N908DE

Part: UNKNOWN — MALFUNCTIONED (EMERGENCY LIGHTS) · airframe 66,801 hrs · 52,393 cycles

EMERGENCY FLOOR LIGHTING DAMAGED OR INOPERATIVE. EMERGENCY FLOOR LIGHTING DAMAGED OR INOP. TRACK LIGHTING GOES ON & OFF. CHECKED OPERATION OF EMERGENCY LIGHTS - UNABLE TO DUPLICATE PROBLEM - SYSTEM OP'S NORMAL REF AMM 33-53. (LP1267573)

Part: WIRE — PULLED (CASBIN) · airframe 66,744 hrs · 52,339 cycles

FA REPORTS DURING TAKEOFF EMERGENCY LIGHTS WERE FLASHING. COCKPIT SW. IN ARM FA SW. OFF. FA LATER REPORTED EMERGENCY LIGHTS ON BUT VERY DIM. FOUND WIRES PULLED OUT OF CONNECTOR AT SEAT 26E. REPLACED SEAT EMERGENCY LIGHT EXTENSION HARNESS. ALL CKS GOOD PER WDM 33-51. EMER LIGHTS ALL CK GOOD. (LP4303558)

Part: LIGHT — DAMAGED (TAXI LIGHT) · airframe 66,613 hrs · 52,218 cycles

RT TAXI LIGHT MISSING. FOUND BLUE RING TERMINAL FOR RT TAXI NOSE LIGHT DAMAGED. REMOVED AND REPLACED IAW SWPM CH.20. REPLACED MISSING RT NOSE LIGHT PER MD88 AMM 33-41.

Part: SMOKE DETECTOR — FAULTY (LAVATORY) · airframe 66,323 hrs · 51,967 cycles

FIRST CLASS LAV SMOKE DETECTOR BEEPING. R/R FWD LAV SMOKE DETECTOR PER MD88 AMM 23-16. (LP1144630)

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 66,286 hrs · 51,934 cycles

BOTH FWD OVERWING EMERGENCY LIGHTS INOPERATIVE. REMOVED AND REPLACED THE BATTERIES AT POWER SUPPLY B5-103. PREFORMED OPS CHECK IAW AMM 33-53. CHECKED OK. OK FOR SERVICE.

Part: SMOKE DETECTOR — MALFUNCTIONED (AFT LAVATORY) · airframe 66,163 hrs · 51,819 cycles

AIRCRAFT LEFT AFT LAV SMOKE DETECTOR IS CHIRPING. REMOVED & REPLACED AFT LEFT LAV SMOKE DETECTOR. OPS CHK GOOD. (LP1102304)

Part: TERMINAL — OUT OF POSITION (CABIN) · airframe 66,128 hrs · 51,785 cycles

FA REPORTS THAT EMERGENCY LIGHTS FLICKERS ON/OFF AT HALF BRIGHTNESS AT 3-4 MINUTE INTERVALS IN FLIGHT. FOUND OVERHEAD EMERGENCY LIGHT SWITCH TERMINAL TOUCH ADJACENT STRUCTURE. REPOSITION TERMINAL. PER WDM 33-51. REF SWPM CH 20. CKS GOOD. (LP5564892)

Part: ACCESS PANEL — MISSING (NR 1 COWLING) · airframe 66,078 hrs · 51,741 cycles

FOUND ON ARRIVAL #1 ENG UPPER COWLING MISSING ACCESS PANEL. I/B SIDE JUST AFT OF NOSE COWL. INSTALLED #1 ENG INBD PANEL. (LP5564856)

Part: ENGINE — FAILED (LEFT) · airframe 65,944 hrs · 51,617 cycles

ON SHORT FINAL HEARD A LOUD BANG FOLLOWED BY NOTICEABLE YAW MOMENT TO THE LEFT. LEFT ENGINE INSTRUMENTS ROLLED BACK TO 1.02 EPR 20 PERCENT N1 EGT 525, N2 48 PERCENT WITH THROTTLE @ APROX 1.3 ENGINE UNRESPONSIVE TO THROTTLE MOVEMENT ON GROUND. REMOVED AND REPLACED #1 ENGINE ON LOG # 1046678 OPS CKS GOOD. (LP5526662)

Part: OVEN — MALFUNCTIONED (GALLEY) · airframe 65,728 hrs · 51,424 cycles

SHIP 9008 - ATB - RETURNED TO ATL DUE TO SMOKE DETECTOR IN FORWARD LAVATORY ACTIVATED ALONG WITH STRONG SMELL ON TAKE-OFF AT 300FT. CORRECTIVE ACTION: WHILE WORKING NO GO ODI WORK CARD 2120-2367 FOUND OVEN PRODUCING ODOR DESCRIBED ON SMOKE AND FUMES QUESTIONNAIRE, REMOVED AND REPLACED PER AMM 2534 OPS CHKS GOOD. C/B J-7 POPPED C/W ON LOG 4883541 COMPLETED NO GO ODI ATA 2172 AND CONFERENCE CALL A/C OK FOR SERVICE. MAINTENANCE IS IN PROGRESS.

Part: SLIDE — DAMAGED (L1 DOOR) · airframe 65,399 hrs · 51,138 cycles

1L DOOR SLIDE LACING PINS UNDONE. REMOVE AND INSTALL L1 SLIDE PER WC 2561-4964 SLIDE, PASSENGE OFF 09-2561-9-0011 01919 ON 97-2561-9-0003 02652. (LP4752842)

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 64,790 hrs · 50,617 cycles

CENTER AISLE FLOOR PANEL EXCESSIVE SPONGY AT ROW 24 WITH EDGE COVER FRACTURED. FOUND HARDWARE LOOSE RT SIDE FILLER PANEL. RESECURED. REPAIRED FILLER PANEL PER SRM 53-22. (LP5159970)

Part: SKIN — CRACKED (VERTICAL STAB) · airframe 64,473 hrs · 50,350 cycles

WHILE IN C CHECK, ACCOMPLISHING REPETITIVE INSPECTIONS PER AD 2011-15-01 AND SB MD8880-55A067, MTC FOUND A CRACK COMMON TO A HOLE COMMON TO THE DORSAL SKIN, BELOW THE SKIN SPLICE AND IN THE INTERNAL OEM DOUBLER( P/N 9911960-3)ONLY, LOCATED APPROXIMATELY 15 FASTENERS FROM THE SIDE SKIN. COMPLIED WITH ERA 493777-14 REV A.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 64,472 hrs · 50,349 cycles

AFT LAVATORY SERVICE PANEL LOWER FUSELAGE SKIN WAS CORRODED. COMPLIED WITH PRI 570970-14, REV O.

Part: TORSION BAR — CORRODED (LT WING SPOILER) · airframe 64,472 hrs · 50,349 cycles

LEFT WING, CENTER SPOILER TORSION BAR CORRODED. REPLACED THE TORSION BAR IAW AMM 27-61-06.

Part: TORSION BAR — CORRODED (RT WING SPOILER) · airframe 64,472 hrs · 50,349 cycles

RT WING, MID SPOILER TORSION BAR CORRODED. REPLACED THE TORSION BAR IAW AMM 27-61-06.

Part: TORSION BAR — CORRODED (LT WING SPOILER) · airframe 64,472 hrs · 50,349 cycles

LEFT WING OTBD FLIGHT SPOILER TORSION BAR WAS CORRODED. REPLACED THE TORSION BAR IAW AMM 27-61-06.

Part: SKIN — CORRODED (BS 1307-1322) · corrosion level 2 · airframe 64,472 hrs · 50,349 cycles

CORROSION LOCATED AT THE AFT LAV SERVICE PANEL CUTOUT, BS 1307 - 1322, LONGERON 21L AND 22L.

Part: LINKAGE — OBSTRUCTED (THROTTLE SYS) · airframe 64,078 hrs · 50,018 cycles

RT THROTTLE IS JAMMED AND STUCK AT IDLE POSITION. T/S REF AMM 76-11 THROTTLE OPERATION NML AFTER CARGO COMP 3 BAGS REMOVED FROM CEILING AREA INSP LINKAGE NO DISCREPANCIES NOTED NO 30 DAY HISTORY.

Part: BATTERY — DISCHARGED (CABIN) · airframe 63,724 hrs · 49,734 cycles

EMERGENCY LIGHT INOP ON CEILING PANELS ON ROW 21-26. FOUND BATTERY BAD IN BATTERY PACK IN BAG BIN 24E,D. REPLACED BATTERIES. LIGHTS WORK GOOD.

Part: ENGINE — POWER LOSS (NR 1) · airframe 63,566 hrs · 49,603 cycles

CLIMBING THRU FL230 A LOUD BANG OCCURED AND A DROP IN POWER ON THE LEFT ENGINE WAS OBSERVED. RAN QRH 7.6 CONTACTED OCC AND MCC. RAN QRH 7.45 AND ELECTED TO LEAVE ENGINE RUNNING AT IDLE DUE TO NORMAL OIL PRESSURE AND LACK OF VIBRATION OR FURTHER ABNORMAL INDICATIONS. LANDED IN ATL WITH LEFT ENGINE AT IDLE POWER. REMOVED AND REPLACED THE NR 1 ENGINE.

Part: SUPPORT ANGLE — CRACKED (NR 1 NACELLE) · airframe 63,566 hrs · 49,603 cycles

NR 1 ENGINE NOSE COWL LOWER AREA AFT VERTICLE SUPPORT ANGLE CRACKED AT THE 5:30 POSITION. REMOVED AND REPLACED IAW AMM 71-10.

Part: SEAT — OUT OF ADJUST (CABIN) · airframe 62,891 hrs · 49,063 cycles

SEAT BACK LOOSE IMPEDES EXIT ROW BEHIND. ADJUSTED SEAT BACK FASTENERS IAW AMM 25-21, ACFT OK FOR SERVICE.

Part: WIRE HARNESS — DEFECTIVE (CABIN) · airframe 62,045 hrs · 48,389 cycles

DURING SERVICE CHECK FOUND EMERGENCY EXIT ROW 25DE SEAT PATH LIGHTING INOP. REPLACED HARNESS FROM WALL TO LIGHTS. OPS CHECK GOOD REF MD88 AMM 33-53. (LP3520720)

Part: SKIN — CRACKED · airframe 61,002 hrs · 47,536 cycles

DURING A WALK AROUND, FOUND CRACKING IN SKIN IN 48 SECTION LOWER RIGHT SIDE UNPRESSURIZED AREA ABOVE ACCUM ACCESS DOOR. STOP DRILLED THE CRACK. FABRICATED A DOUBLER. TREATED, INSTALLED, AND PAINTED IAW SRM 53-01, PAGE 12, FIG 2, SHEET 3.

Part: CABLE — FRAYED (TAILCONE) · airframe 60,792 hrs · 47,371 cycles

TAILCONE CABLE FRAYED. REPLACED THE CABLE IAW AMM 53-53-00.

Part: PIN — MISSING (SLIDE) · airframe 59,371 hrs · 46,315 cycles

MISSING LOCK PIN ON L1 AND L2 DOOR SLIDE. PINS INSTALLED IAW AMM 25-62-00.

Part: CABLE — DAMAGED (HYD PUMP) · airframe 59,371 hrs · 46,315 cycles

LOOSE LACING ON ELECTRICAL CABLE AT AUXILIARY HYDRAULIC PUMP AT RT MLG WW. LACING INSTALLED IAW ER/A 467688-14MA AD.

Part: PIN — MISINSTALLED (SLIDE) · airframe 59,371 hrs · 46,315 cycles

DURING OK TO INSTALL FWD SERVICE DOOR SLIDE, LOWER LOCK PIN WAS FOUNDED IMPROPERLY INSTALLED. FWD SERVICE DOOR SLIDE WAS REMOVED AND INSTALLED IAW AMM 25-62-00.

Part: SKIN — CRACKED (BS 1418) · airframe 59,371 hrs · 46,315 cycles

A CRACK WAS FOUND, 0.125 INCH IN LENGTH ON FUSELAGE SKIN BETWEEN BS 1418, LONGERON 2-3R. REPAIRED IAW ER/A 549225-14AD REV. ORIGINAL AND ETI-88-16-282.

Part: FRAME — CRACKED (BS 1510) · airframe 59,371 hrs · 46,315 cycles

CRACKED FRAME BS 1510. THE FRAME WAS REPLACED IAW 51-30-2 AND 51-30-5 AND DWG 9911843 REV. AC.

Part: SKIN — CORRODED (RT WING) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON RT WING LOWER SKIN XRS 115. FAIRING WAS REMOVED, AREA WAS BLENDED, MEASURE (UT) NDT SPM 04-00-07 PAR 5 FIGURE 3 SHEET 1 & 2 WAS ACCOMPLISHED WITH ORIGINAL .340" MINIMUM REMAINING .333" AND FOUND WITHIN LIMITS, FLAP PENNING WAS PERFORMED, TREATED AND PAINTED IAW SRM 57- 03D FIGURE 30 SHEET 1, PS 900-4 05 AND SRM 51-30-1.

Part: SKIN — DAMAGED (BS 170) · airframe 59,371 hrs · 46,315 cycles

LIGHTNING STRIKE ON OUTER FUSELAGE SKIN BS 170 BETWEEN LONGERONS 28 - 29L. REPAIRED IAW ETI 88-16-228 AND ER/A 547886-14 REV ORIGINAL.

Part: BEAM — CRACKED (ENTRY DOOR) · airframe 59,371 hrs · 46,315 cycles

CRACKED BEAM NR 1 ON FWD ENTRY DOOR. PASSENGER FORWARD ENTRY DOOR WAS REMOVED AND INSTALLED IAW AMM 52-11-00 401. REPAIR BEAM NR 1 IAW SRM 52-05, FIG 98, SHEET 3.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON FRAME STA Y=1380, BETWEEN LONGERONS 29L-27R AT AFT ACCESSORY COMPARTMENT. FRAME WAS R & R IAW DWG 9912246-115, SRM 51-30-2, SRM 51-30-5 AND ER/A 547884-14, REV ORIGINAL.

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 59,371 hrs · 46,315 cycles

.405 INCH CRACK ON HORIZONTAL STABILIZER SKIN UPPER PANEL RT SIDE NEAR TO REAR SPAR PLANE BETWEEN XH=7.234 TO XH= 13.486. THE SKIN WAS REPLACED AND REPAIRED PER DWG SR09550028 REV.D AND SRM 51-30-2, SRM 51-30-5, SRM 51-30-9, SRM 51-10-3 PAR 14.21.

Part: FRAME — CRACKED (BS 1437) · airframe 59,371 hrs · 46,315 cycles

CRACKED LOWER CAP ON FRAME BS 1437, LONGERON 2R. THE FRAME WAS REPAIRED IAW SRM 53-01 FIG. 2 & DWG 9953016 REV. AT.

Part: BRACKET — CRACKED (HORIZONTAL STAB) · airframe 59,371 hrs · 46,315 cycles

CRACKED RT HORIZONTAL STAB SIDE ROLLER BRACKET. THE ROLLER BRACKET WAS REPLACED AND ADJUSTED IAW AMM 55-10-00.

Part: LONGERON — CRACKED (BS 1437) · airframe 59,371 hrs · 46,315 cycles

CRACKED LONGERON 3L BS 1437. LONGERON REPAIRED IAW SRM 53-02 FIG. 18.

Part: DOUBLER — CORRODED (BS 1205-1234) · airframe 59,371 hrs · 46,315 cycles

CORROSION ON INNER PRODUCTION DOUBLER BETWEEN BS 1222 - 1234 AND BS 1205 - 1216, LONGERONS 25 - 26L. THE DOUBLER WAS REPLACED IAW SRM 53-34-0 FIG 3 AND 51-10-1 FIG G.36 (SHEET 6).

Part: CUSP WEB — CORRODED (BS 1174-1193) · airframe 59,371 hrs · 46,315 cycles

CORROSION ON PREVIOUS REPAIR DOUBLER OF LT CUSP WEB BETWEEN BS 1174 - 1193 AND X 54 - 60. THE DOUBLER WAS REPLACED IAW SRM 53-05 FIG 131A-7, SRM 51-30-5, AND SRM 51-10-3.

Part: SPLICE — CRACKED (RT WING) · airframe 59,371 hrs · 46,315 cycles

CRACKED SPLICE ON FIXED LEADING EDGE STRUCTURE XFS=194.850 ON RT WING. THE DOUBLER WAS REPLACED IAW ER/A 379404-14MA REV.A.

Part: BEAM — CRACKED (L1 DOOR) · airframe 59,371 hrs · 46,315 cycles

CRACKED NR 8 BEAM AT L1 DOOR. BEAM WAS REPAIRED IAW SRM 52-05D PAR.83 FIG.111.

Part: LONGERON — CRACKED (BS 1437) · airframe 59,371 hrs · 46,315 cycles

CRACKED LONGERON 12L, BS 1437. LONGUERON WAS REPLACED IAW SRM 53-14-4 & 51-30-2 & 51-30-5.

Part: FRAME — CRACKED (FUSELAGE) · airframe 59,371 hrs · 46,315 cycles

CRACKS ON FRAME Y=1452 BETWEEN LONGERONS 1, 8L-9L AT AFT ACCESSORY COMPARTMENT. FRAME WAS REPLACED IAW DWG 9911860, REV L AND SRM 51-30-2,51-30-5 AND 51-10-3.

Part: STRINGER — CRACKED (WING TE FLAP) · airframe 59,371 hrs · 46,315 cycles

A CRACK WAS FOUND OF 1.500" LENGTH ON STRINGER 11(OUTSIDE) AT THE OUTBD FLAP, INBD DRIVE HINGE AT XRS=164. STRINGER 11 WAS REPAIRED UNDER TASK CARD 5712-01030-03 AND SERVICE REWORK DRAWING SR09570100 REV B.

Part: DOOR FRAME — CORRODED (BS 370-427) · airframe 59,371 hrs · 46,315 cycles

CORROSION ON FWD CARGO COMPARTMENT LWR DOOR FRAME BETWEEN BS 370 - 427. THE DOOR FRAME WAS REPAIRED IAW SRM 53-05 FIG.55A.

Part: SKIN — CRACKED (BS 1380) · airframe 59,371 hrs · 46,315 cycles

.250 INCH CRACK IN FUSELAGE SKIN BS 1380 BETWEEN LONGERONS 12 - 13L. REPAIRED IAW SRM 53-04 FIG18 SHEET 1,2 AND 53-01 FIG 4 SHEET 4.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 59,371 hrs · 46,315 cycles

CRACKED INTERCOSTAL X=0 BETWEEN STA Y=1041 TO Y=1022,Y=769 TO Y=788 AND Y=1287 TO Y=1307 ALSO X=4, STA Y=1287 TO Y=1271 AT FLOOR STRUCTURE CABIN. REPLACED INTERCOSTAL STA=1287 TO STA=1271 INTERCOSTAL STA=769 TO STA=788 WAS REPAIRED. 2 CRACKS 1- .250 AND 2- .218" IAW SRM 53-01, FIG 2,51-30-2, 51-30-5, 51-10-3 PAR 14 AND 21 51-70-5,51-10-4. HFEC WAS ACOMPLISHED INTERCOSTAL 769 TO 788 ALONG TRIM LINE AND NO CRACKS WERE FOUND.

Part: LONGERON — CRACKED (BS 1418) · airframe 59,371 hrs · 46,315 cycles

CRACKED LONGERON 2R, BS 1418. THE LONGERON WAS REPAIRED IAW SRM 53-02 FIG 18.

Part: LONGERON — CRACKED (BS 1338) · airframe 59,371 hrs · 46,315 cycles

CRACKED LONGERON 7L, BS 1338. LONGERON WAS REPLACED IAW DWG 4912515 REV.H AND SRM 51-30-5.

Part: VANE — WORN (RT WING TE FLAP) · airframe 59,371 hrs · 46,315 cycles

WEAR ON LOWER SKIN OF INBD FLAP,INBD VANE XW 4 RT WING. THE SKIN ON INBD FLAP,INBD VANE WAS REPAIRED IAW SRM 57-03D PAR11.

Part: STOP FITTING — CRACKED (CARGO DOOR) · airframe 59,371 hrs · 46,315 cycles

CRACKED OUTER PAN BELOW STOP FITTING NR 2 AFT EDGE AT FWD CARGO COMPARTMENT DOOR . FWD CARGO COMPARTMENT DOOR WAS REPAIRED PER DC-9/MD80 SRM 52-03 FIG.8.

Part: LONGERON — CRACKED (BS 965) · airframe 59,371 hrs · 46,315 cycles

CRACKED LONGERON 2R, BS 965. LONGERON WAS REPAIRED IAW SRM 53-02 FIG.18.

Part: CUSP WEB — CORRODED (BS 1233) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION OUT OF LIMITS ON CUSP WEB BS 1233, X 54 TO 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG 131A-14,51-30-6, 51-30-1,51-10-3 PAR 14,21 AND 38.

Part: ANGLE — CORRODED (BS 196) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON CUSP ANGLE BS 196 AND X 59. CUSP ANGLE REPAIRED IAW SRM 53-05 FIG.55.

Part: DOUBLER — DENTED (TE FLAP) · airframe 59,371 hrs · 46,315 cycles

SEVERAL DENTS ON PREVIOUS REPAIR DOUBLER ON INBD FLAP, INBD VANE ON RT WING. REPAIRED IAW SRM 57-03D P.11.

Part: CUSP WEB — CRACKED (BS 214) · airframe 59,371 hrs · 46,315 cycles

CRACK ON RT CUSP WEB BS 214, RBL 55. CUSP WEB REPLACED IAW SRM 53-14-1 .

Part: CUSP WEB — CRACKED (BS 225) · airframe 59,371 hrs · 46,315 cycles

CRACKED RT CUSP WEB BS 225, X -58. CUSP WEB WAS FABRICATED AND REPLACED IAW SRM 53-05 FIG.131A-24.

Part: CUSP WEB — CORRODED (BS 788-807) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON LT CUSP WEB UPPER AND LOWER SURFACE BS 788 TO 807 X 44 TO X 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG 131A-14,51-30-2,51-30-1,51-10-3 PAR 14 AND 21.

Part: CUSP WEB — CORRODED (BS 1098-1174) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION OUT OF LIMITS ON RT CUSP WEB BETWEEN BS 1098 - 1174, X -54 TO -60. THE CUSP WEB WAS REPLACED IAW SRM 53-05 FIG 131A, 51-30-1,51-30-2,51-30-5,51-10-3 PAR 14 AND 21.

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 59,371 hrs · 46,315 cycles

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

Part: LONGERON — CRACKED (BS 522) · airframe 59,371 hrs · 46,315 cycles

CRACK ON LONGERON 4R BS 522. THE LONGERON WAS REPAIRED IAW SRM 53-02 FIG 18,51-30-2,51-30-5,51-10-4 ,AMM 20-30-00.

Part: JACKSCREW — WORN (HORIZONTAL STAB) · airframe 59,371 hrs · 46,315 cycles

WORN OUT THE HORIZONTAL STABILIZER ACTUATOR. END PLAY ON HORIZONTAL STAB ACTUATOR ASSEMBLY END PLAY IS 0.041. REPLACEMENT OF HORIZONTAL STABILIZER JACK SCREW IS ACCOMPLISHED UNDER CARD 2742-4540 JOB 00-0002.

Part: CUSP WEB — CORRODED (BS 1209) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION OUT OF LIMITS ON LT CUSP WEB BS 1209, X 54 - 60. REPAIRED IAW SRM 53-05 FIG 131A-7,51-30-2,51-30-5,51-30-1,51-10-3 PAR 14,21 AND 36.

Part: CUSP WEB — CORRODED (BS 598-712) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION FOUND ON THE LT CUSP WEB UPPER AND LOWER SURFACE BS 598 - 712, X 44 - 60. THE CUSP WEB WAS REPLACED IAW SRM 53-05 FIG 131 A-7 AND 131A-19, 53-14-2 FIG 4, 51-30-2, 51-30-1, 51-30-5, AND 51-10-3 PAR 14,21.

Part: CUSP WEB — CORRODED (BS 712-720) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION FOUND ON THE LT CUSP WEB BS 712 - 720, X 44 - 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG 131A-10 SHEET 1, 51-31-2, 51-30-1, AND 51-10-3 PAR 14,21 & 38.

Part: CUSP WEB — CORRODED (BS 1229) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION OUT OF LIMITS ON RT CUSP WEB ON BS 1229 X -54 TO - 60. REPAIRED IAW SRM 53-05 FIG.131A-10.

Part: CUSP WEB — CORRODED (BS 886-905) · airframe 59,371 hrs · 46,315 cycles

CRACKS FOUND ON THE RT CUSP WEB BS 886 - 905, -54 TO -60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG 131A-6, 51-30-2, AND 51-10-3 PAR 14, 21.

Part: LONGERON — CRACKED (BS 541) · airframe 59,371 hrs · 46,315 cycles

CRACKED LONGERON 4L BS 541 AT INNER FUSELAGE STRUCTURE. LONGERON WAS REPAIRED IAW SRM 53-02 FIG18.

Part: CUSP WEB — CORRODED (BS 503-598) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION UPPER AND LOWER ON RT CUSP WEB BS 503 TO 598 BETWEEN X -54 AND X -60. THE CUSP WEB WAS REPLACED IAW SRM 53-14-2 FIG.4,51-30-1, 51-30-2, 51-30-5, 53-14-3.

Part: BULKHEAD WEB — CRACKED · airframe 59,371 hrs · 46,315 cycles

CRACKED WEB ON AFT PRESSURE BULKHEAD BEHIND 6 PULLEY BRACKET. BULKHEAD WEB WAS REPAIRED IAW SRM 53-01 FIG 1,51-30-2, 51-30-5 AMM 20-30-01.

Part: CUSP WEB — CRACKED (BS 597) · airframe 59,371 hrs · 46,315 cycles

CRACKED RT CUSP WEB BS 597 BETWEEN X -44 TO -54. THE CUSP WEB WAS REPAIRED IAW SRM 53-05 FIG 131A-24,51-10-3 PAR 14, 21 AND 38, 51-30-2, 51-30-5.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA OF FUEL ACCESS PLATE 1414C ON RT WING. THE ACCESS PLATE WAS REPLACED IAW SRM 51-22-2A CONDITION II.

Part: CUSP WEB — CORRODED (BS 712-788) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON RT CUSP WEB FROM BS 712 TO 788 BETWEEN X -54 AND X -60. CUSP WEB WAS REPLACED IAW SRM 53-05 FIG 131A-19.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA OF FUEL ACCESS PLATE 1311C, ON LT WING. THE ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A CONDITION II.

Part: ANGLE — CORRODED (BS 1022-1041) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON ANGLE AND NICK AT RT CUSP WEB BS 1022 TO 1041 BETWEEN X -54 AND X -60. ANGLE REMOVED AND INSTALLED, CORROSION WAS REMOVED FOUND WITHIN LIMITS IAW ER/A 511165-14MA REV C , OUT LIMITS IAW SRM 53-05 PAR 166, PANAMETRICS 38DL SONOPEN V260-SM C/N 1325 27OCT16, HFEC WAS ACCOMPLISHED ON ANGLE(2 EA)NO CRACKS WERE FOUND AFTER REMOVE CORROSION IAW ER/A 511165-14MA REV.C. EQUIPMENT:PHASEC 2D C/N 925 EXP.DATE:8-ABR-17,51-10-3 PAR 14,21,26, 51-30-2 AREA OUT OF LIMITS IS ATTENDED WITH NRC SERIAL NUMBER 01149. (LP2597672)

Part: LONGERON — CRACKED (BS 1437) · airframe 59,371 hrs · 46,315 cycles

CRACKED LONGERON 3R BS 1437. LONGERON REPAIRED PER SRM 53-02 FIGURE 18.

Part: CUSP WEB — CORRODED (BS 298-307) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION UPPER AND LOWER OF RT CUSP WEB BS 298 TO 307 BETWEEN X -54 AND X -60 . REPAIRED IAW 53-05 131A,51-10-3 PAR 14, 21, 26, 38, 51-30-2, HFEC WAS ACCOMPLISHED, NO CRACKS WERE FOUND.

Part: FRAME — CRACKED (BS 1322) · airframe 59,371 hrs · 46,315 cycles

CRACK ON FRAME BS 1322 AND LONGERON 17R. REPAIRED IAW ER/A 493697-14MA REV.B.

Part: CUSP WEB — CORRODED (BS 252) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION OUT LIMITS ON BS 252 LT CUSP WEB. THE AREA WAS REPAIRED PER DC9MD80 SRM 53-05 FIG 131A-14,51-10 PAR 14,21.26 AND 38, 51-30-5.

Part: ANGLE — CRACKED (BS 1380 FRAME) · airframe 59,371 hrs · 46,315 cycles

CRACKED FRAME ANGLE BS 1380 BTW LONGERONS 13 - 14R. THE FRAME ANGLE WAS REPLACED IAW SRM 53-14-4 & 51-30-5.

Part: VANE — PUNCTURED (RT WING TE FLAP) · airframe 59,371 hrs · 46,315 cycles

PUNCTURE ON OUTBD CUTOUT AT OUTBD VANE INBD FLAP RT WING. OUTBD VANE WAS REPAIRED PER ER/A 547865-14 REV. ORG. AND ETI-88-16-257 REV. 2.

Part: CUSP WEB — CRACKED (BS 467-481) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON REPAIR DOUBLER OF RT CUSP WEB BS 467 TO 481 BTW X -54 AND X -60. A NEW REPAIR WAS INSTALLED IAW SRM 53-05 FIG.131A-7 (SHEET 1).

Part: FLOOR PANEL — CRACKED (NOT REPORTED) · airframe 59,371 hrs · 46,315 cycles

CRACKED FLOOR PANEL 120C. A NEW FLOOR PANEL WAS MANUFACTURED IAW AMM 53-20-01-201.

Part: TORSION BAR — CORRODED (RT WING SPOILER) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON RT WING INBOARD FLIGHT SPOILER TORSION BAR. DAMAGED TORSION BAR, CAM ARM AND LEVER WERE REPACED IAW AMM 27-61-06.

Part: ANGLE — CRACKED (R1 DOOR) · airframe 59,371 hrs · 46,315 cycles

CRACKED ANGLE ON FRAME NR 1 AT FWD R1 DOOR. ANGLE WAS REPLACED IAW SRM 51-30-5 AND DWG 9911579 ITEM -12.

Part: BEARING — CRACKED (RT AILERON) · airframe 59,371 hrs · 46,315 cycles

CRACKED HOUSING BEARING ON RT AILERON CONTROL SECTOR. SECTOR WAS REPLACED IAW AMM 27-10-03.

Part: CUSP WEB — CORRODED (BS 458-464) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION FOUND ON REPAIR DOUBLER OF RT CUSP WEB BS 458 TO 464 BETWEEN X -54 AND X -60. THE WEB WAS REPAIRED IAW SRM 53-05 FIG 131 A-13, 51-10-3 PAR 12 AND 21 51-30-2, 51-30-5,51-30-1.

Part: DUCT — CRACKED (A/C PACK) · airframe 59,371 hrs · 46,315 cycles

CRACKED LEFT Y DUCT. THE DUCT WAS REPAIRED ER/A 547872-14 REV. ORIG.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON COUNTERSINK AREA OF FUEL ACCESS PANEL 1460C ON RT WING. THE ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A CONDITION II.

Part: CUSP WEB — CORRODED (BS 584-588) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION OUT LIMITS BS 584 - 588 ON CUSP WEBS. AREA WAS REPAIRED IAW SRM 53-05 FIG. 131. A -14 HFEC INSPECTION WAS ACCOMPLISHED AND NO CRACKS WERE FOUND.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA OF FUEL ACCESS PANEL 1307C ON LT WING. THE ACCESS PANEL WAS REPLACED IAW 51-22-2A CONDITION II.

Part: TORSION BAR — CORRODED (RT WING SPOILER) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON RT WING OUTBOARD FLIGHT SPOILER TORSION BAR. DAMAGED TORSION BAR, CAM ARM AND LEVER WERE REPLACED IAW AMM 27-61-06.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA OF FUEL ACCESS PANEL 1361C ON LT WING. THE ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A CONDITION II.

Part: PAN — CRACKED (CARGO DOOR) · airframe 59,371 hrs · 46,315 cycles

CRACKED PAN INNER FACE ON BEAM 5 BS 1212 AT AFT CARGO DOOR. AFT CARGO DOOR WAS REPLACED IAW 52-30-02.

Part: ACCESS PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON COUNTERSINK OF FUEL ACCESS PLATE NR 1436C AT RT WING. ACCESS WAS REPLACED IAW SRM 51-22-2A CONDITION II.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON COUNTERSINK OF FUEL ACCESS PLATE NR 1454C AT RT WING. ACCESS PLATE WAS REPLACED IAW SRM 51-22-2A, CONDITION II.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON COUNTERSINK OF FUEL ACCESS PLATE NR 1476C AT RT WING. THE FUEL ACCESS PLATE NR 1476C WAS REPLACED IAW SRM 51-22.

Part: SKIN — DAMAGED (BS 886-905) · airframe 59,371 hrs · 46,315 cycles

SCRATCHES ON WINDOW BELT BS 886 - 905. BLENDED OUT, MEASURED AND TREATED. ALL ARE WITHIN LIMITS IAW 53-05 FIGURE 111.

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON WEB STA Y=1380 BETWEEN LONG 25 RT TO 25 LT AT AFT ACC COMPARTMENT. WEBS WERE FABRICATED IAW DWG NR 9912246, ITEM-121,109, REV CE.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON COUNTERSINK OF FUEL ACCESS PLATE NR 1456C AT RT WING. ACCESS PLATE WAS REPLACED IAW SRM 51-22-2A CONDITION II.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA OF FUEL ACCESS PLATE NR 1472C AT RT WING. ACCESS PLATE 1472C WAS REPLACED IAW SRM 51-22-2.

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 59,371 hrs · 46,315 cycles

DELAMINATED FLOOR PANELS NR 160D, 313B, 256D, 160E, 160B, 160F, 160A AND 148A. FLOOR PANELS NR 160D, 160E, 160B, 160F, 160A AND 148A WERE FABRICATED IAW AMM 53-20-01-201 FLOOR PANELS 256D AND 313B WERE REPAIRED IAW AMM 25-00-00-801.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON COUNTERSINK OF FUEL ACCESS PLATE NR 1371C AT LT WING. ACCESS PLATE WAS REPLACED IAW SRM 51-22-2A, CONDITION II.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON COUNTERSINK AND SETTLEMENT AREA OF FUEL ACCESS PLATE NR 1363C AT LT WING. ACCESS WAS REPLACED IAW SRM 51-22-2A, CONDITION II.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON COUNTERSINK OF FUEL ACCESS PLATE NR 1355C AT LT WING. ACCESS NR: 1355C WAS REPLACED IAW SRM 51-22-2A,CONDITION II.

Part: FERRULE — DAMAGED (FLOOR PANEL) · airframe 59,371 hrs · 46,315 cycles

DAMAGE FERRULES ON FLOOR PANELS NR 160C,148C,148D, 313B AND 256C. THE FERRULES ON FLOOR PANELS NR 148C,148D,313B AND 256C WERE REPLACED IAW AMM 53-20-01-201 2, FLOOR PANEL 160C WAS FABRICATED IAW AMM 53-20-01-201.

Part: SKIN — DAMAGED (RT WING) · airframe 59,371 hrs · 46,315 cycles

DURING NDT INSPECTION A DISCREPANT AREA WAS FOUND ON LOWER RT WING SKIN XRS 163 - 168 REAR SPAR. REPAIRED IAW ER/A 547864-14AD REV.ORIGINAL.

Part: VANE — WORN (TE FLAP) · airframe 59,371 hrs · 46,315 cycles

WEAR ON AFT OTBD CORNER UPPER SURFACE ON OTBD FLAP, INBD VANE AT RT WING. AFT OTBD CORNER UPPER SURFACE ON OTBD FLAP, INBD VANE AT RT WING WAS REPAIRED IAW ER/A 492663-14MA, REV ORIG.

Part: SKIN — DAMAGED (LT WING) · airframe 59,371 hrs · 46,315 cycles

DURING NDT INSPECTION A DISCREPANT AREA WAS FOUND ON LOWER SKIN AT XRS 163 - 168 LT WING REAR SPAR. REPAIRED IAW ER/A 547864-14AD REV.ORIGINAL.

Part: PAN — CRACKED (FUSELAGE) · airframe 59,371 hrs · 46,315 cycles

CRACK ON LT FWD UPPER CORNER RING PAN BETWEEN Y= 807 AND Y=-826 AT CABIN PASSENGER INTERNAL STRUCTURE. RING PAN WAS REPAIRED IAW SRM 53-05, FIG 122 AND ERA 493648-14MA, REV A.

Part: CHANNEL — CRACKED (FLOOR PANEL) · airframe 59,371 hrs · 46,315 cycles

CRACKS ON CHANNELS OF FLOOR PANELS NR 313A, 313E, 541F, 1079E, 541A AT PAX CABIN. CRACKS ON FLOOR PANELS 313A .165", 313E .187", 541F .190", 1079E .270", 541A" .185" WERE REPAIRED IAW SRM 53-05 FIG 131B AND 131C. HFEC INSPECTION WAS ACCOMPLISHED NO CRACKS WERE FOUND IAW NDT SPM 06-10-01.001.

Part: CHANNEL — CRACKED (FLOOR PANEL) · airframe 59,371 hrs · 46,315 cycles

CRACKS ON CHANNELS OF FLOOR PANELS NR 389G, 693A, 927A, 1003A, 617A AT PAX CABIN. CRACKS ON FLOOR PANELS 1003A .185", 389G .220" 617A .165", 693A .137" AND 927A .155" WERE REPAIRED IAW SRM 53-05, FIG 131B AND 131C. NO CRACKS WERE FOUND AFTER DAMAGE REMOVED IAW NDTSPM 06-10-01.001.

Part: PAN — CRACKED (FUSELAGE) · airframe 59,371 hrs · 46,315 cycles

CRACK ON LT AFT UPPER CORNER RING PAN BETWEEN Y= 1174 AND Y=-1193 AT CABIN PAX INTERNAL STRUCTURE. RING PAN WAS REPAIRED IAW SRM 53--05, FIG 122 AND ERA 493648-14MA, REV A.

Part: PAN — CRACKED (FUSELAGE) · airframe 59,371 hrs · 46,315 cycles

CRACK ON RT FORWARD LOWER CORNER RING PAN BETWEEN Y=984 AND Y=1003, Y=1041 AND Y=1060 AT CABIN PAX INTERNAL STRUCTURE. RING PAN WERE REPAIRED IAW SRM 53-05, FIG 122 AND ER/A 493648-14MA, REV A.

Part: PAN — CRACKED (FUSELAGE) · airframe 59,371 hrs · 46,315 cycles

CRACK ON RT FWD LOWER CORNER RING PAN BETWEEN Y=1060 AND Y=1079, Y=1098 AND Y=1117 AT CABIN PASSENGER INTERNAL STRUCTURE. RING PAN WERE REPAIRED IAW SRM 53-05, FIG 122 AND ERA 493648-14MA, REV A.

Part: VANE — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON MID INBD STUD ALSO INNER FITTING ON OUTBD FLAP, OUTBD VANE AT LT WING. THE GUIDE VANE WAS REPLACED.

Part: PAN — CRACKED (FUSELAGE) · airframe 59,371 hrs · 46,315 cycles

CRACK ON LT FORWARD LOWER CORNER RING PAN BETWEEN Y=1022 AND Y=1041, Y=984 AND Y=1003 AT CABIN PASSENGER INTERNAL STRUCTURE. RING PAN WERE REPAIRED IAW SRM 53-05, FIG 122 AND ERA 493648-14MA, REV A. BETWEEN STA Y=1060- Y=1079, CRACK=L 550", AND STA Y=1098, Y=1117, CRACK=L.400" HFEC WAS ACCOMPLISHED ON RT FORWARD LOWER CORNER RING PAN BETWEEN Y=1060 AND Y=1079,Y=1098 AND Y=1117 AT CABIN PASSENGER INTERNAL STRUCTURE. NO CRACKS WERE FOUND AFTER REMOVED DAMAGE IAW NDT SPM 06-10-01.001.

Part: PAN — CRACKED (FUSELAGE) · airframe 59,371 hrs · 46,315 cycles

CRACK ON LT FORWARD LOWER CORNER RING PAN BETWEEN Y=1060 AND Y=1079, Y=1098 AND Y=1117 AT CABIN PASSENGER INTERNAL STRUCTURE. RING PAN WERE REPAIRED IAW SRM 53-05, FIG 122 AND ERA 493648-14MA, REV A. BETWEEN STA Y=1060- Y=1079 CRACK=L.550", AND STA Y=1098-Y=1117 CRACK=L.400". HFEC WAS ACCOMPLISHED ON RT FORWARD LOWER CORNER RING PAN BETWEEN Y=1060 AND Y=1079, Y=1098 AND Y=1117 AT CABIN PASSENGER INTERNAL STRUCTURE. NO CRACKS WERE FOUND AFTER REMOVED DAMAGE IAW NDT SPM 06-10-01.001.

Part: PAN — CRACKED (FUSELAGE) · airframe 59,371 hrs · 46,315 cycles

CRACK ON RT AFT LOWER CORNER RING PAN BETWEEN Y=1060 AND Y=1079 AT CABIN PASSENGER INTERNAL STRUCTURE. RING PAN WAS REPAIRED IAW SRM 53-05, FIG 122 AND ERA 493648-14MA, REV A, CRACK: L=.500", HFEC WAS ACCOMPLISHED ON RT AFT LOWER CORNER RING PAN BETWEEN Y=1060 AND Y=1079 AT CABIN PASSENGER INTERNAL STRUCTURE. NO CRACKS WERE FOUND AFTER REMOVED DAMAGE IAW NDT SPM 06-10-01.001.

Part: PAN — CRACKED (FUSELAGE) · airframe 59,371 hrs · 46,315 cycles

CRACK ON RT AFT UPPER CORNER RING PAN BETWEEN Y=1060 AND Y=1079 AT CABIN PASSENGER INTERNAL STRUCTURE. RING PAN WAS REPAIRED IAW SRM 53-05, FIG 122 AND ERA 493648-14MA, REV A. HFEC WAS ACCOMPLISHED ON RT AFT UPPER CORNER RING PAN BETWEEN Y=1060 AND Y=1079 AT CABIN PAX INTERNAL STRUCTURE. NO CRACKS WERE FOUND AFTER REMOVED DAMAGE IAW NDT SPM 06-10-01.001.

Part: VANE — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 59,371 hrs · 46,315 cycles

CORROSION ON OUTBD LOWER FACE MID VANE OUTBD FLAP RT WING. DUE TO EXCESSIVE CORROSION THE GUIDE VANE WAS REPLACED IAW SRM 57-03D PAR 11.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHT) · airframe 59,138 hrs · 46,149 cycles

SEAT 17 DE EMERGENCY LIGHT INOPERATIVE. REPLACED HARNESS IAW AMM 33-53. CHECKS GOOD.

Part: STRUCTURE — CORRODED (LAV SERVICE DOOR) · corrosion level 2 · airframe 58,919 hrs · 45,989 cycles

ON "A" CHECK, FOUND AFT LAV SERVICE DOOR CORRODED THROUGH AROUND LATCH. DOOR WAS REPLACED.

Part: STRUCTURE — DAMAGED (HORIZONTAL STAB) · airframe 58,234 hrs · 45,484 cycles

LEFT HORIZONTAL STABILIZER TIP FOUND DAMAGED. INSTALLED LT HORIZONTAL STABILIZER TIP IAW STANDARD PRACTICES 2040.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 57,369 hrs · 44,864 cycles

MAINTENANCE FOUND A CABIN EMERGENCY LIGHT INOPERATIVE. AN EMERGENCY BATTERY BACK WAS REPLACED.

Part: UNKNOWN — SMOKE (CABIN) · airframe 55,362 hrs · 43,486 cycles

DURING A HOLDING PATTERN, THE F/A REQUESTED MORE HEAT FOR A COLD CABIN. AFTER THE COCKPIT CREW ADJUSTED THE TEMPERATURE UP, THE F/A REPORTED SMOKE AND HAZE FILLING CABIN. COCKPIT CREW DONNED O2 MASKS AND ADJUSTED THE TEMP BACK DOWN AND HAZE DISSIPATED. MAINTENANCE CLEANED THE APU INLET AS A PRECAUTION AND COMPLETED A DUCT BURNOUT. NO FURTHER SMOKE, HAZE, ODOR NOTED.

Part: BALANCE WEIGHT — CORRODED (RT ELEVATOR) · airframe 54,047 hrs · 42,514 cycles

RIGHT ELEVATOR L/E POSITION NR 4 BALANCE WEIGHTS AND ATTACHING HARDWARE CORRODED FABRICATED NEW L/E SKIN, NOSE CAP ON SAA TRAVELER NR 7000629511, LOCATED AND DRILLED NEW L/E SKIN IAW SRM 51-10-04, HAND CLEANED L/E BALANCE WEIGHTS AND TREATED AND PRIMED IAW SRM 51-20-0 AND SRM 51-10-03. ASSEMBLED NEW L/E SKIN, NOSE CAP, AND BALANCE WEIGHTS REF MANUAL 27-30-1 ASSY WILL BE INSTALLED ON CARD 300-6.

Part: LONGERON — CORRODED (BS 1287-1309) · airframe 54,039 hrs · 42,506 cycles

AFT CARGO BAY BS 1287-1309 LONGERON 29R CORRODED INSIDE CHANNEL AND AROUND FASTENERS. REMOVED CORROSION ON LONGERON, FOUND OUT OUT OF LIMITS IAW SRM 53-0. ACCOMPLISHED PERMANENT REPAIR IAW SRM 53-02, FIG 19, SHT 2.

Part: FLOOR PANEL — CORRODED (AFT CARGO BAY) · airframe 54,047 hrs · 42,514 cycles

AFT CARGO FLOOR PANEL 181LF HAS CORROSION ON UPPER AND LOWER SURFACE. BLENDED & REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS IAW SRM 53-01. FABRICATED NEW FLOOR PANEL IAW ER/A NR 228602-14.

Part: WIRE HARNESS — FAILED (EMERGENCY LIGHT) · airframe 54,005 hrs · 42,480 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHT AT SEAT 16DE WAS INOPERATIVE. MAINTENANCE REPLACED THE WIRE HARNESS AND FUNCTIONALLY CHECKED THE SYSTEM.

Part: INDICATOR — FROZEN (AIRSPEED) · airframe 53,240 hrs · 41,937 cycles

DURING TAKEOFF, CREW REPORTED BOTH CAPTAIN`S & F/O`S AIRSPEED INDICATIONS FROZE AT 80 KNOTS. SUBSEQUENT TAKEOFF RESULTED IN OVERBOOST & OVERTEMP OF BOTH ENGINES. DECLARED AN EMERGENCY AND DIVERTED, LANDED SAFELY. MAINTENANCE FOUND EXCEEDANCES ON BOTH ENGINES AND WERE REPLACED. A FULL PURGE AND LEAK CHECK OF BOTH PITOT-STATIC SYSTEMS WAS ACCOMPLISHED AND BOTH AIR DATA COMPUTERS WERE REPLACED. DURING THE PITOT STATIC CHECKS, IT WAS DETERMINED THE LT STATIC PORT HEATER WAS INOPERATIVE AND IT WAS ALSO REPLACED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 52,655 hrs · 41,559 cycles

DURING SERVICE CHECK FOUND CEILING MOUNTED EMERGENCY EXIT LIGHTS FROM ROW 20 FWD INOPERATIVE. REPLACED BATTERIES AT POWER SUPPLIES B5-100-B5-103. ALL EMERGENCY LIGHTS OPERATE NORMALLY REF WDM 33-54-12.

Part: LANYARD — FRAYED (L1 DOOR SLIDE) · airframe 51,120 hrs · 40,447 cycles

DURING SERVICE CHECK, L1 DOOR SLIDE LANYARD FOUND FRAYED. R & R L1 DOOR SLIDE LANYARD IAW AMM.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 51,072 hrs · 40,406 cycles

DURING SERVICE CHECK, FOUND FORWARD OVERWING EMERGENCY LIGHTS INOPERATIVE. R & R BATTERIES OF OVERWING BATTERY PACKS IAW MM. OPS CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 50,756 hrs · 40,171 cycles

PEANUT BULB LIGHTS FOR EMERGENCY LIGHTS STAY ILLUMINATED DIM WHEN SWITCH IS IN ARM AND OFF POSITION. REMOVED AND REPLACED ENTRY LIGHTING BATTERY PACK. OPERATION CHECKS GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 50,659 hrs · 40,107 cycles

DURING SERVICE CHECK, MX FOUND EMERGENCY LIGHTS OVER AFT EMERGENCY DOOR INOPERATIVE. R & R BATTERY PACK AT LOCATION B5-105 IAW MM. OPS CHECKEDS GOOD. ACFT OK FOR SERVICE.

Part: ACTUATOR — CRACKED (RUDDER) · airframe 50,326 hrs · 39,851 cycles

RUDDER LIMITER ACTUATOR ATTACH TO STA 1510 FRAME IS CRACKED AT 2:30 POSITION. CRACKED EMPENNAGE. REMOVED FASTENER. NDT CRACK. END TO END .92". REMOVED ALL ATTACHING HARDWARE, CUT FRAM AT 1:00 POSITION RT SIDE FOR FRAME REPAIR. HFEC. DAMAGE CONTAINED. FORMED NEW FRAME SECTION, PICKED UP HOLES, TREATED, PRIMED AND INSTALLED FRAME SECTION IAW DWG 9911843. INSTALLED REPAIR ANGLE AND SPLICE REPAIR. COMPLETED WORK REPAIR IAW SRM 51-30.

Part: FRAME — CRACKED (BS 1510) · airframe 50,326 hrs · 39,851 cycles

BS 1510, FRAME IS CRACKED AT TAIL CONE SPADE ATTACH POINT HOLE THREE O`CLOCK POSITION. CRACKED AFT FUSELAGE. REMOVED RT LOWER FRAME. DRILLED NEW FRAME. INSTALLED FRAME AND FRAME SPLICES IAW DWG 9911843.

Part: SILL — CORRODED (BS 1155-1212) · airframe 50,326 hrs · 39,851 cycles

AFT CARGO DOOR SILL HAS CORROSION ON FASTENERS AND STRUCTURE BETWEEN BS 1155 AND 1212. REMOVED SILL AND SCUFF PLATE. CORROSION ON L28L BETWEEN BS 1155 AND 1212 BEAM. R & R BEAM IAW SRM AND DWG 5930483 REF NR 81.

Part: ENGINE — FAILED (NR 1) · airframe 50,310 hrs · 39,842 cycles

PERFORMED AIR TURN BACK, FOLLOWING A NR 1 ENGINE STALL ON CLIMB OUT. LOST GENERATOR AND BEGAN TO LOSE OIL QUANTITY AND OIL PRESSURE. WHEN OIL PRESSURE REACHED 7 PSI, PILOT SHUTDOWN ENGINE. NON EVENTFUL LANDING. MX FOUND SECTION OF LOWER COWL MISSING DUE TO UNCONTAINED TURBINE FAILURE. MX REPLACED THE ENGINE AND DAMAGED COWLING.

Part: UNKNOWN — ODOR (CABIN) · airframe 50,222 hrs · 39,774 cycles

CREW DECLARED EMERGENCY AND RETURNED TO DEPARTURE, AFTER DETECTING AN ODOR IN CABIN AFTER TAKEOFF. NO VISIBLE SMOKE PRESENT, ONLY FUMES. MX COULD NOT DETECT ANY ODORS BUT DID ACCOMPLISH A DUCT BURNOUT PROCEDURE IAW CARD 7100-2619.

Part: CABLE — LOOSE (L1 DOOR SLIDE) · airframe 49,993 hrs · 39,616 cycles

DURING SERVICE CHECK, MAINTENANCE FOUND 1L DOOR SLIDE CABLE LOOSE. MAINTENANCE SECURED CABLE. OK FOR SERVICE.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 49,036 hrs · 38,936 cycles

DURING SERVICE CHECK, MAINTENANCE FOUND SEAT 3C EMERGENCY LIGHT INOPERATIVE. MAINTENANCE REMOVED AND REPLACED LIGHT ASSEMBLY PER AMM. OPERATION CHECKS GOOD.

Part: RELEASE CABLE — STICKS (TAILCONE) · airframe 48,778 hrs · 38,760 cycles

DURING INSPECTION THE TAIL CONE RELEASE CABLE WAS FOUND TO BE STICKING. MAINTENANCE REPLACED THE TAIL CONE RELEASE CABLE AND THE FUNCTIONAL CHECK WAS GOOD.

Part: SKIN — WORN (VERTICAL STAB) · airframe 46,882 hrs · 37,449 cycles

FOUND THE VERTICAL STAB L/E UPPER REMOVAL PANEL RT SKIN WITH MULTIPLE WORN HOLES ALONG THE LOWER L/E ISSUED ERA 493753-14 REV ORG DATED 06/19/2011.

Part: SKIN — DAMAGED (RUDDER) · airframe 45,032 hrs · 36,240 cycles

DAMAGED METALLIZED ON LT RUDDER SURFACE MID AREA FWD AND AFT EDGE AND DAMAGED PAINT COAT ON RT SURFACE AT SKIN PANEL. REPAIRED IAW SRM 51-70-01A-D AND ERA 479662-14MA.

Part: FRAME — UNKNOWN (FUSELAGE) · airframe 44,459 hrs · 35,851 cycles

FUSELAGE OVERWING FRAME REPAIRED IAW EO 09-460094-12, ME 03.

Part: BALLAST — FAILED (CABIN LIGHTS) · airframe 44,404 hrs · 35,811 cycles

RETURNED TO DEPARTURE DUE TO STRONG BURNING RUBBER ODOR AROUND EMERGENCY EXIT ROWS. ACFT WAS AT FL330, ODOR DISSIPATED ON DESCENT AND WAS GONE BY TOUCHDOWN. PERFORMED OPERATION 5088 (SIC TROUBLESHOOTING) ITEM 3 FOUND LIGHT BALLAST B6-53 BAD. R & R SAME. RAN ENGINES AND COULD NOT DUPLICATE.

Part: UNKNOWN — ODOR (CABIN) · airframe 44,405 hrs · 35,812 cycles

STRONG BURNING RUBBER ODOR AT ALTITUDE (FL330) AT EMERGENCY EXIT ROWS OVER WINGS. RETURNED TO DEPARTURE, MX IN PROGRESS TROUBLESHOOTING ODOR IN CABIN.

Part: SPAR CAP — CORRODED (HORIZONTAL STAB) · airframe 41,416 hrs · 33,785 cycles

ONE FASTENER HOLE IN THE RT HORIZONTAL STABILIZER REAR SPAR UPPER CAP WAS FOUND WITH DAMAGE. THE STRUCTURE IS THE SUBJECT OF AD 2007-10-04. THE HOLE WAS OVERSIZED TO REMOVE THE DAMAGE AND A LARGER FASTENER WAS INSTALLED. AN AMOC WAS PROVIDED FROM BOEING AS A TIME LIMITED REPAIR UNTIL 11/30/2010.

Part: CONTROL PANEL — ARCED (COCKPIT) · airframe 40,936 hrs · 33,386 cycles

BATTERY CIRCUIT BREAKER POPPED INFLIGHT ELECTRICAL ARCING AND FLASH FROM HYDRAULIC PANEL F/O RECEIVED SHOCK FROM YOKE ELECTRICAL BURNING SMELL BUT NO SMOKE. FOUND BATTERY CHARGER C/B POPPED, REPLACED C/B, BATTERY CHARGER & BATTERIES, REPLACED HYD AUX PUMP & TRANSFER PUMP SWITCHES, PERFORMED OPS 5088, ALSO CHK L1 & R1 DOOR DRAIN SYSTEM, FOUND OPS NORMAL.

Part: B-NUT — LOOSE (HYDRAULIC SYSTEM) · airframe 40,091 hrs · 32,450 cycles

ON DESCENT AFTER TURNING ON AUX AND TRANS PUMPS, HYD QTY LOW LIGHT ILLUM AND QTY INDICATED 2 QTS. C/W QRH. FOUND LOOSE B NUT ON ELBOW FITTING TO FILTER MODULE ASSY LEFT TAIL COMPT. SECURED SAME AND REPLACED BOTH FILTERS ON MODULE ASSY. LEAK CKS OK.

Part: SKIN — DENTED (FUSLEAGE) · airframe 33,187 hrs · 25,322 cycles

FUSELAGE SKIN PREVIOUSLY DAMAGED AT STA 228 BETWEEN L-17L AND 18L. PERMANENT REPAIR INSTALLED PER ERA 382691-14 REV B.

Part: THROTTLE CABLE — BINDING (NR 2 ENGINE) · airframe 31,276 hrs · 23,993 cycles

ABORTED TAKEOFF AT 65 KIAS ENGAGED AUTOTHROTTLES FOR FLEX 50 TAKEOFF AT 75 PERCENT N1 THROTTLES IMMEDIATELY CLAMPED AND DID NOT ADVANCE AT ALL TOWARDS TAKEOFF THRUST. ABORTED T/O FOR THIS REASON. FOUND THRUST CABLE AT ENGINE BINDING. REPLACED SAME.

Part: CHARGER — UNSERVICEABLE (EMERGENCY LIGHT) · airframe 29,946 hrs · 23,088 cycles

EMERGENCY ESCAPE PATH LIGHTS INOPERATIVE, 31DE THRU 38DE. REPLACED BATTERY CHARGER.

Part: LIGHT — BROKEN (L2 DOOR) · airframe 29,622 hrs · 22,862 cycles

L2 GALLEY DOOR EXIT LIGHT IDENTIFIER BASE BROKEN. REPLACED L2 GALLEY EXIT DOOR EMERGENCY LIGHT BASE. EMERGENCY LIGHT, CHECKS OK.

Part: STRUCTURE — CORRODED (KEELBEAM) · airframe 29,323 hrs · 22,664 cycles

THE OUTER FRAME OF THE LONGERON 18R CUSP BEAM WAS FOUND WITH AN AREA OF CORROSION ON THE HORIZONTAL FLANGE AT FS 683. THE CORROSION WAS REMOVED WITH A CUTOUT TO THE FLANGE AND REPAIRED WITH A STEEL REPAIR ANGLE PER ER/A 384979-14, REV B.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 29,323 hrs · 22,664 cycles

THE RT FUSELAGE TO VERTICAL STABILIZER ATTACH ANGLE WAS FOUND WITH A CRACK NEAR CANTED FS 1474. THE CRACK WAS REMOVED WITH A TRIMOUT TO THE HORIZONTAL FLANGE OF THE ANGLE. THE AREA WAS REPAIRED WITH A STEEL REPAIR ANGLE PER ER/A 384977-14, REV A.

Part: SKIN — DENTED (FS 228, S-17L) · airframe 26,485 hrs · 20,640 cycles

FUSELAGE / SKIN / FS 228 / STRG. 17L-18L : DENT CUTOUT REPAIR THE FUSELAGE SKIN WAS FOUND WITH 3 DENTS NEAR FS 228 BETWEEN STRINGERS 17L & 18L. THE DENTS WERE REMOVED WITH A SINGLE 10" X 10" CUTOUT IN THE SKIN. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 382691- 14, REV A.

Part: SMOKE DETECTOR — INOPERATIVE (LAVATORY) · airframe 26,057 hrs · 20,299 cycles

SMOKE DETECTOR IN RIGHT AFT LAV DID NOT OPERATE WHEN PASSENGER SMOKED TWO CIGARETTES AND TRASH BIN BEGAN TO SMOLDER. REPLACED SMOKE DETECTOR, QA INVESTIGATING.

Part: LIGHT — MISSING (SEAT 19) · airframe 23,021 hrs · 18,066 cycles

EMERGENCY EXIT LIGHT ON SEAT 19E IS INOP. RELAMPED BOTH LIGHTS.

Part: SKIN — GOUGED (CARGO DOORWAY)

A GOUGE WAS NOTED ON THE AFT EDGE OF THE C3 DOORWAY. THE DAMAGE WAS REMOVED W/A 1 BY 1.4 TRIM OUT IN THE SKIN AND SURROUND DOUBLER. REPAIR PER ERA 333011-14, REV. A.

Part: FRAME — CRACKED (BS 1418)

CRACKS AT L2R AND L2L ON THE FS 1418 FRAME WERE FOUND IN THE TYPICAL LOCATIONS. THE CRACKS WERE 1.25 EACH. REPAIRED PER ERA 332990-14.

Part: SKIN — DENTED (BS 237)

A DENT WAS FOUND ON THE FUSELAGE SKIN AT FS 237 JUST BELOW L17L. CUTOUT MEASURED APPROX 6 BY 2.5. REPAIRED PER ERA 332994-14, REV A.

Part: SKIN — DENTED (BS 250)

AT HMV, A DENT WAS TRIMMED OUT IN THE FUSELAGE SKIN; DAMAGE CUTOUT IS APPROX 30 BY 8; AND IS LOCATED AT APPROX FS 250 AND L19L. REPAIRED PER ERA 266889-14, REV B.

Part: SKIN — CRACKED (NLG DOOR)

DURING A ROUTINE SHOP INSPECTION, NR 6921 WAS WRITTEN ON LT NLG DOOR FOR DAMAGE ON INNER SKIN LOWER FLANGE 10 INCHES FROM FWD EDGE. INSTALLED DOUBLER PER SRM 52-02 FIG. 6.

Part: SKIN — CRACKED (L1 DOOR)

FOUND DURING TRIP CHECK, L-1 DOOR HOLD OPEN WAS OUT OF ADJUSTMENT. FOUND SKIN CRACKED BELOW HOLD OPEN HOOK ON DOOR SKIN. REPAIRED PER SRM 52-05 FIG 20B.