N916DE

Part: WIRE HARNESS — DISCONNECTED (CABIN) · airframe 62,823 hrs · 48,732 cycles

SEAT 33ED EMERGENCY PATH LIGHT INOP. RECONNECTED UNDER SEAT HARNESS. CKS GOOD PER AMM 33-50.

Part: BATTERY — DISCHARGED (COCKPIT) · airframe 62,704 hrs · 48,630 cycles

DURING SERVICE CHECK, MAINTENANCE FOUND THE COCKPIT EMERGENCY LIGHT TO BE INOPERATIVE. TROUBLESHOOTING LEAD TO A DEFECTIVE BATTERY IN THE POWER PACK REF AMM 33-53. BOTH BAD CELLS IN THE BATTERY PACK WERE REPLACED. OPERATIONAL CHECK WAS GOOD.

Part: BATTERY — DISCHARGED (CABIN) · airframe 62,329 hrs · 48,312 cycles

FWD EMERGENCY LIGHTS INOP. REMOVED AND INSTALLED NEW BATTERIES IAW AMM 33-53 OP CHECK GOOD P/N AD-4002P.

Part: BATTERY — DISCHARGED (CABIN) · airframe 61,831 hrs · 47,917 cycles

FWD EMERGENCY LIGHTS INOP. REPLACED BATTERIES IAW AMM 33-53 OP CHECK GOOD.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 61,070 hrs · 47,298 cycles

AFT EMERG LIGHT RT SIDE IN 48 SEC INOP. RELAMPED PER AMM 33-00 OPS CK NORMAL AT THIS TIME.

Part: UNKNOWN — ODOR · airframe 60,941 hrs · 47,197 cycles

DUE TO REPORT OF BURNING RUBBER SMELL ON TAKE OFF. PER CREW VERBAL, ALL ENG. INDICATIONS NORMAL. CLOSE VISUAL INSP OF WHEEL WELLS, LOWER AFT FUSELAGE, APU INLET AND BOTH ENGINES REVEALED NO FLUID CONTAMINATION.

Part: SKIN — DENTED (BS 256) · airframe 60,160 hrs · 46,589 cycles

FUSELAGEDENTED BS 256, LONGERON 18L TO 20L. REPAIRED IAW ER/A 560919-14, REV ORIGINAL.

Part: POWER SUPPLY — NO TEST (EMERGENCY LIGHTS) · airframe 60,162 hrs · 46,590 cycles

DURING AN EMERGENCY LIGHTS CHECK, THE BATTERY POWER SUPPLY FAILED. THE BATTERY POWER SUPPLY WAS REPLACED IAW AMM 33-53-00-401. FUNCTIONAL TEST WAS PERFORMED IAW AMM 33-53- 00-601. TESTED OK.

Part: STEP — CORRODED (VENTRAL STAIRS) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON STAIR STEP AT VENTRAL STAIRWAY. STAIR STEP WAS REPLACED PER SRM 51-30-5.

Part: SPAR CAP — CRACKED (VERTICAL STAB) · airframe 60,160 hrs · 46,589 cycles

ONE CRACK INDICATION ON HOLE AT STA ZFS=57.767 AT VERTICAL STABILIZER FRONT SPAR CAP FWD FLANGE RT SIDE. ONE CRACK INDICATION ON HOLE AT STA ZFS=57.767 AT VERTICAL STABILIZER FRONT SPAR CAP FWD FLANGE. RT SIDE WAS REPAIRED PER ETI-88-17-226 REV 2 AND ER/A 560902-14AD REV ORIGINAL.

Part: PANEL — WORN (NR 2 SLAT) · airframe 60,160 hrs · 46,589 cycles

FOUND SEVERAL WORN AREAS ON INBOARD CORNER ON SLAT PANEL NR 2 ON THE RT WING. THE SLAT PANEL WAS REPLACED.

Part: LONGERON — CRACKED (BS 845) · airframe 60,160 hrs · 46,589 cycles

CRACKED LONGERON 1, BS 845. THE LONGERON WAS REPAIRED IAW ETI-88-17-224, REV ORIGINAL, AND ER/A 560887-14, REV ORIGINAL.

Part: STRUCTURE — DAMAGED (VERTICAL STAB) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

VERTICAL STABILIZER LEADING EDGE SKIN AT ZFS 52.287 DAMAGED. THREE BUSHINGS WERE REPLACED IAW ERA 535916-14, AD, REV ORIGINAL AND DWG SG 09550004, REV D.

Part: DOUBLER — CORRODED (BS 1155-1212) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

WEAR AND CORROSION ON DOUBLER OF AFT CARGO DOOR FRAME, BS 1155 TO 1212, LONGERON 28R. THE DOUBLER WAS REPLACED IAW SRM 53-05, FIG 123.

Part: CARGO TRACK — CORRODED (BS 1007-1215) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON THE CARGO TRACK BS 1007 TO 1215. THE CARGO TRACK WAS REPLACED IAW SRM 51-10-4.

Part: CARGO TRACK — CORRODED (BS 1007-1155) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON THE RT CARGO TRACK BETWEEN BS 1007 - 1155 IN THE AFT CARGO BAY. THE CARGO TRACK WAS REPLACED IAW SRM 51-10-4.

Part: FASTENER — DAMAGED (VERTICAL STAB) · airframe 60,160 hrs · 46,589 cycles

LOOSE AND SUNKEN FASTENERS ON SPLICE ZFS=52.267 UPPER & LOWER FASTENER ROWS AT VERTICAL STABILIZER L/E. HOLES AND COUNTERSINK OF REMOVABLE LEADING EDGE AND FIXED LEADING EDGE WERE EVALUATED AND WAS FOUND 80 OF 1/4 AND 99 OF 3/16 WITHIN LIMITS 5 OF 3/16 AND 1 OF 1/4 OUT OF LIMITIS. OUT LIMITS HOLES WERE REPAIRED IAW DWG SG09550004, REV. D.

Part: VANE — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON FITTING AT THE RT WING OTBD FLAP CENTER GUIDE VANE. THE FLAP CENTER GUIDE VANE WAS REPLACED IAW AMDS 2710-4628, AND 2710-4629.

Part: FINGER DOUBLER — CORRODED (BS 1212) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

EXCESSIVE CORROSION ON FINGER DOUBLER BS 1212 ,LONGERON 26L. THE FINGER DOUBLER WAS REPLACED IAW SRM 51-10-1, FIG 36, 51-30-2, AND 51-30-5.

Part: ACCESS PANEL — CRACKED (RT WING) · airframe 60,160 hrs · 46,589 cycles

CRACKED LWR ACCESS DOOR CUTOUT XRS 189 TO 214 BETWEEN STRINGERS 12 AND 15 ON THE RT WING. REPAIRED IAW ETI-88-17-222, REV 1, AND ER/A:560893-14AD REV ORIGINAL.

Part: SKIN — DENTED (BS 370) · airframe 60,160 hrs · 46,589 cycles

FUSELAGE SKIN DENTED AT BS 370 BETWEEN LONGERONS 23 - 24R. THE SKIN WAS REPAIRED IAW SRM 53-05, PAR 159, FIG 153.

Part: FLOORBEAM — CORRODED (BS 218) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON FLOORBEAM BS 218 BETWEEN LONGERONS 27L- 27R IN THE FWD CARGO BAY. A NEW FLOORBEAM ANGLE WAS FABRICATED AND REPLACED IAW SRM 53-14-1, FIG 7A.

Part: SKIN — DAMAGED (RT WING) · airframe 60,160 hrs · 46,589 cycles

DURING NDT INSPECTION, A DISCREPANT AREA WAS FOUND. SEVEN DIFFERENT FASTENERS OF PSE ON LOWER SKIN BETWEEN WS 163 TO 168 REAR SPAR ON THE RT WING. REPAIRED IAW ER/A 560873-14AD REV ORIGINAL.

Part: RUB STRIP — CORRODED (ACCESS PANEL) · airframe 60,160 hrs · 46,589 cycles

INITIAL; CORROSION AND DISBONDED RUB STRIB ON RH SIDE UPPER FUEL ACCESS PANELS NBRS 2302C, 1436C,1409C, 1410C AND 1414C (AD). RUB STRIPS ON FUEL ACCESS PANELS NBR2302C, 1436C, 1409C, 1410C AND 1414C WERE REPLACED PER DC/9 MD-80 S.R.M. 51-22-2A PAR 4. (LP0207136)

Part: ACCESS PANEL — NOT REPORTED (WING) · airframe 60,160 hrs · 46,589 cycles

SIDE UPPER FUEL ACCESS PANELS NBRS 2301C, 1311C, 1307C, 1303C AND 1335C. RUB STRIPS ON FUEL ACCESS PANELS NBR2301C,1311C, 1307C, 1303C AND 1335 WERE REPLACED PER DC/9 MD-80 S.R.M. 51-22-2A PAR 4. (LP0206371)

Part: CUSP WEB — CORRODED (BS 1174-1250) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

EXCESSIVE CORROSION ON CUSP WEB LBL 44 - 60, UPPER & LOWER SURFACES FROM BS 1174 - 1250. THE CUSP WEB WAS REPLACED IAW SRM 53-05, FIG 131 A.

Part: SEAT TRACK — DAMAGED (BS 273-308) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

SEAT TRACK, RT SIDE BS 273 TO 276, BETWEEN RBL 54, AND BS 306 TO 308 LBL 54. THE AREAS ARE OUT OF LIMITS IAW NRC 00219. A NEW SECTION OF SEAT TRACK AND REPAIR PARTS WERE INSTALLED IAW SRM 53-05, FIG 4 F, SHEET 3.

Part: INTERCOSTAL — CORRODED (BS 1309-1322) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION WAS FOUND ON THE INTERCOSTAL BETWEEN BS 1309 - 1322 AND LONGERONS 27 - 28L. THE INTERCOSTAL WAS REPLACED IAW SRM 51-30-2, AND 51-30-5.

Part: FLOOR SUPPORT — CRACKED (BS 769-788) · airframe 60,160 hrs · 46,589 cycles

A CRACK WAS FOUND ON THE FLOOR SUPPORT BETWEEN BS 769 TO 788, BL 0. A NEW INTERCOSTAL WAS FABRICATED IAW DWG:9936580, REV BW, INSTALLED IAW SRM 51-30-2, AND 51-30-5.

Part: FLOOR SUPPORT — CRACKED (BS 1287-1307) · airframe 60,160 hrs · 46,589 cycles

A CRACK WAS FOUND ON THE FLOOR SUPPORT BETWEEN BS 1287 - 1307, BL 0. THE FLOOR SUPPORT WAS REPLACED IAW DWG 9936580, REV BS, AND SRM 51-30-5.

Part: CUSP WEB — CORRODED (BS 1088-1090) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON THE LEFT CUSP WEB BETWEEN BS 1088 TO 1090. REPAIRED IAW SRM 53-05, FIGURES 131, A-13, 51-30-2, 51-30-5, 51-10-3 PAR. 21, 14 AND 38.

Part: CUSP WEB — CORRODED (BS 1070-1098) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON THE RT CUSP WEB BETWEEN BS 1070 TO 1072 AND BS 1096 TO 1098. REPAIRED IAW SRM 53-05, FIG 131 A, FIGURES 9 AND 13.

Part: CUSP WEB — CORRODED (BS 797-800) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON THE CUSP WEB LBL 44 - 60, UPPER & LOWER SURFACES BS 797 - 800. REPAIRED IAW SRM 53-01, FIG. 1.

Part: SERVICE PANEL — CORRODED (LAVATORY) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON FWD, LOWER LATCH SETTLEMENT AREA ON CUT OUT AT THE AFT LAVATORY SERVICE PANEL. THE LAVATORY SERVICE PANEL WAS REPAIRED IAW ER/A 397822-14, MA REV B. (LP# 0203427)

Part: FERRULE — DAMAGED (CABIN) · airframe 60,160 hrs · 46,589 cycles

DAMAGED AND MISSING FERRULES ON CABIN FLOOR PANELS 160D, 160A, 1117E, 160B, 693C, 465D, 200D, 120E, 1250C,1155B, 769D, 200B, 256B. REPLACED FLOOR PANELS. (LP# 0201721)

Part: CUSP WEB — CORRODED (BS 424-428) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

EXCESSIVE CORROSION ON CUSP WEB RT FROM BS 724 - 728. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-13.

Part: CUSP WEB — CORRODED (BS 465-484) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON PREVIOUS REPAIR DOUBLER OF CUSP WEB RBL 54 TO 60, BS 465 - 484. THE CUSP WEB WAS REPLACED IAW SRM 53-05, FIG 131A-13, AND SRM 51-30-5.

Part: CUSP WEB — CRACKED (BS 802-804) · airframe 60,160 hrs · 46,589 cycles

CRACK ON THE CUSP WEB MEMBRANE AT RBL 54 - 60, BS 802 - 804. REPAIRED IAW SRM 53-05, PAR 144, FIG 131A-1.

Part: CUSP WEB — CORRODED (BS 897-905) · airframe 60,160 hrs · 46,589 cycles

CORROSION ON CUSP WEB, RBL 54, UPPER & LOWER SURFACES FROM BS 897 - 905. REPAIRED IAW SRM 53-05, PAR 144, FIG 131A.

Part: CUSP WEB — CORRODED (BS 1256-1260) · airframe 60,160 hrs · 46,589 cycles

CORROSION ON THE CUSP WEB FROM BS 1256 - 1260, RBL 54 TO 60. REPAIRED IAW SRM 53-05, FIGURE 131A-13.

Part: VANE — WORN (LT WING TE FLAP) · airframe 60,160 hrs · 46,589 cycles

WEAR ON LEADING EDGE AT LT INBOARD VANE OUTBOARD FLAP. REPAIRED IAW 2000-8149-04.

Part: ACCESS PANEL — CORRODED (WING) · airframe 60,160 hrs · 46,589 cycles

CORROSION ON THE FUEL PANEL ACCESS PANEL 1456C. THE ACCESS PANEL WAS REPLACED.

Part: ACCESS PANEL — CRACKED (NOT REPORTED) · airframe 60,160 hrs · 46,589 cycles

CRACKED FUEL ACCESS PANEL 1355C. THE ACCESS PANEL WAS REPAIR IAW SRM 51-22-2A, PAR 6.

Part: FLOOR SUPPORT — CORRODED (CABIN) · airframe 60,160 hrs · 46,589 cycles

CORROSION ON FLOOR SUPPORT 160G. A NEW FLOOR SUPPORT WAS FABRICATED IAW SRM 51-10-4 AND DWG 9957828, REV AB.

Part: CUSP WEB — CORRODED (BS 419-422) · airframe 60,160 hrs · 46,589 cycles

CORROSION OUT OF LIMIT ON THE CUSP WEB FROM BS 419 - 422 , RBL 60. REPAIRED IAW SRM 53-05, PAR 144, FIGURE 131A-6.

Part: SEAT TRACK — DAMAGED (BS 878-880) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

SEAT TRACK, BS 878 TO 880, LBL 22. DAMAGED OUT OF LIMITS. THE SEAT TRACK WAS REPAIRED IAW SRM 53-05, FIG 4A.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 60,160 hrs · 46,589 cycles

DELAMINATION ON CABIN FLOOR PANELS 160E, 693C, 465D, 200D, 617C, 120E, 1250D, 1250B, 1250C, 927B. FLOR PANES NBRS:927B, 160E, 1250C,1250D, AND 1250B WERE FABRICATED AND IDENTIFIED PER MD-88 A.M.M. 53-20-01-201. AND FLOOR PANEL NBR:617C WAS CLEANING PER P.S. 900-1-2-2 N? 2 AND NO DELAMINATION WAS FOUND.FLOORS PANELS NBR:693C,465D, 200D AND 120E WAS ATTENDED WITH N.R.C. 00955. (LP0200453)

Part: SKIN — CORRODED (BS 731-826) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON FUSELAGE SKIN UNDER FILLET PANEL RUB STRIPS FROM BS 731 - 826. THE CORROSION WAS REMOVED IAW SRM 53-04, PAR. 57. NDT WAS ACCOMPLISHED IAW SPM 04-00-07, PAR 5, FIG 3, SHEET I AND 2. FOUND TO BE WITHIN LIMITS IAW SRM 53-04, PAR. 57.

Part: CUSP WEB — CORRODED (BS 503-598) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON CUSP WEB, LBL 44 - 60 UPPER & LOWER SURFACES, BS 503 - 598. THE CUSP WEB WAS REPLACED IAW SRM 53-05, FIGURE 131A-24, 51-30-1, 51-30-2, 51-30-5, AND DWG 9930538-11, REV BF.

Part: CUSP WEB — CORRODED (BS 598-617) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON CUSP WEB RT SIDE, RBL 54 TO 60 UPPER & LOWER SURFACES FROM BS 598 TO 617. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131-14.

Part: FLOOR SUPPORT — CORRODED · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON A FLOOR SUPPORT. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-10-4.

Part: ACCESS PANEL — CORRODED (WING) · airframe 60,160 hrs · 46,589 cycles

CORROSION IN FUEL PANEL ACCESS NBR# 1303C AND 1409C. THE FUEL ACCESS NBR 1303C AND 1409C BLEND OUT REPAIR IS NOT PERMITTED ON THE UPPER WING ACCESS DOOR (P/N 3912757) DUE TO THE REDUCED AREA OF THE CONDUCTIVE INTERFACE. THEREFORE THEY ARE OUT LIMITS AND ACCESS NBR 1303C AND 1409 WERE REPLACED PER DC-9/MD-80 SRM 51-22-2A CONDITION III. (LP0200220)

Part: ANGLE — CORRODED (BS 503-522) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

EXCESSIVE CORROSION ON LOWER ANGLE, BS 503 TO 522, RBL 60. THE ANGLE WAS REPLACED IAW SRM 51-30-5, 51-10-4, AND DWG 9930538, REV CF.

Part: FERRULE — PUNCTURED (FLOOR PANEL) · airframe 60,160 hrs · 46,589 cycles

PUNCTURED AND DAMAGED FERRULE ON FLOOR PANEL 200C. A NEW FLOOR PANEL WAS FABRICATED IAW AMM 53-20-01-201.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 60,160 hrs · 46,589 cycles

CRACKED RT CUSP WEB BTW STA Y=200-256 AT PAX CABIN. RT CUSP WEB BTW STA Y=218-236 WAS REPLACED PER SRM 51-30-02 AND 51-30-05.

Part: LONGERON — CRACKED (BS 1437) · airframe 60,160 hrs · 46,589 cycles

CRACKED LONGERON 16L, BS 1437 IN THE AFT ACCESSORY BAY. THE LONGERON WAS REPLACED IAW SRM 53-14-4, FIG 4, 51-30-2, AND 51-30-5.

Part: HINGE FITTING — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 60,166 hrs · 46,591 cycles

CORROSION ON THE LT WING FWD FLAP HINGE FITTING AND LOWER STUDS, XW 251.383. THE HINGE FITTINGS WERE REPLACED IAW AMM 57-40-01.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 60,160 hrs · 46,589 cycles

DAMAGED ON FLOOR PANELS 160D, 160E, 160F. FLOOR PANELS NBRS: 160D, 160E AND 160F WERE REPLACED AND IDENTIFIED PER MD88 AMM 53-20-01-201. (LP0196779)

Part: SEAT TRACK — CORRODED (BS 424-485) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON THE SEAT TRACK LBL 54, BS 424 AND 485. THE SEAT TRACK WAS REPAIRED SRM 53-05, FIG. 4A.

Part: SEAT TRACK — CORRODED (BS 702-704) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

AWR: CORROSION ON LT SEAT TRACK LBL 54 BETWEEN BS 702 TO 704. THE SEAT TRACK WAS REPAIRED IAW SRM 53-05, FIG 4A.

Part: CUSP WEB — CORRODED (BS 326-351) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON THE CUSP WEB BS 326 TO 351, RBL 54 TO 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 PARA 144, FIG 131 A-13.

Part: FLOOR SUPPORT — CORRODED (BS 1309-1346) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON FLOOR SUPPORT BETWEEN BS 1309 & 1346, RBL 18.0. THE FLOOR SUPPORT WAS REPLACED IAW SRM. 51-30-1.

Part: SLIDE — MALFUNCTIONED (TAILCONE) · airframe 60,160 hrs · 46,589 cycles

UNPACKAGED TAILCONE SLIDE AT AFT ACC COMPARTMENT. THE TAILCONE SLIDE WAS REPLACED IAW AMM 25-62-01.

Part: ANGLE — CRACKED (BS 1174) · airframe 60,160 hrs · 46,589 cycles

CRACKED ANGLE ON LOWER FITTING BETWEEN BEAM 1 AND LOWER EDGE BS 1174 AT AFT CARGO DOOR. THE ANGLE WAS REPLACED IAW SRM 51-30-1, AND 51-30-5.

Part: CHANNEL — CRACKED (FLOOR PANEL) · airframe 60,160 hrs · 46,589 cycles

CRACKED CHANNEL ON FLOOR PANEL 1079A. THE CHANNEL WAS REPAIRED IAW SRM 51-90-1.

Part: CUSP WEB — CORRODED (BS 732-738) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

EXCESSIVE CORROSION ON CUSP WEB, BS 732 TO 738. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-13.

Part: ANGLE — CRACKED (CARGO DOOR) · airframe 60,160 hrs · 46,589 cycles

CRACK ON INTERNAL ANGLE,LOWER DOOR C-1. DAMAGED ANGLE ON LOWER EDGE WAS REPLACED IAW SRM 51-30-1 AND 51-30-5.

Part: CUSP WEB — CORRODED (BS 772-775) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

EXCESSIVE CORROSION ON CUSP WEB, BS 772 TO 775. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-13.

Part: FLOOR SUPPORT — CORRODED (BS 168-200) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON FLOOR SUPPORT LBL 52, BETWEEN BS 168 AND 200. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-30-2 AND SRM 51-30-5.

Part: CUSP WEB — CORRODED (BS 281-283) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

EXCESSIVE CORROSION ON THE CUSP WEB, BS 281 TO 283 , RBL 54 TO 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG. 131A-13.

Part: FLOOR PANEL — PUNCTURED (NOT REPORTED) · airframe 60,160 hrs · 46,589 cycles

PUNCTURED FLOOR PANEL 1307B. THE FLOOR PANEL WAS REPAIRED IAW AMM 53-20-01-201.

Part: FLOOR SUPPORT — CORRODED (BS 160-200) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON FLOOR SUPPORT LBL 54, BS 160 AND 200. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-30-2 AND SRM 51-30-5.

Part: INTERCOSTAL — CRACKED (PAX DOOR) · airframe 60,160 hrs · 46,589 cycles

CRACKED INTERCOSTAL BTW BEAMS 4-5 AT FWD ENTRY DOOR. INTERCOSTAL WAS REPLACED IAW SRM 51-30-2.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 60,160 hrs · 46,589 cycles

CRACK ON FLOOR SUPPORT BEAM X=16L, STA 180 APPROX. FLOOR SUPPORT FROM STA Y=180 X=16L WAS REPLACED PER SRM 51-10-4.

Part: ACCESS PANEL — CRACKED (WING) · airframe 60,160 hrs · 46,589 cycles

CRACK IN HOLES ON ACCESS FUEL PANEL ACCESS NR 1361C AND 1355C. BUSHINGS ON ACCESS FUEL PANEL ACCESS NR 1361C AND 1355C WERE REPLACED PER SRM 51-22-2A.

Part: TAB — NICKED (LT ELEVATOR) · airframe 60,160 hrs · 46,589 cycles

NICK ON LT ELEVATOR ANTI FLOAT TAB OUTBD CORNER. LT ELEVATOR ANTI FLOAT TAB WAS REPAIRED IN ACCORDING SRM 55-04 PARAGRAPH 3 FIGURE 2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

EXCESSIVE CORROSION ON FLOOR SUPPORT BTW STA Y= 200 , X=7 TO X=-7 IN REF NRC 899. FLOOR SUPPORT FROM STA Y=200 X=-7 TO 7 WAS REPLACED PER SRM 51-10-4.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

EXCESSIVE CORROSION ON END OF FLOOR SUPPORT FROM STA Y= 200 ,X = -7. END OF FLOOR SUPPORT FROM STA Y=200 X=-7 WAS REPLACED PER SRM 51-10-4.

Part: DOUBLER — CRACKED (FWD PAX DOOR) · airframe 60,160 hrs · 46,589 cycles

CRACKED PLATE ON THE FWD ENTRY DOOR FWD UPPER CORNER CAVITY DOUBLER. REPLACED IAW SRM 51-30-1, 51-30-2 AND DWG 9955752, REV K.

Part: FLOOR PANEL — CRACKED · airframe 60,160 hrs · 46,589 cycles

CRACK FLOOR PANEL NR 389G. FLOOR PANEL NR 389G WAS REPAIRED PER SRM 53-01 FIG 4 SHEET.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 60,160 hrs · 46,589 cycles

CORROSION AND ELONGATED HOLES ON FLOOR SUPPORT BTW X=-44 AND X=-60 STA Y=200 AT FLOOR STRUCTURE CABIN. FLOOR SUPPORT FROM STA Y=200 X=44-60 WAS REPLACED PER SRM 51-10-4.

Part: CUSP WEB — CORRODED (BS 598-712) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON THE CUSP WEB, LBL 44 - 60 UPPER & LOWER SURFACE FROM BS 598 - 712. THE CUSP WEB WAS REPLACED IAW DWG.9930538, ITEM -9 REV CF, AND SRM 53-05, FIG 131A-24.

Part: SKIN — DAMAGED (LT WING) · airframe 60,160 hrs · 46,589 cycles

DURING AN NDT INSPECTION, A DISCREPANT AREA WAS FOUND ON LOWER SKIN BETWEEN XCW=163 TO 168 REAR SPAR AT LT WING. REPAIRED IAW ER/A 560873-14AD, REV ORIGINAL.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,160 hrs · 46,589 cycles

CORROSION ON FITTING STA=693 BTW X 60 LT AT CABIN PAX. FITTING STA=693 BTW X 60 LT AT CABIN PAX WAS REPLACED PER DWG 4911383 ITEM 1 REV "K".

Part: SKIN — DENTED (LT WING SLAT) · airframe 60,160 hrs · 46,589 cycles

DENTS ON SLAT PANEL NR 1 XIS 83, LT WING. THE DENTD WERE REPAIRED IAW SRM 57-03D, PAR 19. FIG 19, SHEET 2.

Part: SKIN — DENTED (LT ELEVATOR TAB) · airframe 60,160 hrs · 46,589 cycles

SEVERAL DENTS ALONG UPPER SKIN OF GEARED TAB AT LT ELEVATOR GEARED TAB AT LT ELEVATOR N/P 5910414-403 N/S 53421 FOR EXCESSIVE DAMAGE WAS REPLACED BY GEARED TAB AT LT ELEVATOR N/P 5910414-503 N/S 49809 PER SRM 55-04.

Part: SKIN — DENTED (RT ELEVATOR TAB) · airframe 60,160 hrs · 46,589 cycles

SEVERAL DENTS ALONG UPPER SKIN OF RT CONTROL TAB AT RT ELEVATOR. CONTROL TAB AT RT ELEVATOR N/P 5910413-512 N/S 55421 FOR EXCESSIVE DAMAGE WILL BE REPLACED PER SRM 55-04.

Part: SKIN — DENTED (LT ELEVATOR TAB) · airframe 60,160 hrs · 46,589 cycles

SEVERAL DENTS ALONG UPPER SKIN OF CONTROL TAB AT LT ELEVATOR. CONTROL TAB AT LT ELEVATOR N/P 5910413-507 N/S 49653 FOR EXCESSIVE DAMAGE WAS REPLACED BY CONTROL TAB AT LT ELEVATOR N/P 5910413 N/S DL19 PER SRM 55-04.

Part: TAB — DENTED (RT EL11EVATOR874) · airframe 60,160 hrs · 46,589 cycles

SEVERAL DENTS ALONG UPPER SKIN OF THE RT GEARED TAB ON THE RT ELEVATOR. THE TAB WAS REPLACED IAW SRM 51-50-2, PAGE 4.

Part: DUCT — BLOWN (LT A/C PACK) · airframe 60,141 hrs · 46,575 cycles

AT FL330 LOST PRESSURIZATION WITH AN ASSOCIATED FLOW LIGHT. NO AUTO 1 OR 2 PRESSURIZATION CONTROLLER FAILURES WERE OBSERVED. THE CREW FOLLOWED THE QRH PROCEDURES AND DESCENDED DOWN TO 10,000' AT WHICH TIME THE FLOW LIGHT EXTINGUISHED. DURING THE EVENT, THE PRESSURE DROP WAS GRADUAL AND THE OXYGEN MASKS DID NOT DROP. MAINTENANCE TROUBLESHOT IAW NOGO ODI 2130. FLOW LIGHT ILLUMINATED/PRESSURIZATION ISSUES AND FOUND A BLOWN LEFT PACK DISCHARGE DUCT. THE DUCT AND CLAMPS WERE REPLACED IAW AMM 21-20. CLAMPS ON THE RIGHT PACK UPSTREAM OF THE DISCHARGE DUCT WERE FOUND LOOSE AND SECURED. THE PACK CONFIDENCES CHECKS PER WC 2132-1002 AND A FUSELAGE LEAK DOWN TEST IAW AMM 21-00-00-501 WERE PERFORMED AND CHECKED OKAY. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 59,056 hrs · 45,739 cycles

ROW 25 OVERWING EXIT LIGHTS INOPERATIVE. BOTH SIDES. REPLACED THE BATTERY PACKS IAW AMM 33-53. TESTED GOOD.

Part: WEDGE — SPLIT (RT WING TE FLAP) · airframe 58,886 hrs · 45,617 cycles

DURING PREFLIGHT, FOUND THE RT INBD FLAP TRAILING EDGE WEDGE SPLIT APPROXIMATELY 2-3 INCHES LONG, 18 INCHES OTBD FROM FUSELAGE. PERFORMED TEMP REPAIR IAW SRM 51-02.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 57,476 hrs · 44,578 cycles

CORROSION ON LONGERONS AND FRAME, FWD AND AFT SIDE OF FRAME AND FROM L28R TO L28L. REMOVED CORROSION IAW SRM 53-01, FIG 1 AND REPAIRED IAW SRM 53-02, FIG 18.

Part: FRAME — CORRODED (BS 655) · corrosion level 2 · airframe 57,468 hrs · 44,574 cycles

MID CARGO BILGE AREA EDGE OF FRAME BS 655 ABOVE STRINGER 29R CORRODED. REMOVED AND REPLACED IAW DWG 5936597.

Part: TAB — DAMAGED (LEFT) · airframe 57,468 hrs · 44,574 cycles

LEFT ANTI-FLOAT TAB HAS DAMAGE ON TRAILING EDGE. REMOVED AND INSTALLED PER AMDS 2730-4590-LH STEP 20. (LP2598280)

Part: FRAME — CORRODED (TAILCONE) · airframe 57,468 hrs · 44,574 cycles

FUSELAGE TAILCONE FRAME HAS A CRACK. REMOVED, LOCATE, DRILLED AND INSTALLED A NEW FRAME IAW DRWG 9911843.

Part: ANGLE — CORRODED (BS 788) · corrosion level 2 · airframe 57,468 hrs · 44,574 cycles

MID CARGO BILGE AREA, DOME NUT BROKEN WITH EXTENSIVE EXFOLIATION ON FRAME BS 788 ABOVE LONGERON 28L VIEWED ON BACKSIDE OF FRAME. REMOVED AND REPLACED THE ANGLE PER DWG 953667.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 57,398 hrs · 44,520 cycles

FOUND OVERHEAD EMERGENCY LIGHTS 34 & 36 11-21 INOPERATIVE. REPLACED THE BATTERY PACK IAW MM 33-53. CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 57,398 hrs · 44,520 cycles

ROW 11-21 OVERHEAD EMERGENCY LIGHTS INOPERATIVE. REPLACED THE BATTERY PACK IAW AMM 33-53-00 AND REPLACED POWER SUPPLY AT ROW 12 IAW AMM 33-53-00. OPS CHECKED GOOD.

Part: CHANNEL — CRACKED (LT MLG WW) · airframe 56,215 hrs · 43,673 cycles

LT W/W FWD DOOR JAM CHANNEL CRACKED. LOCATED ENDS OF CRACK USING 10X MAGNIFICATION. STOP DRILLED BOTH ENDS OF CRACK IAW SRM 53-05D, FIG 810D. MAINTENANCE IN PROGRESS. REPLACED LT GEAR DOOR FRAME IAW LONG BEACH DWG 5930584.

Part: VANE — DAMAGED (LT WING TE FLAP) · corrosion level 2 · airframe 56,112 hrs · 43,600 cycles

NR 4 LEFT OTBD FLAP FIXED VANE HAS HOLE .7500" TO 1" LARGER AREA MAYBE DETERIATED. INSP LT OTBD FLAP, OTBD VANE AND FOUND DAMAGE IN 2 LOCATIONS BOTH WITH CORROSION AND BOTH WITH HOLES. FIRST AREA IS 18" FROM INBD END AND IS 1.25" FROM L/E. TAP TEST SHOWS AN AREA OF DELAM AT ABOUT 3" X 1.50". THE HOLE IS ABOUT .500". SECOND AREA IS 23.5" FROM INBD END AND 2.0" FROM LT TAP TEST SHOWS AN AREA OF DELAMINATION AT ABOUT 1.25" X .5". THE HOLE IS ABOUT .250" CONTACT ENGINEERING FOR POSSIBLE TEMP REPAIR. ACOMPLISHED PRI 543018-14 REV ORG. RECEIVED RI 543018-14 PERMANENT REPAIR WILL NEED TO BE ACCOMPLISHED WITHIN 100 FLIGHT HOURS FROM ARRIVAL.

Part: PIN — CRACKED (TAILCONE) · airframe 55,715 hrs · 43,322 cycles

FRAMED 1510 CRACKED AT LOWER RT ALIGNMENT PIN FOR TAILCONE. C/W EDDY CURRENT INSPECTION OF CUT-OUT IAW ERA 497316-14MA, REV ORIG, SECTION 1, STEP 4, NO ITEMS NOTED. COMPLETED THRU STEP 9, ERA 497316-14MA, REV ORIG. COMPLETED ERA 497316-14MA, REV ORIG.

Part: BULB — INOPERATIVE (EMERGENCY LIGHTS) · airframe 55,463 hrs · 43,119 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY EXIT SIGN AT ROW 25E HAS SEVERAL BULBS INOPERATIVE. MAINTENANCE REPLACED THE BULBS AS NEEDED IN THE NOTED LIGHT AND THE OPS CHECK WAS GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 55,289 hrs · 42,973 cycles

DURING PREFLIGHT, MAINTENANCE FOUND EMERGENCY LIGHTS IN OVERHEAD PANEL AFT NOT WORKING. BATTERIES WERE REPLACED IN FWD OVERHEAD CEILING. CHECKED OK.

Part: LANYARD — BROKEN (L1 DOOR SLIDE) · airframe 55,256 hrs · 42,955 cycles

L1 DOOR GIRT-BAR TO SLIDE CONTAINER BOX CONNECTING CABLE LANYARD WAS FOUND BROKEN. MAINTENANCE REPLACED BROKEN LANYARD. CKS OK.

Part: OVEN — ODOR (GALLEY) · airframe 55,018 hrs · 42,804 cycles

ELECTRICAL ODOR DURING CRUISE. CHECK LIST COMPLIED WITH, ODOR DISSIPATED AFTER GALLEY POWER TURNED OFF. IDENTIFIED OVEN AS FAULT CAUSE.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB) · airframe 54,446 hrs · 42,419 cycles

LEFT AFT BARREL NUT HOLE RETAINER TABS MISSING AND CORROSION PRESENT CLEANED CORROSION AND CHECKED LIMITS REF SRM 55-03, FIG 32, INSTALLED NEW HARDWARE REF DWG 5930603-531 (-79) VIEW AA HOLES A1, A2. COMPLIED WITH ERA 535953-14AD REV ORIGINAL.

Part: SPAR CAP — CRACKED (VERTICAL STAB) · airframe 54,437 hrs · 42,413 cycles

LT SIDE VERTICAL STAB FRONT SPAR CAP FWD FLANGE JUST ABOVE THE ZFS 52.267 SPLICE, IN THE FIRST HOLE, HAS A EDDY CURRENT CRACK INDICATION STARTING AT THE COUNTERSINK SKIN HOLE ENTRANCE. -M- COMPLIED WITH PRI 535794-14AD, REV 1. REPAIR PERFORMED IAW ER/A 535794, AD REV ORIGINAL.

Part: STRUCTURE — DAMAGED (VERTICAL STAB) · airframe 54,437 hrs · 42,413 cycles

FOUND FASTENER HOLE ON UPPER ROW COMMON TO SPLICE BAND FROM LT SIDE OF VERTICAL STABILIZER FIXED L/E TO BE OUT OF LIMITS. STA ZFS 52.267, C/W PRI 535916-14, REV 1 AND ER/A 535916-14AD, REV ORIGINAL, LP 1946704.

Part: STRUCTURE — DAMAGED (FUSELAGE) · airframe 54,437 hrs · 42,413 cycles

FOUND 2 HOLES ON LOWER FIXED L/E FOR HORSE COLLAR TO BE OVERSIZED AND OUT OF ROUND ON UPPER ROW. C/W PRI 535916-14, REV 1 AND ER/A 535916-14AD ORIGINAL.

Part: SPAR CAP — CRACKED (VERTICAL STAB) · airframe 54,437 hrs · 42,413 cycles

LT SIDE VERTICAL STABILIZER FRONT SPAR CAP FWD FLANGE JUST ABOVE THE ZFS 52.267 SPLICE, IN THE FIRST HOLE, HAS A EDDY CURRENT CRACK INDICATION STARTING AT THE COUNTERSINK SKIN HOLE ENTRANCE. REPAIRED IAW PRI 535794-14AD. LP 1943822.

Part: STRUCTURE — DAMAGED (VERTICAL STAB) · airframe 54,437 hrs · 42,413 cycles

FOUND 20TH FASTENER HOLE ON UPPER ROW COMMON TO SPLICE BAND FROM LT SIDE OF VERTICAL STABILIZER FIXED L/E TO BE OUT OF LIMITS. FS ZFS 52.267. REPAIRED THE BUSHINGS IAW ERA 535916-14.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 54,244 hrs · 42,285 cycles

DURING CHECK, MAINTENANCE FOUND THE CEILING EMERGENCY LIGHTS WERE INOPERATIVE FORWARD OF THE L2 DOOR. MAINTENANCE REPLACED THE BATTERIES AND THE OPS CHECK WAS GOOD.

Part: SKIN — DENTED (BS 712) · airframe 53,467 hrs · 41,772 cycles

FUSELAGE SKIN BS 712, STRINGERS 25-26R DENTED. REPAIRED IAW ER/A 531636-14 .

Part: SKIN — DENTED (BS 712) · airframe 56,757 hrs · 44,038 cycles

MAINTENANCE DISCOVERED A LARGE DENT NEXT TO THE C2 CARGO DOOR AT BS 712, S-26L. MAINTENANCE CUT OUT THE DENT AND REPAIRED IAW ER/A 531636-14 INSTRUCTIONS. ER/A 531636-14 INSTALLS A REPAIR FILLER AND DOUBLER, COVERING THE DAMAGED AREA AND THE NEARBY FACTORY DOUBLER. THIS LOG PAGE PROVIDES TRACKING FOR THE DTE RESTRICTION ASSOCIATED WITH ER/A 531636-14 ONLY. ASSOCIATED ER/A 00-531636 ADDED FOR AC 9016. REDEFERRED LOG TO QC, ESTABLISH MONITOR INSPECTION, 20-0553-8-9369, SN 09016, L/L SEC I DTA. ER/A 531636-14, REV A IS CURRENT. DTA RESTRICTION REMOVED, LOGPAGE TO BE TERMINATED. CLOSED LOG AND REMOVED MONITOR INSP IAW ALERT 07DEC15 AND LOG COMMENTS.

Part: BULB — INOPERATIVE (EMERGENCY LIGHT) · airframe 53,209 hrs · 41,591 cycles

DURING CHECK, MAINTENANCE FOUND THE EMERGENCY LIGHT IN THE AFT EQUIPMENT BAY WAS INOPERATIVE. MAINTENANCE REPLACED THE LENS AND REPLACED TWO BULBS AND THE LIGHTS WERE OPERATIONAL.

Part: LIGHT — INOPERATIVE (SEAT 21) · airframe 53,092 hrs · 41,502 cycles

DURING CHECK, MAINTENANCE FOUND THAT THE ROW 21 SEAT EMERGENCY LIGHT WAS INOPERATIVE. MAINTENANCE REPLACED THE LIGHT ASSEMBLY AND OPS CHECKED GOOD.

Part: APU — CONTAMINATED · airframe 52,882 hrs · 41,334 cycles

CREW REPORTED BURNING ODOR IN FLIGHT COMPARTMENT. VERY SLIGHT HAZE IN CABIN WHEN ENG ANTI ICE SELECTED ON. TURNED OFF ANTI ICE. FOUND APU INLET AREA WET WITH HYDRAULIC FLUID. REMOVED, CLEANED AND RE-INSTALLED APU INLET. PERFORMED WC 4950-2215 MINI DUCT BURNOUT. NO SMOKE AND/OR ODOR PRESENT.

Part: CSD — MALFUNCTIONED (NR 1) · airframe 52,378 hrs · 40,956 cycles

FLIGHT DIVERTED DUE TO THE NR 1 CSD INDICATING "OIL PRESSURE LOW" AND FAILURE OF THE CSD TO DISCONNECT IAW QRH. MAINTENANCE REPLACED THE NR 1 CSD, NR 1 GENERATOR, AND NR 1 CSD OIL COOLER. ALSO FLUSHED ALL LINES AND SERVICED WET SPLINE AND CSD. CSD DISCONNECT FUNCTION, LEAK CHECK, AND OPS CHECK WERE ALL GOOD.

Part: THRESHOLD — CORRODED (BS 693-750) · corrosion level 2 · airframe 52,302 hrs · 40,906 cycles

MID CARGO DOOR FRAME THRESHOLD HAS CORROSION FROM BS 693-750. REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS IAW SRM 51-10-03, VOL II, PAR 26, 53-00-01, VOL I. REMOVED BEAM LOCATED AND DRILLED NEW DOOR BEAM AND INSTALLED IAW DWG 5930481, REV AE, REMOVED TEE FITTING LOCATED AND DRILLED AND INSTALLED IAW DWG 5930481, REV: AE.

Part: SKIN — DAMAGED (BS 229-245) · airframe 52,284 hrs · 40,897 cycles

DURING BELLY SKIN REPLACEMENT IT WAS DISCOVERED THE SKIN HAS 9 EA HOLES WITH LESS THAN MINIMAL EDGE DISTANCE AT STA 229. R & R DAMAGED SKIN AT BS 229 TO BS 245-626L IAW SRM 53-04, FIG 12C AND SRM 53-03, FIG 44.

Part: SKIN — DAMAGED (BS 294-313) · airframe 52,284 hrs · 40,897 cycles

FUSELAGE SKIN DAMAGED BS 294-313 BETWEEN STRINGERS 23L-29R. REPAIRED IAW ER/A 526324-14, SECT 2.

Part: SKIN — DAMAGED (BS 300) · airframe 52,284 hrs · 40,897 cycles

FUSELAGE SKIN DAMAGE BS 300 BETWEEN L25-26L. REPAIRED IAW SRM 53-04, FIG 12C.

Part: FRAME — DAMAGED (BS 313) · airframe 52,284 hrs · 40,897 cycles

DAMAGE TO BS 313 FRAME L28L. REMOVED SECTION OF FRAME. FABRICATED SPLICES AND PLATES AND INSTALLED IAW SRM 53-03, FIG 2A.

Part: SKIN — DAMAGED (BS 313) · airframe 52,284 hrs · 40,897 cycles

DURING GROUND SERVICING, FUSELAGE SKIN DAMAGE BETWEEN STRINGERS 23L-29R. REPAIRED IAW ER/A 526324-14, SECT 2.

Part: LONGERON — DAMAGED (BS 229) · airframe 52,302 hrs · 40,906 cycles

DURING BELLY SKIN REPLACEMENT IT WAS DISCOVERED THAT BS 229 LONGERON L25L DAMAGED. REMOVED DAMAGED SECTION AND REPLACED IAW SRM 53-02.

Part: SLIDE — OUT OF TOLERANCE (TAILCONE) · airframe 52,282 hrs · 40,895 cycles

INSPECTION DISCOVERED THAT THE EMERGENCY ESCAPE SLIDE IN THE TAILCONE WAS NO LONGER IN AN ACCEPTABLE CONFIGURATION. SLIDE WAS REPLACED.

Part: LONGERON — DAMAGED (BS 300) · airframe 52,282 hrs · 40,895 cycles

LONGERON 30L, BS 300 IS DAMAGED. R & R SECTION OF LONGERON BETWEEN BS 230 - 323 IAW SRM 51-30-2 AND SRM 51-30-5 AND 53-14-2, FIG 3.

Part: LONGERON — DAMAGED (BS 297) · airframe 52,282 hrs · 40,895 cycles

LONGERON 28L IS DAMAGED BS 297. R & R SECTION OF LONGERON FROM BS 320-341 IAW SRM 51-30-2 AND 51-30-5.

Part: LONGERON — DAMAGED (BS 297) · airframe 52,282 hrs · 40,895 cycles

LONGERON 27L IS DAMAGED BS 297. R & R SECTION OF LONGERON BETWEEN BS 230-341 IAW SRM 51-30-2 AND 51-30-5.

Part: UNKNOWN — UNKNOWN · airframe 52,107 hrs · 40,768 cycles

ACFT STALLED AT ALTITUDE. PRIMARY AIRSPEED INDICATOR STAYED AT 260 KTS. STANDBY AIRSPEED WAS DECREASING. POWER WAS UP TO CRUISE. MAINTENANCE PERFORMED TEST ON PITOT AND STATIC SYS AND ON PITOT TEMPERATURE. NO PROBLEMS NOTED. MAINTENANCE ALSO INSPECTED MOISTURE TRAPS WITH NO WATER FOUND.

Part: CONTROL ARM — BINDING (TAILCONE RELEASE) · airframe 52,085 hrs · 40,751 cycles

DURING PERFORMANCE OF AMDS WC 2562-7267, TAILCONE DID NOT JETTISON. FOUND THE AFT FUSELAGE CONTROL ARM ASSY BINDING. PERFORMED ADJUSTMENT OF ARM ASSY IAW AMM 53-53-02-201. TAILCONE JETTISONED PROPERLY IAW AMDS WC 2562-7267.

Part: WIRE — DAMAGED (EMERGENCY LIGHT) · airframe 51,599 hrs · 40,426 cycles

EMERGENCY LIGHTS INOPERATIVE, FIRST CLASS AND AFT FROM ROW 30. REPAIRED WIRES L982T14 AND L982U14 FOUND SHORTED TO ACFT STRUCTURE APPROXIMATELY 2FT OTBD OF TAILCONE EJECT HANDLE IDENTIFIER. REPAIRED WIRING IAW AMM 20-50. EMERGENCY LIGHTS CKS OK.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 51,412 hrs · 40,308 cycles

DURING SERVICE CHECK, FOUND EMERGENCY LIGHTING INOPERATIVE FROM SEAT 32 AFT. REPLACED BATTERY PACK AND POWER SUPPLY ABOVE SEAT 35E, CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 51,229 hrs · 40,180 cycles

DURING LINE CHECK, NOTED THE LAST FIVE SEAT ROWS AND AFT STAIRWELL EMERGENCY LIGHTS INOPERATIVE. REPLACED BATTERY PACK AT AFT POSITION AND REPLACED LIGHT BASE C2-873 SYS CHECKED GOOD IAW AMM 33-53.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 50,955 hrs · 39,992 cycles

DURING LINE CHECK, EMERGENCY LIGHTS WOULD NOT ILLUMINATE WHEN TESTED. BATTERY PACK REPLACED AND OPERATION THEN CHECKED NORMAL.

Part: FUSE — BLOWN (EMERGENCY LIGHTS) · airframe 50,894 hrs · 39,953 cycles

DURING LINE CHECK, EMERGENCY LIGHTS FROM ROW 32-35 INOPERATIVE. REPLACED FUSE AT B5-212 BATTERY PACK PER WDM 33-51 AND OPS CHECKED NORMAL.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 50,757 hrs · 39,859 cycles

DURING LINE CHECK, THE EMERGENCY LIGHTS FROM ROWS 32-36 AND L2 DOOR FOUND INOPERATIVE. REPLACED BATTEY PACK IAW AMM 33-51 AND OPS CHECKED NORMAL.

Part: FUSE — BLOWN (EMERGENCY LIGHTS) · airframe 50,739 hrs · 39,849 cycles

DURING LINE CHECK, SEAT MOUNTED EMERGENCY LIGHTS WERE INOPERATIVE FROM ROW 32 AFT. REPLACED BLOWN FUSE ON POWER SUPPLY B5212 AND OPS THEN CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 50,633 hrs · 39,771 cycles

WHILE CHECKING EMERGENCY LIGHTS DURING SERVICE CHECK, FOUND OVERHEAD EMERGENCY LIGHTS OUT AT ROWS 12-14. REPLACED BATTERIES FOR EMERGENCY LIGHTS AT ROWS 12-14. OPS CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 50,382 hrs · 39,593 cycles

DURING LINE CHECK, THE EMERGENCY LIGHTS AT ROWS 25 -33 WERE FOUND TO BE INOPERATIVE. BATTERIES REPLACED AND OPS CHECKED NORMAL.

Part: LENS — MISSING (EMERGENCY LIGHT) · airframe 49,996 hrs · 39,304 cycles

FA REPORTED AN EMERGENCY FLOOR LIGHT LENS WAS MISSING. MX INSPECTED THE FLOOR LIGHTING SYS AND REPLACED THE MISSING LENS.

Part: CONNECTOR — UNSECURE (EMERGENCY LIGHT) · airframe 49,635 hrs · 39,044 cycles

DURING SERVICE CHECK, SEAT MOUNTED EMERGENCY PATH LIGHT AT ROW 33 INOPERATIVE. SIDEWALL CONNECTION WAS FOUND LOOSE AND WAS RECONNECTED SECURELY AND THE OPERATION OF THE SYS CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 49,486 hrs · 38,933 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT ROWS 22B, 24BD, AND 25B IN THE CABIN WERE INOPERATIVE. MX REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: UNKNOWN — ODOR (CABIN) · airframe 47,764 hrs · 37,699 cycles

CREW REPORTED A STRONG ELECTRICAL BURNING ODOR ON TAKEOFF. PERFORMED A CABIN SMOKE/ODOR INSPECTION AND A DUCT BURNOUT WITH NO DEFECTS FOUND. REMOVED AND REPLACED COALESCER BAGS AS PRECAUTION. NO LEAKS NOTED.

Part: LIGHT — INOPERATIVE (COCKPIT) · airframe 46,573 hrs · 36,901 cycles

DURING SERVICE CHECK MAINTENANCE FOUND THE FLIGHT DECK EMERGENCY LIGHTS TO BE INOPERATIVE. RELAMPED AND OPERATION CHECKS GOOD.

Part: BATTERY — DISCHARGED (CABIN) · airframe 46,573 hrs · 36,901 cycles

DURING SERVICE CHECK MAINTENANCE DISCOVERED THAT THE OVERWING EMERGENCY LIGHTS WOULD NOT TURN OFF. REPLACED RACK AND BATTERY PER AMM AND OPERATION CHECKS GOOD.

Part: WIRE HARNESS — DEFECTIVE (CABIN) · airframe 45,515 hrs · 36,185 cycles

DURING LINE CHECK, MAINTENANCE FOUND EMERGENCY PATHWAY LIGHT AT ROW 20DE INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE SEAT HARNESS PER MAINTENANCE MANUAL. OPERATION CHECKS GOOD.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 45,395 hrs · 36,094 cycles

FLIGHT CREW FOUND EXTERIOR EMERGENCY LIGHT INOPERATIVE. FLIGHT CREW PLACARD WAS INSTALLED PER MEL 33-00-20. MAINTENANCE REPLACED B5-49 OVERWING BATTERY PACK AND BATTERY PER WDM AND MM. MCO AND PLACARD WERE REMOVED. ATL/ 334789 (2011-D1162).

Part: MOUNT — CRACKED (FUSELAGE) · airframe 45,321 hrs · 36,033 cycles

CRACK RT CABIN WINDOW MOUNT PLATE STA 1117. INSTALLED REPAIR DOUBLER AND SHIM PER MD80 SRM 53-05 PG 851 FIG 122.

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 45,321 hrs · 36,033 cycles

PER EA 09-470871-12 OPN 0801 STEP 3. SUBMIT SDR VERTICAL STAB LEADING EDGE SKIN REPAIR WAS ACCOMPLISHED PER THE REF EA.

Part: SKIN — DAMAGED (ELEVATOR) · airframe 45,321 hrs · 36,033 cycles

WAVINESS ON LT ELEVATOR TRAILING EDGE UPPER AND LOWER SKIN BTW STA XE=114 AND XE=123. REPAIRED PER ERA 494580-14 REV ORG.

Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 45,321 hrs · 36,033 cycles

DAMAGE ABOUT 3FT AFT OF L1 DOOR ON EXISTING REPAIRS. REPAIRED PER SRM 53-04D.

Part: SKIN — CRACKED (ELEVATOR) · airframe 45,321 hrs · 36,033 cycles

CRACKED LOWER SKIN AT STA XE=54 AND BENT LOWER SKIN BTW STA XE=58 ON LT ELEVATOR. REPAIRED PER ERA 494580-14 REV ORG.

Part: REPAIR — DENTED (FUSELAGE) · airframe 45,321 hrs · 36,033 cycles

REPORTS OF DENT ON REPAIR 2 FEET AFT OF L1 DOOR 8 INCHES ABOVE FLOOR LEVEL. REPAIRED PER SRM 53-04D.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 45,321 hrs · 36,033 cycles

DURING HMV REWORK WAS DONE ON PREVIOUS REPAIR DOUBLER AT FUSELAGE SKIN STA Y=218-228 LONGS 16-17LT. FUSELAGE SKIN WAS REPAIRED IAW SRM 53-04D FIG 12B.

Part: SKIN — CORRODED (FUSELAGE) · airframe 45,321 hrs · 36,033 cycles

DURING HMV CORROSION WAS FOUND ON INNER FUSELAGE SKIN STA Y=1060-1070 BETWEEN LONGERON 27-29L AT AFT CARGO COMPARTMENT. FUSELAGE SKIN WAS REPAIRED IAW SRM 53-04D FIG 53.

Part: SKIN — CORRODED (FUSELAGE) · airframe 45,321 hrs · 36,033 cycles

DURING HMV CORROSION WAS FOUND ON FUSELAGE SKIN AT SETTLEMENT AREA OF FILLET PANEL RUBSTRIPS STA Y=1081-1090 AND 1099-1102 BTW LONGERON 30 AND 28RT ALSO STA Y=1110-1127 BTW LONGERON 28 AND 26RT. FUSELAGE SKIN WAS REPAIRED IAW SRM 53-04D FIG 53.

Part: TUBE — WORN (FUSELAGE) · airframe 45,321 hrs · 36,033 cycles

DURING HMV A WORN FUSELAGE TUBE OF T/E TAIL CONE CONTROL CABLES RELEASE SYSTEM WAS FOUND AT STA Y=1510 CANT 5 AND 7 O'CLOCK POSITION. FUSELAGE TUBE WAS REPLACED IAW MM 20-30-01-201.

Part: SKIN — DAMAGED (ELEVATOR TAB) · airframe 45,321 hrs · 36,033 cycles

AT HMV ITEM TRANSFERED FROM OMI C/N C06031826 REPAIR TO LT ELEVATOR GEARED TAB UPPER SURFACE FOR DENTS AND DELAM. GEAR TAB WAS REPAIRED IAW SRM 55-04 PARA 3A AND SRM 55-04 PARA 2A.

Part: SKIN — DAMAGED (RUDDER) · airframe 45,321 hrs · 36,033 cycles

DURING HMV DAMAGE WAS FOUND ON METALLIZED COAT OF RT SKIN OF RUDDER. RUDDER WAS REPAIRED IAW SRM 51-70-1AD.

Part: WEB — CORRODED (FUSELAGE) · airframe 45,321 hrs · 36,033 cycles

CORROSION ON WEB AND PREVIOUS REPAIR OF WEB STA Y=1158-1168 BETWEEN X=-54 FLOOR STR. NEW WEB INSTALLED IAW DC9/MD80 SRM 53-24-0D FIG 802D.

Part: PAN — CRACKED (CARGO DOOR) · airframe 45,321 hrs · 36,033 cycles

HIDDEN DAMAGE CRACKS ON C1 DOOR PAN FWD EDGE BELOW DOOR STOP NR 4. REPAIR DOUBLER WAS INSTALLED IAW MD80 SRM 52-05D FIG 5 SHEET 1&3.

Part: SKIN — CORRODED (FUSELAGE) · airframe 45,321 hrs · 36,033 cycles

CORROSION ON FUSELAGE SKIN AT SETTLEMENT AREA OF FILLET PANELS RUBSTRIPS STA Y=1090. REF NR T0215490. REPAIR ACCOMPLISHED IAW SRM 53-04 FIG 53.

Part: SKIN — DAMAGED (VERTICAL STAB) · airframe 45,321 hrs · 36,033 cycles

EA 09-470871 REV D ME04. ELONGATED HOLES ON VERTICAL STABILIZER FIXED LEADING EDGE STA ZFS=52.267. BUSHING REPAIRS INSTALLED IAW MD88 SG09550004 REV A.

Part: DOOR FRAME — WORN (FUSELAGE) · airframe 45,321 hrs · 36,033 cycles

WEAR ON FWD UPPER CORNER OF FWD CARGO DOOR JAMB STA Y=370. REPAIRED IAW ERA 494595-14 REV ORIG.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 45,321 hrs · 36,033 cycles

CORROSION ON RT CUSP WEB LOWER SURFACE STA Y=1174 TO 1212. NEW CUSP WEB WAS INSTALLED IAW DC9/MD80 SRM 53-24-00 FIG 802D.

Part: WINDOW FRAME — DAMAGED (FUSELAGE) · airframe 45,321 hrs · 36,033 cycles

LIGHTNING STRIKE ON LT WINDOW FRAME LOWER FORWARD CORNER STA Y=788-807 AT FUSE SKIN. DOUBLER REPAIR INSTALLED IAW 494589-14 REV ORIG.

Part: CHANNEL — CRACKED (ELEVATOR) · airframe 45,200 hrs · 35,953 cycles

CRACKS ON LT ELEVATOR TRAILING EDGE REAR J CHANNEL UPPER AND LOWER CAPS STA XE=119. REPAIRED PER ERA 494580-14 REV ORG.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 45,181 hrs · 35,938 cycles

DURING LINE CHECK, MAINTENANCE FOUND AFT OVERWING EMERGENCY EXIT SIGNS INOPERATIVE. MAINTENANCE REMOVED AND REPLACED 2 EACH BATTERY PACKS AT B5-105. OPERATION CHECKS GOOD.

Part: WIRE — DAMAGED (CABIN) · airframe 45,181 hrs · 35,938 cycles

DURING LINE CHECK, MAINTENANCE FOUND SEAT 31D EMERGENCY LIGHT INOPERATIVE. MAINTENANCE REPAIRED WIRING AT CONNECTOR. OPERATION CHECKS GOOD.

Part: THRESHOLD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,488 hrs · 34,850 cycles

C-2 THRESHOLD CORRODED 25 - 50 PERCENT OF THICKNESS. REMOVED REPAIR BY SRM 53-05 FIG 123. (DLM88102965)

Part: THRESHOLD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,488 hrs · 34,850 cycles

CENTER CARGO THRESHOLD Z-ANGLE CORRODED REPAIRED PER SRM 53-05-FIG 123 (DLM88102970).

Part: FITTING — CORRODED (DOOR FRAME) · corrosion level 2 · airframe 43,488 hrs · 34,850 cycles

AFT CARGO DOORWAY AFT FRAME LOWER CORNER FITTING CORRODED. REPLACED FITTING (DLM88102969).

Part: SLIDE — LOOSE (L1 DOOR) · airframe 43,378 hrs · 34,771 cycles

CREW WROTE UP L1 DOOR SLIDE UNPINNED. MX REPLACED L1 DOOR SLIDE IAW THE MM.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 43,324 hrs · 34,735 cycles

LIGHT WAS INOPERATIVE, REPLACED LIGHT POWER SUPPLY.

Part: SOCKET — FAILED (EMERGENCY LIGHT) · airframe 43,324 hrs · 34,734 cycles

DURING LINE CHECK, MX FOUND EMERGENCY CEILING LIGHTS AT ROW 23-25 INOPERATIVE. MX REPLACED POWER SUPPLY AND BAD LIGHT SOCKET AT ROW 23. OPS CHECK OF LIGHTS NOW CHECKS GOOD.

Part: SKIN — DENTED (BS 351-370) · airframe 41,549 hrs · 33,476 cycles

GROUND DAMAGE FROM ACFT TUG STA 351 TO 370 LONG 23L TO 24L. CUT OUT DAMAGE AND INSTALLED DOUBLER.

Part: BATTERY PACK — WEAK (EMERGENCY LIGHT) · airframe 39,151 hrs · 31,848 cycles

FOUND OVERWING EMERGENCY LIGHT BATTERY PACK WEAK. REPLACED BATTERY PACK.

Part: SLIDE — LOW PRESSURE (R1 DOOR) · airframe 34,806 hrs · 26,622 cycles

EMERGENCY SLIDE PRESSURE BELOW LIMITS AT R-1 DOOR. REPLACED SLIDE.

Part: STRUT — WARNING LIGHT (NLG) · airframe 34,718 hrs · 26,501 cycles

AFTER RAISING GEAR HANDLE ON TAKEOFF RED NOSE GEAR LIGHT REMAINED ILLUMINATED ALONG WITH LOUD AIR NOISE. DURING QRH PROCEDURES GEAR CAME DOWN SUCCESSFULLY BUT RED NOSE LIGHT REMAINED ON DURING SUBSEQUENT RETRACTION. PERFORMED OPN 50006 NOSE LANDING GEAR STRUT TROUBLESHOOTING ACJIC. SERVICED STRUT REF AMM. JACKED AND SWUNG NOSE LANDING GEAR REF AMM. NO DISCREPANCIES NOTED. ALL INDICATIONS NORMAL.

Part: WIRE — CHAFED (E AND E COMPRT) · airframe 26,961 hrs · 20,792 cycles

CLIMBING THROUGH 14000 FT LOST PRESSURIZATION. FOLLOWING CHECK LIST FOUND BREAKERS U-22 AND W0-22 POPPED. DECENDED TO 10000 FT AND RETURNED TO DFW. FOUND WIRE CHAFING AT PLUG R5-390 REPAIRED SAME

Part: VALVE — MALFUNCTIONED (NR 2 ENGINE) · airframe 26,686 hrs · 20,594 cycles

IN CRUISE AT FL330, THE RT START VALVE OPEN LIGHT CAME ON. RAN CHECKLIST, WITH RIGHT ENGINE. AT IDLE THE OIL TEMP ROSE TO 136. AFTER APPROX. 1 MIN THE START VALVE LGHT WENT OFF. WITH THE POWER BACK UP THE LIGHT CAME BACK ON AGAIN. LT ENGINE AT IDLE FOR REMAINDER OF FLIGHT. CHECKED AND RESERVICED STARTER. NO METAL FOUND. REPLACED START VALVE PRECAUTIONARY. SHOOK START VALVE HARNESS AT ENGINE. CHECKS OK. FOUND RT SIDE ENGINE A/I DUCT RUPTURED. REPLACED SAME.

Part: WIRE — BROKEN (FIRST CLASS) · airframe 22,951 hrs · 17,881 cycles

FIRST CLASS WALL MOUNTED RED EMER. LIGHT INOP. CORR:REPAIRED 2 EA BROKEN WIRES APPROX. 3.5 FEET FROM LITE ASSY.

Part: COALESCER BAG — CONTAMINATED (AFT) · airframe 20,815 hrs · 16,349 cycles

UNUSUAL SMELL IN CABIN ON TAKEOFF. SMELL WENT AWAY, THEN CAME BACK AT 27000. DIVERTED TO IAH. FOUND PLASTIC BAG IN INLET NR 2 ENG. PERFORMED DUCT BURNOUT PER M/M. REPLACED COALESCER BAGS, OPS CKS GOOD.

Part: SKIN — DENTED (BS 229 - 237)

THE FUSELAGE SKIN WAS DENTED BETWEEN FS 229 AND 237 BETWEEN STRINGERS 18L AND 19L. THE DAMAGE WAS REPAIRED PER ERA 333663-14 AT HMV.

Part: HYD LINE — LEAK (LT TR CONTL VLV)

LT HYD PRESS LOW LIGHT AFTER SLATS EXTENDED. BOTH LT AND RT ENG PUMPS AND AUX AND XFER PUMPS ON. LT PRESS 0 QTY 19 QTS. FOLLOWED POM AND LANDED. FOUND LT T/REV CONTROL VLV HYD PRESS SUPPLY LINE LEAKING. REPLACED LINE, LEAK CK GOOD. RAN ENGS CYCLED ALL FLT CONTROLS AND T/REV CKS GOOD.

Part: CONTROL VALVE — FAILED (NLG STEERING)

NOSE WHEEL STEERING WOULD NOT RESPOND TO STEERING YOKE INPUTS DURING TAXI, AND EVENTUALLY, LOCK IN FULL LEFT TURN. REPLACED STEERING CONTROL VALVE, OPERATION NORMAL.

Part: LAMP — FAILED (AFT GALLEY)

ON APPROACH INTO ATL, F/A REPORTED STRONG ELEC SMELL IN THE AREA OF AFT GALLEY. FOUND FLUORESCENT LIGHT AT 31E SIDEWALL MELTED AT 1 SOCKET AND BULB PIN. REMOVED LAMP. FWD TO MCO. REPLACED LIGHT ASSEMBLY.

Part: RIB — CRACKED (KEEL BEAM)

DURING B-2 LETTER CHECK, FOUND MLG W/W KEEL BEAM CROSSOVER RIB CRACKED. REPAIRED PER MM FIG 101.

Part: DOOR FRAME — GOUGED (CARGO DOOR)

DURING LETTER CHECK, FWD CARGO DOOR PAN WAS FOUND DAMAGED AT HOLD OPEN AFT SIDE. REPAIRED PER SRM 52-05 FIG 27.

Part: DOOR PAN — GOUGED (CARGO DOOR)

DURING LETTER CHECK, CENTER CARGO DOOR PAN WAS FOUND DAMAGED AT HOLD OPEN FORWARD SIDE, REPAIRED PER SRM 52-05 FIG 27.