N373US

Part: SKIN — CRACKED (FUSELAGE)

FOUND SKIN CRACKED .600 INCH LONG, S-23L AT FS 744. REPAIR DOUBLER INSTALLED PER SRM 53-00-01, FIG 229. (M)

Part: SKIN — CRACKED (FUSELAGE)

FOUND SKIN CRACKED 1.250 INCH LONG, 3 INCHES FORWARD OF FS 727E ADJACENT TO S-24L. INSTALLED DOUBLER PER SRM 53-00-01, FIG 229. (M)

Part: SKIN — CRACKED (FUSELAGE)

FOUND SKIN CRACKED 1.250 INCH LONG, INSTALLED DOUBLER PER SRM. 53-00-01, FIG 229. INSTALLED DOUBLER PER SRM 53-00-01, FIG 229. (M)

Part: SKIN — CRACKED (FUSELAGE)

CLT - FOUND SKIN CRACKED .600 INCH LONG, S22R 12 INCHES AFT OF FS 727D. INSTALLED DOUBLER PER SRM 53-00-01. (M)

Part: SKIN — CRACKED (FUSELAGE)

FOUND SKIN CRACKED 1.450 INCH LONG, FS 891 ADJACENT OT S23R. INSTALLED DOUBLER PER SRM 53-00-01. (M)

Part: SKIN — CRACKED (FUSELAGE)

PIT - FOUND SKIN CRACKED 2.5 INCHES STATION 765 ABOVE STRINGER 19R. CRACK CUT OUT AND DOUBLER INSTALLED PER SRM 53-00-01. (M)

Part: SKIN — CRACKED (FUSELAGE)

PIT - FOUND SKIN CRACKED .25 INCH, AFT SERVICE DOOR UPPER HINGE STATION 951. INSTALLED DOUBLER PER SRM 53-60-01 FIG 205. (M)

Part: CLAMP — LOOSE (PNEUMATIC DUCT)

ON CLIMB-OUT FROM PIT, AT FL170, THE NR 1 ENGINE OVERHEAT LIGHT ILLUMINATED. LIGHT EXTINGUISHED WHEN THROTTLE WAS RETARDED. FLIGHT RETURNED TO FIELD AT PIT AND LANDED WITHOUT FURTHER INCIDENT. AN EMERGENCY WAS DECLARED. MAINTENANCE TIGHTENED A LOOSE PNEUMATIC DUCT CLAMP ON NR 1 ENGINE. LEAK CHECK GOOD. (M)

Part: CHARGER — INOPERATIVE (EMERGENCY LIGHT)

PHL - MAINTENANCE REPORTED THE EMERGENCY EXIT AISLE LIGHTS AT SEAT ROWS 12 THROUGH 16 INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE BATTERY PACK, P/N 201301A, AND CHARGER ASSEMBLY. OPS CHECK GOOD. (M)

Part: LIGHT — INOPERATIVE (CABIN)

PILOT REPORTED THE EMERGENCY EXIT LIGHT AT SEAT 12C INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE EMERGENCY EXIT LIGHT ASSEMBLY. OPERATIONAL CHECK GOOD. (M)

Part: SKIN — CRACKED (FUSELAGE)

PIT - FOUND SKIN CRACKED 2 INCHES, RIGHT SIDE STATION 727E STRINGER 24 RT. CUTOUT DAMAGE, INSTALLED DOUBLER AND FILLER PER SRM 53-00-01 FIG 225. (M)

Part: SOCKET — SHORTED (CABIN)

GSO - MAINTENANCE FOUND THE BULLNOSE EMERGENCY LIGHTS AT SEAT ROWS 12, 16 AND 20 INOPERATIVE. MAINTENANCE FOUND THE LIGHT SOCKET AT SEAT ROW 16 SHORTED. REPAIRED LIGHT SOCKET AND REPLACED ONE BATTERY PACK AND TWO POWER SUPPLIES . OPERATIONAL CHECK NORMAL. (M)

Part: SKIN — CRACKED (FUSELAGE)

PIT - FOUND SKIN CRACKED 3.5 INCH, S25R BETWEEN STATION 727E AND 747. INSTALLED DOUBLER PER SRM 53-00-01 FIG 2. (M)

Part: BULKHEAD — CORRODED (FUSELAGE) · corrosion level 2

PIT - FOUND Y-CHORD AND BULKHEAD CORRODED, BS 1016 AFT PRESSURE BULKHEAD AT FLOOR LINE CENTER. CORROSION LEVEL 2, REMOVED CORROSION AND INSTALLED DOUBLERS PER EA 74025. (M)

Part: STIFFENER — CORRODED (FUSELAGE)

PIT - FOUND STIFFENER CORRODED 3 INCH BY 3 INCH AREA, AFT PRESS BULKHEAD STIFFENER BS 1018 BL 00. INSTALLED DOUBLER, SPLICED SECTION OF STIFFENER PER BOEING DRAWING 65C28106. (M)

Part: BULKHEAD — CORRODED (FUSELAGE)

PIT - FOUND CHORDS AND WEBS CORRODED 5 INCH BY 6 INCH AREA, FORWARD SIDE AFT PRESSURE BULKHEAD BS 1018 BL 00 4 INCH BY 5 INCH. CORROSION LEVEL 2. BULKHEAD WEB AND CHORDS INSTALLED DOUBLERS PER EA 74025. (M)

Part: BULKHEAD — CRACKED (FUSELAGE)

PIT - FOUND SKIN CRACKED 1.125 INCH BY 6.625 INCH CRACK, BETWEEN STRINGER 16 AND 17 OUTERSKIN STATION 178. DOUBLER INSTALLED PER EO 5300V157. (M)

Part: BULKHEAD — CRACKED (FUSELAGE)

PIT - FOUND SKIN CRACKED 7.875 INCH BY 6.75 INCH, BETWEEN STRINGER 16/17, OUTER SKIN STATION 178. DOUBLER INSTALLED PER EO 5300V157. (M)

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

PIT - FOUND SUPPORT CORRODED ENTIRE SURFACE, DIAGONAL FLOOR SUPPORT RBBL 12, STATION 987-1016. FOUND DEFECTIVE PART REPLACED WITH IDENT PART NR. CORRODED LEVEL 1, TASK NR C53-107-02. (M)

Part: CLIP — CORRODED (FUSELAGE)

PIT - FOUND CLIP CORRODED, STATION 727E BETWEEN S26R AND S27R. DOUBLER TREATED PER SRM 53-00-07 PAGES 210-212. (M)

Part: STRINGER — CRACKED (FUSELAGE)

PIT - FOUND STRINGER CRACKED .25 INCH, STATION 663 STRINGER 2R. INSTALLED DOUBLERS PER SRM 53-00-07 FIG 209. (M)

Part: INTERCOSTAL — CRACKED (FUSELAGE)

PIT - FOUND INTERCOSTAL CRACKED 1.5 INCH, JUST ABOVE AFT ENTRANCE DOOR BS 967. INSTALLED NEW ATTACH ANGLE. (M)

Part: INTERCOSTAL — CRACKED (FUSELAGE)

PIT - FOUND INTERCOSTAL CRACKED 1 INCH, UPPER AFT FLANGE INTERCOSTAL BL 0 STATION 294.5-312. INSTALLED NEW INTERCOSTAL PER SRM 51-10-02. (M)

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2

PIT - FOUND LEFT INBOARD SEAT TRACK, STATION 827-945 LBBL 24. CORROSION LEVEL 2. SPLICED IN SECTION OF TRACK PER SRM 53-00-52. (M)

Part: FRAME — CRACKED (FUSELAGE)

PIT - FOUND FRAME CRACKED TWO PLACES .125 INCH AND .25 INCH, STATION 380 BETWEEN S8R AND S9R. INSTALLED DOUBLER PER SRM 53-00-07. (M)

Part: KEELBEAM — CORRODED (FUSELAGE)

PIT - FOUND KEEL BEAM CORRODED 3 INCHES BY 1 INCH CORRODED, 13.5.546 STRINGER 28L. CORROSION LEVEL 2, TASK NR C53-212-01. REMOVED DAMAGED AREA, INSTALLED NEW SECTION AND INSTALLED DOUBLER PER EA 73807. (M)

Part: CREASE BEAM — CORRODED (FUSELAGE)

PIT - FOUND CREASE BEAM CORRODED, STATION 277-360. DEFECTIVE PART REPLACED WITH IDENT PART. (M)

Part: SKIN — CRACKED (L/E SLAT)

PIT - FOUND SKIN CRACKED IN 13 SMALL CONTINUOUS PLACES, RIGHT WING, NR 6 SLAT, LOWER SURFACE SLAT STATION 299.10-314. REMOVED DAMAGED SKIN PER SRM 57-43-01. (M)

Part: FRAME — CRACKED (FUSELAGE)

PIT - FOUND FRAME CRACKED .25 INCH, STATION 767 BETWEEN S8L AND S9L AT PSU SUPPORT BRACKET. INSTALLED DOUBLER PER TYPICAL REPAIR 53-10-14A. (M)

Part: FRAME — CRACKED (FUSELAGE)

PIT - FOUND Z-FRAME CRACKED .25 INCH, STATION 807 BETWEEN S8R AND S9R. CUT OUT CRACKED, INSTALLED DOUBLER PER TYPICAL REPAIR 53-10-14A. (M)

Part: FRAME — CRACKED (FUSELAGE)

PIT - FOUND FRAME CRACKED .25 INCH, STATION 480 BETWEEN S8R AND S9R. CUT OUT CRACK, INSTALLED DOUBLER PER TYPICAL REPAIR 53-10-14A. (M)

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

IT - FOUND FLOOR SUPPORT CORRODED, STATION 727-787 AND 787-827 ABOVE S25L. SPLICED IN NEW SECTION PER SRM 53-60-53. (M)

Part: ARM — CORRODED (RUDDER)

PIT - FOUND RUDDER BALANCE ARM WITH CORROSION 3 INCH BY 12 INCH AREA, RUDDER BALANCE ARM STRUCTURE. CORROSION LEVEL 2. RUDDER REPLACED AND INSTALLED PER JOB CARD. (M)

Part: ANGLE — CRACKED (VERTICAL STAB)

PIT - FOUND DRAG ANGLE CRACKED .5 INCH, SECTION 48, RIGHT SIDE, AFT OF AFT LUGS FOR VERTICAL STABILIZER. FILLERS AND STRAPS INSTALLED ON BOTH SIDES OF DRAG ANGLE PER TYPICAL REPAIR 53-80-03. (M)

Part: ANGLE — CRACKED (EMPENNAGE)

PIT - FOUND DRAG ANGLE CRACKED .25 INCH, SECT 48 DRAG ANGLE LIGHT SIDE 10 INCH BEHIND ATTACH LUG. REPAIRED FILLER AND STRAPS ON OUTSIDE AND INSIDE OF DRAG ANGLE PER TYPICAL REPAIR 53-80-03. (M)

Part: FUEL CELL — LEAKING (LT WING)

CLT - FLT 1290 - AFTER TAKEOFF, FUEL WAS REPORTED STREAMING OUT OF THE LEFT WING BY AN AMERICAN FLIGHT BEHIND AND WAS ALSO CONFIRMED BY THE CLT TOWER. AN EMERGENCY WAS DECLARED AND THE FLIGHT RETURNED TO FIELD AT CLT. FLIGHT LANDED WITHOUT FURTHER INCIDENT. (M)

Part: CHARGER — FAILED (CABIN)

PHL - MAINTENANCE FOUND THE LOW LEVEL EMERGENCY LIGHTS AT ROWS 1 THROUGH 4 INOPERATIVE AND THE EMERGENCY LIGHTS AT THE FORWARD ENTRY AND SERVICE DOORS INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE BATTERY PACK (P/N 2013-1A) AND CHAGER ASSEMBLY AT STATION 338L IN ASSOCIATION WITH MM. OPS CHECK GOOD. (M)

Part: THROTTLE CABLE — FAILED (NR 2 ENGINE)

EWR - FLT 1024 - EN ROUTE FROM DCA TO ALB, THE NR 2 THRUST LEVER STUCK AT CLIMB POWER. CREW DISENGAGED AUTO THROTTLES BUT WAS STILL UNABLE TO RETARD THRUST LEVER. CREW DECLARED AN EMERGENCY, ACCOMPLISHED ENGINE SHUTDOWN CHECKLIST AND SHUTDOWN THE NR 2 ENGINE. FLIGHT DIVERTED TO EWR AND LANDED WITHOUT FURTHER INCIDENT. TOTAL SINGLE ENGINE TIME WAS 25 MINUTES. MAINTENANCE REMOVED, REPLACED AND RIGGED THE NR 2 ENGINE TELEFLEX THROTTLE CABLE. THROTTLE OPERATES SMOOTHLY THROUGHTOUT ALL TRAVEL. PERFORMED POWER ASSURANCE ENGINE RUM. ENGINE PERFORMED WITHIN LIMITS PER MM 71-00-00, TEST NR 5. (M)

Part: SWIVEL — BROKEN (HYD SYSTEM)

BOS - FLT 1090 - EN ROUTE FROM PHL TO BOS, FLT LOST A-SYSTEM HYDRAULIC QUANTITY AND PRESSURE. MX CONTROL ADVISED THAT FLIGHT SHOULD PROCEED TO ORIGIN OR DESTINATION, WHICHEVER WAS CLOSER. FLIGHT WAS CLOSER TO BOS, SO IT CONTINUED ONTO BOS. FLIGHT LANDED WITHOUT FURTHER INCIDENT AND WAS TOWED TO THE GATE. NO EMERGENCY WAS DECLARED. MX REMOVED AND REPLACED A BROKEN SWIVEL ON THE LEFT MAIN LANDING GEAR RETRACTION ACTUATOR. ALSO, REPLACED NR 1 ENGINE DRIVEN PUMP (P/N 65075-06), B-SYSTEM ELECTRIC PUMP TRANSMITTR (P/N ST107R), A-SYSTEM ELECTRIC HYD PUMP (P/N MPEV3-056-9A), STANDBY HYDRAULIC PUMP (P/N 165W01020) AND ALL ASSOCIATED FILTERS. SERVICED HYDRAULIC SYSTEM. PERFORMED GEAR SWING. OPS CHECKED AND LEAK

Part: BULKHEAD — CRACKED (FUSELAGE)

CLT - FOUND BULKHEAD WEB CRACKED .75 INCH, STATION 178 RBL .5, WL 188. INSTALLED REPAIR DOUBLER AND FILLER PER SRM 53-10-08. (M)

Part: FRAME — CORRODED (FUSELAGE)

PIT - FOUND FRAME CORRODED 4 INCHES BY 3 INCHES, STATION 1006 AT STRINGER 18 AND 19 RIGHT SIDE. CORROSION LEVEL 2, TASK NR C53-206-01. CUT FRAME AND REPLACED PER SRM 51-20-05, SRM 51-40, SRM 53-00-07 FIG 201. (M)

Part: LIGHT — SHORTED (COCKPIT)

IAH - FLT 2231 - ON CLIMB-OUT FROM IAH, AT APPROXIMATELY 9,000 FEET, CAPTAIN REPORTED THERE WAS A LOUD POP AND SPARKS THAT DROPPED DOWN ON THE FIRST OFFICER FROM THE OVERHEAD PANEL. AT 18,000 FEET, ALL APPEARED TO BE OPERATING NORMAL. NO SMOKE OR SMELL OF ANY TYPE WAS NOTED. CAPTAIN DECIDED TO RETURN TO FIELD AT IAH AS PRECAUTIONARY MEASURE. FLIGHT LANDED WITHOUT FURTHER INCIDENT. NO EMERGENCY WAS DECLARED. MAINTENANCE FOUND A SHORT ON THE CIRCUT BREAKER PANEL LIGHT OVERHEAD THE FIRST OFFICER. TIGHTENED GROUND. LIGHT OPERATIONAL CHECK GOOD. (M)

Part: WEB — CRACKED (BS 233)

CLT - DURING DROP IN VISUAL INSPECTION, FOUND A 4 INCH CRACK AT BS 233, BL 0, WL 192.5 WEB. INSTALLED DOUBLER PER BOEING SRM 51-70-13. (M)

Part: BATTERY PACK — DISCHARGED (CABIN)

ALB - MAINTENANCE FOUND THE LIGHTS FOR THE EMERGENCY EXIT SIGNS AT THE COCKPIT ENTRANCE AND OVER THE FORWARD ENTRY DOOR INOP AND THE BULLNOSE EVACUATION LIGHT AT ROWS 3 RIGHT SIDE INOP. MAINTENANCE REMOVED AND REPLACED THE BATTERY PACK IN THE FORWARD ENTRYWAY CEILING LEFT SIDE. OPERATIONAL CHECK GOOD. (M)

Part: FLOORBEAM — CRACKED (BS 520)

CLT - DURING EDDY CURRENT CHECK INSPECTION, FOUND A .6 INCH CRACK AT STA 520 RBL 45.5 FLOORBEAM. REPAIR ANGLE AND DOUBLER WERE MADE PER REPAIR DOCUMENT EA 60887 SRM 51-10-02. (X)

Part: ANGLE — CRACKED (BS 360)

CLT - DURING Q-2 CHECK VISUAL INSPECTION, FOUND A 2 INCH CRACK AT BS 360, STR 11L ANGLE. REPAIRED AND REPLACED STRINGER ANGLE PER REPAIR DOCUMENT SRM 51-40-02. (X)

Part: FRAME — CRACKED (BS 291.5)

CLT - DURING Q-2 CHECK VISUAL INSPECTION, FOUND A .750 INCH CRACK AT BS 291.5 S17R SERVICE DOOR FORWARD/FRAME FLOOR AT Z-ANGLE. INSTALLED FILLER DOUBLER PER REPAIR DOCUMENT SRM 51-70-11. (X)

Part: STRINGER — CRACKED (BS 360)

CLT - DURING Q-2 CHECK VISUAL INSPECTION, FOUND A 1 INCH CRACK AT BS 360 STRINGER 11L CHANNEL. INSTALLED NEW FABRICATED ANGLE PER REPAIR DOCUMENT SRM 51-10-02. (X)

Part: FLOORBEAM — CORRODED (BS 360)

CLT - DURING Q-2 CHECK VISUAL INSPECTION, FOUND CORROSION AT BS 360 RBL 13-63 ON FLOORBEAM. CORROSION TASK NR C53-107-01. INSTALLED REPAIR ANGLES PER EA 60865 AND TYPICAL REPAIR 53-10-05. (X)

Part: FLOORBEAM — CRACKED (BS 520)

CLT - DURING EDDY CURRENT CHECK VISUAL INSPECTION, FOUND A .5 INCH CRACK AT STA 520 LBL 45.5 FLOORBEAM. REPAIR ANGLES AND DOUBLERS WERE MADE PER REPAIR DOCUMENT EA 60887 AND SRM 51-10-02. (X)

Part: CLIP — CRACKED (BS 663.75)

CLT - DURING Q-2 CHECK VISUAL INSPECTION, FOUND A CRACK AT THE RIVET HOLE STR 10R TIE-CLIP AT STA 663.75 STRINGER TIE. PART REPLACED WITH IDENTICAL PART. (X)

Part: SKIN — CRACKED (NR 2 PYLON)

CLT - DURING Q-2 CHECK VISUAL INSPECTION, FOUND A 2 INCH INNER SKIN CRACK AT NR 2 PYLON/OUTBOARD SKIN AT PANEL NR 5824R OPENING. INSTALLED DOUBLER, OVERSIZE DRILL HOLE PER REPAIR DOCUMENT SRM 54-50-04C TYPICAL REPAIR. (X)

Part: FLOORBEAM — CRACKED (BS 520)

CLT - DURING EDDY CURRENT CHECK VISUAL INSPECTION, FOUND A 1.25 INCH CRACK AT STA 520 RBL 24.75 FLOORBEAM. INSTALLED NEW T-CAP, AND SEAT TRACK POWER REPAIR DOCUMENT SRM 53-00-51 AND EA 9445 AND EA 60887. (X)

Part: SHAFT — FAILED (HPT AFT)

HPT AFT SHAFT FAILED ON TAKEOFF ROLL AT 80 PERCENT N1. HPT AFT SHAFT FAILED AT SEAL TEETH CAUSING EXTENSIVE DAMAGE DOWN STREAM IN THE TURINE 2ND LPT AREAS.

Part: SEAL — ROLLED UNDER (PAX DOOR)

CLT - FLT 489 - AFTER TAKEOFF, CREW WAS UNABLE TO PRESSURIZE AIRCRAFT DUE TO MAIN ENTRY DOOR SEAL BEING PARTIALLY ROLLED UNDER. FLIGHT RETURNED TO FIELD AT CLT AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED MAIN ENTRY DOOR SEAL AND FOUND THE SEAL PARTIALLY ROLLED UNDER. OPERATED DOOR FOR PROPER SEAL, DOOR CHECKED NORMAL. (M)

Part: VSV ACTUATOR — LEAKING (RT ENGINE)

DCA - FLT 2299 - CREW REPORTED SMELLING JET FUEL FUMES IN THE COCKPIT DURING FLIGHT. MAINTENANCE FOUND THE RIGHT ENGINE VSV ACTUATOR LEAKING AND REPLACED IT. (M)

Part: SOCKET — FAILED (CABIN)

ROC - MAINTENANCE FOUND THE AFT ENTRY DOOR EXTERIOR EMERGENCY LIGHT INOP. MAINTENANCE REPLACED THE REFLECTOR LIGHT SOCKET ASSEMBLY AT THE AFT ENTRY DOOR, EXTERIOR FUSELAGE. OPS CHECK GOOD. (M)

Part: WIRE — BROKEN (CABIN)

FLT NR 592 - BWI - MAINTENANCE FOUND AISLE EMERGENCY LIGHT AT 7D INOP. MAINTENANCE REPAIRED BROKEN WIRE AT 7D. OPS CHECK SATISFACTORY. (M)

Part: EEL BATT CHARGER — INOPERATIVE (CABIN)

CLT - THE AFT EMERGENCY FLOOR LIGHTS WERE FOUND TO BE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY CHARGER AND BATTERY PACK. (M)

Part: EEL BATT PACK — INOPERATIVE (CABIN)

CLT - THE AFT EMERGENCY FLOOR LIGHTS WERE FOUND TO BE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY CHARGER AND BATTERY PACK.