N779NC

Part: CONNECTOR — UNSECURE (EMERGENCY LIGHT) · airframe 74,033 hrs · 69,373 cycles

EMERGENCY PATHWAY LIGHT INOPERATIVE AT SEAT 6R. SECURED CONNECTOR UNDER SEAT. CHECKED GOOD.

Part: SLIDE — UNSERVICEABLE (R1 DOOR) · airframe 73,661 hrs · 68,954 cycles

DURING LINE CHECK, MAINTENANCE FOUND THE 1R DOOR SLIDE PRESSURE READING ZERO. MAINTENANCE REPLACE THE DOOR SLIDE AND RETURNED THE AIRCRAFT TO SERVICE.

Part: FASTENER — LOOSE (TAIL CONE) · airframe 73,312 hrs · 68,537 cycles

DURING LINE CHECK, MAINTENANCE FOUND THE LOCK FASTENER LOOSE ON THE TAIL CONE DOOR HATCH. MAINTENANCE REPLACED THE RECEPTICAL, SECURED THE FASTENER AND RETURNED THE AIRCRAFT TO SERVICE.

Part: BATTERY — DISCHARGED (CABIN) · airframe 3,235 hrs · 2,921 cycles

EMERGENCY EGRESS AISLE LIGHTS INOP AT ROWS 19, 20, 21, 22 AND 2R LOWER EXIT SIGN. REPLACED POWER SUPPLY BATTERIES, CHECKS OK.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 3,170 hrs · 2,853 cycles

EMERGENCY EGRESS AISLE LIGHTS INOP AT ROWS 13, 14 AND 16. REPLACED AISLE LIGHT ASSEMBLY, CHECKS OK.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 2,985 hrs · 2,665 cycles

DURING EMERGENCY LIGHT TEST FOUND PATH LIGHT ROW 9 TO ROW 13 AND FORWARD OVER WING EXIT SIGN INOP. THE BATTERY PACK AND FUSE WERE REPLACED AND TESTS OK.

Part: CONNECTOR — DISCONNECTED (CABIN) · airframe 2,804 hrs · 2,492 cycles

DURING SERVICE CHECK, MAINTENANCE FOUND EMERGENCY ESCAPE PATH LIGHTING AT ROW 17 INOPERATIVE. MAINTENANCE RECONNECTED THE ROW 17 EMERGENCY ESCAPE PATH LIGHT WIRE CONNECTOR. OPERATIONAL CHECK WAS NORMAL.

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 71,372 hrs · 66,618 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY EXIT IDENTIFIER AT THE MAIN CABIN DOOR WAS INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY LIGHT POWER SUPPLY AND OPERATIONALLY CHECKED THE SYSTEM.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,333 hrs · 66,584 cycles

CORROSION ON CABIN FLOOR PNL 21. REMOVED CORROSION IAW DC9 SRM 51-10-3 FIG 1. AFTER BLEND THICKNESS IS .005, OUT OF LIMITS IAW DC9 SRM 53-01. CUT OUT DAMAGE IAW DC9 SRM 53-01. (1) HFEC INSP IAW NDT SPM 06-10-01.001. NO CRACKS NOTED A2700. FABRICATED AND INSTALLED REPAIR FROM 7075-T6 .032 IAW DC9 SRM 53-01 AND ER/A 490833-14. INSTALLED 3EA ID TAGS DPS 900-5-1, NR 4 P-102 28 MAR 11. REQUIRED INSPECTION COMPLETED BY Q-942 451310.

Part: DOOR FRAME — DAMAGED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN PASSENGER CABIN FWD SERVICE DOOR JAMB REPAIR 53-05 FIG 55 DOOR SPLICE -43 SPLICE HOLES FALL IN RADIUS. FAB -43 SPLICE FROM MAT .071 2024-0. HEAT TREATED TO .071 2024-T42 ON PEMCO TRAVELER 2469NO1540. DRILLED AND INSTALLED -43 SPLICE IAW DC9 ERA 490833-14 116441 475747 01 APR 11 P-138.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN CUSP ANGLE UNDER R-1 DOOR PAN HAS CORROSION. LOSS OUT OF LIMITS IAW DC-9 SRM 51-10-3. REMOVED CUSP ANGLE FROM STA 164-227 RBL 59. LOCATED AND DRILLED NEW ANGLE AND INSTALLED ANGLE IAW DC-9 SRM 53-05 FIG 55 WEIGHT OF REPAIR PARTS IS 7.8 INSTALLED ID TAG IAW DPS 900-5-1 NR 4.6.

Part: CUSP WEB — DAMAGED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN PASSENGER CABIN R1 DOOR PAN REQUIRE CUT FOR R1 DOOR CUSP REPAIR. CUT OUT DOOR PAN IAW DC-9 SRM 53-05 FIG 55. RECEIVED NEW PAN PN 5912492-1. LOCATED, DRILLED AND INSTALLED NEW PAN IAW DC-9 SRM 53-05 FIG 55. WEIGHT FOR REPAIR 8.3 OZ NDT VERIFIED DAMAGE REMOVED PER NDT 06-10-01.001. INSTALLED ID TAG DS 900-5-1 NR 4.

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PANEL 97 IS CRACKED AT FASTENER HOLE AFT END OF PANEL. REMOVED DAMAGE AT AFT END OF PNL IAW SRM 53-01, FIG 4. HFEC INSP IAW NDT SPM 06-10-01.001. FOUND DAMAGE REMOVED. REPAIRED PANEL IAW SRM 53-01, FIG 4, ERA 490832-14 & MFG DWG 9919600. INSTALLED ID TAG IAW DPM900-5-1, NR 4.

Part: CHANNEL — BROKEN (FLOOR PANEL) · airframe 71,333 hrs · 66,584 cycles

MAIN PASSENGER CABIN FLOOR PANEL 70 AFT END HAT CHANNEL BROKEN AT FASTENER HOLE. REMOVED & REPLACED 4 EA HAT CHANNELS IAW DC-9 SRM 51-30-2 & ERA 490831-14. REMOVED PREVIOUS MISDRILLED REPAIR & REPAIRED PANEL IAW DC-9 SRM 53-05 FIG 1 & 51-30-2. INSTALLED 2 EA ID TAGS IAW DPS 900-5-1#4.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PANEL 37 HAS CORROSION ON TOP OF PANEL. REMOVED CORR. 6X1 INCH IAW DC-9 SRM 53-01 FIG 1 AND CARD 5100-01570-01. ORIG MATERIAL .020 REMOVED .013 REMAINING MAT.007 OUT OF LIMITS. FABBED NEW PNL FROM .025 7075-T6 IAW DWG9957918 AND ERA 490827-14. COPY ATTACHED REV ORIGINAL ID TAG APPLIED 29 MAR 11 REQUIRED INSPECTION COMPLETED 29 MAR 11.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PANEL 60C HAS 4EA HAT CHANNELS CRACKED ON BOTTOM OF PANEL. REMOVED 5EA HAT CHANNELS IAW SRM 51-30-2. FOUND WEB CRACKED, FABRICATED, LOCATED, DRILLED AND DEBURRED TO SKIN WITH .025 7075-T6 IAW ERA 490830-14. TRIMMED, LOCATED, DRILLED AND DEBURRED 4EA NEW HAT CHANNELS USING S2912282 IAW ERA 490830-14. INSTALLED 5EA HAT CHANNELS LOCATED, DRILLED AND DEBURRED HOLES IAW DC-9 SRM 51-10-4.

Part: FRAME — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

AFT ACCESSORY COMPARTMENT CANTED FRAME 1243 IS CRACKED AT L4R. REMOVED CANTED FRAME AT STA 1243 IAW DC-9 SRM 51-30-5 AND 51-30-2. LOCATED AND DRILLED NEW FRAME P/N SR09530086-81 IAW DC9 SRM 51-10-4. INSTALLED NEW FRAME IAW DC9 SRM 51-30-5 P-102.

Part: KEELBEAM — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

LEFT KEEL AREA STA 712 BETWEEN L29L AND L30 FRAME HAS CORROSION. REMOVED CORROSION IAW DC9 SRM 51-10-3. 100 PERCENT MATERIAL LOSS. REMOVED FRAME IAW DC-9 SRM 51-30-2. LOCATED, DRILLED AND INSTALLED NEW FRAME P/N 9957740-3 IAW DC9 SRM 51-10-4, 51-30-2 AND 51-30-5, P-102 26.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN PASSENGER CABIN FLOOR PANEL 72 TOP SKIN HOLE PUNCH CUTOUT DAMAGE IAW DC9 SRM 53-01. HFEC INSP IAW NDT SPM 06-10-01.001. NO CRACKS NOTED. FABRICATED FILLER AND DOUBLER FROM 7075-T6 .025 LOT 1120200 IAW DC9N SRM 53-01. INSTALLED FILLER AND DOUBLER IAW DC9 SRM 51-30-2 AND 51-30-8.

Part: SUPPORT BRACKET — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STATION 200 L4L CRACKED. REMOVED L4L STA 160-228 AND 2 EA SPLICES STA 160-180 & 116-228. INTERCOSTAL SUPPORT BRACKET AND ATTACHMENT CLIP TO GO IN ACCESS. LOCATED, DRILLED, DEBURRED, TREATED, PRIMED AND INSTALLED IAW 51-10-4, 51-20-2, 51-30-2. RE-INSTALLED 2EA SPLICES AND INTERCOSTAL SUPPORT BRACKET.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STATION 200 LONGERON L2L CRACKED. REMOVED 32 INCHES OF L2L & 2 EA SPLICES. REMOVED CENTER AC DUCT STA 180 FOR ACCESS. RECEIVED NEW CAST FORM MAT P/N S2777922-3, LOCATE, DRILL, TRIM, DEBURRED, TREAT, PRIME & INSTALL IAW SRM 51-10-2, 51-30-2, 51-30-5, 53-13-1 ,51-10-4 AMM 20-11-00. INSTALLED CENTER UPPER AC DUCT IAW AMM 20-11-00.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 1132 LBL 44 LEFT SIDE CUSP WEB CRACKED APPROX 2 INCHES UNDER SEAT TRACK. REMOVED DAMAGED AREA 12"X 12". NDT VERIFIED DAMAGE REMOVED IAW NDT SPM 06-10-01.001. FABRICATED, LOCATED, DRILLED, DEBURRED AND INSTALLED NEW WEB AND SPLICE. INSTALLED PARTS PER BOEING DRAWING SG09530019.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 200 RBL 47 TO 57 FLOOR SUPPORT HAS CORROSION. REMOVED FLOOR SUPPORT IAW DC-9 SRM 51-30-5. REMOVED CORROSION IAW DC-9 SRM 51-10-3. ORIG MAT .060 MAT REMOVED .050 MAT REMAIN.010. FOUND TO BE OUT OF LIMITS L=8.00 W: 1.75D= .050 IAW DC-9 SRM 53-01 FIG 1. FABBED NEW FLOOR SUPPORT S2652479 7075-T6. INSTALLED NEW SUPPORT IAW DC-9 SRM 51-30-5.

Part: ANGLE — BROKEN (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 225 RBL 56 Z-ANGLE BROKEN OUT AT FASTENER HOLE. REMOVED Z-ANGLE IAW DC-9 SRM 51-30-2. RECEIVED NEW Z-ANGLE IAW DC-9 SRM 51-10-1. LOCATED, DRILLED & DEBURRED Z-ANGLE IAW DC-9 SRM 51-10-4. INSTALLED NEW Z-ANGLE IAW DC-9 SRM 51-30-5.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN PAX CABIN RT SIDE CUSP WEB HAS 1EA CRACKED AT RBL 40 AFT 1 INCH FROM FLOORBEAM BS 239. REMOVED DAMAGE FROM WEB IAW DC9 SRM 53-10-16-801-663A FIG 2. HFEC INSP IAW DC9 NDT SPM 06-10-01. FOUND DAMAGE REMOVED INSTALLED 1EA REPAIR DOUBLER .020 7075T6 CLAD IAW DC9 53-10-16.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN PAX CABIN/GALLEY HOLE IN EXISTING FRAME REPAIR BLOWN OUT AT STA 1151 AND L-17-L. REMOVED EXISTING REPAIR IAW SRM 51-30-2, 51-30-5. FABBED NEW REPAIR PLATE .063 7070-T6. FABBED REPAIR ANGLE & FILLER .050 7075-0. TREATED & PRIMED IAW DC-9 SRM 51-10-3. INSTALLED IAW DC-9 SRM 53-03 FIG 4.

Part: DIAPHRAGM — DAMAGED (FUSELAGE) · airframe 71,333 hrs · 5,321 cycles

MAIN CABIN - FASTENER HOLE IN DIAPHRAGM TORN STA 172 RBL 44. REMOVED DAMAGE IN 3 EA PLACES .400" IN DIAMETER IAW DC9 SRM 53-01. HFEC INSP IAW NDT SPM 06-10-01.001. NO CRACKS NOTED. FABBED DOUBLER 7075-T6 IAW DC-9 SRM 53-13-1 FIG 11. TREATED & PRIMED DOUBLER IAW DC-9 SRM 51-10-3. INSTALLED DOUBLER ID TAG IAW DC-9 SRM 51-30-2 & DPS 900-5-1.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 160 TO 200 RBL 44 FLOOR SUPPORT HAS CORROSION. REMOVED 1 EA FLOOR SUPPORT IAW SRM 51-30-5. REMOVED CORR IAW SRM 53-01. FOUND TO BE OUT OF LIMITS IAW SRM 53-01. FABBED 1 EA FLOOR SUPPORT MAT S2652479-7075-T6511. LOCATED, DRILLED & DEBUR IAW DC9 SRM 51-10-4. TREATED AND PRIMED IAW DC-9 SRM 51-10-3. INSTALLED IAW DC-9 SRM 51-30-5.

Part: DIAPHRAGM — DAMAGED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

ELONGATED HOLE IN DIAPHRAGM AT STA 198 AND RBL 46. REMOVED DAMAGE IN 1EA PLACE .500 IN DIAMETER IAW DC-9 SRM 53-01. HFEC INSP IAW NDT SPM 06-10-01.001. NO CRACK NOTED. FABBED DOUBLER 7075-T6 IAW DC-9 SRM 53-13-1 FIG 11. TREATED AND PRIMED DOUBLER IAW DC-9 SRM 51-10-3. INSTALLED DOUBLER ID TAG IAW DC-9 SRM 51-30-2.

Part: GUSSET — GOUGED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 832 LBL-10 GUSSET GOUGED. REJECTED FOR GUSSET IMPROPERLY INSTALLED. FABBED, LOCATED, DRILLED, COUNTERSUNK AND DEBURRED GUSSET IAW DC9 SRM 51-10-4 & DOUGLAS DWG 4915719. INSTALLED GUSSET IAW DC9 SRM 51-30-2.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,333 hrs · 66,584 cycles

CORROSION ON CABIN FLOOR PNL 16. FABRICATED NEW FLOOR PANEL IAW ER/A 490110-14 AND DC08 SRM 51-10-2. ASSEMBLED FLOOR PANEL IAW DC9 SRM 51-30-2. TREATED AND PRIMED PANEL IAW DC9 SRM 51-10-3. DRILLED AND COUNTERSUNK HOLES IAW DC-9 SRM 51-10-4.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PANEL 84 CRACKED AT FWD I/B EDGE. STOP DRILLED CRACK IAW DC9 SRM 53-01. NDT VERIFIED CRACK CONTAINED IAW NDT SPM 06-10-01. FABBED AND INSTALLED REPAIR DOUBLER FROM 7075 T6 .020 IAW DC-9 SRM 53-01.

Part: LONGERON SPLICE — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

FWD CARGO COMPT LONG 28L SPLICE HAS EXFOLIATED CORROSION BETWEEN BS 237 AND BS 229. REMOVED DAMAGED SPLICE. SEALED AND REPLACED WITH NEW SPLICE IAW DC9 SRM 51-30-2, 51-10-4, 51-10-3, 51-20-0, 51-30-5.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN PASSENGER CABIN STA 435 LT CUSP WEB CRACKED. CUT OUT DAMAGED AREA 2"X 3.5". NDT VERIFIED DAMAGE REMOVED IAW NDT SPM 06-10-01. FABBED AND INSTALLED DOUBLER AND FILLER FROM 7075-T6 .025 & 7075T6 .020 IAW DC9 SRM 53-10-16.

Part: FRAME SPLICE — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

AFT CARGO COMPARTMENT FRAME AT STA 1116 HAS CORROSION ON LOWER AFT FLANGE SPLICE ANGLE BETWEEN LONG 28L AND LONG 30. FOUND SPLICE OUT OF LIMITS IAW DC9 SRM 53-01. REMOVED SPLICE IAW DC9 SRM 51-30-5. FABBED NEW SPLICE FROM 7075-0 .050. HEAT TREATED TO TO 7075T6 ON TRAVELER 2496 NO1489 AND INSTALLED IAW DC9 SRM 51-10-4, 51-10-2 & 51-30-5 P-205 Q-948 490448.

Part: ATTACH BRACKET — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

FWD CARGO STA 365 RBL 6 SURFACE CORROSION. REMOVED CORR 1 X 3 INCHES ON SURFACE OF ATTACH BRACKET. ORIG MAT .100 REMOVED .035 REMAINING .065. FOUND TO BE OUT OF LIMITS. RECEIVED, SEALED AND INSTALLED NEW BRACKET P/N 3457317-1. ALL WORK ACCOMPLISHED IAW DC-9 SRM 53-01, 51-20-00, 51-30-5 AND DOUGLAS DWG 3457317 REV A.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PANEL 45 HAS CORROSION ALONG FWD I/B EDGE REMOVED CORR. ORIG. MAT. 020" REMOVED .015" FOUND TO BE OUT OF LIMITS IAW SRM 53-01 FIG 1. CUT OUT DAMAGE 5.75 X 1.75 INCHES NDT INSP VERIFIED DAMAGE REMOVED IAW NDT SPM 06-10-01. FABBED DOUBLER AND FILLER .020" 7075-T6 INSTALLED DOUBLER AND FILLER IAW SRM 53-01 FIG 4.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PANEL 33 HAS CORROSION ON TOP AROUND FASTENER HOLES. REMOVED CORR OUT OF LIMITS IAW SRM 53-01 FIG 1. CUT OUT DAMAGE IN 4EA PLACES IAW SRM 53-5 FIG 1. FABBED 4EA DOUBLERS AND FILLERS FROM .025 INCH 7075-T-6 AND .032" 7075-T6. INSTALLED DOUBLERS AND FILLERS IAW SRM 51-10-3.

Part: SUPPORT CHANNEL — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

NLG STA 106 RIGHT LONG 28 DOOR CUTOUT SUPPORT CHANNEL CRACKED APPROX 1.25 INCH. RECEIVED FORMER P/N 5913421023. REMOVED CRACKED FORMER AND REPLACED IAW SRM 51-30-05 AND 51-10-3.

Part: SKIN — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

FUSELAGE EXTERIOR CANTED FRAME STA 1292 BETWEEN LONG 13-14L SKIN CRACKED AT FASTENER. REMOVED DAMAGE 1 5/8"X 1 1/16". NDT VERIFIED DAMAGE REMOVED IAW NDT SPM 06-10-01. FABBED FILLER AND DOUBLER FROM .040" 7075-T6 AND .050" 7075-T6. INSTALLED DOUBLER AND FILLER IAW SRM 53-01 FIG 4.

Part: GUSSET — GOUGED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 832 LBL-10 GUSSET GOUGED. GOUGE FOUND TO BE OUT OF LIMITS 90 PERCENT MAT. LOSS IAW SRM 53-01 FIG 1. REMOVED GUSSET, FABBED NEW ONE FROM .032" 7075-0 AND HEAT TREATED TOT6 ON TRAVELER #24961416. INSTALLED NEW GUSSET IAW SRM 51-30-5 AND 51-10-3.

Part: STRUCTURE — MISREPAIRED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 785 RBL 50 PREVIOUS REPAIR NOT MEETING FASTENER REQUIREMENT. REMOVED EXISTING REPAIR IAW SRM 51-30-2. FABBED AND INSTALLED FILLER.040" 7075-T6 AND DOUBLER .050" 7075-T6 IAW SRP DC-9 A-53-10-16-801-663A-A.

Part: SKIN — GOUGED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

FUSELAGE EXTERIOR STAIRS CONTROL CUTOUT SKIN BELOW HINGE GOUGED. NDT FOUND CRACK CONTAINED AT FASTENER HOLE. REMOVED STAIR CONTROL DOOR. FABBED DOUBLER FROM .032" 2024-T3 AND INSTALLED DOUBLER AND DOOR IAW SRM 53-01 FIG 4.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,333 hrs · 66,584 cycles

CORROSION ON CABIN FLOOR PANEL 20. CORROSION FOUND TO BE OUT OF LIMITS IAW SRM 53-01 FIG 1. CUT OUT DAMAGED SECTION OF FLOOR PANEL 1.5"X 4". FABBED AND INSTALLED NEW SECTION OF PANEL FROM .032" 2024-T3 IAW DWG 9957828 AND SRM 53-01 FIG 4.

Part: SKIN — CRACKED (BS 1209) · airframe 71,333 hrs · 66,584 cycles

FUSELAGE EXTERIOR BS 1209 BETWEEN L13-14R SKIN CRACKED AT FASTENER. CUTOUT DAMAGED AREA 1.5"X 1.5" NDT VERIFIED CRACK REMOVED IAW NDT SPM 06-10-01. FABBED AND INSTALLED FILLER AND DOUBLER FROM .040" 7075-T6 PO#1023415 IAW SRM 53-01 FIG 4. REPAIR INSTALLED WITH BLIND FASTENERS. ESTABLISH MONITOR FOR REPETITIVE VISUAL

Part: HINGE — CRACKED (TE FLAP) · airframe 71,333 hrs · 66,584 cycles

LT WING NR 3 FLAP HINGE FLAP HALF OF THE HINGE IS CRACKED. REMOVED AND REPLACED NR 3 FLAP HINGE HALF IAW CARD 5753-9893M-LT.

Part: STINGER — DAMAGED (HORIZ STAB) · airframe 71,333 hrs · 66,584 cycles

HORIZONTAL STABILIZER STRINGER LT SIDE UPPER ANGLE HAS ELONGATED HOLES. REPLACED ANGLE, FABBED OUT OF .032 2024-T3 IAW SRM 55-31-00 FIG 8. SUBED 2024T43 FOR 2024-T3 IAW DC-9 SRM 51-60-0 FIG.1. LOCATED AND DRILLED IAW DC-9 SRM 51-10-04, 51-30-02 AND 51-30-05.

Part: PANEL — DAMAGED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN PANEL 102C HAS SEVERAL FASTENER HOLES ELONGATED. REMOVED DAMAGED HOLES AT 3EA LOCATIONS. FWD INBD & OTBD SIDES & AFT OTBD SIDE IAW DC9 SRM 53-01 FIG 4 & 53-05 FIG 1. HFEC IAW DC9 NDT SPM 06-10-01. FOUND DAMAGE REMOVED. REPAIRED PANEL IAW DC9 SRM 53-01 FIG 1. INSTALLED ID TAG PER DPS 900-5-1 NR 4.

Part: CARGO TRACK — DAMAGED (CARGO BAY) · airframe 71,333 hrs · 66,584 cycles

FWD CARGO STA 446 LT TIE DOWN TRACK HAS 2EA HOLES IN EDGE OF SPLICE. REMOVED DAMAGED SPLICE IAW DC9 SRM 51-30-05. FOUND SPLICE TO BE MISS LOCATED ON TIE DOWN TRACK IAW DWG 5932875. FABBED 2EA SPLICE ANGLES IAW DC9 SRM 53-03. TRIMMED TO FIT & LOCATED & DRILLED 2 EA SPLICE ANGLES IAW DC9 51-10-4. PRIMED & TREATED IAW DC9 SRM 51-10-3. INSTALLED 2EA REPAIR SPLICES IAW DC9 SRM 51-30-05.

Part: FLOOR PANEL — CORRODED (COCKPIT) · airframe 71,333 hrs · 66,584 cycles

COCKPIT FLOOR PANEL 15 HAS CORROSION. REMOVED CORROSION IAW DC09 SRM 51-10-3 & CPP 5100-01570-01. ORIGINAL THICKNESS .040 REMOVED .02 REMAINING .038 IN LIMITS IAW DC-9 SRM 53-01TOOL H8332.2 EA AREAS KNIFE EDGED & REQUIRE REPAIR. REPAIRED IAW DC9 SRM 53-01 USING 7075T6 .040 HFEC USING ZETEC PER NDTSPM 06-10-01. FOUND DAMAGE REMOVED P-205 REQUIRED INSPECTION COMPL.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PNL HAS CORROSION ON TOP OF PNL. REMOVED, FABRICATED, AND INSTALLED DOUBLERS IAW DC9 SRM 51-30-2.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PNL 83 HAS CORROSION ON BOTTOM SIDE AROUND FASTENER HOLES. REMOVED FLOOR PNL 83, FOUND TO BE OUT OF LIMITS. FABRICATED AND INSTALLED REPAIRS IAW DC-9 SRM 51-30-1.

Part: STRUCTURE — DAMAGED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 765 RBL-50 PREVIOUS REPAIR NOT MEETING FASTENER REQUIREMENT. REMOVED EXISTING REPAIR AND FOUND HOLE DAMAGED. TRIMMED OUT DAMAGE, NDT VERIFIED NO CRACKS IAW NDT SPM 06-10-01.001 A2799. FABRICATED AND INSTALLED REPAIR & ID TAG IAW DC-9 SRP 53-10-16-801-663A-A &DPS 900-5-1 #4.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

UPON FURTHER OPEN UP FOUND INTERNAL DOUBLER AT STAIR CONTROL CUT OUT CRACKED. ORIG MAT .032 2014-T6 IAW DC-9 SRM 53-33-0 FIG 5. REMOVED AND REPLACED INTERNAL DOUBLER MAT .032 7075-T6IAW DC9 SRM 53-30-2 & 51-30-5.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 200 TO 285 LBL 44 SEAT TRACK HAS CORROSION. REMOVED AND REPLACED CORROSION DAMAGED SEAT TRACK SEC LBL 44 STA 200-285 PN 2772660 IAW DC-9 SRM 53-05 FIG 42.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 753 LBL 46 LEFT SIDE CUSP WEB CRACKED APPROX 1.25. REMOVED 2"X 2" OF DAMAGED CUSP WEB STA 753 DAMAGE REMOVED IAW NDT SPM 06-10-01.001. FABRICATED REPAIR FILLER AND DOUBLER .040 7075-T6. TREATED, PRIMED AND INSTALLED IAW BOEING DRAWING SG 09530019, DC9 SRM 51-10-3, 51-30-1, 51-30-2, 51-30-5. INSTALLED ID TAG PER DPS 900-5-1 NR 4. P-102 REQUIRED.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 200 TO 285 LBL 22 SEAT TRACK HAS CORROSION. REMOVED CORROSION ON SEAT TRACK IAW DC9 SRM 51-10-3. ORIGINAL THICKNESS WAS .090 IAW DC9 SRM 53-23-0 FIG 4. AFTER BLEND THICKNESS IS .029. OUT OF LIMITS IAW DC9 SRM 53-01. SEAT TRACK REMOVED, FABBED AND INSTALLED FROM STA 200-303 ON WORKCARD 6C/271.

Part: FLOOR PANEL — CHAFED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PANEL 90 IS CHAFED THROUGH FASTENER HOLE FWD END. REMOVED 2EA CHAFED AREA.1ST AREA REMOVED 1"X 1" AND 2ND AREA REMOVED 1.5 X 1.25 HAD AREA NDT NO CRACKS NOTED. FABBED 2EA REPAIR DOUBLERS OUT OF 7075-T6 .032 AND FABBED 2EA REPAIR FILLERS OUT OF 7075-T6 .025". LOCATED, DRILLED TREATED AND INSTALLED IAW DC9 SRM 51-10-03, 51-10-04, 53-01 FIG 1, 53-23-0.NDT SPM 06-10-01, 51-30-02. REQUIRED INSPECTION COMPLETED.

Part: SKIN — GOUGED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

FWD SERVICE DOOR JAMB AFT LOWER CORNER HAS GOUGES IN SKIN WHERE SCUFF PLATE WAS REMOVED. INCOMING BLENDED GOUGES IAW DC-9 SRM 53-01 FIG 1 SHT 3 ORIG MAT .050 IAW DC-9 SRM 53-33-0 FIG 1 SHT 3. MAT REMAIN .036 OUT OF LIMITS IAW DC-9 SRM 53-01 FIG 1. NDT SPM 04-00-07. FABBED & INSTALLED DOUBLER IAW DC-9 SRM 53-04 FIG 38 SHT 22 & E8825. REQUIRED INSPECTION COMPLETED.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PNL 64 HAS CORROSION ON TOP SIDE OF PNL AROUND FASTENER HOLES. REMOVED CORROSION ON TOP SKIN OF FLOOR PANEL IAW DC9 SRM 53-01 2EA FASTENER HOLES REMOVED FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01. FABBED 2EA NEW DOUBLER & FILLER .032 DOUBLER & FILLER .020 IAW DC9 SRM 53-01 FIG 1. TREATED AND PRIMED 2EA DOUBLERS & FILLER IAW DC9 SRM 51-10-3. INST 2EA DOUBLER & FILLER IAW DC9 SRM 53-01 FIG 1. REQUIRED INSPECTION COMPLETED.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN PASSENGER CABIN FOUND CUSP WEB BETWEEN STA 200 STA 218 BETWEEN LBL 24 - LBL 59 CORRODED. FOUND TO BE OUT OF LIMITS. CUT OUT DAMAGED AREA 3X3 INCHES, FABBED DOUBLER AND 2 EACH FILLERS, LOCATED, DRILLED, DEBURRED DOUBLER AND FILLER,TREATED, PRIMED DOUBLER AND FILLERS AND INSTALLED DOUBLER AND FILLER IAW DC9 SRM 51-10-3, 53-01 FIG 1, 53-01 FIG 4, 51-01, 51-10-4, 53-13-1 FIG 11, 51-30-8.

Part: WEB — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 208 L11L WEB CRACKED AT FASTENER. CUT OUT DAMAGE IAW DC-9 SRM 53-01 FIG 4.FABBED DOUBLER & FILLER OUT OF .050 2024-T3. LOCATED & DRILLED IAW DC-9 SRM 53-10-01 FIG 1 SHEET 10 AND 51-10-04. INSTALLED REPAIR IAW DC-9 SRM51-30-02, 51-30-5 & 53-01 FIG 4. INSTALLED ID TAG IAW DELTA DPS 900-5-1.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 241 LBL 52 LEFT SIDE CUSP WEB CRACKED ON BOTTOM SIDE APPROX 1.25 INCHES. CUT OUT DAMAGED AREA 2.5 X 2 INCHES. NDT VERIFIED DAMAGE REMOVED IAW NDT SPM 06-10-01. FABBED & INSTALLED FILLER FROM 7075T6 .020 & DOUBLER FROM 7075T6 .032 IAW DC-9 SRM 53-20-01. DPS 900-5-1 NO 4 TAGGED PERMANENT REPAIR P-205. REQUIRED INSPECTION COMPLETED.

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PANEL NR 32 IS CRACKED AT FWD END AT FASTENER HOLE. CUT OUT DAMAGE SECTION FABRICATED DOUBLER & FILLER AND INSTALLED IAW SRM 51-30-02, 53-05, FIG 1. TREATED & PRIMED IAW SRM 51-10-3. REQUIRED INSPECTION COMPLETED.

Part: SEAT TRACK — CORRODED (BS 200-285) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 200 TO 285, RBL 22, SEAT TRACK HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-3. ORIG MAT .090 IAW SRM 52-20-0 AND 51-10-1, FIG 26, MAT LOSS OVER 50 PERCENT OUT OF LIMITS IAW SRM 53-01, FIG 1. R & R SEAT TRACK IAW SRM 53-05.

Part: DOOR FRAME — BENT (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

FUSELAGE EXTERIOR STA 1068 BETWEEN L23R AND L24R PREVIOUS REPAIR AT AFT CARGO DOOR JAMB BENT. REMOVED & REPLACED PREVIOUS REPAIR IAW SRM 51-30-2 & 51-30-5. FABBED NEW DOUBLER. LOCATED, DRILLED & DEBURRED IAW SRM 51-10-2 & 51-10-4. ALODINED & PRIMED IAW SRM 51-10-3. REQUIRED INSPECTION COMPLETED.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN PASSENGER CABIN BETWEEN STA 278 LBL 44 CUSP WEB CRACKED. CUT OUT DAMAGE 1" X 1" IAW DC-9 SRM 53-01 FIG 4. WEB ORIG MAT .020 7075-T6. FAB AND INSTALLED 1 EA DOUBLER 1 EA FILLER MAT .020 7075T6 IAW DC9 SRM 51-30-2 & 53-01 FIG 4. REQUIRED INSPECTION COMPLETED.

Part: CHANNEL — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN METAL SKIN FLOOR PANEL NR 32, 1EA HAT CHANNEL CRACKED AT END. CUT OUT DAMAGE SECTION, RECV MATERIAL FOR HAT SECTION & SPLICE. TREATED, PRIMED & INSTALLED IAW SRM 53-05, FIG 1, 51-10-03, 51-30-02 ID TAG IAW DELTA PSM 900-5-1. REQUIRED INSP COMPLETED.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 285 TO 313 LBL 22 SEAT TRACK HAS CORROSION. REMOVED CORROSION IAW DC9 SRM 51-10-3. ORIGINAL THICKNESS WAS 115 IAW DC9 SRM 53-23-0 AFTER BLEND THICKNESS IS .057. MEASURED WITH TOOL H9340 CAL DUE 18 JUL 11 OUT OF LIMITS IAW DC9 SRM 53-01. REMOVED AND FABBED NEW TRACK FROM S27722660 IAW DC9 SRM 53-23-0. INSTALLED NEW TRACK STA 200-302 IAW DC9 SRM 51-30-1 AND 51-30-5.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PANEL 70 HAS 1 EA HOLE CRACKED AND ELONGATED. REMOVED DAMAGED AREA IAW DC9 SRM 53-05 FIG 1. HFEC INSP IAW DC9 NDT SPM 06-10-01. FOUND DAMAGE TO BE REMOVED. REPAIRED FLOOR PANEL IAW DC9 SRM 53-05 FIG 1. INSTALLED ID TAG PER DPS 900-5-1. REQUIRED INSPECTION COMPLETED.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 160 TO 200 LBL 55 Z-ANGLE CRACKED AT FASTENER HOLES. REPLACED Z-ANGLE. LOCATED AND DRILLED IAW DC-9 SRM 51-30-05 & 51-10-04.

Part: INTERCOSTAL — BENT (BS 1314-1326) · airframe 71,333 hrs · 66,584 cycles

AFT ACC COMPT INTERCOSTAL BETWEEN STA 1314-1326 ABOVE EXTERIOR PULL HANDLE BOX BENT. RECEIVED INTERCOSTAL AND CLIPS IAW SRM 51-30-2. CLIPS CRACKED AND INTERCOSTAL NOTED TO HAVE GOUGE & TOOLING MARKS OUT OF LIMITS IAW SRM 53-01, FIG1. T=.032 2024T3 FOR CLIPS .025 2024T3 FOR INTERCOSTAL. RECEIVED MATERIAL. FABRICATED & INSTALLED 2 CLIPS & INTERCOSTAL IAW SRM 51-10-2, 51-10-4, 53-13-4, FIG 3 & DWG 9917701, 51-30-2, 51-30-5.

Part: FLOORBEAM — CHAFED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 294 RBL 3 TO 19 FLOORBEAM CHAFED. REMOVED REPAIR STRAP IAW DC9 SRM 51-30-1. FABED NEW IAW DC9 SRM 53-05. PRIMED IAW DC9 SRM 51-10-3. BLENDED FLOORBEAM RBL 3-19 CHAFED AND FOUND TO BE WITHIN LIMITS IAW DC9 SRM 53-01. ORG THICKNESS .125 REMOVED .003 REMAINING .122.

Part: INTERCOSTAL — DAMAGED (BS 220-225 RBL22) · airframe 71,333 hrs · 66,584 cycles

MAIN PASSENGER CABIN STA 220-STA 225, RBL 22 INTERCOSTAL HOLES ELONGATED. ORIGINAL MATERIAL FOR INTERCOSTAL .040, 2024-T42 IAW SRM 53-13-2, FIG4. FABRICATED 2EA REPAIR ANGLES FROM MAT .020 7075-76 IAW SRM 51-10-4 & 53-01, FIG.2. INSTALLED 2EA REPAIR DOUBLERS IAW SRM 53-01. REQUIRED INSPECTION COMPLETED.

Part: FLOOR SUPPORT — CORRODED (BS 160-218 BL 0) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 160 TO 218, BL 0, FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-3. ORIGINAL THICKNESS WAS .060 IAW SRM 53-13-1, FIG 11. AFTER BLEND THICKNESS IS OVER 50 PERCENT LOSS OUT OF LIMITS IAW SRM 53-01. REMOVED SUPPORT IAW SRM 51-30-5. FABRICATED NEW SUPPORT IAW SRM 53-13-1 FIG.11. INSTALLED NEW SUPPORT IAW SRM 51-30-5. REQUIRED INSP COMPLETED.

Part: FLOOR SUPPORT — CORRODED (BS 218-237 BL 0) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 218 TO 237, BL 0, FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION AT FLOOR SUPPORT STA 218 TO 237, BL0, AREA 2" X .5" MAT LOSS FOUND TO BE MORE THAN 50 PERCENT. FLOOR SUPPORT OUT OF LIMITS. REMOVED FLOOR SUPPORT AND NEW EXTRUSION TRIMMED, LOCATED, DRILLED, DEBURRED, TREATED AND PRIMED. INSTALLED NEW FLOOR SUPPORT IAW SRM 51-30-3, FIG 1, DWG 5910137, 51-10-4, 51-30-5, 51-30-1. REQUIRED INSP COMPLETED.

Part: ATTACH ANGLE — DAMAGED (BS 160 LBL 55) · airframe 71,333 hrs · 66,584 cycles

MAIN PASSENGER CABIN STA 160, LBL 55, Z-ANGLE LT ATTACH ANGLE HAS ELONGATED HOLES. REMOVED LT ATTACH ANGLE. FABRICATED FROM .0502024-T3 IAW SRM 51-30-05 & 51-60-0 FIG 1. LOCATED AND DRILLED AND INSTALLED IAW SRM 51-10-04 AND 51-30-05.

Part: ATTACH FITTING — CRACKED (BS 180 LBL 1) · airframe 71,333 hrs · 66,584 cycles

E & E COMPT STA 180 LBL-1 INTERCOSTAL CLIP CRACKED. REMOVED CRACKED INTERCOSTAL CLIP FS 180, LBL-1, E & E CEILING. FABRICATED, TREATED, PRIMED, AND INSTALLED REPLACEMENT CLIP IAW SRM 51-30-02, 51-10-02,51-10-04, 51-10-03, AND 51-30-05. REQUIRED INSPECTION COMPLETED.

Part: PANEL — DAMAGED (RT WING) · airframe 71,333 hrs · 66,584 cycles

RT WING STA XRS-353 FIXED PANEL GOUGED ON LOWER SURFACE T/E. REMOVED DAMAGED SKIN MEASURING .3750" RADIUS. FAB FILLER & DOUBLER FROM .040. REMOVED AL CAD AND PREPARED ALL MATING SURFACES FOR BOND. BONDED FILLER & DOUBLER FOR 90 MINUTES AT 230 DEGREES IAW SRMS 57031-3 & 51-70-2. PRIMED & TREATED & TOPCOATED IAW SRM 51-10-3. REQUIRED INSPECTION COMPLETED.

Part: KEELBEAM — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

KEEL AREA BETWEEN DOORS, THRU ACCESS 5501NW LBL 6 ANGLE CRACKED APPROX 2 INCHES. CUT OUT DAMAGED ANGLE IAW ENGINEERING SERVICE REQUEST 2496N01328 AND DC9 SRM 53-01. FABRICATED NEW ANGLE FROM 7075-0 .063 AND REPAIR ANGLES FROM7075-T6 .032 IAW DWG 9923459. HEAT TREATED ON PEMCO TRAVELER2496N01393. INSTALLED ALL REPAIR PARTS IAW SRM 53-01 AND SERVICE REQUEST 2496N01328 P102 29 MAR 11 REQ INSP COMPLETED 14 MAR 11.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

AFT ACCESSORY STA 1258 LEFT LONG. 5 O/B FAN VERTICAL SUPPORT CRACKED. REMOVED CRACKED SUPPORT IAW DC-9 SRM 51-30-2 & 51-30-5. LOCATED DRILLED & DEBURRED NEW SUPPORT BRACKET IAW DC-9 SRM 51-10-4. INSTALLED NEW BRACKET IAW DC-9 SRM 51-30-2 & 51-30-5.

Part: CAP — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

AFT CARGO STA 1167 RIGHT LONG 21 LONG END CAP HAS CORROSION. REMOVED CORROSION IAW DC9 SRM 51-10-3. ORIGINAL THICKNESS WAS .094 IAW DRAWING 4914957. UT THICKNESS IAW NDT SPM 04-00-07 FOUND REMAINING THICKNESS IS .072 OUT OF LIMITS IAW DC9 SRM 53-01. REMOVED FITTING IAW DC9 SRM 51-30-2 AND 51-30-5. DRILLED AND INSTALLED NEW FITTING P/N 4914957-1 IAW DC9 SRM 51-30-2 AND 51-30-5 P102.

Part: INTERCOSTAL — DAMAGED (BS 294-313 BL 0) · airframe 71,333 hrs · 66,584 cycles

MAIN PAX CABIN/GALLEYS; INTERCOSTAL BETWEEN STA 294 AND 313 AND BL-0, HAS ELONGATED AND OVER SIZED HOLES. REMOVED INTERCOSTAL IAW SRM 51-30-5. FABRICATED NEW INTERCOSTAL FROM 2024-T3 .025, IAW SRM 53-13-2 FIG 4 AND 51-60 FIG 4 AND 51-60 FIG 1 INSTALLED NEW INTERCOSTAL IAW SRM 51-30-5. REQUIRED INSP COMPLETED.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PNL 78 IS CRACKED ON END AT FASTENER. REMOVED DAMAGE AT FWD END OF PANEL & HAT CHANNEL IAW DC9 SRM 53-05 FIG 1. HFEC INSPEC IAW DC9 NDT SPM 06-10-01. FOUND DAMAGE REMOVED. REPAIRED PANEL IAW DC9 SRM 53-05 FIG 1. INSTALLED ID TAG PER DPS 900-5-1.

Part: FLOORBEAM — CHAFED (BS 636 BL0-22) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 636 BETWEEN BL-0 AND LBL-22 FLOOR SUPPORT CHAFED. CORR BY FILLING IM 316479 BLENDED SUPPORT IAW SRM 51-10-3. ORIGINAL THICKNESS WAS .050 IAW SRM 53-13-2, AFTER BLEND THICKNESS IS .027 OUT OF LIMITS IAW SRM 53-01, FIG 1 FABBED NEW SUPPORT IAW SRM 53-13-2. INSTALLED NEW SUPPORT IAW SRM 51-30-5. REQUIRED INSP COMPLETED.

Part: FLOOR PANEL — BROKEN (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PNL 74 CORNER OF PNL IS BROKEN OFF CUT OUT DAMAGE (2 X .75 INCH) IAW DC/9 SRM 51-10-2. FABRICATED, LOCATED, DRILLED AND INSTALLED REPAIR DOUBLER AND FILLER USING.020 IAW DC/9 SRM 53-23-00 FIG 5 AND 51-30-2. REQUIRED INSPECTION COMPLETED 10 MAR 11.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

PARTS RACK 92B FWD CARGO FLOOR SUPPORT C8 HAS CORROSION. REMOVED CORROSION IAW DC9 SRM 51-10-3. ORIGINAL THICKNESS WAS .063 IAW DRAWING 9C25-90981, AFTER BLEND THICKNESS IS .044 OUT OF LIMITS IAW DC9 SRM 53-01. FABRICATED NEW SUPPORT FROM 2024-T3.063 LOT 1120302 IAW DRAWING 9C25-90981. TREATED AND PRIMED IAW DC9 SRM 51-10-3 P102 12 MAR 11.

Part: FLOORBEAM — CHAFED (STA 655 BL0-22) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 655 BETWEEN BL-0 AND LBL-22 FLOORBEAM CHAFED ON TOP SIDE. BLENDED AREA IAW SRM 53-01. ORIGINALTHICKNESS WAS .125 IAW SRM 53-13-2, AFTER BLEND THICKNESS IS .073 OUT OF LIMITS IAW SRM 53-01. FABRICATED 5 EA REPAIR PLATES IAW SRM 53-05, FIG 20. INSTALLED PLATES IAW SRM 51-30-5. REQUIRED INSP COMPLETED.

Part: FLOOR SUPPORT — CHAFED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 617 BETWEEN BL-0 AND LBL-22 FLOOR SUPPORT CHAFED. BLENDED AREA IAW DC9 SRM 53-13-2 FIG 4 AND 51-10-3. ORIG THICKNESS WAS .050 IAW DC9 SRM 53-13-2 FIG4, AFTER BLEND THICKNESS IS .027, OUT OF LIMITS IAW DC9 SRM 53-01. REMOVED AND FABRICATED NEW SUPPORT IAW DC9 SRM 53-13-2 FIG 4. INST NEW SUPPORT IAW DC9 SRM 51-30-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 775 BETWEEN BL 0 AND LBL 22 FLOOR SUPPORT HAS CORROSION AND CRACKED. REMOVED DAMAGED FLOOR SUPPORT, OBTAINED MATERIAL .0502024T3 FORMED, DRILLED, DEBURRED, TREATED, PRIMED, SEALED, INSTALLED, IAW DC-9 SRM'S 51-30-2 53-13-3 FIG 11 51-10-2, 51-10-4, 51-10-3, 51-20-0, & DPS 900-2-4-1#02, 900-3-6#03.RIS 072082 ,470504 09 MAR 11 P102 09 MAR 11 REQUIRED INSPECTION COMPLETED 09 MAR 11.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

PARTS RACK 92B FWD CARGO FLOOR SUPPORT C5 HAS CORROSION. CORR BY FILLINGIM 316479 STA DHN 03MAR11 ATA REMOVED CORROSION IAW DC9 SRM 51-10-3. ORIGINAL THICKNESS WAS.063 IAW DRAWING 9C25-90981, AFTER BLEND THICKNESS IS OUT OF LIMITS IAW DC9 SRM 53-01. FABRICATED NEW SUPPORT FROM 2024-T3 .063 LOT 1120302 IAW DRAWING 9C25-90981. TREATED AND PRIMED IAW DC9 SRM 51-10-3 P102 12 MAR 11.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

PARTS RACK 92B FWD CARGO FLOOR SUPPORT C9 HAS CORROSION CORR BY FILLINGIM 316479. REMOVED CORROSION IAW DC9 SRM 51-10-3. ORIGINAL THICKNESS WA.063 IAW DRAWING 9C25-90981, AFTER BLEND THICKNESS IS .041 OUT OF LIMITS IAW DC9 SRM 53-01. FABRICATED NEW SUPPORT FROM 2024-T3 .063 LOT 1120302 IAW DRAWING 9C25-90981. TREATED AND PRIMED IAW DC9 SRM 51-10-3. P102 12 MAR 11.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 71,333 hrs · 66,584 cycles

CORROSION ON CABIN FLOOR PNL 26 CORROSION FOUND TO BE OUT OF LIMITS, REMOVED DOUBLER, CHANNELS RECEIVED MAT .032 7075-T6 & HAT CHANNEL P/N 5290282, FABED, LOCATED, DRILLED, DEBURRED NEW PANEL, TREATED AND AND INSTALLED HAT CHANNELS AND DOUBLER IAW DC9 SRM 51-10-3, 53-01 FIG 1, 51-30-2, DWG 490108-14, 51-10-4, 51-10-2, 51-10-3.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PNL 69 IS CRACKED ON END AT FASTENER HOLE REMOVED CRACKED EXPANSION JOINT IAW DC9 SRM 51-30-2. LOCATED AND DRILLED NEW EXPANSION JOINT, P/N 9957925-109 IAW SRM 51-10-4. INSTALLED NEW EXPANSION JOINT TO FLOOR PANEL IAW SRM 51-30-2 P102.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

PARTS RACK 92B FWD CARGO FLOOR SUPPORT C14 HAS CORROSION. REMOVED CORROSION IAW DC-9 SRM 51-10-3. FOUND TO BE LIMITS IAW DC-9 SRM 53-01 FIG 1. FABRICATED NEW PANEL FROM 2024-T3 .063 ALUMINUM IAW DRAWING 9C25-90981 AND DC9 SRM 51-10-2. DRILLED AND COUNTERSUNK NEW HOLES IAW DC-9 SRM 51-10-4. TREATED AND PRIMED IAW DC-9 SRM 51-10-3.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 655 BETWEEN BL-0 AND LBL-22 FLOOR SUPPORT CRACKED. REMOVED FLOOR SUPPORT, FABBED NEW FLOOR SUPPORT, LOCATED, DRILLED, TREATED, PRIMED AND INSTALLED NEW FLOOR SUPPORT IAW DC9 SRM 51-30-2, 53-13-2 FIG 1, 51-10-2, 51-10-4, 51-10-3. REQUIRED INSPECTION COMPLETED Q968/280012 08 MAR 11.

Part: VERTICAL SUPPORT — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN JUST UNDER FLOOR STA 775 RBL-44 VERTICAL SUPPORT CRACKED APPROX 2 INCHES. REMOVED CRACKED SUPPORT, RECEIVED NEW SUPPORT. LOCATED, DRILL, DEBURRED, TREAT, PRIME & INSTALL IAW DC-9 SRM 51-30-2, 51-30-5, 51-10-4, 51-10-3. REQUIRED INSPECTION COMPLETED.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 712 RIGHT SIDE CUSP WEB CRACKED UNDER HORSE SHOE COLLAR APPROX 2 INCHES. CPCP TASK 53-53300. REMOVED, FABRICATED, AND INSTALLED DOUBLER IAW DRAWING SG09530019. APPLIED REPAIR TAG IAW PROCESS STANDARDS 900-5-1 NR 4.

Part: GUSSET — GOUGED (BS 794 LBL10) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 794 LBL-10 GUSSET GOUGED. REWORKED GOUGE AREA ON GUSSET, STA 794 LBL-10, L=1 W=.500, D=.017 ORG MAT WAS FOUND TO BE .032 IAW SRM 53-13-3, FIG 12, ITEM 1. REWORKED IAW SRM 51-10-3. AREA FOUND TO BE OUT OF LIMITS IAW SRM 53-01 FABRICATED NEW GUSSET IAW SRM 53-13-3 FIG 12 TREATED & PRIMED IAW SRM 51-10-3 AND INSTALLED IAW SRM 51-30-2. REQUIRED INSP COMPLETED.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PANEL 65 HAS 4 EA FASTENER HOLES CRACKED. REMOVED DAMAGE BY CUTOUT 2.25" X 21"-ORIGINAL MAT. 7075T-6.025 IAW DC-9 SRM 53-01 FIG 4-NDT VERIFIED DAMAGE. REMOVED IAW NDT SPM 06-10-01 RECEIVED MAT 7075-T6-.025. FABBED LOCATED, TRIMMED, DRILLED, COUNTERSUNK, DEBURRED, TREATED, PRIMED & INSTALLED REPAIR DOUBLER & FILLER IAW DC-9 SRM 53-01 FIG 4 SH 4, 53-30-2 REQUIRED INSPECTION COMPLETED 09 MAR 11.

Part: CUSP WEB — DAMAGED (BS 770 LBL 50) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 770, LBL-50 CUSP WEB PREVIOUS REPAIR NOT MEETING FASTENER REQUIREMENT. REMOVED EXISTING DOUBLER IAW SRM 51-30-8. FABRICATED NEW DOUBLER FROM 7075-T6 .050 IAW SRM 53-13-3, FIG 11 AND SRP DC9-53-10-16-801-663A-A. INSTALLED NEW DOUBLER IAW SRM 51-30-2. REQUIRED INSP COMPLETED.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

PARTS RACK 92B FWD CARGO FLOOR SUPPORT C10 HAS CORROSION. REMOVED CORROSION IAW DC-9 SRM 51-10-3. FOUND TO BE OUT OF LIMITS IAW DC-9 SRM 53-01 FIG 1. FABRICATED NEW PANEL FROM 2024-T3 .063 ALUMINIUM IAW DRAWING 9C25-90981 AND DC-9 SRM 51-10-2. DRILLED NEW HOLES AND COUNTERSUNK IAW DC-9 SRM 51-10-4. TREATED AND PRIMED IAW DC-9 SRM 51-10-3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

PARTS RACK 92B FWD CARGO FLOOR SUPPORT C11 HAS CORROSION. REMOVED CORROSION IAW DC-9 SRM 51-10-3. FOUND TO BE OUT OF LIMITS IAW DC-9 SRM 53-01 FIG 1. FABRICATED NEW PANEL FROM 2024-T3 .063 ALUMINUM IAW DRAWING 9C25-90981 AND DC-9 SRM 51-10-2. DRILLED AND COUNTERSUNK NEW HOLES IAW DC-9 SRM 51-10-4. TREATED AND PRIMED IAW DC-9 SRM 51-10-3.

Part: CUSP WEB — CRACKED (BS 734 LBL50) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 734, LBL-50 LT SIDE CUSP WEB CRACKED APPROX 1 IN. STOP DRILLED CRACK IAW SRM 53-10-16. REMOVED 1 FASTENER IAW 51-30-2. REQUESTED NDT, NDT REPORTS CRACK CONTAINED. RECEIVED LOCATED, DRILLED, FIT, TRIMMED, AND DEBURRED REPAIR DOUBLER IAW SRM 51-30-4. TREATED AND PRIMED DOUBLER IAW SRM 51-10-3. INSTALLED DOUBLER IAW SRM 51-30-2. REQUIRED INSP COMPLETED.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

FWD CARGO STA 440 LBL 10 CORROSION ON INTERCOSTAL REMOVED CORROSION IAW DC9 SRM 51-10-3, UPON REMOVAL FOUND INTERCOSTAL TO BE CRACKED. REMOVED INTERCOSTAL IAW SRM 51-30-5. FABRICATED NEW INTERCOSTAL FROM 7075-0 .050 AND HEAT TREATED ON PEMCO TRAVELER 2496N01548. INSTALLED NEW INTERCOSTAL IAW DC9 SRM 51-30-5.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

PARTS RACK 92B FWD CARGO FLOOR SUPPORT C15 HAS CORROSION. REMOVED CORROSION IAW DC-9 SRM 51-10-3. FOUND TO BE OUT OF LIMITS IAW DC-9 SRM 53-01 FIG 1. FABRICATED NEW PANEL 2024-T3 .063 ALUMINUM IAW DRAWING 9C25-90981 AND DC-9 SRM 51-10-2. DRILLED AND COUNTERSUNK NEW HOLES IAW DC-9 SRM 51-10-4. TREATED AND PRIMED IAW DC-9 SRM 51-10-3.

Part: ANGLE — GOUGED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 1136 RBL 54 RIGHT PYLON BULKHEAD ANGLE AT FLOORBEAM GOUGED. BLENDED GOUGE. ORIGINAL .076 REMOVED OVER 50 PERCENT MAT. OUT OF LIMITS IAW DC-9 SRM 53-01 FIG 1 DWG 9912243. REMOVED AND REPLACED ANGLE AND END FITTING IAW DC-9 SRM 51-30-5.

Part: FLOOR PANEL — CHAFED (MAIN CABIN) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN FLOOR PANEL 81 CHAFED THROUGH AT FASTENER HOLE, FWD END. INSTALLED REPAIR DOUBLER AQUIRING MAT IAW DC9 53-23-0 .025 7075T6 PO 1120200 FABED. REPAIR IAW SRM 53-01, TREATED & PRIMED IAW SRM 51-10-3S. REQUIRED INSP COMPLETED.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 1151, L17L CRACKED AT FWD SIDE OF FRAME. REMOVED SECTION OF DAMAGED L-17-L, STA 1167 TO 1119, FROM EXISTING CLIP TO EXISTING SPLICE, REPLACED SECTION OF L-17-LENGTH 36 INCHES, REINSTALLED CLIP & SPLICE IAW DC-9 SRM (51-30-2) (51-32-5)(51-10-4)(51-20-0) (51-10-3).

Part: FRAME — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

AFT ACCESSORY COMPARTMENT CANTED FRAME CRACKED AT L18L BEHIND PREVIOUS REPAIR. REMOVED OLD REPAIR IAW DC-9 SRM 51-30-2, 51-30-5. CUT OUT CRACKED SECTION OF WEB AT STA 1292 L18L IAW DC-9 SRM 53-03 NO CRACKS FOUND FABED, TRIMMED, DRILLED NEW DOUBLER IAW SRM 53-03 FIG 38. TREATED, PRIMED IAW DC-9 SRM 51-10-3. INSTALLED FILLER, DOUBLER IAW DC-9 SRM 51-30-2, 51-30-5.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 155 L10R INTERCOSTAL CRACKED IN RADIUS. REMOVED INTERCOSTAL IAW DC9 SRM 51-30-2 AND 51-30-3. FABRICATED REPAIR ANGLES TO REPLACE INTERCOSTAL FROM 301 1/2HARD STEEL .063 IAW DC9 SRM 53-05 FIG 100. LOCATED, DRILLED AND INSTALLED 2 EA REPAIR ANGLES IAW DC9 SRM 53-05 FIG 100 AND 51-30-5 REPAIR IS BASED ON ROD SKETCH 90-06-18-007 P102 22 MAR 11 REQUIRED INSPECTION COMPLETED Q968/280012 22 MAR 11.

Part: FLOORBEAM — CORRODED (BS 200 LBL 1-20) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 200, LBL 1 TO 20, FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION, MATERIAL LOSS FOUND TO BE MORE THAN 50 PERCENT, REMOVED FLOOR SUPPORT. RECEIVED NEW PN 52652479, TRIMMED, LOCATED, DRILLED, DEBURRED, TREATED, PRIMED AND INSTALLED NEW SUPPORT IAW SRM 51-10-3, 53-01 FIG 1, 51-10-4, 51-30-5. REQUIRED INSP COMPLETED.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

FOUND CORROSION STA 1088 LONGERON 25L. REMOVED CORR ORIG MAT .063,7075T-6 RMVD .025 REMAINING .038 OUT OF LIMITS IAW DC-9 SRM 53-01. REMOVED APPROX 51" L25L STA 1088 & 2 EA SPLICES RECEIVED CUST MATERIAL LOCATE, DRILL,TRIM, DEBURR, TREAT, PRIME & INSTALL IAW DC-9 SRM 51-10-3, 53-02 FIG 18 SHT 1, 51-30-2, 51-30-5, 51-13-3, 51-10-2.

Part: INTERCOSTAL — CRACKED (BS 275-294 BL 0) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 275 TO 294, BL 0 INTERCOSTAL CRACKED AT FWD END. REMOVED INTERCOSTAL IAW SRM 51-30-5. FABRICATED NEW INTERCOSTAL FROM 2024-T3 .025 IAW SRM 53-13-2, FIG 4 AND 51-60 FIG 1. INSTALLED NEW INTERCOSTAL IAW SRM 51-30-5. P102 07 MAR 11. REQUIRED INSP COMPLETED.

Part: FLOOR PANEL — CORRODED (COCKPIT) · airframe 71,333 hrs · 66,584 cycles

COCKPIT FLOOR PANEL 13 HAS CORROSION. CPCP TASK 46-53303. REMOVED CORROSION IAW DC9 SRM 51-10-3 BUT FOUND OUT OF LIMITS. INSTALLED NEW FLOOR PANEL IAW DC9 SRM 51-10-3P102.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 200 TO 284.5 RBL 44 SEAT TRACK HAS CORROSION. REMOVED CORR IAW DC9 SRM 51-10-3. ORIGINAL THICKNESS WAS .090. AFTER BLEND THICKNESS IS .065, OUT OF LIMITS IAW DC9 SRM 53-01. REMOVED SEAT TRACK STA 200-284.5 IAW DC9 SRM 51-30-5. LOCATED, DRILLED, AND INSTALLED NEW TRACK P/N S2772660-7075T6 IAW DC9 SRM 51-10-4 AND 51-30-5.

Part: FLOOR SUPPORT — CORRODED (BS 237-303 BL 0) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 237 TO 303, BL 0, FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-3. ORIGINAL THICKNESS WAS .125 IAW DWG 5910137, MATERIAL LOSS OVER 50 PERCENT OUT OF LIMITS IAW SRM 53-01. REMOVED FLOOR SUPPORT STA 237-313 IAW SRM 51-30-5. FABRICATED AND INSTALLED NEW SUPPORT IAW SRM 51-30-5, P102 07 MAR 11. REQUIRED INSPECTION COMPLETED.

Part: BRACKET — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

AFT CARGO DOOR CUTOUT CENTER DOOR STOP T-BRACKET UNDER PAN HAS CORROSION. REMOVED CORRODED BRACKET IAW DC9 SRM 51-30-5. REMOVED CORROSION IAW DC9 SRM 51-10-3, FOUND OUT OF LIMITS. LOCATED AND DRILLED NEW BRACKET, P/N 4912460-501 IAW DC9 SRM 51-10-4. INSTALLED NEW BRACKET IAW DC9 SRM 51-30-5.

Part: FLOORBEAM — CORRODED (STA 200) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 200, RBL 24 TO 43 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-3. ORIGINAL THICKNESS WAS .060 IAW SRM 53-13-1, FIG 11, AFTER BLEND MATERIAL THICKNESS IS .010 OUT OF LIMITS IAW SRM 53-01. REMOVED SUPPORT IAW SRM 51-30-5. FABRICATED NEW SUPPORT IAW SRM 53-13-1, FIG 11. INSTALLED IAW SRM 51-30-5. REQUIRED INSP COMPLETED.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

MAIN CABIN STA 160 LBL 14 TO 53 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION IAW DC9-50 SRM 51-10-3. T = .060 7075 T6511 IAW DC9-50 SRM 53-13-1 FIG 11 & 51-10-1 FIG 22. 50% MATERIAL LOSS, OUT OF LIMITS IAW DC9-50 SRM 53-01 FIG 1. RECEIVED NEW MATERIAL PN S2652479 & AND 10137-0606 7075T6. FABRICATED & REPLACED FLOOR SUPPORT IAW DC9-50 SRM 51-10-2, 51-10-4, 51-30-1, 51-30-2, 51-30-5 & DWG #9910078.

Part: ANGLE — CRACKED (LT MLG WW) · airframe 71,333 hrs · 48,101 cycles

LEFT MLG WW LOWER HYD SHELF I/B OF GEAR DOOR AFT ATTACH BRACKET CRACKED. REMOVED CRACKED ANGLE IAW DC9 SRM 51-30-5. FABRICATED NEW ANGLE FROM 60-7330 IAW DC9 SRM 53-13-3 FIG 2. INSTALLED ANGLE IAW DC9 SRM 51-30-5 P102 13 MAR 11 REQUIRED INSPECTION COMPLETED Q968/280012 13 MAR 11.

Part: WEB — CORRODED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

OR PAN WEB HAS CORROSION AROUND SEVERAL RIVNUTS. GAIN ACCESS, CLEANED CORROSION. CORROSION FOUND TO BE OUT OF LIMITS. REMOVED WEB AND 4 EACH SPLICES. RECEIVED NEW WEB. LOCATED AND DRILLED, DEBURRED, TREATED, PRIMED, INSTALLED NEW WEB AND 4 EACH SPLICES IAW DC9 SRM 51-30-7, 51-10-3, 53-01, 51-10-4.

Part: FLOOR SUPPORT — DAMAGED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

AFT CARGO COMPT RT SIDE FLOOR SUPPORT HAS 1 EA FASTENER HOLE ON RADIUS AND SOME FASTENERS HOLES HAVE NO E.D. BETWEEN HOLES AT FRAME BS 1136.091. REMOVED CORR FROM INTERCOSTAL ORIG MAT, 040 REMOVED.002 REMAIN .038 FOUND TO BE IN LIMITS IAW DC9 SRM 53-01 FIG 1 SHT 3. RE-INSTALLED FLOOR SUPPORT, SPLICES, TIE DOWN TRACK, 4 EA NUT PLATES IAW DC-9 SRM 51-30-1, 51-10-3, 53-01 FIG 1 SHT 3, 51-30-2, 51-30-5.

Part: FLOOR SUPPORT — DAMAGED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

AFT CARGO COMPT LT SIDE FLOOR SUPPORT AT FRAME BS 1136.091 HAS DOUBLE DRILL FASTENERS HOLE'S, AT O/B AND ABOVE LONG 30. REMOVED & WELDED FLOOR SUPPORT IAW DC9 SRM 51-30-2 51-30-5 AND PEMCO TRAVELER N00837. RE-INSTALLED FLOOR SUPPORT IAW DC9 SRM 51-30-2 51-30-5.

Part: WEB — CRACKED (RT MLG WW) · airframe 71,333 hrs · 66,584 cycles

RIGHT WHEEL WELL WING STA XRS-58 WEB CRACKED APPROX 1/4 INCH. REMOVED DAMAGE BY CUTOUT NDT VERIFIED DAMAGE REMOVED PER NDT SPM 06-10-01-RECEIVED MATERIAL 7075-T6 .040 IAW DC-9SRM 51-60-0 FIG 1 SH 1, 53-53-0 FIG 8. FAB, LOCATED, DRILLED, DEBURRED, TREATED, PRIMED AND INSTALLED REPAIR DOUBLER AND FILLER IAW DC-9 SRM 53-53-0 FIG 8, 57-01 FIG 5 SHEET 01, 51-10-3.

Part: CARGO TRACK — CORRODED (CARGO BAY) · airframe 71,333 hrs · 66,584 cycles

AFT CARGO RIGHT TIEDOWN TRACK HAS CORROSION STA 889-1060. REMOVED CORROSION IAW DC9 SRM 51-10-3. ORIGINAL THICKNESS WAS.090 IAW DRAWING S2922357. AFTER BLEND THICKNESS IS .040, OUT OF LIMITS IAW DC9 SRM 53-05 FIG 4C. REMOVED TRACK IAW DC9 SRM 51-30-1. LOCATED AND DRILLED NEW TRACK, P/N S2922357 IAW DC9 53-23-0. INSTALLED NEW TRACK IAW DC9 SRM 51-30-1.

Part: STIFFENER — CRACKED (NR 1 PYLON) · airframe 71,333 hrs · 66,584 cycles

NR 1 ENGINE PYLON UNDER PANEL 8101A FWD STIFFENER CRACKED AT I/B END. REMOVED CRACKED STIFFENER ON NR 1 ENGINE PYLON UNDER PNL 8101A IAW DC-9 SRM 51-30-5, 51-30-2. FABBED, FORMED, DRILLED, COUNTERSUNK NEW STIFFENER FROM .040 2024-T3 IAW DC-9 SRM 54-10-0 FIG 1, 51-10-4. TREATED, PRIMED IAW DC-9 SRM 51-10-3. INSTALLED NEW STIFFENER IAW DC-9 SRM 51-30-5.

Part: SKIN — CRACKED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

FUSELAGE EXTERIOR STA 1209 BETWEEN L13L AND L12L SKIN CRACKED AT FASTENER. REMOVED FASTENER IAW SRM 51-30-02, VERIFIED CRACK IAW DC9 SRM 53-01 FIG 4. UPPER CUTOUT IS .890X 1.0", LWR CUTOUT IS .800 X 1.1", FABBED 1EA DOUBLER AND 2EA FILLERS IAW SRM 53-01 FIG 4 ORG MAT .040 2014 T6 IAW DC9 SRM 53-33-0 FIG 4 SUB .040 2014T6 .040 7075T6 IAW DC9 51-60-0 FIG 1 INSTALLED 2EA FILLERS 1EA DOUBLERS IAW DC9 SRM 53-01 FIG 4 AND DC9 SRM 51-30-02, 51-30-08.

Part: DOOR FRAME — CRACKED (CARGO BAY) · airframe 71,333 hrs · 66,584 cycles

FWD CARGO DOOR JAMB FWD UPPER CORNER HAS CRACK AT FASTENER. CUT OUT DAMAGE IAW DWG SR09530117. HFEC IAW NDT SPM 06-10-01.001 NO CRACKS NOTED ZETEC. FABRICATED DOUBLER FROM 2024-T3 .071 AND TRIPLER FROM 2024-T3 .090 IAW DWG SR 09530117. INSTALLED REPAIR PARTS IAW DWG SR 09530117 AND ER/A 490107-14AD. PERMANENT REPAIR REQUIRED WITHIN 24 MONTHS IAW ER/A 490107-14AD.

Part: DOUBLER — CHAFED (FUSELAGE) · airframe 71,333 hrs · 66,584 cycles

FUSELAGE EXTERIOR STA 1108 BETWEEN L14R AND L13R PREVIOUS REPAIR CHAFED. REMOVED AND REPLACED FUSELAGE EXT REPAIR DOUBLER STA 1108 BETWEEN L14R AND L13R. TITANIUM 6AL-4V IAW SRM 53-04 PG 6C FIG 3A SHT 3.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 1,520 hrs · 1,354 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 15-18 AND THE AFT LT OVERWING EXIT SIGN WERE INOPERATIVE. MX REPLACED THE BATTERIES. OPS CHECK WAS GOOD.

Part: LIGHT — DISCONNECTED (CABIN) · airframe 70,043 hrs · 65,462 cycles

DURING LINE CHECK MAINTENANCE FOUND EMERGENCY LIGHTS AT ROW 17 DEF INOP. MAINTENANCE RECONNECTED LIGHT ASSEMBLY, OPERATIONAL CHECK OF LIGHT NOW CHECK GOOD.

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 68,526 hrs · 64,164 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 23-26 OF THE CABIN WERE INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY LIGHT POWER SUPPLY AND OPERATIONALLY CHECKED THE SYSTEM.

Part: BATTERY — DISCHARGED (CABIN) · airframe 68,443 hrs · 64,095 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY FLOOD LIGHT FOR THE AFT EVACUATION SLIDE WAS NOT FUNCTIONAL. MAINTENANCE REPLACED THE BATTERIES. OPERATIONAL CHECK WAS GOOD.

Part: LIMITER — RUPTURED (LT MLG WW)

CREW REPORTED LOSING THE LT HYDR SYS FLUID QUANTITY AND PRESSURE DURING TAXI OUT FOR TAKEOFF. COM PROCEDURES WERE COMPLIED WITH AND THE ACFT RETURNED TO THE GATE WITHOUT ANY FURTHER PROBLEM. MX FOUND HYDR QUANTITY LIMITER IN THE LT WHEEL WELL HAD RUPTURED. THEY REPLACED THE FAILED FUSE, THE ENGINE DRIVE HYDR PUMP, AND ALL APPLICABLE HYDR SYS FILTERS (INCLUDING THE RETURN SYS FILTERS). NO DEBRIS WAS FOUND IN ANY FILTER OR PUMP HSG. LEAK CHECK AND OPS CHECK WERE GOOD AND THE ACFT WAS RETURNED TO SERVICE. (K)

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 67,093 hrs · 62,922 cycles

DURING LINE CHECK MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING FOR THE CATWALK IN THE TAIL COMPARTMENT WAS INOPERATIVE. MX REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: BATTERY PACK — DISCHARGED (EMERGENCY LIGHTS) · airframe 67,006 hrs · 62,836 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING FOR THE CATWALK IN THE TAIL COMPARTMENT WAS INOPERATIVE. MX REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 65,694 hrs · 61,666 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN THE TAIL COMPARTMENT WAS INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY BATTERY PACK AND OPERATIONALLY CHECKED THE SYSTEM. THE AIRCRAFT RETURNED TO SERVICE.

Part: CONTROLLER — FAILED (AUTO TEMP) · airframe 53,538 hrs · 59,739 cycles

DURING TAXI OUT CABIN AIR HOT. PACK CONTROL SWITCHED TO MANUAL AND FULL COLD. AT ROTATION CREW REPORTED SMOKE AND HEAT IN CABIN. FLIGHT RETURNED TO ATL FOR AN UNEVENTFUL LANDING. MAINTENANCE FOUND AUTO TEMP CONTROLLER BAD. MANUAL CONTROL WORKS OK. REPLACED TEMP CONTROL. OPERATION CHECKS GOOD.

Part: RIB — GOUGED (LT WING) · airframe 63,222 hrs · 59,454 cycles

DURING "L" CHECK, FOUND GOUGE ON THE INBOARD SURFACE OF THE LT WING LEADING EDGE NOSE RIB FORMER AT XOS 381.729. REPAIRED PER EA 98-207761.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 59,885 hrs · 56,549 cycles

DURING H-CHECK FOUND CRACK IN FLOORBEAM AT BS 674 LBL 5. REPAIRED PER EA 98-202520.

Part: SKIN — CRACKED · airframe 54,249 hrs · 51,304 cycles

During Accomplishment of a Hck in ATL, a crack was found on the Aft Pressure Bulkhead skin on hte left side of the aircraft just above the ventral door cutout. Repaired per EA 98-188225.

Part: FRAME — CRACKED · airframe 54,249 hrs · 51,303 cycles

During Mck in ATL, a crack was found in the area of the Verticle Access Cover, the crack was on the LH side of former P/n 9911986-11. Repaired per EA.98-185563.

Part: DOOR FRAME — CRACKED · airframe 54,249 hrs · 51,303 cycles

During Mck at Atl, the right hand Sta. 753 two small cracks were noted in the upper forward corner of the aft overwing exit doorjamb. Repaired per EA. 98-185539.

Part: DOOR — CRACKED (RT MLG) · airframe 53,753 hrs · 50,876 cycles

DURING WALK-AROUND AT MSP, THE RT MAIN LANDING GEAR DOOR WAS FOUND TO HAVE A 1.25 INCH CRACK COMMON TO THE FORWARD .050 INCH THICK DOOR PAN 9 INCHES INBOARD OF THE LATCH FITTING. REPAIRED PER EA 98-186641.

Part: SKIN — CRACKED (LT WING) · airframe 52,994 hrs · 50,205 cycles

DURING OVERNIGHT IN MSP, THE LT WING LEADING EDGE NOSE SKIN WAS FOUND WITH A 1.125 INCH CRACK FROM A FASTENER HOLE TO THE EDGE OF THE SKIN. DAMAGE IS LOCATED JUST OUTBOARD OF NR 2 L/E SLAT DRIVE ACTUATOR CUTOUT. REPAIRED PER EA 98-182743.

Part: CONTROLLER — MALFUNCTIONED (CABIN PRESSURE) · airframe 52,721 hrs · 49,975 cycles

AIRCRAFT LOST PRESSURIZATION AT FL280. CABIN ALTITUDE WENT TO 16,000 FT AND MASKS DEPLOYED. REPORTS OF SMOKE IN CABIN WERE UNFOUNDED, POSSIBLE CONDENSATION DUE TO RAPID DECOMPRESSION. FLIGHT DIVERTED TO YYZ AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED A DIRTY CABIN TEMPERATURE ANTICIPATOR. AIRCRAFT RETURNED TO SERVICE.

Part: FRAME — CRACKED (FUSELAGE) · airframe 51,312 hrs · 48,686 cycles

CRACKED FRAME WEB APPROX 1 INCH LONG AT FS 1292C 18L. REPAIRED PER SRM 53-01 FIG 2 WITH A VARIANCE GRANTED ON EA 98-177298. STOP DRILLED CRACK .25 INCH DRILL PASSIVATED DOUBLER.

Part: SKIN — CORRODED (FUSELAGE) · airframe 50,785 hrs · 48,178 cycles

MAUS SCANNED LOWER FUSELAGE L29 STA 1077-1082. CORROSION OUT OF LIMITS PER SRM. INSTALLED REPAIR PER EA 98-175410 AND SRM 53-04 FIG 12B. L/P 1447302.

Part: POWER SUPPLY — INOP (TAIL COMPT)

DURING LINE MAINTENANCE INSPECTION, FOUND TAIL COMPARTMENT EMERGENCY PATH LIGHTING INOPERATIVE. REPLACED POWER SUPPLY AND BATTERIES, OPERATIONAL CHECK NORMAL.

Part: PIN — INCORRECT PART (NLG)

NOSE LANDING GEAR DID NOT RETRACT AFTER TAKEOFF. CREW RECYCLED GEAR WITH SAME RESULTS. FLIGHT WAS RETURNED TO VPS AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND IMPROPER LOWER NOSE GEAR TORQUE LINK HINGE PIN INSTALLED. REMOVED AND INSTALLED CORRECT HINGE PIN. OPERATIONAL CHECK NORMAL ON SEVERAL GEAR CYCLES.

Part: FLASHLIGHT — INOPERATIVE (CABIN)

FLIGHT ATTENDANT REPORTED AN INOPERATIVE EMERGENCY FLASHLIGHT AT THE FORWARD FLIGHT ATTENDANT SEAT. MAINTENANCE REPLACED THE EMERGENCY FLASHLIGHT, OPERATIONAL CHECK OK.

Part: BATTERY PACK — DISCHARGED (CABIN)

DURING INSPECTION, THE AFT OVERHEAD EMERGENCY LIGHTS WERE FOUND TO BE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK, OPERATIONAL CHECK OK.

Part: MECHANISM — OUT OF ADJUST (PAX DOOR)

DOOR 1L DIFFICULT TO OPEN. ADJUSTED DOOR HEIGHT PER MM 52-11-00, OPERATIONAL CHECK OK.

Part: BATTERY PACK — DISCHARGED (CABIN)

DURING LINE CHECK, FOUND EMERGENCY LIGHTS INOPERATIVE ROWS 8 THROUGH 15. REPLACED BATTERY PACK, SYSTEM CHECKED OK.

Part: CLIPS — OUT OF ADJUST (TAIL CONE)

DURING LINE CHECK, FOUND THAT EXCESSIVE FORCE WAS REQUIRED TO REMOVE INTERIOR TAIL CONE RELEASE HANDLE FROM CLIPS. ADJUSTED CLIPS, FUNCTIONAL CHECK OK.

Part: CLIPS — OUT OF ADJUST (TAILCONE)

DURING LINE CHECK, FOUND THAT EXCESSIVE FORCE WAS REQUIRED TO REMOVE INTERIOR TAILCONE RELEASE HANDLE FROM CLIPS. ADJUSTED CLIPS. FUNCTIONAL CHECK OK.

Part: STRUT — REQD SERVICE (NLG)

AFTER TAKEOFF, AIRCRAFT WOULD NOT SHIFT FROM GROUND MODE, UNABLE TO RAISE GEAR. FLIGHT CONTINUED TO DTW AND LANDED WITHOUT INCIDENT. MAINTENANCE RESERVICED NOSE LANDING GEAR STRUT, GEAR OPERATIONAL CHECK OK.

Part: BATTERY — DISCHARGED (CABIN)

DURING LINE CHECK, FOUND EMERGENCY LIGHTS OVER FORWARD OVERWING EXITS INOPERATIVE. REPLACED BATTERIES AND OPERATION CHECKED GOOD.

Part: EXIT DOOR — NOT CLOSED (CABIN)

DURING CLIMB, FOUND INADEQUATE PRESSURIZATION CONTROL. FOUND THE AFT RIGHT OVERWING EMERGENCY EXIT NOT FULLY CLOSED. RETURNED TO DTW WITHOUT FURTHER INCIDENT. REINSTALLED AFT RIGHT OVERWING EMERGENCY EXIT, PRESSURIZATION CHECK OK.

Part: FITTING — CRACKED (DOOR STOP)

DURING H-CHECK, FOUND TWO CRACKS, 2 INCHES AND 2.25 INCHES IN THE AFT ENTRY DOOR UPPER LEFT AND RIGHT DOOR STOP FITTINGS. REPLACED FITTINGS PER EM 5270-01005 AND DWG J060229.

Part: FITTING — CORRODED (FS 701-708)

DURING H-CHECK, FOUND CORROSION ON THE LONGERON 29L KEEL FITTING BETWEEN FS 701 - 708. REPLACED FITTING PER SRM 51-10-4.

Part: BATTERY — DISCHARGED (CABIN)

DURING LINE MAINTENANCE INSPECTION, FOUND CEILING EMERGENCY LIGHTS AT ROWS 21 THROUGH 26 INOPERATIVE. REPLACED BATTERIES AT ROW 22R AND OPERATIONAL CHECK OK.