N783TW
Registered owner: SIERRA AMERICAN CORP, DE (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
TWO HOURS INTO CRUISE AT FL 350 ENCOUNTERED A LOSS OF CABIN PRESSURE. RAN COM PROCEDURES CABIN ALTITUDE WARNING/RAPID DEPRESSURIZATION. CABIN RECOVERED AND HELD AT 8500 FEET FOR ABOUT 20 MIN BEFORE A RAPID SPIKE IN CABIN CLIMB (FULL SCALE) INITIATED AN EMERGENCY DESCENT WITH ATC. CABIN DID NOT RECOVER FOR REMAINDER OF FLIGHT. DIVERTED TO KABQ. CORRECTIVE ACTION - LOG PAGE 78763 - 11/23/2025 - DURING TROUBLESHOOTING FOUND RH TEMP CONTROL VALVE STUCK IN FULL HEAT POSITION CAUSING RH AIR CONDITIIONING SYSTEM TO OVERHEAT AND SHUT DOWN. REPLACED RH TEMP CONTROL VALVE PER AMM 21-61-1; TESTED PER 21-61-1 OPS CHECK GOOD. PERFORMED CABIN PRESSURE CONTROL SYSTEMS PER AMM 21-32-0 3(A) OPS CHECK GOOD.
WHILE CRUISING AT FL350 A MASTER WARNING LIGHT ILLUMINATED, THE CABIN PRESSURE LIGHT WAS ALSO ILLUMINATED. BOTH THE CAPTAIN AND FIRST OFFICER COMPLETED THE IMMEDIATE ACTION ITEMS FOR A CABIN PRESSURE WARNING, THEN COMPLETED THE COM PROCEDURE FOR THE WARNING. PRESSURE WAS NOT RESTORED. MX TROUBLESHOT AND TESTED ON GROUND LOG PAGE 77904 PRESSURIZATION SYSTEM OPS CHECK GOOD ON GROUND. WHILE PASSING THROUGH FL235 A MASTER WARNING LIGHT ILLUMINATED, THE CABIN PRESSURE LIGHT WAS ALSO ILLUMINATED. WE STOPPED THE CLIMB AT 240. BOTH THE CAPTAIN AND FIRST OFFICER COMPLETED THE IMMEDIATE ACTION ITEMS FOR A CABIN PRESSURE WARNING. PRESSURE WAS NOT RESTORED. THE FO THEN ADVISED ATC THAT WE WOULD REQUIRE A DESCENT TO 10,000FT. ATC CLEARED US TO 10,000 FEET WITHOUT DELAY. THE IMMEDIATE ACTION ITEMS AND COM PROCEDURES FOR EMERGENCY DESCENT WERE COMPLETED DURING THE DESCENT. 7 MX FOUND LOOSE AND DAMAGED CONNECTOR AT RH ACM COMPRESSOR DISCHARGE TEMP SENSOR. R&R CONNECTOR PER DC9 SWPM 20-31. OPS CHECK PRESSURIZATION SYSTEM IN AUTO AND MANUAL MODE PER DC9 AMM 21-32. ALL OPS CHECKS GOOD ON GROUND.
WHILE CRUISING AT FL350 A MASTER WARNING LIGHT ILLUMINATED, THE CABIN PRESSURE LIGHT WAS ALSO ILLUMINATED. BOTH THE CAPTAIN AND FIRST OFFICER COMPLETED THE IMMEDIATE ACTION ITEMS FOR A CABIN PRESSURE WARNING, THEN COMPLETED THE COM PROCEDURE FOR THE WARNING. PRESSURE WAS NOT RESTORED. 2/19/2025 - MX TROUBLESHOT AND TESTED ON GROUND LOG PAGE 77904 PRESSURIZATION SYSTEM OPS CHECK GOOD ON GROUND. WHILE PASSING THROUGH FL235 A MASTER WARNING LIGHT ILLUMINATED, THE CABIN PRESSURE LIGHT WAS ALSO ILLUMINATED. WE STOPPED THE CLIMB AT 240. BOTH THE CAPTAIN AND FIRST OFFICER COMPLETED THE IMMEDIATE ACTION ITEMS FOR A CABIN PRESSURE WARNING. PRESSURE WAS NOT RESTORED. THE FO THEN ADVISED ATC THAT WE WOULD REQUIRE A DESCENT TO 10,000FT. ATC CLEARED US TO 10,000 FEET WITHOUT DELAY. THE IMMEDIATE ACTION ITEMS AND COM PROCEDURES FOR EMERGENCY DESCENT WERE COMPLETED DURING THE DESCENT. 3-5-2025 LOG PAGE 77907 MX FOUND LOOSE AND DAMAGED CONNECTOR AT RH ACM COMPRESSOR DISCHARGE TEMP SENSOR. R&R CONNECTOR PER DC9 SWPM 20-31. OPS CHECK PRESSURIZATION SYSTEM IN AUTO AND MANUAL MODE PER DC9 AMM 21-32. ALL OPS CHECKS GOOD ON GROUND.
THE ATTACH BOLTS REFERENCE IPC 52-60-04-01 ITEM 105 P/N NAS1203-9 ITEM 110 P/N NAS1103-9 THAT SECURE RETAINER ASSEMBLY (VENTRAL STAIR DOOR BEARING) REFERENCE IPC 52-60-04-01 ITEM 26 P/N 3917209-501 TO ADJACENT STRUCTURE AND AFT STAIR ACTUATING MECHANISIMS SHEARED DURING AFT STAIR OPENING PROCEDURE WHICH CAUSED STRESS CRACKING AND FAILURE OF SURROUNDING SUPPORT STRUCTURES.
DURING CRUISE ALTITUDE 35.0, THE AIRCRAFT STARTED LOSING PRESSURIZATION AND THE CABIN ALTITUDE CLIMBED TO 11.5 K FEET. THE PILOT DECLARED AN EMERGENCY AND DECENDED TO 10K FEET, LANDED WITHOUT INCIDENT. FOUND A DUCT CLAMP LOOSE.
EMERGENCY EXIT LIGHT SYSTEM, PORTABLE EMERGENCY EXIT LIGHT WILL NOT ACTIVATE WHEN SELECTED TO ON. AWAITING DETAILS ON REPAIR.
1.5 INCH CRACK RT TRAPEZOIDAL PANEL BETWEEN BOLT HOLES COMMON TO THE HORIZONTAL FLANGE OF THE LOWER SUPPORT FITTING.
FORWARD MAIN ENTRY DOOR JAMB UPPER AFT SEAL DEPRESSOR BENT AND GOUGED.
1.75" LONG CRACK IN FUEL TANK ACCESS PANEL LANDING ON LT WING UPPER SURFACE AT WING BS XRS 111.
CRACK IN RT INBD L/E UPPER SPAR CAP APPROXIMATELY 2" IN LENGTH THROUGH THE 2 MOST INBD UPPER BOLTS.
FUSELAGE WINDOW BELT SKIN REPAIR STATION 422.5, L 11R TO L 15R.
CLIMBING THROUGH APPROXIMATELY 14,000 FEET OBSERVED NO AIRFLOW COMING FROM THE AIR VENTS, CHECKED THE CABIN ALTITUDE AND IT WAS 9,000 FT AND CLIMBING 1,000 FPM. BEFORE PROCEDURES, CABIN PRESSURE AND MASTER WARNING LIGHTS ILLUMINATED DURING DESCENT THROUGH ABOUT 12,000 FEET. DECLARED AN EMERGENCY. EXECUTED CABIN ALTITUDE WARNING IMMEDIATE ACTION ITEMS FOLLOWED BY COM PROCEDURES. AT AN ALTITUDE OF 9,500 THE CABIN PRESSURE WARNING LIGHT EXTINGUISHED. ACCOMPLISHED ALL CHECKLISTS AND LANDED WITH NO FURTHER ISSUES.
EMERGENCY LIGHTS INOPERATIVE.
LT ELEVATOR SPAR FORWARD SPAR CRACKED BEYOND LIMITS.
LEFT VERTICAL STAB HAS CORROSION.
LT AFT SKIN CORRODED OUT OF LIMITS.
MAIN DECK FLOORBOARD CRACKED SEVERAL PLACES.
CANTED BULKHEAD LOWER TEE CORRODED.
RT VERTICAL STABILIZER HAS CORROSION ON EXTERIOR SKIN.
CANTED FRAME AT BS 796 LT IS CORRODED OUT OF LIMITS.
UPPER AND MID LT CANTED FRAME CORRODED AND FOUND TO BE OUT OF LIMITS AT BS 989.
SKIN CRACKED AT BS 340 BETWEEN L17 - 18R.
CORROSION ON OUTER SKIN AT BS 566 BELOW OVERWING EXITS.
ACFT LT SIDE REAR FUSELAGE, UN-PRESSURIZED AREA AFT OF VENT LOUVERS HAS CORROSION.
RT NR 11 PASSENGER COMPARTMENT WINDOW CUTOUT HAS CRACK INDICATION LOWER AFT CORNER.
AFT PRESSURE BULKHEAD DOOR FRAME CRACKED APPROX 12 INCHES FROM BOTTOM FRAME.
FUSELAGE SKIN CRACKED BS256 BETWEEN LONGERONS 4 & 5 LT.
AFT PRESSURE BULKHEAD EXTERNAL SIDE, SURFACE CORROSION FOUND UNDER ADHESIVE, 9 O`CLOCK POSITION APPROX 1.5' FROM DOOR FRAME LT BULKHEAD.
UPPER FUSELAGE MAIN CARGO CABIN AT STA Y 446 AT LEVEL LONGERON 18L FRAME WITH CRACK.
MAIN CARGO CABIN SUPPORT FITTING CRACKED AT STA Y 446 BETWEEN LONGERON 18L AND 19L.
UPPER FUSELAGE PAX CABIN STA 441 BETWEEN LONGERON 18 AND 19 LT FRAME FWD SECTION FITTING CRACKED.
UPPER FUSELAGE PAX CABIN STA Y 441 BETWEEN LONGERON 18 AND 19 LT DOOR FRAME CRACKED.
DURING INSPECTION UPPER FUSELAGE EXTERIOR FUSELAGE SKIN WITH SCRATCH AT STA Y147.
DURING INSPECTION RT WING FLAP T/E PANEL NR 3 LOWER SKIN WITH CORROSION.
DURING INSPECTION EMPENNAGE VERTICAL STABILIZER RUDDER SKIN WITH CRACK AT ZR27.25 RT.
UPPER FUSELAGE CARGO CABIN VERTICAL WEB WITH CRACK AT Y STA 525,+X=58,Z=-1.
DURING INSPECTION MAIN CARGO CABIN DOOR LOWER JAMB BEAM WITH CORROSION AT SEVERAL PLACES BETWEEN Y STA 303 AND Y STA 439.
DURING INSPECTION UPPER FUSELAGE AFT ACCESSORIES COMPARTMENT BETWEEN LONGERON 1L AND 2L Y STA 908 FRAME, SHEAR TIE WITH CRACK.
DURING INSPECTION RT WING FLAP T/E LOWER PANEL SKIN WITH DENTS AT XS 114 AND XS 94.
DURING INSPECTION UPPER FUSELAGE SKIN WITH CORROSION FROM Y STA 474 AND Y STA 642, BETWEEN LONGERON 16L AND 19L CORRODED.
DURING INSPECTION LOWER FUSELAGE AFT ACCESSORY COMPT LATERAL ANGLE BLENDED AND CRACK AT CANTED STA 965,-X=17.5.
DURING INSPECTION LOWER FUSELAGE AFT ACCESSORY COMPT LATERAL UPPER ANGLE WITH CRACK AT CANTED STA 962.019,-X=17.5.
DURING INSPECTION AFT FUSELAGE SUPPORT CANTED BULKHEAD LOWER FRAME WITH CORROSION AT CANTED STA 964,-X19.
DURING INSPECTION RUDDER WITH CORROSION SKIN AT LT BETWEEN ZR 94 AND ZR 99.
DURING INSPECTION UPPER FUSELAGE CARGO CABIN RT AT Y STA 585,-X59,-Z4 OVER WHEEL WELL FRAME AFT POCKET AREA WITH CRACK.
DURING INSPECTION LT WING FLAP INTERNAL, FLAP FRONT SPAR LOWER ANGLE WITH CORROSION AT XF 72.
DURING INSPECTION LOWER FUSELAGE SKIN WITH DENT BETWEEN Y STA 381 AND Y STA 395 BETWEEN LONGERONS 19L AND 21L.
DURING INSPECTION UPPER FUSELAGE MAIN CARGO CABIN Y STA 525 BETWEEN LONGERONS 18L AND 19L FUSELAGE FRAME WEB CRACKED.
DURING INSPECTION UPPER FUSELAGE MAIN CARGO CABIN Y STA 544 BETWEEN LONGERONS 18R AND 19R FUSELAGE FRAME WEB CRACKED.
DURING INSPECTION LOWER FUSELAGE SKIN WITH CORROSION AT PERIPHERY WTBF ATTACHMENT HOLES AREA Y STA 470 TO Y STA 565 BETWEEN LONGERON 23L AND 30L.
DURING INSPECTION LOWER FUSELAGE FWD CARGO COMPARMENT DOOR INNER PAN WITH CRACK AT BEAM NR 1 AFT SECTION.
DURING INSPECTION LOWER FUSELAGE FWD CARGO COMPARTMENT DOOR OUTER PAN WITH CRACK AT AFT SECTION BEAM NR 1 LOCATION.
DURING INSPECTION LOWER FUSELAGE FWD CARGO COMPARTMENT DOOR INNER PAN WITH CRACK AT BEAM NR 1 FWD SECTION.
DURING INSPECTION LOWER FUSELAGE AFT CARGO COMPARMENT DOOR OUTER PAN FWD SECTION WITH CRACKS AT BEAM 2 & 3 LOCATION.
DURING INSPECTION LOWER FUSELAGE AFT CARGO COMPARTMENT DOOR OUTER PAN WITH CRACKS AT AFT SECTION BEAMS NR 1, 2, 3 & 5 LOCATIONS.
DURING INSPECTION LOWER FUSELAGE AFT CARGO COMPARTMENT DOOR OUTER PAN REPAIR WITH CRACK AT SECTION BETWEEN BEAMS 1 & 2 LOCATION.
DURING INSPECTION LOWER FUSELAGE TRAPEZOIDAL PANEL WITH CRACK FWD SECTION AT Y STA 582 LONGERON 20L.
DURING INSPECTION LOWER FUSELAGE RT MAIN WHEEL WELL MAIN FRAME CRACKED AT Y STA 604 LONGERON 20R.
DURING INSPECTION CABIN FLOORING SKIN WITH CRACK BETWEEN Y STA 166 AND Y STA 190-X3.
DURING INSPECTION MAIN CARGO CABIN DOOR LOWER JAMB BEAM AREA ANGLES WITH CORROSION BETWEEN Y STA 389 AND Y STA 432.
DURING INSPECTION MAIN CARGO CABIN SUPPORT FITTING CRACKED AT Y STA 446 BETWEEN LONGERON 18L AND 19L.
DURING INSPECTION LOWER FUSELAGE AFT CARGO COMPARTMENT Y STA 738 BETWEEN LONGERON 29R AND 30 FITTING CRACKED.
DURING INSPECTION LOWER FUSELAGE FWD CARGO COMPARMENT LEFT TUNNEL FUSELAGE FRAME ATTACHING FITTING CRACKED AT Y STA 446 BETWEEN LONGERONS 18L AND 19L.
DURING INSPECTION LOWER FUSELAGE AFT CARGO COMPARTMENT Y STA 766 OVER LONGERON 26L FITTING WITH CRACK.
DURING INSPECTION LOWER FUSELAGE UNDER WING FILLET FAIRING STRAPS WITH CORROSION FROM Y STA 642 TO Y STA 718 BETWEEN LONGERONS 18R AND 28R.
DURING INSPECTION LOWER FUSELAGE AT STA Y 654.5 BETWEEN LONGERON 28R AND 29R SKIN WITH CRACK.
FUEL HEAT REMAINED ON (UNCONTROLLABLE) DURING FLIGHT. PERFORMED PRECAUTIONARY ENGINE SHUT DOWN. PERFORMED PRECAUTIONARY LANDING.
SHEAR TIE CRACKED BELOW LONGERON 14 LEFT AT FRAME STA 801 REPAIRED SHEAR TIE IAW DWG K050159. (A)
LONGERON 3 LEFT CRACKED AT FRAME TO LONGERON ATTCH POINT STA 930. REMOVED LONGERON SECTION, SPLICED NEW LONGERON IAW DC9 SRM 53-02, FIG 18. (A)
HORZ, STAB JACK SCREW THREADS PITTED/CORRODED. REMOVED AND REPLACED JACK SCREW IAW DC9 MM 27-40-1. (A)