N969AT

Part: LIGHT — DAMAGED (CABIN) · airframe 47,370 hrs · 32,353 cycles

THE EMERGENCY SEAT MOUNTED LIGHTING IS DAMAGED AND INOPERATIVE AT SEAT 27C. MAINTENANCE RESECURED THE PANEL. OK FOR SERVICE.

Part: SIGN — LOOSE (CABIN) · airframe 47,370 hrs · 32,353 cycles

THE EMERGENCY EXIT SIGN COVER AT DOOR 1L IS LOOSE. MAINTENANCE RESECURED EXIT THE EEPL SIGN AT 1L DOOR. AIRCRAT IS OK FOR SERVICE.

Part: ENGINE — ODOR (NR 2) · airframe 45,921 hrs · 31,340 cycles

ODOR PREVALENT AFTER TAKEOFF AND THROUGHOUT FLIGHT. ODOR STRONGEST FROM RT PACK ON THE NR 2 ENGINE BLEED. NO CONTAMINATION WAS FOUND. FOUND TURBINE OIL ODOR ISOLATED TO THE NR 2 ENGINE. SUSPECT ISSUE WITH BUFFER AIR VALVE. REPLACED NR 2 ENGINE BUFFER AIR VALVE IAW AMM 75-22-01. RAN THE NR 2 ENGINE AT HIGH POWER, OIL ODOR IN CABIN WITH RT PACK RUNNING. NO OIL ODOR FROM THE NR 1 ENGINE. REPLACED THE NR 2 ENGINE IAW AMDS 7100-9901-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,233 hrs · 29,451 cycles

CORROSION ON FLOOR SUPPORT X=-52 BTW STA Y=132 TO Y=-148. AT COCKPIT FLOOR STRUCTURE. FLOOR SUPPORT WAS REPLACED PER DRAWING 9936533 ITEM 35 REV CM AND SRM 51-41-02.

Part: WINDOW FRAME — CRACKED (COCKPIT) · airframe 43,126 hrs · 29,380 cycles

CRACK ON LWR FWD SECTION OF RT SLIDE WINDOW COUNTER FRAME AT COCKPIT. DAMAGE AREA WAS REPAIRED PER ETI -17-16-170 REV 1 AND ER/A 551770-14 REV ORIG.

Part: PAN — CRACKED (BS 388) · airframe 43,126 hrs · 29,380 cycles

CRACK ON INBD AND OUTBD PAN LOWER EDGE BS 388 AT FWD CARGO DOOR. INBD & OUTBD PAN LOWER EDGE WAS REPAIRED IAW ETI-17-16-161 REV 1 AND ER/A 551739-14 REV ORIGINAL.

Part: VANE — DENTED (LT WING TE FLAP) · airframe 43,126 hrs · 29,380 cycles

SEVERAL DENTS ON AFT MOVABLE FLAP VANE ON THE LT WING. THE FLAP VANE WAS REPAIRED IAW SRM 57-53-01 REP.1 PARAGRAPH 4.

Part: SKIN — CRACKED (BS 1133) · airframe 43,126 hrs · 29,380 cycles

CRACKED FUSELAGE SKIN BS 1133 BETWEEN LONGERONS 2-3L. THE SKIN WAS REPAIRED IAW ETI-17-16-139 REV. 3 AND ER/A 551722-14AD REV. ORIGINAL.

Part: FITTING — CRACKED (FUSELAGE) · airframe 43,126 hrs · 29,380 cycles

CRACKED FRAME CLIP STA Y=1037 LONG 16L TO 17L AT W2. CLIP WAS REPAIRED PER ETI-17-16-145 REV 1 AND ER/A 551734-14 REV ORIG.

Part: CARGO TRACK — CORRODED (BS 813-899) · corrosion level 2 · airframe 43,126 hrs · 29,380 cycles

CORROSION ON LT CARGO TRACK BETWEEN BS 899 TO 813 AT AFT CARGO BAY. THE DAMAGE SECTION WAS REPLACED IAW SRM 53-20-51 FIG 1.

Part: FITTING — CRACKED (FUSELAGE) · airframe 43,126 hrs · 29,380 cycles

CRACKED FRAME CLIP STA Y 1037 BTW LONG 16-17R AT RT AFT LAVATORY AREA. CLIP WAS REPAIRED PER ETI-17-16-145 REV 1 AND ER/A 551734-14 REV ORIG.

Part: CARGO TRACK — CORRODED (BS 899-1022) · corrosion level 2 · airframe 43,126 hrs · 29,380 cycles

CORROSION ON THE LEFT CARGO TRACK BS 899 - 1022. THE CARGO TRACK WAS REPLACED IAW SRM 53-20-51 FIG 1.

Part: CARGO TRACK — CORRODED (BS 899-1022) · corrosion level 2 · airframe 43,126 hrs · 29,380 cycles

CORROSION ON RT CARGO TRACK BS 899 - 1022 IN AFT CARGO BAY . THE CARGO TRACK WAS REPLACED IAW SRM 53-20-51 FIG 1.

Part: FRAME — CRACKED (BS 1022) · airframe 43,126 hrs · 29,380 cycles

CRACKED FRAME ANGLE BS 1022 BETWEEN LONGERON 13 & 14L, REPLACED IAW SRM 51-41-02, 51-41-05 AND DRAWING 9912243 REV JS.

Part: FRAME — CRACKED (BS 1037) · airframe 43,126 hrs · 29,380 cycles

CRACKED FRAME BS 1037 LONGERON 17L. THE FRAME WAS REPAIRED IAW SRM 53-20-07 FIG 201 REPAIR 4.

Part: ACCESS PANEL — CRACKED (RT WING) · airframe 43,126 hrs · 29,380 cycles

RIGHT WING FUEL ACCESS PANEL 620MB FOUND CRACKED. THE ACCESS PANEL WAS REPLACED, NO LEAK WAS FOUND.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,126 hrs · 29,380 cycles

CORROSION ON LONGERON 30 FROM STA Y=988 TO Y=1009 AT AFT CARGO COMPARTMENT. SECTION LONGERON 30 FROM STA Y=900 TO Y=1012 WAS REPLACED PER SRM 51-41-01, SRM 51-41-02, SRM 51-41-05, AND SRM 53-20-05 FIG 201 REPAIR 1.

Part: ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,126 hrs · 29,380 cycles

CORROSION ON ANGLES (2EA) STA Y=383 AND Y=415 FRONT OF LOWER DOOR JAMB PAN AT FWD CARGO COMPARTMENT. ANGLES (2EA) STA Y=383 AND Y=415 FRONT OF LOWER DOOR JAMB PAN AT FWD CARGO COMPARTMENT WERE REPLACED PER SRM 51-41-02 AND DWG 5910142 REV DJ.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,126 hrs · 29,380 cycles

CORROSION ON LONGERON 30 FROM STA Y=908-Y=993 AT AFT CARGO COMPARTMENT. SECTION LONGERON 30 FROM STA Y=905-993 WAS REPLACED PER SRM 51-41-01, SRM 51-41-02, SRM 51-41-05, AND SRM 53-20-05 FIG 201 REPAIR 1.

Part: PAN — CRACKED (CARGO DOOR) · airframe 43,126 hrs · 29,380 cycles

HIDDEN DAMAGE, CRACK ON INNER PAN STA Y=370 BTW BEAMS 1 AND 2 AT FWD CARGO COMPARTMENT DOOR. HFEC WAS ACCOMPLISHED ON CONFIRMED CRACK NDT SPM 06-10-01.001 IS 1.593". CRACK WAS STOPPED PER SRM 51-00-07 PAR 5-16 HFEC OK NO CRACKS AFTER STOP DRILL PER SRM 51-00-07 PAR 5 16 B. PAN STA Y=370 BTW BEAMS 1 AND 2 WAS REPAIRED PER SRM 52-30-02 REPAIR 5 PERFORM DECAL CONDITION INSPECTION EVERY C CHECK PER TOPP 30-10-70 PAR I PG 14.

Part: STRUCTURE — CRACKED (AC BAY) · airframe 43,126 hrs · 29,380 cycles

CRACK ON GROUND CONDITIONED AIR ACCESS CUT OUT. REPLACED PER ETI-17-16-147 REV ORIGINAL, ER/A 551737-14 REV ORIGINAL, AND SRM 51-41-02 AND 51-41-08.

Part: PAN — WORN (CARGO DOORWAY) · airframe 43,126 hrs · 29,380 cycles

WEAR ON INNER PAN OF AFT CARGO DOOR AT BS 994 BETWEEN BEAMS 1 AND 2. THE PAN WAS REPAIRED IAW SRM 52-30-02 REP 5 FIG 201.

Part: FRAME — CRACKED (BS 674) · airframe 43,126 hrs · 29,380 cycles

CRACKED FRAME BS 674 LBL TO RBL 42. THE FRAME WAS REPAIRED IAW SRM 51-70-11 FIG 201 REP 1.

Part: ANGLE — WORN · airframe 43,126 hrs · 29,380 cycles

WEAR ON LOWER RT ANGLE AT THE AFT CABIN BULKHEAD DOOR. THE DAMAGED AREA WAS REPAIRED IAW SRM 52-10-02-2R REPAIR 16 PARAGRAPH 4 B (2).

Part: FRAME — CORRODED (BS 696) · airframe 43,126 hrs · 29,380 cycles

CRACKED LH/RH FRAMES BS 696 RBL 32 AND LBL-32 AT KEEL BEAM. THE FRAME WAS REPAIRED IAW SRM 51-70-11 FIG 201 REP 1 .

Part: ANGLE — CRACKED (OVERWING EXIT) · airframe 43,126 hrs · 29,380 cycles

CRACKED ANGLE ON FWD & AFT ENDS OF NR 1 BEAM AT RH FWD OVERWING EMERGENCY EXIT DOOR. THE ANGLE WAS REPLACED IAW SRM 51-41-01, 51-41-02, 51-41-05, AND DWG 9957735 REV G.

Part: FRAME — CRACKED (BS 715) · airframe 43,126 hrs · 29,380 cycles

CRACKED FRAME BS 715 RBL-LBL 44. THE FRAME WAS REPAIRED IAW SRM 51-70-11 FIG 201 REP 1.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 43,126 hrs · 29,380 cycles

CORROSION ON FUEL TANK ACCESS PANEL 620AT RT WING. THE CORROSION WAS REMOVED. FOUND OUT LIMITS. THE ACCESS PANEL WAS REPLACED IAW SRM 51-10-01.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 43,126 hrs · 29,380 cycles

CORROSION ON CENTER TANK FUEL ACCESS PANEL 141AL. THE CORROSION WAS REMOVED AND FOUND OUT LIMITS. THE ACCESS PANEL WAS REPLACED IAW SRM 57-10-01.

Part: FLOOR PANEL — CRACKED (COCKPIT) · airframe 43,126 hrs · 29,380 cycles

CRACKED COCKPIT FLOOR PANEL. THE FLOOR PANEL WAS REPAIRED IAW SRM 53-00-00 FIG 201.

Part: ANGLE — CRACKED (EMERGENCY EXIT) · airframe 43,126 hrs · 29,380 cycles

CRACKED ANGLE ON BEAM NR 1 FWD END, AT RT AFT OVERWING EMERGENCY EXIT DOOR. THE ANGLE WAS REPLACED IAW DWG 9957735 REV. G, SRM 51-41-02 AND 51-41-05.

Part: PAN — CRACKED (CARGO BAY) · airframe 43,126 hrs · 29,380 cycles

CRACKED PAN BS 427 BETWEE BEAM 1 AND 2 AT FWD CARGO COMPARTMENT DOOR. HFEC INSPECTION WAS ACCOMPLISHED ON PAN BEAM 1 AND 2 AT FWD CARGO COMPARTMENT DOOR, 2 CRACKS WERE FOUND AS FOLLOW 1) 0.875" 2) 1.062 PER DC/MD BOEING NDTSPM 06-10-01 .001. EQUIPMENT: PHASEC 2D N/C 925 EXP 08APR17 STOP DRILL WAS PERFORMED ON PAN STA Y=427 BTW BEAM 1 AND 2 PER B-717 SRM 52-30-02 FIG.201 REPAIR 4 HFEC INSPECTION WAS ACCOMPLISHED ON PAN BEAM 1 AND 2 AT FWD CARGO COMPARTMENT DOOR, NO CRACKS WERE FOUND AFTER STOP DRILL PER DC/MD BOEING NDTSPM 06-10-01 .001. EQUIPMENT: PHASEC 2D N/C:925 EXP 08APR17 PAN ON STA Y=427 BTW BEAM 1 AND 2 WAS REPAIRED PER B-717 SRM 52-30-02 FIG. 201 REPAIR 4.

Part: FLOORBEAM — CRACKED (BS 737) · airframe 43,126 hrs · 29,380 cycles

CRACKED FLOORBEAM LBL 54.5 AND BS 737. THE FLOORBEAM WAS REPLACED IAW SRM 51-41-01, 51-41-02, AND 51-41-05.

Part: ANGLE — CRACKED (DOOR FRAME) · airframe 43,126 hrs · 29,380 cycles

CRACKED ANGLE ON FWD END OF BEAM NR 1, AT THE LT AFT OVERWING EMERGENCY EXIT DOOR. THE ANGLE WAS REPLACED IAW SRM 51-41-02 AND 51-41-05.

Part: FITTING — CRACKED (FUSELAGE) · airframe 43,126 hrs · 29,380 cycles

CRACK FRAME CLIP 2 EA, STA Y=1152 PROJECTION LONG 2R AND 2L AT AFT ACCESSORY COMPARTMENT. REPLACED CLIPS PER DRAWING 9911860 REV L AND SRM 51-40-02 AND 51-40-05.

Part: PAN — CRACKED (CARGO DOOR) · airframe 43,126 hrs · 29,380 cycles

CRACK ON INNER PAN STA Y=370 IN BEAM 3 (FWD EDGE) AT FWD CARGO COMPARTMENT DOOR. HFEC INSPECTION WAS ACCOMPLISHED IN BEAM 3 AT FWD CARGO COMPARTMENT DOOR ,ONE CRACK OF 2.125" WAS FOUND PER NDTSPM 06-10-01.001. STOP DRILL WAS PERFORMED ON INNER PAN STA Y=370 IN BEAM 3 (C1) PER SRM 52-30-02 FIG 201 SHEET 2. HFEC WAS ACCOMPLISHED ON INNER PAN STA Y=370 IN BEAM 3 (FWD EDGE) AT FWD CARGO COMPARTMENT DOOR, NO CRACKS WERE FOUND AFTER STOP DRILL, PER NDT SPM 06-10-01.001. CRACK ON INNER PAN WAS REPAIRED PER SRM 52-30-02 FIG 201.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 43,126 hrs · 29,380 cycles

DELAMINATED FLOOR PANEL 223CF IN THE PAX CABIN. THE FLOOR PANEL WAS FABRICATED IAW SRM 53-20-50 AND REPLACED IAW SRM 53-20-50.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 43,126 hrs · 29,380 cycles

DELAMINATED FLOOR PANEL 222KF AT PASSENGER CABIN. FLOOR PANEL 222KF AT PASSENGER CABIN WAS REPLACED PER SRM 53- 20-50.

Part: BEAM — CRACKED (PAX DOOR) · airframe 43,126 hrs · 29,380 cycles

CRACKED BEYOND STOP DRILL ON BEAM NR 1 AT PASSENGER ENTRANCE DOOR (L1). BEAM NR 1 AT PASSENGER ENTRANCE DOOR (L1) WAS REPAIRED PER B-717 SRM 52-10-2 REPAIR 7 FIG 201 SHEET 3.

Part: CUSP WEB — CORRODED (BS 638) · corrosion level 2 · airframe 43,126 hrs · 29,380 cycles

CORROSION ON RT CUSP WEB BETWEEN X -54 TO X -60 BS 638. DAMAGED AREA WAS TRIMMED AND REPAIRED IAW SRM 53-00-55 REPAIR 4 FIG 216, HFEC INSPECTION WAS ACCOMPLISHED ALONG THE TRIM LINE IAW NDT SPM 06-10-01.001, NO CRACKS WERE FOUND.

Part: DOUBLER — CORRODED (BS 579-598) · corrosion level 2 · airframe 43,126 hrs · 29,380 cycles

CORROSION ON PRODUCTION DOUBLER BETWEEN BS 579 - 598 X -60. THE DOUBLER WAS REPLACED IAW SRM 53-20-51 FIG. 1 ITEM 25 AND 51-41-05.

Part: SEAT TRACK — CORRODED (BS 200-256) · corrosion level 2 · airframe 43,126 hrs · 29,380 cycles

CORROSION ON RT SEAT TRACK X -22 AND X -44.5 BS 200 - 256. THE SEAT TRACK WAS REPLACED IAW SRM 53-20-52 REPAIR 5 FIGURE 201.

Part: SPLICE — CORRODED (BS 579-598) · corrosion level 2 · airframe 43,126 hrs · 29,380 cycles

CORROSION ON SPLICE FROM BS 579 TO 598 BETWEEN LONGERONS 17 - 18R. REPAIRED IAW SRM 53-20-51 FIG.1 AND 51-41-05.

Part: CUSP WEB — CRACKED (BS 420) · corrosion level 2 · airframe 43,126 hrs · 29,380 cycles

CORROSION ON RT CUSP WEB X 14 TO X 60 BS 420. CORROSION WAS REMOVED IAW SRM 53-00-00 FIG 201. HFEC INSPECTION WAS ACCOMPLISHED AND NO CRACKS WERE FOUND AFTER TRIM OUT IAW NDT SPM 06-10-01. REPAIRED IAW SRM 53-000-00 FIG 201.

Part: FLOOR PANEL — DELAMINATED (COCKPIT) · airframe 43,126 hrs · 29,380 cycles

DELAMINATION ON FLOOR PANEL IN COCKPIT. THE FLOOR PANEL WAS REPAIRED IAW AMM 20-60-10 340-801 SUBTASK 390-002.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 43,433 hrs · 29,599 cycles

CORROSION ON FLOOR SUPPORT BTW STA Y=200-208 AND X=-56 AT PAX CABIN (CS) (SM). DUE TO EXCESSIVE DAMAGE SUPPORT WAS REPAIRED PER SRM 53-00-00 REPAIR 1 FIG 201.

Part: CHANNEL — CRACKED · airframe 43,126 hrs · 29,380 cycles

CRACKED HAT CHANNEL. REPAIRED IAW SRM 53-20-50 REP. 5.

Part: STOP FITTING — CRACKED (CARGO DOOR) · airframe 43,126 hrs · 29,380 cycles

CRACKED STOP FITTINGS ON FWD EDGE OF AFT CARGO DOOR. THE STOP FITTINGS WERE REPLACED IAW SRM 51-41-01 AND 51-41-05.

Part: CUSP WEB — CRACKED (BS 219) · airframe 43,126 hrs · 29,380 cycles

CRACKED RT CUSP WEB BELOW SEAT TRACK X 44 BS 219. DAMAGE AREA WAS REPAIRED IAW SRM 53-00-55 FIG 219 AND 51-41-02.

Part: DOOR FRAME — CRACKED · airframe 43,126 hrs · 29,380 cycles

CRACKED UPPER AREA OF AFT VENTRAL DOOR FRAME. THE DOOR FRAME WAS REPAIRED IAW SRM 51-41-02 PAR. 7.C. (1), 51-41-05 PAR 10 FIG. 19, AND SRM 53-00-00 REPAIR 1, FIGURE 201, 51-41-02 AND 51-41-05.

Part: CUSP WEB — CRACKED (BS 617-636) · airframe 43,126 hrs · 29,380 cycles

CRACK ON RT CUSP WEB BS 617 - 636. DAMAGE WAS REMOVED IAW SRM 53-00-00 FIG 101. HFEC INSPECTION WAS ACCOMPLISHED AFTER DAMAGE REMOVED AND NO CRACKS WERE FOUND IAW NDT SPM 06-10-01.001.

Part: CUSP WEB — CRACKED (BS 623) · airframe 43,126 hrs · 29,380 cycles

CRACK ON LT CUSP WEB BS 623 BETWEEN X 54 - X 60. THE DAMAGE WAS REMOVED IAW SRM 53-00-00 FIG 101.

Part: FLOOR PANEL — DELAMINATED (PAX CABIN) · airframe 43,126 hrs · 29,380 cycles

DELAMINATED FLOOR PANEL 221PF IN THE PAX CABIN. THE FLOOR PANEL WAS REPAIRED IAW SRM 53-20-50 AND AMM 20-60-10 340-801 SUBTASK 390-002.

Part: PAN — CRACKED (FUSELAGE) · airframe 43,126 hrs · 29,380 cycles

CRACKED RING PAN ON FWD UPPER AND LOWER CORNER STA Y=637, FWD UPPER CORNER STA Y=656, AFT LOWER CORNER STA Y=713, AFT UPPER CORNER STA Y=869 AT PAX CABIN LT SIDE. RING PAN ON FWD UPPER AND LOWER CORNER STA Y=637, FWD UPPER CORNER STA Y=656, AFT LOWER CORNER STA Y=713, AFT UPPER CORNER STA Y=869 AT PAX CABIN LT SIDE WERE REPAIRED PER SRM 56-20-02 FIG 203.

Part: PAN — CRACKED (FUSELAGE) · airframe 43,126 hrs · 29,380 cycles

CRACKED RING PAN ON AFT LOWER CORNER STA Y=578, FWD UPPER AND LOWER CORNER STA Y=795, AND FWD LOWER CORNER STA Y=890 AT PAX CABIN RT SIDE. REPAIRED RING PAN ON AFT LOWER CORNER STA Y=578, FWD UPPER AND LOWER CORNER STA Y=795, AND FWD LOWER CORNER STA Y=890 RT PER SRM 56-20-02 FIG 202.

Part: LANYARD — DISCONNECTED (L1 DOOR SLIDE) · airframe 42,244 hrs · 28,652 cycles

THE PILOT DISCOVERED THAT THE EMERGENCY ESCAPE SLIDE AT L1 DOOR HAD A DISCONNECTED LANYARD. THE LANYARD WAS DISCONNECTED FROM THE DOOR. THIS WOULD PREVENT PROPER DEPLOYMENT OF THE ESCAPE SLIDE AND IS NOT IN COMPLIANCE WITH 14 CFR, PART 121.703. MAINTENANCE REINSTALLED THE DOOR SLIDE LANYARD IAW AMM 25-61.

Part: LIGHT — DAMAGED (CABIN) · airframe 40,667 hrs · 27,409 cycles

F/A REPORTED EMERGENCY SEAT MOUNTED LIGHTING WAS DAMAGED AND/OR INOPERATIVE. MAINTENANCE DETERMINE ALL FUNCTIONS WERE NORMAL AFTER CHECK.

Part: TERMINAL — BROKEN (EMERGENCY LIGHT) · airframe 40,643 hrs · 27,396 cycles

RETURNED TO DEPARTURE DUE TO UNCONTROLLABLE PA CHIMES & A ELECRICAL SMOKE ODOR IN THE GALLEY. THE CHIMES WERE ADDRESSED BY REPLACING THE AFT F/A HANDSET THAT WAS STUCK IN THE "CALL" POSITION. THE SOURCE OF THE ODOR WAS A SIGN OVER THE R-1 DOOR. THE SIGN HAD A BROKEN TERMINAL AND THERE WAS EVIDENCE OF ARCING ON THE SIDEWALL. THE TERMINAL AND LIGHT ASSEMBLY WERE REPLACED.

Part: CABLE — FRAYED (TAILCONE SLIDE) · airframe 40,227 hrs · 27,081 cycles

DURING LINE CHECK, FOUND TAILCONE SLIDE CABLE FRAYED. REPLACED THE CABLE IAW AMDS 5352-2001.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 38,226 hrs · 25,500 cycles

SHEAR TIE CRACKED AT BS 1116 LONGERON 16L. R & R SHEAR TIE IAW SRM & DWG.

Part: LIGHT — CRACKED (CABIN) · airframe 38,226 hrs · 25,500 cycles

R1 DOOR AFT EMER LIGHT CRACKED. R & R LIGHT IAW AMM.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 38,226 hrs · 25,500 cycles

RIGHT OVERWING EXIT LIGHTS ABOVE DOOR LIGHT INOPERATIVE. R & R BULB IAW AMM.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 38,226 hrs · 25,500 cycles

LEFT OVERWING EXIT LIGHTS ABOVE DOOR LIGHT INOPERATIVE. R & R BULB IAW AMM.

Part: SUPPORT BRACKET — CRACKED (LT AILERON) · airframe 37,499 hrs · 25,010 cycles

LEFT WING AILERON OTBD HINGE TE PANEL SUPPORT BRACKET CRACKED. R & R BRACKET IAW DWG.

Part: LINER — LOOSE (EMERGENCY EXIT) · airframe 37,499 hrs · 25,010 cycles

RIGHT AFT OVERWING EMER EXIT DOOR LINER LOOSE. SECURED LINER IAW MM.

Part: LINER — LOOSE (EMERGENCY EXIT) · airframe 37,499 hrs · 25,010 cycles

LEFT FWD OVERWING EMER EXIT DOOR LINER LOOSE. SECURED LINER IAW MM.

Part: SUPPORT ANGLE — CRACKED (FUSELAGE) · airframe 37,499 hrs · 25,010 cycles

CENTER WING BOX TEE SUPPORT ANGLE CRACKED AT BS 715 RBL 43. R & R ANGLE IAW SRM.

Part: CABLE — DISCONNECTED (L1 DOOR) · airframe 37,499 hrs · 25,010 cycles

L1 DOOR SLIDE CABLE DISCONNECTED. R & R SLIDE ASSEMBLY IAW MM.

Part: MOUNT — CORRODED (GIRT BAR) · airframe 37,499 hrs · 25,010 cycles

R1 DOOR EMER EVAC SLIDE GIRT BAR FITTING MOUNTS CORRODED. R & R MOUNTS IAW SRM.

Part: ROLLER TRACK — CRACKED (L1 DOOR) · airframe 37,499 hrs · 25,010 cycles

L1 DOOR CTR ROLLER TRACK FITTING CRACKED. R & R L1 DOOR CTR ROLLER TRACK IAW MM.

Part: DUCT — CRACKED (VERTICAL STAB) · airframe 37,499 hrs · 25,010 cycles

VERTICAL STABILIZER RAM AIR INLET DUCT LT SIDE CRACKED. REPAIRED DUCT IAW SRM.

Part: LANYARD — LOOSE (L1 DOOR) · airframe 38,142 hrs · 25,441 cycles

L1 DOOR EMER EVAC SLIDE GIRT BAR LANYARD LOOSE. REINSTALLED LANYARD IAW MT.

Part: PIN — MISSING (EVAC SLIDE) · airframe 37,978 hrs · 25,329 cycles

L1 DOOR SLIDE PIN MISSING. R & R L1 DOOR SLIDE IAW MM.

Part: SLIDE — DEFECTIVE (L1 DOOR) · airframe 36,964 hrs · 24,669 cycles

L1 DOOR EMERGENCY EVAC SLIDE LOWER PIN LOOSE. R & R SLIDE IAW AMM.

Part: COVER — MISSING (EXIT SIGN) · airframe 36,177 hrs · 24,147 cycles

FWD LAVATORY EXIT SIGN COVER MISSING. INSTALLED LIGHT ASSEMBLY IWA MM.

Part: DRIVE UNIT — FAULTY (E&E BAY) · airframe 35,699 hrs · 23,827 cycles

AIR TURNBACK, CAPTAIN NOTICED THE PRIMARY TRIM WAS NOT RESPONDING. FIRST OFFICERS PRIMARY TRIM SWITCHES ALSO DID NOT RESPOND. R&R PRIMARY STAB TRIM DRIVE UNIT IAW MM.

Part: CABLE — OUT OF POSITION (R1 DOOR) · airframe 355,070 hrs · 23,707 cycles

R1 DOOR EMERGENCY EVAC SLIDE CABLE OUT OF POSITION. REPOSITIONED CABLE IAW AMM.

Part: LENS — MISSING (EXIT SIGN) · airframe 35,151 hrs · 23,486 cycles

CENTER AISLE OVERHEAD EMERGENCY EXIT SIGN MISSING AT ROW 1. INSTALLED LENS IAW MM.

Part: LANYARD — DISCONNECTED (L1 DOOR) · airframe 34,980 hrs · 23,380 cycles

L1 DOOR EMERGENCY EVAC GIRT BAR LANYARD DISCONNECTED. RECONNECTED LANYARD IAW MM.

Part: DOOR — CRACKED (LT WING) · airframe 34,879 hrs · 23,316 cycles

LEFT WING I/B BUTE DOOR CRACKED. REPAIRED BUTE DOOR PER SRM.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

FLOOR PANEL CORRODED AT STA 431, RBL 44.5. REMOVED AND REPLACED PANEL IAW SRM.

Part: DOOR — CRACKED (LT WING) · airframe 34,266 hrs · 22,955 cycles

LEFT WING INBOARD BUTE DOOR CRACKED. REMOVED BUTE DOOR IAW SRM.

Part: ANGLE — CRACKED (L1 DOOR) · airframe 34,266 hrs · 22,955 cycles

L1 DOOR LOWER LINER SUPPORT CRACKED. REMOVED AND REPLACED ANGLE IAW SRM AND DWG.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

LEFT CUSP WEB CRACKED AT FS 674, LBL 46. REMOVED AND REPLACED WEB IAW SRM.

Part: WINDOW FRAME — CRACKED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

LEFT WINDOW FRAME CRACKED BETWEEN STA 598 TO STA 617. REPAIRED FRAME IAW SRM.

Part: FITTING — CRACKED (L1 DOOR) · airframe 34,266 hrs · 22,955 cycles

L1 DOOR INTERIOR NR 1 BEAM CRACKED AT AFT END LOWER SURFACE. REMOVED AND REPLACED FITTING IAW SRM.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

LONGERON CRACKED AT BS 1133, LONGERON 2R. REMOVED AND REPLACED LONGERON IAW SRM.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

VERTICAL STIFFENER CRACKED AT FS 661, RBL 24. REMOVED & REPLACED STIFFENER IAW SRM.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

RIGHT CUSP WEB CRACKED AT FS 674, RBL 46. REPAIRED WEB IAW SRM.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

VERTICAL STIFFENER CRACKED AT FS 661, LBL 24. REMOVED & REPLACED STIFFENER IAW SRM.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

VERTICAL WEB LOWER ANGLE CRACKED AT FS 663, BL 0. REMOVED AND REPLACED ANGLE IAW DWG & SRM.

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

LEFT SIDE OF EMERGENCY DOOR FRAME SUPPORT FITTING CRACKED AT STA 1053, LONGERON 9L. REMOVED AND REPLACED FITTING IAW SRM.

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

SEAT TRACK SUPPORT FITTING CRACKED AT FS 737, LBL 45. REMOVED AND REPLACED FITTING IAW SRM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

SEAT TRACK SECTION CORRODED BETWEEN STA 898 TO STA 927, RBL 22. REPAIRED TRACK IAW SRM.

Part: STRAP — CORRODED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

STRAP CORRODED AT BS 944, L28R. REMOVED AND REPLACED STRAP IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

CUSP WEB CORRODED BETWEEN STA 465 TO STA 484, RBL 55.0. REPAIRED WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

CUSP WEB CORRODED BETWEEN STA 545 TO STA 551, RBL 55. REPAIRED WEB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

CUSP WEB CORRODED BETWEEN STA 507 AND STA 513, RBL 55. REMOVED AND REPLACED WEB IAW SRM.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

LEFT WING TO BODY SUPPORT CRACKED AT BS 636, WBL. REPAIRED SUPPORT IAW SRM AND DWG.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

FLOOR PANEL CORRODED AT BS 612, RBL 44.0. REMOVED AND REPLACED PANEL IAW AMM.

Part: FLOORBOARD — CORRODED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

FLOORBOARD CORRODED AT STA 283, RBL 44.5. REMOVED AND REPLACED PANEL IAW MM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

SEAT TRACK CORRODED BETWEEN BS 608 TO BS 641, RBL 44.5. REMOVED AND REPLACED TRACK IAW SRM.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

LEFT CUSP WEB CRACKED AT STA 917. REMOVED AND REPLACED WEB IAW SRM.

Part: FITTING — CRACKED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

MAIN FRAME WING TO FUSELAGE FITTING CRACKED AT 661, LONG 22R. REMOVED AND REPLACED FITTING IAW SRM & DWG.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

SPOT AFT WEB JAMB CORRODED AT STA 1002, LONGERON 26R. REPAIRED JAMB IAW SRM.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

LEFT CUSP WEB CORRODED BETWEEN STA 870 TO STA 889. REPAIRED WEB IAW SRM.

Part: CARGO TRACK — CRACKED (CARGO BAY) · airframe 34,266 hrs · 22,955 cycles

FWD CARGO TRACK CRACKED AT BS 370 LONG 28R. REMOVED & REPLACED ANGLE IAW SRM.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

SHEAR TIE CORRODED AT STA 927, L30. REMOVED AND REPLACED SHEAR TIE IAW SRM.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

BOTTOM THRESHOLD WEB JAMB CORRODED AT STA 974, LONGERON 28R. REMOVED AND REPLACED JAMB IAW SRM.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 34,266 hrs · 22,955 cycles

MAIN CABIN FLOOR PANEL 221UF DELAMINATED. REMOVED AND REPLACED PANEL IAW SRM.

Part: PAN — CORRODED (FUSELAGE) · airframe 34,266 hrs · 22,955 cycles

C1 LOWER DOOR JAMB PAN CORRODED. REPAIRED PAN IAW SRM.

Part: SIGN — BROKEN (CABIN)

FIRST CLASS EXIT SIGN BROKE. REMOVED AND REPLACED FIRST CLASS EXIT SIGN. REF AMM 33-51.

Part: COVER — MISSING (CABIN)

EPL LIGHT COVER MISSING AT 2DF. INSTALLED COVER AT REQ'D.

Part: ANGLE — CRACKED (THRUST REVERSER)

NR 2 ENGINE, I/B LEADING EDGE END TR DEFLECTOR DOOR ANGLE, CRACKED. ACCOMPLISHED TR DEFLECTOR DOOR ANGLE DOUBLER REPAIR PER EA 17-54-03118IR AND B717 SRM 54-30-05.

Part: PAN — CORRODED (FUSELAGE)

AFT CARGO DOOR JAMB PAN, CORROSION. ACCOMPLISHED JAMB PAN SPLICE REPAIR PER B717 SRM 53-20-15 FIG 201 REPAIR 7.

Part: FASTENER — SHEARED (FUSELAGE)

SHEAR CLIP O/N 9911840-165 FASTENER, STA 1152, LONG L1, SHEARED. ACCOMPLISHED FASTENER PLUGGED PER EA 17-53-03117IR.

Part: STRUCTURE — CRACKED (LT PYLON)

LEFT PYLON APRON LOWER NR 2 HINGE CUTOUT AREA, CRACKED. ACCOMPLISHED NR 2 HINGE CUTOUT AREA DOUBLER REPAIR PER TRA 17-54-TR00129.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 200, RBL 9 TO RBL45, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: RELEASE MECH — OUT OF ADJUST (TAILCONE)

TAIL CONE RELEASE MECHANISM, OUT OF ADJUSTMENT. ACCOMPLISHED RELEASE MECHANISM ADJUSTMENT PER B717 AMM 53-52-03-820-801.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

COCKPIT FLOOR SUPPORT, STA 148, RBL 35, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 200, LBL 5 TO RBL 5, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: ATTACH FITTING — CORRODED (FUSELAGE)

GALLEY ENTRANCE FWD AND AFT GIRT BAR ATTACH FITTINGS, CORROSION. ACCOMPLISHED GIRT BAR ATTACH FITTINGS REPLACEMENT PER B717 SRM 51-41-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 200, LBL 9 TO LBL 13, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 179, RBL8 TO RBL42, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: SEAT TRACK — CORRODED (FUSELAGE)

CABIN SEAT TRACK, STA 237 TO 265.5, RBL 22, CORROSION. ACCOMPLISHED SEAT TRACK REPLACEMENT PER BOEING DWG SR09530085.

Part: FINGER DOUBLER — CRACKED (FUSELAGE)

CABIN LONGERON FINGER DOUBLER, STA 210, LONG L15L, CRACKED. ACCOMPLISHED LONGERON FINGER DOUBLER FILLER AND DOUBLER REPAIR PER B717 SRM 51-70-10 FIG 201.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 179 TO 200, RBL 45, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 237, BL 0, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-05.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 160 TO 200, LBL 7, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT, STA 160 TO 200, RBL 7, CORROSION. ACCOMPLISHED FLOOR SUPPORT REPLACEMENT PER B717 SRM 51-41-01.

Part: LENS — MISSING (CABIN)

EPL LENS MISSING 2DF. INSTALLED LENS AS REQUIRED.

Part: SKIN — DENTED (FUSELAGE)

DENT ON FUSELAGE LEFT SIDE STA 240 BETWEEN L-16 AND L-17 (REF TRA 17-53-TR00109 SECTION 6 CONDITION 3B). REPAIRED DENT ON LT FUSELAGE AT STA 240 L16 AND L17 PER BOEING DRAWING SG09530002.

Part: SKIN — DENTED (FUSELAGE)

DENT ON FUSELAGE LEFT SIDE STA 240 BETWEEN L-16 AND L-17 (REF TRA 17-53-TR00109 SECTION 6 CONDITION 3B). REPAIRED DENT ON LT FUSELAGE AT STA 240 L16 AND L17 PER BOEING DRAWING SG09530002. SEE NRWC N161377 FOR WORK ACCOMPLISHED AND REQUIRED INSPECTION ITEMS.

Part: PIN — OUT OF POSITION (EVAC SLIDE)

REINSTALL PIN IN L-1 DOOR SLIDE PACK. RE-INSTALLED LANYARD PER AMM 25-61.

Part: PIN — OUT OF POSITION (EVAC SLIDE)

FWD DOOR (L-1) SLIDE PIN CAME OUT OF ARMED POSITION. REINSTALLED GIRT BAR LANYARD ASSY. SLIDE OK FOR SERVICE REF MM 25-61.

Part: STRUCTURE — CORRODED (CARGO BAY)

CORROSION AFT CARGO PIT STA 1022 LONG 30. CUT OUT DAMAGED AREA AND REPAIRED PER B717 SRM 53-00-05 FIG 201.

Part: UNKNOWN — ODOR (CABIN)

FLIGHT ATTENDANT REPORTED A SULFUR SMOKE SMELL IN THE AFT CABIN SHORTLY AFTER TAKEOFF FROM LGA. NO VISIBLE SMOKE WAS NOTED. DIVERTED INTO EWR. A/C LANDED WITHOUT INCIDENT. THE SMELL ONLY LASTED FOR ABOUT 1 MINUTE. PERFORMED INSPECTION OF A/C AND GROUND RAN ENGINES AND PACKS. NO DEFECTS WERE NOTED. NO UNUSUAL SMELLS WERE NOTED AT ANY TIME BY MAINTENANCE.

Part: ENGINE — MALFUNCTIONED (NR 1)

DURING CLIMB IN THE MID TO HIGH TEENS, OBSERVED LOUD BANG FROM THE LEFT ENGINE. ENGINE ROLLED BACK AND TGT REMAINED STEADY BUT ROSE TO 974 DURING CALLING CHECK LIST. EMERGENCY RETURN TO PBI, LANDING NORMAL. NR 1 (LEFT) ENG HAS BEEN REMOVED AND REPLACED IAW TC 603 REF SP 8140.2, ALL LEAK OPS AND RTS PASS (NORMAL).

Part: ANGLE — CRACKED (FUSELAGE)

AFT ACCESSORY COMPARTMENT FS 1178 CANTED FRAME ANGLE CRACKED NEAR LONGERON 15R. INSTALLED ANGLE FOR REPAIR 1 SIDE OF ANGLE 11 1/2 X 2 1/2 IAW B717 SRM 51-70-11.

Part: ANGLE — CRACKED (FUSELAGE)

AFT ACCESSORY COMPARTMENT FS 1178 CANTED FRAME ANGLE CRACKED NEAR LONGERON 15R. INSTALLED ANGLE FOR REPAIR 1 ZIDE OF ANGLE 11 1/2 X 2 1/2 IAW B717 SRM 51-70-11.

Part: CONTROL UNIT — INOPERATIVE (FIRE DETECTION)

IN CLIMB RT ENG FIRE IND CAME ON WITH NO LIGHT IN RT FIRE HANDLE. LANDED IN BWI AT 108000 LBS. PERFORMED FIM TASK 26-11, TASK 807-808 ALERT ENGINE RT FIRE. REMOVED AND REPLACED RIGHT ENGINE FDCU IAW B717 AMM 26-11 FAULT TEST OK. (REF 44EB02) NOTED BY MX OVERWEIGHT LANDING INSP REQUIRED AT 110,000 LBS.

Part: ENGINE — FAILED (NR 1)

AT FL 290, ENGINE LT SURGE APPEARED ON EAD. LOST OIL PRESSURE ON LEFT ENGINE; LOUD BANG PRECEEDED THESE TWO ALERTS FOLLOWED QRH PROCEDURES AND SHUT DOWN ENGINE. REMOVED AND REPLACED NR 11 ENGINE REF TASK CARD 603, OPS CHECK GOOD OK FOR SERVICE.

Part: DEFLECTOR — DAMAGED (NLG)

NOSE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF. REMOVED AND REPLACED SPRAY DEFLECTOR.