N532US

Part: DOOR FRAME — CRACKED (L2 DOOR WAY) · airframe 77,481 hrs · 33,391 cycles

L2 DOOR, UPPER HINGE CUTOUT, FRAME IS CRACKED. R/I DOOR, REPAIRED AND INSPECTED IAW SRM.

Part: MODULE — LEAKING (FLAP/SLATS) · airframe 75,919 hrs · 32,397 cycles

LOST LT HYDRAULIC SYSTEM, DECLARED EMERGENCYP AND PERFORMED AN ALTERNATE GEAR EXTENSION IAW QRH. FOUND AND REPLACED LEAKING FLAP/SLAT DEPRESSURIZATION MODULE. ALSO, REPLACED LT ENGINE DRIVEN HYD PUMP DUE TO NO PRESSURE OUTPUT. LEAK AND OPS CK'S OK.

Part: CONTROLLER — FAILED (WINDOW HEAT) · airframe 74,648 hrs · 31,654 cycles

DUE TO R1 WINDOW SHATTERED. REPLACED WINDOW AND WINDOW HEAT CONTROLLER. OPS CHECKED OK.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 72,346 hrs · 30,132 cycles

EMERGENCY FLOOR PATH LIGHTING AT ROW 33FED THRU 40FED INOPERATIVE. INSTALLED SERVICEABLE EMERGENCY LIGHTS POWER SUPPLY IAW AMM 33-51-00. OPS CHECKS NORMALLY. OK FOR SERVICE.

Part: BOTTLE — LOW PRESSURE (ESCAPE SLIDE) · airframe 72,303 hrs · 30,111 cycles

R4 DOOR SLIDE INFLATOR BOTTLE PRESSURE GAUGE READS BELOW GREEN BAND. REMOVED AND INSTALLED SERVICABLE ESCAPE SLIDE ASSY IAW 2566-9001-4R. CHECKED GOOD.

Part: FUSE — BLOWN (CABIN) · airframe 1,641 hrs · 935 cycles

DURING MAINTENANCE LINE INSPECTION, LEFT AISLE EMERGENCY LIGHT L44 AND L45 WHERE FOUND INOPERATIVE. MAINTENANCE REPLACED POWER SUPPLY FUSES PER B757 AMM 33-51-07. SYSTEM OPERATION NORMAL AFTER FUSES WERE REPLACED.

Part: FLANGE — LEAKING (CENTER WING) · airframe 70,316 hrs · 28,961 cycles

DURING APPROACH PASSING 1200 FEET A STRONG SMELL OF JET FUEL BECAME APPARENT. LASTED STRONG ENOUGH THRU TOUCHDOWN AND DISSIPATED BY TAXI SPEED. FLIGHT CREW FILLED OUT AIRCRAFT FUME QUESTIONNAIRE. ONCE ON GROUND MAINTENANCE FOUND FUEL LEAK IN THE LEFT ECS BAY AT FUEL SUMP DRAIN VALVE. THE LEFT CENTER SUMP DRAIN FLANGE WAS REPLACED. LEAK CHECK WAS ACCOMPLISHED PER B757 AMM 28-11-02-0401-926A-A. ALL CHECKS GOOD.

Part: GATE — CORRODED (R4 DOOR) · airframe 68,796 hrs · 28,091 cycles

(MZAR) R-4 DOOR LOWER GATE CORRODED. REMOVED R4 DOOR LOWER GATE & REPLACED WITH NEW ONE, MATERIAL R & R LOWER SEAL & REMOVED & REINSTALLED 3EA ATTACH FITTINGS IAW SRM 52-11-38. PERFORMED & TESTED GIRT BAR MECHANISM IAW AMM 52-11-25 & FOUND GOOD. REQUIRED INSP COMPLETED BY SAN NR178354, STAMP NR 5. DAMAGE DIM: L=.750" W=.500" D=.125".

Part: SKIN — DAMAGED (BS 500 S27R) · airframe 68,796 hrs · 28,091 cycles

ERA 487447-14, SECTION I, ISSUED FOR FUSELAGE SKIN REPAIR AT BS 500, S-27R. SECTION I ACCOMPLISHED DURING M-CHECK. FOLLOW ON ACTION IS REQUIRED. ACCOMPLISH SECTION II INSP WITHIN 24 MONTHS FROM 10JAN11.

Part: FLOORBEAM — CORRODED (BS 345) · corrosion level 2 · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK FOUND FLOORBEAM AT STA 345, BET BL 0 TO RBL 60 UPPER CHORD HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-02, FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51, FIG 101, DETAIL IV. R & R UPPER CHORD IAW SRM 53-00-51, REPAIR 3 AND SRM 51-40-05. FABRICATED ANGLES AND STRAPS IAW SRM 53-00-51, REPAIR 3. REMOVED UPPER CHORD INTERCOSTAL AT STA 324 TO STA 345 RBL 24 TO GET ACCESS AND REINSTALLED IAW SRM 51-40-02. REMOVED 2EA PULLY 345 RBL 14 AND RBL29 AND REINSTALLED IAW SRM 51-40-02. RECIEVED 2 EA NEW ANGLES FABRICATED IAW DWG 141N5150 INSTALLED IAW SRM 51-40-02 & 51-40-05.

Part: SUPPORT — CORRODED (BS 900 S26L/R) · corrosion level 2 · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK, FOUND LOWER FUSELAGE FAIRING SUPPORT AT STA 900 BETWEEN STR 26L TO STR 26R AND 6 O`CLOCK HAS CORROSION. BLENDED-OUT CORRODED AREAS IAW SRM 51-10-01, DIMENSIONS OF BLENDED-OUT AREAS WHICH WERE FOUND TO BE OUT OF LIMITS IAW SRM 53-00-71 FIG 101. ACCOMPLISHED A HEFC INSP TO BLEND OUT AREAS IAW NTM 51-00-19, PT6, NO CRACK INDICATION NOTED. REPAIRED THE 3 OUT OF LIMITS AREAS IAW NWA REPAIR DOC 09A51-37496.

Part: SILL — CORRODED (BS 1640-1681) · corrosion level 2 · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK FOUND FT AFT CABIN 4L DOOR SILL HAS CORROSION BS 1640-1681 LBL54" TOP SURFACE & LWR SURFACE AT BS 1640. CLEANED OUT CORRODED AREA IAW SRM 51-10-02, DIMENSIONS L=2.6 W=2.0 D=.0205 IAW SRM 53-60-15 OUT OF LIMITS, REMOVED DOOR SILL IAW SRM 51-40-02. LOCATED AND DRILLED IAW SRM 51-40-05, INSTALLED P/NDA-146N5246-7-12 AND DA-146N5246-5-12 IAW SRM 51-40-02. INSTALLED 2EA L-4 DOOR SILL SUPPORT IAW SRM 51-40-02, PAINTED AREA IAW AMM 51-21-00.

Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK FOUND THRESHOLD PLATE SUPPORT ANGLE 2 EA AT BS 1640 & 1681 LBL 54 INCHES HAS CORROSION. REMOVED PLATE SUPPORT ANGLE IAW SRM 51-40-02, FABRICATED PLATE SUPPORT ANGLE AND PLATED ANGLE SUPPORT 1 EA LOCATED AND DRILLED IAW SRM 51-40-05. TREATED AND PRIMED IAW SRM 51-20-01, INSTALLED PLATE SUPPORT ANGLE AFT AND FWD IAW SRM 51-40-02.

Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,796 hrs · 28,091 cycles

REMOVED CORROSION FROM SEAT TRACK SUPPORT IAW SRM 51-10-02 FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51 FIG 101. REMOVED SEAT TRACK SUPPORT IAW SRM 51-40-02, RBL 45 STA 365-418. FABRICATED NEW SEAT TRACK TREATED, PRIMED APPLIED TOPCOAT, LOCATED AND DRILLED IAW SRM 51-20-01 AND 51-40-05. REMOVED SEAT TRACK CROWN IAW SRM 51-40-02. FABRICATED SEAT TRACK LOCATED AND DRILLED, TREATED PRIMED AND INSTALLED SEAT TRACK CROWN IAW SRM 51-20-01, 51-40-05 AND51-40-02. APPLIED TOPCOAT IAW SRM 51-20-01

Part: FLOORBEAM — CORRODED (BS 1640) · corrosion level 2 · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK, FOUND AFT CABIN FLOORBEAM BS 1640 BBL "0" TO RBL 54" CORRODED AT UPPER SKIN & LOWER SKIN SURFACE AROUND FASTENER HOLE. BLENDED OUT AREAS BEAM 1640 BBL 0 TO RBL 54 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-40-51, FIG 101, SHEET 1 AND SHEET 3, DETAIL III. REMOVED ANGLE BRACKET FOR ACCESS AT STA 1640, LBL 2 IAW SRM 51-40-02. REMOVED T-CHORD AND SPLICE PLATES AT STA 1640, LBL 15 TO RBL 56 IAW SRM 51-40-02, LOCATED & DRILLED AND FINISHED FAB OF NEW T-CHORD IAW SRM 53-00-51 REPAIR I, FIG 201. TREATED AND PRIMED PARTS OF REPAIR IAW SRM 51-20-01AND PAINTED PARTS IAW AMM 51-21-00. INSTALLED NEW T-CHORD AND ANGLE BRACKETS IAW SRM 53-40-51 AND SRM 51-40-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK FOUND AFT CABIN FLOORBEAM CORRODED AT BS 1640 LBL 54 00-51 FIG 101. REMOVED STIFFENERS AND UPPER CHORD IAW SRM 51-40 02. RECEIVED EXTRUSION IAW SRP B757-A-53-01-07-801-863A-A AND SRM 53-00-51 FIG 201 PARTS SRM 53-00-51. LOCATED AND DRILLED ALL PARTS IAW SRM 53-00-51 AND 51-40-05. TREATED AND PRIMED IAW SRM 51-20-01, AND PAINTED ALL PARTS IAW SRM 51-20-00.INSTALLED NEW UPPER CHORD AND ATTACHING PARTS IAW SRM 53-00-51 AND SRM 51-40-02.

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK FOUND L4 DOOR LOWER SILL WEB CORRODED AT STA 1640. REMOVED L-4 DOOR SILL WEB AND 5 (EACH) STIFFENERS IAW SRM 51-40-02. FABRICATED NEW L-4 DOOR SILL WEB IAW SRM 51-40-05. TREATED, PRIMED, AND APPLIED TOPCOAT IAW SRM 51-20-01 AND AMM 51-21-10. INSTALLED DOOR SILL WEB AND 5 EA STIFFENERS IAW SRM 51-40-02.

Part: WEB — PUNCTURED (APU BAY) · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK, FOUND APU COMPARTMENT UPPER SURFACE SKIN AT STA 1914 AND 17" LT FROM CTR WAS PUNCTURED. REMOVED DAMAGED SKIN, FABRICATED REPAIR DOUBLER . ALL WORK PERFORMED IAW SRM 51-70-10.

Part: SKIN — DENTED (BS 1896-1918) · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK FOUND APU COMPT EXTERNAL SKIN DENTED BETWEEN STA 1896.20 & STA 1918.9, BL 25.0. CHECKED DENT LIMITS, SANDED DAMAGED AREA, POTTED DENT, FABRICATED REPAIR DOUBLER, BONDED REPAIR DOUBLER,CLEANED AREA APPLIED SEALANT AROUND DOUBLER AND PRIMED.ALL WORK PERFORMED IAW SRM 53-80-01, SRM 51-70-10. FABBED REPAIR DOUBLER 3"D FROM 2024 T3 IAW SRM 53-80-01 & 51-70-10 REP NR 2 PRIMED REPAIR IAW SRM 51 -70-10.

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK FOUND AFT CBN 4R SILL HAS CORROSION BS 1640-1681 RBL 54 BLENDED CORROSION AND FOUND TO BE OUT OF LIMITS IAW SRM 53-60-15 BS 1640 TO 1660. REMOVED 2 EA SUPPORTS IAW SRM 51-40-02. FABRICATED 2 EA SUPPORTS TREATED, PRIMED & PAINTED DOOR SILLS IAW SRM 51-20-01 AND AMM 51-21-00. LOCATED AND DRILLED 2 EA DOOR SILLS IAW SRM 51-40-05. INSTALLED 2 EA DOOR SILLS ON AFT R-4 CABIN DOOR BS 1640-1681 RBL 54 IAW SRM 51-40-02.

Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,796 hrs · 28,091 cycles

DURING “M” CHECK FOUND SEAT TRACK SUPPORT BET STA 365 & 377 RBL 24 HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-02 FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51 FIG 101, FABRICATED NEW SEAT TRACK SUPPORT IAW TRAVELLER T10/859329 P/N DA-141N5131-4-20.TREATED AND PRIMEDPER SRM 51-20-01 AND PAINTED PER AMM 51-21-00.REMOVED AND REINSTALLED BOX BEAM PER SRM 51-40-02.

Part: FLOORBEAM — CORRODED (BS 365) · corrosion level 2 · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK, FOUND FLOORBEAM STA 365 UPPER CORD FROM BL0 TO RBL 60 HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-02 DIM. L=44" W=2" D=.065" ORIG MAT .130" FOUND TO BE OUT OF LIMITS IAW SRM 53-10-51, REMOVED FLOORBEAM REPAIR IAW SRM 51-40-02 FABRICATED NEW REPAIR UPPERCORD FROM MAT BAC 1505-100880, 2EA STRAPS FROM MAT 7075T6 .063C & 7075T6 .071C. LOCATED AND DRILLED IAW SRN53-40-05 & 53-00-51 REPAIR 3, TREATED AND PRIMED THE REPAIR PARTS IAW SRM 51-20-01PAINTED REPAIR PARTS IAW AMM 51-20-00 INSTALLED NEW REPAIR UPPER CORD IAW SRM 51-40-02 & 53-00-51 REPAIR 3.

Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,796 hrs · 28,091 cycles

DURING L-CHECK FOUND CORROSION ON SEAT TRACK SUPPORT AT BS 324 TO BS 418 RBL 0. REPAIRED PER SRM 51-40-05, SRM 51-21-02, SRM 51-120-01.

Part: SKIN — DAMAGED (BS 1452-1453) · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK SCRIBE LINE DAMAGE FOUND AT S-20R LAP SPLICE FROM BS 1452.062 TO BS 1453.687, WITH (D MIN) =.031" AND (D MAX) =.219" N/R 100/12. TASK ELAPSE TIME HRS: 0000.0 RII: N SCRIBE LINE DAMAGE FOUND AT S-20R LAPSPLICE FROM BS 1452.062TO BS 1453.687, WITH (D_MIN) =.031" AND (D_MAX) =.219". THE FOLLOWING NDT INSP TO DETECT CRACKS WERE ACCOMPLISHED: UT PHASED ARRAY INSP IAW 53-00-02 PT 4 AND A DETAILED INSP AT S-20R FROM BS 1440 TO BS 1460. LOCAL SURFACE HFEC INSP IAW 51-00-19 PT 6 OF SCRIBE LINE. FOLLOW UP ACTION IS REQUIRED. ACCOMPLISH REPETITIVE FOLLOW-UP INSPECTION IAW SA5331-01215-03 AT 1500 CYCLE INTERVALS. ACCOMPLISH PERMANENT REPAIR WITHIN 50,000 TOTAL FLIGHT CYCLES.

Part: SKIN — DAMAGED (BS 1498-1605) · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK SCRIBE LINE DAMAGE FOUND AT S-14R LAP SPLICE FROM BS 1598.75TO BS 1605.812, WITH (D MIN)=.156" AND (D MAX)=.313" N/R 200/10. DFRD BY BROWN III (D_MIN)=.156" AND (D_MAX)=.313".FOLLOWING NDT INSP TO DETECT CRACKS WERE ACCOMPLISHED: LOCAL SURFACE HFEC INSP IAW 51-00-19, PT 6 ND A DETAILED AND A DETAILED INSP OF SCRIBE LINE. FOLLOW-UP ACTION IS ACCOMPLISH REPETITIVE FOLLOW-UP INSP IAW SA5331-01215-03 AT1500 CYCLE INTERVALS. PERMANENT REPAIR WITHIN 50,000 TOTAL FLIGHT CYCLES.

Part: SKIN — DAMAGED (BS 1598-1605) · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK SCRIBE LINE DAMAGE FOUND AT S-14R LAP SPLICE FROM BS 1598.75 TO BS 1605.812, WITH (D MIN)=.156" AND (D MAX)=.313"N/R 200/10. SCRIBE LINE DAMAGE FOUND AT S-14R LAP SPLICE FROM BS 1598.750TO BS 1605.812, WITH (D MIN)=.156" AND (D MAX)=.313". THE FOLLOWING NDT INSPECTIONS TO DETECT CRACKS WERE ACCOMPLISHED: LOCAL SURFACE HFEC INSP IAW 51-00-19, PT 6 AND A DETAILED INSPECTION OF SCRIBE LINE. FOLLOW-UP ACTION IS ACCOMPLISH REPETITIVE FOLLOW-UP INSP IAW SA5331-01215-03 AT 1500 CYCLE INTERVALS. ACCOMPLISH PERMANENT REPAIR WITHIN 50,000 TOTAL FLIGHT CYCLES.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,796 hrs · 28,091 cycles

DURING M-CHECK FOUND CORROSION ON UPPER CHORD OF FLOORBEAM AT BS 377 LBL 60. REPAIRED PER SRM 53-00-51 FIGURE 201, SRM 51-40-05, SRM 51-20-01 & SRM 51-40-02.

Part: SKIN — CRACKED (NR 2 NACELLE) · airframe 35,421 hrs · 13,862 cycles

DURING "M" CHECK, FOUND CRACK IN NR 2 PYLON SKIN AT NAC STA 132 RT. REPAIRED PER EA 56-212921.

Part: OVEN — SMOKE (GALLEY)

THE FIRST CLASS (G-1) OVEN BEGAN TO RELEASE SMOKE AFTER BEING TURNED ON. AN ELECTRICAL SMELL WAS NOTICED IN THE COCKPIT AND BY PASSENGERS. THE SMELL DISSIPATED WHEN THE OVEN WAS TURNED OFF. MAINTENANCE INSPECTED THE AREA AND FOUND NO EVIDENCE OF FIRE OR SMOKE DAMAGE. REMOVED AND REPLACED THE OVEN, OPERATIONALLY CHECKED AND RETURNED TO SERVICE.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 52,375 hrs · 21,645 cycles

DURING "H" CHECK FOUND CRACK IN FLOORBEAM AT BS 700 LBL 25. REPAIRED PER EA 55-198777.

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 46,438 hrs · 19,227 cycles

AFTER TAKEOFF WHEN RETRACTING GEAR, CREW RECEIVED LEFT MAIN GEAR DISAGREE AND GEAR DOOR MESSAGE. CREW CYCLED GEAR AND SAME INDICATION REMAINED. FLIGHT RETURNED TO DTW AND COMPLETED AN UNEVENTFUL LANDING. DTW MAINTENANCE PERFORMED OPERATIONAL CHECK PER MM AND COMPLETED 12 NORMAL GEAR SWINGS. MAINTENANCE CALLED AIRCRAFT OK FOR SERVICE. NWA MAINTENANCE CONTROL FOLLOWED UP THIS EVENT WITH LOG TO CHANGE GEAR SEQUENCE VALVE AND THE GEAR DOWNLOCK ACTUATOR AS A PRECAUTIONARY MEASURE.

Part: SLIDE — FAILED (CABIN) · airframe 42,336 hrs · 17,667 cycles

DURING SLIDE SHOP TEST, INFLATABLE SUB ASSEMBLY RUPTURED DURING FLAT FIRE PROCEDURE AT NORMAL OPERATING PRESSURE. INFLATABLE SEAMS FAILED AT UPPER TUBE LEFT AND RIGHT. NEW INFLATABLE SUB ASSEMBLY WAS INSTALLED.

Part: ENGINE — FAILED (NR 1)

DURING CRUISE FLIGHT, NR 1 ENGINE OIL PRESSURE AND QUANTITY DETERIORATED. AIRCRAFT DIVERTED TO GEG AND PERFORMED AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED ENGINE FOR OIL LEAKS, NONE FOUND. AIRCRAFT MAINTENANCE FERRIED TO SEA AND REPLACED NR 1 ENGINE.

Part: BATTERY PACK — DISCHARGED (CABIN)

DURING PREFLIGHT, FOUND RIGHT OVERHEAD EMERGENCY LIGHT INOPERATIVE. REPLACED BATTERY PACK AND CHARGER, OPERATIONAL CHECK OK.

Part: OVEN — DIRTY (AFT GALLEY)

DURING CLIMB WHILE PREPARING MEALS, FLIGHT ATTENDANT REPORTED SMOKE COMING FROM AFT GALLEY LT OVEN. FIRE BOTTLE WAS USED TO EXTINGUISH SMOKE. DECLARED AN EMERGENCY, RETURNED TO DTW, LANDING WAS UNEVENTFUL. UPON AIRCRAFT COMING TO A STOP ON TAXIWAY, CREW INITIATED AN EMERG EVAC ENGINES AND APU WERE SHUTDOWN PER EMERG PROC AND FIRE EXTINGUISHING AGENTS DISCHARGED. AFTER FIRE DEP, RELEASED AIRCRAFT, MAINT BEGAN INVESTIGATION. SMOKE WAS DUE TO HAMBURGER GREASE DURING MEAL PREPARATION. REPLACED AFT GALLEY OVENS AND CONTROLLERS. DURING EMERGENCY EVACUATION, DOORS 1R, 2L AND 4R DID NOT DEPLOY, INVESTIGATION CONTINUES.

Part: SKIN — DAMAGED (FS 660-670)

DURING PERIODIC CHECK, THE FUSELAGE BELLY SKIN BETWEEN FS 660 - 670 AROUND STRINGER 27R WAS FOUND WITH TYPICAL NICK AND GOUGE DAMAGE CAUSED BY CARGO NETS. INSTALLED REPAIR DOUBLER PER SRM 53-00-01 AND NWA EA 55-93840.

Part: SKIN — DAMAGED (FS 1355-1410)

DURING PERIODIC CHECK, THE FUSELAGE BELLY SKIN BETWEEN FS 1355 - 1410, STR 24L - 26L WAS FOUND WITH NICKS AND GOUGES CAUSED BY CARGO NETS. REMOVED DAMAGED SKIN AND INSTALLED REPAIR PER SRM 53-00-01, FIG 205 AND NWA EA 55-93836.

Part: SKIN — DAMAGED (FS 1340-1360)

DURING PERIODIC CHECK, NUMEROUS NICKS AND SCRATCHES WERE FOUND ON THE FUSELAGE BELLY SKIN BETWEEN FS 1340 - 1360, STR 26R. DAMAGE WAS CAUSED BY CARGO NETS. INSTALLED REPAIR DOUBLER PER SRM 53-00-01, FIG 204 AND NWA EA 55-93835.