Tiffin Aire Inc.

Operated by Tiffin Aire (per NTSB report)

A loss of aircraft control for undetermined reasons.

Part: SPAR CAP — CORRODED (LT WING) · airframe 11,752 hrs · 7,789 cycles

BLENDED CORRODED AREAS ON THE LEFT AND RIGHT HAND WINGS AFT SPARS LOWER SPAR CAPS, LOCATED IN THE MAIN LANDING GEAR WHEEL WELL AREAS, PERFORMED ULTRASONIC AND EDDY CURRENT INSPECTIONS AND REPORTED FOR REPAIR DISPOSITION. TREATED AND PRIMED REPAIR AREAS IAW TEXTRON REPAIR MEMO.

Part: PANEL — CORRODED (NLG WW) · airframe 10,871 hrs · 7,123 cycles

LEVEL 1 CORROSION AROUND NLG SQUAT SWITCH WIRE HARNESS CARRY THROUGH ON LT SIDE OF NOSE WHEEL WELL APPROX 1 O'CLOCK AREA.

Part: HINGE BRACKET — CORRODED (VERTICAL STAB) · airframe 8,900 hrs · 5,930 cycles

MECHANICALLY BLENDED CORROSION ON THE MIDDLE RUDDER HINGE BRACKET UPPER HINGE HALF ON VERTICAL STABILIZER NEAR THE BONDING STRAP HOLE, PERFORMED EDDY CURRENT AND ULTRASONIC THICKNESS INSPECTIONS AND SUBMITTED FINDINGS TO MANUFACTURER ENGINEERING. TREATED METAL AND PRIMED IAW ENGINEERING REPAIR MEMO.

Part: BELLMOUTH — CORRODED (APU) · airframe 9,980 hrs · 6,526 cycles

BLENDED CORRODED APU EXHAUST DUCT BELL MOUTH, PERFORMED ULTRASONIC THICKNESS AND EDDY CURRENT CRACK INSPECTION AND REPORTED TO TEXTRON FOR DISPOSITION. REINSTALLED DUCT PER TEXTRON MEMO.

Part: SKIN — CORRODED (RT WING) · airframe 13,207 hrs · 10,479 cycles

CORROSION ON THE RT UPPER WING SKIN, BLENDED AND PERFORMED AN EDDY CURRENT AND ULTRASONIC THICKNESS INSPECTIONS, PREPPED AND TREATED AREAS IAW SRM 51-10-03, 51-70-08, AND MM 51-10-00.

Part: SKIN — CORRODED (LT WING) · airframe 13,207 hrs · 10,479 cycles

BLENDED 10 AREAS OF CORROSION ON THE LT UPPER WING SKIN, PERFORMED EDDY CURRENT CRACK AND ULTRASONIC THICKNESS INSPECTION, PREPPED AND TREATED AREAS IAW SRM 51-10-03, AND MM 51-10-00.

Part: SKIN — CORRODED (BS 187) · airframe 13,207 hrs · 10,479 cycles

BLENDED TWO AREAS OF CORROSION ON THE EXTERIOR FUSELAGE SKIN FWD OF THE CABIN DOOR AT BS 187, PERFORMED EDDY CURRENT CRACK AND ULTRASONIC THICKNESS INSPECTIONS, PREPPED AND TREATED IAW SRM 51-10-03, MM 51-10-00, AND 51-70-08.

Part: DOOR — CORRODED (EMERGENCY EXIT) · airframe 8,556 hrs · 5,585 cycles

EMERGENCY EXIT DOOR CORRODED BEYOND ECONOMIC REPAIR, REPLACED THE DOOR.

Part: RIB — CORRODED (RT WING) · airframe 8,556 hrs · 5,585 cycles

REPAIRED AREAS OF CORROSION ON LOWER FLANGE OF WING RIB P/N 6922037-20, AT WING STATION 18.50 IN RT MLG WELL PER ENGINEERING MEMO DQ10680M1, DATED JANUARY 5, 2018.

Part: SKIN — CORRODED (VERTICAL STAB) · airframe 9,898 hrs · 6,547 cycles

REMOVED FIRST LOCK FASTENER COLLAR, JUST ABOVE APU STINGER, ON LT SIDE OF VERTICAL STAB AFT SPAR FACE. MECHANICALLY BLENDED CORROSION APX 3 INCHES ABOVE APU STINGER PANEL 342AB. SUBMITTED FINDINGS TO CESSNA ENGINEERING AND PERFORMED BLEND TREAT REPAIR PER TEXTRON AVIATION MEMO DQ10551M1R1 RRL DATED 20 DEC 2017. INSTALLED 1 NEW HI-LOK COLLAR HL70-6 IN SAME LOCATION AS REMOVED.

Part: SKIN — CORRODED (TAILCONE) · airframe 14,904 hrs · 8,916 cycles

FOUND LOWER AFT TAILCONE SKIN AND STRINGER, NEAR THE APU, CORRODED. REPLACED PARTS WITH NEW STRINGER P/N 6712615-56 AND LOWER SKIN P/N 6712615-56.

Part: SKIN — CORRODED (FUSELAGE) · airframe 14,904 hrs · 8,916 cycles

FOUND LOWER STINGER SKIN NEAR THE APU CORRODED. REPLACED WITH NEW SKIN P/N 6712615-56.

Part: SKIN — CORRODED (RT WING) · airframe 14,904 hrs · 8,916 cycles

REPLACED CORRODED RT INBOARD UPPER WING SKIN WITH NEW P/N 6722311-18.

Part: SKIN — CORRODED (LT WING) · airframe 14,904 hrs · 8,916 cycles

REPLACED CORRODED LH INBOARD UPPER WING SKIN WITH NEW P/N 6722311-17.

Part: DRAG ANGLE — CORRODED (LT WING) · airframe 14,904 hrs · 8,916 cycles

REPAIRED CORROSION FOUND UNDER THE LH WING FORWARD AND AFT DRAG ANGLES PER CESSNA REPAIR DEFINITION S-750-0190/17RD. REPAIRED CORROSION FOUND UNDER THE RH WING AFT DRAG ANGLE PER CESSNA REPAIR DEFINITION S-750-0190/17RD. MECHANICALLY BLENDED APPROXIMATELY 40 AREAS OF CORROSION ON LH UPPER WING SKIN SURFACES. PERFORMED ULTRASONIC THICKNESS AND EDDY CURRENT INSPECTION AND SUBMITTED FINDINGS TO CESSNA FOR REPAIR DISPOSITION. PERFORMED ROTO PEEN, TREATMENT AND TOPCOAT AS REQUIRED PER CESSNA REPAIR DEFINITION S-750-0190/17RD. MECHANICALLY BLENDED APPROXIMATELY 40 AREAS OF CORROSION ON RH UPPER WING SKIN SURFACES. PERFORMED ULTRASONIC THICKNESS AND EDDY CURRENT INSPECTION AND SUBMITTED FINDINGS TO CESSNA FOR REPAIR DISPOSITION. PERFORMED ROTO PEEN, TREATMENT AND TOPCOAT AS REQUIRED PER CESSNA REPAIR DEFINITION S-750-0190/17RD.

Part: SKIN — DAMAGED (HORIZONTAL STAB) · airframe 14,904 hrs · 8,916 cycles

FOUND CORROSION AT TWO LOCATIONS ON THE EXTERIOR SURFACE UPPER SKIN OF THE LT HORIZONTAL STABILIZER, ONE AREA ABOVE THE INBOARD ELEVATOR HINGE AND ONE AREA AT THE OTBD ELEVATOR CUTOUT. MECHANICALLY BLENDED AREAS, PERFORMED ULTRASONIC THICKNESS AND EDDY CURRENT CRACK INSPECTIONS FOR REPAIR DISPOSION. REPLACED BLENDED FASTENERS AS REQUIRED, TREATED, AND TOP COATED AREAS IAW REPAIR DEFINITION S-750-0190/14RD.

Part: SKIN — CORRODED (LT PYLON) · airframe 14,904 hrs · 8,916 cycles

THREE CORRODED AREAS ON THE CENTER UPPER SKIN OF THE LT PYLON. BLENDED, TREATED, FABRICATED AND INSTALLED DOUBLERS IAW EO ERO-910739, REVISION IR.

Part: SKIN — CORRODED (FUSELAGE) · airframe 14,908 hrs · 8,917 cycles

FOUND CORROSION ON EXTERIOR OF FUSELAGE SKIN AT APPROXIMATELY FS400 AT STRINGERS 3L, 3R, AND 4R. MECHANICALLY BLENDED, MEASURED, TREATED, AND REPLACED FASTENERS AS REQUIRED PER REPAIR DEFINITION S-750-0190/16RD.

Part: RIB — WORN (RUDDER) · airframe 10,979 hrs · 8,711 cycles

EXCESSIVE FREE-PLAY FOUND IN RUDDER TRIM TAB HINGE. REPLACED RUDDER TRIM TAB HINGES WITH NEW HINGE PINS. FOUND RUDDER RIB, BELOW THE TRIM TAB, WORN/DAMAGED BY FROM OLD TRIM TAB HINGE PIN, REPLACED RIB WITH NEW.

Part: BRACKET — CORRODED (RUDDER) · airframe 12,710 hrs · 10,270 cycles

UPPER BRACKET OF THE CENTER RUDDER HINGE FOUND CORRODED OUT OF LIMITS. REPLACED THE BRACKET.

Part: FITTING — LOOSE (HYDRAULIC LINE) · airframe 8,382 hrs · 4,933 cycles

DURING CRUISE FLIGHT, CREW RECEIVED A CAS MESSAGE FOR LOW HYDRAULIC FLUID LEVEL ON NR 1 SYSTEM. AIRCRAFT LANDED. ON ARRIVAL AT AIRCRAFT MAINTENANCE CREW FOUND A LEAKING MS FITTING. NO PRIOR MAINTENANCE WAS DONE TO OR AROUND THAT FITTING OR LINE AT OUR FACILITY. THE FITTING WAS SECURED BY TIGHTENING APPROXIMATELY 1/4 TURN AND NO LEAKS NOTED. AIRCRAFT WAS RETURNED TO SERVICE AFTER THAT AND NO FURTHER DEFECTS HAVE BEEN REPORTED.

Part: MANIFOLD — LEAKING (APU FUEL)

THE FLIGHT CREW NOTED A STRONG FUEL ODOR IN THE AFT CABIN, UPON INVESTIGATION, FUEL WAS FOUND ON THE AFT EQUIPMENT ACCESS DOOR AND UNDER THE APU. THE APU SHROUD WAS OPENED AND THE FUEL MANIFOLD WAS REMOVED AND IT WAS DISCOVERED TO HAVE A SMALL PINHOLE IN ONE OF THE MAIN FUEL LINES WHICH WAS LEAKING ONTO THE APU AND CAUSING THE FUEL ODOR. THE MANIFOLD WAS REPLACED AND NO LEAKS WERE FOUND. THE AIRCRAFT WAS RETURNED TO SERVICE. (K)