N910DL

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 81,550 hrs · 63,093 cycles

EMERGENCY LIGHTS IN CEILING PANELS BETWEEN ROWS 22-31 NOT ILLUMINATING. REPLACED BATTERIES TO CHARGERS PER MD88 AMM 33-53. (LP5243663)

Part: STRUCTURE — CRACKED (FWD SERVICE DOOR) · airframe 81,496 hrs · 63,041 cycles

FWD SERVICE DOOR UPPER FWD CORNER HAS CRACK INDICATION AT ONE FASTENER MARKED. REF AMDS 5240-2344 STEP 1. REPAIRED PER SRM SRM 53-05 FIGURE 176. (LP0861915)

Part: UNKNOWN — ODOR (CABIN) · airframe 81,388 hrs · 62,944 cycles

EXHAUST FUMES SMELLED AT AFT FA JUMPSEAT RIGHT AFTER TAKEOFF AFT LEFT LAV SMOKE DETECTOR ACTIVATED. SMELL WENT AWAY IN LESS THAN ONE MIN. AND SMOKE DETECTOR STOPPED SOUNDING. R/R APU PER MD88 AMM 49-10. APU STARTS OK APU OK FOR SERVICE. REMOVED CROSS OVER DUCT AND FOUND NO SIGNS OF OIL. REMOVED DUCTS ON THE AFT AND FWD OF ACMS. NO OIL NOTED AT THIS TIME. OPENED BOTH ENG SADDLE DUCTS FOR BORO NO OIL FOUND IN ANY OF THE SADDLE DUCTS OF EITHER ENG. ALL DUCTS AND BOTH ENG INLETS WERE INSPECTED FOR OIL WITH BLACK LIGHT NO OIL NOTED AT THIS TIME. ALL DUCTS WORKED WERE PREVIOUSLY INSTALLED ALL LEAK CHEK GOOD. (LP4569046)

Part: UNKNOWN — ODOR (CABIN) · airframe 81,388 hrs · 62,943 cycles

AT DEPARTURE AFTER AFT AIRSTAIRS CLOSED AFT LAV SMOKE DETECTOR ACTIVATED AND EXHAUST SMELL NOTICED AFT CABIN APU AIR ON AND EXTERNAL AIR SOURCE ALSO ON. C/W ODI PREVENTION T/S PER ATA 2172 NO/GO ODI C/W WORK CARDS 2120-2367 AND 7100-2619 REF NO GO ODI LOG 0829264 OK FOR SERVICE. (LP4569030)

Part: HYDRAULIC LINE — LEAKING (THRUST REVERSER) · airframe 81,279 hrs · 62,851 cycles

FUME EVENT ON CLIMBOUT AND DESCENT AT 12K ALTITUDE BOTH TIMES WITH ENG A/I USAGE. AFT LAV, CAPT SIDE, FIRE ALARM ACTIVATED. WENT OUT AFTER 5 MINS. NO SMOKE OF FIEW REPORTED. FOUND APU AIR INLET CONTAMINATED WITH HYD FLUID. LEFT THRUST REVERSER CNTL VALVE UPPER LINES HAS PIN HOLE AT BEND. FABRICATED NEW HYD PER AMM 20-12. C/W APU CLEANG PER W/C 4900-1185. R-R LT HYD T-REV DEPLOY LINE PER AMM 29-21. NEW LT T-REV DEPLOY LINE LEAKS AT B-NUT ON VALVE. REQUIRES NEW LINE. REMOVED LR T-REV DEPLOY LINE PER AMM 29-21. REPLACED LT T-REV DEPLOY LINE REQUIRES LEAK CHECK. REPLACED LINE IAW AMM 29-21. LEFT THR REV DEPLOY LINE HYD LINE LEAK CKS GOOD. NR 2 ENG CHG DUE TO OIL CONTAMINATION ON LOG 5037935. FUME EVENT WORKED ON NO GO ODI LOG 0800338. (LP5037932)

Part: BATTERY — DISCHARGED (CABIN) · airframe 80,981 hrs · 62,585 cycles

ON SVC CHK FOUND LEFT AND RIGHT AFT OVERWING EXIT SIGN IDENTIFIERS LAMPS INOP. REMOVED AND REPLACED BATTERY PACK SUPPLY BATTERIES PER AMM 33-53. OPS CHK GOOD.

Part: HYDRAULIC LINE — UNSECURE (THRUST REVERSER) · airframe 80,690 hrs · 62,339 cycles

FLIGHT ATTENDANT REPORTED SMOKE/FUMES IN THE AFT CABIN. MAINTENANCE FOUND AND REPAIRED A HYDRAULIC LEAK AT THE LEFT THRUST REVERSER ISOLATION VALVE BY SECURING THE RETURN LINE. NO-GO ODI PREVENTION PROCEDURES WERE COMPLIED WITH.

Part: SERVICE PANEL — DAMAGED (WING) · airframe 80,686 hrs · 62,334 cycles

FUEL DOOR OPEN ON ARRIVAL/FUEL DOOR DAMAGED. REMOVED AND REPLACED FUEL SERVICE PANEL DOOR IAW AMM 57-30. OPS CHECK GOOD. C/W ERA 570489-14 REV ORG. SECTION 1 TIME LIMITED REPAIR. C/W TERMINATING REPAIR AT NEXT CCK AND INITIAL INSPECTION WITHIN 7 DAYS. CORRECTED LRU TO NR 2 RT SLAT FTN 329ARB.

Part: PANEL — CRACKED (LE SLAT) · airframe 80,618 hrs · 62,270 cycles

CRACK INDICATION ON COVE PANEL AT CENTER ATTACH POINT. NR 2 LT SLAT REP REF RC 2700-4224-LH-02.

Part: STRUCTURE — CRACKED (LT WING) · airframe 80,618 hrs · 62,270 cycles

ON WALK AROUND FOUND 2 INCH CRACK LT WING NR 2 UNDER NR 2 SLAT.

Part: SEAT TRACK — DAMAGED (BS 279) · airframe 79,482 hrs · 61,330 cycles

WHILE TROUBLESHOOTING A FAULT, FOUND ELECTRICAL ARC DAMAGE ON THE SEAT TRACK AT BS 279. REPAIRED THE SEAT TRACK IAW PRI 565645-14, REV 0.

Part: SEAT TRACK — DAMAGED (BS 279) · airframe 79,475 hrs · 61,324 cycles

DUE PRI 565645-14 REV 0. MD-88 / FUSELAGE / AUXILIARY STRUCTURE / SEAT TRACK STA 279, LBL 54.5 / DAMAGED FROM AN ARCING FEEDER CABLE. C/W PRI 565645-14 REV 0. C/W ERA 565645-14 REV 0. (LP0420138)

Part: GENERATOR — FAILED (RT ENGINE) · airframe 79,435 hrs · 61,289 cycles

DECLARED EMERGENCY DUE TO REPORTED TOTAL LOSS OF ELECTRICAL POWER. UPON ARRIVAL IT WAS DETERMINED THAT THE RT GEN HAD FAILED ALONG WITH THE A/C CROSS TIE LOCK OUT MESSAGE. T/S THE RT GENERATOR SYSTEM AND THE A/C CROSS TIE SYSTEM. R&R R2-216 AND R2-45 AMM 24-20 PERFORMED X TIE TEST PER AMM 24-20-00-201 ALL CK NML. FOUND T4 TERMINAL OM RT GEN BROKEN INSIDE OF GEN CASE. ALSO NR 2 GEN WAS NOT TURNED OFF OR DISCONNECTED FROM COCKPIT. SAFETY WIRE STILL INTACT AND SWITCH IN ON POSITION CAUSING THE LOCKOUT WITH POWER STILL ON BUS.

Part: SHEAR TIE — CRACKED (BULKHEAD) · airframe 78,695 hrs · 60,706 cycles

LEFT AND RIGHT AFT PRESSURE BULKHEAD SPLICES ON FWD SHEAR ANGLE TAB ONLY HAVE TWO FASTENERS ON THE ONE SIDE OF THE CUT(EXAMPLE 2+4)SPLICES ARE AT 26LT AND 27LT AND 26RT AND 27RT. ALSO TWO FASTENERS HAVE CRACK INDICATIONS ON 26RT FWD OF APB 11 INCHES. C/W ERA 562174-14 REV O. (LP0241522)

Part: FRAME — CRACKED (FUSELAGE) · airframe 78,695 hrs · 60,706 cycles

CRACK IN FRAME STRUCTURE 1485 LEFT. REPAIRED PER ERA 562285-14 REV ORIG.

Part: POWER SUPPLY — MALFUNCTIONED (EMERGENCY LIGHT) · airframe 77,503 hrs · 59,779 cycles

DURING RAMP CHECK, COCKPIT OVERHEAD EMERGENCY LIGHT ON DIM WITH SWITCH ON OR OFF POSITION. REPLACED POWER SUPPLY IAW WDM 33-51-12.

Part: CAP — DISPLACED (APU OIL SYSTEM) · airframe 76,873 hrs · 59,316 cycles

AT THE GATE JUST PRIOR TO DEPARTURE, WHEN THE AIR-CONDITIONING SUPPLY SWITCHES WERE PLACED ON, THE FLIGHT ATTENDANTS NOTICED HAZE AND SMOKE ODOR IN THE AFT CABIN. MAINTENANCE FOUND THE APU OIL CAP OFF AND OIL AROUND THE APU RAM AIR DOOR INLET. APU AND INLET CLEANED. DUCT BURNOUT PERFORMED, COALESCER BAGS REPLACED. NO FURTHER HAZE OR ODOR PRESENT. A/C RETURNED TO SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 76,353 hrs · 58,966 cycles

FWD OVERWING, OVERHEAD EXIT LIGHTS INOP. REMOVED AND REPLACED BATTERIES AS REQUIRED IAW AMM 33-50. OPS CHECKED GOOD.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 75,243 hrs · 58,135 cycles

DURING SERVICE CHECK FOUND NUMEROUS EMERGENCY LIGHTS INOPERATIVE THROUGH CABIN & TAIL AREA. REPLACED POWER SUPPLY BATTERIES AND LAMP IAW WDM 33-51-13. OPS CHECKED GOOD. OK FOR SERVICE.

Part: ACCESS PANEL — CORRODED (HEATER BLANKET) · corrosion level 2 · airframe 73,430 hrs · 56,902 cycles

CORROSION ON HEATER BLANKET SKIN AROUND OF SETTLEMENT SECONDARY ACCESS PANELS NR 1303C AND 1307C AT LT WING. HEATER BLANKET WAS REPAIRED IAW ER/A 537748-14AD, REV ORIGINAL.

Part: BUSHING — CORRODED (RT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

ACFT HAS CORROSION ON BUSHINGS OF T/E RT WING UPPER SKIN FROM AFT BOLTS HEATER BLANKET. REPAIR WAS ACCOMPLISHED IAW ER/A 537750-14, AD REV. A AND ETI-88-15-291, REV. 2.

Part: FASTENER — MISSING (VERTICAL STAB) · airframe 73,428 hrs · 56,901 cycles

LOOSE AND MISSING FASTENERS, TWO ROWS ABOVE AND TWO ROWS BELOW THE SPLICE AT ZFS=52.267, LT/RT SIDE. FASTENERS WERE REMOVED AND FASTENERS WERE INSTALLED IAW SRM 51-30-1, REPAIR WAS ACCOMPLISHED IAW ETI-88-15-319, REV 2, ERA 477118-14AD, REV B.

Part: CAP — CRACKED (BS 1437) · airframe 73,428 hrs · 56,901 cycles

OUTER CAP HAS A CRACK BETWEEN LONGERONS 1 - 2L, BS 1437. LOWER OUTER CAP WAS REPAIRED IAW ER/A NR 537773-14, REV ORIGINAL.

Part: FRAME — CRACKED (BS 1463) · airframe 73,428 hrs · 56,901 cycles

A CRACK WAS FOUND ON SPLICE OF CANTED FRAME BS 1463 AND LONGERON 18L. CRACK WAS ATTENDED ETI-88-15-311, REV 1 AND ERA 537771-14, REV ORIGINAL.

Part: FRAME — CRACKED (BS 1463) · airframe 73,428 hrs · 56,901 cycles

A CRACK WAS FOUND ON SPLICE OF CANTED FRAME BETWEEN BS 1463 AND LONGERON 18R. REPAIRED IAW ETI-88-15-311, REV 1 AND ER/A 537771-14, REV ORIGINAL.

Part: SKIN — CRACKED (BS 1418) · airframe 73,428 hrs · 56,901 cycles

ACFT HAS FIVE CRACKS, WERE FOUND ON FUSELAGE SKIN: RT SIDE.- 0.250", 0.180" AND 0.100" AT BS Y=1418 AND BETWEEN LONGERON 2 AND 3 AND LT SIDE-0.125" AND 0.100" AT BS Y=1418 AND BETWEEN LONGERON 2 AND 3. FUSELAGE SKIN WAS REPAIRED IAW ER/A 537744-14 AD REV A AND ETI 88-15-282, REV 4.

Part: SKIN — CORRODED (BS 218) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

HAS A BULGE ON FUSELAGE SKIN BETWEEN BS 218 AND LONGERONS 29-30R. THE SKIN WAS REPAIRED IAW ETI88-15-295, REV 1 AND ER/A 537751-14, REV ORIGINAL.

Part: WEB — CRACKED (BS 1437) · airframe 73,428 hrs · 56,901 cycles

A CRACK WAS FOUND ON WEB ON BS 1437 BETWEEN LONGERONS 1 AND 2L. WEB REPAIRED IAW ETI NR 88-15-317, REV 1 AND ER/A 537778-14 REV ORIGINAL.

Part: SKIN — CRACKED (RT WING) · airframe 73,428 hrs · 56,901 cycles

CRACK ON RT WING FIXED L/E XRS=406. RT WING FIXED L/E WAS REPAIRED IAW ER/A 537770-14. REV ORIGINAL AND ETI 88-15-310.

Part: SKIN — NOT REPORTED (BS 210) · airframe 73,428 hrs · 56,901 cycles

FUSELAGE SKIN BS 210, LONGERON 5L. REPAIRED IAW ER/A 518525-14AD, SEC III, REV A.

Part: CARGO TRACK — CORRODED (BS 1222-1322) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

FOUND CORROSION ON LT CARGO TRACK BETWEEN BS 1222 - 1322, UPPER AND LOWER SURFACES. THE CARGO TRACK WAS REPLACED IAW SRM 53-24-0D, DWG 5936660 REV B2, AND SRM 51-30-1.

Part: FLANGE — CRACKED (RT ENGINE) · airframe 73,428 hrs · 56,901 cycles

FOUND A CRACK ON FLANGE J1 AT RT ENGINE 6 RT SIDE POSITION. THE ENGINE WAS REPLACED.

Part: LONGERON — CRACKED (BS 1437) · airframe 73,428 hrs · 56,901 cycles

ACFT HAS A CRACK ON LONGERON 4L BS 1437 IN AFT ACCESSORIES COMPARTMENT. THE LONGERON WAS REPAIRED IAW SRM 53-02, FIG 18, 51-10-3, 51-30-5, AND 51-10-4.

Part: FRAME — CRACKED (BS 1455) · airframe 73,428 hrs · 56,901 cycles

FOUND A CRACK ON FRAME BS 1455, LONGERON 1. THE FRAME WAS REPLACED IAW SRM 51-30-2 AND 51-30-5 AND DWG 99860.0 , REV L.

Part: CARGO TRACK — CORRODED (BS 1003-1098) · airframe 73,428 hrs · 56,901 cycles

FOUND CORROSION ON LT CARGO TRACK BETWEEN BS 1003 - 1098, UPPER AND LOWER SURFACES,. THE CARGO TRACK WAS REPLACED IAW SRM 51-30-1, 51-30-5, SRM 53-24-0D AND DWG DWGS936660, REV B2.

Part: LONGERON — CRACKED (BS 1437) · airframe 73,428 hrs · 56,901 cycles

ACFT HAS A CRACK ON LONGERON 3R BS 1437. THE LONGERON WAS REPAIRED IAW SRM 53-02, FIG 18.

Part: LONGERON — CRACKED (BS 1437) · airframe 73,428 hrs · 56,901 cycles

ACFT HAS CRACK ON LONGERON 4R BS 1437. THE LONGERON WAS REPAIRED IAW SRM 53-02, FIG 18.

Part: CHANNEL — CRACKED (FLOOR PANEL) · airframe 73,428 hrs · 56,901 cycles

CRACKED CHANNEL ON FLOOR PANEL. CHANNEL REPAIRED IAW SRM 53-05, FIG 131B AND 51-70-1.

Part: FRAME — CRACKED (BS 1437) · airframe 73,428 hrs · 56,901 cycles

CRACKED FRAME BETWEEN LONGERONS 1 - 2L BS 1437. THE FRAME WAS REPLACED IAW SRM 51-30-5.

Part: ANGLE — CRACKED · airframe 73,428 hrs · 56,901 cycles

CRACKED LT AND RT INTERNAL DORSAL ANGLES BETWEEN JOIN OF VERTICAL STABILIZER L/E AND FUSELAGE SKIN BS 1418. THE ANGLE WAS REPLACED IAW SRM 51-30-2 AND DWG 5912188, REV BD.

Part: CAP — CRACKED (BS 1437) · airframe 73,428 hrs · 56,901 cycles

CRACKED UPPER CAP BETWEEN LONGERONS 1 - 2L BS 1437. CAP WAS REPLACED IAW SRM 51-30-5.

Part: FLOOR PANEL — CORRODED (COCKPIT) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION FOUND ON COCKPIT FLOOR PANEL. THE FLOOR PANEL WAS REMOVED IAW SRM 51-30-1. THE FLOOR PANEL WAS REPLACED.

Part: CARGO TRACK — CORRODED (BS 1212-1322) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION FOUND ON RT CARGO TRACK BETWEEN BS 1212 - 1322. THE CARGO TRACK WAS REPLACED IAW SRM 51-30-1.

Part: FLOOR PANEL — CRACKED (NOT REPORTED) · airframe 73,428 hrs · 56,901 cycles

CRACKED FLOOR PANEL. THE FLOOR PANEL WAS REPAIRED IAW SRM 51-70-4.

Part: DOUBLER — CORRODED (BS 446-484) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

SEVERAL CORRODED POINTS ON INNER FUSELAGE SKIN DOUBLER BETWEEN BS 446 - 484 AND LONGERON 25-26L. THE DOUBLER WAS REPLACED IAW SRM 53-04-5, FIG 9 51-30-2, AND 51-10-3, PAR 14-21.

Part: LONGERON — CORRODED (BS 1309) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION FOUND ON LONGERON 20R, BS 1309. THE LONGERON WAS REPLACED IAW SRM 53-02, FIG 18.

Part: ATTACH ANGLE — CRACKED (RT PYLON) · airframe 73,428 hrs · 56,901 cycles

CRACKED ANGLE TO ATTACH RT PYLON T/E LOWER SURFACE. ANGLE REPAIRED IAW SRM 54-04 FIG 10A SHEET 2 AND 3 NOTE 15 AND 51-30-5.

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION FOUND ON PRODUCTION DOUBLER LOWER AND UPPER CUT OUT AT AFT LAVATORY SERVICE PANEL. REPAIRED IAW ER/A 537752-14, REV ORIGINAL.

Part: SKIN — DAMAGED (BS 1474) · airframe 73,428 hrs · 56,901 cycles

ELONGATED HOLES ON SKIN AT BS 1474 BETWEEN LONGERONSS 17 - 18L. SKIN REPAIRED IAW SRM 53-01, FIG 2.

Part: SCUFF PLATE — CRACKED (CARGO DOOR) · airframe 73,428 hrs · 56,901 cycles

CRACKED SCUFF PLATE AT CARGO DOOR. THE SCUFF PLATE WAS REPAIRED IAW ER/A 491023-14MA, REV A.

Part: DUCT — CRACKED (APU EXHAUST) · airframe 73,428 hrs · 56,901 cycles

AIRCRAFT HAS CRACKED APU EXHAUST DUCT AT FUSELAGE SKIN. THE APU EXHAUST DUCT WAS REPAIRED IAW ER/A 473221-14MA REV ORIGINAL.

Part: LONGERON — CORRODED (BS 237-256) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

SURFACE CORROSION FOUND ON LONGERON 30, BETWEEN BS 237 - 256. LONGERON SECTION WAS REPAIRED IAW SRM 53-14-1, FIG 3, 51-10-4, 51-30-2, 51-10-3 AND 53-02, FIG 18.

Part: BUSHING — CRACKED (HORIZONTAL STAB) · airframe 73,428 hrs · 56,901 cycles

A CRACK WAS FOUND ON BUSHING IN THE INBD HOLE OF THE RT REAR UPPER CAP. FORCE MATE BUSHING INSTALLATION PROCEDURE WAS ACCOMPLISHED IAW DWG SR 09550032, REV B AND FORCE MATE FIT TIP SHEET 238263, REV A PROCEDURE 3.2 PAR 3-12. ON UPPER HOLES.

Part: SKIN — DAMAGED (BS 200-218) · airframe 76,488 hrs · 59,066 cycles

FUSELAGE SKIN BS 200 - 218, LONGERON 29L - 29R CORRODED & DEFORMED. REPAIRED IAW ER/A.

Part: ANGLE — CRACKED (BS 826) · airframe 73,428 hrs · 56,901 cycles

CRACKED ANGLE OVER CENTRAL TANK AT BS 826 LBL 44. THE ANGLE WAS REPAIRED IAW ER/A 498192-14MA, REV A.

Part: LONGERON — CORRODED (BS 200-218) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION FOUND ON LONGERON 30, BS 200-218. LONGERON WAS REPLACED IAW SRM 53-14-1, FIG I.

Part: SEAT TRACK — CORRODED (BS 793-800) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION FOUND ON LEFT SEAT TRACK X 54, BS 793 - 800. THE SEAT TRACK WAS REPAIRED IAW SRM 53-05, FIG 4 F.

Part: STRUCTURE — WORN (RT WING TE FLAP) · airframe 73,428 hrs · 56,901 cycles

WEAR ON RT FLAP L/E NR 4. REPAIR ON RT FLAP L/E NR 4 WAS REPLACED IAW ER/A 503745-14, REV ORIGINAL.

Part: LONGERON — CORRODED (BS 200-218) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION FOUND ON LONGERON 29L FROM BS 200-218. LONGERON WAS REPLACED IAW SRM 53-14-1, FIG 3 AND SRM 51-30-5, 50-30-2.

Part: SKIN — NICKED (LT WING TE FLAP) · airframe 73,428 hrs · 56,901 cycles

A NICK WAS FOUND ON THE LOWER SKIN OF THE LT WING OTBD FLAP XFLS 361. REPAIRED IAW SRM 57-03, PAR 9, FIG 8 AND SRM 51-10-3, PAR 14, 21.

Part: CARGO TRACK — CORRODED (BS 1007-1155) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION FOUD ON THE RT CARGO TRACK BETWEEN BS 1007 - 1155, UPPER AND LOWER SURFACES,. THE CARGO TRACK WAS REPLACED IAW SRM 51-10-3, PAR 14, 21 & 26, SRM 51-10-4, AND SRM 51-30-1.

Part: SUPPORT — CORRODED (BS 1117-1155) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON ZEE SUPPORT BETWEEN BS 1117 - 1155, LONGERON 28R. THE SUPPORT WAS REPLACED IAW SRM 51-30-2 AND DWG 5936660, REV.

Part: LONGERON — CORRODED (BS 1174) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON LONGERON 22L BS 1174 IN AFT CARGO BAY UTILITARY TUNNEL. THE LONGERON WAS REPAIRED IAW SRM 53-02, FIG 18.

Part: FINGER DOUBLER — CORRODED (BS 587-613) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON FINGER DOUBLER LONGERON 26LT AT BS 587 TO 613. FINGER DOUBLER WAS REPLACED IAW SRM 53-34-0 AND 51-10-1. CORROSION WAS REMOVED AND REWORKED AREA WAS TREATED AND PAINTED.

Part: FLOOR PANEL — DELAMINATED (PAX CABIN) · airframe 73,428 hrs · 56,901 cycles

DELAMINATED AND PUNCTURED FLOOR PANEL IN PAX CABIN. FLOOR PANEL FABRICATED IAW AMM 53-20-01-201.

Part: FINGER DOUBLER — CORRODED (BS 728-752) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORRODED FINGER DOUBLER BETWEEN LONGERONS 25-26L BS 728 - 752. FINGER DOUBLER WAS REPLACED IAW SRM 53-34-0 AND 51-10-1.

Part: SKIN — NICKED (RT WING TE FLAP) · airframe 73,428 hrs · 56,901 cycles

SEVERAL NICKS ON INBD FLAP LOWER SKIN ON RT WING. REPAIRED IAW SRM 57-03D FIG 8.

Part: HINGE — DAMAGED (CARGO DOOR) · airframe 73,428 hrs · 56,901 cycles

ACFT HAS ELONGATED HOLE ON FWD HINGE OF FWD CARGO DOOR. HINGE REPAIRED IAW ER/A 497387-14 MA, REV B.

Part: DOUBLER — CORRODED (BS 200-218) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON PRODUCTION DOUBLER BS 200-218 BTW LONGERONS 29 AND 30R. THE DOUBLER WAS REPLACED IAW DWG 9911520-147 REV. W.

Part: DOUBLER — DELAMINATED (TE FLAPS) · airframe 73,428 hrs · 56,901 cycles

DELAMINATED DOUBLER ON INTRADOSE OF INBD FLAP INBD GUIDE VANE AT RT WING. INBD FLAP, INBD GUIDE VANE AT RT WING WAS REPAIRED IAW SRM 57-03D, PAR 11.

Part: LONGERON — CRACKED (BS 541) · airframe 73,428 hrs · 56,901 cycles

ACFT HAS CRACKS ON LONGERON 4L BS 541. THE LONGERON WAS REPLACED IAW SRM 53-02, FIG 18, 51-30-2 AND 51-30-5.

Part: SKIN — CRACKED · airframe 73,428 hrs · 56,901 cycles

CRACK ON OUTER SKIN NEAR BEAM NR 4 IN LT LOWER AFT CORNER AT VENTRAL DOOR. REPAIR WAS ACCOMPLISHED IAW ERA 537757-14, REV ORIGINAL AND ETI-88-15-300.

Part: FLOOR PANEL — DELAMINATED (NOT REPORTED) · airframe 73,428 hrs · 56,901 cycles

DELAMINATED FLOOR PANEL. FLOOR PANEL FABRICATED IAW AMM 53-20-01-201.

Part: TORQUE TUBE — CORRODED (RUDDER DRIVE) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON RUDDER DRIVE TORQUE TUBE. RUDDER DRIVE TORQUE WAS REPLACED IAW AMM 27-00-00 .

Part: SKIN — CRACKED (BS 423) · airframe 73,428 hrs · 56,901 cycles

TWO CRACKS WERE FOUND ON FUSELAGE SKIN AND DOUBLER AT THE AFT LOWER CORNER OF: 0.250", FUSELAGE SKIN AND 1.593", DOUBLER AT BS 423.750 AND BETWEEN LONGERON 26 AND 27 RT. CRACKS ON FUSELAGE SKIN WERE REPAIRED IAW SRM 53-05, FIG 105.

Part: INTERCOM — CRACKED (BS 1338-1350) · airframe 73,428 hrs · 56,901 cycles

ACFT HAS CRACKED INTERCOSTAL, BS 1338-1350 AND RBL 18 AT RT AFT LAVATORY AREA. THE INTERCOSTAL WAS REPAIRED IAW SRM 53-1 FIG. 2.

Part: FAIRING — CRACKED (HORIZONTAL STAB) · airframe 73,428 hrs · 56,901 cycles

CRACKED REPAIR DOUBLER ON RT HORIZONTAL STABILIZER FAIRING 3806A. REPAIR WAS ACCOMPLISHED IAW ER/A 464895-14MA, REV F, SRM 51-30-2, 51-10-2, 51-10-3 PAR 14/21, CARD 2000.

Part: DOUBLER — CORRODED (BS 674-693) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON DOUBLER AT RADIO ALTIMETER CUT OUT BS 674 - 693. THE DOUBLER WAS REPLACED IAW SRM 51-30-2, 51-30-5 , 51-30-3 P.26, 21, 14, 53-01 FIG 1, AND DWG 5911412, REV DV.

Part: FAIRING — CRACKED · airframe 73,428 hrs · 56,901 cycles

CRACK ON LOWER FAIRING 3703A AFT SECTION. DAMAGE AREA WAS CUT OUT IAW SRM 55-03, D FIG 17 AND ERA 464895-14MA, REV F AND WAS REPAIR IAW SRM 55-03-D, FIG 17 AND ERA 464895-14MA, REV F.

Part: CUSP WEB — CORRODED (BS 1183-1185) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON LT CUSP WEB BETWEEN BS 1183 - 1185 AND RBL 54 TO 60. DAMAGE WAS REMOVED IAW SRM 53-05, FIG 131A-13. REPAIR WAS FABRICATED, TREATED, PAINTED AND INSTALLED IAW SRM 53-05, FIG 131A-13, 57-10-3, 51-30-2 AND 51-30-5.

Part: FLOOR PANEL — DELAMINATED (PAX CABIN) · airframe 73,428 hrs · 56,901 cycles

DELAMINATED FLOOR PANEL 389C IN PAX CABIN. FLOOR PANEL FABRICATED IAW AMM 53-20-01-201.

Part: LONGERON — CORRODED (BS 1174) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON LONGERON 23L BS 1174. THE LONGERON WAS REPAIRED IAW SRM 51-10-3, PAR 14, 21, 53-02 PAR 12 FIG 18.

Part: GUIDE VANE — DAMAGED (LT WING TE FLAP) · airframe 73,428 hrs · 56,901 cycles

NICKS AND WEAR ON REPAIR DOUBLER ON INBD FLAP, GUIDE VANE LT WING. REPAIR DOUBLER WAS REPLACED IAW SRM 57-03D, PAR 11.

Part: DOOR FRAME — CORRODED (BS 636-693) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON LOWER DOOR FRAME IN THE MID CARGO BAY, BS 636 - 693. DOOR FRAME WAS REPLACED IAW SRM 51-30-2, 51-30-5, 51-10-3 PAR. 14 - 21 AND DWG 5936038, REV. A.

Part: SKIN — DAMAGED (RUDDER) · airframe 73,428 hrs · 56,901 cycles

DAMAGED METALLIZATED COAT OF RUDDER. METALLIZATED COAT OF RUDDER WAS REPAIRED IAW SRM 51-70-1A, PAR 23.

Part: LONGERON — CRACKED (BS 541) · airframe 73,428 hrs · 56,901 cycles

CRACK ON LONGERON 4R, BS 541 AT PAX CABIN. THE LONGERON WAS REPAIRED IAW IAW SRM 53-02, FIG 18.

Part: INTERCOSTAL — CORRODED (BS 389) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON INTERCOSTAL BETWEEN LOWER EDGE AND BS 389 . THE INTERCOSTAL WAS REPLACED IAW SRM 51-30-2.

Part: SKIN — DENTED (CARGO DOOR) · airframe 73,428 hrs · 56,901 cycles

ACFT HAS SEVERAL DENTS ON OUTER SKIN OF MID CARGO COMPARTMENT DOOR. THE CARGO DOOR WAS REPLACED.

Part: BULKHEAD — CORRODED (BS 1439) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON BULKHEAD AT VENTRAL STAIRWAY STRUCTURE BS 1439. THE BULKHEAD WAS REPLACED IAW SRM 51-30-2, 51-10-2, 51-10-3 PAR 14-21.

Part: CUSP WEB — CRACKED (BS 706-712) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON CUSP WEB OUT OF LIMITS LBL 54 TO 60 BETWEEN BS 706-712IN. CUSP WEB REPAIRED IAW SRM 53-05, FIG 131A-7, SHEET 1.

Part: CUSP WEB — CORRODED (BS 598-617) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON REPAIR DOUBLER OF THE CUSP WEB BS 598 - 617 BETWEEN LBL 54 TO 60. THE CUSP WEB WAS REPLACED IAW SRM 53-05, FIG 131A.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK AND SETLEMENT SURFACE AT RT WING ACCESS PANEL 1472C. THE ACCESS PANEL WAS REPLACED.

Part: FLOOR PANEL — DELAMINATED (NOT REPORTED) · airframe 73,428 hrs · 56,901 cycles

DELAMINATED FLOOR PANEL. THE FLOOR PANEL WAS FABRICATED IAW AMM 53-20-01-201.

Part: GUIDE VANE — WORN (RT WING TE FLAP) · airframe 73,428 hrs · 56,901 cycles

WEAR ON INBD EDGE UPPER & LWR SIDE OF T/E AT RT WING OTBD FLAP, OTBD GUIDE VANE. REPAIRED IAW SRM 57-03D, PAR 11.

Part: CUSP WEB — CORRODED (BS 1276) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON RT CUSP WEB IN BS 1276 BETWEEN RBL 54 - 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-14, 51-10-3 PAR 14-21, AND 51-30-2.

Part: CUSP WEB — CORRODED (BS 605-607) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON CUSP WEB OUT OF LIMITS X=54 TO X=60 BETWEEN BS Y=605-607, LT PAX CABIN. CUSP WEB WAS REPAIRED IAW SRM 53-05, 131A-6, SHEET 1, 51-30-1, 51-30-2, 51-30-5.

Part: SKIN — DAMAGED (RUDDER TAB) · airframe 73,428 hrs · 56,901 cycles

DAMAGE METALLIZATED COAT OF RUDDER TAB. METALLIZED COAT OF RUDDER TAB WAS REPAIRED IAW SRM 51-70-1A, PAR 23 AND CARD 200-8149-17, JOB 000-0022.

Part: FRAME — CRACKED (BS 1322) · airframe 73,428 hrs · 56,901 cycles

CRACKED FRAME ON BS 1322 OVER LONGERON 17L. FRAME WAS REPAIR IAW ER/A 493697-14 MA REV B.

Part: SKIN — DAMAGED (LT WING) · airframe 73,428 hrs · 56,901 cycles

ELONGATED HOLES ON LOWER AND UPPER SKIN AT LT WING TIP. DAMAGE HOLES WERE REPAIRED IAW EA 09-478904-14MA, REV : ORIG.

Part: SKIN — DAMAGED (RT WING) · airframe 73,428 hrs · 56,901 cycles

ELONGATED HOLES ON UPPER AND LOWER SKIN AT RT WING TIP. DAMAGE HOLES REPAIRED IAW EA 09-478904-14 MA, REV ORIG.

Part: FLOOR PANEL — DELAMINATED (NOT REPORTED) · airframe 73,428 hrs · 56,901 cycles

DELAMINATED FLOOR PANEL NR 200A. FLOOR PANEL NR 200A WAS REPAIRED IAW SRM 51-90-0, PAR 8 K.

Part: CUSP WEB — CORRODED (BS 1257-1267) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON CUSP WEB BETWEEN BS 1257-1267 AND BETWEEN X -54 TO X -60 . REPAIR WAS ACCOMPLISHED IAW SRM 53-05, FIG 131A-B.

Part: CUSP WEB — CORRODED (BS 543-570) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION OUT OF LIMITS AFTER CORROSION REMOVAL ON RT CUSP WEB FROM BS 543-558 AND BS 559-570 X -54 TO X -60. AREA OUT OF LIMITS WAS REPAIRED IAW SRM 53-05, FIG 131A-7 AND CIC WILL BE APPLIED IAW NRC 20000072167 CARD, NR 18, AC ZONE 201.

Part: SKIN — CRACKED (RT WING SLAT) · airframe 73,428 hrs · 56,901 cycles

CRACKED SKIN ON SLAT PANEL NR 1 AT RT WING, XIS=136.421. CRACK WAS REPAIRED IAW SRM 57-01, FIG 3.

Part: HINGE — WORN (LT ELEVATOR) · airframe 73,428 hrs · 56,901 cycles

WEAR ON HINGES XET= 119.7 AT LT ELEVATOR T/E. HINGE WAS REMOVED, NEW HINGE WAS DRILLED NEW HINGE WAS TREATED AND PAINTED, NEW HINGE WAS INSTALLED IAW SRM 51-30-2, 51-30-1, 51-10-4, 51-10-3 PAR 14 AND 21.

Part: INTERCOSTAL — CRACKED (BS 1355) · airframe 73,428 hrs · 56,901 cycles

CRACKED INTERCOSTAL BS 1355 AND X -22 AT RT AFT LAVATORY AREA. CRACK WAS STOP DRILL IAW SRM 51-01, PAR 21, PARTS WERE FABRICATED, TREATED AND PAINTED IAW SRM 51-10-3, PAR 14 AND 21, 53-01 FIG 2, NEW PARTS WERE INSTALLED IAW SRM 51-30-2 AND 51-30-5.

Part: CUSP WEB — CORRODED (BS 875-877) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON CUSP WEB OUT OF LIMITS X 54 TO X 60 BETWEEN BS 875 - 877, LT PAX CABIN. CUSP WEB WAS PREPARED IAW SRM 51-30-2, 53-05, FIG 131A-3, SHEET 1, 51-10-3 P, 14, 21.

Part: CUSP WEB — CORRODED (BS 237) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON CUSP WEB BS 237 BETWEEN X=-54 / X=-60. DAMAGE WAS REMOVED TO REPAIR THE DAMAGED AREA IAW SRM 53-05. THEN, THE TRIM WAS INSPECTED FOR CRACKS AND NO CRACKS WERE FOUND. AFTER THAT, REPAIR PARTS WERE FABRICATED IAW SRM 53-05, FIG 131A-10 TO BE TREATED AND PAINTED IAW SRM 51-10-3, PAR 21 AND 14 THEN REPAIR PARTS WERE INSTALLED IAW SRM 51-30-2. FINALLY FITTING AND SEAT TRACK WERE INSTALLED IAW SRM 51-30-1 AND 51-30-5. CIC WILL BE APPLIED WITH THE NRC 20000072167, CARD 18, ACFT ZONE 201.

Part: CUSP WEB — CORRODED (BS 900) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON REPAIR DOUBLER ON LT CUSP WEB BS 900 BETWEEN X 54 - 60. REPAIR WAS REPLACED IAW SRM 53-05, FIG 131A.

Part: SKIN — DAMAGED (BS 430-440) · airframe 73,428 hrs · 56,901 cycles

OUT OF LIMITS REWORKED AREA ON FUSELAGE SKIN BETWEEN BS 430 - 440 AND LONGERONS 23 - 25L. FUSELAGE SKIN REPAIRED IAW SRM 53-04-2, FIGURE 2, SHEET 6.

Part: CUSP WEB — CORRODED (BS 1238-1250) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON REPAIR DOUBLER OF LT CUSP WEB BETWEEN BS 1238-1250 AND BETWEEN X 54 - 60 . REPAIR DOUBLER WAS REPLACED IAW SRM 53-05, FIG 131A-6.

Part: DOOR — CRACKED (SLAT TRACK) · airframe 73,428 hrs · 56,901 cycles

CRACK ON DOOR SLAT TRACK NR 4 AT RT WING. SLAT TRACK DOOR NR 4 RT WAS REPLACED IAW ERA: 512356-14MA, REV ORIGINAL ERA 512356-14MA, REV ORIGINAL.

Part: LONGERON — CRACKED (BS 1003) · airframe 73,428 hrs · 56,901 cycles

CRACKED LONGERON 5L BS 1003. LONGERON SECTION WAS REMOVED, AND A NEW LONGERON SECTION AND SPLICES WERE FABRICATED, DRILLED, TREATED, PAINTED AND INSTALLED IAW SRM 51-30-1, 51-30-2, 51-30-5, 53-02, FIG 18, 51-10-4, AND 51-10-3, PAR 14 AND 21.

Part: CUSP WEB — CORRODED (BS 1044-1052) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON RT CUSP WEB BS 1044-1052 BETWEEN X -54 X -60, IN REF TO CARD 140, ZONE 201, CFS, SM. RT CUSP WEB BS Y=1044-1052, X-54/X=-60 WAS REPAIRED IAW SRM 53-05, FIG 131A-7, 51-30-2, AND 51-10-3, PAR 14 AND 21.

Part: SKIN — DAMAGED (BS 394-401) · airframe 73,428 hrs · 56,901 cycles

OUT OF LIMITS, REWORKED AREA ON FUSELAGE SKIN BETWEEN BS Y=394.5 TO Y=401 AND LONGS 23 LT TO 25 LT. FUSELAGE SKIN BETWEEN BS Y=394.5 TO Y=401 AND LONG 23 LT TO 25 LT. CRACK OF 0.375" AT BS Y=394.5 WAS TRIMMED OUT WITHIN 0.750 OF DIAMETER IAW SRM 53-04-2 FIGURE 2, SHEET 6. CRACK WAS REPAIRED AND INSTALLED NEW FINGER DOUBLER AND FILLER IAW SRM 53-04-2, FIGURE 2, SHEET 6. MAINTENANCE REQUIREMENTS VISUAL INSPECTION INITIAL 8,000 CYCLES AND REPETITIVE 8,000 CYCLES SRM 53-04-2, PAR D, PAGE 52.

Part: CUSP WEB — CRACKED (BS 223) · airframe 73,428 hrs · 56,901 cycles

CRACK ON LT CUSP WEB BS 223 BETWEEN LBL 52-60. CUSP WEB WAS REPLACED IAW SRM 51-30-5, 51-30-2, 51-30-1, 51-10-4, 51-10-3 PAR 14 AND 21, AND DWG 9930538, REV CF.

Part: SERVICE PANEL — CORRODED (LAVATORY) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON AFT LAVATORY SERVICE PANEL. AFT LAVATORY SERVICE PANEL WAS REPLACED IAW DWG 5914792, REV AG AND SRM 51-30-2, 51-10-3 PAR 14 AND 21.

Part: CUSP WEB — CORRODED (BS 564-566) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON CUSP WEB OUT OF LIMITS X 54 TO X 60 BETWEEN BS Y= 564-566. CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-13, SHEET 1, 51-30-2, AND 51-30-5.

Part: LONGERON — CRACKED (BS 1437) · airframe 73,428 hrs · 56,901 cycles

CRACK ON LONGERON 5L AND BS 1437 AT AFT ACCESSORY COMPARTMENT. THE LONGERON WAS REPAIRED IAW SRM 53-02, PAR 12, FIG 18, 51-10-3, PAR 14 AND 21, 51-30-2, 51-30-5, AND 51-10-4.

Part: CUSP WEB — CRACKED (BS 855) · airframe 73,428 hrs · 56,901 cycles

CRACKED CUSP WEB BS 855, BETWEEN RBL 54 - 60. DAMAGE WAS REMOVED WAS ACCOMPLISHED AROUND CUTOUT AREA AND NO CRACK WERE FOUND, REPAIR DOUBLER AND RING DOUBLER WERE FABRICATED. REPAIR TREATED AND PAINTED WAS INSTALLED AND WAS APPLIED CIC IAW SRM 53-05, FIG 131A-2, 51-10-3 PAR 14, 21, AND 38 51-30-5.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT SURFACE AT RT WING FUEL TANK ACCESS PLATE NR 1466C. MRB 57-083-02, CARD 143, ZONE 10. CORROSION ON COUNTERSINK WAS REMOVED AND MEASURED. THE MAX DIAMETER ON 3 HOLES ADJACENT MEASURED IS .547", THEREFORE IT IS OUT LIMITS. FUEL ACCESS PLATE 1466C WAS REPLACED IAW SRM 51-22-2A.

Part: FLOOR PANEL — DELAMINATED (PAX CABIN) · airframe 73,428 hrs · 56,901 cycles

DELAMINATION ON FLOOR PANEL. FLOOR PANEL FABRICATED IAW AMM 53-20-01-201.

Part: CUSP WEB — CORRODED (BS 1022-1023) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON RT CUSP WEB BS 1022 - 1023 BETWEEN X -54- X 60. REPAIRED IAW SRM 53-05, FIG 131A-10, SHEET 1.

Part: SUPPORT BRACKET — CRACKED (BS 1338) · airframe 73,428 hrs · 56,901 cycles

CRACK ON SUPPORT OF SIX PULLEY BRACKET BETWEEN BS 1338 AND LONGERON 3RT AT AFT ACCESORIES COMPARTMENT. SUPPORT WAS REPAIRED IAW SRM 51-30-2, 53-01, FIG 2, SHEET 4, 51-10-3 PAR 14, 21 51-30-5.

Part: CUSP WEB — CORRODED (BS 1073-1074) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON RT CUSP WEB BS 1073-1074 BETWEEN X -54 & X -60. NEW DOUBLER AND FILLER FABRICATED IAW SRM 53-05, FIG 131A-14 AND TREATED AND PAINTED IAW SRM 51-10-3, PAR 11, 14 AND 21 AND INSTALLED IAW SRM 51-30-2.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT SURFACE AT RT WING FUEL ACCESS PLATE NR 1460C. MRB 57-083-02, CARD 144, ZONE 10. CORROSION ON COUNTERSINK WAS REMOVED AND MEASURED. THE MAX DIAMETER MEASURED ON 3 HOLES ADJACENT IS .557", THEREFORE IS OUT LIMITS. FUEL ACCESS PLATE 1460C WAS REPLACED IAW SRM 51-22-2A.

Part: CUSP WEB — CORRODED (BS 830) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON CUSP WEB REPAIR, BS 830 BETWEEN X 54 TO X 60 RT. PREVIOUS REPAIR WAS REPLACED IAW SRM 53-05, FIG 131A-14 SHEET 1, 51-10-3, PAR 21 AND 14, 51-30-2.

Part: FRAME — CORRODED (BS 1212) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON FRAME ANGLE BS 1212 BETWEEN LONGERONS 24 - 25L . FRAME ANGLE WAS REPAIRED IAW SRM 53-03D, FIG. 3.

Part: WEB — CORRODED (BS 620-700) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON WEB FROM BS 620-700 AT MID CARGO COMPARTMENT LOWER DOOR JAM. (C2). WEB WAS REPLACED IAW SRM 51-10-3, PAR 14-21, 51-10-4 DWG 5910142, REV DJ.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 73,428 hrs · 56,901 cycles

DELAMINATED AND PUNCTURED FLOOR PANEL. FLOOR PANEL FABRICATED IAW AMM 53-20-01-201.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA ON FUEL ACCESS PLATE, 1311C AT RT WING, LW, SM, CARD 147, ZONE 10. CORROSION ON COUNTERSINK WAS REMOVED AND MEASURED. THE MAX DIAMETER ON 3 HOLES ADJACENT IS .695", THEREFORE IS OUT LIMITS. FUEL ACCESS PLATE 1311C WAS REPLACED IAW SRM 51-22-2A.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK AT LT WING FUEL TANK ACCESS PLATE NR 1361C. MRB 57-083-02, CARD 145, ZONE 10. CORROSION ON COUNTERSINK HOLES WAS REMOVED AND MEASURED AND THE MAX DIAMETER ON 3 HOLES ADJACENT IS .560", THEREFORE IT IS OUT LIMITS. FUEL ACCESS PLATE 1361C WAS REPLACED IAW SRM 51-22-2A.

Part: SEAT TRACK — CORRODED (BS 820-826) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON LT SEAT TRACK X=54, BS 820-826. REPAIRED IAW SRM 53-05, FIG 4A.

Part: SKIN — CRACKED (BS 1474) · airframe 73,428 hrs · 56,901 cycles

CRACK ON FUSELAGE SKIN ON BS 1474 ON LONGERON 21 TO 22L. HOLES WERE STOP DRILLED AND REPAIR DOUBLER WAS FABRICATED, TREATED AND PAINTED AND INSTALLED IAW SRM 53-01, FIG 2, 51-10-3, P 14 AND 21 AND 51-30-2. HFEC WAS PERFORMED IAW NDT SPM 06-10-01.001.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK AT SETTLEMENT AREA AT FUEL ACCESS PLATE NR 1335C LT WING. FUEL ACCESS 1335C WAS REPLACED IAW SRM 51-22-2A.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT SURFACE AT RT WING FUEL TANK ACCESS PLATE NR 1414C, MRB 57-083-02, ACCESS 1414C WAS REPLACED IAW SRM 51-22-2A.

Part: CUSP WEB — WORN (BS 617) · airframe 73,428 hrs · 56,901 cycles

WEAR ON CUSP WEB, BS 617, BETWEEN LBL 44 - 54. CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A.

Part: CUSP WEB — CORRODED (BS 387-389) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON LT CUSP WEB BETWEEN BS 387-389 AND BETWEEN X 56-60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A, 51-10-3, PAR 14-21.

Part: WEB — CORRODED (BS 160) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON WEB AROUND OF WATER LINES BS 160 BETWEEN X -44 AND X -54 LOWER SURFACE. DUE TO AN EXESSIVE DAMAGE, THE WEB WAS REPAIRED IAW SRM 51-70-4. DAMAGE WAS REMOVED, DOUBLER WAS FABRICATED, TREATED AND PAINTED AND FINALLY DOUBLER REPAIR WAS INSTALLED IAW SRM 51-30-2.

Part: LONGERON — CRACKED · airframe 73,428 hrs · 56,901 cycles

CRACKED LONGERON NR 8, RT STA Y=13. LONGERON WAS REPAIRED IA SRM 51-30-2, 51-30-5, 53-02 FIG 18, 51-10-3 PAR 14 AND 21.

Part: CUSP WEB — PUNCTURED (BS 1129) · airframe 73,428 hrs · 56,901 cycles

PUNCTURE ON CUSP WEB BS 1129 AND X -54 DAMAGE AREA WAS REMOVED, NEW FILLER AND DOUBLER WERE FABRICATED, NEW FILLER AND DOUBLER WERE TREATED AND PAINTED, NEW DOUBLER AND FILLER WERE INSTALLED IAW SRM 53-05, FIG 131A-19 AND 51-10-3, PAR 14 AND 21.

Part: SEAT TRACK — CORRODED (BS 670-674) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON PREVIOUS REPAIR LT SEAT TRACK PLUG X=22 BS 670-674 AT PAX CABIN. PLUG WAS REPLACED IAW SRM 53-05, FIG 4A.

Part: SEAT TRACK — CORRODED (BS 695-698) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON PREVIOUS REPAIR ON SEAT TRACK X=-22 AND BS 695-698. PLUG WAS REPLACED IAW SRM 53-05, FIG 4 AND CIC WAS APPLIED IAW SRM 51-10-3.

Part: SEAT TRACK — CORRODED (BS 305-309) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON SEAT TRACK, X -54 AND BS 305-309 AT PAX CABIN. DAMAGE OUT LIMITS WAS CUT OUT AND REPAIRED IAW SRM 53-05, FIG 4A.

Part: SEAT TRACK — CORRODED (BS 496-503) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON RT SEAT TRACK X -54 BETWEEN BS 496-503. DAMAGE OUT OF LIMITS, CUT OUT AND REPAIRED IAW SRM 53-05, FIG 4A.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK FUEL ACCESS PLATE NR 1409C AT RT WING. FUEL ACCESS WAS REPLACED IAW SRM 51-22-2A.

Part: SKIN — DENTED (AFT CARGO DOOR) · airframe 73,428 hrs · 56,901 cycles

SEVERAL DENTS ON OUTER SKIN OF AFT CARGO DOOR. THE AFT CARGO DOOR WAS REPLACED IAW AMM 52-31-00-401.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 76,488 hrs · 59,066 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT SURFACE AT RT WING FUEL TANK ACCESS PANEL 1462C. THE ACCESS PANEL WAS REPLACED IAW SRM 51-22- 2A.

Part: PAN — WORN (CARGO DOOR) · airframe 73,428 hrs · 56,901 cycles

ACFT HAS WEAR ON PREVIOUS REPAIR DOUBLER INNER AND OUTER PAN AT MID CARGO DOOR. MID CARGO DOOR WAS REPLACED IAW AMM 52-31-00-401. AND WILL BE INSTALLED UNDER AMDS CARD 5200-4291, JOB 001-0267.

Part: CUSP WEB — CORRODED (BS 712-720) · airframe 76,488 hrs · 59,066 cycles

CORROSION ON CUSP WEB BS 712 - 720 BETWEEN RBL 54 TO 60. CORROSION WAS REMOVED IAW SRM.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT SURFACE AT RT WING FUEL TANK ACCESS PLATE NR 1436C, MRB 57-083-02. CORROSION ON COUNTERSINK WAS REMOVED AND MEASURED. THE MAX DIAMETER ALLOWED IS .660" AND MAX DIAMETER MEASURED ON 3 HOLES ADJACENT IS 0.686", IT IS OUT LIMITS IAW SRM 51-22-2A. FUEL ACCESS PLATE NR 1436C WAS REPLACED.

Part: CUSP WEB — CRACKED (BS 767) · airframe 73,428 hrs · 56,901 cycles

CRACK ON CUSP WEB, BS 767 BETWEEN X 44 - 54 LT SIDE AT CPAX. CUSP WEB REPAIRED IAW SRM 53-01, FIG 4, 53-05, 51-10-3 PAR 14 AND 21 AND 51-30-2. LENGTH OF CRACK IS 2.250".

Part: SEAT TRACK — CORRODED (BS 450-489) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON PREVIOUS REPAIR, LT SEAT TRACK PLUGS X=22, STA 450-455 AND 484-489 AT PAX CABIN. PLUGS WERE REMOVED IAW SRM 51-30-1. PLUGS WERE ADJUSTED IAW SRM 53-05, FIG 4A, SHEET 1-2. AREA AND PLUGS WERE TREATED AND PAINTED IAW SRM 51-10-3 PAR 14 AND 21. PLUGS WERE INSTALLED IAW SRM 51-30-1.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK FUEL ACCESS PLATE 1355CT LT WING. CORROSION ON COUNTERSINK HOLES WAS REMOVED AND MEASURED. MAX DIAMETER ALLOWABLE IS 0.532" AND MAX DIAMETER MEASURED ON 3 ADJACENT HOLES IS 0.563", THEREFORE, IT IS OUT OF LIMITS IAW SRM 51-22-2A AND WAS REPLACED IAW IPC 57-30-00-05B.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA ON FUEL ACCESS PLATE 1365C AT LT WING. CORROSION ON COUNTERSINK AND SETTLEMENT AREA WAS REMOVED AND COUNTERSINK HOLES WERE MEASURED, MAX DIAMETER ALLOWABLE IS 0.532" AND MAX DIAMETER MEASURED ON 3 ADJACENT HOLES IS 0.594", THEREFORE, IT IS OUT OF LIMITS IAW SRM 51-22-2A AND WAS REPLACED IAW IPC 57-30-00-05B.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK AT LT WING FUEL TANK ACCESS PLATE NR 1357C, MRB 57-083-02. CORROSION ON COUNTERSINK HOLES WAS REMOVED AND MEASURED. MAX DIAMETER ALLOWABLE IS 0.532" AND MAX DIAMETER MEASURED ON 3 ADJACENT HOLES IS 0.562". THEREFORE IT IS OUT OF LIMITS IAW SRM 51-22-2A AND WAS REPLACED IAW IPC 57-30-00-05B.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK AT RT WING FUEL TANK ACCESS PLATE 1456C. CORROSION ON COUNTERSINK HOLES AT ACCESS PLATE NR 1456C WAS REMOVED AND MEASURED. MAX DIAMETER ALLOWABLE IS 0.532" AND MAX DIAMETER MEASURED ON 3 ADJACENT HOLES IS 0.580". THEREFORE ITS OUT OF LIMITS IAW SRM 51-22 -2A AND WAS REPLACED.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA ON ACCESS PLATE 1363C AT LT WING CORROSION ON COUNTERSINK AND SETTLEMENT AREA WAS REMOVED AND COUNTERSINK HOLES WAS MEASURED. MAX DIAMETER ALLOWABLE IS 0.532" AND MAX DIAMETER MEASURED ON 3 ADJACENT HOLES IS 0.565", THEREFORE, IT IS OUT OF LIMITS IAW SRM 51-22-2A AND WAS REPLACED IPC 51-22-2A.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK AT RT WING FUEL TANK ACCESS PLATE NR 1464C, MRB 57-083-02. CORROSION ON COUNTERSINK HOLES AT ACCESS PLATE NR 1464C WAS REMOVED AND MEASURED MAX DIAMETER ALLOWABLE IS 0.532" AND MAX DIAMETER MEASURED ON 3 ADJACENT HOLES IS 0.586". THEREFORE, IT IS OUT OF LIMITS IAW SRM 51-22-2A AND WAS REPLACED IAW IPC 57-30-00-05B.

Part: FLOOR PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON FLOOR PANEL 160G. FILLER WAS REMOVED FROM PANEL IAW SRM 51-30-2 THEN NEW FILLER AND PANEL WERE FABRICATED IAW DWG 9957828 AND SRM 51-10-2. AFTER THAT, THE FABRICATED PARTS WERE TREATED AND PAINTED IAW SRM 51-10-3, PAR 21 AND 14. FINALLY FLOOR PANEL ASSY WAS INSTALLED IAW SRM 51-30-2.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON COUNTERSINK FUEL ACCESS PLATE NR 1303C AT LT WING, LW, SM, CARD 155, ZONE 010. CORROSION ON COUNTERSINK HOLES WERE MEASURED, MAX DIAMETER ALLOWABLE IS 0.532", AND MAX DIAMETER MEASURED ON 3 ADJACENT HOLES IS 0.592". THEREFORE ITS OUT OF LIMITS IAW SRM 51-22-2A AND WAS REPLACED IAW IPC 57-30-00-31A.

Part: PAN — CRACKED (BS 826) · airframe 73,428 hrs · 56,901 cycles

CRACKED RT UPPER AFT WING PAN CORNER ON BS 826. REPAIRED IAW SRM 53-05, FIG 122 AND 51-30-2, 51-30-5, 51-10-3, PARG 14 AND 21.

Part: PAN — CRACKED (BS 927) · airframe 73,428 hrs · 56,901 cycles

CRACKED RT UPPER FWD RING PAN CORNER ON BS 927. REPAIRED IAW SRM 53-05, FIG 122 AND 51-30-2, 51-30-5, 51-10-3, PARA 14 AND 21.

Part: SEAT TRACK — CORRODED (BS 480-610) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON LT SEAT TRACK REPAIR PLUGS X 54, BS 480-484, AND 605-610. PLUGS WERE REPLACED IAW SRM 51-30-1, 53-05, FIG 4, 51-10-3, PAR 14, 21.

Part: SEAT TRACK — CORRODED (BS 269-666) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON OF SEAT TRACK REPAIR X -54, BS 269-272, AND 662-666. PLUGS WERE REPLACED IAW SRM 51-10-3 PAR 14, 21, 53-05, 51-30-1.

Part: SEAT TRACK — CORRODED (BS 1245-1298) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON LT SEAT TRACK REPAIR PLUGS X -54 BS 1245-1250 AND 1294-1298. PLUGS WERE REPLACED IAW SRM 51-10-3, PAR 14, 21, 53-05, 51-30-1.

Part: SEAT TRACK — CORRODED (BS 930-1125) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON LT SEAT TRACK REPAIR PLUGS X 54, BS 930-935 AND 1120-1125. PLUGS WERE REPLACED IAW SRM 51-10-3, PAR 14, 21, 53-05, 51-30-1.

Part: SEAT TRACK — CORRODED (BS 351-427) · corrosion level 2 · airframe 73,428 hrs · 56,901 cycles

CORROSION ON LT SEAT TRACK, REPAIR PLUG X54, BS Y=351-355 AND BS 421-427. REPAIR PLUG REMOVED IAW SRM 51-30-1, AND NEW PLUGS INSTALLED IAW SRM 51-30-1.

Part: TAB — DENTED (RT ELEVATOR) · airframe 73,428 hrs · 56,901 cycles

SEVERAL DENTS ON UPPER SKIN AT RT ANTI-FLOAT TAB GEARED TAB AND CONTROL TAB AT RT SIDE. DUE EXCESSIVE DAMAGE THE RT ANTI-FLOAT TAB, GEARED TAB AND CONTROL TAB AT RT SIDE WERE REPLACED IAW SRM 55-04, P.2.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 73,374 hrs · 56,860 cycles

DURING LINE CHECK, MAINTENANCE FOUND THE EMERGENCY LIGHTING FOR THE CATWALK IN THE TAIL COMPARTMENT WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES. OPS CHECKED GOOD.

Part: ENGINE — SHUTDOWN (NR 2) · airframe 72,859 hrs · 56,497 cycles

FLIGHT DIVERTED, WITH THE NR 2 ENGINE SHUTDOWN. CREW REPORTED THAT WHILE LEVEL AT FL 350, SMOKE STARTED CIRCULATING IN THE CABIN, THE NR 2 ENGINE WAS LOSING OIL QUANTITY, AND THE NR 2 ENGINE OIL PRESSURE WENT TO ZERO. THE QRH PROCEDURES WERE COMPLIED WITH AND THE NR 2 ENGINE WAS SHUTDOWN. MAINTENANCE FOUND OIL IN THE NR 2 ENGINE INLET AND EXHAUST SO THE NR 2 ENGINE WAS REPLACED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 72,493 hrs · 56,244 cycles

MAINTENANCE FOUND AFT SECTION OF OVERHEAD EMERGENCY LIGHTS INOPERATIVE. MAINTENANCE REPLACED BATTERY PACK IAW AMM 33-53. CKS GOOD.

Part: SELECTOR SWITCH — LOOSE (COCKPIT) · airframe 72,358 hrs · 56,146 cycles

THE CREW DIVERTED THE FLIGHT DUE TO AN "AFT CARGO FIRE" INDICATION DURING CLIMB OUT, AT APPROXIMATELY 14K. CREW COMPLIED WITH QRH PROCEDURES AND DISCHARGED THE CARGO FIRE BOTTLE. MAINTENANCE PLACED THE CARGO COMPARTMENTS AND FIRE DETECTION SYSTEM ON MEL AND THE FLIGHT CONTINUED. THE CARGO FIRE EXTINGUISHING BOTTLES WERE REPLACED ALONG WITH THE COCKPIT CONTROL PANEL DUE TO A LOOSE AFT COMPARTMENT SELECTOR SWITCH. THE CARGO FIRE INDICATION SYSTEM WAS FOUND OPERATIONAL.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 71,690 hrs · 55,682 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING IN THE TAIL WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 71,217 hrs · 55,343 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE OVERHEAD EMERGENCY LIGHTS IN FIRST CLASS SECTION WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACKS AND THE OPS CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 69,523 hrs · 54,172 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTS AT ROW 12 OF THE CABIN WOULD REMAIN ON WHEN POWER WAS REMOVED. MAINTENANCE REPLACED THE BATTERIES. OPS CHECKED GOOD.

Part: A/C PACK — FAILED (LEFT) · airframe 69,321 hrs · 54,043 cycles

CREW NOTED THAT DURING LEVEL OFF AT FL240, THE FLOW LIGHT ILLUMINATE AND THE CABIN LOST PRESSURIZATION. INITIATED A RAPID DESCENT, PAX OXYGEN MASKS DEPLOYED AUTOMATICALLY, AND LANDED SAFELY. LT PACK FAILED. MAINTENANCE FOUND LT PACK ICE SCREEN AND WATER SEPARATOR OBSCURED WITH ICE. WATER DRAIN LINE CLEARED, LT WATER SEPARATOR REPLACED, AND ASSOCIATED TEMPERATURE CONTROL VALVE REPLACED.

Part: SILL — DAMAGED (FWD CARGO DOOR) · airframe 69,185 hrs · 53,947 cycles

DURING CHECK, FWD CARGO DOOR SILL HAS THREE HOLES MISDRILLED, BS 377, 379 AND 419. REPAIRED IAW ER/A 520930-14.

Part: FITTING — NOT REPORTED (SLAT DRIVE) · airframe 69,178 hrs · 53,945 cycles

SLAT DRIVE FITTING REPAIRED IAW AA 2700-01074.

Part: SILL — CORRODED (CARGO DOORWAY) · corrosion level 2 · airframe 69,185 hrs · 53,947 cycles

DURING CHECK, CARGO DOOR SILL HAS SEVERAL SPOTS OF CORROSION ALONG DOOR STOP. COMPLETED REPAIR IAW ER/A 520930-14.

Part: BUSHING — WORN (TAILCONE RELEASE) · airframe 69,178 hrs · 53,945 cycles

DURING CHECK, BUSHINGS WERE NOTED TO BE WORN AT THE TAIL CONE RELEASE TEE PIN. REPLACED BUSHINGS IAW AMM 20-10-02.

Part: LANYARD — MISRIGGED (TAILCONE SLIDE) · airframe 69,178 hrs · 53,945 cycles

INSPECTION DISCOVERED THAT THE EMERGENCY ESCAPE SLIDE IN THE TAILCONE WAS NO LONGER IN AN ACCEPTABLE CONFIGURATION. MISRIGGED, IMPROPERLY INSTALLED STRAP FOR SLIDE COVER WOULD PREVENT PROPER DEPLOYMENT OF THE ESCAPE SYSTEM AND IS NOT IN COMPLIANCE. TAILCONE SLIDE COVER LANYARD WAS REINSTALLED CORRECTLY.

Part: DOOR — NOT REPORTED (CARGO) · airframe 69,098 hrs · 53,881 cycles

CARGO DOOR REPAIRED IAW AA 5230-01159.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 69,053 hrs · 53,841 cycles

DURING LINE CHECK, MX FOUND THE EMERGENCY EXIT SIGNS IN THE AFT ACCESSORY COMPARTMENT INOPERATIVE. MX REPLACED THE BATTERIES. OPS CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 68,659 hrs · 53,557 cycles

DURING LINE CHECK, THE CEILING MOUNTED EMERGENCY EXIT LIGHTS WERE INOPERATIVE AT ROWS 1-4 AND ROWS 24-36. BATTERIES WERE REPLACED IN PACKS B5-100 AND B5-106 IAW AMM 33-50 AND OPS THEN CHECKED NORMALLY.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 68,061 hrs · 53,101 cycles

DURING LINE CHECK, MX FOUND THAT THE OVERHEAD EMERGENCY PATHWAY LIGHTING IN THE COCKPIT AND AT DOORS L1 & L2 WERE INOPERATIVE. MX REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 66,787 hrs · 52,198 cycles

DURING LINE CHECK, MX FOUND THAT BOTH OF THE OVERWING EMERGENCY EXIT SIGNS WERE INOPERATIVE. MX REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 66,340 hrs · 51,875 cycles

DURING LINE CHECK, MX FOUND THAT THE OVERHEAD EMERGENCY PATHWAY LIGHTING AT ROWS 11-14 WERE INOPERATIVE. MX REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: SEAT TRACK — CORRODED (BS 1136-1155) · airframe 65,676 hrs · 51,356 cycles

DURING CPCP/PSV, PAX CABIN, AFT AREA BETWEEN BS 1136 AND 1155 X22, SEAT TRACK WITH CORRODED. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS. REMOVED AND REPLACED SEAT TRACK IAW SRM 51-10-4.

Part: FLOOR SUPPORT — CORRODED (BS 180) · airframe 65,676 hrs · 51,356 cycles

CORROSION ON PLATE ATTACH STRUCTURE AT POS BS 180 AND L56 APPROXIMATELY IN PASSENGER CABIN. REMOVED SUPPORT, FABRICATED AND INSTALLED FLOOR SUPPORT DURING CPCP/PSV.

Part: SEAT TRACK — CORRODED (BS 1136) · airframe 65,676 hrs · 51,356 cycles

PAX CABIN AFT AREA BETWEEN BS 1136 AND 1155 X22, SEAT TRACK WITH CORROSION. FOUND SEAT TRACK TO BE OUT OF LIMITS. REMOVED AND REPLACED SEAT TRACK FROM BS 1117 TO 1309 IAW SRM 51-30-1 DURING CPCP/PSV.

Part: SKIN — CRACKED (RT WING TE FLAP) · airframe 65,676 hrs · 51,356 cycles

RIGHT WING OTBD TRAILING EDGE FLAP, LEADING EDGE SURFACE CRACKED AT XW 251. FOUND REPAIR DOUBLER TO BE CRACKED, REMOVED DOUBLER AND ACCOMPLISHED ERA 503745-14 REV ORIGINAL DURING CPCP/PSV.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 65,676 hrs · 51,356 cycles

AFT CARGO DOOR FRAME CORRODED. FABRICATED AND INSTALLED REPAIR AT BS 1155 TO 1211 IAW SRM 51-30-05 DURING CPCP/PSV.

Part: LUG — NOT REPORTED (HORIZONTAL STAB) · airframe 65,551 hrs · 51,264 cycles

HORIZONTAL STABILIZER HINGE RIB PIVOT BEARING LUG REPAIRED IAW AA 5500-01011.

Part: SKIN — NOT REPORTED (HORIZONTAL STAB) · airframe 65,551 hrs · 51,264 cycles

HORIZONTAL STABILIZER UPPER CENTER SKIN PANEL REPAIRED IAW AA 5510-01086.

Part: CONNECTOR — DISCONNECTED (CATWALK) · airframe 64,668 hrs · 50,669 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE FIRST EMERGENCY PATHWAY LIGHTING ON THE CATWALK IN THE TAIL COMPARTMENT WAS INOPERATIVE. MAINTENANCE FOUND PIN AND RECEPTACLE AT THE CONNECTOR NOT PROPERLY SEATED. RESEATED CONNECTOR AND THE SYSTEM RETURNED TO NORMAL OPERATION.

Part: CONNECTOR — DISCONNECTED (CABIN) · airframe 64,353 hrs · 50,448 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT SEAT 2C IN THE FIRST CLASS CABIN, WAS INOPERATIVE. MAINTENANCE FOUND A CONNECTOR IN THE WIRE HARNESS HAD FAILED AND REPLACED IT. THE FUNCTIONAL CHECK OF THE SYSTEM WAS GOOD.

Part: POWERPACK — INOPERATIVE (CABIN) · airframe 64,347 hrs · 50,442 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN THE FIRST CLASS SECTION OF THE CABIN HAD FAILED. MAINTENANCE REPLACED THE POWER PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BATTERY — DISCHARGED (CABIN) · airframe 64,116 hrs · 50,277 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY EXIT SIGN AT THE FORWARD OVERWING EMERGENCY HATCH WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES IN THE POWERPACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BATTERY — DISCHARGED (CABIN) · airframe 62,623 hrs · 49,204 cycles

DURING LINE CHECK MAINTENANCE FOUND CABIN CEILING EMERGENCY LIGHTS BETWEEN ROWS 28-30 INOPERATIVE. MAINTENANCE REPLACED BATTERIES AT POWER SUPPLY B5-106 ABOVE SEAT 29DC. OPERATION OF LIGHTS NOW CHECKS GOOD.

Part: SPAR — CRACKED (WING) · airframe 62,085 hrs · 48,848 cycles

WING REAR SPAR CRACKING AT XRS 164 REPAIRED IAW AA 5710-01110.

Part: HEATER — NOT REPORTED (STATIC PORT) · airframe 62,085 hrs · 48,848 cycles

STATIC PORT HEATER REPAIRED IAW AA 3030-01027.

Part: CONNECTOR — DISCONNECTED (EMERGENCY LIGHT) · airframe 61,478 hrs · 48,467 cycles

DURING LINE CHECK, MX FOUND PASSENGER EMERGENCY PATHLIGHT AT 11D INOPERATIVE. MX RECONNECTED EMERGENCY LIGHT HARNESS PLUG TO LIGHT. OPERATION OF LIGHT NOW CHECKS OK.

Part: ENGINE — FAILED (NR 1) · airframe 60,560 hrs · 47,838 cycles

NR 1 ENGINE FAIL INFLIGHT. LOUD BANG WITH ROLLBACK AND ENGINE LOSS OF POWER. DISCOVERED METAL IN TAILPIPE.

Part: BEAM — CORRODED (FUSELAGE) · airframe 59,085 hrs · 46,827 cycles

DURING HMV EXFOLIATION CORROSION WAS FOUND ON C3 DOOR JAMB LWR BEAM AT STA Y=1174 AND 1193. BEAM WAS REPAIRED IAW SRM 53-05 FIG 123.

Part: SUPPORT FITTING — OUT OF LIMITS (LT MLG) · airframe 59,085 hrs · 46,827 cycles

DURING HMV LT GEAR SUPPORT FITTING BUSHING BORE WAS FOUND OUT OF LIMITS. BUSHING BORE WAS REPAIRED IAW EA 09-093855-03AD REV B.

Part: SUPPORT FITTING — DAMAGED (RT MLG) · airframe 59,085 hrs · 46,827 cycles

DURING HMV ELONGATED RT GEAR SUPPORT FITTING BEARING BORE WAS FOUND. RT GEAR FITTING BORE WAS REPAIRED IAW EA 09-093855-03AD REV B.

Part: SUPPORT FITTING — DAMAGED (LT MLG) · airframe 59,085 hrs · 46,827 cycles

DURING HMV ELONGATED LT GEAR SUPPORT FITTING BEARING BORE WAS FOUND. BEARING BORE WAS REPAIRED IAW EA 09-093855-03AD REV B.

Part: FASTENER — CORRODED (TAIL CONE) · airframe 59,085 hrs · 46,827 cycles

DURING HMV RUSTED PULLEY ATTACHING HARDWARE AND GUARD PIN WAS FOUND FOR THE TAIL CONE RELEASE SYSTEM CABLE AT STA Y=1510 RUSTED HARDWARE AND GUARD PIN WAS REPLACED IAW AMM 20-10-17-201.

Part: SUPPORT FITTING — CORRODED (RT MLG) · airframe 59,085 hrs · 46,827 cycles

DURING HMV PITTING CORROSION WAS FOUND ON RT GEAR SUPPORT FITTING BUSHING BORE. BUSHING BORE WAS REPAIRED IAW EA 09-093855-03AD ME02 REV B.

Part: SKIN — CRACKED (FUSELAGE) · airframe 59,085 hrs · 46,827 cycles

DURING HMV A CRACK WAS FOUND ON FUSELAGE SKIN AT STA Y=374 BETWEEN LONGERON 20RT AND 21RT AT FWD UPPER CORNER OF THE FWD CARGO DOOR JAMB .718. CRACK IN FUSELAGE SKIN WAS REPAIRED IAW SRM 53-05 FIG 105.

Part: SKIN — CORRODED (FUSELAGE) · airframe 59,085 hrs · 46,827 cycles

DURING HMV GENERAL SURFACE CORROSION ON DRAIN HOLES BETWEEN LONGERON 30RT AND 29RT AT STA Y=689 TO 691 AT C2 WAS FOUND. DRAIN HOLES WERE REPAIRED IAW ERA 477123-14 REV ORG.

Part: FRAME — CRACKED (FUSELAGE) · airframe 59,085 hrs · 46,827 cycles

DURING HMV A CRACK WAS FOUND ON FUSELAGE FRAME OVERWING STA Y=864 X=-52 RT. FRAME WAS REPLACED IAW DWG SR09530282.

Part: CLEVIS — CORRODED (TAIL CONE) · airframe 59,085 hrs · 46,827 cycles

DURING HMV RUSTED CLEVIS (3 EACH) WAS FOUND FOR TAIL CONE RELEASE CABLE SYSTEM STA Y=1510. RUSTED CLEVIS WAS REPLACED IAW AMM 20-30-01.

Part: LEVER — WORN (TAIL CONE) · airframe 59,085 hrs · 46,827 cycles

DURING HMV WEAR WAS FOUND ON LEVER OF TAIL CONE UPPER RT LATCH. LEVER OF TAIL CONE RT UPPER LATCH WAS REPLACED IAW CMM 53-50-01.

Part: SKIN — CRACKED (FUSELAGE) · airframe 59,085 hrs · 46,827 cycles

DURING HMV A CRACK WAS FOUND ON FUSELAGE SKIN STA Y=1437 BETWEEN LONGERON 3 RT AND 4 RT. CRACK WAS REPAIRED IAW SRM 53-04D FIG 27.

Part: LATCH — CORRODED (TAIL CONE) · airframe 59,085 hrs · 46,827 cycles

DURING HMV CORROSION WAS FOUND ON HOUSING OF LATCH ASSY TO ATTACH TAIL CONE STA Y=1510 7 HRS POSITION. LATCH PIN WAS REPLACED IAW AMM 53-53-00-501.

Part: PIN — WORN (TAIL CONE) · airframe 59,085 hrs · 46,827 cycles

DURING HMV A WORN PIN OF TAIL CONE INTERNAL RELEASE MECHANISM WAS FOUND. PIN WAS REPLACED IAW AMM 20-30-01-201.

Part: TAB — DAMAGED (RUDDER) · airframe 59,085 hrs · 46,827 cycles

DURING HMV DAMAGE METALIZED COAT WAS FOUND ON RUDDER CONTROL TAB SKIN. METALIZED COAT OF RUDDER CONTROL TAB SKIN WAS REPAIRED IAW SRM 51-70-1AD PARAGRAPH 23.

Part: SKIN — DAMAGED (RUDDER) · airframe 59,085 hrs · 46,827 cycles

DURING HMV DAMAGE METALIZED COAT WAS FOUND ON RUDDER SKIN. METALIZED COAT OF RUDDER SKIN WAS REPAIRED IAW SRM 51-70-1AD PARAGRAPH 23.

Part: PAN — CORRODED (FUSELAGE) · airframe 59,085 hrs · 46,827 cycles

DURING HMV PITTING CORROSION WAS FOUND ON LOWER DOOR JAMB PAN REPAIR AT STA Y=377 TO 383 AND Y=418 TO 423 AT FWD CARGO COMPARTMENT. LOWER DOOR JAMB PAN WAS REPAIRED IAW SRM 53-05D FIG 804D.

Part: CLAMP — WORN (TAIL CONE) · airframe 59,085 hrs · 46,827 cycles

DURING HMV WORN CLAMPS WERE FOUND FOR TAIL CONE RELEASE CABLE STA 1510. CLAMPS WERE REPLACED IAW AMM 20-30-01-201.

Part: TAB — CORRODED (HORIZ STAB) · airframe 58,999 hrs · 46,769 cycles

DURING SHOP VISIT THE SUBJECT HORIZONTAL STABILIZER ELEVATOR ANTI-FLOAT TAB WAS FOUND WITH CORROSION. REPAIRED PER ERA 474926-14.

Part: ENGINE — MALFUNCTIONED (NR 2) · airframe 56,842 hrs · 45,406 cycles

RT OIL PRESSURE DROPPED TO 0 AND RT OIL PRESSURE LOW MSG ON EOAP. SECURED RT ENG IN ACCORDANCE WITH THE QRH. OPENED LOWER COWL DOOR, REMOVED MAG CHIP DETECTOR. CLEANED INTO PAPER TOWEL. RE-INSTALLED MAG DETEDCTOR. PAPER TOWEL WITH ME LOCATED IN MCO PLACARD POUCH IN LOG BOOK. REPLACED NR 2 ENGINE PER TRANS 9T102.

Part: OUTFLOW VALVE — BINDING (CABIN PRESSURE) · airframe 55,887 hrs · 44,723 cycles

ON CLIMB-OUT AROUND 7000 FT AUTO PRESS INOP ILLUMINATED (ALONG WITH AUTO1 AND AUTO 2 PRESS) MANUAL PRESSURIZATION WHEEL WOULD NOT MOVE FORWARD OF THE 15 FLAP POSITION. UPON INSPECTION, FOUND 2 SCREWS IN CHANNEL OF OUTFLOW VALVE CONTROL WHEEL CAUSING IT TO BIND. REMOVED SCREWS AND INSPECT AREA, FOUND 2 SCREWS MISSING FROM UNDER FMS CONTROL PANEL. INSTALLED SCREWS IN PANEL, PERFORMED BITE CK OF CABIN PRESS CONTROLLERS PER 21-32-00 OF AMM, NO FAULTS FOUND. PERFORMED T OF OUTFLOW VALVE MANUAL CONTROL PER AMM, NO DEFECTS FOUND.

Part: UNKNOWN — UNKNOWN (CABIN PRESSURE) · airframe 55,030 hrs · 44,178 cycles

DURING CLIMB-OUT, CABIN WOULD NOT REPRESSURIZE. BOTH AUTO CONTROLLERS ATTEMPTED. DURING RETURN CABIN REPRESSURIZED BITE BOTH CONTROLLERS NO FAULTS FOUND. RAN OUTFLOW VALVE, MANUALLY CKS GOOD OK FOR SERVICE.

Part: LINE — LOOSE (APU) · airframe 53,491 hrs · 43,186 cycles

AFTER TAKEOFF (APPROX 60 SECOND) ALL 3 LAV SMOKE DETECTORS SOUNDED FA'S AND PAX'S REPORTED SMOKE SMELL AND HAZE EMERG RETURN TO ATL. FOUND OIL CONTAMINATION IN APU INLET. LK CKD APU. FOUND B-NUT LEAKING ON OIL LINE AFT FILTER MODULE. TIGHTENED SAME. LK CK GOOD. REMOVED LOWER DOOR ASSY CLEANED INLET AND DOOR ASSY. REPLACED SEPARATOR BAGS AND CLEANED OIL FROM DUCTS. PERFORMED FULL DUCT BURNOUT OPN 5089. RAN ENGS TO T/O PWR SEVERAL TIMES. ALL CK GOOD, BORO OF 6TH 7TH STG COMPRESSOR ON BOTH ENGS CKD GOOD. NO OIL PRESENT.

Part: SPAR — CORRODED (HORIZONTAL STAB) · airframe 53,203 hrs · 42,990 cycles

TOOLING DAMAGE WAS FOUND IN TWO HOLES IN THE OUTER SECTION OF THE HORIZONTAL STABILIZER REAR SPAR AND RIB. THE HOLES WERE OVERSIZED.

Part: SPAR — CORRODED (HORIZONTAL STAB) · airframe 53,203 hrs · 42,990 cycles

THE LT OUTER SECTION REAR SPAR OF THE HORIZONTAL STABILIZER WAS FOUND CORRODED IN THE LOWER CAP BARREL NUT HOLE. THE DAMAGED HOLE WAS OVERSIZED.

Part: APU — CONTAMINATED (APU BAY) · airframe 50,898 hrs · 41,479 cycles

AFTER T/O, ALL LAV SMOKE DETECTORS SOUNDED WITH SMOKE AND HAZE REPORTED IN CABIN BY FLIGHT ATTENDANTS. EMERGENCY RETURN TO ATL. FOUND APU INLET CONTAMINATED WITH OIL. OIL LEVEL IN SIGHT GAUGE WAS AT RE-FILL LINE. OIL TANK CAP IS INSTALLED AND SECURE. MX STILL IN PROGRESS 0910/17. FOUND OIL CONTAMINATION IN APU INLET. LK CKD APU. FOUND B-NUT LEAKING ON OIL LINE AFT FILTER MODULE. TIGHTENED SAME. LK C GOOD. REMOVED LOWER DOOR ASSY CLEANED INLET AND DOOR ASSY REPLACED.

Part: RELEASE CABLE — DISLODGED (TAILCONE) · airframe 50,395 hrs · 41,123 cycles

TAIL CONE UNSAFE MSG AT FL 220. FOUND UPPER RELEASE CABLE (INNER RELEASE CABLE) TRIPPED. REINSTALLED CABLE. NO MSG ON EOAP.

Part: ENGINE — FAILED (NR 2) · airframe 49,188 hrs · 40,266 cycles

NR 2 ENG FAILED DURING CLIMB-OUT AT 19,800 FT MSL, LOUD BANG, MODERATE VIBRATION FOLLOWED. REPLACED ENGINE.

Part: BALLAST — OVERHEATED (CABIN LIGHTS) · airframe 47,987 hrs · 39,382 cycles

SMOKE IN CABIN JUST PRIOR TO PUSHBACK. FOUND LIGHT BALLAST (B652) AT SEAT ROW 29ABC OVERHEATING. REPLACED BALLAST ASSY LIGHTS AND BALLAST, OPS CHECKS NORM.

Part: O-RING — BROKEN (RT HYD RES) · airframe 47,967 hrs · 39,366 cycles

ON CLIMBOUT NOTED RT HYD QTY AT 2 WITH CAUTION LIGHT ON, HYD PRESS WAS GOOD. TURNED RT ENGINE HYD PUMP AND HYD QTY SLOWLY ROSE UP TO 10 LEFT PUMP, UNTIL APPROACH RT HYD WOULDN'T COME UP WITH ENGINE PUMP SWITCH ON AND AUX PUMP. PERFORMED FLAP 15 LANDING AFTER EMERGENCY EXT OF LANDING GEAR. REPLACED LEAKING O-RING ON BOTTOM OF RT RESERVOIR. SERVICED FLUID.

Part: ODOR — DETECTED (COCKPIT) · airframe 47,159 hrs · 38,814 cycles

DURING CRUISE AT FL 310 ODOR OF BURNING RUBBER PRESENT IN COCKPIT FOR ABOUT 30 SECONDS, OVENS WERE OFF AND HAD NOT BEEN USED. PACKS NORMAL. ALL SYSTEMS INDICATE NORMAL. T/S PER OPN 5088 PERFORMED OPN 5088 AND 5089 NO TROUBLE FOUND.

Part: SWITCH — SHORTED (COCKPIT) · airframe 47,031 hrs · 38,724 cycles

WHEN ATTENDANT CALL RESET WAS PUSHED IN, LIGHT FIZZLED FOLLOWED BY SMOKE COMING FROM BEHIND SWITCH. REPLACED ATTENDANT CALL RESET SWITCH. SYSTEM NOW CHECKS NORMALLY.

Part: FLASHLIGHT — INOPERATIVE (L-1 DOOR) · airframe 46,122 hrs · 38,099 cycles

L-1 UPPER EMERGENCY FLASHLIGHT INOP. REPLACED AND TESTED PER MM.

Part: CHARGER — INOPERATIVE (EMERGENCY LIGHT) · airframe 44,409 hrs · 36,929 cycles

EMERGENCY LIGHTS INOP IN AFT CABIN. REPLACED POWER SUPPLY, BATTERY AND LIGHT ASSY L2-845. EMERGENCY LIGHTS SELF TEST GOOD.

Part: STUD — LOOSE (EPC) · airframe 43,936 hrs · 36,587 cycles

ON CLIMBOUT LOST LT DC AND AC BUSSES WITH APU POWERING BUSS. APU VOLTS/FREQS GOOD. MULTIPAL C/B POPPED LT AC BUS BREAKER LT TR1 AND TR2 EMER AC BUS FEED - F25 F16. LOST FMS MPC DFGC LDC BUS MSG ILLUMINATED. REPLACED LT APU CONTROL RELAY AND GCU.

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 42,321 hrs · 35,475 cycles

ON L/O INSPECTION, AFT EMERGENCY ISLE EXIT LIGHTS WILL NOT TEST. REPLACED POWER SUPPLY

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 41,920 hrs · 35,184 cycles

EMERGENCY AISLE LIGHTS FROM ROW 24-30 INOPERATIVE. REPLACED BATTERY PACK.

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 41,196 hrs · 34,647 cycles

FOUND ALL SEAT EMERGENCY LIGHTS AND DOOR IDENTIFIERS NOT WORKING WITH COCKPIT SWITCH. FOUND AFT SEAT ROW POWER SUPPLY BAD SENDING POWER BACK TO SWITCH. REPLACED AFT POWER SUPPLY FOR SEATS, EMERGENCY LIGHTS CHECK NORMAL.

Part: ENGINE — DAMAGED (NR 2) · airframe 40,381 hrs · 34,028 cycles

ACFT RTO DUE NR 2 ENGINE OVERTEMP. ACFT RETURNED TO GATE. SUBSEQUENT BORESCOPE CONFIRMED 7 STAGE FAILURE. REPLACED ENGINE.

Part: ENGINE — FAILED (#2 ENGINE) · airframe 38,724 hrs · 32,792 cycles

T.O ABORTED FOR RT GEN FAILURE/ RESET ON GND SEEMED OK FOR 3 MIN THEN FAILED AGAIN TRIED NEW GCU RT SIDE NO HELPP GCU FAULTS GEN. REPLACED CSD AND GEN PER M/M OPS AND LK CKS GOOD

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 37,122 hrs · 31,608 cycles

EGRESS LIGHTING INOP ROW 24 - 30. FOUND WIRING SHORTED BETWEEN ROWS 27 - 28. REPAIRED WIRING AND REPLACED AFT PWR SUPPLY.

Part: APU — LEAKING (APU BAY) · airframe 36,472 hrs · 31,147 cycles

AFT SMOKE DETECTORS SOUNDED AND FLT ATTNS REPORT SMELLING UNIDENTIFIABLE ODOR WHEN AIRFOIL A/I IN USE. ALARMS STOPPED 1.5 MIN AFTER A/I OFF. MTC FOUND OIL AT APU INLET APPEARS TO BE COMING FROM INSIDE APU. PERFORMED DUCT BURNOUT. REPLACED APU FOR OIL LEAK.

Part: APU — SMOKE (AFT) · airframe 36,411 hrs · 31,102 cycles

DURING DESCENT THRU ICING WITH WING ANTI-ICE ON GOT A SMOKY SMELL IN CABIN AND RT AFT LAV SMOKE DETECTOR WENT OFF. C/W DUCT BURNOUT PROCEDURE.

Part: MOTOR — MALFUNCTIONED (STAB TRIM) · airframe 36,179 hrs · 30,924 cycles

PRIMARY STAB TRIM FAILED DURING CLIMB. ALTERNATE TRIM OPERATED NORMAL. RETURNED TO CVG. YOKE AND SUITCASE SWITCHES BOTH WERE INOP. TRIM FAILED AT 2 UNITS. CHECKED POWER IN AND OUT OF TRIM RELAYS. CHECKED POWER AT PRIMARY TRIM MOTOR AND BRAKE WITH METER AND TEST LIGHT. ALL CKS OK. REPLACED PRIMARY STAB TRIM MOTOR AS PRECAUTIONARY. ALL CKS GOOD.

Part: SLIDE — FAILED (TAIL CONE) · airframe 36,071 hrs · 30,843 cycles

TAIL CONE DEPLOYED AT GATE FOR UNKNOWN REASONS. AFTER TAIL CONE DEPLOYED EMERGENCY SLIDE FAILED TO OPEN. STRAP FAILED TO PULL COVER FROM SLIDE. LANYARD AND STRAP FELL TO GROUND WITH TAIL CONE ASSY. REPLACED DAMAGED PORTION OF TAIL CONE. REINSTALLED CONE AND SLIDE.

Part: JAMB — CORRODED (BS 1174)

CORROSION FOUND AT THE C3 DOORWAY LWR DOOR JAMB BEAM. MOST BLENDS WERE WITHIN ALLOWABLE LIMITS, EXCEPT AT FS 1174. REPAIRED PER ERA 333204-14, REV A.

Part: SKIN — DAMAGED (BS 320)

LIGHTNING STRIKE DAMAGE WAS FOUND NEAR AN EXISTING REPAIR. EVALUATION OF LIGHTNING STRIKE REQUIRED THE FUSELAGE SKIN TO BE CUT OUT. BOTH DAMAGES ARE INCORPORATED INTO A NEW REPAIR. REPAIRED PER ERA 366417-14, REV B.

Part: SKIN — DENTED (BS 229-269)

SEVERAL DENTS WERE FOUND IN THE FUSELAGE SKIN FROM STA 229 TO 269 AND BETWEEN L17L AND 18L. REPAIRED PER ERA 333232-14, REV. A.

Part: HINGE — CORRODED (HORIZ STAB)

DURING INSPECTION OF THE VERTICAL TO HORIZONTAL STAB HINGE PLATES (REF ERA 373241-14AD) CORROSION WAS FOUND ON THE FACES AND WITHIN THE BORES OF THE HINGE PLATES. DAMAGE WAS WITHIN SRM ALLOWABLE LIMITS. BORE CLEAN UP EXCEEDED SRM ALLOWABLE LIMITS BY 0.003. REWORKED PER ERA 333220-14AD.

Part: CLAMP — LOOSE (NR 2 ENGINE)

RT ENGINE NR 2 FAILED PASSING APPROX 5000 FT ON INITIAL CLIMBOUT. THIS APPEARED TO HAPPEN AFTER ENG ANTI-ICE WAS TURNED OFF. ENG RESTARTED NORMALLY AND RAN NORMAL. FOUND STARTER VALVE CLAMP UPSTREAM OF VALVE, OFF THE DUCT. REPLACED CLAMP, RAN ENGINE TO T/O POWER. CHECKED OK.

Part: AIR DIST — ODOR (CABIN)

SMOKE SMELL IN FWD GALLEY/FWD CABIN AFTER TAKEOFF. NO VISIBLE SMOKE OR FIRE, DIVERT TO MCO. MTC INSPECTED A/C DUCTS, RECIRC FAN AND FILTER. ALSO, REPLACED A/C WATER SEPARATOR COALESCER BAGS AND LEFT WATER SEPARATOR. CHECKED VALVE, RAN ENGS AT HI POWER OFF GATE WITH FLT CREW AND FOUND RT A/C SYS WITH SLIGHT OILY SMELL IN AIR FWD RT A/C SYS TO MCO. PLAC PER MEL.

Part: AIR DIST — SMOKE (GALLEY)

ON CLIMBOUT, THE FLT ATTENDANTS REPORTED SMOKE IN THE FWD GALLEY AND THE FLOOR WAS UNUSUALLY WARM. FOUND THE COFFEEMAKER CIRCUIT BREAKERS HAD POPPED. FLIGHT RETURNED TO MLB. CONTRACT INSPECTED THE A/C FOR EVIDENCE OF OVERHEATING UNDER THE GALLEY FLOOR. FWD GALLEY INOPED FOR FLT TO ATL. OVERWEIGHT INSPECTION C/W PER M/M, NO TROUBLE FOUND.

Part: PAN — CORRODED (C1 DOORWAY)

FOUND AT D-2 LTR CK, CORROSION ON C-1 DOOR CUTOUT LWR THRESHOLD PAN. SPLICE REPAIR PAN PER SRM 53-05 FIG 44.

Part: WINDOW — CRACKED (RT COCKPIT)

F/O CLEARVIEW WINDOW CRACKED CLIMBING THROUGH FL 315 LARGE MIDDLE SECTION OF OUTER PANE HAS SEPARATED FROM ACFT. REPLACED RT AFT WINDSHIELD PER M/M.

Part: LIGHT — INOPERATIVE (CABIN)

FIRST CLASS EMERGENCY AISLE LIGHTS INOP. REPLACED BATTERIES, CHECKS NORMAL.

Part: EEL WIRE — BROKEN (CABIN)

ON PRE-FLIGHT, FOUND EMERGENCY FLOOR LIGHTING INOP AFT OF ROW 24. REPAIRED BROKEN WIRE IN TRACK, OPERATION NORMAL.

Part: LINK — BROKEN (NLG DOOR)

AFTER TAKEOFF HAD LOUD NOISE COMING FROM NOSE GEAR AREA, AFTER GEAR RETRACTION. RETURNED OAK. FOUND RT NLG DOOR OPEN. REPLACED DOOR ACTUATOR LINK, CYCLED GEAR RETRUNED TO SERVICE.

Part: BRACKET — CRACKED (NR 2 ENGINE)

ON LANDING HAD EXCESSIVE SMOKE COMING FROM NR 2 ENGINE. AIRCRAFT WAS EVACUATED. FOUND FUEL LEAK AT NOZZLE AREA OF ENGINE, ENGINE WAS REPLACED AND ROUTED TO SHOP FOR INVESTIGATION. UPON SHOP DISASSEMBLY OF ENGINE IT WAS FOUND THAT BRACKETPART NR 773243 HAD BROKEN AND A PIECE OF THE BRACKET HAD WEDGED BETWEEN THE FUEL MANIFOLD P/N 806266 AND CHAFED A HOLE IN THE MANIFOLD CAUSING THE FUEL LEAK.

Part: THERMAL SWITCH — FAILED (TAIL COMP)

DURING APPROACH, HAD FUMES AND OR HOT SMELL IN CABIN AND COCKPIT WITH AIR FOIL ANTI-ICE SELECTED, SMELL GOT STRONGER WITH TAIL DE-ICE ON. LAVATORY SMOKE DETECTORS ACTIVATED. LANDED ATL. REPLACED TEMPERATURE SENSOR RAN ENGINES AND PACKS WITH ANTI-ICE ON OPERATION NORMAL.