N128NA

Part: SMOKE WARNING — FALSE ACTIVATION (CARGO BAY) · airframe 59,670 hrs · 46,298 cycles

CARGO SMOKE LIGHT ILLUMINATED IN FLIGHT, RAN ALL APPROPRIATE CHECKS, FALSE INDICATION, CONTINUED FLIGHT. MX PERFORMED AN OPS TEST OF THE SMOKE DETECTION SYS AND FOUND GOOD IAW THE MM.

Part: SMOKE DETECTOR — DIRTY (CABIN) · airframe 59,638 hrs · 46,280 cycles

ON DESCENT, MAIN CABIN SMOKE DETECTOR LIGHT ILLUMINATED. NO EVIDENCE OF SMOKE DISCOVERED. MX DISCOVERED NR 1 SMOKE DETECTOR DIRTY. THE DETECTOR WAS CLEANED AND THE SYS TESTED NORMAL.

Part: WARNING SYSTEM — MALFUNCTIONED (SMOKE WARNING) · airframe 59,232 hrs · 46,019 cycles

AMERIJET FLIGHT 8110 FROM TSSJ TO KMIA - MAIN CARGO COMPARTMENT SMOKE WARNING CAME ON IN CRUISE FLIGHT. VISUALLY CHECKED FALSE WARNING. ON ARRIVAL KMIA THE MAIN CARGO SMOKE DETECTION SYSTEM WAS OPERATIONALLY TESTED AND NO DEFECTS WERE FOUND.

Part: SWITCH — INTERMITTENT (LT WING)

NR 2 KRUGER FLAP EXTEND LIGHT REMAINED ON AFTER TAKEOFF. REMOVED AND REPLACED NR 2 KRUGER FLAP SWITCH IAW MM.

Part: SKIN — CORRODED (FUSELAGE)

FOUND FUSELAGE SKIN CORRODED STRINGER 17 LT STATION 1183. INSTALLED EXTERNAL SKIN REPAIR IAW B727 SRM 53-30-3 FIG 3A. REPAIR DOUBLER FABRICATED FROM 2024-T3, .080 BY 17 BY 11.80. (M)

Part: SKIN — CRACKED (FUSELAGE)

FOUND FUSELAGE SKIN CRACKED STRINGER 21 LEFT STATION 1233. INSTALLED EXTERNAL SKIN REPAIR IAW B727 SRM 53-30-3 FIG 3. REPAIR DOUBLER, FABRICATED FROM 2024-T3, .080 BY 8 BY 7. (M)

Part: SKIN — CORRODED (FUSELAGE)

FOUND FUSELAGE SKIN CORRODED STRINGER 27 RIGHT STATION 500. INSTALLED EXTERNAL SKIN REPAIR IAW B727 SRM 53-30-3 FIG 6. REPAIR DOUBLER FABRICATED FRAME 2024-T3, .050 BY 31.25 BY 18. (M)

Part: HINGE — CRACKED (MAIN CARGO DOOR)

FOUND MAIN CARGO DOOR UPPER AFT HINGE SECTION CRACKED. REMOVED AND REPLACED UPPER AFT HINGE SECTION PER AEI SERVICE BULLETIN AE01-01 AND AEI MM CHAPTER 52 PAGE 15. (M)

Part: PCU — LEAKING (LT ELEVATOR)

IN CRUISE NOTED DECREASING HYDRAULIC A-SYSTEM QUANTITY. FOLLOWED ABNORMAL PROCEDURES QUANTITY STABILIZED AT .6 GALLONS. FOUND LT ELEVATOR POWER CONTROL UNIT LEAKING. REMOVED AND REPLACED LT ELEVATOR PCU IAW MM. OPS AND LEAK CHECK GOOD.

Part: PCU — LEAKING (LT ELEVATOR)

IN CRUISE NOTED DECREASING HYDRAULIC A-SYSTEM QUANTITY. FOLLOWED ABNORMAL PROCEDURES QUANTITY STABILIZED AT .6 GALLONS. FOUND LEFT ELEVATOR POWER CONTROL UNIT LEAKING. REMOVED AND REPLACED LEFT ELEVATOR PCU IAW B727 MM 27-30-81, OPS AND LEAK CHECK GOOD. (M)

Part: PIN — BROKEN (CONNECTOR)

REJECTED TAKEOFF, NR 3 EPR UNRELIABLE AT TAKEOFF POWER READS LOW. SEEMS TO READ NORMAL AT CRUISE POWER. FOUND WIRE NOT CONNECTED TO PIN NR 3 AT EPR GAUGE CANNON PLUG. INSTALLED NEW PIN AND RECONNECTED WIRE IAW WIRING STANDARD PRACTICE CH 20 EPR READS NORMAL IAW MM 77-11-00. (M)

Part: LINE — LEAKING (HYD SYSTEM)

LOST SYSTEM A HYDRAULIC. ENGINE NR 1 PUMP LOW PRESSURE LIGHT FOLLOWED BY FLUID LOSS IN FLIGHT. REMOVED AND REPLACED TWO EACH HYDRAULIC LINES, P/N 65-17844-250 AND 65-17844-17, LEAK CHECK GOOD. (M)

Part: CONTROL PANEL — SHORTED (PEDESTAL)

WHEN ENGAGING AUTOPILOT, CRUISE STABILIZER TRIMS TO THE FULL NOSE DOWN POSITION. WITH AUTOPILOT DISCONNECTED, AFTER LEVEL OFF AT FL350, AN ELECTRICAL OVERHEAT ODOR STARTED TO FILL THE COCKPIT. CHECKLIST PERFORMED, ODOR STOPPED. REMOVED AND REPLACED RIGHT ELEVATOR POSITION SENSOR PER MM 22-11-71. OPS CHECK GOOD PER MM 22-11-0, P/N 2588838. FOR OVERHEAT ODOR FOUND CENTER PEDESTAL LIGHTS POPS CIRCUIT BREAKER. REMOVED AND REPLACED NR 1 AUDION NAV/COMM CONTROL PANEL PER M/M 33-11-0 AND 23-21-0. OPS CHECK GOOD, P/N INSTLALED G1982B. (M)

Part: ADC — FAILED (COCKPIT) · airframe 54,809 hrs · 43,317 cycles

AIRCRAFT DEPARTED YIP AT 23:52Z AND HAD AIR DATA INSTRUMENT FAILURE CLIMBING THRU 5000FT. AIRCRAFT RETURNED TO YIP AND MADE OVERWEIGHT LANDING.

Part: CONNECTOR — BROKEN (ADC)

DURING FLIGHT, THE NR 1 ALTIMETER FLAG CAME IN VIEW AND STAYED. DIVERTED FLIGHT TO YIP. FOUND PIN 16 ON TOP PLUG OF AIR DATA COMPUTER BROKE. REPAIRED WIRE IAW MM CHAPTER 20. PERFORMED BITE TEST IAW MM 34-12-0 IAW BOEING MM 34-12-0. REF C7WA200200030 - AIRCRAFT DEPARTED YIP, AND HAD AIR DATA INSTRUMENT FAILURE CLIMBING 5000 FT. AIRCRAFT RETURNED TO YIP AND MADE OVERWEIGHT LANDING. (M)

Part: PITOT TUBE — OBSTRUCTED (PITOT/STATIC SYS) · airframe 54,805 hrs · 43,313 cycles

REJECTED TAKEOFF FROM SJC AT 90 KNOTS DUE TO LACK OF AIRSPEED INDICATION ON COPILOTS SIDE. CHECKED PITOT TUBES AND REMOVED INSECT BLOCKAGE FROM F/O PITOT SYSTEM IAW MM 34-11-31.

Part: PITOT TUBE — OBSTRUCTED (PITOT/STATIC SY)

REJECTED TAKEOFF FROM SJC AT 90 KNOTS DUE TO LACK OF AIRSPEED INDICATION ON COPILOTS SIDE. CHECKED PITOT TUBES AND FOUND INSPECT BLOCKAGE FROM FIRST OFFICERS PITOT TUBE. REMOVED BLOCKAGE CHECKED SYSTEM IAW MM 34-11-31. (M)

Part: SKIN — DELAMINATED (LT WING SPOILER)

LEFT WING SPOILER NR 7 (PN 65-17348-74) (SN 7888K) LOWER SKIN WITH DELAMINATION.

Part: SKIN — DELAMINATED (LT WING SPOILER)

LEFT WING, SPOILER NR 5, (PN 65-17348-75), (SN 1781P) WITH DELAMINATION AT UPPER SKIN AND LOWER SKIN.

Part: STRUCTURE — DELAMINATED (RT WING SPOILER)

RIGHT WING, SPOILER NR 8 (PN 651734866A) WITH DELAMINATION.

Part: STRUCTURE — CORRODED (RT WING TE FLAP)

RIGHT WING, INBOARD AFT FLAP (PN 65-21634-92) (SN BN480) UPPER, LOWER SKIN AND HONEYCOMB CORE CORRODED.

Part: SKIN — CORRODED (LT WING TE FLAP)

LEFT WING, OUTBOARD AFT FLAP (PN 65-21635-85) (SN BN120) UPPER SKIN AND HONEYCOMB CORE SECTION CORRODED.

Part: STRUCTURE — DELAMINATED (AILERON TAB)

LEFT WING, OUTBOARD AILERON TAB (PN 65-21726-33) TMC 189 WITH DELAMINATION.

Part: SKIN — CORRODED (LT WING TE FLAP)

LEFT WING, INBOARD AFT FLAP (PN 65-21634-79)(SN BN147) UPPER, LOWER SKIN AND HONEYCOMB CORE CORRODED.

Part: STRUCTURE — DELAMINATED (RT WING SPOILER)

RIGHT WING, SPOILER NR 10, PN 65-17348-75, SN 4268H WITH DELAMINATION.

Part: STRUCTURE — DELAMINATED (RT WING AILERON)

RIGHT WING, OUTBOARD AILERON TRAILING EDGE (PN 65-21766-66)(SN BN-26) WITH DELAMINATION.

Part: PANEL — DELAMINATED (RT WING T/E)

RIGHT WING, TRAILING EDGE-UPPER PANEL (PN 6521657242) DELAMINATED.

Part: PANEL — DELAMINATED (RT WING T/E)

RIGHT WING, TRAILING EDGE - LOWER PANEL (PN 6521652616) DELAMINATED.

Part: SKIN — DELAMINATED (LT WING SPOILER)

LEFT WING, SPOILER NR 4, (PN 65-17347-42), (SN TC-248) WITH DELAMINATION AT UPPER SKIN.

Part: STRUCTURE — DELAMINATED (RT WING SPOILER)

RIGHT WING, SPOILER NR 14, (PN 651734757), SN 9126S WITH DELAMINATION.

Part: SKIN — DELAMINATED (RT WING SPOILER)

RIGHT WING SPOILER NR 9 (PN 65-17348-74) (SN 9087K) LOWER SKIN WITH DELAMINATION.

Part: PANEL — DELAMINATED (RT WING T/E)

RIGHT WING, TRAINLING EDGE - LOWER FIX PANEL (PN 65216522) DELAMINATED.

Part: ANGLE — CRACKED (CARGO DOOR FRAME)

MAIN CARGO DOOR (PER STC NO SA1797SO) UPPER JAMB, FORWARD AND AFT CORNER ANGLE CRACKED.

Part: NR 3 DISK — FAILED (NR 1 ENGINE)

FLT 312 - KCLT-KMIA - AFTER TAKEOFF EPR DECREASED AND EGT INCREASED. RETARDED THROTTLE TO CONTROL EGT WHEN VIBRATION WAS NOTICED AND EXPERIENCED COMPRESSOR STALL. WHEN THROTTLE RETURNED TO IDLE, EGT CONTINUED TO CLIMB. PERFORMED ENGINE INFLIGHT SHUTDOWN PROCEDURES AND RETURNED TO KCLT. AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. FOUND NR 3 COMPRESSOR DISK HAD DROPPED. REMOVED AND REPLACED NR 1 ENGNIE. NO OTHER DEFECTS NOTED. AIRCRAFT RETURNED TO SERVICE. (M)

Part: AIR DISTRIBUTION — ODOR (COCKPIT)

FLT 230 - DTW-LRD - FLIGHT DIVERTED TO HDY, STRONG SMELL OF ELECTRICAL SMOKE. NO VISIBLE SMOKE, SEEMED TO BE AROUND FE PANEL. INSPECTED FE PANEL AND ADJACENT AREAS, P-6 PANEL, STAB TRIM C/B FOR ABNORMAL SMELL AND EXCESSIVELY HOT COMPONENTS. NONE FOUND. INSPECTED R/E COMPT FOR SAME, NONE FOUND. BATTERY FOUND COOL TO TOUCH. NO ABNORMALITIES NOTED THIS MX INSPECTION. (M)

Part: ENGINE — FAILED (NR 2)

FLT 224 - KPAP-KMIA - ON TAKEOFF ROLL, AT APPROXIMATELY 65 KTS, ENGINE NR 2 FAILED. WITH PRONOUNCED VIBRATION IN POWER QUADRANT AND ENGINE FAIL LIGHT ILLUMINATED. ENGINE READINGS, EPR 0, N1 22 PERCENT, N2 45 PERCENT, FF 1200, EGT 570 DEGREES. (M)

Part: FUEL CONTROL — FAILED (NT 1 ENGINE)

FLT PT 301 DEPARTED MIAMI, FL FOR CUARAZAO (CUR) ON THIS DATE. TAKEOFF WAS NORMAL UP TO THE TIME OF THE FIRST POWER REDUCTION. POWER REDUCTION WAS NORMAL FOR NR 2 AND NR 3 ENGINES; BUT, NR 1 ENGINE REMAINED AT HI POWER WITH NO RESPONSE TO THROTTLE MOVEMENT. ENGINE NR 1 WAS SHUT DOWN AND AIRCRAFT RETURNED TO MIA. ENGINE PARAMETERS WERE HIGH AT TIME OF SHUT DOWN. EVENT RECORDED IN A/C LOG BOOK.

Part: DOWNLOCK SWITCH — INOPERATIVE (NLG)

AFTER TAKEOFF FROM TPA WITH THE GEAR HANDLE IN THE GEAR UP POSITION, BOTH THE RED AND GREEN NOSE GEAR LIGHTS REMAINED ILLUMINATED. THE GEAR HANDLE WAS PLACED IN THE GEAR DOWN POSITION AND THE AIRCRAFT RETURNED TO TPA WITHOUT INCIDENT. TROUBLESHOOTING OF THE NOSE GEAR INDICATING SYSTEM REVEALED A FAULTY DOWNLOCK SWITCH. THE SWITCH WAS REPLACED, A NOSE GEAR SWING WAS ACCOMPLISHED. THE SYSTEM CHECKED NORMAL IAW 727 MM 32-61-01 AND THE AIRCRAFT WAS RELEASED FOR FLIGHT.

Part: PITOT TUBE — BLOCKED (LEFT)

MIAMI - ON TAKEOFF ROLL, THERE WAS NO AIRSPEED INDICATION ON THE CAPTAIN'S AIRSPEED INDICATOR. DISCONNECTED PITOT PRESSURE LINE, APPLIED NITROGEN PRESSURE AND FOUND INSECTS (BEES) CLOGGING CAPTAIN'S PITOT TUBE. CLEARED AL INSECTS FROM CAPTAIN'S PITOT LINES, RECONNECTED LINE, OPERATION AND LEAKED CHECKED PITOT SYSTEM IAW B727 MM, REF 34-11-0. ACFT RELEASED FOR FLIGHT.

Part: STRINGER — CORRODED (NR 2 CARGO DOOR)

IN THE PROCESS OF COMPLYING WITH SB 53-159 BELLY SKIN REPLACEMENT, SOME CORROSION WAS FOUND ON LEFT SIDE OF STRINGER PN 65-56129-10. THE STRINGER HAD TO BE REPLACED. THIS STRINGER RUNS ALONG THE LOWER END OF NR 2 CARGO DOOR. SUBMITTER STATED CAUSE OF THIS CORROSION IS WATER AND DEBRIS LAYING INSIDE THE CHANNEL.

Part: STRINGER — CORRODED (BS 950)

IN THE PROCESS OF COMPLYING WITH S/B 53-159 BELLY SKIN REPLACEMENT, STRINGER (P/N 65-56441-8) WAS FOUND CORRODED ALONG TOPSIDE. STRINGER WAS REPLACED.

Part: STRINGER — CORRODED (BS 950)

IN THE PROCESS OF COMPLYING WITH SB 53-159, BELLY SKIN REPLACEMENT STRINGER P/N 65-56441-8 WAS FOUND CORRODED ALONG TOP SIDE. STRINGER WAS REPAIRED. SUBMITTER STATED CAUSE OF CORROSION WAS EITHER MOISTURE BUILD-UP OR LACK OF FINISH ON THE PART.

Part: STRINGER — CRACKED (STA 950)

IN THE PROCESS OF COMPLYING WITH S/B 53-159 BELLY SKIN REPLACEMENT STRINGER (P/N 65-56441 WAS FOUND TO BE CRACKED AT BOLT HOLES FWD END OF STRINGER.

Part: BLKHD WEB — CORRODED (FS 351.2)

DURING A C-CHECK INSPECTION, CORROSION WAS FOUND AT STA 351.2 FORWARD BULKHEAD WEB SHEAR TIE AND ADJACENT AREA. AS THE CORROSION WAS FOUND IN NUMEROUS AREAS, THE BULKHEAD WEB WAS REPLACED. THE REPAIR WAS ACCOMPLISHED WITH THE HELP OF BOEING AIRCRAFT COMPANY. AS THIS IS A CLOSED AREA, THE CORROSION WOULD BE FOUND ONLY AT THE TIME THE LOWER SKIN PANEL WAS REMOVED.

Part: STRUCTURE — CORRODED (FS 320-361)

DURING A C-CHECK INSPECTION, FOUND SEVERAL STRINGERS AND DOUBLERS CORRODED IN LOWER BELLY AREA FROM STA 320 - STA 360. INTERNAL DOUBLER CORRODED ON SKIN PANEL STA 351 TO STA 360, STR 27L TO STR 27R. STRINGER SEGMENT CORRODED STA 351 TO STR 360, STR 26R. FRAME TO TEE CHORD SHEAR TIE CORRODED STA 328R BELOW STR 28. RIGHT SUBFRAME CORRODED WHERE FLANGE MEETS LOWER TEE CHORD STA 320, STR 28. DEFECTS COULD BE MOISTURE AS PARTS ARE IN CLOSED AREA.

Part: STRINGER — CRACKED (FS 950)

IN THE PROCESS OF COMPLYING WITH SB 53-159 BELLY SKIN REPLACEMENT, STRINGER (P/N 65-56441-7) WAS FOUND TO BE CRACKED AT BOLT HOLES FWD END OF STRINGER.

Part: STRINGER — CRACKED (FS 950)

IN THE PROCESS OF COMPLYING WITH S/B 53-159 BELLY SKIN REPLACEMENT, CHORD STRINGER (P/N 65-56441-7) WAS FOUND TO BE CRACKED AT FWD BOLT HOLES. THE ED IN THAT AREA SEEMS TO BE MARGINAL.