT OF LIMITS PER SRM 53-04 FIG 38 DUE TO DEPTH AND PROX TO FRAME AND LONGERON. TRIMMED OUT SKIN EXT REPAIR DOUBLER, INSTALL REPAIR FINGER DOUBLER AND.050" THK REPAIR FILLER INSTALL ON TRIMOUT. ERA 492111-14AD REV ORIG FOR REPAIR APPR IS FOR 12 MONTHS ONLY. ADDL ENG AUTH ERA REV IS REQ FOR CTND SERVICE OF 12 MONTHS FROM THE FAA 8100-9 APPRL DATE.

Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

FLOOR PANEL NR 105 CRACK AROUND RIVETS FWD EDGE REMOVED AND INSTALLED FLOOR PANEL NR 105 PER DC-9 AMM 53-20-01. FABRICATED FLOOR PANEL NR 105 IAW DC-9 SRM 53-23-0 FIG 7 PG:11AND TREATED AND PRIMED FLOOR PANEL NR 105 PER SRM 53-10-3 PAR21 AND PG 31 PAR 14.

Part: SKIN — CORRODED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

LWR FUSELAGE, FROM STA Y468 TO STA Y481, BTWN L29L AND L30, EXT SKIN AND EXT REPAIR DOUBLER WITH CORROSION. REMOVED AND REPLACED EXTERNAL REPAIR FILLER CORROSION REMOVED ON SKIN, REWORK AREA IN LIMITS IAW SRM 53-04, 1EA EXT REPAIR DOUBLER, 1EA REPAIR FILLER, AND 4 EA INT FINGER REPAIR DOUBLER WERE INST PER ER/A 491561-14 ACCOMP AN EXT VISUAL INSP FOR CORROSION, LOOSE OR MISSING FASTENERS PRIOR TO 8000 CYCLES AFTER REPAIR COMP.

Part: SKIN — DENTED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

LT EXTERIOR FUSELAGE DENT AT B STA 256 APPROX AND BETWEEN LONG 15L AND 16L IS WITHIN 1 INCH FROM THE FRAME STRUCTURE. COLD FORMED SKIN BACK TO ORIGINAL CONTOUR TO REMOVE DENTED AREA IAW DC9 SRM 53-04 FIG 38 PG 2/7 TABLE C, FABRICATED, TREATED, PRIMED AND INSTALLED DOUBLER REPAIR IAW DC9 SRM 53-04 FIG 38 VIEW GC107.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,726 hrs · 65,746 cycles

PASSENGER CABIN FLOOR PANEL NR 79-50 HAS CORROSION. PANEL NR 79-50 REPAIRED IAW DC-9 SRM 53-23-0 PG: 8 FIGURE 5. FABBED NEW WEB PANEL IAW DC-9 SRM 53-23-0 PAGE 8 FIGURE 5. INSTALLED 2 EA HAT CHANNELS.

Part: FLOOR PANEL — PUNCTURED (CABIN) · airframe 71,726 hrs · 65,746 cycles

PASSENGER CABIN FLOOR PANEL 59-50 HAS PUNCTURE. REMOVED HAT CHANNELS 2EA AT IAW DC-9 SRM 51-30-2 PG 24, 26. CUT OUT DAMAGED AREA IAW DC-9 SRM 53-05 PG 10. FABBED DOUBLER AND FILLER IAW DC-9 SRM 53-05 PG 10. TREATED AND PRIMED DOUBLER AND FILLER IAW DC-9 SRM 51-10-3 PG 31 AND DC-9 SRM 51-10-3. INSTALLED DOUBLER AND FILLER IAW DC-9 SRM 51-30-2 PG 26B PAR 8. INSTALLED HAT CHANNELS 2EA IAW DC-9 SRM 51-30-2 PG 26B.

Part: SKIN — DENTED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

LOWER FUSELAGE, STA Y97.25, Z49, LT SIDE EXTERNAL SKIN WITH DENT, MEASURED DENT OUT OF LIMITS IAW SRM 53-04 FIG 38 CONDITION 1A. CUT OUT DAMAGE, FABBED AND INSTALLED REPAIR DOUBLER AND REPAIR FILLER IAW SRM 53-01 FIG 4. HFEC SURFACE NO CRACKS NOTED AT IAW NDTSPM 06-10-001 AND 003. INSTALLED ID TAG IAW PS 900-5-1.

Part: ANGLE — CRACKED (NR 2 STRUT) · airframe 71,726 hrs · 65,746 cycles

NR 2 STRUT LWR INNER SURFACE, ADJACENT TO AFT ENGINE MOUNT POINT, ANGLE CRACKED AT FASTENER ON AFT FACE OF BULKHEAD. REMOVED ANGLE PER SRM DC-9 51-30-1, FABBED ANGLE IAW 9915500 (-8) PER SRM DC-9 51-10-4 & 51-10-2 INSTALLED ANGLE PER SRM DC-9 51-30-5 PG 1. USED TORQUE WRENCH ASSET DATE DUE 09-28-11 ID#11-564 & T.W. ASSET 09-28-11 ID#11-580 AT NR 2 STRUT LWR INNER SURFACE ADJACENT TO AFT ENG MOUNT.

Part: FLOOR PANEL — CORRODED (COCKPIT) · airframe 71,726 hrs · 65,746 cycles

COCKPIT FLOOR PANEL 14 HAS SURFACE CORROSION AND SECURING FASTENERS PULLING THRU AND PUNCTURED. REMOVED COCKPIT PANEL 14 PER MM A-53-20-01-201-925A-A PG 1-4 FOUND PANEL TO BE OUT OF LIMITS PER SRM 53-05 PG 9 PAR 3 FABRICATED PANEL PER SRM 53-05 FIG 1. REINSTALLED PANEL 14 IN COCKPIT PER A-53-20-01-201-925A-A PG 1-4.

Part: SUPPORT — CRACKED (NR 2 PYLON) · airframe 71,726 hrs · 65,746 cycles

NR 2 PYLON AFT MOUNT LWR BEAM SUPPORT STRUCTURE CORNER ANGLE CLIP CRACKED, VIEWED THRU ACCESS DOOR PNL 8212. REMOVED ANGLE CLIP PER SRM DC9 51-30-1, FABBED ANGLE CLIP DWG 9915500 TRAVELER 8736011001 LOCATED & DRILLED HOLES PER SRM DC -9 51-10-4 INSTALLED ANGLE CLIP PER SRM DC-9 51-30-5 PG 1 AT NR 2 PYLON AFT MOUNT LWR BEAM SUPPORT.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,726 hrs · 65,746 cycles

CABIN FLOOR PANEL 27 METAL THRU PLATE 2 EACH FOR LAV WATER LINES HAS CORROSION ON CABIN FLOOR PANEL 27, REMOVED 2EA. LAV WATER LINE DOUBLER IAW DC9/MD-80 SRM 51-70-02 PARA 6 PAGE 11. FABBED 2EA DOUBLER PLATE PER FSI DWG 94RS481265. BONDED 2EA DOUBLER PLATE ON FLOOR PANEL 27 IAW FOR ENGINEERING SUPPORT 87359480001 AND PS900-7-1- NR 03.

Part: VANE — DAMAGED (TE FLAP) · airframe 71,726 hrs · 65,746 cycles

I/B FLAP FIXED VANE THE AFT ATTACH POINT HAS METAL PEELING UP. REPAIRED DISCREPANT AREA ON I/B FLAP FIXED VANE IAW SRM 51-30-2 PAGE 1, SRM 51-70-2 PARAGRAPH 18(4) PAGE 91&92, SRM 57-50-9 PAGE 5 PER DWG PL591004, SRM 51-70-2 PARAGRAPH 26 PAGE 269-274, SRM 51-70-2 PARAGRAPH 18B AND TABLE 7, SRM 51-30-2, SRM 51-10-3 PARA 2, SRM 51-70-2 PARAGRAPH 24.

Part: SKIN — DENTED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

DURING MCK AT SAT, 4 EA DENTS WERE FOUND ON THE FUSELAGE SKIN, JUST AFT OF THE LOWER AFT CORNER OF THE FWD CARGO DOOR CUTOUT. PERFORM ER/A 491082-14 SECTION II AS FOLLOWS: INITIAL INSPECTION - ON OR BEFORE 25-APR-13 REPEAT INSP - EVERY 24 MOS AFTER THE INITIAL INSP ASSOCIATED ER/A 13-491082 ADDED COMPLIED WITH ER/A 491082-14 REV ORIG.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

LWR FUSELAGE FROM STA Y367 TO Y370, BETWEEN LONGERON 26 LT AND 28 LT EXT SKIN WITH TOOL MARKS. CUT OUT DAMAGE AREA AT STA Y368 ABOVE LONGERON 27 LT, NDT INSPECTED AREA NO DAMAGE NOTED. FABRICATE AND INSTALLED FILLER AND INTERNAL REPAIR DOUBLER PER SRM 53-04 FIG 38 PG 281M VIEW 1.

Part: FLOOR SKIN — DENTED (FLOOR PANEL) · airframe 71,726 hrs · 65,746 cycles

CABIN FLOOR PANEL 49 HAS 4 EA DENTS IN UPPER SKIN. DAMAGE IN EXCESS OF 8 INCHES OUT OF LIMITS IAW SRM 53-05. FABRICATED FLOOR PANEL 49 IAW SRM 53-23-0 AND 53-05, REMOVED HAT CHANNELS IAWSRM 53-05 PAINTED AND TREATED FLOOR 49 RE-INSTALLED HAT CHANNELS IAW SRM 53-05.

Part: SKIN — DENTED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

LOWER FUSELAGE STA Y 245 BETWEEN LONGERON 15 RT AND 16 RT EXTERNAL SKIN WITH DENT. CHECKED DENT FROM STA Y 245 BETWEEN LONGERON 15 RT AND 16 RT OUT OF LIMITS PER SRM 53-04 PG: 217 FIG 38 CONDITION 1A COLD FORMED SKIN BACK TO ORIGINAL. CONTOUR IAW SRM 53-04 FIG 38 TABLE C "NOTE" FABBED REPAIR DOUBLER IAW SRM 53-04 FIG 38 PAGE 218AA. INSTALLED ID TAG IAW PS 900-5-1 PG 4.

Part: SKIN — DENTED (FUELAGE) · airframe 71,726 hrs · 65,746 cycles

PASSENGER AFT ENTRANCE DOOR STAIRWAY EXTERNAL SKIN WITH DENT AT STA YSD94 - X12.5. OUT OF LIMITS IAW SRM 53-04, PG 217, CUT OUT DENTED AREA IAW SRM 52-05, FIG 3, PG 8 HFEC SURFACE INSP IAW NDT SPM 06-10-01.001. NO CRACKS NOTED FABRICATED, TREATED, PRIMED AND INSTALLED REPAIR DOUBLER FILLER AND TAPERED SHIMS IAW SRM 52-05, FIG 3. CLOSED PASSENGER AFT ENTRANCE DOOR STAIRWAY EXTERNAL SKIN SECTION IAW SRM 51-30-2, PAGES 1, 2, 3, INSTALLED. REPAIR ID TAG IAW PS 900-5-1, NR 4.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,726 hrs · 65,746 cycles

PASSENGER CABIN FLOOR PANEL 22-50 HAS CORROSION OUT OF LIMITS REF SRM 53-01, PG 8 FIG 1. REMOVED HAT CHANNELS SKIN REF SRM 51-30-2, PG 1-14. FABRICATED SKIN USING 7075T6-.040 BATCH 0001804643 REF SRM 53-23-0, PG 6, FIG 3. TREATED SKIN REF SRM 51-10-3, PG 40, PARA 21 & PRIMED REF SRM 51-10-3, PG 31, PARA 14. INSTALLED HAT CHANNELS REF SRM 51-30-2, PG 1-14, (5EA).

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,726 hrs · 65,746 cycles

PASSENGER CABIN FLOOR PANEL 25-50 HAS CORROSION. REMOVED CORROSION ON FLOOR PANEL 25-50 SKIN, FOUND TO BE OUT OF LIMITS, REMOVED, FABRICATED, AND INSTALLED NEW SKIN IAW AMM DC-9-A-51-21-03-701-929A-A, SRM 53-23-07 P.7, SRM 51-10-4, SRM 51-10-2, SRM 51-10-3 P.31-32,P.40-41 AND SRM 51-30-2 P.2 FIG 1,P.24-26.

Part: FLOOR PANEL — CORRODED (PANEL 98-50) · airframe 71,726 hrs · 65,746 cycles

PASSENGER CABIN FLOOR PANEL 98-50 HAS CORROSION. REMOVED CORROSION IAW AMM DC9-A-51-21-03-701-929A-A ORIGINAL OUT OF LIMITS IAW AMM SRM 53-01 PG:5-8. REMOVED 2 EA HAT CHANNELS IAW SRM 51-30-02, PG 24. RECEIVED MATERIAL IAW SRM 53-23-0. TREATED AND PRIMED REPLACEMENT FLOOR PANEL IAW SRM 51-10-3, PAR 14, PG 31 AND PAR 21, PG 40. INSTALLED 2 EA HAT CHANNELS ON 51-30-02, PARA 8, PG 26B.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,726 hrs · 65,746 cycles

CABIN FLOOR PANEL 46 HAS SURFACE CORROSION ALONG ROW OD OTBD FASTENER HOLES. BLENDED CORRODED FASTENER HOLES IAW SRM 51-10-3 PG 46-47 ORIG MAT THICKNESS .020 IAW SRM 53-23-0 MAX MAT LOSS .020 OUT OF LIMITS IAW SRM 53-01. REMOVED IAW SRM 51-30-11 AND 51-30-2. REMOVED 8 EA RIVETS AND 2 HAT CHANNELS IAW SRM 51-60-0, PG 7, FIG 1 INSTALLED 2 EA HAT CHANNELS AND RIVETS IAW SRM 51-20-0, PG 10-11 AND 51-30-02, PG 2-4 AND 26B.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

LWR FUSELAGE STA Y79 TO STA Y589 BETWEEN LONGERON 21L AND 22L EXTERNAL SKIN WITH TOOL MARKS. REMOVED DAMAGE, NDT NO DAMAGE NOTED. FABRICATED REPAIR PARTS PER SRM 53-04 FIG 38 PG 218L. TREATED AND PRIMED PARTS PER SRM 51-10-3 PARA 14 AND 21. INSTALLED ALL REPAIR PARTS PER SRM 53-04 FIG 38 PG 218L.

Part: FLOOR SUPPORT — CRACKED (BS 200-215) · airframe 71,726 hrs · 65,746 cycles

CABIN FLOOR SUPPORT COMPOSITE ANGLE CRACKED STA 200 TO 215 RBL-55. R & R FLOOR SUPPORT COMPOSITE ANGLE WITH PN S4616493-12500, BATCH 0002032988 AT STA 200 TO 215 RBL 55 IAW SRM 51-30-8, PG 3. PRIMED IAW SRM 51-10-3 PG 31, PAR 14. .

Part: SKIN — DENTED (BS 60) · airframe 71,726 hrs · 65,746 cycles

EXTERIOR FUSELAGE DENT AT BS 60.0 AND 20" ABOVE NOSE GEAR CUTOUT RT SIDE IS WITHIN 1" FROM FRAME. REPAIRED AREA ON MAT USE 2014-T6 .050 BATCH 1654113 TREATED, PRIMED IAW SRM 51-3, APPLIED SEALANT IAW SRM 53-01 FIG 4 AND CIC ON REPAIR AREA IAW SRM 53-01, PG 25, FIG 4, STEP 1-7 INSTALLED ID TAG IAW PS900-5-1 NR 4.

Part: SKIN — DENTED (BS 233) · airframe 71,726 hrs · 65,746 cycles

LWR FUSELAGE, STA Y233, BETWEEN L18 AND 19LT, EXTERNAL SKIN WITH DENT REMOVED SKIN DAMAGE. FABRICATED REPAIR PARTS IAW SRM 53-04, FIG 12B TREATED AND PRIMED REPAIR PARTS IAW SRM 51-10-3 PG.31, 40 AND INSTALLED IAW SRM53-04, FIG 12B INSTALLED ID TAG IAW PS 900-5-1, NR 4.

Part: SKIN — DENTED (BS 576) · airframe 71,726 hrs · 65,746 cycles

LOWER FUSELAGE, STA Y576, BETWEEN L26 AND 27 LT, EXTERNAL SKIN WITH DENT. DENT OUT OF LIMITS IAW SRM 53-04, TRIM OUT DAMAGE SRM 53-04 LOCATED AND DRILLED PARTS IAW SRM 51-10-4, PG 2, TREATED AND PRIMED DOUBLER AND FILLER IAW SRM 51-10-3. INST DOUBLER INTERNAL REPAIR AND FILLER IAW SRM 53-04, FIG 38, AND INST ID REPAIR TAG IAW PS 900-5-1, NR 4.

Part: FLOOR SKIN — DAMAGED (BS 1159) · airframe 71,726 hrs · 65,746 cycles

AFT CABIN STA 1159, RBL 15 SUB FLOOR SKIN HAS 2 EA TOOL MARKS. MEASURED AFT CABIN SUB FLOOR ORIG MAT.040" MAT LOSS .015" OUT OF LIMITS IAW SRM 53-01, PG 8, FIG 1, SHT 3. REMOVED DAMAGE AREA IAW SRM 53-01. NO CRACKS NOTED. FABED DOUBLER IAW SRM 53-01. INST DOUBLER IAW 53-01 PG.25. APPLIED IDENTIFICATION TAG IAW PS 900-5-1, NR 4 PG3.

Part: SPAR — CRACKED (HORIZONTAL STAB) · airframe 71,726 hrs · 65,746 cycles

LT HORIZ STABILIZER FRONT SPAR WEB WITH CRACK AT STA XFS 77.5. STOP DRILLED CRACK ON LT HORIZ STAB FRONT SPAR WEB AT STA XFS 77.5 IAW SRM 55-01, PG 9, FIG 2. FABRICATED DOUBLER REPAIR IAW SRM 55-01, PG 9, FIG 2. TREATED AND PRIMED DOUBLER REPAIR IAW SRM 51-10-3, PG 40 & PG 21 INST DOUBLER REPAIR ON LT HORIZ STABILIZER FRONT SPAR WEB AT STA77.5 IAW SRM 55-01 PG 9, FIG 2. INST ID TAG IAW PS.

Part: LONGERON — CRACKED (BS 1136) · airframe 71,726 hrs · 65,746 cycles

MAIN CABIN LT/ AFT LAVATORY AREA, STA Y1136, LONG 16LT WITH CRACKS. CUT OUT DAMAGE LONGERON. FABRICATED LONGERON SECT AND SPLICE SECTION IAW SRM 53-02, FIG 18 AND INST LONGERON SECTION AND SPLICE SECTION FROM MAIN CABIN LT AFT LAVATORY AREA STA Y1136 LONG, 16LT NDT CUTOUT AREA NO CRACKS NOTED, INST LONGER ON SECTION AND SPLICE SECTION IAW SRM 51-30-2, PAGE 2 AND 53-02 FIG 18, PAGE 52.

Part: FLOOR SUPPORT — CRACKED (BS 168-200) · airframe 71,726 hrs · 65,746 cycles

CABIN FLOOR SUPPORT COMPOSITE HAT CHANNEL CRACKED AND NUT PLATES CORRODED, RBL 53, BETWEEN STA 168-200. REMOVED 7 EA NUT PLATES TO FOM COMPOSITE REPAIR IAW SRM 51-30-2, FIG 19. REMOVED DAMAGE IAW ER/A 491541-14 AND SRM 51-70-1, PAR 3A, PG:4. APPLIED REPAIR SPLICES TYPE 120, BATCH 0001751564 IAW ER/A 4915414-14, SRM 51-70-1, PAR 3A PG:4 INST 7EA NUT PLATES PN MS 21059 BATCH 0001985950 IAW SRM 51-30-02, FIG 12, COMPLETED.

Part: SKIN — DENTED (PAX DOOR) · airframe 71,726 hrs · 65,746 cycles

PASSENGER AFT ENTRANCE DOOR STAIRWAY EXTERNAL SKIN WITH DENTAT STA YSD33 X 2.5. MEASURED DENT AND FOUND TO BE OUT OF LIMITS IAW SRM 53-04 CUTOUT DENTED AREA IAW SRM 52-05, FIG 3, PG 8. FABRICATED TREATED PRIMED AND INSTALLED REPAIR DOUBLER FILLER AND TAPERED SHIMS IAW SRM 52-05, FIG 3, PG:8. INSTALLED REPAIR IDENTIFICATION AROUND REPAIR AREA IAW PS900-5-1, NR 4 COMPLETED.

Part: FLOOR SUPPORT — CORRODED (STA 160-200) · airframe 71,726 hrs · 65,746 cycles

CABIN FLOOR SUPPORT ANGLE, RBL-44, STA 160 TO 200 HAS CORROSION. REMOVED CORROSION FLOOR SUPPORT ANGLE RBL 44, STA 160-200 IAW SRM 51-10-3 MEASURED MATERIAL ORIGINAL THICKNESS FOUND MATERIAL LOSS. OUT OF LIMITS IAW SRM 53-01, FIG 1 FABED FLOOR SUPPORT ANGLE WITH EXTRUSION IAW SRM 53-13-1, FIG: 11 LOCATED AND DRILLED HOLES IAW SRM 51-10-3, PG 40 FOR REMOVAL AND INSTALLATION OF SUPPORT ANGLE, COMPLETED AND INSPECTED.

Part: SKIN — DENTED (BS 1134) · airframe 71,726 hrs · 65,746 cycles

LWR FUSELAGE BS Y1134,BETWEEN LONGS. 24 RT AND 25 RT EXT SKIN WITH DENT. DAMAGE AT STA 1134, BETWEEN L24R TO L25R, L=1.5",D=0.025", & 0.2 FROM L24R, FOUND OUT OF LIMITS IAW SRM 53-04, FIG 38, SHEET 2, TABLE C, CONDITION 1B. REFORMED DENT TO ORIGINAL CONTOUR IAW SRM 53-04, FIG 38, FABED & INST REPAIR DOUBLER IAW SRM 53-04, FIG 38, COMPLETED.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,726 hrs · 65,746 cycles

PASSENGER CABIN FLOOR PANEL NR74-50 EDGE IS DAMAGED AND HAS CORROSION. REMOVED 2EA HAT CHANNELS FROM FLOOR WEB PANEL IAW SRM 51-30-2, FIGURE 20, FABED NEW WEB PANEL REF SRM 53-23-0, PAGE 8, FIG 5,TREATED AND PRIMED IAW SRM 51-10-3, PAGE 41, SRM 51-10-3 PAGE 31, INSTALLED HAT CHANNELS 2 EA IAW SRM 51-30-2, PAGE 26B, 51-20-0, PAGE 10. COMPLETED AND INSPECTED.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,726 hrs · 65,746 cycles

PASSENGER CABIN FLOOR PANEL NR 21-50 HAS CORROSION. REMOVED CORROSION IAW 51-10-3 FOUND TO BE OUT OF LIMITS IAW 57-01. FABED FLOOR PNL 21-50 IAW SRM 53-01. FABRICATED FLOOR PNL 21-50 IAW SRM 53-23-0 TREATED AND PRIMED IAW SRM 51-10-3. REASSEMBLED FLOOR PANEL 21-50 IAW SRM 51-03 (REMOVED & REINSTALLED HAT CHANNELS IAW SRM 51-03.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,726 hrs · 65,746 cycles

PASSENGER CABIN FLOOR PANEL NR 20-50 HAS CORROSION. REMOVED CORROSION AREAS ON CABIN FLOOR PANEL IAW SRM 51-10-3. MATERIAL ORIGINAL .025" IAW SRM 53-23-0, ITEM 18. MATERIAL LOSS .010" OUT LIMITS IAW SRM 53-01, PG 8, FIG 1. FABED PANEL .025" 2024T3 BATCH 0001172292 IAW SRM 53-23-0, PG6 & 51-60-0 FIG 1 & LOCATED AND DRILLED PANEL IAW SRM 51-10-4, PG1, TREATED AND PRIMED PASSENGER CABIN FLOOR PANEL NR 20-50 IAW SRM-51-10-3,PG 40&31, COMPLETED.

Part: FLOOR SUPPORT — CORRODED (BS 200 RBL 44) · airframe 71,726 hrs · 65,746 cycles

CABIN FLOOR SUPPORT ANGLE, STA 200 BETWEEN RBL-44 HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-3, PG:46, PAR 26. MATERIAL ORIGINAL THICKNESS .06 3 MATERIAL LOSS .024 FOUND OUT OF LIMITS IAW SRM 53-01, FIG 1 FABRICATED SUPPORT ANGLE WITH EXTRUSION PN 00-0210-3-0973, BATCH 0002026473 IAW SRM 53-13-1, FIG 11, SHEET 1-2, PG:25-26 LOCATED AND DRILLED HOLES IAW SRM 51-10-4 PG:1 TREATED AND PRIMED IAW SRM 51-10-3 INST FLOOR SUPPORT ANGLE IAW SRM 51-30-05, COMPLETED AND INSPECTED.

Part: FLOORBEAM — CORRODED (BS 200) · airframe 71,726 hrs · 65,746 cycles

CABIN FLOOR SUPPORT ANGLE, STA 200 BETWEEN BL-0 AND RBL-22 HAS CORROSION. REMOVED CORR FLOOR SUPPORT ANGLE STA 200 BETWEEN BL-0 TO RBL-22 IAW SRM 51-10-3 PG46, PARA 26, MATERIAL ORIGINAL THICKNESS .063, MATERIAL LOSS .024 FOUND MATERIAL OUT OF LIMITS IAW SRM 53-01, FIG 1, SHEET 3, PG8, FABED SUPPORT ANGLE WITH EXTRUSION IAW SRM 53-13-1 LOCATED AND DRILLED HOLES IAW SRM 51-10-4, PG 1, PARA 2, TREATED INSTALLED IAW SRM 51-30-5, COMPLRETED.

Part: SKIN — DENTED (BS 984 L17R) · airframe 71,726 hrs · 65,746 cycles

FUSELAGE DENT AT BS 984 AND LONGERON 17R WITHIN 1 FROM THE FRAME. MEASURED DENT AT EXT SKIN BS 984, L17R. OUT OF LIMITS IAW SRM 53-04, FIG 38 COLD FORM SKIN BACK AT SKIN BS 982-985, 1" ABOVE L17R IAW SRM 53-04, FIG 38, PAR AG 4B. FABRICATED DOUBLER IAW SRM 53-04, FIG 38. TREATED AND PRIMED DOUBLER IAW SRM 51-10-3, PG 40&31, INST DOUBLER IAW SRM 51-30-2, PG1. INSTALLED DOUBLER IAW SRM 53-04.

Part: FLOOR SUPPORT — CORRODED (BS 160-313 BL0) · airframe 71,726 hrs · 65,746 cycles

SUPPORT ANGLE HAS AREAS OF CORROSION BL-0 FROM STA 160 TO 313. REMOVED CORR IAW SRM 51-10-3, PG 46. OUT OF LIMITS IAW SRM 53-01 FIG 1, SHEET 3, PG 8, REM FLOOR SUPPORT ANGLE IAW SRM 51-30-5, FLOOR SUPPORT ANGLE IAW SRM 53-13-1, FIG 11, SHEET 1-2, PG25-26, LOCATED AND DRILLED HOLES IAW SRM 51-10-3PG1, PAR 2, TREATED, PRIMED IAW SRM 51-10-3 PG 40, PAR.21 & PG 31, PAR. 14. INST FLOOR SUPPORT ANGLE AT STA 160 TO 313,BL-0 IAW SRM 51-30-5, PG12, PAR 7.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

CABIN FLOOR PNL NR 37 HAS SURFACE CORROSION AT OTBD FASTENER HOLES. REMOVED CORROSION REF SRM 51-10-3. ORIG MATERIAL IS .020 REF SRM 53-23-0. MAX ALLOWABLE MATERIAL LOSS IS .004 MATERIAL LOSS .007, OUT OF LIMITS, REF SRM 53-01, PG8 FIG 1. REMOVED CHANNELS FROM WEB. FABRICATED WEB IAW SRM 53-23-0 PG7 FIG 4. TREATED IAW SRM 51-10-3, PG 40, PARA 21 & PRIMED SRM 51-10-3, PG31, PARA 14. INST HAT CHANNELS REF 51-30-2. INSTALLED IAW AMM 53-20-01-201-925A-A.

Part: WEB — CRACKED (BS 1100-1110) · airframe 71,726 hrs · 65,746 cycles

AFT CABIN LT STA 1100-1110, LBL 44-LBL 56 SUB FLOOR WEB IS CRACKED. FABRICATED 2 EA DOUBLERS AND 1 EA FILLER. INSTALLED 2 EA DOUBLERS AND FILLERS 1 EA AT AFT CABIN LT STA 1100-1110, LBL 44 TO LBL 56 IAW SRM 51-30-2 PG:1-2 AND 51-30-05 PG:1-3 INSTALLED FITTING AT STA 1108, LBL 59 PER SRM 51-30-1, PG:4 A TO 13 TOOL ID 01-187T DATE DUE 05/17/11, COMPLETED, INSPECTED.

Part: INTERCOSTAL — CRACKED (CARGO DOOR) · airframe 71,726 hrs · 65,746 cycles

FWD CARGO DOOR LOWER AFT INTERNAL INTERCOSTAL BEHIND DOOR STOP IS CRACKED. REMOVED AND REPLACED LWR AFT INTERNAL INTERCOSTAL P/N 5918036-52 1 AT FWD CARGO DOOR PER SRM 51-30-0.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 71,726 hrs · 65,746 cycles

PASSENGER CABIN FLOOR PANEL 62-50 EDGE IS CRACKED. REMOVED HAT CHANNELS FROM PASSENGER CABIN FLOOR PANEL 62-50 IAW SRM 53-05. FABRICATED, PRIMED AND TREATED WEB/ PANEL IAW SRM 53-23 AND 51-10-3, PG 26-28 AND REINSTALLED HAT CHANNEL ON PASSENGER CABIN FLOOR PANEL 62-50 IAW SRM 51-30-2.

Part: SKIN — CORRODED (FLOOR PANEL) · airframe 71,726 hrs · 65,746 cycles

CABIN FLOOR PANEL 91 OTBD ATTACH AREA TOP SKIN IS CORRODED. CORRECTED BY BOSS 280546, STA SAT 18APR11 ATA CORROSION ON PNL 91 OTBD ATTACH AREA IAW SRM 51-10-3, PGS 4 6-47, ORIGINAL MAT=.020 IAW SRM 53-01, PG 8. REMOVED FLOOR PANEL 91 IAW SRM53-23-0, PG 9, FIG 6. TREATED AND PRIMED IAW SRM 51-10-3 PG 31. INSTALLED 2 HAT CHANNELS TO PNL 91 IAW SRM 51-20-0.

Part: DOUBLER — DENTED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

DURING INSP FOUND DENT AT LT EXTERIOR FUSELAGE BS Y113 AND BETWEEN L19L, 20L. REMOVED EXIST DOUBLER BTW STA 97-STA 110, L18L -L19L IAW SRM 51-30-2. FABRICATED DOUBLER IAW SRM 53-04, INSTALLED IAW SRM 51-30-2. FABRICATED DOUBLER, FILLER, FINGER DOUBLER, IAW SRM 53-04, INSTALLED PARTS, CUT AND REMOVED STR STA 110-STA 140, L19L IAW SRM 51-30-2 AND SRM 53-02. FABRICATED HAT SECT AND SPLICE IAW SRM 53-02. SPLICED NEW SECT BTW STA 134-STA 148, L19L, IAW SRM 51-30-5.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

WINDOW MOUNT PLATING IS CRACKED (AFT LOWER AREA) STA 946 ABOVE LONGERON 15R. TRIM OUT DAMAGED AREA, HFEC PERFORMED, NO CRACKS NOTED AT TRIM OUT AREA, FABBED REPAIR PARTS & INSTALLED DOUBLER REPAIR ITEM -3 & SHIM REPAIR ITEM -9 & WASHER AT WINDOW MOUNT PLATING STA 94 6 ABOVE LONGERON 15R, IAD DC9 SRM 55-03, FIG 122, WINDOW PAN.

Part: MOUNT — CRACKED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

WINDOW MOUNT PLATING IS CRACKED STA 946 ABOVE L15R. TRIM OUT DAMAGED AREA, HFEC PERFORMED NO CRACKS NOTED AT TRIM OUT AREA. FABRICATED REPAIR PARTS AND INSTALLED DOUBLER REPAIR ITEM -3 AND SHIM REPAIR -9 AND WASHER AT WINDOW MOUNT PLATING STA 946 ABOVE LONGERON 15R IAW DC9 SRM 53-05, FIG 122, WINDOW RING PAN REPAIR.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 71,726 hrs · 65,746 cycles

PASSENGER CABIN FLOOR PANEL NR 68-50 EDGE IS DELAMINATED AND SUPPORT HONEYCOMB IS LOOSE, REPAIRED PER ER/A 492476-14. PANEL TO BE INSTALLED ON T/C 0590-4 020-8M.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 71,726 hrs · 65,746 cycles

PASSENGER CABIN FLOOR PANEL 31-50 IS CRACKED. REPAIRED DISCREPANT AREA ON PASSENGER CABIN FLOOR PANEL 31-50 IAW DC9-AMM 53-22-01-801-663A-A, PAGE 3 AND 4, PARA C. APPLIED REPAIR PLIES, DC9 SRM 51-70-2, PAGE 28, PARA 13, AND PRIMER, DC9 SRM 51-10-3, PAGE 31, PARA 14.

Part: CARGO TRACK — CORRODED (CARGO BAY) · airframe 71,726 hrs · 65,746 cycles

AFT CARGO BS 908 -1060, RT TRACK CORRODED AT SCREW REMOVED CORROSION AT SCREW IN LIMITS (RT TRACK FRO STA 908 TO STA 1059) OUT OF LIMITS FROM STA 1059 TO STA 1060, IAW DC9 SRM 53-01, FABRICATED REPAIR ANGLES IAW AMM DC9-A-53-10-19-801-663A-A. LOCATED AND DRILLED IAW AMM DC9-A-53-10-19-801-663A-A. FABRICATED TIE DOWN TRACK IAW AMM DC9-A-53-10-19-801-663 A-A, PG 1.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

AFT CARGO COMP AFT VERTICAL BULKHEAD WEB AFT FACING SIDE CORRODED AND CRACKED RBL-7 ABOVE S29R, FS 1167. REMOVED "L" ANGLE STIFFENERS LBL 27 TO RBL 27, FS 1167 IAW DC9 SRM 51-30-2, FABBED WEBS AND DOUBLERS IAW SRM 51-70-4. INSTALLED WEBS AND DOUBLERS REPAIRS AND ALL PARTS ACCESS FOR REPAIR, IAW SRM 51-30-5, INSTALLED "L" ANGLES AND PLASTIC STRAPS IAW SRM 51-30-5.

Part: FLOOR PANEL — PUNCTURED (CABIN) · airframe 71,716 hrs · 65,746 cycles

CABIN FLOOR PNL 96 TOP SKIN HAS PUNCTURE AND SCREW PULLED THRU. REMOVED MAIN CABIN PANEL NR 96 AND REMOVED DAMAGE FROM PNL PUNCTURE AND PLUGGED HOLE PER REF SRM DC9 53-01, PG 7, FIG 1, AND INSTALLED FLOOR PANEL NR 96 IAW AMM DC9-A-53-20-01-201-925A-A, PG 1-4 (FLOOR PANEL WAS REMOVED PER AMM DC9-A-53-20-01-201-925A.

Part: STRUCTURE — CORRODED (BS 180) · airframe 71,726 hrs · 65,746 cycles

CABIN METAL SUBFLOOR HAS UPPER SURFACE CORROSION AND IT EXTENDS UNDER LAP JOINT STA 180, RBL-48. CORROSION AT AREA ON SUBFLOOR, OUT OF LIMITS PER SRM 53-01, PG 8, CUT OUT DAMAGE PER SRM 51-70-4, FABRICATED REPAIR DOUBLER AND FILLERS, LOCATED AND DRILLED PARTS PER SRM 51-70-4, INSTALLED REPAIR ON PER SRM 51-30-2 AND SRM 51-70-4, INST EA FLOOR SUPPORT CHANNEL SUPPORT ON MAIN CABIN PER SRM 51-30-5 AND SRM 51-30-2.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 71,726 hrs · 65,746 cycles

CABIN FLOOR PNL 47 HAS A 20 INCH LONG CREASE IN THE UPPER SKIN-KK16, OUT OF LIMITS IAW SRM 53-05, PG 9. REMOVED 5 EA HAT CHANNELS FROM PNL IAW SRM 51-30-2, PG 24, 26, PARA 7. FABBED CABIN FLOOR PNL IAW SRM 53-23-0, PG 7, FIG 4, SRM 51-10-4, AND SRM 51-10-2 INSTALLED HAT CHANNELS ON FABBED FLOOR PNL IAW SRM 51-30-2, PG 24. INSTALLED PNL IAW AMM 53-20-01, PG 3-4. ACCOMP ER/A 491529-14MA.

Part: SKIN — DENTED (CARGO DOOR) · airframe 71,726 hrs · 65,746 cycles

FWD CARGO COMP DOOR, STA Y400, FROM UPPER PAN TO NR 1 BEAM, EXTERNAL SKIN WITH DENT OUT OF LIMITS PER SRM 53-04, PG 217, FIG 38. COLD FORMED SKIN BACK TO ORIG. CONTOUR PER SRM 53-04, PG 218H, FIG 38, TABLE C, NDT-NO CRACK NOTED. FABBED, TREATED, PRIMED AND INSTALLED INTERNAL DOUBLER REPAIR AT FWD CARGO DOOR STA Y400, PER SRM 53-04, PAGE 218H, FIG 38, VIEW "E".

Part: SKIN — DENTED (CARGO DOOR) · airframe 71,726 hrs · 65,746 cycles

FWD CARGO COMP DOOR, STA Y381, AT UPPER PAN LOCATION, EXTERNAL SKIN WITH DENT OUT OF LIMITS PER SRM 53-04, PG 217, FIG 38, CONDITION 1B. COLD FORMED SKIN BACK TO ORIG. CONTOUR PER SRM 53-04, PG 218H, FIG 38, TABLE "C", NDT-NO CRACKS NOTED. FABBED,TREATED, PRIMED, AND INSTALLED INTERNAL DOUBLER REPAIR AT FWD CARGO DOOR OUTER SKIN, STA Y381 PER SRM 53-04, PG 218H FIG 38, VIEW E.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 71,726 hrs · 65,746 cycles

LOWER FUSELAGE STA 579, BETWEEN LONG 29 RT AND L30 EXTERNAL SKIN WITH TOOL MARKS. TOOL MARKS ON FUSELAGE SKIN AT STA 579 BETWEEN LONGERON 29 RT TO 30 WAS TRIMMED OUT. A (1EA) .071" THK 2024-T3 CLAD SHT EXTERNAL REPAIR DOUBLER, (1EA) FILLER MADE FROM .063" THK 2024-T3 AND (6EA) .025" THK 2024-T3 INTERNAL REPAIR FINGER DOUBLER, WERE INSTALLED ON CUTOUT LOCATION PER COMPLIED ER/A 492114-14, REV ORIG.

Part: RECEPTACLE — FIRE (EXTERNAL POWER) · airframe 71,573 hrs · 65,617 cycles

AFTER ARRIVAL WITH EXTERNAL POWER CONNECTED, VISIBLE FLAMES WERE NOTICED COMING FROM THE EXTERNAL POWER PANEL. SMOKE ENTERED THE ACFT THROUGH DOOR L1. PASSENGERS WERE SAFELY EVACUATED THROUGH THE AFT BOARDING DOORS. THE TAILCONE AND ITS' SLIDE FAILED TO DEPLOY.

Part: CONNECTING ROD — FIRE (TAIL SLIDE) · airframe 71,573 hrs · 65,617 cycles

AFTER THE AIRCRAFT PARKED AT THE GATE, THE EXTERNAL ELECTRICAL CONNECTION CAUGHT FIRE. PASSENGERS WERE EVACUATED FROM THE AIRCRAFT. DURING THIS EVACUATION THE TAILCONE FAILED TO EJECT AND THE TAIL SLIDE DID NOT DEPLOY.

Part: DOOR — OUT OF RIG (RT MLG) · airframe 70,144 hrs · 64,386 cycles

RETURNED TO DEPARTURE DUE TO RT MLG INDICATION. FOUND DAMAGE AT RT MLG DOOR PROX SENSOR. MX FOUND RT DOOR OUT OF RIG. DOOR WAS REPLACED ON LOG 0238796 AND FUNCTIONAL CHECK OF DOOR CHECKS GOOD.

Part: LANDING GEAR — MALFUNCTIONED (LEFT) · airframe 70,143 hrs · 64,385 cycles

AFTER TAKEOFF WITH POSITIVE RATE OF CLIMB, LT GEAR UNSAFE LIGHT AND AMBER GEAR DOOR LIGHT ILLUMINATED AFTER GEAR HANDLE BROUGHT TO THE UP POSITION. CREW ACCOMPLISHED QRM PROCEDURES 14.17 AND 14.15 RETURNED TO MSP FOR LANDING. MX REMOVED GEAR DOORS JACKED ACFT AND PERFORMED FUNCTIONAL CHECK OF MLG IAW AMM 32-10-00-501-927 ALL PARAMETERS NORMAL. REPLACED RIGHT MLG DUE TO DAMAGE ON LANDING AND MADE REPAIRS TO DAMAGED DOUBLER FOR LT MLG DOOR. DOORS INSTALLED AND ROLLERS AND PROX SWITCHES ADJUSTED.

Part: FUSE — BLOWN (POWER SUPPLY) · airframe 69,295 hrs · 63,647 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING FOR THE CATWALK IN THE TAIL COMPARTMENT WAS INOPERATIVE. MAINTENANCE REPLACED THE FUSE IN THE POWER SUPPLY. OPERATIONAL CHECK WAS GOOD.

Part: BATTERY — DISCHARGED (CABIN) · airframe 69,135 hrs · 63,505 cycles

DURING LINE CHECK, FOUND THAT THE EMERGENCY PATHWAY LIGHTING FOR THE CATWALK IN THE TAIL COMPARTMENT AND THE EMERGENCY FLOOD LIGHT FOR THE AFT EVACUATION SLIDE WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES. OPERATIONAL CHECK WAS GOOD.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 68,946 hrs · 63,345 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING IN THE COCKPIT WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK & CHARGER AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 68,846 hrs · 63,269 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING FOR THE CATWALK IN THE TAIL COMPARTMENT AND THE AFT EMERGENCY HANDLE LIGHT WERE INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY LIGHT POWER SUPPLY AND OPERATIONALLY CHECKED THE SYSTEM.

Part: SKIN — DENTED (FUSELAGE) · airframe 74,571 hrs · 68,711 cycles

DENT TO FUSELAGE SKIN.

Part: PRESSURE SYSTEM — MALFUNCTIONED (CABIN) · airframe 68,749 hrs · 63,182 cycles

LEAVING FL300, THE RED "CABIN PRESS" WARNING LIGHT ILLUMINATED WITH THE CABIN ALTITUDE BETWEEN 12,000 AND 13,000 FT. FLIGHT WAS ALREADY CLEARED TO FL120 BUT CAPTAIN DIRECTED AN IMMEDIATE TO 10,000 AND EXECUTED THE RED BORDERED CHECK LIST. THE MASKS DID NOT DEPLOY. UPON COMPLETION OF THE RB CHECK LIST THE CABIN WAS STARTING TO DESCEND. AT FL170 THE CABIN SEEMED TO BE RE-PRESSURIZING, ALTHOUGH THE CABIN NEVER DID CATCH UP WITH THE DESCENT SCHEDULE. NO EMERGENCY WAS DECLARED, NO SPECIAL HANDLING REQUIRED, AND THERE WAS NO RAPID LOSS OF PRESSURIZATION. ONCE THE CABIN ALTITUDE REACHED 10,000 THE USE OF THE FLIGHT DECK OXYGEN WAS TERMINATED. THE FLIGHT LANDED WITHOUT FURTHER INCIDENT AT SCHEDULED DESTINATION.

Part: SKIN — DAMAGED (BS 292) · airframe 74,571 hrs · 68,711 cycles

FUSELAGE SKIN CRACKED AND DENTED AT BS 292 BETWEEN LONGERONS 22L & 23L. DAMAGED AREA REPAIRED IAW SRM 53-04-00, FIG 12B.

Part: SOCKET — INOPERATIVE (EMERGENCY LIGHT)

DURING LINE CHECK, MX FOUND THAT THE RT OVERWING EMERGENCY EXIT SIGNS WAS INOPERATIVE. MX REPLACED THE LIGHT SOCKET ASSY AND FUNCTIONALLY CHECKED IT. (K)

Part: SKIN — DENTED (BS 503) · airframe 74,571 hrs · 68,711 cycles

HFEC DENT BS 503 AND LONGERON 24LT. FUSELAGE SKIN 4 INCHES AFT OF BS 503 AND 2.5 INCHES ABOVE L24L SKIN HAS DENT L=1", W= 1", D= .015, FOUND TO BE IN LIMITS IAW SRM 53-04, FIG 38 COND. 1B. HFEC INSP. IAW NDTSPM 06-10-01.001, NO CRACKS NOTED AT DENTED AREA.

Part: SKIN — DENTED (BS 237) · airframe 74,571 hrs · 68,711 cycles

FUSELAGE EXTERIOR SKIN BS 237 BETWEEN 18LT AND 17LT, SKIN HAS AREA OF DENTS WHICH ARE OUT OF LIMITS DUE TO PROXIMITY. GAINED ACCESS. CUTOUT DAMAGED SECTION STA 212 TO 229 14" X 12.25" AND FROM STA 229 TO 237 12" X 9". FABRICATED AND INSTALLED 2EA DOUBLERS FROM 0.063 2024T3, 2EA FILLERS FROM 7075T6 .050, 2EA FINGER DOUBLERS .025 7075T6. THIS A CLASS I PERMANENT REPAIR WITH CARRY ON INSPECTIONS: THRESHOLD: 8,000 LANDINGS. REPETITIVE INTERVAL: 8,000 LANDINGS. INSP METHOD: EXTERNAL VISUAL. INSPECTED DECAL AND DISCOVERED MISSING. INSTALLED NEW DECAL AND EDGE SEALED IAW PS900-5-1 NR 4. OK TO CONTINUE ON MONTIOR IAW TOPP 30-10-70 PG13.

Part: WEB — CRACKED (LT NACELLE) · airframe 66,359 hrs · 60,985 cycles

DURING ENGINE CHANGE, FOUND CRACKS IN LT PYLON CLOSURE WEB AT STA YN 135. REPAIRED PER EA 98-211617.

Part: SHAFT — SHEARED (FUEL PUMP) · airframe 65,015 hrs · 59,810 cycles

DURING CRUISE FLIGHT ENGINE NR 2 FLAMED OUT. FLIGHT CREW SECURED ENGINE NR 2 AND LANDED AT DESTINATION. MAINTENANCE FOUND THE FUEL PUMP SHAFT SHEARED, REPLACED FUEL CONTROL UNIT AND FUEL PUMP.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 60,630 hrs · 55,878 cycles

DURING H-CHECK, FOUND CRACKED BULKHEAD STIFFENER AT BS 1168 RBL 60. REPAIRED PER EA 98-203198.

Part: RHEOSTAT — FAILED (COCKPIT) · airframe 59,799 hrs · 55,111 cycles

DURING CRUISE, THE CAPTAIN'S BRIEFCASE LIGHT BEGAN TO SMOKE AND EMIT ACRID FUMES INTO THE COCKPIT. CREW PULLED THE CIRCUIT BREAKER TO THE MAP AND BRIEFCASE LIGHT CIRCUIT AND THE SMOKE STOPPED. FLIGHT CONTINUED TO A NORMAL SAFE LANDING AT ROC. MAINTENANCE AT STL ON 27OCT REPLACED THE RHEOSTAT CONTROLLER TO THE LIGHT AND CLEARED THE MEL THAT ROC ASSIGNED. AIRCRAFT RETURNED TO SERVICE.

Part: PUMP — FAILED · airframe 56,117 hrs · 51,730 cycles

During climb out from MSP the left engine driven hydraulic pump failed. Crew performed COM procedures for pump failure and overweight landing. Flight returned and landed uneventfully back at MSP. Maintenance replaced the engine driven pump and filters. Aircraft has been returned to service.

Part: FRAME — CORRODED · corrosion level 2 · airframe 54,940 hrs · 50,726 cycles

During Mck in ATL the left side of the upper cusp sta 200 was found to be damaged by corrosion. Repaired per EA 98-188435.

Part: BULB — BURNED OUT (TAIL) · airframe 50,792 hrs · 46,990 cycles

DURING LINE MAINTENANCE INSPECTION, FOUND FORWARD EMERGENCYFLOOR PATH LIGHTING ON CATWALK AND ONE FLOOR PATH LIGHT AT SEAT ROW 6 INOPERATIVE. RELAMPED, CHECKED OK.

Part: ENGINE — FAILED (LEFT)

DURING TAKEOFF, THE LEFT ENGINE FAILED AT ABOUT 100 KNOTS AIRSPEED WITH AN ASSOCIATED EPR INDICATION OF 1.0, A DECREASE OF N1 AND N2 RPM SPEED, AND A NOTICEABLE ENGINE VIBRATION. TAKEOFF WAS ABORTED WITHOUT INCIDENT AND THE FLIGHT RETURNED TO BLOCKS. MAINTENANCE REPLACED THE LEFT ENGINE. OPERATIONAL CHECK OK.

Part: BATTERY — DISCHARGED (CABIN)

FLIGHT ATTENDANT REPORTED LOWER EMERGENCY FLASHLIGHT NOT BLINKING AT ENTRY DOOR 1L. MAINTENANCE REPLACED BATTERY PACK, OPERATIONAL CHECK NORMAL.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

DURING LINE CHECK, FOUND THE FIRST SECTION OF CABIN EMERGENCY PROXIMITY LIGHTING INOPERATIVE. MAINTENANCE REPLACED POWER SUPPLY AND BATTERY, OPERATIONAL CHECK NORMAL.

Part: OIL FILTER — DIRTY (RT ENGINE)

DURING CLIMB, THE RIGHT ENGINE OIL STRAINER CLOG LIGHT ILLUMINATED. CREW REDUCED POWER ON THE RIGHT ENGINE AND THE LIGHT EXTINGUISHED. THE AIRCRAFT DIVERTED TO MKE AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED THE RIGHT ENGINE MAIN OIL FILTER.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

DURING LINE MAINTENANCE INSPECTION, FOUND OVERHEAD EMERGENCY LIGHTS AT ROWS 1, 2, 3, AND 5 INOPERATIVE. REPLACED POWER SUPPLY, OPERATIONAL CHECK NORMAL.

Part: PT7 LINE — CRACKED (LT ENGINE)

AS TAKEOFF POWER WAS APPLIED, THE LEFT ENGINE WOULD NOT REACH TARGET EPR INDICATION. CREW ABORTED TAKEOFF AND RETURNED TO THE GATE. MAINTENANCE REPLACED CRACKED PT7 LINE ON THE LEFT ENGINE, OPERATIONAL CHECK OK.

Part: FRAME — CRACKED (BS 1316)

DURING L-CHECK, FOUND A CRACK IN THE 1316 CANTED FRAME BELOW THE VENTRAL STAIR ACTUATOR CYLINDER. REPAIRED PER E A 98-153401.

Part: PRESS PANEL — CRACKED (BS 83)

DURING L-CHECK, FOUND CRACK IN NOSE LANDING GEAR WHEEL WELL HORIZONTAL PRESSURE PANEL AT RIGHT FRAME ATTACH FITTING FS 83. REPAIRED PER EA 98-153390.

Part: BATTERY — DISCHARGED (CABIN)

DURING LINE CHECK, FOUND EMERGENCY TRACK LIGHTING INOPERATIVE ROWS 1 THRU 8. REPLACED BATTERY, OPERATIONAL CHECK OK.

Part: PT7 LINE — FAILED (RT ENGINE)

AS TAKEOFF POWER WAS APPLIED, THE RIGHT ENGINE WOULD NOT REACH TARGET EPR. CREW ABORTED TAKEOFF AND RETURNED TO THE GATE. MAINTENANCE REPLACED THE PT7 LINE, OPERATIONAL CHECK OK.

Part: BATTERY PACK — DISCHARGED (CABIN)

DURING LINE CHECK, FOUND FLOOR ESCAPEMENT LIGHTS INOPERATIVE AT ROW 16 TO 22. REPLACED BATTERY PACK AND POWER SUPPLY, OPERATIONAL CHECK OK.

Part: SKIN — CRACKED (FS 1124)

DURING H-CHECK, FOUND TWO CRACKS, 1.25 INCH AND .25 INCH IN THE FUSELAGE SKIN AT FS 1124 BELOW LONGERON 14L. REPAIRED SKIN (P/N 5911427-3) PER EA 98-109449.

Part: EEL WIRE — SHORTED (CABIN)

DURING LINE CHECK, FOUND THIRD SECTION OF EMERGENCY PROXIMITY LIGHTS INOPERATIVE. FOUND POWER SUPPLY BURNED DUE TO A SHORTED WIRE. INSULATED WIRE AND REPLACED POWER SUPPLY AND BATTERY. OPERATIONAL CHECK GOOD.

Part: EEL POWER SUPPLY — INOPERATIVE (CABIN)

DURING LINE MAINTENANCE INSPECTION, FOUND ONE SECTION OF CABIN EMERGENCY LIGHTS INOPERATIVE. REPLACED THE POWER SUPPLY AND BATTERY, OPERATIONAL CHECK OK.

Part: BOLT — SHEARED (RT ENG MOUNT)

DURING LINE CHECK, FOUND RIGHT ENGINE FORWARD MOUNT AFT SIDE UPPER AND LOWER STRUTS LOOSE. FURTHER INVESTIGATION REVEALED A SHEARED UPPER BOLT. REPLACED BOLT PER MM 71-20-03.