N258PB

Part: SPAR CAP — CRACKED · airframe 37,132 hrs · 35,978 cycles

A CRACK WAS IDENTIFIED AT THE RT SIDE OF THE LWR FWD CARRYTHROUGH SPAR CAP (AFT MOST IB FASTENER COMMON TO WING JOINT FITTING) WHILE PERFORMING NDT PROCEDURE AS AMOC FOR AD2018-03-03R1. THE CRACK WAS CONFIRMED WITH BOLT HOLE EDDY CURRENT PROCEDURE AFTER THE FASTENER WAS REMOVED. CRACK DIRECTION IS AFT AND MEASURES APPROXIMATELY 0.1875".

Part: SPAR CAP — CORRODED (LT WING) · airframe 35,957 hrs · 33,615 cycles

WHILE CONDUCTING OTHER MAINTENANCE, CORROSION WAS NOTED ON THE HORIZONTAL LEG OF THE LOWER LEFT AFT OUTBOARD SPAR CAP, AT WS 222.46. THE CORROSION AREA MEASURED .218 BY .086. THE DEPTH OF THE CORROSION MEASURED AT .022, WHICH IS DEEPER THAN THE ALLOWABLE REMOVAL LIMITS PER MEB 95-11 R1 SECTION 7 PARAGRAPH B. AS A RESULT, THE SPAR CAP WITH CHANGED WITH NEW.

Part: FRAME — CORRODED (FUSELAGE) · airframe 35,957 hrs · 36,315 cycles

WHILE CONDUCTION OTHER MAINTENANCE, AN AREA OF CORROSION WAS NOTED ON THE FUSELAGE FRAME ASSEMBLY AT FS 214.00, JUST ABOVE THE 501110-12 STRIKER PLATE FOR THE LOWER PASSENGER DOOR PIN. THE 501110-12 STRIKER PLATE WAS REMOVED FOR FURTHER INSPECTION. UPON REMOVAL OF THE STRIKER PLATE, MORE CORROSION WAS DISCOVERED. THIS AREA OF CORROSION MEASURED AT 2 HIGH BY .75 WIDE, WITH A DEPTH OF .055. THE FUSELAGE FRAME AND STRIKER PLATE WERE REPLACED WITH NEW PARTS.

Part: STRAP — CORRODED (LT WING) · airframe 35,957 hrs · 33,615 cycles

WHILE CONDUCTING A VISUAL INSPECTION, CORROSION WAS NOTED ON THE LEFT SPAR STRAP. ONE AREA OF CORROSION WAS FOUND AT LWS 127.04 TO 129.04 AT THE AFT ROW OF FASTENERS. CORROSION MEASURED .50 IN WIDTH AT IT'S WIDEST POINT. A SMALL PORTION OF THIS AREA WAS BLENDED TO DETERMINE DEPTH OF THE CORROSION. CORROSION DEPTH WAS MEASURED AT .050. A SECOND AREA OF CORROSION WAS NOTED AT LWS 131.54 TO 136.54 AT THE MOST FORWARD EDGE OF THE SPAR STRAP. THIS CORROSION MEASURED .25 IN WIDTH AT IT'S WIDEST POINT. A SMALL PORTION OF THIS CORROSION WAS BLENDED TO DETERMINE THE DEPTH. CORROSION DEPTH WAS MEASURED AT .055. THE SPAR STRAP WAS REPLACED.

Part: BOLT — SHEARED (ENGINE)

ENGINE DISASSEMBLED FOR OVERHAUL. CRANKSHAFT CLUSTER GEAR BOLTS (6 EACH) SHEARED. NEW PART NUMBER LARGE GEAR (P/N 656991) AND BOLTS (P/N 656990) WERE IN PLACE IAW LATEST SERVICE BULLETINS. LACK OF FRETTING SIGNATURES ON CRANKSHAFT GEARS AND ATTACHING BOLTS INDICATE THAT THIS WAS A SINGLE OVERLOAD EVENT; LIKELY KICK-BACK DURING STARTING. NOTIFIED OPERATOR TO INSPECT SHOWER OF SPARKS STARTING SYSTEM.

Part: RIB — CRACKED (RT WING) · airframe 35,441 hrs · 32,608 cycles

DURING A ROUTINE INSPECTION, A CRACK WAS IDENTIFIED IN THE RT CLOSEOUT RIB AT RWS 106.79. ON REMOVAL, IT WAS NOTED THAT THE FASTENER HOLE WHERE THE CRACK STARTED FROM WAS NO LONGER IN TOLERANCE FOR THE LOCK FASTENER THAT WAS PREVIOUSLY INSTALLED THERE.

Part: FITTING — CRACKED (RT NACELLE) · airframe 35,310 hrs · 32,285 cycles

DURING A ROUTINE INSPECTION, A CRACK WAS DISCOVERED ON THE RT OUTBOARD NACELLE FITTING. THE CRACK WAS FOUND ON THE INBOARD SIDE OF THE FITTING, JUST FORWARD OF THE SPAR STRAP. THE CRACK MEASURED .171 IN LENGTH.

Part: FITTING — CRACKED (LT NACELLE) · airframe 35,310 hrs · 32,285 cycles

DURING A ROUTINE INSPECTION, A CRACK WAS DISCOVERED ON THE LT OUTBOARD NACELLE FITTING THE CRACK WAS DISCOVERED ON THE INBOARD SIDE OF THE FITTING, JUST FORWARD OF THE SPAR STRAP. THE CRACK WAS .108 IN LENGTH.

Part: GOVERNOR — DEFECTIVE (RIGHT) · airframe 33,562 hrs · 28,352 cycles

ON CLIMB OUT RT PROP INCREASED RPM BEYOND THE RED, BY ITSELF, HAD NO CONTROL OF RT PROP. ALSO RT PROP WOULD NOT FEATHER. PERFORMED AN AIR RETURN & LANDED WITH NO FURTHER INCIDENT. INSPECTED THE RT PROP CONTROL, REPOSITIONED PROP GOVERNOR CABLE. R & R PROP GOVERNOR IAW MM CHAPTER 61-20-00. OPERATIONS CHECKED GOOD WITH NO FURTHER DEFECT NOTED.

Part: BEAM — CHAFED (LT NACELLE) · airframe 33,184 hrs · 27,663 cycles

DURING SCHEDULED INSPECTION, CHAFE DAMAGE WAS NOTED AT LT NACELLE OTBD ENG BEAM AFT OF CORRESPONDING ENG MOUNT. THIS DAMAGE WILL BE REPAIRED IAW REPAIR DEFINITION SUPPLIED & SUBSTANTIATED BY DER. A SUPPLEMENT TO THIS SDR WILL BE FORWARDED SEPARATELY FURTHER ILLUSTRATING DAMAGE POINT.

Part: SPAR — CRACKED (WING) · airframe 33,184 hrs · 27,663 cycles

DURING SCHEDULED INSPECTION, MULTIPLE SPAR WEB CRACKS WERE NOTED INITIATING FROM SPAR WEB MOUSE HOLE CUT OUTS AT AFT CARRY THROUGH SPAR ASSEMBLY, PN 5211173-2, AT CTR LOWER SECTION OF FWD & AFT WEBS. THIS DAMAGE WILL BE REPAIRED IAW REPAIR DEFINITION SUPPLIED & SUBSTANTIATED BY DER. A SUPPLEMENT TO THIS SDR WILL BE FORWARDED SEPARATELY FURTHER ILLUSTRATING DAMAGE POINTS.

Part: BEAM — CHAFED (RT NACELLE) · airframe 33,184 hrs · 27,663 cycles

DURING SCHEDULED INSPECTION, CHAFE DAMAGE WAS NOTED AT RT NACELLE OTBD ENG BEAM AFT OF CORRESPONDING ENG MOUNT. THIS DAMAGE WILL BE REPAIRED IAW REPAIR DEFINITION SUPPLIED & SUBSTANTIATED BY DER. A SUPPLEMENT TO THIS SDR WILL BE FORWARDED SEPARATELY FURTHER ILLUSTRATING DAMAGE POINT.

Part: SPAR — CRACKED (WING) · airframe 33,184 hrs · 27,663 cycles

DURING SCHEDULED INSPECTION, MULTIPLE SPAR WEB CRACKS WERE NOTED INITIATING FROM SPAR WEB, MOUSE HOLE CUT OUTS AT FWD CARRY THROUGH SPAR ASSEMBLY, PN 5211171-2, AT CTR LOWER SECTION OF FWD & AFT WEBS. THIS DAMAGE WILL BE REPAIRED IAW REPAIR DEFINITION SUPPLIED & SUBSTANTIATED BY DER. A SUPPLEMENT TO THIS SDR WILL BE FORWARDED SEPARATELY FURTHER ILLUSTRATING DAMAGE POINTS.

Part: STRAP — CORRODED (WING SPAR) · airframe 33,184 hrs · 27,663 cycles

DURING ROUTINE SCHEDULED INSPECTION, AREAS OF CORROSION WERE FOUND AT LT & RT LOWER WING SPAR CAP STRAPS PREVIOUSLY INSTALLED VIA SK402-47B ON 12/05/2005 TO SATISFY REQUIREMENT OF AD2005-12-13 & MEB02-5. THE CORRECTIVE ACTION TO REMEDIATE CONDITION WILL BE TO PERFORM A DETAILED VISUAL INSPECTION OF SURROUNDING STRUCTURE & TO REPLACE LT & RT LOWER WING SPAR CAP STRAPS WITH NEW PN 5292029-1-2 IAW CURRENT REVISION OF SK402-47.

Part: SPAR — CRACKED (WING) · airframe 33,184 hrs · 27,663 cycles

DURING ROUTINE SCHEDULED INSPECTION, MULTIPLE WEB FLANGE CRACKS WERE NOTED AT AFT FUSELAGE CARRY THROUGH SPAR ASSEMBLY, PN 5211173-2 AT CTR UPPER SECTION FWD & AFT WEBS. THIS DAMAGE WILL BE REPAIRED, REPAIR DEFINITION SUPPLIED & SUBSTANTIATED BY DER. A SUPPLEMENT TO THIS SDR WILL BE FORWARDED SEPARATELY FURTHER ILLUSTRATING DAMAGE POINTS.

Part: BEARING SUPPORT — CORRODED (RUDDER) · airframe 33,184 hrs · 27,663 cycles

AT SCHEDULED INSPECTION, SEVERE CORROSION WAS FOUND AT LWR RUDDER HINGE BRACKET & ASSOCIATED BEARING BLOCK. CORRECTIVE ACTION WILL BE TO REMOVE AFFECTED PARTS FOR REPLACEMENT WITH NEW IAW MEB00-4 & PERFORM ADDITIONAL DETAILED INSPECTION OF SURROUNDING STRUCTURE.

Part: GOVERNOR — OVERSPEED (PROPELLER) · airframe 32,592 hrs

PILOT REPORTED THAT ON CLIMBOUT, THE RT PROP BECAME UNCONTROLLABLE AND WOULD OVERSPEED. THE PILOT ELECTED TO RETURN TO THE DEPARTURE AIRPORT. UPON MX INSPECTION, THE RT PROP AND PROP GOVERNOR WERE REPLACED IAW MM CHAPTER 61. THE PROP OPS AND LEAK CHECKED GOOD.

Part: DRAG BRACE — CRACKED (NLG) · airframe 32,475 hrs

AT SCHEDULED INSPECTION, NLG DRAG BRACE, PN 5142002-5 WAS FOUND TO BE CRACKED IN THE AREA OF NLG ACTUATOR ATTACH POINT. METHOD OF INSPECTION WAS DYE PENETRANT. THIS CRACK WAS FOUND TO BE BEYOND LIMIT ALLOWABLE OF MEB91-11R1. THIS UNIT HAS BEEN SCRAPPED & A REPLACEMENT DRAG BRACE HAS BEEN INSTALLED IN ACFT.

Part: BOLT — FAILED (TORQUE LINK) · airframe 32,296 hrs

PILOT REPORTED THAT WHILE TAXIING, A DISCREPANCY WAS NOTED ON THE LT MAIN. ON INSPECTION, IT WAS DISCOVERED THAT THE LT MLG TORGUE LINK CENTER BOLT HAD COME APART. THE TORQUE LINK WAS REASSEMBLED WITH NEW HARDWARE.

Part: DRAG BRACE — CRACKED (NLG) · airframe 31,210 hrs

AT SCHEDULED INSPECTION, NLG DRAG BRACE, PN 5142002-5, WAS FOUND TO BE CRACKED IN THE AREA OF NLG ACTUATOR ATTACH POINT. METHOD OF INSPECTION WAS DYE PENETRANT. THIS CRACK WAS FOUND TO BE WITHIN ALLOWABLE LIMIT OF MEB91-11R1. THIS UNIT HAS BEEN REPAIRED IAW PROCEDURE OUTLINED IN MEB941-11R1 & RETURNED TO SERVICE.

Part: BEAM — CRACKED (ZONE 400) · airframe 28,485 hrs · 16,575 cycles

LEFT ENGINE OUTBOARD SIDE OF CROSSOVER BEAM IS CRACKED. MAINTENANCE TO REMOVE AND REPLACE CROSSOVER BEAM ASSY.

Part: AXLE — CRACKED (RT MLG) · airframe 27,300 hrs

ON TAXI AFTER LANDING, PILOT REPORTED RIGHT BRAKE "LOCKED UP". UPON FURTHER INSPECTION BY MAINTENANCE IT WAS FOUND THAT THE RIGHT MAIN LANDING GEAR AXLE WAS CRACKED. MAINTENANCE REMOVED AND REPLACED RIGHT MAIN LANDING GEAR LOWER AXLE ASSEMBLY. AIRCRAFT WAS RETURNED TO SERVICE.

Part: MASTER SWITCH — FAILED (LT SWITCH PANEL)

ON PRE-FLIGHT INSPECTION, AVIONICS SWITCH FAILED. MAINTENANCE REPLACED THE SWITCH AND RETURNED AIRCRAFT TO SERVICE. PTRS 12/12/01

Part: SWITCH — FAILED (AVIONICS PANEL)

ON PREFLIGHT INSPECTION, AVIONICS SWITCH FAILED, MAINTENANCE REPLACED THE SWITCH AND RETURNED AIRCRAFT TO SERVICE.

Part: AILERON — WEIGHT BROKEN (BALANCE WEIGHT)

AILERON HAS A 4 FOOT LEAD WEIGHT INSTALLED FOR BALANCING. LEAD WEIGHT HAD BROKEN AWAY FROM MOUNT AND WAS LOOSE IN LEADING EDGE OF AILERON. LEADING EDGE WAS REMOVED AND BALANCE WEIGHT WAS RE-ATTACHED TO AILERON. FLIGHT CONTROL WAS RE-BALANCED AND RETURNED TO SERVICE.