N60PD

ATA 2110

AIR CONDITIONER SYSTEM IS INOPERATIVE. A QUICK CHECK REVELED THE QUILL SHAFT WAS BROKEN. REMOVED AND REPLACED FREON COMPRESSOR WITH NEW (PN: MA006006-001, SN: N/A) AND RECEIVER DRYER WITH NEW (PN: 101-384079-5, SN: N/A) FROM FREON AIR CONDITIONING SYSTEM. ALSO REMOVED AND REPLACED THE COMPRESSOR DRIVE QUILL SHAFT ON THE RIGHT ENGINE WITH NEW (PN: 115-555025-9, SN: N/A). ALL WORK PERFORMED IN ACCORDANCE WITH THE HAWKER BEECHCRAFT KING AIR MAINTENANCE MANUAL SECTION 21-51-00, AND THE API CONVERSIONAIR R134A CONVERSION KIT INSTRUCTIONS/MANUAL. OPERATIONAL CHECK OF FREON AIR CONDITIONING SYSTEM GOOD.

ATA 7320

WHILE PERFORMING ENGINE RUN UP AT RUNWAY 36R RUN UP, LT ENGINE WAS FOUND TO BE UNRESPONSIVE AFTER LT ENGINE PROP GOVERNOR CHECK WAS COMPLETE. N1 DROPPED BELOW 50 PERCENT AND CONTINUED TO DROP. FUEL FLOW ALSO DROPPED AND CONTINUED TO DROP. ENG WAS THEN SHUTDOWN AND MOTORED FOR 30 SECONDS. REPLACEMENT FCU WITH MODES S/B 24 ACCOMPLISHED, WAS INSTALLED AND TORQUED. THE P3 AND THE PY LINES WERE MM 73-20-00. A NEW O-RING WAS INSTALLED, TORQUED AND SAFETIED. THE CONDITION LEVER WAS CONNECTED TO THE CONTROL ARM AND BOLT WAS TIGHTENED, TORQUED AND SAFETIED. FCU DRAIN LANE WAS CONNECTED. AIRFRAME FUEL RETURN LINE WAS INSTALLED AND TORQUED. THE 11" ROD WAS INSTALLED AND THE DEAD BAND INITIALLY SET. UNIT NEEDS TO BE RUN, LEAK CHECKED, AND FINAL RIGGING ADJUSTMENTS NEED TO BE MADE AND SAFETIES NEED TO BE ACCOMPLISHED. REMOVED AND REPLACED FUEL OIL HEAT EXCHANGER WITH A SERVICEABLE AS REMOVED UNIT IAW MM 73-10-01. COMPLIED WITH REQUIRED OPS CHECKS 3,5,6,7,8, AND 11 OF TABLE 501 MM. OPS CHECK GOOD. FUEL TEMP AFTER ENG RUN IS BELOW 140 DEGREES. COMPLIED WITH TABLE 501, OPS CHECKS REQUIRED AFTER FCU REPLACEMENT IAW MM. (K)

ATA 3320

SHUTDOWN THE ENGINES, NOTICED LIGHT SMOKE COMING FROM UNDER INSTRUMENT PANEL & AN ODOR LIKE ELECTRICAL BURNING. MAINT INSPECTED AC & WHEN MASTER SWITCH WAS TURNED ON, A RESISTOR MOUNTED TO FWD BULKHEAD UNDER PILOTS INSTRUMENT PANEL FOUND TO BE GLOWING RED & EMITTING SMOKE. AFTER REVIEWING THE WIRING FROM THE RESISTOR IT WAS DETERMINED TO BE THE (R145) RESISTOR FOR THE FLUORESCENT LIGHTENING SYSTEM. THE WIRING SYSTEM FOR THE FLUORESCENT SYSTEM WAS INSPECTED FOR SHORTS AND THE ONLY ITEM FOUND WAS A LOOSE WIRE CONNECTION TO THE RT ELECTRICAL FILTER MOUNTED ON THE RT SIDE WALL OF THE AC UNDER THE EMERGENCY EXIT WINDOW. A NEW RESISTOR WAS INSTALLED AND THE SYS CHECKED GOOD AND THE AC WAS RETURNED TO SERVICE. I

ATA 3240

WHILE TRANSITIONING FROM TAXI HOLD LINE TO CLEARED POSITION, HOLD AND MAKING A RT TURN ONTO RUNWAY, PILOT EXPERIENCED A LOSS OF BRAKES. PILOT PUT ENGINES INTO REVERSE AND AC WAS TURNING TO THE LT. PILOT THEN SHUTDOWN ENGINES AS THE AC CONTINUED TO TURN LT ONTO OVERRUN AREA OF THE RUNWAY. DURING THE SHUTDOWN OF THE ENGINES, FLAMES WERE NOTED COMING FROM THE ENGINE AREA. WHEN THE AIRCRAFT CAME TO A COMPLETE STOP, ALL PERSONNEL EXITED THE AIRCRAFT. THE AIRCRAFT WAS TAKEN TO MAINTENANCE AND IT WAS DETERMINED THAT THE FLAMES COMING FROM THE ENGINES WAS THROUGH THE EXHAUST STACKS DUE TO THE ENGINES BEING SHUTDOWN WHILE STILL BEING IN REVERSE. REASON FOR THE BRAKE FAILURE IS STILL NOT KNOWN AT THIS TIME.

ATA 5330

DURING EVENT NR 1 INSPECTION AND SPECIAL STRUCTURAL, BELOW FLOORBOARD FROM FORWARD PRESSURE BULKHEAD TO AFT PRESSURE BULKHEAD, A 1.50 INCH LATERAL CRACK WAS FOUND IN THE LOWER SKIN PANEL AT APPROXIMATE CENTERLINE OF AIRCRAFT ABOUT .50 INCH FORWARD OF BS 167.625. SUBMITTER STATED THIS WILL REQUIRE DOUBLER REPAIR. (X)

ATA 5620

DURING ROUTINE CLEANING OF THE AIRCRAFT WINDOWS, DELAMINATION BUBBLES WERE NOTED NEAR THE BOTTOM EDGE AREA OF THE NR 5 PASSENGER WINDOW. BUBBLES WERE ABOUT THE SIZE OF A PENCIL ERASER OR SMALLER. TOTAL AREA WAS APPROXIMATELY 8 INCHES BY .50 INCH. WINDOW WAS REPLACED WITH NEW.