N762NC

Part: PLACARD — MISSING (EMERGENCY EXIT) · airframe 82,920 hrs · 83,800 cycles

RED/WHITE EMERGENCY EXIT SIGN ON OUTSIDE OF COCKPIT DOOR IS MISSING. REPLACED MISSING EXIT SIGN ON COCKPIT DOOR.

Part: STOP FITTING — CRACKED · airframe 82,402 hrs · 83,228 cycles

DETECTED A CRACK ON THE NR 4 AFT DOOR STOP APPROXIMATELY .125 IN LENGTH STARTING AT DOOR STOP HOLE AND EXTENDING FORWARD. REMOVED DAMAGE PER DRAWING SR095302 52. FABRICATED DOUBLER AND FILLER PER DWG SR09530252 AND LOCATED AND DRILLED REPAIR PARTS TREATED AND PRIMED REPAIR PER SRM 51-10-3 PG:31. INSTALLED DOUBLER PER DPS 900-5-1 NR 4 AND INSTALLED CONICAL SPACER ON THE AFT NR 4 DOOR STOP PER SRM 51-30-11 PG:1 AND 3 AND INSTALLED REPAIR ON THE NR 4 DOOR STOP AFT PER DWG SR09530252 AND SRM 51-30-5 PG:1 COMPLIED WITH PER 5330-01142-02.

Part: DOOR FRAME — CORRODED (CARGO DOORWAY) · airframe 82,402 hrs · 83,228 cycles

FORWARD CARGO DOOR FRAME LOWER EDGE HAS CORROSION AND IS BULGED. REMOVED AND REPLACED DOOR FRAME IAW SRM 53-05 FIG 44 AND SRM 51-30-2 SRM 51-30-8 .

Part: SKIN — TORN (FUSELAGE)

ON ARRIVAL, FOUND SKIN TORN APPROX 0-12 INCHES FROM LOWER FWD CORNER OF FWD BAGGAGE BIN FWD DOOR FRAME. INSTALLED INTERNAL REPAIR, EXTERNAL REPAIR DOUBLER AND FILLER IAW SRM 53-05 FIG. 82 AND ERA 501682-14.

Part: CONNECTOR — DIRTY (CABIN) · airframe 81,147 hrs · 81,873 cycles

THE FORWARD AND MIDDLE EMERGENCY EGRESS CATWALK PATH LIGHTS ARE INOP. CLEANED LIGHTING CONNECTORS AND RECONNECTED, CHECKS OK.

Part: PROXIMITY SENSOR — FAULTY (RT MLG) · airframe 808,228 hrs · 81,539 cycles

ON APPROACH, GOT A NORMAL GEAR DOWN INDICATION. ON SHORT FINAL, THE RIGHT GEAR RED UNSAFE LIGHT STARTED FLICKERING AND THE GREEN LIGHT FLICKERED. CREW DECLARED AN EMERGENCY, DID A GO AROUND, AND MANUAL GEAR EXTENSION. ON SECOND FINAL APPROACH, THE RIGHT MAIN GEAR LIGHT WENT OUT AND THE RED UNSAFE LIGHT ILLUMINATED STEADY. CREW DID A SECOND GO AROUND AND MANUAL GEAR EXTENSION. THE RIGHT MAIN GREEN LIGHT WENT OUT AND THE RED ABNORMAL LIGHT ILLUMINATED. CREW COMPLETED EMERGENCY LANDING. MAINTENANCE REPLACED THE RIGHT MAIN LANDING GEAR DOWNLOCK PROXIMITY SENSOR AND THE PSEU PER AMM.

Part: SKIN — CRACKED (BS 200 L20-21L) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND FUSELAGE EXTERIOR STA 200 BETWEEN L20L AND L21L SKIN CRACKED AT FASTENER. TRIMMED SKIN CRACKED AREA IAW DWG SR09530219. FABRICATED 4 EA FILLERS, 2 EA SKIN DOUBLERS, 1 EA FINGER DOUBLER, IAW DWG SR09530219 & SRM 53-05 FIG 57A, TREAT & PRIME PARTS IAW SRM 51-10-3, INSTALLED PARTS IAW SRM 51-30-1, 51-30-2, 51-30-5 & DWG SR09530219 PAINTED IAW SRM 51-10-3B.

Part: FRAME — CRACKED (BS 1209 S13-14R) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND AFT ACCESSORY COMPARTMENT RT SIDE STA 1209 BETWEEN STRINGER 13-14, LARGE CRACK IN WEB. CUTOUT SECTION OF WEB FROM LONGERON 7 TO 14 IAW SRM 51-70-4, NO DEFECT IAW NDT SPM 06-10-01-001 FABRICATED AND INSTALLED NEW SECTION DOUBLER IAW SRM 51-70-4 & ERA 487364-14 .

Part: LONGERON — CORRODED (BS 1136-1117) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING MX, CORROSION WAS FOUND ON LONGERON L17R BETWEEN STA 1136 AND STA 1117. WHEN THE FASTENERS IN THE SKIN PANEL WERE REMOVED, THE FASTENER HOLES WERE ELONGATED. WORK IAW ER/A 487366-14 AS FOLLOWS: SECTION I - COMPLETED DURING MX, SECTION II - WITHIN 8,000 CYCLES AFTER SECTION I SECTION III - WITHIN EVERY 8,000 CYCLES THEREAFTER ASSOCIATED ER/A 13-487366 ADDED.

Part: SKIN — CRACKED (BS 1247) · airframe 79,845 hrs · 80,395 cycles

WHILE ACCOMPLISHING A SID INSP OF PSE 53.09.028, IAW AD2006-21-06, EM5330-01148-01B, A 1.8" LONG CRACK WAS FOUND IN THE SKIN, STA 1247, L1 TO L2R. WORK IAW ER/A 482375-14AD AS FOLLOWS: SECTION I ACCOMPLISHED DURING MX - DEC 2010, SECTION II - ON OR BEFORE 24MOS AFTER SECTION I - TBD PENDING DAMAGE TOLERANCE EVALUATION ASSOCIATED AA 5330-01148 ADDED FOR AC 0853 ASSOCIATED ER/A 13-482375 ADDED FOR AC 0853.

Part: WEB — CHAFED (BS 1209 S5L) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND AFT ACCESSORY COMPARTMENT LT SIDE STA 1209, STR 5 JUST AFT OF ACTUATOR WEB REPAIR CHAFED THROUGH. REMOVED OLD REPAIR. FABRICATED NEW WEB AND REPAIR PARTS IAW DWG 9912246, REV DE AND SRM 53-13-4 NDT FORMED AREAS IAW SPM 08-10-00 AND HFEC. TRIMMED AREA IAW NDT SPM 06-10-01. 001. INSTALLED REPAIR PARTS IAW SRM 51-30-05 AND 51-70-04. P-245

Part: FLOOR PANEL — CORRODED (COCKPIT) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND COCKPIT FLOOR PANEL NR 14B HAS CORROSION IN SEVERAL PLACES ON TOP OF PANEL. REMOVED AND FABRICATED, INSTALLED NEW PANEL IAW ERA 4861146-14.

Part: FLOOR PANEL — LOOSE (MAIN CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND MAIN PASSENGER CABIN FLOOR PANEL NR 60C AFT END OLD REPAIR LOOSE. FABRICATED NEW FLOOR PANEL AND HAT CHANNELS IAW ERA 482363-14.

Part: CHANNEL — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK (AD-FAR) AFT ACCY COMPARTMENT-APB RT LOWER CORNER -37 SEAL CHANNEL HAS APPROX 2 INCH CRACK. FABRICATED REPAIR CHANNEL. TREATED AND PRIMED AND INSTALLED ON APB RT LOWER CORNER IAW SRM 51-30-5, SRM 51-10-3 AND SRM 53-05, FIG 40 H.

Part: HINGE — CORRODED (AIRSTAIR DOOR) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FWD AIRSTAIR DOOR HINGE AND ATTACH FASTENERS CORRODED. CORROSION WAS REMOVED IAW SRM 51-10-3. ORIG MAT .071 IAW SRM 53-33-0. REMOVED .026 REMAINING .045 OUT OF LIMITS IAW SRM 53-01, FIG 1. RECEIVED AIRSTAIR DOOR ON FORM 8130-3 TRACKING NR 8412995.

Part: CHANNEL — CRACKED (FLOOR PANEL) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CABIN FLOOR PANEL NR76 HAS 1EA HAT CHANNEL CRACKED AND 1EA CHAFED THRU FABRICATED NEW PANEL IAW ERA 486157-14. REMOVED HAT CHANNELS FROM PANEL 76. DRILLED, DEBURRED AND COUNTERSUNK HOLES. ALODINED AND PRIMED FLOOR PANEL AND HAT CHANNELS.INSTALLED HAT CHANNELS AND CUT OUT ANGLE IAW SRM 51-30-2, SRM 53-23-0, FIG 5 AND DWG 9957717.

Part: SUPPORT ANGLE — CRACKED (BS 750) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND MAIN PASSENGER CABIN STA 750, LBL44 SUPPORT ANGLE ON TOP OF CTR WING TANK IS CRACKED. REMOVED DAMAGED SECTION OF ANGLE, FABRICATED REPAIR SPLICES, ANGLE & FILLER IAW SRM 57-01, FIG 3 AND 51-10-4 INSTALLED REPAIR PIECES IAW SRM 57-01, FIG 3, P245.

Part: FLOOR PANEL — DAMAGED (BS 1138) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND HOLE IN MAIN PASSENGER CABIN FLOOR PANEL NR98 AT BS1138. REMOVED DAMAGE IAW SRM 51-70-4 FIG 1. 9.2500"X 1.6250" ORIGINAL MATERIAL .020. FABRICATED FILLER AND DOUBLER IAW SRM 51-10-3.

Part: FLOOR SUPPORT — GOUGED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND MAIN PASSENGER CABIN LBL 18 TO RBL 18 AFT ENTRY DOORJAMB LOWER FLOOR PANEL SUPPORT ANGLE HAS 2EA GOUGES. R & R BOTTOM SECTION OF FRAME R & R FLOOR SUPPORT LT AND RT DOOR JAMB SUPPORT AND 3EA STRIKER SECTIONS IAW DWG 5917463 AND SRM 51-30-1, 51-30-2, 51-30-5. FABRICATED AND INSTALLED 2EA ANGLE REPAIR DOUBLERS FROM .063 2024T3 PO 0922430, 4EA SHIMS AND 1EA FILLER IAW SRM 53-05, FIG 34 SHEET 4.

Part: STRAP — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND AFT CARGO DOOR PAN WEB FWD OTBD STRAP HAS CORROSION. R & R AFT CARGO DOOR PAN WEB OTBD STRAP GUSSETT AND INSTALLED NEW OTBD STRAP GUSSETT CUSTOMER FURNISHED PART IAW SRM 51-30-2 & 51-30-5.

Part: STRAP — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND AFT CARGO DOOR PAN WEB AFT INBD STRAP CORRODED. R & R AFT CARGO DOOR PAN WEB AFT INBD STRAP. INSTALLED NEW CUSTOMER FURNISHED PART IAW SRM 51-30-2 & 51-30-5.

Part: PAN — CORRODED (BS 1070-1100) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND AFT CARGO DOOR PAN HAS CORROSION FROM STA 1070-1100. REMOVED AFT CARGO DOOR PAN & WEB AND REPLACED WITH NEW CUSTOMER FURNISHED PARTS IAW DWG NR J060228 & SRM 53-05 FIG 44, SHEET 12. INSTALLED NEW PARTS IAW SRM 51-30-2 & SRM 51-30-5.M.

Part: STRUCTURE — DAMAGED (FUSLEAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND AFT ACCESSORY COMPARTMENT, LT SIDE, BETWEEN CANTED FRAMES 1275 & 1292 UNDER INBD ATTACH POINTS FOR AIRSTAIR RELEASE MOUNT FITTING. PREVIOUS REPAIR CRACKED PAST STOP DRILLS ALSO DOUBLER CRACKED. CUT OUT DAMAGED SECTION 2 FT X 2 IN. SPLICE NEW FRAME. FABRICATED NEW FRAME SECTION HEAT TREATED IAW SRM 51-10-4, 51-30-5 & 51-30-2. HFEC IAW NDT SPM 06-10-01. DAMAGE REMOVED & INSTALLED NEW SPLICE SECTION IAW SRM 51-70-5.

Part: DOOR — CORRODED (AIRSTAIR) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND FUSELAGE EXTERIOR AIR STAIR DOOR HAS CORROSION ALONG BOTTOM EDGE IN CHANNEL. REMOVED CORROSION FROM DOOR EDGE IN CHANNEL. FOUND TO BE OUT LIMIT IAW SRM 53-01, FIG 1 REMOVED SKIN FROM DOOR EDGE. RECEIVED NEW PN 5915064-501, INSTALLED IAW SRM 51-30-2 & 51-10-4.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FUSELAGE EXTERIOR AFT CARGO DOOR JAMB FWD LOWER CORNER HAS ELONGATED FASTENER HOLE THRU SKIN AND INTERNAL DOUBLERS AND DOOR PAN AND PAN SPLICE HOLE CLEANED UP AT .3680 IAW SRM 51-20-03. INSTALLED FREEZE PLUG IAW SRM 51-20-03-801-663A-A.

Part: INTERCOSTAL — CORRODED (BS 218-237) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND FWD CARGO BETWEEN STA 218 AND 237 JUST OTBD OF LT LONG 28 INTERCOSTAL HAS CORROSION AND CRACKS APPROX 1 INCH. REMOVED CORROSION ORIGINAL MATERIAL .063. REMOVED .003 REMAIN .060 IN LIMITS IAW SRM 53-01 FIG.1 DRILLED STOP HOLE IN INTERCOSTAL IN FWD CARGO STA 218-237 JUST O/B OF LONG 28 FABRICATED REPAIR DOUBLERS FROM .025 7075T6 PO1022687 IAW SRM 51-13-1, FIG 2 TREATED & PRIMED DOUBLERS IAW SRM 51-10-3 NDT STOP HOLE FROM CRACK IAW NDT SPM 06-10-01.001, NO CRACKS NOTED. INSTALLED DOUBLERS IAW SRM 53-01 FIG 2 & 53-30-2.

Part: ANGLE — CRACKED (BS 1209 L12L) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND AFT ACC COMPT STA 1209 AT L12L FRAME SHEAR ANGLE CRACKED. REMOVED 5 EA ANGLES AND CRACKED SHEAR TIE BETWEEN LONGERON 10 AND 14 RH STA 1209. FABRICATED, LOCATED, DRILLED NEW SHEAR TIE IAW SRM 51-13-4, FIG 1 AND 51-60-00 FIG.1, 51-30-2, 51-30-5. INSTALLED NEW SHEAR TIE AND ANGLES IAW SRM 51-30-5-51-30-2.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CABIN/HORSE SHOE DOUBLER CRACKED FWD SIDE OF STA 712 FRAME AT CUSP WEB. REMOVED CRACKED HORSESHOE DOUBLER AT STA 712 IAW DC9 51-305. DRILLED AND DEBURRED IAW DC-9 51-10-4. INSTALLED NEW HORSESHOE DOUBLER IAW DC-9 51-30-5.

Part: FLOOR SUPPORT — BROKEN (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN FLOOR PANEL SUPPORT STA 617 LBL 22-44 IS BROKEN. FABRICATED 1 EA FLOOR SUPPORT IAW DC9 SRM 53-10-3 FIG 10. INSTALL 1EA FLOOR SUPPORT IAW DC9 SRM 51-30-2 PER DWG 59107601.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN FLOOR PANEL 33 STA 351 I/B SIDE HOLE IN SKIN. REMOVED AND RECEIVED NEW FLOOR PANEL AND COUNTERSUNK ALL HOLES INSTALLED IAW DC9 SRM 51-10-4 AND SRM 51-30-1 P-130.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND MAIN PASSENGER CABIN APB LT NR2 FORMER FROM FLOOR LEVEL UPPER OTBD ATTACH ANGLE IS CRACKED. REMOVED CRACKED ATTACH ANGLE IAW DC-9A53-10-25-801-663A-A. FABRICATED NEW ATTACH ANGLE FROM MAT .025 6A1-4V PO1022791 IAW DWG 9915558. LOCATED, DRILLED, DEBURRED IAW DC9 51-12-4. INSTALLED ATTACH ANGLE IAW DC9 51-30-1 AND 51-30-2.C.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M=CHECK FOUND MAIN PASSENGER CABIN FLOOR PANEL 32 CRACKED ON FORWARD INBOARD END. REMOVED CABIN FLOOR PANEL 32. RECEIVED NEW FLOOR PANEL AND COUNTERSUNK HOLES FOR FLOOR PANEL. INSTALLED IAW DC9 SRM 51-10-4 AND 51-30-2.P-130.

Part: CARGO TRACK — CORRODED (CARGO BAY) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND AFT CARGO RT TRACK HAS CORROSION AT STA 1068. RT AFT CARGO TRACK FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-05, LOCATED, DRILLED AND INSTALLED NEW CARGO TRACK IAW DC9 SRM 51-10-4 & 51-30-2.

Part: HINGE — GOUGED (HORIZ STAB) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND LT HORIZONTAL STAB T/E NR 6 ELEVATOR HINGE GOUGED AT UPPER ATTACH POINT TO REAR SPAR. REMOVED, REPAIRED AND RE-INSTALLED IAW DC-9 MM 20-16-00 & SRM 51-10-04 & SRM 51-10-03.

Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M CHECK FOUND MAIN CABIN FLOOR PANEL 77 EXPANSION PANEL HAS CORROSION. REMOVED AND REPLACED EXPANSION CHANNEL IAW DC9 SRM 51-10-4, 51-30-2, 53-01 FIG 1 SHEET 3.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN STA 655 LBL 22-42 FLOOR SUPPORT CRACKED. REMOVED, FABRICATED AND INSTALLED FLOOR SUPPORT ANGLE IAW DC9 SRM 53-10-3 FIG 10 PG 19 & 51-30-2.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN FLOOR PANEL 55 FORWARD END SKIN CHAFED AND TORN AROUND FASTENER HOLES. REMOVED CABIN FLOOR PANEL.RECEIVED NEW FLOOR PANEL PICKED UP AND COUNTERSUNK ALL HOLES AND INSTALLED FLOOR PANEL IAW DC9 SRM 51-10-4 AND DC-9 SRM 51-30-1.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN STA 706 LBL 50 CUSP WEB CRACKED CUT OUT DAMAGED AREA .5 X 1.5 IAW DC9 A-53-10-16-801-663A-A. CUSP WEB REMOVED AND REPLACED ON PEMCO NON ROUTINE 2281N01606 P243.

Part: INTERCOSTAL — DAMAGED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND INTERCOSTAL BL-0 FROM STA 218-237 HAS CORROSION AND ELONGATED HOLES. REMOVED AND INSTALLED NEW INTERCOSTAL AT BL 0 BETWEEN STA 218 TO STA 237 IAW DC9 SRM 51-30-5.

Part: SKIN — CRACKED (RUDDER) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND VERTICAL STAB, TOP AFT T/E OF RUDDER IS CRACKED, RUDDER ASSY OFF 09-5541-9-9003. UPON EVALUATION VERT STAB TOP AFT T/E OF RUDDER HAS SEPARATION, NO FIBER DAMAGE INJECTED RESIN HYSOL EA 9396 CURED USING HEAT THERMOCOUPLER HT7581 APPLIED WET LAYUP UNDER VACUUM PRESSURE IAW SRM 51-70-1 PARA 10 TAP TESTED NO DELAMINATION NOTED. WEIGHT & BALANCE ACCOMPLISHED ON TRAVELER 2281N01956. REQUIRED INSP COMPLETED.

Part: CARGO TRACK — CORRODED (CARGO BAY) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FORWARD CARGO COMPT, RT TIE DOWN TRACK CORRODED IN SEVERAL PLACES FROM STATION 218-370. REMOVED AND REPLACED TRACK. SCALLOPED TRACK IAW DRAWING NR 5932875. INSTALLED NUT PLATES ON TRACK IAW DC-9 SRM 51-30-2. INSTALLED TIE DOWN TRACK RT FROM STA 218 TO 370 IAW DC-9 SRM 51-30-1.

Part: WEB — CRACKED (LT PYLON) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND LEFT PYLON INTERIOR WEB CRACKED IN O/B LOWER RADIUS JUST AFT OF 8TH STAGE DUCT. STOP DRILLED 1 INCH CRACK IAW DC-9 SRM 54-01, INSTALLED 2 EA REPAIR DOUBLERS CRACK CONTAINED IAW DC-9 NDT SPM 06-10-01-001.

Part: ATTACH ANGLE — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND AFT CARGO DOOR PAN DOOR STOP 2 EA INNER ATTACH ANGLES CORRODED. REMOVED 2 EA INNER ATTACH ANGLES FROM AFT CARGO DOOR PAN DOOR STOP IAW DC9 SRM 51-30-5. RECEIVED CUSTOMER FURNISHED PARTS.2 EA ANGLES PART#4912460-501. LOCATED, DRILLED, DEBURRED, TREATED, PRIMED, SEALED & INSTALLED 2 EA ANGLES IAW DC9 SRM'S 51-10-4, 51-10-3, 51-20-00, 51-30-.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN STA 1136 LBL 46 CUSP WEB IS CRACKED. REMOVED OLD CUSP WEB REPAIR FABRICATED NEW CUSP WEB REPAIR AND INSTALLED RING DOUBLERS FOR LIGHTNING HOLES AND INSTALLED 2EA DOUBLER SPLICES AND INSTALLED IAW DC9 SRM 51-70-4 FIG 2, DOUGLAS DWG SG 09530003, TRM DC9-A-53-10-16-801C.

Part: LONGERON — CRACKED (BS 1136 L16L) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN STA 1136, LONG 16L CRACKED. FWD EXISTING SPLICE HAS WRONG FASTENERS INSTALLED & FWD END OF LONGERON SECTION DOES NOT MEET GAP REQUIREMENTS. REMOVED L16L AT STA 1136 FABED NEW LONGERON PN S2777922-4 AND INSTALLED IAW SRM 53-02, FIG 18.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FORWARD CARGO COMPT STA 389 ABOVE DOOR OPENING FLOORBEAM SUPPORT IS CRACKED. REMOVED AND REPLACED FLOORBEAM SUPPORT IN FWD CARGO COMPARTMENT IAW DC9 SRM 51-30-5 & 51-30-1 & 51-20-0.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN STA 693 RT CUSP WEB HAS APPROX 2 INCH CRACK L18R. REMOVED CRACKED CUSP WEB IAW DC9 SRM 51-30-1 & 51-30-2. FABRICATED IAW DWG 9910140 NEW CUSP WEB FROM 7075-0.025 NR 2281N01834 IAW DWG 9910140, 53-13-2 RING DOUBLERS .050 & .100 7075T6 PO 0442440 & 0923042 IAW DWG SG095310019. INSTALLED RING DOUBLER TO WEB & INSTALLED NEW IAW DC9 SRM 51-30-2 & 51-30-5.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FUSELAGE EXTERIOR-STA 837 INTERCOSTAL BETWEEN MLG DOORS CORRODED. REMOVED INTERCOSTAL AT STA 837 B/W MLG DOORS PER SRM 51-30-2 & 51-30-5. FORMED, LOCATED, DRILLED, DEBURRED, TREATED, PRIMED, INSTALLED IAW DOUGLAS DWG 9923459 REV AE & DC9 SRM'S 51-10-4, 51-10-2, 51-10-3, 51-20-00 & 51-30-5. INTERCOSTAL HEAT TREATED TO 7075-T6 IAW DOUGLAS DWG 9923459 REV AE.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FUSELAGE EXTERIOR BETWEEN WHEEL WELL DOORS STA 792 RBL 10 INTERCOSTAL CRACKED. REMOVED INTERCOSTAL IAW DC9 SRM 51-30-5 FABRICATED, LOCATED, DRILLED, DEBURRED, TREATED, PRIMED, SEALED & INSTALLED INTERCOSTAL IAW BOEING DRAWING 9923459 REV AE & DC9 SRM'S 51-10-4, 51-10-3, 51-20-00, 51-30-00, 51-30-5, 51-30-2, 51-30-1.

Part: BULKHEAD — CRACKED (FUSLEAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK AND IAW AD-FAR AFT ACCY COMPARTMENT-AFT PRESSURE BULKHEAD RT LOWER CORNER HAS CRACK IN 5910130-85 GUSSET AND 5910130-87 DOUBLER, JUST ABOVE -37 SEAL CHANNEL. NDT VERIFIED CRACK STOPS ABOVE -37 SILL CHANNEL USING A2469 ZETEC IAW NDT SPM 06-10-01. NO REPAIR REQUIRED IAW DWG J060088-50.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN STA 234-236 RBL 50 CUSP WEB CRACKED (2EA) PLACES UNDER Z-ANGLE. MAIN CABIN CUSP WEB STA 234-236, REMOVED AND REPLACED PER DC9 SRM 51-10-4 & INSTALLED RING DOUBLERS PER DWG SG09530003.

Part: FRAME — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK PER AD-FAR MAIN CABIN STA 712 LT MAIN FRAME IS CRACKED INRADIUS BELOW FLOOR. REPAIR PRIOR TO FURTHER FLIGHT REPAIR REQUIRES REQUIRES FAA MANAGER LOS ANGELES ACO APPROVAL PRIOR TO FLIGHT. MUST BE REPORTED ON SSI FORM 5100-3201. REF EM 5320-01037-01A STEP 9 RII. THIS NR WILL SUPERCEDE ANY OTHER DISCREPANCIES ON THIS PART. REMOVED AND INSTALLED NEW FRAME IAW DC9 SRM 51-30-5.

Part: CARGO TRACK — CORRODED (BS 426) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FWD CARGO LT SIDE FS 426 BETWEEN LONGERON 28-29 CARGO TIE DOWN TRACK CORRODED. TIE DOWN TRACK FOUND TO BE OUT OF LIMITS. NEW TIE DOWN TRACK SRM 53-23, FIG 9 LOCATED AND DRILLED, DEBURRED IAW SRM 51-10-4. TREATED & PRIMED IAW SRM 51-10-3. INSTALLED 1 EA TIE DOWN 4 EA SPLICES IAW SRM 51-30-5/51-30-1 IAW SRM 53-05.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN STA 1104-1136 LBL 55 Z-ANGLE IS CRACKED FOUND DURING CUSP WEB REPAIR. REMOVED CRACKED Z-ANGLE. RECEIVED NEW Z-ANGLE P/N 54616493- 12500. FABBED NEW Z-ANGLE SPLICE INSTALLED Z-ANGLE AND SPLICE IAW DC9 SRM DC-9-A-53-20-01-801.

Part: FLOORBEAM — CORRODED (BS 237) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND MAIN PASSENGER CABIN STA 237, LBL 1-20 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION ON FLOOR SUPPORT IAW SRM 51-10-3. FOUND TO BE OUT OF LIMITS IAW SRM 53-1, FIG 1. REMOVED 1 EA FLOOR SUPPORT IAW SRM 51-30-2 IAW SRM 53-13-2, FIG 4. FABRICATED, DRILLED & DEBURRED 1 EA FLOOR SUPPORT IAW SRM 51-10-2 & 51-10-4. INSTALLED 1 EA FLOOR SUPPORT IAW SRM 51-10-5.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN STA 218-237 BL 0 FLOOR SUPPORT HAS CORROSION. FABRICATED NEW FLOOR SUPPORT TREATED PRIMED IAW DC9 SRM 51-10-3 AND 51-10-4 INSTALLED NEW FLOOR SUPPORT IAW DC9 SRM 51-30-5.

Part: FLOORBEAM — CRACKED (BS 775) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN STA 775, FLOORBEAM HAS 3 CRACKS AT LT FRAME TO FLOORBEAM ATTACH POINT. ALL REPAIRS INCLUDING SRM REPAIRS REQUIRE EA APPROVAL MANAGER ACO, FORM 5100-3201 REQUIRED. PRIOR TO FLIGHT PSE 53-09-015 REF EM 5320-01037-01A STEP 9. REMOVED CABIN FLOORBEAM AT STA 775 L/S LBL 20 & LBL 60 IAW SRM 51-30-2 & 51-30-5 ORDERED & RECIEVED NEW FLOORBEAM PN 991527-505, LOT 1031961 LOCATED DRILLED & DEBURRED HOLES IN FLOORBEAM AT STA 775 IAW SRM 51-10-4 & DWG 9916527-5058 ALODINED & PRIMED HOLES IAW SRM 51-10-3 INSTALLED FLOORBEAM AT STA 775 LBL 20-60 IAW SRM 51-30-2 & 51-30-5.

Part: FLOOR PANEL — CORRODED (COCKPIT) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND COCKPIT, FLOOR PANEL NR15 HAS CORROSION SEVERAL PLACES ON TOP OF PANEL. REMOVED CORROSION ORIG MAT .025 REMOVED .014 REMAINING .011 OUT OF LIMITS IAW SRM 53-01 FIG 1 LOCATED DRILLED AND INSTALLED NEW CUSTOMER FURNISHED PANEL IAW SRM 51-10-4 AND 51-30-1.

Part: FRAME — GOUGED (BS 1243) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND AFT ACCESSORY COMPARTMENT RT SIDE CANTED STA 1243, BETWEEN STRINGER 13-14, FRAME GOUGED ON BOTH SIDES COMPLETELY THROUGH. RT CANTED FRAME STA 1243 BETWEEN STR 13-14 CUTOUT DAMAGE 2" X 1" NDT HFEC VERIFIED DAMAGED REMOVED IAW NDT SPM 06-10-01. REPAIRED & INSTALLED WITH 7075T6 .063 REPAIR DOUBLER .050, 1021534 .063, & 0923042 .063 FILLER & ANGLE HEAT TREATED ON TRAVELER 2281N01860 IAW SRM 53-05, FIG 4.

Part: SEAT TRACK — CORRODED (BS 285-313) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND MAIN PASSENGER CABIN STA 285-313, LBL 22 SEAT TRACK HAS CORROSION. REMOVED CORROSION FROM BS 200-313, LBL 22 IAW SRM 51-10-3. ORIG MAT .100, REMOVED .051, AREA BLENDED 3" X 1.5" OUT OF LIMITS IAW SRM 53-05, FIG 4B. REMOVED SEAT TRACK IAW SRM 51-30-01. INSTALLED SEAT TRACK & SPLICE IAW 53-05, FIG 4.

Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN FLOOR 92 FORWARD END SKIN CORRODED AND RIVET HEAD PULLING. CUT OUT DAMAGE 4.4 INCH BY 11.5 INCH FABRICATED AND INSTALLED REPAIR DOUBLER FROM 7075 T6 .025" PO 1022211 IAW DC-9 SRM 51-70-4.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN FLOOR PANEL 41 I/B HAT CHANNEL NUMEROUS FASTENER HEADS PULLING IN SKIN. REMOVED, LOCATED AND DRILLED NEW FLOOR PANEL IAW DC-9 SRM 51-10-4. INSTALLED IAW DC-9 SRM 51-30-1.

Part: FRAME — CRACKED (BS 1230 L2L) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CRACK IN FRAME STA 1230 L2, LT CUT OUT DAMAGED AREA 3.5" X 8750" IAW SRM 53-02, FIG 32. PERFORMED NDT SPM 06-10-01. CRACK WAS REMOVED. FABRICATED -3 REPAIR ANGLE FROM S09530095-03 FABRICATED -29 FILLER FROM .050 7075-T6 FABRICATED L ANGLE -7 FROM .063 7075-T6. FABRICATED DOUBLER STRAP FROM .100 7075-T6 PO 0442440. INSTALLED ALL PARTS IAW SRM 51-30-5 AND 53-03 FIG 32. RESTORES AREA IAW SRM 51-30-5.

Part: HINGE FITTING — CRACKED (TE FLAP) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND RIGHT WING FLAP IN SIDE ACCESS HOLE O/B SIDE OF NR 4 FLAP HINGE SUPPORT ANGLE IS CRACKED AT UPPER ATTACH BOLT. REMOVED PER DC-9 SRM 51-30-02. REMOVED & INSTALLED FLAP HINGE IAW DC-9 SRM 51-30-01.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND E&E COMPT STA 200 LONGERON 23L CRACKED. REMOVED CRACKED LONGERON SPLICE IAW DC9 SRM 53-02 FIG 18. RECEIVED NEW LONGERON SPLICE P/N 00-0210-3-1972. RECEIVED NEW LONGERON P/N 2777922-3 IAW DC9 SRM 53-13-1 FIG 3. LOCATED, DRILLED TREATED, PRIMED AND INSTALLED IAW DC9 SRM 53-02 FIG 18.

Part: INTERCOSTAL — CRACKED (BS 218-237) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FWD CARGO BETWEEN STA.218 AND 237 JUST OTBD OF LT LONG 28. INTERCOSTAL HAS CORROSION AND CRACKED APPROX 1 IN. DRILLED STOP HOLE IN INTERCOSTAL IN FWD CARGO STA 218-237 JUST OTBD OF LONG 28. FABRICATED REPAIR DOUBLERS FROM .025" 7075T6. IAW SRM 51-13-1, FIG 2. TREATED & PRIME DOUBLERS IAW SRM 51-10-3. NDT STOP HOLE FOR CRACK IAW NDT SPMM 06-10-01.001. NO CRACK NOTED. INSTALLED DOUBLERS IAW SRM 53-01, FIG 2, 53-30-2.19.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN STA 160 LONG 2 IS CRACKED. REMOVED L2L FWD CLIP AND CUT OUT 23 INCHES SECTION OF L2L IAW DC9-50 SRM 51-30-2, 51-30-5, 51-10-2 NDT. VERIFIED CRACK CONTAINED IN CUTOUT IAW HPEC INSPECTION NDT SPM 06-10-07. RECEIVED NEW LONGERON 23 INCHES P/N S2777922-3 AND SPLICE P/N 00-0210-3- IAW DC9-50 SRM 53-13-1 FIG 3, 53-02 FIG 18 AND 51-10-1 FIG 36 CUT, TRIMMED, LOCATED, DRILLED AND INSTALLED PARTS IAW DC9-50 SRM 51-10-2, 51-10-4, 53-02 FIG 18, 51-30-5 R.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN STA 200-285, RBL44, SEAT TRACK HAS CORROSION IN SEVERAL AREAS. REMOVED CORROSION AT RBL 44, BS 200-285, ORIGINAL MATERIAL .115 MAT, REMAINING .080 OUT OF LIMITS IAW SRM 53-01, FIG 1, REMOVED SEAT TRACK IAW SRM 51-30-2. MAT FOR NEW SEAT TRACK S2776220 7075-T6511 PO 0920397, INSTALLED NEW SEAT TRACK IAW SRM 51-30-01 AND SRM 51-30-5.

Part: SUPPORT ANGLE — CRACKED (TE FLAP) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND LT WING FLAP, NR4 FLAP HINGE OTBD INSIDE ACCESS HOLE SUPPORT ANGLE IS CRACKED. REMOVED FLAP HINGE SUPPORT ANGLE (NR 4) IAW SRM 51-30-02. INSTALLED NEW SUPPORT ANGLE PN 09-2700-3-2828, PO0304W007 AND NEW BRACKET PN 09-2100-3-0515 IAW SRM 51-30-02 AND DWG 9957450 REPLACED NR4 FLAP HINGE FITTING IAW 51-30-01.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 79,845 hrs · 80,395 cycles

DURING M-CHECK, FOUND MAIN PASSENGER CABIN STA 160 LONG 4L IS CRACKED REMOVED L4L END CLIP, REPAIR SPLICE & 19" SECTION OF LONGERON IAW SRM 51-10-4,51-10-2,51-30-2 & 51-30-5. RECIEVED NEW SECTION OF LONGERON PN2777922-3 PO1021994. LOCATED & DRILLED FASTENER HOLES, TRIMMED & INSTALLED NEW LONGERON SECTION, END CLIP & EXISTING SPLICE IAW SRM 51-10-2,51-10-4,51-10-5, 53-13-1 FIG 3,53-02 FIG 18,51-10-1 & DC-9-A-53-10-23-801-663A-A.

Part: SUPPORT ANGLE — CRACKED (TE FLAP) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND LT WING FLAP, NR4 FLAP HINGE INBD INSIDE ACCESS HOLE SUPPORT ANGLE IS CRACKED. REMOVED DAMAGED SUPPORT ANGLE ON LT WING NR4 FLAP HINGE INBD SIDE AND FORMER IAW SRM 51-30-02. INSTALLED SUPPORT ANGLE PN 09-2700-3-2300. PO 0297W013 AND INSTALLED NEW FORMER PN 09-2700-3-0517, PO NWA IAW SRM 57-30-02 AND DWG 9957450.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND MAIN PASSENGER CABIN STA 200-285, RBL 22 SEAT TRACK HAS CORROSION SEVERAL AREAS. REMOVED CORROSION IAW SRM 53-05. FOUND TO BE OUT OF LIMITS. ORIGINAL MAT .080, REMOVED .017, .063 REMAINING. REMOVED FLOOR SUPPORT AND SEAT TRACK IAW SRM 51-30-1. MAT ID S2772660, 7075T6, PO0920397 IAW SRM 53-25-0. FABRICATED NEW TRACK IAW SRM 53-05. TREATED & PRIMED IAW SRM 51-10-3. INSTALLED NEW TRACK AND FLOOR SUPPORT IAW SRM 53-05, FIG 1, 51-30-5.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND FUSELAGE EXTERIOR, LT WINDOW BELT, WINDOW NR6 AFT EDGE OF CUTOUT CRACKED AS MARKED. REF SID INSP PROCEDURE SEQUENCE 1, METHOD 01, FOR PSE 53.09.021 SID MANUAL VOL II, SECTION 253-30-09. ATTACH SSI REPORT FORM 5100-3201. ENTER INTO DEF TO ENG. ALL REPAIRS MUST BE APPROVED BY MANAGER FAA ACO EA REQUIRED. R & R DAMAGED FUSELAGE LT WINDOW BELT SKIN STA 313-427, PN 9958156-1, PO 6301W008 IAW DWG 5932737 AND DWG 5930346.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND MAIN PASSENGER CABIN STA 160, LONG 3 IS CRACKED. RECEIVED L3L END CLIP, REPAIR SPLICE & 18.8125" SECTION OF LONGERON IAW SRM 51-10-4, 51-10-2, 51-30-2 & 51-30-5. RECEIVED NEW SECTION OF LONGERON 18.8125" PN S2777922-1 PO 1021968 & END CLIP PN 4912098U505 TRIMMED & INSTALLED NEW LONGERON SECTION, END CLIP & EXISTING SPLICE IAW SRM 51-10-2,51-10-4,51-30-5, FIG 3, 53-02, FIG18 51-10-1, FIG 36 & DC-9-A-53-10-23-801-663A.

Part: FORMER — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN APB NR4 FORMER FROM FLOOR LEVEL RT SIDE OTBD END IS CRACKED. REMOVED EXISTING END CLIP, TRIMMED OUT CRACKED 1" X 2" NDT TO VERIFY, CRACK CONTAINED, RECEIVED 2EA CLIPS PN 09-5300-3-0914, PO1031968, PN9915558-234N, PO1031820, 2EA PADS PN 09-5300-3-0983 PO1031968, FABED 1EA SHIM FROM MAT 2024-T3.040 INSTALLED IAW SRP DC9-A-53-10-25-801-66A-A.

Part: SKIN — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND FUSELAGE EXTERIOR STA 1258 BETWEEN L5R AND L6R SKIN CRACKED AT FASTENER FABRICATED FILLER AND DOUBLER MATERIAL 7075-T6 .040 LOT NR 1022364 IAW SRM 53-01, FIG 4 MAT ID IAW SRM 53-33-0 LOCATED DRILLED AND DEBURRED HOLES IAW SRM 51-10-01. INSTALLED 1EA FILLER AND 1EA DOUBLER IAW SRM 53-01, FIG 4, 51-30-2 AT STA1259 BETWEEN L5L AND L6L TOPCOATED IAW SRM 51-10-3 CUT OUT DAMAGE 1 IN X 1.5 IN HFEC AREA IAW NDT SPM 06-10- 01.001 NO CRACK NOTED.

Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN FLOOR PANEL 37 TOP SKIN CORRODED FWD TO AFT END. LOCATED HOLES AND DRILLED HOLES ON NEW FLOOR PANEL P/N 9957918-20 IAW DC9 SRM 51-10-4.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CORROSION ON INTERCOSTAL BETWEEN BS 130 & BS 160 L28L ORIG. MAT THICKNESS .063 MATERIAL REMOVED .019 REMAINING.044 FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1 AND 53-13-1 REMOVAL AND REPLACE INTERCOSTAL P/N9911550-5 PO1040806 IAW DC9 SRM 51-10-4, 51-30-1, 51-30-02, 51-30-05 AND 51-10-3 AND DAC DRAWING 5910343 P 241.

Part: WEB — CRACKED (BS 105) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND NOSE W/W LT TUNNEL STA 105, LBL 25 PRESSURE DECK WEB CRACKED MATERIAL ID FOR DOUBLER REPAIR .025 DMS1592, T1-6AL-4VPO NR1022171, FILLER .040 2024-T3, PO1022422 IAW 10-02-801-663A. REMOVED WEB SUPPORT BRACKET, FITTING BRACKET AND WIRE BUNDLE BRACKET IAW SRM 51-30-2. TRIMMED OUT CRACK IAW SRM 53-10-2-801-663A 1 X .7500 IN INSP IAW NDT SPM06-10-01 NO INDICATIONS NOTED A2700 MILLEDE FITTING .025 IAW SRM 53-10-02-801-663A ON TRAVELER 2281N01265 FABED FILLER AND DOUBLER IAW 53-10-2-801-663A LOCATED AND DRILLED IAW SRM 51-10-4 TREATED IAW SRM 51-10-3. INSTALLED DOUBLER FILLER BRACKET FITTING WIRE BRACKET IAW SRM 51-10-5.

Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN FLOOR PANEL 102C HAS CORROSION TOP AND BOTTOM AROUND FASTENER HOLES. LOCATED, DRILLED AND DEBURRED FASTENER HOLES IN NEW FLOOR P/N 09-5300-3-3431 IAW DC9 SRM 51-10-4.

Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PAX CABIN/GALLEY FLOOR PANEL 16 HAS CORROSION ON AFT END, ON REPAIR DOUBLER TOP SIDE. REMOVED AND FABRICATED NEW ATTACH PLATE FROM P/N-.080X48X1447075-T6 LOT 102 2531 AND NEW SPACER FROM P/N 7075-T6 LOT 0923042 INSTALLED IAW DC9 SRM 51-30-1.

Part: CUSP WEB — DAMAGED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND LT CUSP WEB HAS 4 EA REPAIRS WITHIN 6 INCHES OF EACH OTHER BETWEEN STA 693 AND 712, OUT OF LIMITS IAW DELTA TOPPS MAN 30-10-70 PAR 6B. REMOVED CUSP WEB IAW SRM 51-30-1, 51-30-2, 51-30-5. FAB AND INSTALLED NEW IAW SRM 51-10-4, DWG 991051 & IAW 51-30-5. FABRICATED RING DOUBLERS AND INSTALLED IAW SRM 51-10-4, 51-30-5 AND DWG SG09530019.

Part: FORMER — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING MHECK FOUND MAIN PASSENGER CABIN APB 6 FORMER RT SIDE FROM FLOOR LEVEL O/B END IS CRACKED. REMOVED OLD FORMER AND CLIPS IAW DC9 SRM 51-30-02 & 51-30-05. RECEIVED NEW FORMER P/N 991555U265 PO 1031907. LOCATED, DRILLED & DEBURRED IAW DC-9 SRM 51-10-04 & 51-13-3 FIG 8A. INSTALLED FORMER & CLIPS IAW DC-9 SRM 51-30-2, 51-30-05, 53-13-3 FIG 8A DWG 9915558.

Part: FRAME — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M CHECK FOUND MAIN CABIN STA 674 RT, FRAME IS CRACKED BELOW 18R. ALL REPAIRS, INCLUDING SRM REPAIRS REQUIRE EA, APPROVAL OF REMOVED FRAME BS674 R/H STR. 18 TO 26 AND ATTACHING FITTINGS, INSTALLED NEW FRAME, REINSTALLED ATTACHING PARTS IAW DC9 SRM 51-30-2, 51-40-1,51-30-5, 53-03 FIG. 2A, 51-10-2,51-10- NS FROM FACTORY SPLICE TO FACTORY SPLICE.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FORWARD CARGO COMPT STIFFENER BELOW LT TIE DOWN TRACK IS BROKEN AT APPROX FS 617. REMOVED AND INSTALLED NEW SUPPORT PART NUMBER 592234461 PO 1031950 IAW DC-9 SRM 51-01 P-226 Q-919 483541.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M CHECK FOUND MAIN CABIN STA 712 LBL 56 FLOORBEAM WEB MISSED DRILLED & PILOT HOLES NOT USED FOUND AFTER REMOVAL OF FRAME REMOVED DAMAGED FLOORBEAM WEB AT STA 712 L/H SIDE LBL 56. FABRICATED NEW FLOORBEAM WEB 7075-T6 .063 IAW DC-9 DWG#19923411. TREATED, PRIMED & INSTALLED NEW FLOORBEAM WEB IAW DC-9 SRM 51-10-3, SRM 51-30-2 & SRM 51-30-5.

Part: STRUT — CRACKED (CARGO BAY) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FORWARD CARGO COMPT RT SIDE STATION 579 VERTICAL STRUT CRACKED LOWER AFT I/B CORNER. REMOVED FASTENERS ORG MATL .025 7075T6 STOP DRILLED CRACK, FABRICATED 2EA DOUBLERS TREATED AND PRIMED AND INSTALLED DOUBLERS IAW DC-9 SRM 51-30-2, 51-30-5, 53-13-2 FIG 4 PO1022687, 51-01 PG 953-01 FIG 2 51-10-3.

Part: FITTING — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND AFT CARGO COMPT OF STA 1151 LT CARGO TIE DOWN TRACK INTERCOSTAL MOUNT CLIP CRACKED. REMOVED CRACKED MOUNT CLIP. FABRICATED NEW CLIP FROM .0407075-T6 MATERIAL PO 1022364 IAW DOUGLAS DRAWING 9915550 REV E AND INSTALLED CLIP IAW DC9 SRM 51-10-40, 51-10-3 AND 51-30-05.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN FLOOR PANEL 73 CRACKED AT AFT END. FABRICATED REPAIR DOUBLER & FILLER IAW DC9 SRM 53-01 FIG 4 SHEET 4. INSTALLED DOUBLER & FILLER IAW DC9 SRM 53-01 SHEET4 FIG 4. ALODINED & PRIMED REPAIR IAW DC9 SRM 51-10-3.

Part: STRUT — CRACKED (CARGO BAY) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FOWARD CARGO COMPARTMENT, LT SIDE, STATION 522, VERTICAL STRUT CRACKED, AT LOWER AFT I/B CORNER. STOP DRILLED CRACK IAW DC-9 SRM 53-01 FIG 2. NDT VERIFIED CRACK CONTAINMENT IAW NDT SPM 06-10-01 .001 FABBED .025 7075T6 P.O.1022687 TREATED, PRIMED AND INSTALLED IAW DC-9 SRM 53-01 FIG 2 51-10-3 TABLE 1 51-30-2,51-30-5.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FORWARD CARGO COMPT STIFFENER BELOW RT TIE DOWN TRACK HAS SEVERAL CRACKS FROM APPROX FS 617 TO APPROX FS 655. REMOVED AND INSTALLED NEW SUPPORT PART NUMBER 5922344-61. PO 1031950 IAW DC-9 SRM 51-01, P-226 Q-919 483541.

Part: SEAT TRACK — CORRODED (BS 200-285) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN STA 200 TO 285, RBL 22 SEAT TRACK HAS CORROSION. ORIGINAL MATERIAL .090, REMOVED .031, REMAINING .059, R & R SEAT TRACK STA 200-285 IAW SRM 51-10-3, 53-01 FIG 1, 51-10-1, 51-30-5, 51-10-2, 51-10-4, 53-05 FIG 4F,51-10-3B, P125.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CABIN FLOOR PANEL NR78 IS CRACKED AT AFT END SCREW HOLE APR 1.5 IN CUT OUT CRACK (ZAE) FLOOR PANEL NR78 1.5"X 4.7" IAW SRM 53-05. MATERIAL IS 7075-T6 .025 PO122211 FILLER, DOUBLER 7075-T6.032, PO1022537. FABRICATED DOUBLER & FILLER IAW SRM 53-03 ALODINED IAW 51-10-3 AND PRIMED. NDT VERIFIED NO CRACK. CONTAINMENT IAW NDT SPM 06-10-01.001, TOOL W-39915 WITH TOOL H-9427 ID REPAIR WITH TAG IAW PROC STANDARD 900-5-11, NR 04, INSTALLED PARTS IAW 53-05.

Part: WINDOW FRAME — CRACKED (BS 889-908) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CABIN/WINDOW FRAME CRACKED BETWEEN STA 889 AND 908 RT SIDE WINDOW 36R AT TOP AFT FASTENER. REMOVED DAMAGE IAW SRM 53-05, FIG 122 FORMED, ALODINED AND PRIMED REPAIR ANGLE IAW 51-10-3 NDT GOOD INSTALLED REPAIR PARTS AND FASTNERS USING MATERIAL 2024 T3 .063 WET WITH SEALANT IAW SRM 53-05, FIG 122H INSP COMPLETED.

Part: CHANNEL — CRACKED (FLOOR PANEL) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN FLOOR PANEL 77 HAS 1EA HAT CHANNEL CRACKED AT END APPROX .5 INCH. ORDERED REPLACEMENT PANEL 77 P/N 09-5300-3-2456 LOCATED DRILLED DEBURRED HOLES IN PANEL 77 IAW DC9 SRM 51-10-4.

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND MAIN CABIN FLOOR PANEL NR67 CRACKED AT END. REMOVED FASTENERS AND SECTION OF SKIN AT DAMAGED AREA FABRICATED FILLER FROM 7075T6 .025 AND DOUBLER FROM 7075T6 .032 USED NDT TO VERIFY NO CRACK EXISTS IAW NDT SPM 06-10-01.001 PRIMED PARTS IAW SRM 51-10-3. INSTALLED DOUBLER AND FILLER IAW SRM 53-05, FIG.1.

Part: FLOOR PANEL — CORRODED (PAX CABIN) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND MAIN PASSENGER CABIN FLOOR PANEL NR70 HAS CORROSION ON TOP OF PANEL AROUND FASTENER HOLES. BLENDED CORROSION AROUND FASTNER HOLES ON CABIN FLOOR PANEL NR70 ORIG MAT .025. REMOVED .008, REMAINING .017 DETERMINED TO BE OUT OF LIMITS IAW SRM 53-01, FIG 1 RECEIVED NEW FLOOR PANEL PART NR09-5300-3-2991. LOCATED & DRILLED FASTNER HOLES ON FLOOR PANEL IAW SRM 51-10-4.

Part: STRUT — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FORWARD CARGO COMPT, LT SIDE, STATION 560, VERTICAL STRUT CRACKED AT LOWER AFT I/B CORNER. STOP DRILLED CRACK IAW DC9 SRM 53-01 FIG 2 NDT VERIFIED CRACK CONTAINMENT IAW NDT SPM 06-10-01.001 FABBED REPAIR DOUBLER .025 7075T6 PO 1022687 IAW DC9 SRM 53-13-2 FIG 2 & 53-01 FIG 2. TREATED, PRIMED & INSTALLED IAW DC9 SRM 51-10-3 & 53-01 FIG 2.

Part: STRUT — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FORWARD CARGO COMPT LT SIDE STATON 541, VERTICAL STRUT CRACKED AT LOWER AFT I/B CORNER. STOP DRILLED CRACK IAW DC9 SRM 53-01 FIG 2 NDT VERIFIED CRACK CONTAINMENT IAW NDT SPM 06-10-01.001 FABBED REPAIR DOUBLER .025 7075T6 PO 1022687 IAW DC9 SRM 53-13-2 FIG.2 & 53-01 FIG 2. TREATED, PRIMED & INSTALLED IAW DC9 SRM 51-10-3 & 53-01 FIG 2.

Part: ATTACH FITTING — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN APB NR5 FORMER FROM FLOOR LEVEL RT SIDE UPPER OTBD ATTACH CLIP IS CRACKED. REMOVED OTBD UPPER CLIP FROM RT NR5 FORMER MAIN CABIN APB IAW SRM 51-30-2. RECEIVED NEW UPPER RT CLIP OTBD IAW SRP DC-9-A-53-10-25-801-663A-A, PG 8. LOCATED, DRILLED, AND DEBURRED 1EA NEW RT UPPER OTBD CLIP IAW SRM 51-10-4. INSTALLED 1EA SRM 51-30-5 & DC-9-A-53-10-25-801-663A-A, P224.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN FLOOR 102C AFT I/B SIDE SKIN LOOSE AND FASTENERS MISSING. FOUND SEVERAL HOLES CRACKED AND OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1. RECEIVED NEW PANEL 102C P/N 9957928-21N LOCATED AND DRILLED HOLES IAW DC9 SRM 51-10-4.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CRACK IN FRAME ATTACH ANGLE AT AFT ACCESSORY COMPARTMENT LEFT SIDE BS 1190 BELOW STRINGER 14. REPAIRED PER DWG 9958239 PAGE 226.

Part: DOUBLER — CRACKED (BS 133) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND FUSELAGE EXTERIOR STA 133 LT SIDE, L1 DOOR HOLD OPEN LATCH DOUBLER HAS APPROX 1 INCH CRACK. R & R FUSELAGE EXTERIOR L1 DOOR HOLD OPEN LATCH DOUBLER PN J060283-3, PO/LOT 0298W028 AT LT FS133 IAW SRM 53-04, FIG 24, SHTS 1-5. TOP COAT PROTECTIVE FINISH APPLIED IAW SRM 51-10-3B.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M- CHECK FOUND MAIN CABIN STA.712 LBL 56 FLOOR BEAM WEB MISSED DRILLED & PILOT HOLES NOT USED FOUND AFTER REMOVAL OF FRAME. REMOVED DAMAGED FLOORBEAM WEB AT STA 712 LT SIDE LBL 56 FABRICATED NEW FLOORBEAM WEB 7075T6 .063 IAW DC9 DWG 19923411. TREATED, PRIMED, & INSTALLED NEW FLOORBEAM WEB IAW DC9 SRM 51-10-3, 51-30-2, & 51-30-5.

Part: STRUT — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND AFT CARGO VERTICAL STRUT AT FWD BLKHD BL 0 CRACKED AT SEVERAL FASTENERS AT LOWER END. REMOVED EXISTING REPAIR IAW DC9 SRM 51-0-2. STOP DRILLED CRACK IAW SRM 53-01 FIG 2. REQUEST NDT TO VERIFY CRACK CONTAINMENT NO CRACK PER NDT SPM 06-10-01.001 MATERIAL USED 7075T6 .025 PO 1022211 AND .032 PO 1022537 FAB 4EA REPAIR ANGLES LOCATED, DRILLED AND DEBURRED HOLES IAW SRM 51-10-4, ALODINED AND PRIMED AND INSTALLED PARTS IAW DC9 SRM 53-01.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND MAIN CABIN FLOOR PANEL NR51 CRACKED AT FWD END FASTENER HOLE. TRIMMED OUT CRACK FROM FLOOR PANEL NR51 WEB (1.7"X 2.2") IAW SRM 53-01 FIG 4 SHT.4 PERFORMED HFEC INSP OF CUTOUT AREA IAW NDT SPM 06-10-01.001 NO CRACKS NOTED. FABBED REPAIR FILLER & DOUBLER FROM .020 7075T6, LOT NR1022528 & INSTALLED IAW SRM 51-10-2, 51-10-4, 51-30-2, & 53-01, FIG 4, SHT 4.

Part: SUPPORT ANGLE — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN STA 712 LBL 45 FLOORBEAM WEB LOWER SUPPORT ANGLE CRACKED. REMOVED DAMAGED ANGLE AT STA 712 LBL 45, FABRICATED NEW SUPPORT ANGLE IAW DC9 DWG 5910464, HEAT TREATED NEW ANGLE PER PEMCO TRAVELER 2281N01724 TREATED, PRIMED, & INSTALLED NEW SUPPORT ANGLE IAW DC9 SRM 51-10-3, 51-30-2, 51-30-5.

Part: DOOR FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND AFT CARGO DOOR JAM STA 1116 TO 1060 LOWER WEB HAS CORROSION UPPER AND LOWER SURFACE. PREVIOUS BLEND. FOUND LOWER WEB TO BE OUT OF LIMITS, IAW DC-9 SRM 53-01 FIG 1 SH 3. RCVD NEW WEB PN 09-5300-3-1055 PO 10227151 IAW DC9 SRM 53-13-3 FIG 3 SH 3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN STA 304-312 BL 0 FLOOR SUPPORT HAS CORROSION. BLENDED CORROSION AT BS 304-312 100 PERCENT MAT LOSS OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1. REMOVED 1EA SPLICE 1EA FLOOR SUPPORT ANGLE NR 35 FLOOR PANEL BS 99-342 BL 0. FABBED 1EA FLOOR SUPPORT ANGLE FROM MAT PN2652479 7075T6 .060 4EA REPAIR ANGLES MAT 7075T6 .050 IAW DC9 SRM 51-70-5 FIG 2. INSTALLED IAW DC9 SRM 51-70-5.

Part: ATTACH ANGLE — CRACKED (NR 2 NACELLE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND NR 2 ENGINE PYLON LOWER ATTACH ANGLE APPROX STA 1136 CRACKED. STOP DRILLED CRACK .25 AT EACH END IAW SRM 54-04, FIG 10, SHEET 2, HFEC INSPECTED STOP DRILL AREA IAW SPM 06-10-01.001 CRACK FOUND TO BE CONTAINED A2700 MAT ID FOR REPAIR ANGLE .050 CRES A286 PO 0540501 IAW SRM 54-04, FIG 10, SHEET 10 LOCATED FABRICATED & DRILLED REPAIR ANGLE IAW SRM 51-10-4 & 54-04 TREATED & PRIMED ANGEL IAW SRM 51-10-3. INSTALLED REPAIR ANGLE IAW SRM 51-30-5, 51-30-2, & 54-04 FIG 10.

Part: DOUBLER — CORRODED (BS 787-837) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

RT MLG W/W-DOOR HINGE ATTACH DOUBLER CORRODED FROM BS 787-837. REMOVED CORROSION. FOUND OUT OF LIMITS MAT LOSS AT 100 PERCENT. MAT ID 0507075-T6 IAW DWG 9923459, REV AE FABRICATED, LOCATED, DRILLED, DEBURRED, TREATED & PRIMED NEW DOUBLER IAW DWG9923459 REV AE & SRM 51-10-4, 51-10-3 51-10-3B.

Part: BULKHEAD — GOUGED (BS 1136) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND MAIN PASSENGER CABIN STA 1136 UPPER LT BULKHEAD WEB FWD SIDE IS GOUGED. GOUGE FOUND OUT OF LIMITS IAW SRM 53-01, FIG 1. REMOVED DAMAGE AND NDT VERIFIED IAW NDT SPM 06-10-01. FABRICATED REPAIR ANGLE FROM .090 7075-0 AND HEAT TREATED TO 7075T6 ON TRAVELER 2281N01220. LOCATED, DRILLED AND DEBURRED REPAIR ANGLE AND FILLER IAW SRM 51-10-4. TREATED AND PRIMED ANGLE AND FILLER IAW SRM 51-10-3 INSTALLED REPAIR WET IAW DC-9-A-51-72-01-801-663A-A AND SRM 51-30-5.

Part: LONGERON — CRACKED (BS 389 L17R) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN STA 389, LONGERON 17 RT IS CRACKED AT FRAME IAW 5310-01313-01, STEP 4 PRIOR TO FURTHER FLIGHT. REMOVED SPLICE AT BS 399, RT L-17 IAW SRM 51-30-2 & 51-30-05. CUT OUT SECTION RT LONGERON 17 RS 379-399 IAW SRM 53-02, FIG 18. FABRICATED SPLICE FROM MAT PN 00-210-31972 PO 0299WO032. FABRIATED LONGERON FROM MAT PN 2777922-3 PO 1021994 INSTALLED SECTION LONGERON & SPLICES IAW SRM 53-02, FIG 18. REQUIRED INSP COMPLETED.

Part: BULKHEAD — GOUGED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING “M” CHECK FOUND MAIN PASSENGER CABIN STA 1136 UPPER RT BULKHEAD WEB FWD SIDE IS GOUGED BLENDED AREA. ORIGINAL MAT .080. REMOVED .048, FOUND TO BE OUT OF LIMITS IAW DC9 SRM 51-01 FIG 1. CUT OUT DAMAGED AREA. NDT VERIFIED NO CRACKS NOTED. FABRICATED,PRIMED,DEBURRED,TREATED & PRIMED NEW ANGLE REPAIR & FILLER. INSTALLED REPAIR & FILLER IAW DC9 SRM A-51-72-01-001 & 51-30-05.

Part: CUSP WEB — DAMAGED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FWD WET AREA RBL 44 BETWEEN STA 237 AND 285 RT CUSP WEB HAS ENLONGATED FASTENER HOLES. TRIMMED 48FT SECTION DAMAGE CUTOUT. PERFORMED HFEC INSP IAW DC-9 SPM 06-10-01.001. FOUND DAMAGE TO BE CONTAINED.A2700. FABBED & INSTALLED 1 EA REPAIR DOUBLER .025 7075T6 REPAIR FILLER .020 7075T6 IAW TRM DC9 A-53-10-16-801-663A.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN STA 237-304 BL 0 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1. REMOVED FLOOR SUPPORT FABRICATED IAW DC9 SRM 53-13-1 FIG 11. USING EXTRUSION S2652479 7075T6 PO 1202199. INSTALLED NEW FLOOR SUPPORT IAW DC9 SRM 51-30-5.

Part: WINDOW FRAME — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CRACK IN CABIN WINDOW FRAME BETWEEN BS 870 AND BS 889 LEFT SIDE WINDOW 35. REPAIRED PER SRM 53-05 FIGURE 122, SPM 06-10-01.001, SRM 51-10-4.

Part: WINDOW FRAME — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CRACK IN CABIN WINDOW FRAME BETWEEN BS 579 AND BS 598 RIGHT SIDE AT AFT UPPER END. REPAIRED PER DC9 A-56-20-02-801-663A-A FIGURE 1, SRM 51-10-4.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN INTERCOSTAL STA 693-712 5-16 LT CRACKED AT END APPROX .25 INCH. FURTHER OPEN-UP FABRICATED NEW INTERCOSTAL FROM 7075-0 PO 0724051 HEAT TREATED ON TRAVELER 2281N01690.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN STA 313 LBL 1-20 FLOOR SUPPORT CRACKED. REMOVED FLOOR SUPPORT AT STA 313 LBL 1-20 IAW DC-9 SRM 51-30-2. FABRICATED PART FROM .050"2024 T3 IAW DC-9 SRM 53-13-2 FIG 4. TREAT AND PRIMED PART IAW DC-9 SRM 51-10-3. INSTALLED PART IAW DC-9 SRM 53-13-2 FIG 4 51-30-2 PG 1-15.

Part: STOP FITTING — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN PASSENGER CABIN LT SIDE DOOR JAMB CENTER STOP FITTING CRACKED. REMOVED CRACKED DOOR STOP FITTING IAW DC-9 SRM 51-30-2 & 51-30-5. RECEIVED NEW FITTING LOCATED, DRILLED, DEBURREED & TREATED HOLES IAW DC-9 SRM 51-10-3 & 51-10-4. INSTALLED NEW FITTING IAW DC-9 SRM 51-30-2 & 51-30-5.

Part: FLOOR SUPPORT — CRACKED (BS 160-200) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK, FOUND MAIN PASSENGER CABIN STA 160-200, LBL 56, FLOOR SUPPORT CRACKED 4EA PLACES. REMOVED DAMAGED FLOOR SUPPORT FROM FS 160 TO FS 200, LBL 56. RECEIVED Z ANGLE FLOOR SUPPORT PN S4616493-12500. CUSTOMER FURNISHED. LOCATED AND DRILLED HOLES IN NEW Z ANGLE. INSTALLED NEW Z ANGLE FLOOR SUPPORT IAW SRM 51-30-2.51-30-5 AND 51-10-4.

Part: ANGLE — DAMAGED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

MAIN PASSENGER CABIN BETWEEN STA 794-813 RBL 55 Z-ANGLE SUPPORT FASTENER HOLES BROKEN OUT. REMOVED AND RE-INSTALLED 1 EACH Z-ANGLE AT STA 794-813 IAW DC9 SRM 51-30-5 & 51-30-2. LOCATED, DRILLED & DEBURRED IAW DC9 SRM 51-10-4. REMOVED AND RE-INSTALLED 2 EACH CLIPS IAW DC9 SRM 51-30-2.

Part: STOP FITTING — CRACKED (DOOR FRAME) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN AFT ENTRY DOOR JAMB CENTER DOOR STOP FITTING CRACKED. REPAIRED PER SRM 51-30-2, SRM 51-10-3, SRM 51-10-4, SRM 51-30-5 PAGE 226.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CABIN FLOOR PANEL 63 HAS CRACK IN SKIN AT AFT END. REPAIRED PER SRM 53-23-0-FIGURE 4, SRM 51-30-2, SRM 53-01 FIGURE 4, SRM 51-20-0 & SRM 51-10-3.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CRACK IN LONGERON 16L AT BS 1136. REPAIRED PER SRM 51-30-5, SRM 51-10-2, SRM 51-10-4, SRM 53-02 FIGURE 18 SHEETS 1-3.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN FLOOR PANEL NR 62 FORWARD END RIVET HEAD PULLED AND CRACKED. REPAIRED PER SPM 06-10-01, SRM 53-05 FIGURE 1 & SRM 51-30-1.

Part: FLOOR PANEL — PUNCTURED (CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND MAIN CABIN FLOOR PANEL 98 HAS 1EA PUNCTURE HOLE. REPAIRED PER SPM 06-10-01, SRM 53-05 FIGURE 1, SRM 51-10-4 & SRM 51-30-2.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CRACK IN MAIN CABIN FLOOR PANEL 59 TOP SIDE. REPAIRED PER SRM 53-01- FIGURE 4 SHEET 4, SPM 06-10-01, SRM 51-10-3 & SRM 51-30-2.

Part: FLOOR PANEL — CRACKED (CABIN) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CORROSION ON MAIN CABIN FLOOR PANEL NR 44 INBOARD SIDE SKIN. REPAIRED PER SRM 53-01-FIGURE 4.

Part: FRAME — GOUGED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND GOUGE IN MAIN CABIN FRAME AT BS 256 BETWEEN L11L AND L12L. REPAIRED PER SRM 53-01 FIGURE 1, SRM 51-10-9 & DC9-A-53-10-05-801-663A-A.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FASTENER HOLE CRACKED OUT ON EXISTING REPAIR TO MAIN CABIN FLOOR PANEL NR 79 SKIN. REPAIRED PER SRM 51-10-4.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CORROSION ON RIGHT CUSP WEB BETWEEN BS 237 AND BS 256. REPAIRED PER DC9-A53-10-16-801-663A-A, SRM 53-01 FIGURE 1, SRM 51-30-2 & SRM 51-10-3.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CRACK IN MAIN CABIN FRAME SHEAR ANGLE AT BS 313 L15L. REPAIRED PER SRM 51-10-4, SRM 51-10-3 & SRM 51-30-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CORROSION ON MAIN CABIN FLOOR SUPPORT AT BS 200 LBL 1 - LBL 20. REPAIRED PER SRM 51-10-3, SRM 53-01 FIGURE 1, SRM 51-30-5 & DWG 9923484.

Part: SKIN — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CRACK IN FUSELAGE SKIN AT FASTENER BS 1209 BETWEEN L13R AND L14R. REPAIRED PER SRM 53-01 FIGURE 2, SRM 51-10-4 & SRM 51-10-3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CORROSION ON MAIN CABIN FLOOR SUPPORT AT BS 237 RBL 1- RBL 22. REPAIRED PER SRM 51-10-3 SRM 51-10-4, SRM 51-30-2 SRM 51-60-0 & DWG 9923484.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CORROSION ON FLOOR SUPPORT AT BS 160 TO BS 200 RBL 44. REPAIRED PER SRM 51-30-5, SRM 51-10-1, SRM 53-13-1, SRM 51-10-2, SRM 51-10-4, SRM 51-60-5 & DWG G9923484.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CORROSION ON MAIN CABIN FLOOR SUPPORT AT BS 200 RBL 1- RBL 20. REPAIRED PER SRM 51-10-3, SRM 53-01 FIGURE 1, SRM 51-30-2, SRM 51-30-5, SRM 51-60-0 & DWG 9923484.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FORWARD CARGO COMPT STA 408 ABOVE DOOR OPENING FLOORBEAM SUPPORT IS CRACKED. REMOVED CRACKED SUPPORT, OBTAINED NEW SUPPORT PO 0307W016 PN 9957907-3, DRILLED AND DEBURRED AND INSTALLED IAW DC-9 SRM 51-30-5 & 51-10-4

Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CORROSION AROUND FASTENER HOLES ON MAIN CABIN FLOOR PANEL 64. REPAIRED PER SRM 53-23-0 FIGURE 5, SRM 51-10-4.

Part: FLOOR PANEL — CORRODED (MAIN DECK) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND FLOOR PANEL NR26 HAS CORROSION ALONG FWD END, TOP AND BOTTOM SIDES. REMOVED 3 STIFFENERS AND TOILET DRAIN FROM PANEL IAW SRM 51-30-2. FAB NEW PANEL HAT IAW DWG NR9957918. ALODINED NEW PANEL HAT IAW SRM 51-10-3. PRIMED IAW SRM 51-10-3. PAINTED IAW SRM 51-10-3. INSTALLED HAT ON PANEL WET IAW ER/A 486156-14.

Part: LONGERON — CORRODED (BS 120-130 L30) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND LONGERON AT E & E COMPT BETWEEN STA 120 AND 130 AT L30 HAS CORROSION AROUND FASTENERS. REMOVED, FABRICATED AND INSTALLED NEW LONGERON SECTION FROM IAW SRM 51-30-5 AND 51-30-2.

Part: FLOOR PANEL — CORRODED (CARGO BAY) · corrosion level 2 · airframe 79,541 hrs · 80,345 cycles

DURING M-CHECK FOUND CORROSION ON AFT CARGO FLOOR PANEL 2, 3 RIB. REPAIRED PER SRM 51-30-1 PAGE 241.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CORROSION ON FLOOR SUPPORT AT BS 200 RBL 45- RBL 55. REPAIRED PER SRM 51-30-05 PAGE 226.

Part: WINDOW FRAME — CRACKED (FUSELAGE) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CABIN/ WINDOW FRAME CRACKED BETWEEN STA 794 AND 813 (WINDOW 31L) AT TOP FWD FASTENER. REMOVED DAMAGE AT STA 794-813 IAW 53-05 FIG 122, NDT GOOD, FABRICATED PART 7075-T3 PO 0922430 IAW 53-05, ALODINED, PRIMED REPAIR IAW 51-10-3, INSTALLED REPAIR ANGLE IAW 53-05 FIG 122.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CORROSION ON MAIN CABIN FLOOR SUPPORT AT BS 160 - BS 218 BL 0. REPAIRED PER SRM 51-10-3, SRM 51-10-4, SRM 51-10-5, SRM 51-30-2 & SRM 51-60-0 DWG 9923484.

Part: SUPPORT ANGLE — CRACKED (TE FLAP) · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND RIGHT WING FLAP IN SIDE ACCESS HOLE I/B SIDE OF NR 4 FLAP HINGE SUPPORT ANGLE IS CRACKED 2 EA PLACES AT UPPER ATTACH BOLTS. REMOVED AND INSTALLED NEW FORMER IAW DC-9 SRM 51-30-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 79,541 hrs · 80,395 cycles

DURING M-CHECK FOUND CORROSION ON MAIN CABIN FLOOR SUPPORT AT BS 200 RBL 24-RBL 24. REPAIRED PER SRM 53-01, SRM 51-10-4, SRM 51-10-5, SRM 51-60-0 DWG 9923984.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 78,437 hrs · 79,433 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT ROW 15 IN THE CABIN WAS INOPERATIVE. MAINTENANCE REPLACED THE LIGHT ASSEMBLY AND FUNCTIONALLY CHECKED IT.

Part: RIB — CRACKED (LT WING) · airframe 77,117 hrs · 78,277 cycles

DURING "L" CHECK FOUND CRACK IN LT WING LEADING EDGE RIB AT STA 134.921. REPAIRED PER EA 98-215904.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 76,050 hrs · 77,340 cycles

DURING LINE CHECK MX FOUND THAT THE RT SIDE EXTERIOR EMERGENCY FLOOD LIGHT WAS INOPERATIVE. MX REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OP CONDITION.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 76,031 hrs · 77,321 cycles

DURING LINE CHECK, MX FOUND THAT THE LAST EMERGENCY PATHWAY LIGHTING IN THE VENTRAL STAIRWAY WAS INOPERATIVE. MX FOUND A BROKEN WIRE AND REPAIRED IT.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 76,031 hrs · 77,321 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN THE VENTRAL STAIRWAY WAS INOPERATIVE. MX REPLACED THE BATTERIES. OPS CHECK WAS GOOD.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 75,544 hrs · 76,887 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN THE AFT SECTION HAD FAILED. MAINTENANCE REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION. (S)

Part: PULLEY — DEFECTIVE (AILERONS) · airframe 75,544 hrs · 76,887 cycles

FLIGHT RETURNED TO A SAFE LANDING AT DTW AFTER CREW DETERMINED AILERONS WERE BINDING DURING LT TURNS. CONTROL CHECK WAS NORMAL ON THE GROUND BOTH BEFORE TAKEOFF AND DURING TAXI IN AFTER RETURN. LT TURNS REQUIRED THE MOST EFFORT BUT AILERON CONTROL WAS DIFFICULT IN BOTH DIRECTIONS AND ROLL RESPONSE WAS NOTABLY SLOW WITH AUTOPILOT ENGAGED. MAINTENANCE REPLACED A DEFECTIVE AILERON CONTROL PULLEY IN THE RT WING. CABLE TENSION AND RIG WAS ACCOMPLISHED AND THE SYSTEM RETURNED TO OPERATIONAL CONDITION. (S)

Part: RELAY — FAILED (EMERGENCY LIGHTS) · airframe 75,429 hrs · 76,788 cycles

DURING THE LINE CHECK, MAINTENANCE FOUND THAT THE EXTERIOR EMERGENCY FLOOD LIGHT WAS INOPERATIVE. MAINTENANCE REPLACED THE POWER SUPPLY AND RELAY R2-271 BUT NEITHER PROCEDURE CORRECTED THE FAULT. AFTER RELAY R2-49 WAS REPLACED THE EXTERIOR EMERGENCY LIGHT FUNCTIONED PROPERLY. (A)

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 74,959 hrs · 76,365 cycles

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

Part: SKIN — CRACKED (BS 1100 S23-25R) · airframe 74,097 hrs · 75,607 cycles

DURING "H" CHECK, FOUND CRACK IN EXISTING REPAIR DOUBLER AT THE AFT EDGE OF AFT CARGO DOOR CUTOUT BS 1100 L23R-L25R. REPAIRED PER EA 98-211036.

Part: DUCT — SEPARATED (A/C BAY) · airframe 62,695 hrs · 65,308 cycles

WHILE EN ROUTE AT 33,000 FT WITH CABIN PRESSURIZATION OPERATING IN MANUAL MODE, THE CREW HAD DIFFICULTIES MAINTAINING CABIN ALTITUDE WITHOUT OPERATING THE LEFT PACK AT FULL HOT. THE PACK'S OVERTEMP PROTECTION TRIPPED AND CREW LOST CONTROL OF PRESSURIZATION. THE CABIN CLIMBED TO 10,000 FT. PERFORMED COM PROCEDURE AND THE CREW MADE AN EMERGENCY DESCENT TO 10,000 FT. FLIGHT DIVERTED TO MEM AND LANDED SAFELY. MAINTENANCE FOUND A 4 INCH DUCT ON THE FORWARD SIDE OF THE ACM AND 1.25 INCH DUCT ON THE AFT SIDE OF THE ACM SEPARATED. RE-ATTACHED THE DUCTS, REPLACED THE CLAMPS, AND RETURNED THE AIRCRAFT TO SERVICE.

Part: SLIDE — INOPERATIVE (FWD FUSELAGE) · airframe 62,513 hrs · 65,142 cycles

DURING LINE CHECK, DISCOVERED RESERVOIR TO BE AT ZERO PSI. REPLACED THE SLIDE AND RETURNED REMOVED SLIDE TO SHOP FOR REPAIR.

Part: BRACKET — CRACKED · airframe 62,535 hrs · 65,162 cycles

During M ck in ATL and while accomplishing the rework per amitask Job #116. The left and Right brackets, P/N 995786-5/-6 brackets, made from .063" thick 7075-t6 aluminum clad sheet. Repaired per EA 98-185170.

Part: BULKHEAD — CRACKED · airframe 62,535 hrs · 65,162 cycles

A radial crack was found in the 5910130-13 doubler that ran under the 5910130-11 channel. Inspection was unable to verify if the radial crack had terminated in a fastener hole or if it had been previously stopdrilled since the 5910130-11 channel covers the end of the crack. Repaired per EA 98-185173.

Part: CONTROL VALVE — CONTAMINATED (RT A/C PACK) · airframe 61,182 hrs · 63,987 cycles

FLIGHT ATTENDANT NOTIFIED CREW OF THE RIGHT AFT LAV SMOKE DETECTOR IN ALARM ALONG WITH A SMELL OF SMOKE IN THE AFT CABIN. AN EMERGENCY WAS DECLARED AND A SAFE LANDING WAS MADE IN JAX. NO EVIDENCE OF FIRE OR SMOKE WAS FOUND AFTER LANDING. SOME OIL RESIDUE WAS FOUND IN THE RIGHT WATER SEPARATOR TEMPERATURE CONTROL VALVE. REPLACED THE RIGHT WATER SEPARATOR TEMPERATURE CONTROL VALVE. REPLACED THE RIGHT WATER SEPARATOR BAG PRECAUTIONARY. AIRCRAFT RETURNED TO SERVICE.

Part: LIGHT — CORRODED (CATWALK) · airframe 60,492 hrs · 63,357 cycles

DURING LINE CHECK, FOUND EMERGENCY ESCAPE PATH LIGHT NEAR CABIN FLOOR IN AFT CATWALK INOPERATIVE. MAINTENANCE FOUND A CORRODED CIRCUIT BOARD INSIDE THE LIGHT MODULE. REPLACED THE LIGHT MODULE. OPERATIONAL CHECK NORMAL.

Part: DOUBLER — CORRODED (CARGO STRAP) · corrosion level 2 · airframe 59,171 hrs · 62,167 cycles

AFT CARGO STRAP DOUBLER HAS CORROSION AROUND ENTRY WAY LOWER SECTION IN SEVERAL SPOTS. BLENDED CORROSION, REMAINING THICKNESS RANGED .036 TO .063 OUT OF LIMITS. REPAIRED PER EA 98-171635.

Part: FAN — FAILED (RT LAVATORY)

AFTER TAKEOFF, FLIGHT ATTENDANT REPORTED SMOKE ALARM IN RIGHT LAVATORY GOING OFF WITH A BURNING SMELL. CREW DECLARED AN EMERGENCY AND THE FLIGHT WAS RETURNED TO ATL. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE RIGHT GROUND COOLING FAN AND LAVATORY SMOKE DETECTOR, OPERATIONAL CHECK NORMAL.

Part: SWITCH — INOPERATIVE (TE FLAP)

DURING CLIMBOUT, THE LANDING GEAR WARNING HORN SOUNDED AND THE LANDING GEAR UNSAFE INDICATION ILLUMINATED. THE FLIGHT CREW FOLLOWED COM PROCEDURES, RETURNED TO MEM, AND LANDED WITHOUT INDICDENT. MAINTENANCE REPLACED THE S1-85 FLAP SWITCH, OPERATIONAL CHECK NORMAL.

Part: BATTERIES — DISCHARGED (CABIN)

DURING LINE MAINTENANCE INSPECTION, FOUND FLOOR PROXIMITY EMERGENCY LIGHTS BETWEEN ROWS 19 THRU 22 INOPERATIVE. REPLACED BATTERIES, OPERATIONAL CHECK NORMAL.

Part: COMPUTER — INOPERATIVE (E/E COMPARTMENT)

DURING CLIMBOUT, THE FIRST OFFICER'S GROUND PROXIMITY SYSTEM, ALTIMETER, ALTITUDE ALERT SYSTEM (AUTO-PILOT AND NR 2 NAV SYSTEM) BECAME INOPERATIVE. FLIGHT RETURNED TO ORIGINATION AND LANDED WITHOUT INCIDENT. ON FINAL APPROACH TO LANDING, FLIGHT CREW NOTED THAT ALL INSTRUMENTS BECAME OPERABLE. MAINTENANCE REPLACED THE NR 2 AIR DATA COMPUTER, OPERATIONAL CHECK NORMAL.

Part: BATTERIES — DISCHARGED (TAIL CONE)

DURING LINE CHECK, FOUND EMERGENCY LIGHTS IN THE TAIL CONE AREA WEAK. REPLACED BATTERIES IN THE EMERGENCY LIGHT PACK B5-28, OPERATIONAL CHECK OK.

Part: WIRE — LOOSE (CABIN)

DURING LINE CHECK, FOUND OVERHEAD EMERGENCY LIGHTS DIM AT ROW 1. REPAIRED GROUND WIRE TO LIGHT, OPERATIONAL CHECK OK.

Part: RELEASE MECH — OUT OF ADJUST (TAIL CONE)

DURING L-CHECK, FOUND THAT EXCESSIVE FORCE WAS REQUIRED TO REMOVE TAIL CONE RELEASE HANDLE FROM CLIPS AND TO RELEASE TAIL CONE. RIGGED RELEASE SYSTEM, ADJUSTED LOWER LEFT CORNER ALIGNMENT PINS, FUNCTIONAL CHECK OK.

Part: SKIN — CRACKED (RT ELEVATOR)

DURING L CHECK, FOUND CRACKS ON RIGHT ELEVATOR LOWER SKIN AT ELEVATOR STA XE62. REPAIRED PER EA 98-115410.

Part: N1 INDICATOR — MALFUNCTIONED (RT ENGINE)

DURING TAKEOFF ROLL, THE RIGHT ENGINE N1 INDICATION WAS ABNORMALLY LOW. CREW ABORTED TAKEOFF AND RETURNED TO THE GATE. MAINTENANCE REPLACED THE N1 INDICATORS FOR BOTH ENGINES, OPERATIONAL CHECK OK.

Part: PROX SWITCH — FAILED (NLG)

AFTER TAKEOFF, NOSE GEAR UNSAFE LIGHT REMAINED ON AFTER GEAR RETRACTION. RECYCLED GEAR, LIGHT REMAINED ON, INDICATION NORMAL WITH GEAR DOWN. FLIGHT CONTINUED TO ORD AND LANDED WITHOUT INCIDENT. FOUND NOSE GEAR DOWNLOCK PROXIMITY SWITCH WITH DELAMINATED FACE. REPLACED SWITCH PROXIMITY SENSOR, OPERATIONAL CHECK OK.

Part: HYD QTY IND — MALFUNCTIONED (RT HYD SYST)

DURING CLIMBOUT, THE RIGHT HYDRAULIC SYSTEM QUANTITY INDICATION WENT TO ZERO. PERFORMED COM AND DIVERTED TO ATL. AIRCRAFT LANDED WITHOUT INCIDENT. FOUND RIGHT HYDRAULIC SYSTEM INDICATOR INOPERATIVE. REPLACED RIGHT HYDRAULIC SYSTEM INDICATOR AND TRANSMITTER. LEAK AND OPERATIONAL CHECK GOOD.

Part: BULKHEAD — CRACKED (NR 2 PYLON)

DURING LINE CHECK, FOUND A CRACK IN THE NR 2 ENGINE PYLON OUTER BULKHEAD. REPAIRED BULKHEAD (P/N 9958159-62) PER EA 98-099525.

Part: COMPRESSOR — STALLED (NR 2 ENGINE)

THE NR 2 ENGINE COMPRESSOR STALLED ON TAKEOFF ROLL. THE TAKEOFF WAS ABORTED AND THE AIRCRAFT RETURNED TO THE GATE. MAINTENANCE REMOVED A PIECE OF CARDBOARD FROM THE INLET AND INSPECTED THE ENGINE. NO DISCREPANCIES WERE NOTED. ENGINE PERFORMANCE RETURNED TO NORMAL.

Part: BATTERY PACK — DISCHARGED (CABIN)

DURING LINE CHECK, FOUND CEILING LIGHTS INOPERATIVE ROWS 15 THROUGH 19. MAINTENANCE REPLACED BATTERIES AND POWER PACK, OPERATIONAL CHECK GOOD.

Part: BATTERIES — DISCHARGED (COCKPIT)

DURING PREFLIGHT CHECK, FOUND COCKPIT EMERGENCY LIGHTS INOPERATIVE. REPLACED BATTERIES AND OPERATIONAL CHECK GOOD.

Part: SWITCH BRACKET — LOOSE (CABIN DOOR)

DTW-RDU - DURING TAKEOFF AT APPROXIMATELY 80 KNOTS, THE AFT CABIN DOOR WARNING LIGHT ILLUMINATED. ABORTED TAKEOFF AND RETURNED TO THE GATE WITHOUT FURTHER INCIDENT. FOUND AND TIGHTENED A LOOSE WARNING SWITCH BRACKET, CHECKED OK.

Part: TR UNLOCK SW — FAILED (NR 1 ENGINE)

NR 1 THRUST REVERSER UNLOCK WARNING ILLUMINATED SHORTLY AFTER TAKEOFF. STAYED ON APPROXIMATELY 15 MINUTES THEN EXTINGUISHED. THE FLIGHT RETURNED TO MSP AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE REVERSER UNLOCK SWITCH. SUBSEQUENT FUNCTIONAL TEST WAS SATISFACTORY.

Part: SUPPORT — CORRODED (FS 237-264)

DURING H-CHECK, FOUND CORROSION ON THE CENTER LINE FLOOR SUPPORT FROM FS 237 TO 264. REPAIRED SUPPORT (P/N5910760-11), PER EA 98-103279.

Part: SEAT TRACK — CORRODED (FS 230)

DURING H-CHECK, FOUND CORROSION IN THE RIGHT INBOARD SEAT TRACK AT FS 230. REPAIRED TRACK (P/N 5910754-11), PER EA 98-101978.

Part: HINGE — CORRODED (NR 2 FLAP)

DURING H-CHECK, FOUND CORROSION ON THE NR 2 FLAP FORWARD HINGE FITTING AT THE UPPER STUD HOLES. REPLACED HINGE (P/N 5919218-505), PER CITEXT 09-5740-1-9800.

Part: FITTING — CRACKED (AFT ENTRY DOOR)

DURING H-CHECK, FOUND A CRACK IN THE AFT ENTRY DOOR LOWER HORIZONTAL BEAM END FITTING. REPLACED FITTING PER SRM 51-30-2.

Part: RELEASE MECH — OUT OF ADJUST (RT EMER EXIT)

DURING H-CHECK, FOUND THAT INADEQUATE FORCE WAS REQUIRED TO RELEASE THE RIGHT AFT OVERWING EMERGENCY EXIT DOOR. ADJUSTED THE EXIT DOOR PER MM 52-21-10 STEP G, CHECKED OK.

Part: FITTING — CRACKED (LT MLG)

DURING H-CHECK, FOUND A CRACK IN THE LEFT MAIN LANDING GEAR FITTING, LOWER INBOARD AND OUTBOARD BOLT HOLES. REPLACED FITTING PER CITEXT 09-5740-1-0006.

Part: FITTING — CORRODED (MLG ATTACH)

DURING H-CHECK, FOUND CORROSION ON THE RIGHT MAIN LANDING GEAR FITTING SIDE BRACE LUG. REPLACED FITTING.

Part: CLIPS — OUT OF ADJUST (TAILCONE)

DURING H-CHECK, FOUND THAT EXCESSIVE FORCE WAS REQUIRED TO RELEASE THE INTERIOR TAILCONE HANDLE FROM THE CLIPS. ADJUSTED THE CLIPS, CHECKED OK.

Part: AIR DATA COMP — MALFUNCTIONED (E/E COMPARTMENT)

CAPTAIN'S ALTIMETER RED FLAG APPEARED ON TAKEOFF ROLL, ABORTED TAKEOFF AT 80 KNOTS. AIRCRAFT RETURNED TO THE GATE. REPLACED AIR DATA COMPUTER, OPERATIONAL CHECK OK. AIRCRAFT RETURNED TO SERVICE.

Part: COMPRESSOR — STALLED (NR 1 ENGINE)

NR 1 ENGINE EXPERIENCED COMPRESSOR STALLS ON TAKEOFF ROLL. THE TAKEOFF WAS ABORTED. THE AIRCRAFT RETURNED TO THE GATE. MAINTENANCE REPLACED THE ENGINE AND PERFORMED A GROUND RUN-UP. THE ENGINE SYSTEMS CHECKED OK. THE AIRCRAFT RETURNED TO SERVICE.

Part: DUCT — LOOSE (RT ACM)

TAIL COMPARTMENT TEMPERATURE HIGH LIGHT ILLUMINATED DURING INITIAL CLIMBOUT. FLIGHT RETURNED TO TPA AND LANDED WITHOUT INCIDENT. REINSTALLED FLEX DUCT AT RIGHT ACM OUTLET. ALSO, TIGHTENED CLAMPS AT LEFT AUGMENTATION VALVE. OPERATIONAL CHECK OK. AIRCRAFT RETURNED TO SERVICE.