N908HA

Part: OIL SYSTEM — LOW (NR 1 ENGINE) · airframe 68,377 hrs · 77,594 cycles

AFTER DEICING, ON TAKEOFF, NR 1 ENGINE OIL PRESSURE WARNING LIGHT ILLUMINATED. ABORTED TAKEOFF AND SHUTDOWN NR 1 ENGINE. WARNING LIGHT WAS ILLUMINATED FOR APPR0X 5 SECONDS. INSPECTED NR 1 ENGINE AND FOUND ENGINE 3 QUARTS LOW. SERVICED ENGINE WITH 3 QUARTS OF 2380. GROUND RAN ACFT. ALL INDICATIONS NORMAL. OK FOR SERVICE.

Part: WARNING LIGHT — FALSE ACTIVATION · airframe 68,354 hrs · 77,566 cycles

NR 1 ITT INCREASED AND DECREASED ON CLIMBOUT. BOTH ANAOLOG AND DIGITAL. ALL OTHER PARAMETERS NORMAL. INSPECTED ENGINE WIRING FOR CONDITION AND SECURITY. CHECKED TRIM RESISTOR, READ WIRING FROM ENGINE TO GAUGE. CHECKED READING AT BOTH TERMINAL BLOCKS ON ENGINE AND CALIBRATION OF SYS IAW PW MM 72-01-60. NO DEFECTS NOTED. RAN ENGINE FOR 20 MINUTES AT VARIOUS POWER SETTINGS. SYS OPS CHECKED NORMAL AT THIS TIME.

Part: LENS — DIRTY (EMERGENCY LIGHT) · airframe 68,340 hrs · 77,551 cycles

EMERGENCY EXIT BETA LIGHT IS DIM. R & R BETA LIGHTS ON AFT EMERGENCY DOORS. CLEANED LENS COVER AND REINSTALLED. OPS CHECKED GOOD.

Part: BULB — FAILED (EMERGENCY LIGHT) · airframe 68,204 hrs · 77,383 cycles

EMERGENCY FLOOR PATH LIGHT IS INOPERATIVE AT ROW 2DF. R & R BULB AT ROW 2DF EMERGENCY FLOOR PATH LIGHTING.

Part: AILERON — OUT OF ADJUST (LEFT) · airframe 67,405 hrs · 76,403 cycles

CONTROL COLUMN IS 10-15 DEGREES RT OF CENTER ON TAKEOFF. LARGE CONTROL INPUTS REQUIRED AT 150 TO MAINTAIN LEVEL FLIGHT. ADJUSTED LT AILERON IAW MM 27-13-00. ACFT RELEASED FOR EVALUATION FLIGHT.

Part: RECORDER — FAILED (FLT DECK) · airframe 66,498 hrs · 75,382 cycles

FDR CAUTION LIGHT ILLUMINATED. R & R FDR IAW 31-33-02. OPS CHECKED GOOD.

Part: STRINGER — CORRODED (RT NACELLE) · airframe 66,362 hrs · 75,227 cycles

STRINGER 31 RT AT STA X336 IS CORRODED. BLENDED MINOR SURFACE CORROSION IAW SRM 51-20-11. ALODINED AND PRIMED AREA IAW AMM 51-25-03.

Part: THRESHOLD — CORRODED (PAX DOORWAY) · airframe 66,362 hrs · 75,227 cycles

PAX DOOR THRESHOLD IS CORRODED. R & R PAX DOOR THRESHOLD IAW ENG DWG 8531241.

Part: STRUCTURE — CORRODED (BS 207) · airframe 66,362 hrs · 75,227 cycles

CORROSION FOUND AT S31, STA 207. BLENDED MINOR SURFACE CORROSION IAW SRM 51-20-11. ALODINED AND PRIMED AREA IAW AMM 51-25-03.

Part: CHANNEL — CORRODED (PAX DOORWAY) · airframe 66,362 hrs · 75,227 cycles

PAX DOOR THRESHOLD CHANNEL IS CORRODED. CLEANED MINOR CORROSION OFF CHANNEL, ALODINED AND PRIMED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 66,362 hrs · 75 cycles

EMERGENCY LIGHTS ABOVE RT FWD EMERGENCY EXIT, GALLEY AND RT FWD FUSELAGE IS NOT WORKING. R & R LOWER EMERGENCY LIGHT BATTERY PACK.

Part: BOLT — CORRODED (LT ELEVATOR TRIM) · airframe 66,362 hrs · 75,227 cycles

LT TRIM TAB CONTROL ROD ATTACH HARDWARE HAS SURFACE CORROSION. R & R TRIM TAB CONTROL ATTACH HARDWARE IAW AMM 27-36-21.

Part: LIGHT — BROKEN (CABIN) · airframe 66,362 hrs · 75,227 cycles

CENTER FLOOR PANEL NR 6 EMERGENCY LIGHT STRIP BROKEN. R & R EMERGENCY LIGHT STRIP ON PANEL.

Part: LENS — MISINSTALLED (EMERGENCY LIGHT) · airframe 66,263 hrs · 75,105 cycles

EXIT LIGHT LENS COVER ABOVE RT FORWARD EMERGENCY EXIT NOT PROPERLY INSTALLED, CANNOT REMOVE EXIT FROM OPENING. REMOVED EXIT LENS COVER AND REINSTALLED DOOR CORRECTLY. OPERATES NORMALLY.

Part: PRESSURE SWITCH — MALFUNCTIONED (SPOILERS) · airframe 65,329 hrs · 74,080 cycles

UPON ADVANCING POWER LEVERS FOR TAKEOFF, THE ROLL SPOILERS OTBD HYD CAUTION LIGHT ILLUMINATED AND THE ROLL OTBD ADVISORY LIGHT STAYED ON. R & R ROLL SPOILER PSI SWITCH, GROUND RAN NR 2 ENGINE, OPS AND LEAKED CHECKED GOOD.

Part: ELECTRONIC UNIT — FAILED (RADIO) · airframe 65,158 hrs · 73,912 cycles

CAN NOT TRANSMITT EITHER RADIO FROM NR1 ACP. R & R REU. OPS CHECKED GOOD. OK FOR SERVICE IAW -8 MM 23-50-00.

Part: SPOILER SYS — MALFUNCTIONED (RIGHT) · airframe 64,759 hrs · 73,492 cycles

ABORTED TAKEOFF DUE TO RT INBD AND OTBD SPOILERS NOT RETRACTING AFTER POWER LEVERS ADVANCED. AFTER CYCLING FLIGHT TAXI SWITCH AND ALL SPOILERS RETRACTED AFTER ADVANCING POWER LEVERS. INSPECTED RT SPOILERS, NO DEFECTS NOTED, GROUND RAN ACFT, CYCLED SPOILERS SEVERAL TIMES. NO DEFECTS NOTED.

Part: BULB — BURNED OUT (EMERGENCY LIGHT) · airframe 64,512 hrs · 73,213 cycles

ROW 6 EMERGENCY FLOOR PATH LIGHT IS INOP. R & R LIGHT BULB AT ROW 6, OPS CHECKED GOOD.

Part: INVERTER — FAILED · airframe 64,247 hrs · 72,925 cycles

26AC AND SECONDARY INVERTER CAUTION LIGHTS ILLUMINATED IN FLIGHT. SECONDARY INVERTER AND 115AC CIRCUIT BREAKER POPPED. LOST INSTRUMENT POWER RT SIDE INVERTERS WITH SECONDARY CIRCUIT BREAKER OUT 115 AC BUSS CIRCUIT BREAKER RESETS. R & R SECONDARY INVERTER IAW -8MM 24-22. OPS CHECKED OK.

Part: SWITCH — FAILED (ELEVATOR HEAT) · airframe 64,247 hrs · 72,925 cycles

LT ELEVATOR HORN HEAT CAUTION LIGHT ILLUMINATED IN FLIGHT. REMOVED SWITCH 3015-S4 AND RETERMINATED WIRING 33A16-1 AND 9C16A-1 REF, WIRING DIAGRAM 30-25-02. OPS CHECKED GOOD IAW WORKCARD 30-10-10F.

Part: LAMP — BURNED OUT (EMERGENCY LIGHT) · airframe 64,208 hrs · 72,883 cycles

ROW 2 CEILING EMERGENCY LIGHT INOP. RELAMP ROW 2 CEILING EMERGENCY LIGHT, OPS CHECKED GOOD.

Part: OIL COOLER — MALFUNCTIONED (NR 1 ENGINE) · airframe 63,359 hrs · 71,934 cycles

ON CLIMBOUT, NR1 ENGINE OIL TEMP CLIMBED TO 125 DEGREES C. CYCLED ENGINE INTAKE DOOR TO SEE IF TEMP WOULD DECREASE. TEMP STAYED THE SAME. THEN REDUCED TORQUE TO 50 PERCENT. TEMP WENT TO 120 DEGREES C AFTER 18 MINUTES. REDUCED TORQUE TO 37.5 PERCENT. THEN TEMP DECREASED TO 110 DEGREES C. R & R OIL COOLER THERMAL VALVE IAW CMM 79-20-11. OPS AND LEAK CHECKED GOOD.

Part: CONTROL HANDLE — MALFUNCTIONED (MLG) · airframe 62,870 hrs · 71,344 cycles

AT ROTATION, AN ABNORNAL THUMP SOUND WAS HEARD FROM NOSE GEAR. RED NOSE GEAR UNSAFE LIGHT STAYED ON AND LT AND RT MAIN DOOR AMBER LIGHTS STAYED ON. AFTER APPR0X 4 MINUTES, GEAR RETRACTED AND LIGHTS EXTINGUISHED. PERFORMED ALTERNATE EXTENSION AT DESTINATION. R & R GEAR CONTROL HANDLE. ALSO ADJUSTED NOSE GEAR FWD DOORS IAW MM 32-21-00, CYCLED GEAR TEN TIMES. OPS CHECKED GOOD AT THIS TIME.

Part: FRAME SPLICE — CRACKED (ZONE 100) · airframe 60,750 hrs · 68,868 cycles

SPLICE IS CRACKED ON LT SIDE OF FLIGHT COMPARTMENT FRAME JOINT AT STA X136.8 AND STR. 15P. ON LT SIDE OF FLIGHT COMPARTMENT FRAME JOINT AT STA. 136.8 AND STR 15P SPLICE REMOVED AND REPLACED IAW SRM 51-40-00 PD 1777.

Part: BRACKET — CORRODED (PAX DOOR) · airframe 60,750 hrs · 68,868 cycles

CORROSION FOUND ON PAX DOOR STEP BRACKETS (UNDERNEATH STAIRS, BOTH CTR BRACKETS AND FWD BOTTOM BRACKETS). PAX DOOR STEP BRACKET (BOTH CTR AND FWD BOTTOM) REPLACED IAW MM 20-14-01.

Part: ANGLE — CORRODED (PAX DOOR) · airframe 60,750 hrs · 68,868 cycles

CORROSION FOUND ON PAX DOOR SHELL ANGLE AT BOTTOM AFT CORNER. PAX DOOR SHELL ANGLE REPLACED IAW MM 52-10-00 WITH SERVICABLE PART ON CARD SEC 2518.

Part: SKIN — DENTED (FUSELAGE) · airframe 60,750 hrs · 68,868 cycles

DURING HEAVY CHECK THE FOLLOWING DENTS FOUND ON RT FUSELAGE SKIN BETWEEN STA X136.8 AND 151.6 BETWEEN STR 23S-24S. BOTH DENTS FOUND TO BE IN LIMITS IAW EA 01-09233 AND EO 8-53-09-304.

Part: INTERCOSTAL — CORRODED (RUDDER) · airframe 60,750 hrs · 68,868 cycles

CABIN UNDER FLOOR STA X396 RUDDER BELLCRANK INTERCOSTAL CORRODED. RUDDER CABLE TENSION RELEASED 07-06-09. UPPER CHANNEL OF CONTROL RUDDER SYS CTR BELLCRACK REPLACED WITH NEW PART LOCALLY FABRICATED, (FABRICATION COVERED ON WC SEQ 20-70) INSTALLED WITH SOLID RIVETS IAW SRM 51-40-00.

Part: SKIN — CORRODED (LT WING) · airframe 60,750 hrs · 68,868 cycles

CATEGORY 1 CORROSION FOUND UNDER THE LT WING AUX BOOST PUMP EXTERNAL ANTI FRET RING ON THE LWR WING SKIN. LT AUX BOOST PUMP EXTERNAL AND INTERNAL SURFACE OF DOUBLER REPAIRED IAW RD8-57-4320 AND RD8-57-1907.

Part: STRUCTURE — DENTED (FUSELAGE) · airframe 60,750 hrs · 68,868 cycles

DURING HEAVY CHECK A DENT WAS REPORTED AT 2 INCHES AFT OF THE PRESSURE BULKHEAD, HAS AN INSPECTION INTERVAL ESTABLISHED BY AN EO SIGNED BY A PERSON NOT AUTHORIZED AS A DT ENGINEER TO DETERMINE AN INSPECTION INTERVAL. THE DENT MAY NOT BE LOCATED IN THIS AREA SINCE IT WAS NOT REPORTED IN THE DAMAGE EVALUATION FILE (FCD). PIEDMONT MAINTENANCE PROGRAM DID NOT HAVE THE CORRECT INSPECTION INTERVAL AS REQUIRED BY EO 8-53-00-150. THE INSPECTION WAS NOT BEING PERFORMED AT THE 1500HR INTERVAL. THE RECORDS MANAGER WAS NOTIFIED AND ISSUED THE INSPECTION THAT WAS COMPLIED WITH ON FEBRUARY 20, 2009. CORRECTION: DENT AT STA X112 STR 27-28P COVERED BY EO 8-53-00-410 AND EO8-53-00-150. BOTH ARE SUPERSEDED BY STS EA01-09066, AND RECORDED ON DAMAGE EVALUATION FILE (FDC) FILE NUMBER 53-82).

Part: FITTING — CORRODED (ZONE 100) · airframe 60,750 hrs · 68,868 cycles

CABIN INTERNAL LAVATORY FITTING CORRODED. CABIN INTERNAL LAVATORY FITTING REPLACED AND NEW PART INSTALLED IAW SRM 51-40-00, DWA 85320983 AND RD8-511-102

Part: HOUSING — CORRODED (BOOST PUMP) · airframe 60,750 hrs · 68,868 cycles

LEFT AUX BOOST PUMP RECEIVER FOUND CORRODED ON THREAD. LT AUX BOOST PUMP ASSY REMOVED AND REINSTALLED. TRANSFERED ON TASK CARD 005-55-13I. REMOVED AND REINSTALLED PLUG-IN ELEMENT IAW 28-21-16. NEW AUX PUMP RECEIVER INSTALLED IAW 28-21-16. OPS AND LEAK CHECKED.

Part: PANEL — CORRODED (ZONE 600) · airframe 60,750 hrs · 68,868 cycles

RIGHT WING STRESS PANEL 623AT CORRODED. RT WING STRESS PANEL 623AT REPLACED IAW AMM 57-20-05 PG 2425. RT WING STRESS PANEL 623AT INSTALLATION COVERED BY CARD 57-25-02R.

Part: ANGLE — CORRODED (ZONE 100) · airframe 60,750 hrs · 68,868 cycles

BAGGAGE COMPARTMENT FLOOR LEVEL AT STA 597, STEP ANGLE FOUND CORRODED. REMOVED AND REPLACED IAW SRM 51-40-00 AT FLOOR LEVEL STA X 597 STEP ANGLE.

Part: APU — SMOKE · airframe 59,787 hrs · 67,816 cycles

WITH AUXILIARY POWER UNIT RUNNING AND BLEEDS ON, SMOKE IN CABIN AND LAVATORY SMOKE DETECTOR SOUNDS. RAN AUXILIARY POWER UNIT WITH BLEED ON, VISIBLE HAZE APPEARS. INSP AUXILIARY POWER UNIT AREA NO DEFECTS NOTED. RAN ENGINES WITH BLEEDS NO HAZE NOTED. R&R AUXILIARY POWER UNIT PER WORK CARD 49-20-02X OPS CHECK GOOD. NO SMOKE FROM APU BLEEDS.

Part: AHRS — FAILED (NR 2) · airframe 59,745 hrs · 67,771 cycles

NR 2 ATTITUDE HEADING AND REFERENCE SYSTEM. R&R NR 2 ATTITUDE HEADING AND REFERENCE SYSTEM COMPUTER. OPS CHECK GOOD IAW MM 34-20-01.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 59,647 hrs · 67,662 cycles

THE 2ND CEILING EMERGENCY LIGHT INOP. RELAMP 2ND CEILING EMERGENCY LIGHT BULB.

Part: HYDRAULIC SYSTEM — CONTAMINATED (NR 2) · airframe 59,617 hrs · 67,622 cycles

JUST AFTER TAKEOFF, THE 'RUDDER PRESSURE' AND 'RUDDER FULL PRESSURE' CAUTION LIGHTS ILLUMINATED. THE CREW ELECTED TO RETURN TO THE ORIGINATING AIRFIELD. AFTER THE LANDING GEAR AND FLAPS WERE EXTENDED, THE CAUTION LIGHTS EXTINGUISHED. BOTH HYDRAULIC SYSTEMS QUANTITIES REMAINED NORMAL. MAINTENANCE DISCOVERED THE NR 2 HYDRAULIC SYSTEM HAD AIR IN THE SYSTEM. SYSTEM WAS BLED AND REPLENISHED. AIRCRAFT WAS RUN ON THE GROUND AND RUDDER ACTUATED SEVERAL TIME WITHOUT ANY CAUTION LIGHTS ILLUMINATING. AIRCRAFT WAS THEN RELEASED FOR SERVICE.

Part: SMOKE DETECTOR — MALFUNCTIONED (LAVATORY) · airframe 59,605 hrs · 67,605 cycles

DURING OPERATIONS, THE LAVATORY SMOKE DETECTOR BEGAN SOUNDING CONTINUOUSLY. THE TEST SWITCH WAS CYCLED AND THE UNIT OPERATED NORMALLY. THE AIRCRAFT WAS NOT TAKEN OUT OF SERVICE.

Part: SMOKE DETECTOR — DEFECTIVE (LAVATORY) · airframe 59,516 hrs · 67,504 cycles

THE LAVATORY SMOKE DETECTOR SOUNDED OFF ABOUT 10 TIMES WITHOUT EVIDENCE OF SMOKE OR FUMES. THE SMOKE DETECTOR WAS DE-ACTIVATED IAW SPECIAL PROCEDURES. MAINTENANCE REPLACED THE DEFECTIVE UNIT, RE-ACTIVATED THE SYSTEM AND OPS CHECKED THE UNIT. OPS CHECKS WERE GOOD AND THE AIRCRAFT WAS THEN RELEASED FOR SERVICE.

Part: SMOKE DETECTOR — MALFUNCTIONED (LAVATORY) · airframe 59,520 hrs · 67,508 cycles

LAV SMOKE DETECTOR SOUNDED ABOUT 10 TIMES AND STOPPED, NO EVIDENCE OF SMOKE OR FUMES. LAV SMOKE DETECTOR DEACTIVATED IAW SP 26.2 REFERENCE LP 279923 ITEM 2. REMOVED AND REPLACED LAV SMOKE DETECTOR IAW 26-12-05 AND REACTIVATED SYSTEM OPS CHECK GOOD. P/N ON/OFF PU90-461S S/N OFF 08243 S/N ON 09254.

Part: FIXTURE — BROKEN (CABIN) · airframe 59,474 hrs · 67,458 cycles

DURING DESCENT FROM 24000 FEET, THE FLIGHT ATTENDANTS NOTICED A BURNING ODOR IN THE CABIN BUT NO VISIBLE SMOKE. UPON LANDING, MAINTENANCE DEACTIVATED THE CABIN INTERIOR NORMAL LIGHTING SYSTEM, REMOVED THE BULB AND PLACED THE SYSTEM ON THE MEL LIST FOR THIS AIRCRAFT. A HIDDEN DAMAGE INSPECTION WAS PERFORMED AND FOUND THAT THE RIGHT HAND ROW 1 LIGHT FIXTURE WAS LOOSE. FURTHER INVESTIGATION FOUND THE LIGHT FIXTURE RECEPTACLE TO BE BROKEN AND BURNT. THE FIXTURE WAS REPLACED ALONG WITH THE LIGHTING BALLAST. SYSTEM WAS THEN RE-ACTIVATED AND OPS CHECKS WERE GOOD. THE SYSTEM MEL WAS CLEARED AND THE AIRCRAFT WAS THEN RELEASED FOR SERVICE.

Part: RELAY — FAILED (MLG) · airframe 57,637 hrs · 65,430 cycles

WHEN LANDING GEAR WAS SELECTED DOWN, THE NOSE GEAR SHOWED AN UNSAFE INDICATION. THE ALTERNATE EXTENSION SYSTEM WAS USED FOR THE NOSE GEAR. THE MAIN GEAR OPERATED NORMALLY WITH NO OTHER CAUTION OR WARNING INDICATIONS. MAINTENANCE SWUNG THE NOSE GEAR, NOTING NO DEFECTS IN THE SYSTEM. THE DRAG STRUT PROXIMITY SENSOR WAS CHECKED AND ADJUSTED, AND THE 3261-K7 RELAY WAS CHANGED. ENTIRE AIRCRAFT WAS THEN JACKED AND FULL GEAR SWINGS WERE DONE. NO DEFECTS WERE NOTED AT THAT TIME AND AIRCRAFT WAS RELEASED FOR SERVICE.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 57,185 hrs · 64,950 cycles

FLIGHT ATTENDANTS EMERGENCY LIGHT SWITCH LIGHTING IS INOP. REMOVED AND REPLACED SWITCH LIGHT BULB, OPERATIONAL CHECK GOOD.

Part: PUMP — FAILED (HYD SYSTEM) · airframe 50,637 hrs · 57,815 cycles

WHILE EN ROUTE FROM CLT TO LYH THE CAPT CALLED MAINTENANCE CONTROL WITH A HYD PUMP CAUTION LIGHT. AFTER TROUBLESHOOTING IT WAS FELT BEST TO DIVERT TO ROA. CREW DID NOT DECLARE AN EMERGENCY. ALSO FOUND HYD SOV FAILED IN CLOSED POSITION. P/N AND S/N OFF AV16B2003D, M26622.

Part: TERMINAL BLOCK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 50,463 hrs · 57,629 cycles

EMERGENCY LIGHTS FLICKERED ON AND OFF SEVERAL TIMES IN FLIGHT. REMOVED AND REPLACED 9811-TB14 MODULES 4 AND 7.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 49,074 hrs · 56,101 cycles

STRINGER 31S IS CORRODED AT X252. SPLICED IN NEW SECTION OF STR 31S IAW EO 8-53-04-0318.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 49,074 hrs · 56,101 cycles

FUSELAGE SKIN BUBBLED AT X202 AND STRINGER 31 BELOW AND INBOARD OF LAV SERVICING DOOR, FOUND TENSION FITTING CORRODED CAUSING PRESSURE ON SKIN. REMOVED AND REPLACED TENSION FITTING, CLEANED PRIMED SKIN.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 49,074 hrs · 56,101 cycles

STRINGER 27S CORRODED FWD OF FRAME X220 JUST UNDER LAV SERVICE PORT. REMOVED AND REPLACED STRINGER 27S.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 49,074 hrs · 56,101 cycles

SKIN CORRODED UNDER FRAME X252 BETWEEN STR 31S AND 30S, REMOVED AND REPLACED FRAME IAW EO 8-53-04-0315 CLEANED AND TREATED SKIN CORROSION.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 49,074 hrs · 56,101 cycles

FRAME X202 CORRODED AT STRINGER 31S.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 49,074 hrs · 56,101 cycles

FRAME X252.7 CORRODED AT STR 31S. INSTALLED NEW FRAME SECTION PER EO8-53-04-0315.

Part: FRAME — INADEQUATE (FUSELAGE) · corrosion level 2 · airframe 49,074 hrs · 56,101 cycles

FRAME X240 HAS AN INADEQUATE SPLICE AT STR 33. REMOVED AND REPLACED FRAME AT X240 PER EO 8-53-04-0314, MAJOR REPAIR.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 49,074 hrs · 56,101 cycles

FRAME X220 CORRODED AT STRINGER 29S. REMOVED AND REPLACED FRAME 220 IAW EO 8-53-04-0316.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 49,074 hrs · 56,101 cycles

FRAME AT X 220 CORRODED AT STR 28S. REMOVED AND REPLACED FRAME 220 IAW EO 8-53-04-0316.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 49,074 hrs · 56,101 cycles

FRAME X220 CORRODED AT STRINGER 31S. REMOVED AND REPLACED FRAME & VERTICAL BEAM IAW EO 8-53-04-0316.

Part: ACTUATOR — DEFECTIVE (MLG) · airframe 47,725 hrs · 54,671 cycles

WHEN GEAR RETRACTED, AMBER LEFT DOOR REMAINED ON AND DOOR VERIFIED OPEN. REPLACED FORWARD GEAR DOOR ACTUATOR.

Part: WARNING LIGHT — ILLUMINATED (PAX DOOR) · airframe 47,502 hrs · 54,422 cycles

PAX DOOR WARNING LIGHT ILLUMINATED IN FLIGHT. DIVERTED INTO CAE. VERIFICATION OF NORMAL OPERATION OF PASSENGER ENTRY DOOR IAW MEL 52-2. CLT MAINTENANCE CERIFIED NORMAL OPERATION CHECK GOOD.

Part: BATTERY — DISCHARGED (EMERGENCY LIGHT) · airframe 47,419 hrs · 54,336 cycles

RED FLOOR EMERGENCY LIGHTS 1 AND 2 INOPERATIVE. REPLACED BATTERY AND POWER SUPPLY 3352-PS2, OPS CHECK GOOD.

Part: VALVE — DEFECTIVE (#2 NACELLE) · airframe 46,015 hrs · 52,819 cycles

When landing gear selected up, the gear did not retract. The #2 hydraulic ISO valve caution light illuminated, roll spoiler outbd hydraulic caution light and nose gear steering caution light illuminated intermittantly. Nose steering did not work. Cleaned and inspected low level pressure switch on #2 hydraulic reservior. Ground ran aircraft, all systems on #2 hydraulic system, op's checked good.After take off gear selected up, gear went up but stayed unsafe- three red lights. #2 hydraulic ISO annunciator light illuminated and roll spoiler outboard hydraulic. Selected gear down - mains extended but not nose gear. Performed alternate extension. Ferried aircraft to ORF. Replaced #2 rudder ISO valve. O

Part: CONTROL BOX — DEFECTIVE (CABIN) · airframe 45,938 hrs · 52,740 cycles

Emergency light over pax door and forward right hand side emergency door flicker on and off during flight. Removed and replaced emergency light control box, operational check good.

Part: SWITCH — DEFECTIVE (COCKPIT) · airframe 45,102 hrs · 51,895 cycles

TAKE OFF WARNING HORN SOUNDED ON TAKE OFF. ABORTED TAKEOFF. COULD NOT SILENCE HORN. THOROUGHLY CLEANED AND INSPECTED MICRO SWITCHES, FOUND 3151-S3, (TAKE OFF WARNING HORN ON NR 1 PCL) DEFECTIVE - REPLACED MICRO SWITCH. TAKE OFF WARNING HORN SOUNDED WITH TAKE OFF POWER, ABORTED TAKE OFF, RE CHECKED ALL TAKEOFF ITEMS, ALL OK. FOUND SWITCH 3151-S3 ACTUATOR TAB BENT. ADJUSTED TAB OPS CHECK GOOD.

Part: CONNECTOR — DIRTY (NR 2 ENGINE) · airframe 44,974 hrs · 51,747 cycles

NR 2 PROP ATTEMPTED TO FEATHER WHILE ADVANCING POWER FOR TAKE OFF. CAPTAIN RAN ENGINE WITH FEATHER SYSTEN OFF, OPS NORMAL. SELECTED AUTO FEATHER ON OPS NORMAL. CALLED CONRACT MAINTENANCE, CLEANED BOTH TSEU CONNECTOR PLUGS AND NR 2 PROP FEATHER SOLENOID CONNECTOR PLUG. REPLACED NR 2 TSEU.

Part: BRAKE — LEAKING · airframe 43,021 hrs · 49,651 cycles

#1 AND #2 HYDRAULIC SYSTEMS FLUID LOSS. #2 RUDDER ISO VALVE CAUTION LIGHT ILLUMINATED. HYD PRESSURES NORMAL. ON LANDING NORMAL BRAKES FAILED. REPLACED #3 BRAKE ASSY.

Part: SHUTTLE VALVE — INOPERATIVE · airframe 43,021 hrs · 49,651 cycles

#1 AND #2 HYDRAULIC SYSTEMS FLUID LOSS. #2 RUDDER ISO VALVE CAUTION LIGHT ILLUMINATED. HYD PRESSURES NORMAL. ON LANDING NORMAL BRAKES FAILED. FOUND LEAK AT #3 BRAKE. #3 SHUTTLE VALVE FAILURE ALLOWED FLUID LOSS FROM BOTH HYD SYSTEMS. REPLACED #3 SHUTTLE VALVE.

Part: CONTROL PANEL — FAULTY (COCKPIT) · airframe 42,185 hrs · 48,779 cycles

COCKPIT PA AUDIO CONTROL SWITCH EMITTED SPARKS AND SMOKE WHEN SWITCH WAS DEPRESSED. REMOVED AND REPLACED PA AUDIO CONTROL PANEL.

Part: FILTER — CLOGGED (NR 2 ENGINE) · airframe 40,123 hrs · 46,637 cycles

NR 2 FUEL PRESSURE CAUTION LIGHT STAYS ON WITH AUX PUMP OFF. OIL PRESSURE OK. WITH AUX PUMP ON LIGHT WILL GO OUT. FOUND FILTER BLOCKED. REMOVED AND REPLACED HP, LP, FUEL FILTERS AND FUEL TO OIL HEATER.

Part: APU — SMOKE (BLEED SYSTEM) · airframe 38,968 hrs · 45,398 cycles

AFTER PUSH BACK AIRCRAFT CABIN FILLED WITH SMOKE. AIRCRAFT RETURNED TO GATE. IT WAS DETERMINED THAT THE SMOKE WAS COMING FROM THE APU BLEED SYSTEM. THE APU WAS MEL''D.

Part: CABLE — DISPLACED (PAX DOOR)

THE PAX DOOR WOULD NOT FULLY OPEN. FOUND COUNTERBALANCE CABLE TO BE OFF THE CABLE DRUM. CABLE WAS PLACED BACK ON THE CABLE DRUM.

Part: STRINGER — CORRODED (BS 467-488)

STRINGER 31S FROM X488 - X467 HAS CORROSION AROUND RIVET HOLES. RIVETS CIRCLED IN RED NEED REMOVED AND CORROSION EVALUATED. REMOVED RIVETS. SEVERAL AREAS OF CORROSION MEASURES FROM .003 - .022 DEEP. SPLICED STRINGER 31S IAW RD8-53-1834.

Part: STRINGER — CORRODED (BS 445-467)

STRINGER 31S FROM X467 - X445 HAS CORROSION, MOSTLY AROUND RIVET HOLES. RIVETS CIRCLED IN RED NEED REMOVED FOR FURTHER EVALUATION. REMOVED RIVETS. SEVERAL AREAS OF CORROSION MEASURE FROM .003 - .012 DEEP. SPLICED STRINGER IAW RD8-53-1834.

Part: BATTERY — DISCHARGED (CABIN)

AFT OVERHEAD EMERGENCY LIGHT AND LT AFT EGRESS LIGHT INOP. RELAMPED, NO FIX. REMOVED AND REPLACED EMERGENCY LIGHT BATTERY PS 3, OPS CHECK GOOD.

Part: STRUT — BROKEN (PAX DOOR)

PASSENGER DOOR WOULD NOT OPEN. FORWARD UPPER DOOR SUPPORT STRUT BROKEN. REPLACED FORWARD SUPPORT STRUT (TUBE ASSY).

Part: CONTROL BOX — FAILED (CABIN)

PHL/PHF - FLT 3175 - DURING PRE-FLIGHT CHECKS, THE CABIN EMERGENCY LIGHTS CYCLE ON AND OFF INTERMITTENTLY. REMOVED AND REPLACED EMERGENCY LIGHTS CONTROL BOX. (X)

Part: ADAPTOR PLATE — FAILED (NR 1 ENGINE)

FLT 3255 - HVN-DCA - ON CLIMB-OUT AT 3000 FEET, THE MASTER WARNING LGIHT ILLUMINATED, THE NR 1 OIL PRESSURE LIGHT WAS ON, AND THE NR 1 OIL PRESSURE WAS FALLING. THE CREW SHUTDOWN NR 1 ENGINE AND RETURNED TO HVN WITHOUT INCIDENT. THE AIRCRAFT WAS FERRIED TO SBY FOR REPAIR. REPLACED ADAPTOR PLATE AND INSTALLED A NEW AC GENERATOR. (M)

Part: GENERATOR — FAILED (NR 1 ENGINE)

FLT 3255 - HVN-DCA - ON CLIMB-OUT AT 3000 FEET, THE MASTER WARNING LGIHT ILLUMINATED, THE NR 1 OIL PRESSURE LIGHT WAS ON, AND THE NR 1 OIL PRESSURE WAS FALLING. THE CREW SHUTDOWN NR 1 ENGINE AND RETURNED TO HVN WITHOUT INCIDENT. THE AIRCRAFT WAS FERRIED TO SBY FOR REPAIR. REPLACED ADAPTOR PLATE AND INSTALLED A NEW AC GENERATOR. (M)

Part: FIRE LOOP — CHAFING (APU)

CLT-EWN - FLT 3220 - THE FIRE DETECTION WARNING LIGHT AND APU FIRE FAULT ADVISORY LIGHT ILLUMINATED DURING FLIGHT. ACFT TURNED BACK AND LANDED IN CLT WITHOUT INCIDENT. REMOVED AND REPLACED APU FIRE LOOP FOR CHAFING.