N514AU

Part: WEB — CRACKED (FUSELAGE) · airframe 59,894 hrs · 36,874 cycles

CLT - MAJOR REPAIR - NR 6007491, CRACKED WEB, BS 294.5, S7L. REPLACED WEB, BS 294.5, S7L IAW B737-300 SRM 51-40-02.

Part: FITTING — CRACKED (FUSELAGE) · airframe 59,894 hrs · 36,874 cycles

CLT - MAJOR REPAIR - NR 6007479, CRACKED UPPER AND LOWER FRAME CHANNEL CLIPS, BS 348 - BS 351, S16L. REPLACED UPPER AND LOWER FRAME CHANNEL CLIPS, BS 348 - BS 351, S16L IAW B737-300 SRM 51-40-02.

Part: TIE CLIP — CRACKED (FUSELAGE) · airframe 59,894 hrs · 36,874 cycles

CLT - MAJOR REPAIR - NR 6007482, CRACKED FRAME TIE CLIP, BS 360, S14L - S15L. REPLACED FRAME TIE CLIP, BS 360, S14L - S15L IAW B737-300 SRM 51-40-02.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 59,894 hrs · 36,874 cycles

CLT - MAJOR REPAIR - NR 6007658, CRACKED WEB, BS 294.5, S15L, FORWARD ENTRY DOOR CUTOUT FORWARD FRAME. REPAIRED WEB, BS 294.5, S15L, FORWARD ENTRY DOOR CUTOUT FORWARD FRAME IAW B737-300 SRM 51-10-02.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 59,894 hrs · 36,874 cycles

CLT - MAJOR REPAIR - NR 6007659, CRACKED WEB, BS 294.5, S12L, FORWARD ENTRY DOOR CUTOUT FORWARD FRAME. REPAIRED WEB, BS 294.5, S12L, FORWARD ENTRY DOOR CUTOUT FORWARD FRAME IAW B737-300 SRM 51-10-02.

Part: BEAM — CRACKED (BS 259.5) · airframe 59,618 hrs · 59,618 cycles

STA 259.5 AT NOSE W/W CEILING WL 192.5, BL 0, RADIUS OF NOSE GEAR ACT BEAM. REPLACED GUSSET PER SRM 51-10-02, DEFECT SIZE: .75 INCH.

Part: FRAME — CRACKED (BS 492 S24R) · airframe 58,144 hrs · 58,144 cycles

STA 492.4 S24R CRACKED. REPAIRED IAW SRM 53-30-15 EA 98295, DEFECT SIZE: .50 INCH.

Part: SWITCH — SHORTED (FIRE WARNING)

CLT - FLT1770 EN ROUTE FROM MYR TO CLT, CREW REPORTED THAT BOTH THE CAPTAIN'S AND FIRST OFFICER'S FIRE WARNING LIGHTS FLASH CONSTANTLY DURING FLIGHT AND WHILE TAXING AFTER LANDING. SEEMS TO BE ASSOCIATED WITH TURBULENCE IN FLIGHT AND BUMPS ON THE TAXIWAYS AND RUNWAYS ON THE GROUND. NO OTHER INDICATIONS OF FIRE WERE NOTED. THE SYSTEM TESTED OK. MAINTENANCE TROUBLESHOT SYSTEM AND FOUND THE FIRE WARNING BELL CUTOUT SWITCH LIGHT SHORTED. REMOVED AND REPLACED SWITCH AND PERFORMED SATISFACTORY ENGINE FIRE DETECTION SYSTEM TEST PER MM 26-11-00. AIRCRAFT OK FOR SERVICE.

Part: SKIN — DELAMINATED (L/E SLAT)

PIT - FOUND TOP SKIN CORE BOND DELAMINATED 3 INCHES BY 3 INCHES, NR 5 SLAT OUTBOARD TRAILING EDGE. REMOVED DAMAGE, INSTALLED NEW CORE, FILLERS, DOUBLERS PER SRM 51-70-10. (M)

Part: SKIN — CRACKED (FUSLEAGE)

CLT - FOUND SKIN CRACKED 1.375 INCH, FS 727D STRINGER 23R. INSTALLED DOUBLER IAW SRM 53-00-01. (M)

Part: SPAR — DAMAGED (LT AILERON)

PIT - Q2 - SPAR, 2 INCHES X 1 INCH AREA, COMPOSITE DAMAGE/ DELAMINATION, LT AILERON, LEADING EDGE SPAR 34 INCH FROM OB END, UPPER FLANGE. INSTALLED REPAIR PLYS AND EXTRA IAW EA AND SRM.

Part: SKIN PANEL — DAMAGED (LT AILERON)

PIT - Q2 - TOP SKIN PANEL, 2 INCH SQ SINGLE LAYER, COMPOSITE DAMAGE, LT AILERON TOP SKIN PANEL AT TAB CONTROL ROD FAIRING MOUNT SURFACE. REMOVED DAMAGED MATERIAL, INSTALLED REPAIR PLYS, RESTORES FINISH IAW SRM.

Part: FLOOR SUPPORT — BENT (FUSELAGE)

SUPPORT, .2500 INCH X 20 INCH AREA, BENT/LIFTING METAL, BS540 BETWEEN IB AND OB SEAT TRACKS. REMOVED AND REPLACED FLOOR SUPPORT IAW SRM 51-10-2.

Part: BELTFRAME — CRACKED (FUSELAGE)

PIT - FOUND BELTFRAME CRACKED .125 INCH, IN FRAME AT FS 767 LOWER OVERHEAD BIN ATTACH POINT, RIGHT SIDE. INSTALLED REPAIR ANGLES 1 AND 2 PER TYPICAL REPAIR 53-10-20A. (M)

Part: WINDOW FRAME — CRACKED (FUSELAGE)

PIT - FOUND WINDOW FRAME CRACKED .25 INCH, UPPER OUTBOARD CORNER OF CAPTAIN WINDOW FRAME. REMOVED DAMAGE, DOUBLER INSTALLED PER SRM 53-10-01. (M)

Part: DOUBLER — CRACKED (LT NACELLE)

PIT - FOUND DOUBLER AND SKIN CRACKED .75 INCH LONG, OPENING FOR ACCESS PANEL 5727L, LEFT PYLON NACELLE STATION 180 OUTBOARD SIDE. DOUBLER INSTALLED PER TYPICAL REPAIR 54-30-07. (M)

Part: ANCHOR FITTING — CORRODED (FUSELAGE)

ANCHOR FITTINGS; CORROSION; LEVEL 1; TASK NR C53-107-02, ANCHOR FITTINGS AT STA 993R. REPLACED FITTINGS IAW SRM 51-10-2.

Part: FITTING — CORRODED (HORIZONTAL STAB)

PIT - Q2, R-1 LUG .1250 BY .2500 INCH AREA, CORROSION; NO LEVEL OR TASK, RT HORIZ STAB R-1 LUG. CLEANED CORROSION, REMOVED AND REPLACED BUSHING, CAB PLATED IAW SRM 55-10-10, NDTM 0-4-53-10.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE)

PIT - FOUND FLOOR SUPPORT HAS TWO CRACKS .25 INCH, NR 6 SLAT BOARD, 1 AT 4 INCH AND 1 AT 5 INCH OUTBOARD OF DEICING TUBE, 1 AT 5 INCH. CLEANED, TREATED AND PRIMED, REPLACED FLOOR SUPPORT. (M)

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

PIT,Q2, FLOOR SUPPORT .1250 INCH X .2500 INCH AREA, CORROSION, LEVEL 1; TASK NR C53-107-02. FLOOR SUPPORT, BETWEEN STA 312 AND 344, APPROX. 10 INCHES LT OF CENTER. CLEANED, TREATED, PRIMED AND REPLACED FLOOR SUPPORT IAW SRM 53-10-06B.

Part: ATTACH ANGLE — CRACKED (FUSELAGE)

PIT - FOUND ATTACH ANGLE CRACKED 1 INCH LONG, BS 538, STRINGER 22, PACK RAM AIR INLET AREA. FABRICATED AND INSTALLED REPAIR ANGLES PER TR 53-50-03. (M)

Part: RIB — CRACKED (RT WING)

PIT - FOUND RIB CRACKED .5 INCH, RIGHT WING AT RIB STATION 135.5, LOWER CHORD. DOUBLER INSTALLED PER EA 79058. (M)

Part: SPAR — CRACKED (LT WING)

PIT - FOUND UPPER CHORD CRACKED MORE THAN .343, BUT LESS THAN .6285, NR 2 HOLE, LEFT REAR SPAR UPPER CHORD AT RSS 224.14. OVERSIZED HOLE, INSTALLED FILLER, INSTALLED WING SKIN DOUBLER PER EA 78987. (M)

Part: KEELBEAM — WORN (FUSELAGE)

PIT - FOUND KEEL BEAM .1875 INCH DIAMETER METAL WEAR AROUND FASTENER HOLES, L/N KEEL BEAM LOWER FLANGE BETWEEN BS 704-727. DOUBLER STRAP INSTALLED PER EA 79006. (M)

Part: KEELBEAM — WORN (FUSELAGE)

PIT - FOUND KEEL BEAM WITH DEEP METAL WEAR .1875 INCH AT FASTENER HOLES, KEEL BEAM LOEWR FLANGE BETWEEN BS 727-704. INSTALLED STRAP DOUBLER PER EA 79007. (M)

Part: FITTING — CRACKED (MLG)

PIT - FOUND FITTING CRACKED .5 INCH, RT MLG SUPPORT FITTING NR 2 HOLE 5:30 POSITION. REPLACED RT MLG SUPPORT FITTING AND INSTALLED UPPER WING CHORD DOUBLER PER EO 5702V054, EA 78985 AND 78986. (M)

Part: WEB — CORRODED (FUSELAGE)

PIT - FOUND WEB CORRODED BETWEEN STATION 794 TO 847, BETWEEN STATION 794 TO 847. WEB AND STRAP REPLACEMENT ON AIR CARGO DOOR SILL PER DWG 65-47957. (M)

Part: SKIN — DAMAGED (RUDDER)

PIT - FOUND RUDDER WITH COMPOSITE DAMAGE 5.25 INCH BY 1.5 INCH SINGLE LAYER, STATION 180 PLUS 10 INCHES FROM T/E RT SIDE. REMOVED DAMAGE AND INSTALLED REPAIR PLYS PER EA 79025 AND SRM 51-70-17. (M)

Part: SKIN — CHAFED (RUDDER)

PIT - FOUND RUDDER WITH CHAFE MARKS .25 INCH BY .20 INCH, STATION 174 AT LEFT LEADING EDGE. REMOVED DAMAGE AND APPLIED REPAIR PLYS PER EA 79025 AND SRM 51-70-17. (M)

Part: STRUCTURE — WORN (RUDDER)

RUDDER, 1 INCH LENGTH, WEAR WITH KNIFE EDGING, LOWER TR EDGE. SCALED DAMAGE IAW EA79025.

Part: STRUCTURE — CRACKED (RUDDER)

PIT - FOUND RUDDER CRACKED 1 INCH WITH DELAMINATION, LOWER LEFT LEADING EDGE. REMOVED DAMAGE, INSTALLED REPAIR PLYS PER EA 79025, SRM 51-70-17. (M)

Part: SKIN — DAMAGED (RUDDER)

PIT - FOUND RUDDER WITH COMPOSITE DAMAGE 4 INCH BY 5 INCH SINGLE LAYER, STATION 170 PLUS 10 INCHES FROM T/E RT SIDE. REMOVED DAMAGE AND INSTALLED REPAIR PLYS PER EA 79025 AND SRM 51-70-17. (M)

Part: SKIN — CHAFED (RUDDER)

PIT - FOUND RUDDER COMPOSITE CHAFED 1 INCH BY .125 INCH, RUDDER LOEWR LEFT EDGE 9.5 INCHES FROM TRAILING EDGE. INSTALLED REPAIR PLYS, REINSTALLED HARDWARE AND REFINISHED PER SRM 51-70-17 AND EA 79025. (M)

Part: SUPPORT ANGLE — CORRODED (FUSELAGE)

ANGLE SUPPORT, .1250 INCH X .1250 INCH AREA, CORROSION; LEVEL 1; TASK NR C53-202-01, BS 794, S-25R. REPLACED ANGLE IAW SRM 51-40-02.

Part: ANGLE — CRACKED (FUSELAGE)

ANGLE, 1.5 INCH LONG CRACK, RT WING ROOT, BS 540 AT S22R, AFT END. INSTALLED REPAIR ANGLE DOUBLER IAW T/R 53-50-03.

Part: ANGLE — CRACKED (FUSELAGE)

PIT - FOUND ANGLE CRACKED 2 INCHES, RT WING ROOT, BS 540 AT S22R. REPLACED CREASE BEAM SECTION PER SRM 51-40-00. (M)

Part: HINGE FITTING — WORN (GROUND SPOILER)

HINGE FITTING WORN .0625 INCH AT PIVOT POINT NR 5 GROUND SPOILER OB AND WBL 169.25. FABRICATED NEW PART IAW MFG DRG 69-39228.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE)

FLOOR SUPPORT, .5 INCH CRACK, DAMAGE AREA FLOORBEAM, STA727B, LBBL 8-10. MODIFIED REPAIR ANGLE IAW TR 53-10-06B, INSTALLED DOUBLER.

Part: FLOORBEAM — CORRODED (FUSELAGE)

T-CAP, 1 INCH BY 1 INCH AREA, CORROSION; LEVEL 1; TASK NR C53-107-02, STA 328 BL 0, RBL 59 INCH, 3 AREAS. INSTALLED NEW T CAP PER SRM 53-10-51.

Part: STIFFENER — CORRODED (FUSELAGE)

PIT - FOUND STIFFENER CORRODED 1 INCH BY 1 INCH AREA, FLOOR SUPPORT BETWEEN STATION 312-328 RBL 11. REPLACED STIFFENER PER SRM 51-40-02. CORROSION LEVEL 1, TASK NR C53-107-02. (M)

Part: SKIN — CHAFED (RUDDER)

PIT - FOUND RUDDER CHAFED 1 INCH BY .125 INCH, LOWER LT EDGE 9.5 INCH FROM TRAILING EDGE. REMOVED DAMAGED MATERIAL, INSTALLED REPAIR PLYS, SEAL REPAIR AND REFINISH PER SRM 51-70-17. (M)

Part: SKIN — CRACKED (RUDDER)

PIT - FOUND RUDDER CRACKED WITH DELAMINATION AND PEELING, RUDDER LOWER LEFT LEADING EDGE. INSTALLED REPAIR PLYS, SEAL REPAIR AND REFINISH PER SRM 51-70-17 AND EA 79025. (M)

Part: BUSHING — CORRODED (HORIZONTAL STAB)

PIT - FOUND BUSHING CORRODED .125 INCH BY .125 INCH, RIGHT HORIZ STAB, R-8 CLEVIS BUSHING. MADE NEW BUSHINGS WITH AMS 4640 PER SRM 55-10-10. (M)

Part: BUSHING — CORRODED (HORIZONTAL STAB)

PIT - FOUND BUSHING CORRODED .25 INCH BY .125 INCH AREA, LEFT HORIZONTAL NR 12 LUG. NEW BUSHING INSTALLED PER SRM 55-10-10. (M)

Part: BUSHING — CORRODED (HORIZONTAL STAB)

PIT - FOUND BUSHING CORRODED .125 INCH BY .125 INCH AREA, LEFT HORIZ STABILIZER STAB NR 9 LUG. MADE NEW BUSHING PER SRM 55-10-10. (M)

Part: BUSHING — CORRODED (HORIZONTAL STAB)

PIT - FOUND BUSHING CORRODED .125 INCH BY .125 INCH AREA, RT HORIZ STAB R-10 LUG. NEW BUSHING INSTALLED PER SRM 55-10-10. (M)

Part: BUSHING — CORRODED (HORIZONTAL STAB)

PIT - FOUND BUSHING CORRODED .25 INCH BY .25 INCH AREA, RIGHT HORIZ STAB R10 LUG. MADE NEW BUSHING AMS 4640 PER SRM 55-10-10. (M)

Part: WEB — CRACKED (CARGO DOOR)

PIT - FOUND AFT CARGO INNER WEB CRACKED .25 INCH, LIGHTENING HOLE AFT OF SPRING MOUNT. REMOVED DAMAGE, INSTALLED DOUBLER PER EA 78996. (M)

Part: STRUCTURE — CRACKED (PAX DOOR)

PIT - FOUND FORWARD ENTRY DOOR CRACKED 1 INCH, LOWER FORWARD FRAME CORNER. REMOVED DAMAGE, REPAIRED WITH ANGLES PER SRM 51-70-13. (M)

Part: CHANNEL — CRACKED (FUSELAGE)

PIT - FOUND FLOOR CHANNEL CRACKED .125 INCH, STATION 867 RBBI 3.00 FLOOR CHANNEL AFT CARGO NUTPLATE HOLE. CRACK REMOVED AND FILLER AND DOUBLER INSTALLED PER SRM 51-70-11. (M)

Part: HOUSING — WORN (DOOR LATCH)

PIT - FOUND HOUSING WITH EXCESSIVE WEAR CAUSING GOUGES, LATCH HANDLE SHAFT HOUSING, AFT CARGO DOOR. BLENDED OUT GOUGES AND REPLACED WORK HOUSING ASSEMBLY PER SRM 52-30-01, FIG 101, DETAIL V. (M)

Part: FRAME — CRACKED (FUSELAGE)

PIT - FOUND BELL FRAME CRACKED .125 INCH, SIDE AIR SUPPORT RIVET STATION 908 AND S-9. DOUBLER INSTALLED PER SRM 53-60-07, FIG 201, SRM 53-00-07, FIG 201. (M)

Part: SKIN — WORN (RUDDER)

PIT - FOUND COMPOSITE RUDDER SKIN WITH WEAR AND KNIFE EDGING, RUDDER RIGHT LOWER EDGE. REMOVE DAMAGE, INSTALLED REPAIR PLYS, SEAL AND REFINISH PER SRM 51-70-17 AND EA 79025. (M)

Part: STRINGER — CRACKED (FUSELAGE)

PIT - FOUND STRINGER CRACKED .5 INCH, STRINGER 5A, BS 1138. INSTALLED NEW PART, ANGLES, FILLER SPER TYPICAL REPAIR 53-80-04. (M)

Part: SKIN — DAMAGED (RUDDER)

PIT - FOUND RUDDER COMPOSITE SKIN DAMAGE 5.25 INCH BY 1.5 INCH SINGLE LAYER, RUDDER RIGHT SIDE AT FS 180 10 INCHES FROM TRAILING EDGE. INSTALLED REPAIR PLYS, SEAL REPAIR AND REFINISH PER SRM 51-70-17 AND EA 79025. (M)

Part: ANCHOR FITTING — CORRODED (FUSELAGE)

ANCHOR FITTINGS, .1250 INCH BY .1250 INCH AREA, CORROSION: LEVEL 1; TASK NR C53-107-02 ANCHOR FITTINGS (2) STA 993L. REPLACED FITTINGS IAW SRM 51-10-2.

Part: SKIN — CHAFED (RUDDER)

PIT - FOUND RUDDER COMPOSITE SKIN CHAFED .25 INCH BY .125 INCH SINGLE LAYER CHAFE MARKS, RUDDER LEFT LEADING EDGE AT STATION 174. REMOVED DAMAGE, INSTALLED REPAIR PLYS, SEAL REPAIR AND REFINISH PER SRM 51-70-17 AND EA 79025. (M)

Part: DUCT — CRACKED (FUSELAGE)

PIT - AIRCO PAC INLET DUCT CRACKED 1 INCH, BS 538 S22 PACK RAM AIR INLET LEFT SIDE. INSTALLED DOUBLER PER TYPICAL REPAIR 53-50-03. (M)

Part: SUPPORT — DAMAGED (FUSELAGE)

PIT - FOUND SUPPORT HAS 15 OVERSIZED HOLES, BS 540 BETWEEN RIGHT INBOARD AND OUTBOARD SEAT TRACKS. REMOVED AND REPLACED FLOOR SUPPORT PER SRM 53-00-52. (M)

Part: BELTFRAME — CRACKED (FUSELAGE)

PIT - FOUND BELTFRAME CRACKED .125 INCH, FS 787 LEFT OVERHEAD BIND LOWER ATTACH POINT. REMOVED CRACK AND INSTALLED REPAIR ANGLES PER TYP REPAIR 53-10-20A. (M)

Part: STOP — CRACKED (PAX DOOR)

PIT - FOUND .5 INCH CRACK , AFT DOOR STOP NR'S 4, 5 AND 6 AT PAN. INSTALLED DOUBLERS PER TYPICAL REP 52-10-16. (M)

Part: BELTFRAME — CRACKED (FUSELAGE)

PIT - FOUND BELTFRAME CRACKED .125 INCH, AT FS 807, RIGHT OVERHEAD BIN LOWER ATTACH POINT. INSTALLED 1 AND 2 DOUBLER PER TR 53-10-20A. (M)

Part: INTERCOSTAL — CRACKED (FUSELAGE)

PIT - FOUND FLOOR SUPPORT INTERCOSTAL CRACKED THREE PLACES, 3 INCH EACH, BETWEEN 927 AND 947 AT 0 INCH LBL. REMOVED AND REPLACED PER SRM 53-60-51. (M)

Part: WEB — CRACKED (FUSELAGE)

PIT - FOUND WEB CRACKED .25 INCH LONG, STATION 1040 BL 0 JUST ABOVE CENTER PLUG OF PRESSURE WEB. MANUFACTURED REPAIR DOUBLER AND FILLER, PLATE/DOUBLER PER SRM 53-80-08 FIG 201. (M)

Part: SKIN — CRACKED (AFT CARGO DOOR)

PIT - FOUND AFT CARGO DOOR CRACKED 1.5 INCH BY 1 INCH, MIDDLE OF DOOR 6 INCH AFT OF L/E. INSTALLED DOUBLER PER TYPICAL REPAIR 52-10-01, REV A. (M)

Part: SKIN — CRACKED (DOOR)

PIT - FOUND SKIN CRACKED .1875 INCH, LOWER AFT CORNER EDGE. REMOVED DAMAGED AREA, AND INSTALLED DOUBLER PER SRM 52-00-01. (M)

Part: MODULE — FAILED (HYD SYSTEM)

ON CLIMB-OUT, EN ROUTE, CREW RECEIVED A LEADING EDGE SLAT TRANSITION LIGHT. CREW COULD NOT RETRACT THE LEADING EDGE SLATS. TRAILING EDGE DEVICES WERE NORMAL. CREW ELECTED TO RETURNED TO FIELD WHERE THE FLIGHT LANDED WITHOUT FURTHER INCIDENT. NO EMERGENCY WAS DECLARED. MAINTENANCE REMOVED AND REPLACED THE STANDBY HYDRAULIC SYSTEM MODULE IAW MM 29-15-81. OPERATIONAL CHECK AND LEAK CHECK GOOD. (M)

Part: HYDRAULIC SYSTEM — CONTAMINATED (A SYSTEM)

DURING GEAR RETRACTION AFTER TAKEOFF FROM PIT, MASTER CAUTION HYD LIGHT ILLUMINATED ALONG WITH BOTH 'A' SYSTEM LOW PRESSURE LIGHTS. PRESSURE IN 'A' SYSTEM READ ZERO. CREW NOTICED A STRONG HYD FLUID ODOR DURING THIS TIME. ONCE LANDING GEAR RETRACTED, ALL RETURNED TO NORMAL WITH ODOR DISSIPATING. FLT RETURNED TO FIELD & LANDED WITHOUT INCIDENT. LANDING GEAR & FLAP EXTENSION NORMAL. NO EMERGENCY DECLARED. MAINT CHECKED FLUID LEVELS & CHECKED FOR LEAKS. RAN BOTH ENGINES & EXERCISED ALL FLT CONTROLS SEVERAL TIMES. PRESSURES REMAINED NORMAL, NO ODOR OR LEAKS PRESENT. IT WAS BELIEVED THAT THERE WAS POSSIBLE AIR IN THE HYD SYS AS AN ENGINE CHANGE WAS COMPLETED PRIOR TO FLT. AIRCRAFT OK FOR SERVICE. (M)

Part: CONTROL PANEL — FAULTY (COCKPIT)

CLT - FLT 1125 - EN ROUTE PIT TO MSY, THE FUEL CROSSFEED VALVE WOULD NOT CLOSE AND THE LEFT CENTER BOOST PUMP LOW PRESSURE LIGHT ILLUMINATED WITH 1,000 LBS OF FUEL IN THE TANK. FLIGHT DIVERTED TO CLT AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE REMOVED AND REPLACED THE P5-2 FUEL PANEL AND THE RIGHT CENTER LOW PRESSURE SWITCH, P/N 7G110-6. OPERATIONAL CHECK GOOD. (M)

Part: CHARGER — FAILED (CABIN)

PIT - MAINTENANCE FOUND THE EMERGENCY LIGHT OVER THE AFT LEFT ENTRY DOOR INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE BATTERY PACK AND CHARGER ASSEMBLY. OPERATIONAL CHECK GOOD. (M)

Part: SKIN — CRACKED (FUSELAGE)

PIT - FOUND SKIN CRACKED 1 INCH LONG, STATION 380 B/L 0. INSTALLED REPAIR DOUBLER PER EA 75166 AND TYPICAL REPAIR 53-30-07. (M)

Part: WIRE — BROKEN (CABIN)

EWR - MAINTENANCE FOUND THE EMERGENCY LIGHT ON SEAT ROW 5ABC INOPERATIVE. MAINTENANCE REPAIRED A BROKEN WIRE UNDER SEAT 5C. OPERATIONAL CHECK GOOD. (M)

Part: CONTROLLER — FAULTY (CABIN PRESSURE)

RIC - FLT 1980 - EN ROUTE NAS TO LGA, AT FL330, LOST CABIN PRESSURIZATION, CABIN ALTITUDE WARNING SOUNDED. CABIN ALTITUDE WAS AT 10K FT AND CLIMBING AT 600 FPM. DESCENDED TO FL310. CREW ON OXYGEN. REGAINED CONTROL OF CABIN THROUGH USE OF MANUAL PRESSURIZATION MODE, FOR A SHORT TIME, CABIN BEGAN TO CLIMB AGAIN. DURING DESCENT THROUGH FL200, CABIN REACHED ITS MAX ALTITUDE OF 15K FT. O2 MASKS AUTO DEPLOYED AT FL280. DIVERTED TO RIC AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE REMOVED AND REPLACED THE CABIN PRESSURE CONTROLLER. OPS CHECK GOOD. FOUND THE CARGO DOORS, SERVICE DOORS, ENTRY DOORS AND FUSELAGE DRAIN VALVES LEAKING. REPAIRED DOOR LEAKS AND REMOVED AND REPLACED FUSELAGE DRAIN VALVES. LEAK

Part: CONTROL CABLE — EXCESS PLAY (MANUAL EXTENSION)

FLT 493 - FINAL APPROACH TO RDU, APPROX 4,000 FT AGL, CREW DID NOT RECEIVE THE RT MLG GREEN LIGHT ON GEAR EXTENSION. CREW ABORTED APPROACH AND REPLACED BULB FOR RT MLG INDICATION WITH NO HELP. CREW ACCOMPLISHED MANUAL GEAR EXTENSION PROCEDURES WITH STILL NO CHANGE IN RT MLG LIGHT STATUS. CREW DECLARED AN EMERGENCY AND PREPPED FOR AN EMERGENCY LANDING. FLT LANDED INCIDENT. MX FOUND THE WRONG TYPE OF BULB INSTALLED FOR THE RT MLG INDICATION. REPLACED BULB WITH CORRECT TYPE. OPERATIONAL CHECK GOOD. AIRCRAFT WAS FERRIED FOR REPAIR OF RT MLG MANUAL EXTENSION PULL HANDLE NOT STOWING. APPROX 5 INCHES OF SLACK WAS IN CABLE. MX RESET RT MLG MANUAL EXTENSION PULL HANDLE, CHECKED CABLE RUN AND ADJUSTMENT.(M)

Part: DOOR — LEAKING (AFT SERVICE)

ATL - FLT 2403 - ON CLIMB-OUT FROM ATL, EN ROUTE TO PHL, CREW REPORTED THE AIRCRAFT WOULD NOT PRESSURIZE IN ANY PRESSURIZATION MODE. FLIGHT RETURNED TO FIELD AT ATL AND LANDED WITHOUT FURTHER INCIDENT. NO EMERGENCY WAS DECLARED. MAINTENANCE FOUND THE AFT RIGHT SERVICE DOOR NOT SEALING PROPERLY. (M)

Part: CHARGER — INOPERATIVE (CABIN)

PIT - MAINTENANCE FOUND THE EMERGENCY LIGHTS INOPERATIVE FROM SEAT ROW 17 AND AFT. ALSO, FOUND TWO AFT EMERGENCY EXIT DOOR LOWER LIGHTS INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE BATTERY PACK (P/N 2013-1A) AND CHARGER ASSEMBLY, LOCATED ABOVE AISLE BETWEEN LAST ROW OF SEATS, IN ASSOCIATION WITH MM 33-51-51. OPS CHECK GOOD. (M)

Part: HOSE — FAILED (NR 2 ENGINE)

YUL - FLT 0442 - EN ROUTE FROM PIT TO YUL, AT FL330, THE CABIN ALTITUDE WARNING HORN SOUNDED. CREW PERFORMED EMERGENCY PROCEDURES AND WHEN CABIN ALTITUDE CLIMED TO MORE THAN 10,000 FEET, THEY DECLARED AN EMERGENCY. CREW DESCENDED THE FLIGHTS TO FL100 AND WERE ABLE TO CONTROL CABIN ALTITUDE IN MANUAL AND STANDBY MODE. FLIGHT CONTINUED ONTO YUL AT FL100 AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE REMOVED AND REPLACED THE NR 2 ENGINE HOSE ASSY FROM THE 450 DEGREE THERMOSTAT TO THE PRESSURE REGULATOR AND SHUTOFF VALVE (PRSOV). OPS CHECK GOOD. DUCT PRESSURE NORMAL PER MM 36-11-05. ACCOMPLISHED CHECK OUT OF PRESSURIZATION SYSTEM. PRESSURIZATION SYSTEM CHECKS NORMAL. (M)

Part: WARNING SYSTEM — ACTIVATED (COCKPIT)

YUL - FLT 442 - EN ROUTE FROM PIT, AT FL330, THE CABIN ALTITUDE WARNING HORN SOUNDED. CREW PERFORMED EMERGENCY PROCEDURES AND WHEN CABIN ALTITUDE CLIMBED TO MORE THAN 10,000 FEET, THE DECLARED AN EMERGENCY. CREW DESCENDED THE FIGHT TO FL100 AND WERE ABLE TO CONTROL CABIN ALTITUDE IN MANUAL AND STANDBY MODE. FLIGHT CONTINUED ONTO YUL AT FL100 AND LANDED WITHOUT FURTHER INCIDENT. (M)

Part: ADC — FAILED (EE BAY)

CLT - FLT 230 - AT ROTATION, THE FIRST OFFICERS ALTIMETER AND AIRSPEED INDICATOR FAILED. FLIGHT RETURNED TO FIELD AT CLT AND LANDED WITHOUT FURTHER INCIDENT. NO EMERGENCY WAS DECLARED. MAINTENANCE REMOVED AND REPLACED THE NR 2 AIR DATA COMPUTER. FUNCTIONAL CHECK GOOD. (M)

Part: SWITCH — DAMAGED (RT ACM)

PIT - FLT 1140 - EN ROUTE FROM LGA-PIT, FLIGHT LOST PRESSURIZATION AT FL220. DESCENDED TO FL090 AND SET PRESSURIZATION SYSTEM MANUAL. OXYGEN MASKS DEPLOYED NORMALLY. FLIGHT LANDED WITHOUT FURTHER INCIDENT AT PIT. MAINTENANCE FOUND A DAMAGED COMPRESSOR DISCHARGE OVERHEAT SWITCH ON THE RIGHT ACM DAMAGED. REMOVED AND REPLACED COMPRESSOR DISCHARGE OVERHEAT SWITCH. PRESSURIZED AIRCRAFT TO 5 PSI. OPERATIONAL CHECK AND LEAK CHECK GOOD. (M)

Part: SKIN — CRACKED (FUSELAGE)

PIT - FOUND SKIN CRACKED .5 INCH, FORWARD SERVICE LOWER AFT CORNER OF DOOR CUTOUT. REPAIRED PER SRM 53-10-01 PAGE 206 AND EA 54358. (M)

Part: BEARING — FAILED (NR 1 ENGINE)

CLT - FLT 1782 - CAPTAIN REPORTED THE NR 1 ENGINE EXPERIENCED COMPRESSOR STALLS AT FL 370, REPEATED AT FL 350, THEN A SUSTAINED SURGING AT FL 310. CREW ELECTED TO DIVERT TO CLT WHERE THE FLIGHT LANDED WITHOUT INCIDENT. NO EMERGENCY WAS DECLARED. DURING TAXI-IN, THE NR 1 ENGINE SUSTAINED A VIBRATION AND AN UNCONTROLLABLE EGT (733 AND CLIMBING). THE NR 1 ENGINE WAS SHUT DOWN AT THIS TIME. AIRCRAFT PROCEEDED TO TAXI TO THE GATE. MAINTENANCE REMOVED AND REPLACED THE NR 1 ENGINE ASSEMBLY PER JOB CARD. ENGINE RUN, OPERATIONAL CHECK AND LEAK CHECK GOOD. FOLLOW-UP REVEALED NR 4 BEARING FAILED PER OPERATOR P/P ENGINEER. (X)

Part: NAV SWITCH — FAILED (FLT COMPARTMENT)

BUF - FL 1078 - FIRST OFFICERS HSI LOCKED UP ON NAV AFTER LIFTOFF. THE CDI COURSE KNOB WOULD NOT ROTATE CDI AND SEEMED TO BE FROZEN IN NAV SELECTION. FLIGHT DIVERTED TO BUF AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE REMOVED AND REPLACED THE VOR/ILS NAV SWITCH ON THE GLARESHIELD. OPERATIONAL CHECK GOOD. (M)

Part: ATTITUDE DIR IND — FAILED (COCKPIT P1 PNL)

MCI - FLT 139 - AT CRUISE, CAPTAINS ATTITUDE IN PITCH BEGAN JUMPING 2 TO 3 DEGREES. SELECTED ATTITUDE TRANSFER SWITCH TO 'BOTH ON 2' WITH NO HELP. FLIGHT DIVERTED TO MCI WITH NO FURTHER INCIDENT. MAINTENANCE REPLACED THE CAPTAINS ATTITUDE DIRECTOR INDICATOR. PERFORMED OPS CHECK OF ADI PER MM. OPS CHECK GOOD. (M)