N675MC

Part: INTERCOSTAL — CRACKED (BS 160) · airframe 78,272 hrs · 65,807 cycles

INTERCOSTAL CRACKED FORWARD RT CABIN, 4" FWD OF STA 160 AT LONGERON R-9 . REMOVED 1 EA GUSSET TO FOM & DAMAGED ANGLE, 4" FWD OF STA 160 AT L-9R, FABRICATED TOP ANGLE REPAIR ON TRAVEL (SAA 700022065-T3 PN) 70002195820001. FABRICATED BOTTOM ANGLE REPAIR PN 700022065-B3 ON TRAVEL 70002195810001 IAW SRM 53-05 FIG 100, PAGE 600. LOCATED AND DRILLED 2EA ANGLES REPAIRS IAW SRM 51-10-4. INSTALLED REPAIR ANGLES & GUSSET IAW SRM SRM 53-05, FIG 100, PAGE 600 AND 51-30-5, 51-30-2. INSTALLED REPAIR TAG IAW PS 900-5-1 NO.4.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 78,272 hrs · 65,807 cycles

FUSELAGE CENTER SECTION FUEL AUXILIARY TANK LOWER STRINGER CRACKED, VIEWED THRU NR 5115A AND RBL 8. DOT 21-02. ACCOMPLISHED PERMANENT REPAIR ON CENTER FUEL AUXILIARY TANK LOWER STINGER RBL 8 IAW SRM 53-05, FIG 46. INSTALLED ID TAG IAW DPS 900-5-1 NR 4.

Part: STRINGER — CRACKED (FUEL CELL) · airframe 78,270 hrs · 65,806 cycles

FUSELAGE CENTER SECTION FUEL AUXILIARY TANK LOWER STRINGER CRACKED VIEWED THRU 5115A & RBL6. CUT OUT DAMAGE IAW SRM 53-05, FIG 46. NDT VERIFY NO CRACKS NOTED AT CUT OUT. FABRICATED TWO REPAIR ANGLES. FABRICATED ONE REPAIR FILLER IAW SRM 53-05, FIG 46. LOCATED AND DRILLED REPAIR ANGLES & FILLER IAW 53-05, FIG 46. INSTALLED REPAIR ANGLES & FILLER IAW SRM 51-10-5 AND 53-05 FIG 46. TREATED AND PRIMED ANGLES & FILLER & AREA TO INSTALL. ANGLES FABRICATED & HEAT TREATED.

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 78,270 hrs · 65,806 cycles

MAIN CABIN ALUMINUM FLOOR PANEL 72A FWD EDGE BENT, BUCKLED, CRACKED BS 734. FABRICATED STIFFENER AND FLOOR PANEL 72, IAW SRM 53-23-0, FIG 5.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 3,168 hrs · 2,780 cycles

WATER LEAKING FROM CEILING AT ROW 25. REPAIRED FUSELAGE SKIN LAP PER ERA 498220-14. (L/P 8497670, 0402767)

Part: O-RING — LEAKING (ACM) · airframe 3,030 hrs · 2,647 cycles

DURING CLIMBOUT, AFTER A REQUEST FOR INCREASED CABIN TEMP INBACK OF AIRCRAFT, STRONG ODOR (OIL SMELL) ENTERED CABIN, CAUSING FLIGHT ATTENDANTS TO GET SICK. WITH CABIN TEMP CONTROL RETURNED TO AUTO, SMELL WENT AWAY. SECURED AND REPLACED O-RING ON RIGHT PACK ACM SERVICE PORT FOR OIL LEAKAGE. REPLACED RIGHT MLG DOOR RETRACT ACTUATOR FOR LEAK TRAILING INTO APU INLET. CLEANED APU INLET, AND PERFORMED DUCT BURNOUT AND REPLACED COALESCER BAGS.

Part: PIN — LOOSE (CABIN) · airframe 76,373 hrs · 63,757 cycles

MAINTENANCE FOUND SEAT 1C EMERGENCY ESCAPE PATH LIGHTING INOPERATIVE. MAINTENANCE RECONNECTED LOOSE PIN ON SEAT BOTTOM. AIRCRAFT OK FOR SERVICE.

Part: SKIN — CRACKED (FUSELAGE) · airframe 76,363 hrs · 63,748 cycles

CRACK IN SKIN AT CANTED FRAME STA 1303 JUST ABOVE STRINGER 14 LT SIDE. CRACK IS APPROXIMATELY 2.6 INCHES IN LENGTH. REPAIRED CRACK IN SKIN PER DC-9 SRM 53-01 FIG 4 SHEET 4 AND DC-9 TRM 53-30-01-801-663A-A. JOB COMPLETE.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 76,010 hrs · 63,413 cycles

CABIN FLOOR PNL 37 FWD END TOP SKIN IS CRACKED, DENTED, AND CORRODED. RII: Y. REMOVED EXISTING REPAIR WITH CRACK AT CENTER PORTION OF PANEL 37. FURTHER EVALUATION FOUND CRACK IN PNL. STOP DRILL CRACK IN PANEL. FABRICATED AND INSTALLED REPAIR IAW SRM 51-30-2 PG 2. REMOVED CORROSION IAW WITHIN LIMITS IAW SRM 53-01 PG 8. TREATED AND PRIMED.

Part: SKIN — WORN (VERTICAL STAB) · airframe 76,010 hrs · 63,413 cycles

RT SIDE VERTICAL STABILIZER LEADING EDGE TIP SKIN HAS A DEEP WEAR AREA APPROX 22 INCH LONG, CAUSED BY BANANA FAIRING. BLENDED AREA REF SRM 55-01 FIG 1. LOWER BLEND FOUND OUT OF LIMITS & WAS TRIMMED OUT. A REPAIR DOUBLER MADE AND INSTALLED. REF COMPLIED ER/A49 3038-14 REV ORIG. ASSOCIATED ER/A 14-493038 ADDED FOR AC 0880.

Part: SKIN — DENTED (AILERON) · airframe 76,010 hrs · 63,413 cycles

LT WING AILERON UPPER SKIN WITH SEVERAL (7) DENTS FROM STA XRS 383 TO XRS 509 (MM067) RII: Y. PROCURED SERVICEABLE AILERON. AILERON REMOVED, REPLACED, AND ADJUSTED. RII INSPECTION COMPLETED (87761280001) & WC 2711-9800M, JOB 000-0022 (87761390001).

Part: SKIN — GOUGED (LE SLAT) · airframe 76,010 hrs · 63,413 cycles

RT WING NR 1 SLAT PANEL INBOARD LOWER SKIN WITH GOUGE DUE TO CHAFING WITH L/E (MMO89) BLENDED AREA ON LWR SKIN INBD ON RT WING NR 1 SLAT REF DC9 SRM 57-01 FIG 1. BLENDED AREA FOUND TO BE OUT OF LIMITS. REMOVED AND REPLACED NR 1 RT SLAT IAW AMM DC9-27-80-01-401-926A. SLAT, NR 1 RT, DC OFF 09-2780-9-0010 00998 ON 09-2780-9-0010 00925.

Part: SKIN — DENTED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

LWR FUSELAGE STA Y351, BETWEEN LONG 29LT AND LONG 30. EXT SKIN WITH DENT. RII: Y. DENT AT FUSELAGE AT STA Y351 BETWEEN LONG 29L AND LONG 30, OUT OF LIMITS. CUT OUT DAMAGE, FABRICATED, AND INSTALLED EXTERNAL REPAIR DOUBLER, FINGER DOUBLER, AND FILLER IAW SRM 53-04 FIG 12B SHEET 22 AT STA 351 TO STA 362.

Part: SKIN — DAMAGED (AILERON) · airframe 76,010 hrs · 63,413 cycles

RT WING AILERON INBOARD LATERAL FACE SKIN WITH HOLES ELONGATED (MM095). RII: Y PROCURED SERVICIABLE AILERON, AILERON REMOVED, REPLACED AND ADJUSTED. AILERON, RIGHT; OFF 09-5751-9-0002 47321 ON 09-5751-9-0002 47659.

Part: SKIN PANEL — DENTED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

DURING MCK AT SAT, 9 DENTS WERE FOUND IN THE FUSELAGE SKIN PANEL BETWEEN RT STA 297 - 333 AND L23R - L25R. ACCOMPLISHED PERMANENT REPAIR AT STA 298 TO STA 333.5 BETWEEN L-23R TO L-25R REFERENCE ERA 492119-14 REV ORIGINAL, 1. ASSOCIATED ER/A CHANGED FROM 13-492119 TO 14-492119 FOR AC 0880.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

STRINGER 17L CRACKED ON RADIUS NEAR UPPER ATTACHMENT FASTENER OF FRAME STA 237. REMOVED DAMAGED SECTION PER SRM 53-02 FIG 18, NDT NO DAMAGE NOTED. FABBED STRINGER SECTION AND SPLICE PER 53-02 FIG 18. TREATED AND PRIMED ALL PARTS PER SRM 51-10-3 PAGE 31-40. INSTALL REPAIR PARTS PER SRM 53-02 FIG 18 PAGE 49-52 AND INSTALLED ID TAG PER PS 900-5-1 NO 4 AT STA 237 AND LONGERON 17L.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

RT CUSP WEB AT STA 215 LIGHTENING HOLE HAS CRACK. STOP DRILLED CRACK AT FLOOR WEB BY LIGHTENING HOLE STA 218 IAW DC9 SRM 53-01 FIG 2. FABRICATED REPAIR DOUBLER IAW SRM 51-70-4 FIG 2. INSTALLED DOUBLER FLOOR WEB STA 215 IAW SRM 51-30-2.

Part: SKIN — DENTED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

LOWER FUSELAGE STA Y1115.5 BETWEEN LONGERON 27R AND 28R, EXTERNAL SKIN WITH DENT. COMPLIED WITH PERMANENT REPAIR PER ERA#492136-14 REV ORIGINAL AT FUSELAGE STA 1115.5 BETWEEN LONGERON 27R AND 28R.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 76,010 hrs · 63,413 cycles

PASS CABIN FLOOR PANEL NR 66 WITH ELONGATED HOLES. FABRICATED DOUBLER REPAIR WASHER IAW DC9 SRM 53-05 PG: 12 FIG 3 SRM 51-60-0 PG: 6 FIG 1 AND INSTALLED 3 DOUBLER REPAIR WASHER PERMACEL TAPE IAW AMM DC9 -A-53-20-01-201-925A-A AND SRM 53-05 PG 12 FIG 3.

Part: WEB — CRACKED (FUSELAGE) · airframe 76,010 hrs · 47,651 cycles

FLOOR WEB HAS CRACK INBD EDGE AT FS STA 261 RBL44. CUT OUT DAMAGED SECTION IAW SRM 51-70-4 FIG 2. FABRICATED REPAIR DOUBLER AND FILLER IAW SRM 51-70-4 FIG 2. INSTALLED PER SRM 51-30-2 AND SRM 51-70-4 FIG 2.

Part: SKIN — DENTED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

UPPER FUSELAGE STA 251 BETWEEN LONG 17 LT AND 18 LT EXTERNAL SKIN WITH DENT. RII:Y. CUT OUT DAMAGED AREA, NDT NO DAMAGE NOTED, FABRICATED TREATED AND INSTALLED ALL REPAIR PARTS IAW DC-9 SRM 53-04 FIG 12B PAGE 60F. INSTALLED ID TAG PER PS900-5-1 NR 04.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 76,010 hrs · 63,413 cycles

PASS CABIN FLOOR PANEL NR 72B, ELONGATED HOLES OFF A/C PART. FABRICATED AND INSTALLED 3 DOUBLER REPAIR WASHERS AND PERMACEL TAPE IAW AMM DC-9-A-53-20-01-201-925A-A AND SRM 53-05 PG 12 FIG 3.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 76,010 hrs · 63,413 cycles

PASS CABIN, FLOOR PANEL NR 67B, ELONGATED HOLES OFF A/C PART(JG022). FABRICATED AND INSTALLED 3 DOUBLER REPAIR WASHERS AND PERMACEL TAPE AT PASS CABIN FLOOR PANEL NR 67B IAW AMM DC9-A-53-20-01-201-925A-A AND SRM 53-05 PG 12 FIG 3.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 76,010 hrs · 63,413 cycles

PASS CABIN FLOOR PANEL NR 29 ELONGATED HOLES. FABRICATED AND INSTALLED 2 DOUBLER REPAIR WASHERS AND PERMACEL TAPE AT PASS CABIN FLOOR PANEL NR 29 IAW AMM DC9-A-53-20-01-201-925A-A AND SRM 53-05 PG 12 FIG 3.

Part: FLOORBOARD — CORRODED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

FLOORBOARD 19 HAS CORROSION (DT-09). REMOVED, FABRICATED, AND INSTALLED FLOORBOARD PANEL SKIN 19 AND 2 EA U-CHANNELS AT FLOORBOARD PANEL 19 IAW DC-9 SRM 53-23-0, FIG 3, SHT 3, PG 6, AND DC-9 SRM 51-30-2, PG 24.

Part: CONNECTOR — BROKEN (CABIN) · airframe 2,345 hrs · 1,973 cycles

MAINTENANCE FOUND EMERGENCY LIGHT CONNECTOR BROKEN AT FORWARD LEFT OVERWING EXIT SIDEWALL PANEL. MAINTENANCE REMOVED AND REPLACED EMERGENCY LIGHT CONNECTOR. OPERATIONAL CHECK WAS GOOD.

Part: FLOORBOARD — DAMAGED (CABIN) · airframe 76,010 hrs · 63,413 cycles

MAIN CABIN FLOOR BOARD NR 23, ENLONGATED HOLES, (5). FABRICATED 5 DOUBLER REPAIR WASHERS IAW DC9 SRM 53-05, PG 12, FIG 3, SRM 51-60-0, FIG 1, AND INSTALLED 5 DOUBLER. REPAIR WASHERS AND PERMACEL TAPE AT MAIN CABIN FLOOR BOARD NR 23 IAW AMM DC-9-A-53-20-01-201-925A-A AND SRM 53-05, PG 12, FIG 3.

Part: VANE — DENTED (TE FLAP) · airframe 76,010 hrs · 63,413 cycles

LT FLAP, MOVABLE VANE LWR SURFACE HAS A DENT. REPAIRED DENT IAW DC9 SRM 57-03, FIG 11, DC9 SRM 51-70-2, DC9 SRM 57-50-9, ITEM 2, FIG 1A, PG 3, DC9 SRM 57-03, PARA. 11B, DC9 SRM 51-70-2, DC9 SRM 51-10-3, PARA 21, DC9 SRM 51-70-2, DC9 SRM 51-10-3, REPAIRED BY CUTTING OUT DAMAGE 2 1/2 INCH BY 1 3/4 INCH AND INSTALLING A FILLER AND EXTERNAL DOUBLER IAW DC9 SRM 57-03, FIG 11.

Part: FLOORBOARD — CRACKED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

FLOORBOARD PANEL NR 69 LOWER STIFFENER CRACKED AT SCREW HOLES. REMOVED AND REPLACED LOWER STIFFENER "SUPPORT" ON FLOORBOARD PANEL NR 69 IAW SRM 51-30-2, PG 1-24, P/N 9957925-110, BATCH NR 0002052379.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 76,010 hrs · 63,413 cycles

PASS CABIN FLOOR PANEL NR 65, ENLONGATED HOLES. FABRICATED DOUBLER REPAIR WASHERS IAW DC9 SRM 53-05, PG 12, FIG 3, SRM 51-60-0, PG 6 FIG 1, AND INSTALLED 3 DOUBLER REPAIR WAS HERS AND PERMACEL TAPE AT PASS CABIN FLOOR PANEL NR 65, IAW AMM DC9-A-53-20-01-201-925A-A AND SRM 53-05, PG 12, FIG 3.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 76,010 hrs · 63,413 cycles

CABIN FLOOR PNL 36 FWD END TOP SKIN IS CORRODED, 77-40. BLENDED CORROSION AT MAIN CABIN FLOOR PNL 36 FWD END OF TOP SKIN ORG MAT. .040 IAW SRM 53-23-0, FIG 4 OUT OF LIMITS IAW SRM 53-01, FIG 1, SHT 3. REMOVED 5 HAT CHANNELS IAW SRM 51-32-0, FABED NEW TOP SKIN REF TRAVELER NR 87752940001, INSTALLED HAT CHANNELS IAW SRM 51-30-2, (5EA).

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 76,010 hrs · 63,413 cycles

CABIN FLOOR PNL 89 TOP SKIN TORN WITH PULLED THRU SCREW. CUTOUT DAMAGE FROM TOP SKIN AND FABRICATED DOUBLER FROM SHT 7075T6, .040, BATCH #0001590589, IAW SRM 51-70-4, PG 6, FIG 2 AND SRM 53-23-0, PG 9. TREATED AND PRIMED IAW SRM 51-10-3,PG 31, 40, AND INSTALLED DOUBLER IAW SRM 51-30-2, PG 1. NO CRACKS NOTED, INSTALLED ID TAG IAW PS 900-5-1, NR 4.

Part: FLOORBEAM — CORRODED (BS 237) · airframe 76,010 hrs · 63,413 cycles

CABIN FLOORBEAM ANGLE HAS CORROSION STA 237 BETWEEN BL-0AND LBL-22 BLENDED CORROSION OUT OF LIMITS PER SRM 53-01, FIG 1, SHEET 3, FORMED NEW FLOORBEAM PER SRM 53-01-2, TREATED AND PRIMED PER SRM 51-10-3, PARA 14 AND 21, REMOVED AND INSTALLED NEW FLOORBEAM PER SRM 51-30-5, STA 237, BL0 TO LBL 22.

Part: FLOOR PANEL — PUNCTURED (CABIN) · airframe 76,010 hrs · 63,413 cycles

CABIN FLOOR PNL 102B HAS PUNCTURES 77-27. CUT OUT DAMAGE ON FLOOR BOARD PANEL NR 102B IAW DC9 SRM 53-05, PG 11, SEC. B-B. FABRICATED AND INSTALLED FLOOR BOARD PANEL NR 102B. REPAIR DOUBLER IAW DC9 SRM 51-30-2, PGS 1-2, 4, 26B.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

CABIN SEAT TRACK HAS AREAS OF CORROSION FROM STA 200 TO 315,LBL 44. BLENDED CORROSION AT 3 AREAS STA 210, 245, AND 260 ON SEAT TRACK LBL 44- OUT OF LIMITS, PER SRM 53-05, FIG 4B, SHEET 1. REMOVED AND REPLACED DAMAGED SECTION FROM STA 200 TO 268 AT PREVIOUS SPLICE REPAIR REF SRM 53-05, PG 32 AND SRM 51-30-1, PG 11, 3 EA AREAS OF SEAT TRACK REWORKED AT STA 210, 245, AND 260 OUT OF LIMITS.

Part: SKIN — CORRODED (FLOOR PANEL) · airframe 76,010 hrs · 63,413 cycles

CABIN FLOOR PNL 32 FWD END TOP SKIN IS CORRODED. FURTHER INSPECTION FOUND CRACK ON PNL 32 FWD END TOP SKIN, NO CORROSION NOTED, CUT OUT DAMAGE PER SRM 53-01, PG 25, FABRICATED REPAIR PARTS FROM 7075T6, .020" BATCH #0001740880PER SRM 53-01, PG 25, FIG 4. TREATED AND PRIMED REPAIR PARTS PER SRM 51-10-3, PG 31, PARA 21; INSTALLED REPAIR PARTS PER SRM 53-01, PG 2 5, FIG 4, PNL 32.

Part: FLOORBOARD — DAMAGED (CABIN) · airframe 76,010 hrs · 63,413 cycles

FLOORBOARD, NR 102C LT AFT CORNER IS BROKEN CUT OUT DAMAGED AREA OF FLOORBOARD NR 102C IAW SRM 51-70-4, FABED (1) EA DOUBLER AND (1) EA SPLICE MAT, IAW SRM 51-70-4, FIG 1, PAGE 1, TREATED AND PRIMED IAW SRM 51-10-3, PAGE 27-31, INST REPAIR IAW SRM 51-70-4. COMP, 478426, INSP BY AND RII COMPL BY 066494.

Part: FLOORBOARD — CORRODED (CABIN) · airframe 76,010 hrs · 63,413 cycles

FLOORBOARD NR 20 METAL CORROSION ENTIRE PIECE. RECEIVED NEW PANEL NR 20, PART NR 09-5300-3-0219. LOCATED AND DRILLED IAW SRM 51-30-0, FIG 3, PG 31. PRIMED NEW FLOORBOARD IAW SRM 51-10-3, PAGE 31, PARA 14.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

CABIN SEAT TRACK HAS AREAS OF CORROSION FROM STA 200 TO 315, RBL-44. REMOVED CORROSION AND FOUND OUT OF LIMITS IAW SRM 53-05, FIG 4B FROM STA 284 TO STA 200, RBL 44 MAIN CABIN SEAT TRACK. CUT OUT DAMAGED SECTION SEAT TRACK T STA 284 TO STA 200 RBL 44 IAW SRM 53-05, FIG 4F. REPLACED SEAT TRACK SECTION IAW SRM 53-05, FIG 4F, IAW SRM 51-30-1, SRM 51-30-5.

Part: FLOOR SUPPORT — CORRODED (BS 160-313) · airframe 76,010 hrs · 63,413 cycles

CABIN FLOOR SUPPORT ANGLE HAS CORROSION FROM BS 160 TO 313 AT BL-0. BLENDED OUT CORROSION MAIN CABIN FLOOR SUPPORT ANGLE AT BL0 BS 160 TO BS 313 IAW SRM 51-10-3 FROM BS 160 TO BS 218 WITHIN LIMITS IAW SRM 53-01, FIG 1, FROM STA 218 TO 285, OUT OF LIMITS AT BS 238 IAW SRM 53-01, FIG 1. REMOVED AND REPLACED SUPPORT ANGLE MAIN CABIN BL0 FROM BS 218 TO BS 285 AT EXISTING SPLICE, IAW SRM 51-40-4, SRM 51-30-5.

Part: TIE CLIP — CRACKED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

TIE CLIP CRACKED AT LT SIDE AFT WALL STA 1136, BELOW LONGERON 14L (MAJOR REPAIR) RII: Y FOUND IN COMING ELONGATED HOLE ON SKIN. EXTERNAL REPAIR DOUBLER AND FILLER INSTALLED TOGETHER WITH THE NEW TIE CLIPS (ANGLES). ACCOMPLISHED ER/A 493033-14, REV ORIG, 2 EA SPLICES AND A NEW LONGERON SECTION WERE INSTALLED ON LONG 14L PER REF DC9 SRM 53-02, PAGE 49, 50.

Part: FLOORBEAM — CORRODED (BS 294 BL 0-22R) · airframe 76,010 hrs · 63,413 cycles

FLOORBEAM UPPER CHORD HAS FRETTING WEAR ON REPAIR, STA 294, BETWEEN BL-0 AND RBL-22. REMOVED 2 SHIMS ON FLOORBEAM UPPER CHORD IAW SRM 51-30-5. FABRICATED 2 SHIMS, IAW SRM 53-05 FIG 20, PG 98, PRIMED IAW SRM 51-10-3, PG 31. INSTALLED 2 SHIMS, FLOORBEAM UPPER CHORD, IAW SRM 51-10-3, PG12, PARA 7. FRETTING WEAR WAS FOUND TO BE ON 2 SHIMS, NOT ON EXIST REPAIR.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

FLOOR SUPPORT ANGLE HAS CORROSION AND LAV ATTACH BOLT SHEARED IN FITTING, FROM STA 200 TO 218, RBL-19. REMOVED AND REPLACED FLOOR SUPPORT ANGLE WITH "EXTRUSION" P/N 00-02-10-3-3672, AT STA 200 TO 218, RBL 19, IAW DWG 94FS481235 AND SRM 51-30-5, PG 12, PARA 7. REMOVED SHEARED BOLTS AND FITTING STA 209, RBL 19, AND INSTALLED FITTING STA 209, RBL 19, IAW SRM 51-30-1.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 76,010 hrs · 63,413 cycles

CABIN FLOOR PNL 81B TOP SKIN IS TORN OUT AT ATTACH SCREWS. CUT OUT DAMAGE FROM PANEL 81B TOP SKIN IAW SRM 53-05, PTG 10, FIG 1, NO CRACKS NOTED, FABRICATED DOUBLER AND FILLER. INSTALLED REPAIR PARTS IAW SRM 53-05, FIG 1, PG 10, AND RII COMPLETED BY 883716, SAA QC 041, 21 MAY 11. INSTALLED ID TAG IAW PS 900-5-1, NR 4.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

CORROSION LEVEL: 2. LAV FLOOR SUPPORT FITTING HAS HEAVY CORROSION AND ATTACH BOLT HOLE THREADS DAMAGED IN FITTING, STA 200, LBL 44 RL005. REMOVED AND REPLACED LAV SUPPORT FITTING AT STA 200, LBL 44, IAW SRM DC9 51-30-5, FIG 1, PG 2, 12, 29, PARA 7, SRM DC9 51-30-1, PG 12 AND EO DOC 94FS481230, REV A.

Part: SEAT TRACK — CORRODED (BS 200-315) · airframe 76,010 hrs · 63,413 cycles

CABIN SEAT TRACK HAS AREAS OF CORROSION FROM BS 200 TO 315, RBL 22. REMOVED CORROSION AT (3 AREAS) STA 237, 285, AND 294 ON SEAT TRACK RBL 22, OUT OF LIMITS IAW SRM 53-05, FIG 4B, SHEET 1. REMOVED SEAT TRACK RECEIVED NEW SEAT TRACK LOCATED AND DRILLED, ALL IAW SRM 51-30-0. INSTALLED NEW SEAT TRACK IAW SRM 51-30-5, FIG 2, PAGE 3, AND SRM 51-30-1.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 76,010 hrs · 63,413 cycles

CABIN FLOOR PNL 76 TOP SKIN HAS CRACK AT EDGE REMOVED EDGE DAMAGE AT CABIN FLOOR PANEL 76, ORG MAT 18 INCHES LONG, MAT LOSS .35, WITHIN LIMITS IAW SRM 53-01, PG 6. FOUND CRACK ON AFT END OF FLOOR PANEL 76, CUT OUT DAMAGE, FABRICATED DOUBLER IAW SRM 51-70-04, PG 1, FIG 2, SRM 53-23-0, NO CRACKS. TREATED AND PRIMED DOUBLER IAW SRM 51-10-3, PG 31, 40, AND INST DOUBLER IAW SRM 51-30-2. INSTALLED ID TAG IAW PS 099-5-1, NR 4.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

CABIN SEAT TRACK HAS AREAS OF CORROSION FROM STA 200 TO 315,LBL -22. BLENDED OUT CORROSION AREAS OUT LIMITS PER SRM 53-05, FIG 4B, SHEET 1. REMOVED AND REPLACED SEAT TRACK AT MAIN CABIN STA 200-300 LBL 22 PER SRM 53-05, FIG 4F. 4EA AREAS OF SEAT TRACK REWORKED AT STA 200, 245, 270, AND 300 WERE FOUND OUT OF LIMITS.

Part: FLOOR SUPPORT — CORRODED (STA 160-200) · airframe 76,010 hrs · 63,413 cycles

CABIN FLOOR SUPPORT ANGLE HAS CORROSION STA 160 TO 200, LBL 44. BLENDED CORROSION ON FLOOR SUPPORT, OUT OF LIMITS, PER SRM 53-01, FIG 1, SHEET 3. REMOVED AND REPLACED FLOOR SUPPORT PER SRM 51-30-5, PG 1-29.

Part: FLOORBEAM — CORRODED (BS 200) · airframe 76,010 hrs · 63,413 cycles

FLOOR SUPPORT ANGLE HAS LIGHT CORROSION STA 200 BETWEEN RBL 22 TO RBL 44 RL017. BLENDED OUT CORROSION OUT OF LIMITS, IAW SRM 53-01, FIG 1. REMOVED SUPPORT ANGLE IAW SRM 51-30-5, PG 1. REPLACED WITH NEW SUPPORT ANGLE IAW DC9 DWG S2652479, LOCATED AND DRILLED IAW SRM 51-10-4, INSTALLED IAW SRM 51-30-5.

Part: FLOORBEAM — CORRODED (BS 200) · airframe 76,010 hrs · 63,413 cycles

CABIN FLOOR SUPPORT ANGLE HAS CORROSION BS 200 BETWEEN RBL 22 AND BL 0 RL018. BLENDED OUT CORROSION MAIN CABIN FLOOR SUPPORT ANGLE IAW SRM 51-10-3 PARA 26, FOUND OUT OF LIMITS IAW SRM 53-01, FIG 1. REMOVED AND REPLACED SUPPORT ANGLE DWGS2652479 BATCH 0002030692 IAW SRM 51-30-5.

Part: SKIN — CRACKED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

LWR FUSELAGE, LT SIDE, STA Y130.5, Z22, EXTERNAL EXISTING DOUBLER WITH CRACK. REMOVED EXISTING DOUBLER IAW SRM 51-30-2. LOCATED AND DRILLED NEW DOUBLER IAW SRM 51-10-4, PG 1. INSTALLED DOUBLER STA IAW SRM 51-10-4, PG 1 AND SRM 53-04, FIG 24, PG 1.

Part: FRAME — CORRODED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

FWD CARGO AREA STA 600 BETWEEN L27L AND L27R, EVIDENCE OF CORROSION ON METAL FRAME FWD OF AUX FUEL TANK. OUT OF LIMITS AT IAW SRM 51-01, FIG 1. REMOVED DAMAGED FLOOR SUPPORT ANGLE SECTION IAW SRM 51-70-5. FABRICATED REPLACEMENT FLOOR SUPPORT ANGLE IAW DWG 5924207-21, FROM AND 2 EA REPAIR ANGLES IAW SRM 51-70-5, FIG 1. TREATED, PRIMED AND INSTALLED ALL REPAIR PARTS IAW SRM 51-70-5, FIG 1, STA 605, L27L TO L27R.

Part: SKIN — DENTED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

LWR FUSELAGE, RT SIDE, BETWEEN STA Y88 AND STA Y90, -Z48, EXTERNAL SKIN WITH DENTS. REPAIRED LWR FUSELAGE RT SIDE EXTERNAL SKIN IAW DC9 SRM 53-01, PG 25, FIG 4, SHEET 4, CUT OUT DAMAGE, L=4.00 W=2.00, HFEC INSPECTION NOTED NO DEFECTS AROUND CUTOUT AND OPEN HOLE. CUTOUT DAMAGED AREA IAW DC9 SRM 53-01, PG 25, FIG 4, SHT 4. INTERNAL REPAIR DOUBLER.

Part: SEAT TRACK — DAMAGED (BS 674) · airframe 76,010 hrs · 63,413 cycles

RT INBOARD SEAT TRACK AT STA 674, CROWN AREA FOUND TO BE OUT OF LIMITS. CUT OUT DAMAGED SEAT TRACK SECTION AT STA 664, TO 684, RT INBD LOCATION, FABRICATED AND INSTALLED REPAIR PARTS IAW DC9 SRM 53-05, FIG 4F, PG 1 TO 11, SEAT TRACK SPLICE REPAIR.

Part: SKIN — DENTED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

LWR FUSELAGE, STA Y314, BETWEEN LONG 27 LT AND LONG 28 LT, EXT SKIN WITH DENT. FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-04, CONDITION 1A, STEP 3. CUT OUT DAMAGED SKIN. FABRICATED AND INST INTERNAL REPAIR DOUBLER IDENTIFIED REPAIR AT STA Y314 BETWEEN L27 AND L28 LT IAW PS 900-5-1, NR 4.

Part: SKIN — DENTED (BS 246.5) · airframe 76,010 hrs · 63,413 cycles

LWR FUSELAGE, STA Y246.5, BETWEEN LONG 26 LT AND LONG 27 LT, EXTERNAL SKIN WITH TOOL MARK. DENT OUT OF LIMITS PER SRM 53-04, REMOVED DAMAGE PER SRM DC9 53-04. FABRICATED REPAIR PARTS PER SRM 53-04, FIG 38, SHEET 33, PG 218W, VIEW "U" TREATED AND PRIMED REPAIR PARTS PER SRM DC9 51-10-3, AND INSTALLED PARTS PER DC9 SRM 53-04, AND SRM 51-30-5.

Part: TAB — DELAMINATED (ELEVATOR) · airframe 76,010 hrs · 63,413 cycles

RT GEARED TAB HAS DELAMINATION ON LOWER OTBD END REMOVED AND REPLACED RT ELEVATOR GEARED TAB IAW DC9-A-30-04-20 1-925A-A.

Part: SKIN — DENTED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

LOWER FUSELAGE, STA Y166 BETWEEN LONGERON 24 RT AND LONG 25 RT, EXTERNAL SKIN WITH DENT MEASURED DENT AT STA Y166 BETWEEN L24 AND L25 RT, FOUND TO BE OUT OF LIMITS PER SRM 53-04, FIG 38, TABLE C, CONDITION 1A, STEP 3. FABRICATED AND INSTALLED INTERNAL REPAIR DOUBLER PER SRM 53-04, FIG 38.

Part: SKIN — DENTED (FUSELAGE) · airframe 76,010 hrs · 63,413 cycles

LOWER FUSELAGE, STA Y294, BETWEEN LONG 28 RT AND LONG 29 RT, EXTERNAL SKIN WITH A DENT. INSPECTED DENT SKIN AT STA Y294 BETWEEN LONG 28 RT AND L29 RT, FOUND TO BE OUT OF LIMITS PER SRM 53-04, FIG 38, CONDITION 1A. FABRICATED AND INSTALLED INTERNAL PERMANENT DOUBLER PER SRM 53-04, FIG 38, PG 218S (CUT OUT DAMAGED AREA OF SKIN AT STA Y294 BETWEEN L28 RT AND L29 RT IAW SRM 53-04, FIG 38, PG 218)

Part: FITTING — BROKEN (NR 4 SLAT TRACK) · airframe 75,678 hrs · 63,132 cycles

RIGHT WING NR 4 SLAT OUTBOARD TRACK HAS BROKEN FITTING ON SLATSIDE. REMOVED AND REPLACED RT WING NR 4 SLAT PER WORKCARD 5740-9826M-RT CHECKS GOOD.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 74,605 hrs · 62,228 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROW 6 OF THE CABIN WAS INOPERATIVE. MAINTENANCE REPLACED THE LIGHT ASSEMBLY AND FUNCTIONALLY CHECKED IT.

Part: BATTERY — DISCHARGED (CABIN) · airframe 71,188 hrs · 59,247 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 9-13 OF THE CABIN WERE INOPERATIVE. MX REPLACED THE BATTERIES. OPS CHECK WAS GOOD.

Part: DIODE — FAILED (EMERGENCY LIGHT) · airframe 70,625 hrs · 58,715 cycles

DURING THE LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN ROWS 5-8 OF THE CABIN WERE INOPERATIVE. MAINTENANCE REPLACED THE "DIODE IN THE FWD RT HAND OVERWING EXIT IDENT". OPERATIONAL CHECK WAS GOOD. (A)

Part: MANIFOLD — LEAKING (NR 2 ENG FUEL) · airframe 70,283 hrs · 58,390 cycles

DURING TAKEOFF ENGINE NR 2 EPR ROLLED BACK FROM 2.17 TO 2.10. FLIGHT CREW ADVANCED ENG NR 2 THROTTLE TO STOPS BUT EPR REMAINED AT 2.10. AFTER TAKEOFF ENGINE NR 2 APPEARED TO FUNCTION NORMAL REMAINDER OF FLIGHT. AT DESTINATION MAINTENANCE NOTICED ENG NR 2 EXHAUST PIPE FULL OF FUEL, OPENED COWLS AND FOUND THEM FULL OF FUEL AND FUEL LEAKING THROUGH THE ENGINE CASE. SECONDARY FUEL MANIFOLD LEAK WAS DISCOVERED. ENGINE REPLACED.

Part: SKIN — DENTED (FUSELAGE) · airframe 68,293 hrs · 56,624 cycles

CATERING REPORTED DENT FWD OF DOOR 1R AT FUSELAGE STATION NR 130 STRINGER NR 17. INSPECTED DENT FOUND TO BE AT WIDTH 1INCH, LENGTH 1 13/16, DEPTH .062 (HFEC FOUND NO CRACKS IAW NDTM 06-10-01 261453 NW204) INSPECTED DENT AT B STA 129-130 AND LONGERON 17R AND FOUND SKIN CREASED AND OUT OF LIMITS IAW DC9 SRM 53-04 FIG 38 CONDITION 2. CUT OUT DAMAGED SKIN .950" ROUND FABRICATED AND INSTALLED PERMANENT INTERNAL REPAIR IAW DC9 SRM 53-04 FIG 38. VIEW "T" PG 218V. ALL WORK ACCOMPLISHED ON N/R 1A/92 (W/0 87770550001) CHANGED TO SDR REPORTABLE OK TO CLOSE LOG.

Part: MANIFOLD — CRACKED (FUEL SYSTEM) · airframe 68,093 hrs · 56,447 cycles

DURING TAKEOFF, THE TOWER REPORTED EXCESSIVE SMOKE FROM THE NR 1 ENGINE. FLIGHT CREW ALSO REPORTED HIGHER FUEL FLOW FROM THE NR 1 ENGINE. THE FLIGHT CONTINUED TO DTW AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND A CRACKED PRIMARY FUEL MANIFOLD. REMOVED AND REPLACED THE NR 1 ENGINE, TESTED AND RETURNED TO SERVICE.

Part: TIRE — SEPARATED (RT MLG) · airframe 66,236 hrs · 54,824 cycles

RT MAIN LANDING GEAR, NR 3 TIRE AND WHEEL SEPARATED FROM THE AXLE ON TAKEOFF OUT OF MEM. NO REPORTS OF ANY DEBRIS IMPACTING ON THE FUSELAGE OR ENGINES AND NO SECONDARY DAMAGE NOTED. THE AIRCRAFT ACCOMPLISHED A RETURN TO BASE AFTER FUEL BURN OFF, AND LANDED SAFELY WITHOUT FURTHER INCIDENT, BACK AT MEM. THE RIGHT MAIN LANDING GEAR WAS INSPECTED AND NEW WHEELS AND TIRES WERE INSTALLED IN THE NR 3 AND NR 4 POSITIONS. THE AIRCRAFT HAS BEEN RELEASED FOR SERVICE.

Part: WIRE — DAMAGED (RT T/R) · airframe 62,155 hrs · 51,122 cycles

DURING TAKEOFF ROLL AT 116 KNOTS, THE RIGHT ENGINE THRUST REVERSER UNLOCK LIGHT ILLUMINATED. CREW ABORTED TAKEOFF AND RETURNED TO THE GATE. MAINTENANCE REPAIRED DAMAGED WIRES AND REPLACED THE CANNON PLUG FOR THE RIGHT ENGINE THRUST REVERSER LATCH SWITCH. ENGINE OPERATIONALLY CHECKED OK. AIRCRAFT RETURNED TO SERVICE.

Part: SMOKE — DETECTED (LAVATORY) · airframe 49,814 hrs · 49,005 cycles

BOTH AFT LAVATORY SMOKE DETECTORS ACTIVATED WHILE EN ROUTE. FLIGHT ATTENDANTS REPORTED BLUE SMOKE IN LAVS. APU WAS NOT OPERATING AND NO INDICATION OF PACK MALFUNCTIONS. ELECTRICAL SMELL WAS REPORTED. IDLE DESCENT BEGAN AT 10,000 FEET. NO POWER TO SMOKE RELATED ISSUES. FLIGHT LANDED SAFELY AT DTW. MAINTENANCE INSPECTED AFT LAVS AND CABIN OVERHEAD WITH ALL FOUND NORMAL. AIRCRAFT RETURNED TO SERVICE.

Part: SMOKE — DETECTED (CABIN) · airframe 58,742 hrs · 48,038 cycles

AFTER TAKEOFF FROM DTW, THE AFT LAVATORY SMOKE DETECTOR WENT INTO ALARM AND THE CABIN WAS REPORTED TO HAVE SMOKE IN IT. FLIGHT RETURNED TO THE FIELD AND LANDED WITHOUT INCIDENT. NO EMERGENCY EVACUATION. MAINTENANCE WAS UNABLE TO DUPLICATE THE SMOKE. A DIVERTER VALVE DUCT WAS FOUND TORN AND HAS BEEN REPLACED AND BOTH WATER SEPARATOR COALESCER BAGS HAVE BEEN REPLACED. THE AIRCRAFT HAS RETURNED TO SERVICE.

Part: SKIN — CRACKED (LE FLAP) · airframe 58,109 hrs · 47,473 cycles

FLAP LEADING EDGE JUST AFT OF NR 2 FLAP HINGE IS CRACKED. REPAIRED PER EA 98-172453. L/P 1437664

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 58,109 hrs · 47,473 cycles

SUBFLOOR UNDER PANELS 71 & 72 OUTBOARD HORIZONTAL ANGLE ON TOP OF CENTER TANK CRACKED AT STA 755. REPAIRED PER EA 98-172430 AND SRM 51-30-5. L/P 1437803

Part: FRAME — CRACKED (FUSELAGE) · airframe 58,109 hrs · 47,473 cycles

CANTED FRAME CRACKED AT STA 1314 AT SKIN SPLICE. STOP DRILLED 3 CRACK, PERFORMED INSPECTION, TO VERIFY CONTAINMENT. REFERENCE 0M200 AND EA 98172407. LOG PAGE 1433037.

Part: BATTERIES — DISCHARGED (COCKPIT)

DURING LINE MAINTENANCE INSPECTION, FOUND COCKPIT AND GALLEY AREA EMERGENCY LIGHTS INOPERATIVE. REPLACED BATTERIES, OPERATIONAL CHECK NORMAL.

Part: BATTERY — DISCHARGED (CABIN)

FLIGHT ATTENDANT REPORTED EMERGENCY FLASHLIGHT NOT BLINKING AT ENTRY DOOR 1L. MAINTENANCE REPLACED BATTERIES. OPERATIONAL CHECK NORMAL.

Part: BATTERY PACK — DISCHARGED (CABIN)

DURING LINE CHECK, FOUND CEILING EMERGENCY LIGHTS AT SEAT ROWS 21 AND 23 INOPERATIVE. MAINTENANCE REPLACED BATTERY PACK, OPERATIONAL CHECK NORMAL.

Part: LIGHT — INOPERATIVE (CABIN)

PILOT REPORTED EMERGENCY AISLE LIGHTS REMAINED ILLUMINATED FROM SEAT ROW 20, AFT REGARDLESS OF FLIGHT DECK LIGHT SWITCH POSITION. MAINTENANCE REPLACED THE LIGHT ASSEMBLY AT SEAT 15D, OPERATIONAL CHECK NORMAL.

Part: ENGINE — FAILED (LEFT)

DURING TAKEOFF ROLL AT 95 KNOTS, A TRAILING AIRCRAFT REPORTED SPARKS EXITING FROM THE LEFT ENGINE. CREW ABORTED TAKEOFF AND RETURNED TO THE GATE. MAINTENANCE REPLACED THE ENGINE DUE TO FOD. AIRCRAFT RETURNED TO SERVICE.

Part: WIRE — BROKEN (AUDIO PANEL)

FLIGHT CREW SMELLED SMOKE UPON ENTERING COCKPIT AT GATE. MAINTENANCE FOUND BROKEN WIRING CAUSING ARC AT OBSERVER'S AUDIO CONTROL PANEL. REPAIRED WIRING, OPERATIONAL CHECK NORMAL.

Part: FUEL HEAT VALVE — INOPERATIVE (LT ENGINE)

DURING CLIMB, THE LEFT ENGINE FUEL TEMPERATURE INDICATION EXCEEDED NORMAL OPERATING LIMITS. CREW RETURNED TO MSP AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED THE LEFT ENGINE FUEL HEAT VALVE. OPERATIONAL CHECK OK. AIRCRAFT RETURNED TO SERVICE.

Part: CONNECTOR — SHORTED (NR 2 GALLEY)

FLIGHT ATTENDANT REPORTED NR 2 GALLEY OVEN CIRCUIT BREAKER POPPED OUT. TRIED TO RESET AND SPARKS EMITTED FROM BREAKER. MAINTENANCE INSPECTED AND FOUND SHORT IN OVEN CONNECTOR. OVEN REMAINS DEFERRED FOR CONNECTOR REPLACEMENT.

Part: SKIN — CORRODED (BS 503-522)

DURING H CHECK, FOUND CORROSION ON INNER SURFACE OF SKIN FS 503 - 522, LONGERON 29R - 30. REPAIRED PER EA 98-113024.

Part: FITTING — CORRODED (BS 700)

DURING H-CHECK, FOUND A CRACK IN LONGERON 30 END FITTING FS 700. REPLACED FITTING (P/N 3924029-501N) PER SRM 51-30-5.

Part: CONTROLLER — FAILED (CABIN)

EN ROUTE TO MKE AT FL290, CABIN PRESSURE LIGHT ILLUMINATED. CABIN ALTITUDE READ 9200, DESCENDED TO 10,000 FEET AND FOLLOWED COCKPIT OPERATING MANUAL PROCEDURES. MASKS DID NOT DEPLOY. FLIGHT CONTINUED TO MKE AND LANDED WITHOUT INCIDENT. REPLACED CABIN PRESSURE CONTROLLER PER MM 21-32-0, SYSTEM OPERATIONAL CHECK OK.

Part: BATTERIES — DISCHARGED (CABIN)

DURING LINE CHECK, FOUND TWO OVERWING EMERGENCY LIGHTS WILL NOT ILLUMINATE DURING TEST. REPLACED BATTERIES. OPERATIONAL CHECK OK.

Part: WARNING HORN — MALFUNCTIONED (COCKPIT)

UPON ADVANCING THROTTLES FOR TAKEOFF, RECEIVED TAKEOFF WARNING HORN AT ABOUT 20 KTS. RETURNED TO THE GATE. REPLACED TAKEOFF WARNING HORN, OPERATIONAL CHECK OK.

Part: BATTERY PACK — DISCHARGED (CABIN)

DURING LINE CHECK, FOUND OVERHEAD EMERGENCY LIGHT DIM IN MAIN CABIN. REPLACED BATTERY PACK. OPERATIONAL CHECK OK.

Part: PT2 PROBE — ICED UP (LT/RT ENGINES)

EPR INDICATION LOW ON BOTH ENGINES DURING TAKEOFF. THE TAKEOFF WAS ABORTED AND THE FLIGHT RETURNED TO THE GATE. MAINTENANCE CLEARED ICE DEPOSITS FROM BOTH PT2 PROBES. ENGINE INDICATION RETURNED TO NORMAL ON SUBSEQUENT RUNUP.

Part: OIL FILTER — DIRTY (NR 2 ENGINE)

AFTER 15 MINUTES OF TAXI TIME, THE NR 2 ENGINE OIL FILTER CLOG WARNING LIGHT ILLUMINATED. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO THE GATE. MAINTENANCE INSPECTED THE OIL FILTER FOR ABNORMALITIES, NONE NOTED. A NEW OIL FILTER WAS INSTALLED AND NO DISCREPANCIES NOTED ON RUNUP.

Part: BULKHEAD ANGLE — CRACKED (FS 37)

DURING L-CHECK, FOUND A CRACK IN THE FS 37 BULKHEAD SUPPORT ANGLE. REPAIRED ANGLE (P/N 9911500-509), PER EA 99-102613.

Part: GENERATOR — FAILED (RIGHT)

DURING CRUISE, THE RIGHT GENERATOR FAILED FOLLOWED BY AN AIRCRAFT CROSSTIE LOCKOUT. FOLLOWED COCKPIT OPERATIONAL MANUAL PROCEDURES FOR BOTH FAULTS. THE AIRCRAFT DIVERTED TO TYS AND LANDED WITHOUT INCIDENT. REPLACED THE RIGHT ENGINE CONSTANT SPEED DRIVE AND GENERATOR, OPERATIONAL CHECK GOOD.

Part: ACTUATOR — FAILED (NLG)

VIBRATION AND NOISE FROM NOSE GEAR AREA OCCURRED ON GEAR RETRACTION AFTER TAKEOFF. NOSE GEAR AND RED UNSAFE LIGHT ALSO ILLUMINATED. RECYCLED GEAR SEVERAL TIMES AND LIGHT REMAINED ON. PERFORMED EMERGENCY GEAR EXTENSION PROCEDURES AND RETURNED TO RDU. AIRCRAFT LANDED WITHOUT INCIDENT. FOUND DAMAGE TO FORWARD NOSE GEAR DOOR, RELEASE ACTUATOR, AND DOOR STOP CABLE. IT IS SUSPECTED THAT THE DOOR RELEASE ACTUATOR HAD FAILED. REPLACED CABLE, ACTUATOR, AND REPAIRED DOOR. INSPECTED NOSE GEAR PROXIMITY SENSOR FOR ADJUSTMENT AND SECURITY. ALL CHECKED GOOD. PERFORMED RETRACTION TEST OF NOSE GEAR SEVERAL TIMES. NO PROBLEMS WERE FOUND. AIRCRAFT RETURNED TO SERVICE.

Part: LATCHES — OUT OF RIG (TAILCONE)

DURING LINE CHECK, FOUND THAT EXCESSIVE FORCE WAS REQUIRED TO RELEASE THE TAILCONE. RERIGGED THE TAILCONE, CHECKED OK.

Part: CONNECTOR — CONTAMINATED (ACCESSORY DOOR)

AFTER TAKEOFF ORD-DTW, THE FORWARD ACCESSORY COMPARTMENT DOOR WARNING LIGHT ILLUMINATED. RETURNED TO ORD WITHOUT FURTHER INCIDENT. THE WARNING LIGHT EXTINGUISHED ON LANDING AND REMAINED OUT DURING TAXI. CLEANED DOOR SWITCH CONNECTION AND RELAMPED ANNUNCIATOR AS PRECAUTIONARY. INDICATION AND DOOR LATCHING MECHANISM CHECKED OK.