N782NC

Part: LANYARD — UNSECURE (R1 DOOR SLIDE) · airframe 73,212 hrs · 67,986 cycles

DURING LINE CHECK, MAINTENANCE FOUND THE R1 DOOR SLIDE LANYARD TO BE DETACHED FROM THE DOOR SLIDE COVER. MAINTENANCE SECURED THE 1R DOOR SLIDE LANYARD AND RETURNED THE AIRCRAFT TO SERVICE.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 71,293 hrs · 66,005 cycles

CABIN FLOOR PANEL HAS VERY SOFT SPOT IN ISLE AT ROW 11. REMOVED DAMAGED FLOOR PANEL 60C. REPLACED FLOOR PANEL IAW ERA 489362-14.

Part: ACM — OVERSERVICED (CABIN) · airframe 70,894 hrs · 65,633 cycles

ACFT RETURNED TO DEPARTURE DUE TO SMOKE IN THE CABIN. LAV SMOKE DETECTORS SOUNDED AND LT AIR COND SUPPLY TEMP HIGH LIGHT ILLUMINATED. QRH WAS COMPLIED WITH AND THE LT PACK WAS SHUTDOWN. MX RAN BOTH ENGINES AT TAKEOFF POWER AND CRUISE POWER FOR 5 MINUTES EA WITH NO FAULTS AND NO SMOKE. INSPECTED THE APU INLET AND NO CONTAMINATION FOUND. REPLACED THE LT AUG VALVE AND THE PRESSURE REGULATOR VALVE. FOUND BOTH ACMS OVERSERVICED AND CORRECTED. THE VALVES, ACMS, AND AIR COND SYS CHECK AND PURGE COMPLETED WITHOUT FURTHER PROBLEMS.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

FUSELAGE EXTERIOR POTABLE WATER DOOR CUTOUT AFT LOWER CORNER INNER DOUBLER IS CRACKED APPROX .75 INCH. CUT OUT DAMAGED PORTION OF DOUBLER, NO CRACKS NOTED. FABBED DOUBLER TITANIUM 6AL-4V .032" FILLER 2024-T3 .063". INSTALLED DOUBLER AND FILLER IAW DC-9-53-30-03-801-663A-A. CUT LONGERON NR 21 RT AT BS 473. INSTALLED SPLICE IAW DC-9 SRM 53-02.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

THE 1F/62 AFT ACC COMPT STA 1247 BETWEEN L1-L2R SHEAR TIE CRACKED. REMOVED AND REPLACED SHEAR TIE IAW SRM 51-11-00 114725. INSTALLED IAW DC9 SRM 53-03 FIG 3.P-127 284425.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

FWD CARGO DOOR CUTOUT STA 370-427 CORROSION ON WEB REMOVED CORROSION ORIG MAT .040 REMOVED .010 REMAINING .030 OUT OF LIMITS PER SRM 53-01. RECEIVED NEW WITH PART NUMBER 5910142U11. CUT OUT 2 06-10-001. FAB AND INSTALLED DOUBLERS .050 2024-T3 AND FILLER .040 2024-T3 PER ERA 490092-14. INSTALLED ID TAG PER DPS 900-5-1 NR 4.

Part: SKIN — CHAFED (LE SLAT) · airframe 1,749 hrs · 1,539 cycles

RIGHT WING NR 2 SLAT CENTER SLAT TRACK L/EDGE SKIN CHAFED I/B SIDE OF CUTOUT. BLENDED CHAFE 3"X 2". FOUND TO BE OUT OF LIMITS IAW DC9 SRM 57-01 WITH AN ORIGINAL THICKNESS .190 IAW DC9 SRM 57-31-1 AND A MAT LOSS OF .062. REMAINING THICKNESS .128 CUT OUT DAMAGE 1"X 1". FABRICATED REPAIR DOUBLER FROM .063 17-7PH & HEAT TREATED TO TH1050 & INSTALLED IAW SRP DC957-20-10-801-66EA. INSTALLED ID TAG PER DPS 900-5-1 NR 4.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN FLOOR PANEL 80 CRACKED ON EDGE. REMOVED DAMAGE ON FLOOR PANEL 1 X 2 INCHES PER ERA 490094-14 AND IAW DC9 SRM 53-01 FIG 4.NDT VERIFIED CRACK IS REMOVED IAW NDT SPM 06-10-01. FABBED REPAIR DOUBLER 3 X 2.5 INCHES & FILLER 2 X 1.5 INCHES. LOCATED AND DRILLED AND DEBURRED IAW DC9 SRM 51-10-4 & TREATED AND PRIMED IAW DC9 SRM 51-10-3 AND IAW DC9 SRM 51-30-2. INSTALLED ID TAG PER DPS 900-5-1 NO 4.

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN-FLOOR PANEL, NR 80, AFT END IS CRACKED AND HAS CORROSION AT FASTENER HOLE. REMOVED CORR & CRACK BY CUTTING OUT DAMAGE 11.5" X 5" IAW SRM 51-10-4 & 51-10-4 NDT. FOUND DAMAGE REMOVED IAW NDT SPM 06-10-01 FABRICATED REPAIR DOUBLER IAW SRM 53-23-0, FIG 6 & 51-70-4, FIG 1. TREATED AND PRIMED DOUBLER IAW SRM 51-10-3 & INSTALLED DOUBLER IAW SRM 51-30-2 & ERA 490094-14. REQUIRED INSP COMPLETED.

Part: INTERCOSTAL — CRACKED (BS 617-636 BL 0) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN BETWEEN STA 617 AND 636 BL-0 INTERCOSTAL CRACKED. REMOVED INTERCOSTAL IAW SRM 51-30-2. REMOVED CRACK IAW SRM 53-01, FIG 1. HFEC INSP IAW NDT SPM 06-10-01. VERIFIED CRACK REMOVED. FABBED REPAIR ANGLE AND FILLER FROM .025 FILLER AND .032 ANGLE IAW 53-13-2, FIG 4 51-70-5, FIG 1 AND DWG 5910766. TREATED IAW SRM 51-10-3 AND INSTALLED IAW SRM 51-30-2. INTERCOSTAL INSTALLED. REQ INSP COMPLETED.

Part: VANE — DELAMINATED (TE FLAP) · airframe 70,709 hrs · 65,469 cycles

LEFT WING CENTER FIXED FLAP VANE DELAMINATED 0N IB END. REMOVED L/WING FLAP CENTER FIXED VANE IAW DC-9 MM 27-51-03. REPLACED FLAP FIXED VANE DUE TO DELAMINATION OUT OF LIMITS PER TRAVELER 2477NO1195. INSTALLED NEW SERVICEABLE VANE IAW DC9 MM 27-51-03. OPS CHECK TO BE ACCOMPLISHED ON TASK CARD 2750-6542M-LT 117411.

Part: FLOOR PANEL — CORRODED (MAIN CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL NR 21 HAS CORROSION FASTENER HOLES. REMOVED CORROSION FROM FLOOR PANEL IAW SRM 51-10-3. FOUND TO BE OUT OF LIMITS. FABBED FLOOR PANEL & 2 EA HAT CHANNELS IAW SRM 51-10-2. DRILLED, COUNTERSUNK FASTENER HOLES IAW SRM 51-10-4. TREATED & PRIMED IAW SRM 51-10-3 AND ERA 1490086-14. INSTALLED ID TAG IAW ERA 490086-14, P-226. REQUIRED INSP COMPLETED.

Part: VANE — DELAMINATED (TE FLAP) · airframe 70,709 hrs · 65,469 cycles

RIGHT WING FLAP FIXED VANE NR 2 FROM I/B HAS SOME DELAMINATION ON UPPER SURFACE AT PREVIOUS REPAIR. REPLACED RT WING FLAP NR 2 FIXED VANE WITH NEW SERVICEABLE NR 2 FIXED VANE DUE TO DELAMINATION BEING UNREPAIRABLE IAW DC9 MM 27-03 ITEM 7 FIGURE 11 SHEET 2. INST NEW SERVICEABLE NR 2 FIXED VANE IAW DC9 MM 27-51-04. OPS CLEARANCE CHECK TO BE ACCOMPLISHED ON TASK CARD 2750-6542M-RT.

Part: FLOOR PANEL — CORRODED (MAIN CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL NR 79 HAS CORROSION AROUND EDGES AND 2 EA HAT CHANNELS CRACKED PARTS RACK 22B. REMOVED CORROSION FROM SEVERAL SPOTS IAW SRM 51-10-3. ORIG MAT .020 REMOVED, .010 REMAINING, .010 FOUND TO BE OUT OF LIMITS. FABRICATED NEW FLOOR PANEL IAW ERA 490088-14 FOR WEB, HAT CHANNEL. REQUIRED INSP COMPLETED.

Part: FLOOR PANEL — CORRODED (MAIN CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL NR 17 HAS CORROSION ON SKIN. PARTS RACK 22B. REPLACED FLOOR PANEL NR 17 WITH SERVICEABLE COMPOSITE FLOOR PANEL IAW DC-9 SRM 51-30-1, 51-10-4. P-109.

Part: FLOORBEAM — CRACKED (BS 617 LBL 1-18) · airframe 70,709 hrs · 65,469 cycles

MAIN PASSENGER CABIN-FLOOR SUPPORT CRACKED STA 617 LBL1 TO LBL18. REMOVED CRACKED FLOOR SUPPORT/ZEE IAW SRM 51-30-2. FABRICATED NEW FLOOR SUPPORT/ZEE FROM .050 2024T3 PO 1120351 IAW SRM 53-13-3 FIG 4 SHEET 1 AND 2 AND 51-10-4. INSTALLED NEW FLOOR SUPPORT/ZEE IAW SRM 51-30-2.

Part: SKIN — DAMAGED (BS 370 L22R) · airframe 70,709 hrs · 65,469 cycles

DURING INSPECTION OF LIGHTNING STRIKE MONITORS FOUND AREAS OF PREVIOUS BLENDS ON FASTENER HEADS AND SKIN STA 370 L22R. BLENDED LIGHTNING STRIKE PER DWG NR S60590000.ORIG .050 PER SRM 53-33-0 FIG 2. LOST .016 PER NDT SPM 04-00-06. REMAINING.034, FOUND TO BE OUT OF LIMITS PER SRM 53-01. FABBED DOUBLER .032 AND FILLER .050 PER SRM 51-10-4, DWG S60590001. INSTALLED ALL REPAIR PARTS PER SRM 51-30-1,51-30-5 AND DWG SG0590001.

Part: CUSP WEB — CRACKED (BS 694) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STA 694 RIGHT SIDE CUSP WEB CRACKED UNDER HORSESHOE COLLAR. REMOVED AND INSTALLED CUSP WEB FROM 693-753 IAW DC9 SRM 51-30-2. FABBED NEW WEB USING 7075-T6 .020. FABBED AND INSTALLED RING DOUBLER USING .050 7075T6, .080 7075T6, .090 7075T6 IAW DWG SG09530019.

Part: ATTACH ANGLE — CRACKED (BS 1167) · airframe 70,709 hrs · 65,469 cycles

MAIN PASSENGER CABIN STA 1167 APB RT BOTTOM HORIZ SUPPORT OTBD BOTTOM ATTACH ANGLE CRACKED. REMOVED ATTACH ANGLE FROM HORIZ SUPPORT IAW DC-9 SRM 51-30-02 AND SRM 51-30-05. TRIM CRACK IAW DC-9-A-53-10-25-801-663A-A NDT SPM 01-10-01.001. CRACK WAS 04, DC9-A-53-10-25-801-663A-A. TREATED AND PRIMED IAW DC9 SRM 51-10-3. INSTALLED CLIPS, PADS AND FILLER IAW DC9-A-53-10-25-801-663A-A.

Part: CUSP WEB — DAMAGED (BS 680) · airframe 70,709 hrs · 65,469 cycles

FOUND ELONGATED HOLES IN CUSP AT STA 680 RT CUSP AT ZEE SPLICE. REMOVED AND INSTALLED CUSP WEB FROM STA 674-693 IAW SRM 51-30-2. FABRICATED NEW WEB FROM .020 7075T6. FABRICATED AND INSTALLED RING DOUBLERS USING .050 7075T6.063 7075T6, .080 7075T6.O90 7075T6 IAW DWG3SG09530019. INSTALLED ZEE ANGLE AND 2 SPLICE IAW DC9 SRM 51-30-05. P-239.

Part: CARGO TRACK — CORRODED (BS 427-579) · airframe 70,709 hrs · 65,469 cycles

FWD CARGO SURFACE CORROSION ON RT TIE DOWN TRACK FROM STA 427-579. REMOVED CORROSION FROM TIEDOWN TRACK 50 PERCENT MATERIAL LOSS. FABRICATED 2 SPLICES FROM .071 7075-0, HEAT TREATED ON TRAVELER 2477NO1494 TOM T-6 IAW AMS 2770. INSTALLED TIE DOWN TRACK IAW SRM 51-30-01, 53-05 FIG 4C, 53-05 FIG 4.

Part: FRAME — CORRODED (STA 579 L26-27R) · airframe 1,749 hrs · 1,539 cycles

STA 579 BET L 26-27 RT CORROSION FOUND UNDER TIE DOWN TRACK ON FRAME. REMOVED CORROSION PER SRM 53-01 FIG 1. MATERIAL LOSS OUT OF LIMITS PER SRM 53-01 FIG 1. REMOVED FORMER PER SRM 51-30-2, ORG MAT .063 2024-T6 PER SRM 53-13-2 FIG 2. MATERIAL SUBSTITUTED PER SRM 51-60 FIG 1. FABRICATED FORMER PER SRM 51-10-2. LOCATED AND DRILLED PER DC9 SRM 51-10-4 7075T6. TREATED AND PRIMED PER SRM 51-10-3. INSTALLED PER SRM 51-30-5.

Part: ATTACH FITTING — CRACKED (BS 579) · airframe 70,709 hrs · 65,469 cycles

C-1 PIT STATION 579 RT TIE DOWN TRACK ATTACH FITTING CRACKED. REMOVED CRACKED TIE DOWN TRACK ATTACH FITTING IAW SRM 51-30-5. RECEIVED NEW FITTING PN 5956034-557. LOCATED AND DRILLED AND DEBURRED FITTING DC9 SRM 51-10-4. TREATED 2 HOLES IAW SRM 51-10-3 AND INSTALLED FITTING IAW SRM 51-10-5. REQUIRED INSPECTION COMPLETED.

Part: FRAME — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

AFT ACCESSORY COMPARTMENT STA 1209 L13R FRAME WEB CRACKED. REPAIRED CRACKED WEB AT AFT ACC COMPT IAW DC-9 SRM 51-70-4 FIG 2. REMOVED CRACKED WEB SECTION FROM STR 10R-14 STA 1209. FABRICATED NEW WEB SECTION. ALODINED, PRIMED, INSTALLED WEB ATTACH PARTS IAW ERA 8788 AND SRM 51-70-4. WEIGHT OF REPAIR PARTS IS 2.9 LBS IAW SCALE H7322 DUE DATE 17 JUN 11..040 7075T6 LOT 1023415 NDT SPM 06-10-01.001. REQUIRED INSPECTION COMPLETED.

Part: ATTACH FITTING — CRACKED (BS 579) · airframe 70,709 hrs · 65,469 cycles

C-1 PIT STATION 579 RT TIE DOWN TRACK ATTACH FITTING CRACKED. REMOVED CRACKED TIE DOWN TRACK ATTACH FITTING IAW SRM 51-30-5. RECEIVED NEW FITTING PN 5956034-557. LOCATED, DRILLED AND DEBURRED FITTING IAW SRM 51-10-4. TREATED 2 HOLES IAW DC9 SRM 51-10-3 AND INSTALLED FITTING IAW SRM 51-10-5. REQUIRED INSPECTION COMPLETED.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN-FS 200-240 RBL 22 SEAT TRACK HAS 1 MISDRILLED HOLE. REMOVED DAMAGED SEAT TRACK. RECEIVED NEW SEAT TRACK PN52772660 PO 1022910 IAW DC-9 SRM 53-23 FIG 3 PAGE 4. TRIMMED, LOCATED, DRILLED AND INSTALLED IAW DC-9 SRM 51-10-04 AND 53-05 FIG 4E PAGE 32.P-226 REQUIRED INSPECTION COMPLETED.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STA 753 LEFT LONGERON 18 JUST BELOW FLOOR MAIN FRAME CRACKED APPROX 2 INCHES ON FWD SIDE NDT VERIFIED #A2700. REPLACE MAIN FRAME PN 9923407-501N STA 753 //H IAW DC9 SRM 51-01 AND ENGINEERING REPAIR/AUTHORIZION #486359-14. REQUIRED INSPECTION COMPLETED.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN FLOOR PANEL 102C CRACKED AT FASTENER HOLE. TRIMMED OUT CRACKED AREA IAW DC-9 SRM 53-05. FABRICATED DOUBLER AND FILLER FROM .032 7075T6 IAW DC-9 SRM 53-05 PO NR 1022537. TRIMMED OUT AREA 1 INCH 1.9 INCH TOOL NR 9573 .1 OZ DOUBLER AND FILLER .3 OZ NDT VERIFIED CRACK CONTAINED IAW NDT SPM 06-10-01.001. INSTALLED IAW DC-9 SRM 51-30-2. REQUIRED INSPECTION COMPLETED.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL NR 99 HAS CORROSION AROUND FASTENER HOLES. PARTS RACK 22B. FABRICATED NEW PANEL FROM .025 7075-T6 SKIN AND HAT CHANNEL PN S2912282FT IAW DOUGLAS DRAWING NR 9957930 AND ERA 2477N01382. REQUIRED INSPECTION COMPLETED.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FORWARD WET AREA STA 256-275 LBL 18 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION 1 INCH BY 3 INCH IAW DC9 SRM 51-10-3 ORIG MATL .060, FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG1. REMOVED FLOOR SUPPORT IAW DC9 SRM 51-30-1 AND 51-30-5. LOCATED DRILLED DEBURRED AND INSTALLED FLOOR SUPPORT USING 52652479 IAW DC9 SRM 51-30-1 51-30-5 AND 51-10-4 L RESPRESS 465885 PEMCO CO-SIGN P106.

Part: FRAME — CHAFED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

AFT ACCESSORY COMP LT SIDE CANTED FRAME STA 1139 AFT SIDE HAS DEEP CHAFE. BLENDED CHAFE ON LT SIDE CANTED FRAME IAW DC-9 SRM 51-10-3. ORIG MAT .063 REMOVED OVER 50 PERCENT MAT OUT OF LIMITS IAW DC-9 SRM 53-01 FIG 1. REMOVED FRAME IAW DC-9 SRM 51-30-1. LOCATED, DRILLED, DEBURRED NEW FRAME IAW DC-9 51-10-4. INSTALLED FRAME IAW DC-9 SRM 51-30-5, SRM 51-30-2, SRM 51-30-1. REQUIRED INSPECTION COMPLETED.

Part: FRAME — CHAFED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

AFT ACCESSORY COMP RT SIDE CANTED FRAME STA 1339 AFT SIDE HAS DEEP CHAFE. BLENDED CHAFE AREA ORIG MAT .063 LOST OVER 50 PERCENT MATERIAL. FOUND TO BE OUT OF LIMITS PER DC-9 SRM 53-01. REMOVED AND REPLACED CANTED FRAME PER DC-9 SRM 51-30-2, 51-30-5, 51-30-1. REQUIRED INSPECTION COMPLETED.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 70,709 hrs · 65,469 cycles

6C/298 CABIN FLOOR PANEL NR 98 CRACKED AT AFT INBOARD CORNER. TRIMMED OUT CRACKED AREA 3 1/8 INCH BY 2 3/8 INCH PER DC9 SRM 53-05 FIG 1. HFEC CHECK COMPLETED PER NDT SPM 06-10-01. VERIFIED CRACK REMOVED. FABRICATED NR 2 DOUBLER AND FILLER. INSTALLED DOUBLER AND FILLER PER DC-9 SRM 53-05 FIG 1 AND 51-30-2. REPAIR WEIGHT 23 OZ PER H9573. INSTALL REPAIR TAG PER PS 900-05-1. REQUIRED INSPECTION COMPLETED.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 70,709 hrs · 65,469 cycles

6C/203 MAIN CABIN METAL FLOOR PANEL NR 26 HAS CORROSION AROUND FASTENER HOLES PARTS RACK 22B CPCP TASK 58-53303 RII: Y. REMOVED CORROSION FROM END OF PANEL NR 26. AREA 1 INCH BY 11 1/2 INCH ORG THICKNESS 0.020 REMOVED 0.010 REMAINING 0.010. OUT OF LIMITS CUT OUT DAMAGED AREA. LOCATED AND DRILLED PANEL SECTION AND INSTALLED REPAIR PARTS IAW DC9 SRM 53-05 FIG 1 AND ERA-4190087-14. INSTALLED TAG IAW DSP 900-5-1 NR 4. P-117 REQUIRED INSPECTION COMPLETED.

Part: SUPPORT ANGLE — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

6C/161 MAIN CABIN LBL-44 BETWEEN STA 750 AND 770 SUPPORT ANGLE FROM WEB TO CENTER TANK CRACKED AT FASTENERS. REMOVED, ORDERED, AND INSTALLED NEW ANGLE PART NR 5410464U23 IAW DC-9 SRM 51-01 AND 51-30-5,1, PC AND DAC DWG 5910414P-226 Q-967 284419.

Part: FLOOR PANEL — CORRODED (COCKPIT) · airframe 70,709 hrs · 65,469 cycles

6C/85 COCKPIT FLOOR PANEL NR 14 HAS CORROSION AT AFT END CPCP 46-53303. FABRICATED NEW FLOOR PANEL FROM .025 7075-T6 PO 1120200 AND HAT CHANNELS S2912282 PER ER 489365-14 P-226 Q-967 284419 Q-967 284419.

Part: FRAME — CORRODED (BS 110) · airframe 70,709 hrs · 65,469 cycles

1C/30 ACCESS FROM COCKPIT-UPPER FACE OF PRESSURE PANEL BELOW RUDDER PEDAL STA 110 JUNCTURE AT FUSELAGE FRAME HAS CORROSION AT RT END OF ANGLE 4 INCHES BY 3 INCHES CPCP TASK 45-53302. FABRICATED AND INSTALLED NEW ANGLE IAW DOUGLAS DRAWING NR 3911397 AND DC-9 SRM 51-30-5.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

6C/194 MAIN CABIN APPROXIMATELY STATION 1134 RT CUSP WEB CRACKED AT AFT HOLE. REMOVED AND REPLACED CUSP WEB STA 1068-1136 IAW DWG SG09537 PN 09-5300-3-3408. REQUIRED INSPECTION COMPLETED.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

6C/299 MAIN CABIN-FS 1136 LBL 1 TO LBL 22 FLOOR SUPPORT IS CRACKED AT INBD END APPROX 1.5 IN. RII: Y. REMOVED DAMAGED ANGLE. FABBED NEW ANGLE IAW DC9 SRM 53-13-3 AND SRM 51-10-4 AND INSTALLED PER DC9 SRM 51-30-02 AND 51-30-05 AS REQ`D, P-109. REQUIRED INSPECTION COMPLETED.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL 60C HAS ELONGATED HOLES AND NO ED PARTS RACK 22B. FABRICATED NEW FLOOR PANEL FROM .025 7075-T6 AND HAT CHANNELS IAW ERA 489362-14.P-226 Q-971. REQUIRED INSPECTION COMPLETED BY Q-971 280318.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN-FS 218-275 RBL 45 SEAT TRACK HAS CORROSION ON UPPER SURFACE. FOUND CORROSION TO BE BEYOND BLEND OUT LIMITS. REMOVED AND REPLACED TRACK STA RBL 45 AT STA 200-280 RT SIDE AS REQ PER DC9 SRM 51-30-05 AND SRM 53-23-0.P-183. REQUIRED INSPECTION COMPLETED BY Q-967 284419.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 70,709 hrs · 65,469 cycles

CABIN COMPOSITE FLOOR PANEL 17 DOES NOT LINE UP WITH HOLES IN A/C. REPAIRED HOLES ON PANEL NR 17 IAW DC9A-53-22-01-801-663A-A AND LOCATED AND DRILLED HOLES IAW DC9 SRM 51-10-4. INSPECTION COMPLETED BY Q-953 186938.

Part: CUSP WEB — PUNCTURED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN PAX CABIN RT SIDE CUSP WEB HAS 1 PUNCTURE APPROX 1/4 INCH DIA AT FUS FRAME STA 351 RBL 57 IN. REPAIRED PUNCTURE AT STA 351 RBL 57 IAW SRM 53-01 FIG 1 SHEET 3.

Part: FLOOR PANEL — GOUGED (CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL NR 55 END HOLES GOUGED PARTS RACK22B. FABRICATED NEW BOTTOM PIECE WITH IAW DC9 SRM 51-10-4 AND 53-23-0 FIG 4. TREATED AND PRIMED IAW DC9 SRM 51-10-3. REQUIRED INSPECTION COMPLETED BY Q-967 284419.

Part: LONGERON SPLICE — CORRODED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

FORWARD CARGO L29L BETWEEN STA 636 AND 655 LONGERON SPLICE HAS CORROSION. REMOVED CORROSION ON SPLICE. FOUND TO BE OUT OF LIMIT. RECEIVED NEW LONGERON SPLICE ON TRAVELER 2477NO1509.LOCATED AND DRILLED AND DEBURRED THE HOLES PER DC9 SRM 51-10-4. TREATED, PRIMED AND PAINTED. INSTALLED NEW SPLICE PER DC9 SRM 51-30-05, 51-30-01 SRM 51-10-3 SRM 53-01 FIG 1 SHEET 1 AND 2.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL NR 73 HAS CORROSION AROUND FASTENER HOLES AND 1 PUNCTURED HOLE PARTS RACK 22B. REMOVED CORROSION ON FLOOR PANEL NR 73. FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-03. ORIGINAL MATERIAL .020 MATERIAL LOSS ON BOTH REPAIRS .010. REMOVED DAMAGE ON BOTH AND FABRICATED AND INSTALLED FILLER AND DOUBLER IAW DC9 SRM 51-70-4, P-226 REQUIRED INSPECTION COMPLETED BY Q-967 284419.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STATION 427 L16L IS CRACKED. REMOVED LONGERON SECTION FROM STA 360 TO 434 AT EXISTING SPLICES. INSTALLED NEW SECTION OF LONGERON FROM S2777922-1 AND SPLICES IAW DC9 SRM 53-02 FIG 18, P-226. REQUIRED INSPECTION COMPLETED BY Q-995 485522.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STATION 484 L17L IS CRACKED. REMOVED DAMAGED L17L STA 455-513. EXISTING SPLICE TO EXISTING SPLICE. REPLACED SECTION L17L WITH NEW. REINSTALLED 2 SPLICES 56 INCHES TOTAL IAW DC9 SRM 53-13-2 FIG 3, 51-10-4, 51-10-3, 51-10-0, 51-30-2, 51-30-5. TAGGED DELTA PS 900-5-1 NR 4.

Part: SKIN — CORRODED (FLOOR PANEL) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL NR 24 HAS CORROSION ON SKIN. PARTS RACK 22B ORDERED AND RECEIVED NEW FLOOR PANEL NR 24. LOCATED AND DRILLED FASTENER HOLES IAW DC9 SRM 57-10-4 284419.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

NLG RIGHT AFT DOOR HINGE CUTOUT CRACKED APPROX 1/2 INCH. REMOVED DOUBLER. FABRICATED AND INSTALLED NEW DOUBLER FROM .050 7075-T6 IAW DC9 SRM 53-05 FIG 62, P-226. REQUIRED INSPECTION COMPLETED.

Part: PAN — CORRODED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

AFT CARGO DOOR CUTOUT LOWER PAN HAS CORROSION IN SEVERAL PLACES. REMOVED CORROSION FROM LOWER JAM PAN AFT CARGO DOOR IAW DC-9 SRM 53-01. ORIG MAT .050 .017 REMAINING .033. FOUND TO BE OUT OF LIMITS IAW DC-9 SRM 51-01 AND 53-13-3. REMOVED LOWER JAM PAN IAW DC9 SRM 51-30-2 AND 51-30-5. RECEIVED NEW LOWER JAM PAN LOCATED AND DRILLED IAW DC9 SRM 51=10-4. INSTALLED NEW JAM PAN IAW DC-9 SRM 51-30-2 AND 51-30-5.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL 60D HAS ELONGATED HOLES. PARTS RACK 22B ORIGINAL MAT .025 7075-T6 FOR SKIN AND EXT 52912282 PER DWG NR 9923615. REC.025 7075-T6 AND EXT S2412282 FABRICATED SKIN AND HAT SECTIONS PER DC9 SRM 51-10-2 AND DWG 9923615 LOCATED, DRILLED AND COUNTERSUNK PER DC9 SRM 51-10-4 AND 51-10-2. TREATED AND PRIMED PER DC9 SRM 51-10-3. STENCILED PER ERA 489638-14.REPAIR TAG PER PS 900-05-1.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN FLOOR PANEL NR 31 FWD END HAS CORROSION ON UPPER AND LOWER SURFACE. REMOVED CORROSION FROM PANEL AT FORWARD END-OUT OF LIMITS IAW DC-9 SRM 53-01 FIG 1, 53-23-0 FIG 4. REMOVED DAMAGED AREA. HFEC INSPECTION IAW DC-9 NDT SPM-06-10-01.001. DAMAGE REMOVED, REPAIRED PANEL IAW DC-9 SRM 51-70-4.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL NR 53 END HOLES ELONGATED AND CRACKED. PARTS RACK 22B CUT OUT DAMAGE PER DC9 SRM 51-70-4. ORIG MAT .025 7075-T6 PER DC9 SRM 53-23 FIG 4. REC MAT .032 7075-T6. FABRICATED NEW PANEL SECTION PER DC9 SRM 51-70-4 AND 51-10-2. TREATED AND PRIMED PER DC9 SRM 51-10-3. INSTALLED PER DC9 SRM 51-70-4 AND 51-30-2. INSTALLED REPAIR TAG PER DPS 900-5-1.

Part: SKIN — GOUGED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

SKIN AND REPAIR DOUBLER GOUGED AT AFT CARGO DOOR CUTOUT STA 1100 L24R. REMOVED OLD DOUBLERS AND FILLERS THAT WERE GOUGED ON SIDE OF REPAIR. FABRICATED NEW DOUBLER AND 2 FILLERS. LOCATED, DRILLED, TREATED, INSTALLED IAW DC9 SRM 51-30-02, 51-30-05, 51-10-03, 51-10-4, 53-35-0 FIG 3, 53-05 FIG 80, 51-30-01.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STATION 1133 AT L18L CUSP WEB IS CRACKED 2 PLACES AT AFT HOLE. DAMAGED CUSP WEB WAS REMOVED IAW DC9 SRM 51-30-1, 51-30-2 AND BOEING DRAWING SG09530019. CUSP WAS TREATED, PRIMED IAW DC9 SRM 51-10-3. INSTALLATION WAS IAW SRM 51- 30-2, 51-30-5, BOEING DRAWING SG 09530019.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

AFT ACC COMPARTMENT STA 1230 BETWEEN L15L-L17L SHEAR TIE CRACKED. REMOVED CRACKED SHEAR TIE STA 1230 BETWEEN LONGERON 15L AND 17L IAW DC-9 SRM 51-30-2 AND 51-30-5. NEW SHEAR TIE LOCATED, DRILLED, DEBURRED, TREATED HOLES AND TOUCH UP PRIMER IAW DC9 SRM 51-10-3, 51-10-4. INSTALLED SHEAR TIE IAW DC-9 SRM 51-30-5. MD DAILY 490493 064365 P-226. REQUIRED INSPECTION COMPLETED BY Q-974 284652.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN FLOOR PANEL NR 19 DELAMINATED PARTS RACK 22B. FABRICATED NEW FLOOR PANEL 9957823-175 FROM .040 AND HAT CHANNELS IAW DRAWING 9957823 PER ERA 489360-14, P-226 Q-987 284650.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STATION 200 L2L CRACKED. REMOVED DAMAGED SECTION 13.625 INCH. RECEIVED NEW SECTION AND INSTALLED .040 AND 2 SPLICES SECTIONS IAW 53-02 FIG 18, P-226. REQUIRED INSPECTION COMPLETED BY Q-995 485522.

Part: FRAME — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

FUSELAGE EXTERIOR CANTED FRAME STA 1303 AT L14R SKIN CRACKED AT FASTENER. REPAIRED CRACKED SKIN AT FUSELAGE EXTERIOR CANTED FRAME STA 1303 AT L14R IAW DC9 53-01 FIG 4, 51-10-4, 51-30-2, 51-30-5. MAT USED FOR REPAIR 7075-T6 .040 DOUBLER AND SKIN 7075-T6 .040 IAW DC9 53-33-0, 51-60-0 ID TAG INSTALLED PER DPS 900-5-1 NR 04.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STATION 313 L17R IS CRACKED. REMOVED L17R STA 285TO 342 AND 2 SPLICES. TRIMMED, LOCATED, DRILLED, TREATED AND PRIMED LONGERON SEALED AND INSTALLED LONGERON AND 2 SPLICES. APPLIED REPAIR TAGS. ALL WORK ACCOMPLISHED IAW DC9 SRM 51-10-3, 51-10-4, 51-30-2, 51-30-5, 51-20-00, 53-02 FIG 18 AND DPS 900-5-1 N04.J

Part: LONGERON — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STA 351 LONGERON 17L IS CRACKED. REMOVED FORWARD AND AFT SPLICE. TRIMMED LONGERON GAP IS NOW .125 FORWARD AND AFT AND INSTALLED IAW SRM DC9 51-30-05 AND 53-02 FIG 18 SHEET 1 PAGE 50.B 487521 117542 17 FEB 11 P-117. REQUIRED INSPECTION COMPLETED BY Q-967 284419.

Part: PAN — CRACKED (BS 734-735) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN WINDOW PAN CRACKED IN TOP FWD CORNER AT FASTENERS BETWEEN STA 734 AND 735 LT SIDE. CUT OUT DAMAGED AREA. NDT VERIFIED CRACKED CONTAINED. WEIGHT REMOVED 2 GRAMS MAT ID FOR REPAIR & FILLER 7075-T6 .063 FOR ANGLE 2024-T3, .040 FOR FILLER & INSTALLED IAW DC9-56-20-02-801-663A-A. ADDED WEIGHT 26 GRAMS IAW TOOL NR H9573. INSTALLED ID TAG IAW PS NR 900-5-1-110-04.

Part: INTERCOSTAL — CRACKED (BS 148-160 L9R) · airframe 70,709 hrs · 65,469 cycles

MAIN PASSENGER CABIN BETWEEN STA 148-STA 160, L9R FITTING CRACKED AT WIRING CONDUIT HOLE. REPAIRED CRACKED INTERCOSTAL USING .063 301 1/2 HARD STAINLESS STEEL SHEET 0722363 IAW SRM 53-05, FIG 100 SHTS 1 & 2. REQUIRED INSP COMPLETED.

Part: PAN — CRACKED (BS 775-794) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN WINDOW PAN CRACKED IN TOP AFT CORNER AT FASTENER BETWEEN STA 775 AND 794 RT SIDE. REMOVED OLD CLIP. RECEIVED NEW CLIP MAT ID FOR FILLER 2024-T3 .040 IAW DC9-56-20-02-801-663A-A. FABED & INSTALLED IAW DC9-56-20-02-800- 663A-A.ADDED WEIGHT 2 GRAMS IAW TOOL H9573. INSTALLED ID TAG IAW DELTA PS 900-5-1 NR 4. REQUIRED INSP COMPLETED.

Part: CUSP WEB — CRACKED (BS 1100) · airframe 70,709 hrs · 65,469 cycles

MAIN PASSENGER CABIN STA 1100 LT CUSP WEB CRACKED AT FRAME FITTING. CUTOUT DAMAGED SECTION 3" X 4" IAW SRM 51-10-4 & DWG SG09530019 FABRICATED & INSTALLED REPAIR DOUBLER WEIGHING 120 GRAMS & FILLER IAW DWG NR SG09530019 & SRM 51-30-2, 51-30-5. P239 REQUIRED INSP COMPLETED.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN PASSENGER CABIN STA 1167 APB RT TOP HORIZONTAL SUPPORT O/B ATTACH ANGLE CRACKED. REMOVED AND REPLACED FORMER. IAW DC-9 SRMS 51-10-4, 51-10-5, 51-30-2 AND 51-20-0.

Part: FRAME — CRACKED (BS 180 L4L) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STA 180, FRAME IS CRACKED AT L4L, ABOVE L-1 DOOR. STOP DRILLED CRACK IAW SRM 53-01, FIG 2 FABRICATED ANGLE, FILLER, GUSSET AND SHIM. LOCATED AND DRILLED ALL REPAIR PARTS IAW SRM 53-03, FIG 36, SHEET 1 &51-10-2 INSTALLED IAW SRM 53-03, FIG 36. REQUIRED INSP COMPLETED.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN...STATION 1054 RBL 55 CRACK AT FASTENER HOLE UNDERNEATH FIBERGLASS "Z" ANGLE AS MARKED. CUTOUT DAMAGED SECTION 1 INCH BY 1 INCH IAW DC-9 SRM 51-10-4 AND DWG NR SG9530019. FABRICATED CUSP WEB REPAIR IAW DC-9 SRM 51-10-4 AND DWG NR SG9530019 AND INSTALLED CUSP WEB REPAIR IAW DC-9 SRM 51-30-2,51-30-5 AND DWG NR SG530019.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL 102C HAS CORROSION AROUND FASTENER HOLES, 2EA HAT CHANNELS CRACKED AND END SKIN TORN. REMOVED CORROSION IAW SRM 53-01 FIG 1 ORIGINAL MATERIAL .032" REMOVED .002 FOUND TO BE WITHIN LIMITS IAW SRM 53-01 FIG 1. REMOVED DAMAGED AREAS OF 3EA HAT CHANNELS AND SKIN PANEL IAW SRM 53-05. INSTALLED HAT CHANNELS AND SPLICES IAW SRM 51-30-02. INSTALLED FILLER AND DOUBLER IAW SRM 53-05 FIG 1 P226.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL 60B HAS ELONGATED HOLES AND 2EAHAT CHANNELS CHAFED. BLENDED HAT CHANNELS OUT OF LIMITS IAW SRM 53-01 FIG 1. FABRICATED 2EA HAT CHANNEL SPLICES. CUT AND TRIMMED 2EA HAT CHANNELS. INSTALLED 2EA HAT CHANNELS AND SPLICES IAW SRM 51-30-2, 51-30-8. CUTOUT DAMAGED AREA IAW 53-05 FABRICATED NEW DOUBLER AND FILLER IAW SRM 53-05 FIG 1. INSTALLED FILLER AND DOUBLER IAW SRM 53-05 FIG 1 P239.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STATION 237 AT L18L FLOOR PANEL SUPPORT CRACKED. REMOVED AND REPLACED SECTION OF SUPPORT ZEE ANGLE IAW DC9 A-53-2 0-01-801-663A-A. NEW ZEE ANGLE 2EA SPLICE FABRICATED IAW DC9A-53-20-01-801-663A-A P226.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL 60A 1EA HAT CHANNEL CRACKED AND CORNER SKIN CRACKED. CUTOUT DAMAGED SECTION OF HAT CHANNEL IAW DC9 SRM 51-10-2. FABRICATED, LOCATED AND DRILLED HAT CHANNEL AND REPAIR SPLICE IAW DC9 SRM 53-05 FIG 1. CUTOUT DAMAGE OF FLOOR PANEL 1"X1" IAW DC9 SRM 53-01 FIG 4. LOCATED DRILLED FILLER & DOUBLER IAW DC9 SRM 51-10-4. INSTALLED FILLER & DOUBLER IAW DC9 SRM 51-30-2 & 53-01 FIG 4.

Part: CARGO TRACK — CORRODED (BS 218-300) · airframe 70,709 hrs · 65,469 cycles

FWD CARGO SURFACE CORROSION ON RT TIE DOWN TRACK FROM STA 218-300. BLENDED CORROSION, BLEND OUT OF LIMITS IAW SRM 53-05, PG 29, FIG.4C. R & R CARGO TIE DOWN TRACK IAW SRM 51-30-2 AND 51-30-1. REQUIRED INSP COMPLETED.

Part: CARGO TRACK — CORRODED (BS 300-363) · airframe 70,709 hrs · 65,469 cycles

FWD CARGO SURFACE CORROSION ON RT TIE DOWN TRACK FROM STA 300-363. BLENDED CORROSION, BLEND OUT OF LIMITS IAW SRM 53-05 FIG 4C. R & R TIE DOWN TRACK IAW SRM 51-30-1. REQUIRED INSPECTION COMPLETED.

Part: FLOORBEAM — CORRODED (BS 200 RBL44-57) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STA 200, RBL 44 TO 57 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION 11" IAW SRM 51-10-ORIG MAT .060 IAW SRM 53-13-1, FIG 4 AND 51-10-14 S-.22 MAT LOSS REMAINING 53-01, FIG 1. R & R FLOOR SUPPORT 116441. REQUIRED INSP COMPLETED.

Part: FLOOR SUPPORT — CORRODED (BS 1116-1136) · airframe 70,709 hrs · 65,469 cycles

MAIN PASSENGER CABIN BETWEEN STA 1116-1136, BL 0, FLOOR SUPPORT CORRODED. REMOVED CORROSION WAS .056 REMAIN MAT .02 REMOVED .032 MATERIAL FOUND OUT OF LIMITS. CUT OUT 20 IN OF FLOOR SUPPORT. RECEIVED FLOOR SUPPORT REPAIR ASSY. FABRICATED REPAIR ASSY. INSTALLED IAW DC9-53-10-03-801-663AM, 53-01, 51-10-1 P-180.

Part: FLOOR PANEL — TORN (CABIN) · airframe 70,709 hrs · 65,469 cycles

CABIN FLOOR PANEL 94 SKIN TORN AT FWD END. RECEIVED NEW FLOOR PANEL LOCATED, DRILLED AND C-SUNK IAW SRM 51-10-04.

Part: FLOOR PANEL — CORRODED (MAIN CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL NR 78, 1EA END HAS CORROSION AND 1EA PUNCTURED HOLE PARTS, RACK 22B BLENDED LIGHT CORROSION BY HAND ORIGINAL IS .025 NO METAL LOST IAW SRM 51-10-3. REMOVED PUNCTURED AREA IAW SRM 51-10-4. NDT VERIFIED CRACK IS REMOVED IAW NDT SPM 06-10-01.001. FABBED REPAIR DOUBLER IAW SRM 53-01, FIG 2 LOCATED, DRILLED AND DEBURRED IAW SRM 51-10-4. INSTALLED IAW SRM 51-20-2. REQUIRED INSP COMPLETED.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STA 200, 305, RBL 22 SEAT TRACK HAS CORROSION. REMOVED CORROSION FROM SEAT TRACK ORIGINAL MAT .090 IAW SRM 51-10-01, FIG 26. REMOVED .028, REMAINING .062 OUT OF LIMITS IAW SRM 53-05, FIG 4B. REMOVED SEAT TRACK. RECEIVED SCALLOPED SEAT TRACK. TRIMMED LOCATED AND DRILLED IAW SRM 51-10-2 TREATED AND PRIMED IAW SRM 51-10-3, INSTALLED IAW SRM 51-30-5. REQUIRED INSP COMPLETED.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STA 160 TO 218, BL0 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION. (2" X 12") ORIG MAT .060. REMOVED .018 WITH .042 REMAINING FOUND TO BE OUT OF LIMITS IAW SRM 51-10-3, 53-13-1 AND 53-01, FIG 1. LOCATED, DRILLED, DEBURRED AND INSTALLED FLOOR SUPPORT IAW SRM 51-30-5, 51-10-4.

Part: PAN — CRACKED (WINDOW) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN WINDOW PAN CRACKED IN TOP FWD CORNER BETWEEN STA 794 AND 813 AT FASTENER LT SIDE. REMOVED 4 EA FASTENERS FROM WINDOW PAN. REMOVED DAMAGED AREA. NDT VERIFIED ALL DAMAGE WAS REMOVED. FABRICATED REPAIR ANGLE FILLER DRILLED, LOCATED AND DEBURRED FASTENER HOLES, TREATED, PRIMED AND INSTALLED IAW DC9-A-56-20-02-801-663A-A AND SRM 51-10-2, 51-10-3, 51-10-4, 51-30-5, 51-60-0 FIG 1, 51-30-2. NDT SPM 10-06-01. REQUIRED INSP COMPLETED.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

E & E COMPARTMENT STA 180 AT BL 0 INTERCOSTAL LT ATTACH ANGLE CRACKED. REMOVED AND INSTALLED ATTACH ANGLE 51-30-5. FABRICATED NEW ANGLE USING 2024-T3 .040 PO 1120172 IAW DWG 9923484.

Part: PAN — CRACKED (WINDOW) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN WINDOW PAN CRACKED IN TOP FWD CORNER AT FASTENER BETWEEN STATION 693 AND 712 RT SIDE. CUT OUT CRACKED AREA. FABRICATED AND INSTALLED IAW SRM 56-20-02-801-663A-A. REQUIRED INSP COMPLETED.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN PASSENGER CABIN STA 234, LBL 22, SEAT TRACK CORRODED. REMOVED CORROSION IAW SRM 51-10-3 ORIGINAL MAT .090 IAW SRM 53-23-0 & 51-10-01, MAT LOSS .035 REMAINING MAT .055 OUT OF LIMITS IAW SRM 53-01, FIG 1. R & R SEAT TRACK SPLICE IAW SRM 51-30-01, 51-30-5 AND 53-05, FIG 4F. REQUIRED INSP COMPLETED.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STA 200, LBL 1 TO 20 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION ORIGINAL MAT .060 REMOVED .048, REMAINING .012 FOUND TO BE OUT OF LIMITS. REMOVED FLOOR SUPPORT TRIMMED, LOCATED , DRILLED, TREATED, PRIMED, SEALED AND INSTALLED NEW FLOOR SUPPORT ALL WORK ACCOMPLISHED IAW SRM'S 53-13-1, FIG 11, 51-10-1, FIG 53-01, FIG 1, 51-10-2, 51-10-4, 51-10-3, 51-20-00, 51-30-5.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STA 200 TO 218, RBL 19 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-03. ORIGINAL .094 REMOVED .022 REMAIN .072 FOUND TO BE OUT OF LIMITS IAW SRM 53-01, FIG 1. REMOVED SUPPORT IAW SRM 51-30-01. LOCATED, FABRICATED AND DRILLED NEW SUPPORT IAW SRM 51-10-04. INSTALLED IAW SRM 51-30-01. REQUIRED INSP COMPLETED.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STA 200, RBL 24 TO 43 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION IAW SRM 53-01, FIG 1. ORIGINAL .060 IAW SRM 53-13-1 AND 51-10-1. REMOVED .019, .041 OUT OF LIMITS IAW SRM 53-01. LOCATED, DRILLED AND TRIMMED NEW FLOOR SUPPORT PRIMED IAW SRM 51-10-3. INSTALLED IAW SRM51-30-5.

Part: FLOOR PANEL — BROKEN (CABIN) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN METAL FLOOR PANEL NR 61, 1 EA CORNER BROKEN OUT, PARTS RACK 22B. REMOVED DAMAGED AREA IAW SRM 53-01, FIG 4. HFEC INSPECT IAW NDT SPM 06-10-01.001. NO CRACKS NOTED REPAIRED FLOOR PANEL IAW SRM 53-01, FIG 4, 51-10-4, 53-23-0, FIG 4. REQUIRED INSP COMPLETED.

Part: MEMBRANE — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN, CRACK FOUND IN SUBFLOOR MEMBRANE STA 205, BL0. REMOVED DAMAGED AREA 2" X 2" AND PERFORMED DVI INSP NO CRACK PRESENT. FABRICATED, DRILLED, DEBURRED PRIMED, SEALED, AND INSTALLED REPAIR FILLER & DOUBLER. ALL WORK ACCOMPLISHED IAW SRM'S (51-10-3) (51-10-4) (51-20-00) (51-30-2) (53-01) FIG 4 (SHEET 4) (51-02) PG.2. REQUIRED INSP COMPLETED.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

MAIN CABIN STA 200 RBL 1 TO 20 FLOOR SUPPORT HAS CORROSION. REMOVED & REPLACE FLOOR SUPPORT IAW DC9 SRM 51-01 & 51-30-05. FABRICATED FLOOR SUPPORT IAW DC9 SRM 53-13-1, 51-10-01 & 51-10-04. REQUIRED INSPECTION COMPLETED.

Part: ATTACH FITTING — CRACKED (FUSELAGE) · airframe 70,709 hrs · 65,469 cycles

AFT CARGO STATION 1151 INTERCOSTAL ATTACH CLIP CRACKED BETWEEN L28L AND L27L. REMOVED ATTACH CLIP AND TIE DOWN TRACK. RECEIVED MATERIAL.040 INCH IAW DRAWING 592249. FABRICATED NEW CLIP AND INSTALLED CLIP AND TIE DOWN TRACK IAW DRAWING 592249, SRM 51-30-1, 51-30-2, 51-10-2, 51-30-5.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 70,593 hrs · 65,370 cycles

LIGHTNING STRIKE AT STA 47 AND 12 IN BELOW L18. CUT OUT DAMAGE IAW SRM 53-01, FIG 4 SH 4. HFEC INSPECT IAW NDT SPM 06-10-01, NO DEFECT NOTED. MFG & INSTALLED DOUBLER WET WITH PRC IAW SRM 53-01, FIG 4. SEALED EDGES OF REPAIR AND PAINTED. JOB COMPLETE.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 70,593 hrs · 65,370 cycles

LIGHTNING STRIKE AT STA 61.5 AND 12.75 IN BELOW L18 C/W SRM53-04, FIG 38, SH3 COND3 -- HFEC C/W --NO CRACKS FOUND. FABRICATED & INSTALLED REPAIR DOUBLER WET WITH PRC IAW SRM. ACFT OK FOR SERVICE.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 70,593 hrs · 65,370 cycles

LIGHTNING STRIKE AT STA 44 AND 11.75 IN BELOW L18. C/W SRM53-04, FIG 38, SH3 COND3 -- HFEC C/W -- NO CRACKS FOUND. CUTOUT DAMAGE IAW SRM 53-01, FIG 4, SH 4. FABRICATED & INSTALLED REPAIR DOUBLER WET WITH PRC IAW SRM. ACFT OK FOR SERVICE. RII COMPLETED ON LP0302770.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 70,593 hrs · 65,370 cycles

LIGHTNING STRIKE AT STA 61 AND 24 INCHES BELOW L18. C/W SRM 53-04, FIG 38, SHEET 3 CON 3. HFEC C/W NO CRACKS NOTED. CUTOUT DAMAGE IAW SRM 53-01, FIG 4, SH 4. HFEC INSPECT IAW NDT SPM 06-10-01, NO DEFECT NOTED. FABED & INSTALLED REPAIR DOUBLER WET WITH PRC IAW SRM 53-01, FIG 4. SEALED EDGES OF REPAIR AND PAINTED, JOB COMPLETE. RII COMPLETE, CLOSE QC LOG.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 70,593 hrs · 65,370 cycles

LIGHTNING STRIKE AT STA 61 AND 8 INCHES BELOW L18. C/W SRM 53-04 FIG 38 SHEET 3 CON 3. HFEC C/W NO CRACKS NOTED. BLEND OUT OF LIGHTNING STRIKE ON EXISTING DOUBLER. REMOVED DOUBLER AND FABRICATED NEW ONE. INSTALLED DOUBLER WET WITH PRC IAW SRM 53-01, FIG 2. INSPECTED DOUBLER INSTALLATION. OK TO PAINT. SEALED EDGES OF REPAIR AND PAINTED, JOB COMPLETE. RII COMPLETE.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 70,593 hrs · 65,370 cycles

LIGHTNING STRIKE AT STA 56 AND 27 INCHES BELOW L 18 C/W SRM 53-04, FIG 38, SHEET 3 CON 3. C/W HFEC NO CRACKS NOTED. CUTOUT DAMAGE IAW SRM 53-01, FIG 4, SH4. FABED & INSTALLED DOUBLER WET WITH PRC IAW SRM. SEALED EDGES OF REPAIR AND PAINTED. JOB COMPLETE, ACFT OK FOR SERVICE RII COMPLETED ON LP 0302771, QC 1987.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 70,484 hrs · 65,276 cycles

CABIN CREW REPORTED SOFT FLOOR IN CTR AISLE NEAR ROW 12 FLOOR PANEL 60C. REPAIRED AND REINSTALLED FLOOR PANEL 60C IAW ER/A 488286-14.

Part: LINE — UNSECURE (EMERGENCY EXIT) · airframe 70,044 hrs · 64,883 cycles

MX FOUND THAT THE EMERGENCY EXIT HATCH OVER THE LT WING WOULD NOT OPEN. INVESTIGATION DIVULGED THAT A SNAP FOR THE ESCAPE LINE WAS NOT ENGAGED. FOLLOWING PROPER INSTALLATION OF THE SNAP THE EXIT FUNCTIONED.

Part: SLIDE — FAILED (TAILCONE) · airframe 68,131 hrs · 63,217 cycles

CLEANERS RELEASED THE TAIL CONE EXPECTING ACCESS TO VENTRAL STAIRS. THE TAIL CONE DROPPED BUT THE EMERGENCY EVACUATION SLIDE DID NOT DEPLOY. TEMPORARY REPAIRS MADE TO THE TAIL CONE AND THE AIRCRAFT WAS FERRIED FROM MCI TO MSP. THE TAIL CONE AND THE EVACUATION SLIDE WERE BOTH REPLACED, RII COMPLETED, AND THE FUNCTIONAL CHECKS WERE GOOD.

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHT) · airframe 66,593 hrs · 61,865 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 19-22 OF THE CABIN AND IN THE TAIL COMPARTMENT WERE INOPERATIVE. MX REPAIRED THE CONNECTOR FOR THE WIRE HARNESS AT THE SIDEWALL AND FUNCTIONALLY CHECKED THE SYSTEM.

Part: UNKNOWN — SMOKE (CABIN) · airframe 65,526 hrs · 60,879 cycles

AFTER TAKEOFF FLT ATTENDANT REPORTED SMOKE IN CABIN. FLT CREW COMPLIED WITH COM PROCEDURES FOR SMOKE REMOVAL & INITIATED A RETURN. PILOTS NOTED RT AC SYS INDICATING FULL HOT IN AUTOMATIC MODE, TRIED FULL COLD IN AUTO MODE. VALVE POSITION REMAINED IN FULL HOT UNTIL CREW SELECTED FULL COLD IN MANUAL MODE, & SMOKE & HEAT SOON DISSIPATED. ATB LANDING UNEVENTFUL. MX INSPECTED ALL POSSIBLE OIL LEAK SOURCES, FOUND MINIMAL RESIDUE. REPLACED WATER SEPARATOR SOCKS & CABIN TEMP CONTROLLER (AT A2-5) & ACCOMPLISHED PACK BURNOUT PROCEDURES. COALESCER BAGS WERE SPECIFICALLY DESCRIBED AS DIRTY BUT NOT OIL SOAKED. AFTER PACK BURNOUT PROCEDURES COMPLETED & NO OTHER EVIDENCE OF SMOKE NOTED, ACFT RETURNED TO SERVICE.

Part: DUCT — CRACKED (LT ACM) · airframe 64,810 hrs · 60,261 cycles

AS THE AIRCRAFT CLIMBED THROUGH 4000 FEET, THE FLIGHT ATTENDANTS INFORMED THE COCKPIT CREW THAT THE AFT RIGHT LAVATORY SMOKE DETECTOR WAS SOUNDING AND THAT THE CABIN HAD A HOT SMELL. FLIGHT CREW MADE NOTE OF POWER SETTINGS AND RETURNED TO A NORMAL SAFE LANDING BACK AT MSP. NO MENTION OF COMPLIANCE OR CABIN HEAT SELECTOR POSITION. MAINTENANCE PERFORMED "SMOKE IN CABIN" TROUBLESHOOTING PROCEDURES AND FOUND A CRACKED DUCT BETWEEN THE LEFT ACM AND COALESCER BUT NO SOURCE OF SMOKE. AFTER THE DUCT WAS REPLACED AND THE COALESCER BAGS CHANGED, PACK BURN OUT PROCEDURES WERE COMPLIED WITH. THE AIRCRAFT HAS RETURNED TO SERVICE.

Part: DUCT — LOOSE (ACM) · airframe 64,789 hrs · 60,240 cycles

AS THE AIRCRAFT CLIMBED OUT WITH BOTH PACKS CONTROLS SET TO "COLD", THE FO NOTICED THAT THE RIGHT PACK WAS INDICATING 94 DEGREES AND THE RIGHT VALVE SHOWED FULL HOT. THE CREW SELECTED MANUAL PACK CONTROL AND WENT TO FULL COLD. THE LEAD FLIGHT ATTENDANT NOTIFIED THE COCKPIT THAT THERE WAS VISIBLE SMOKE IN THE CABIN AND THE AFT LAVATORIES SMOKE DETECTORS WERE SOUNDING. FLIGHT CREW PERFORMED EMERGENCY COM PROCEDURES AND RETURNED TO A NORMAL SAFE LANDING BACK AT MEM. MAINTENANCE REPLACED BOTH WATER SEPARATORS, INSPECTED ALL APPLICABLE DUCTS AND VALVES, AND EACH ENGINE AND APU INTAKES FOR EVIDENCE OF OIL LEAKS OR FOD INGESTION. NO SOURCE OF SMOKE FOUND AND ACM DUCT WAS ONLY ONE FOUND TO BE LOOSE. OPERATIONAL CHECK OF SYSTEM WAS GOOD AND THE AIRCRAFT RETURNED TO SERVICE.

Part: SKIN — CRACKED (FUSELAGE) · airframe 61,223 hrs · 57,113 cycles

DURING LINE CHECK FOUND CRACKS IN FUSELAGE SKIN FROM BS 1292-1314 IN RIVET LINE ABOVE S16R. REPAIRED PER EA 98-205703 AND ESTABLISHED MONITOR AT 3000 CYCLES.

Part: BRACKET — CRACKED · airframe 53,582 hrs · 50,153 cycles

During an Mck in ATL a crack was found at the station 69 bracket (x=+/- 10). Repaired per EA 98-185453.

Part: DRAIN VALVE — CLOGGED (RT SLANT PANEL) · airframe 52,430 hrs · 49,139 cycles

EN ROUTE FROM DFW TO DTW, THE AILERON FLIGHT CONTROLS FROZE. AIRCRAFT DESCENDED TO A LOWER ALTITUDE AND CONTROL RETURNED. FLIGHT DIVERTED TO MEM AND MADE A NORMAL SAFE LANDING. MAINTENANCE FOUND THE RIGHT SLANT PANEL DRAIN VALVE CLOGGED. CLEARED OBSTRUCTION AND AIRCRAFT RETURNED TO SERVICE.

Part: STRUCTURE — CRACKED (CARGO DOOR) · airframe 49,978 hrs · 46,923 cycles

FWD CARGO DOOR HAS A 1.25 INCH CRACK NEAR LOWER AFT CORNER. DYE CHECKED AND STOP DRILLED CRACK IAW EA 98-172187 LOG PAGE 8225111.

Part: BATTERIES — DISCHARGED (CABIN)

DURING LINE MAINTENANCE INSPECTION, FOUND AFT OVERWING EMERGENCY EXIT SIGN LIGHTS INOPERATIVE. REPLACED BATTERIES, OPERATIONAL CHECK NORMAL.

Part: PACK — MALFUNCTIONED (LEFT)

AT THE START OF TAKEOFF ROLL, THE LEFT AIR CONDITIONING PACK HIGH TEMPERATURE INDICATION LIGHT ILLUMINATED. THE FLIGHT CREW ABORTED TAKEOFF BEFORE 35 KNOTS AIRSPEED AND RETURNED TO THE GATE WITHOUT INCIDENT. MAINTENANCE DEFERRED THE LEFT AIR CONDITIONING PACK SYSTEM PER MINIMUM EQUIPMENT LIST 21-A1 AND RETURNED AIRCRAFT TO SERVICE.

Part: SWITCH — FAILED (STALL WARNING)

STALL INDICATION FAILURE LIGHT CAME ON DURING CLIMBOUT, PRIOR TO FLAP RETRACTION. FOLLOWED COCKPIT OPERATING MANUAL PROCEDURE AND DIVERTED TO MSP. FLIGHT LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED SWITCH S1-299 AND TESTED STALL WARNING SYSTEM PER MAINTENANCE MANUAL, OPERATIONAL CHECK OK.

Part: PIN PLATES — WORN (TAILECONE)

DURING LINE CHECK, FOUND INADEQUATE FORCE WAS REQUIRED TO PULL THE EXTERIOR TAILCONE HANDLE FROM THE CLIPS. ALSO, FOUND EIGHT TAILCONE GUIDE PINS WORN, UPPER LEFT LATCH WORN AND TWO ALIGNMENT PIN PLATES WORN. REPLACED CLIPS, GUIDE PINS, LATCH AND PIN PLATES.

Part: TURBINE — FAILED (LT ENGINE)

DURING CLIMB AT FL270 A NOISE WAS HEARD, THE LEFT ENGINE EPR DROPPED TO 1.2. CREW DIVERTED TO ALB AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE LEFT ENGINE.

Part: PRBC — MALFUNCTIONED (LT ENGINE)

WHEN APPLYING TAKEOFF POWER, THE LEFT ENGINE EXPERIENCED COMPRESSOR STALLS. CREW ABORTED TAKEOFF AND RETURNED TO THE GATE. MAINTENANCE REPLACED THE LEFT ENGINE PRBC, RAN ENGINE TO TAKEOFF POWER, LEAK AND OPERATIONAL CHECK OK.

Part: DOOR PAN — CRACKED (EMERG EXIT)

DURING H-CHECK, FOUND A 1.9 INCH CRACK IN THE FORWARD LEFT EMERGENCY OVERWING EXIT DOOR PAN. REPAIRED PAN (P/N 5913195-1) PER EA 98-103293.

Part: DOOR PAN — CRACKED (OVERWING EXIT)

DURING H-CHECK, FOUND A CRACK IN THE RIGHT AFT EMERGENCY OVERWING EXIT DOOR PAN AT THE UPPER AFT DOOR STOP. REPAIRED PAN (P/N 5913195-1), PER EA 98-103292.

Part: BLKHD WEB — OIL CANNED (FS 1167)

DURING H-CHECK, FOUND OIL CANNING IN THE PYLON BULKHEAD WEB FS 1167, LEFT AND RIGHT SIDES. REPAIRED WEB (P/N 9912243-81, -83, -84) PER EA 98-102596.

Part: BUNGEE — OUT OF ADJUST (LT NLG DOOR)

NOSE LANDING GEAR DOOR DID NOT CLOSE ON GEAR RETRACTION AFTER DEPARTURE. FLIGHT RETURNED TO MSY AND LANDED WITHOUT INCIDENT. ADJUSTED LEFT NOSE GEAR DOOR BUNGEE BY LENGTHENING 1/2 TURN. OPERATIONAL CHECK OK ON DOOR CYCLE. AIRCRAFT RETURNED TO SERVICE.

Part: STRUT — REQUIRED SERVICE (NLG)

LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF FROM MOT. PUSHED GEAR HANDLE RELEASE BUTTON IN AND GEAR RETRACTED NORMALLY. FLIGHT CONTINUED TO DESTINATION (MSP) WITHOUT FURTHER INCIDENT. JACKED AIRCRAFT AND PERFORMED GEAR EXTENSION AND RETRACTION CHECK. NO PROBLEMS WERE FOUND. IT IS SUSPECTED THAT WATER WAS MIXED IN WITH NOSE GEAR STRUT FLUID. DRAINED FLUID AND SERVICED NOSE STRUT TO PROPER LEVELS. OPERATIONAL CHECK OK. AIRCRAFT RETURNED TO SERVICE.

Part: RETRACT MECH — ICE BUILD UP (NLG DOOR)

EXCESSIVE VIBRATION WAS COMING FROM THE NOSE GEAR AREA AFTER GEAR RETRACTION. FLIGHT RETURNED TO DTW AND LANDED WITHOUT INCIDENT. UPON INSPECTION, FOUND LEFT NOSE GEAR DOOR OPEN. ALSO, ICE WAS NOTED IN NOSE WELL AND AROUND DOOR. SECURED DOOR AND REMOVED ICE ACCUMULATION. AIRCRAFT RETURNED TO SERVICE.