N792A

Part: BRACKET — CRACKED (ZONE 100) · airframe 7,003 hrs

FLAP HANDLE FORWARD SUPPORT BRACKET FOUND CRACKED. NOTED AREA OF STRESS/CRACK A LACK OF RADIUS. REPLACED WITH FACTORY NEW BRACKET.

Part: RIVET — LOOSE (IMPULSE COUPLING)

MAGNETO P/N 66GC20SFNN S/N 21080300. LOOSE RIVETS FOUND ON IMPULSE COUPLING DURING 500 HOUR INSPECTION. REPLACED IMPULE COUPLING WITH NEW.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 6,807 hrs

PILOT REPORTS THAT THE INITIAL MAGNETO CHECK, THE ENGINE WAS RUNNING ROUGH, ON SECOND MAGNETO CHECK ENGINE SMOOTH OUT. ON TAKE OFF THE ENGINE POWER FLUCTUATED AND AIRCRAFT DID NOT MAKE POWER. PILOT ABORTED TAKE-OFF. WE PERFORMED A VISUAL INSPECTION OF THE ENGINE, NO DISCREPANCY WERE NOTED. WE PERFORMED AN ENGINE RUN WITH THE FOLLOWING FINDINGS: OIL PRESSURE IS GOOD. ON ENGINE RUN-UP, MAX STATIC RPM IS 2200. MAGNETO DROP WAS GOOD, BOTH MAGS DROPPED APPROXIMATELY 50 RPM. ENGINE IDLES AT BETWEEN 650 - 700 RPM. ON ENGINE SHUT DOWN, RPM RAISES APPROX. 50 RPM. WE PERFORMED 2 ENGINE RUNS WITH OUTSIDE AIR TEMP. OF 86 DEGREES. BOTH ENGINE RUNS HAD SIMILAR ENGINE PERFORMANCE NUMBERS. REMOVE ENGINE COWLING AND INSPECTED ENGINE, NO DISCREPANCY NOTED. CHECKED MAGNETO TO ENGINE TIMING, TIMING CHECKED GOOD. REMOVED SPARK PLUGS AND INSPECTED. FOUND EROSION ON THE CERAMIC AND LOWER SPARK PLUGS HAD ALOT OF WHAT APPEARS TO BE CARBON/LEAD BUILD UP. NEW SPARK PLUGS HAVE BEEN INSTALLED AND RAN AIRCRAFT, NO ISSUES. PERFORMED ENGINE RUN WITH MAX STATIC RPM’S OF 2200 AND IDLE TO APPROX.. 700RPM’S WITH ENGINE NOT SHUTTING OFF. MAG. DROP WAS APPROX..50 RPM FOR EACH MAG. OAT WAS 84 DEGREES. NOTE: ENGINE RAN THE SAME BEFORE THE SPARK PLUGS WERE REPLACED AND AFTER THEY WERE REPLACED. NO NOTABLE DIFFERENCE IN AIRCRAFT PERFORMANCE.

Part: STIFFENER — CRACKED (ZONE 500) · airframe 4,099 hrs

LEFT WING INBOARD FORWARD LOWER SKIN FORWARD STIFFENER CRACKED.

Part: LINE — LOOSE (GEARBOX) · airframe 61,862 hrs · 42,117 cycles

NR 1 ENGINE OIL QUANTITY DECREASED TO ZERO. ENGINE SHUTDOWN. FOUND GEARBOX OIL PRESSURE LINE LOOSE. ENGINE REPLACED FOR UNABLE TO CONFIRM POSITIVE OIL PRESSURE DURING WINDMILLING AFTER SHUTDOWN.

Part: SKIN — CRACKED (FUSELAGE) · airframe 61,625 hrs · 41,884 cycles

CORRODED CRACK ON RT FUSELAGE AT STA. 1085-1088 BETWEEN S-12 AND S-13.INSTALLED FUSELAGE SKIN REPAIR BETWEEN BS 1080-1100 AND STRINGERS 12R-14R. REPAIR SKETCH 1-211756245. DOA-300064-NM FORM 8100-9 DATED 22 JULY 2006.

Part: GASKET — WORN (NR 1 STRUT) · airframe 61,250 hrs · 41,482 cycles

NR 1 ENGINE STRUT OVERHEAT INDICATION AT TAKEOFF. REPLACED 2 EACH GASKETS ON THERMAL ANTI-ICE SHUT-OFF VALVE AND REALIGNED V-BAND CLAMP ON NR 1 PRECOOLER. GROUND POWER RUN CHECKED GOOD.

Part: FILTER — CLOGGED (NR 1 ENGINE) · airframe 60,905 hrs · 41,139 cycles

UPON APPLICATION OF POWER FOR TAKEOFF, NR 1 ENGINE LOW OIL PRESSURE LIGHT ILLUMINATED. REPLACED NR 1 ENGINE MAIN OIL FILTER. LEAK CHECKED GOOD. REF: P&W MM 72-00-00 FIG 114. OK FOR CONTINUED SERVICE. FOUND CARBON ONLY.

Part: BOLT — SHEARED (THRUST REVERSER) · airframe 60,878 hrs · 41,110 cycles

NR 2 ENGINE SHUT DOWN DUE TO LOUD BANG WHEN THROTTLE MOVED FROM CLIMB TO CRUISE POWER. PERFORMED INSPECTION FOR WINDMILLING PER JT8D MM 72-00-00 ADJ/TEST-01 (1)C. NO DEFECTS NOTED. PERFORMED DECELERATION SURGE TROUBLESHOOTING PER JT8D MM 72-00-00 TBL SHOOT-04 STEPS 1-6. NO DEFECTS NOTED (EXCEPT AS NOTED ON M2. NR 2 THRUST REVERSER DEFLECTOR DOOR DOES NOT STOW COMPLETELY WHILE CLOSED DUE TO UPPER ACTUATOR PISTON TRUCK LINKAGE BOLT SHEARED). REPLACED HARDWARE AND RIGGED CLAMSHELL PER BOEING 727MM SEC 78-30-31. OP CHECKED GOOD.

Part: CONNECTOR — FAULTY (COCKPIT) · airframe 60,831 hrs · 41,060 cycles

ON GEAR RETRACTION ALL RED LIGHTS ON AND ONLY LEFT GEAR GREEN LIGHT THREE TIMES WITH THE SAME RESULT. FOUND BAD CIRCUIT AT PIN 9 OF D292 AT LANDING GEAR POSITION ANNUNCIATOR PANEL. REPAIRED FAULTY CONNECTION AND OPS CHECKED GOOD DURING 10 RETRACTION AND EXTENSIONS CYCLES. REF B727MM 32-32-0 (2) (A-D;G-M).

Part: DUCT — CRACKED (13TH STAGE) · airframe 60,830 hrs · 41,059 cycles

NR 1 ENGINE STRUT OVERHEAT LIGHT ILLUMINATED, RETURN TO ANCHORAGE. REPLACED CRACKED 13TH STAGE BLEED DUCT IN THE NR 1 ENGINE PYLON. REF BMM 36-00-1 PG 201.

Part: WIRE — DAMAGED (FUEL INDICATOR) · airframe 60,474 hrs · 40,698 cycles

ENGINE NR 1, NR 2 & 3 FUEL FLOW INDICATORS READ ZERO AT TAKEOFF. REMOVED CONNECTOR FROM PREVIOUSLY DEFERRED NR 3 ENGINE FUEL FLOW TRANSMITTER AND NR 1 & NR 2 ENGINE FUEL INDICATIONS OP CHECKED GOOD ON GROUND RUN. THE FUEL FLOW POWER SUPPLY WAS REPLACED WITH NEGATIVE RESULTS. ADDITIONAL TROUBLESHOOTING LEAD TO THE REPAIR OF WIRING. OP CHECK GOOD BY FLIGHT CREW.

Part: INDICATION SYS — INOPERATIVE (FUEL FLOW) · airframe 60,176 hrs · 40,395 cycles

NR 2 ENGINE FUEL FLOW INDICATION INOPERATIVE. ENGINE SLOW TO ACCELERATE. FUEL FLOW INDICATION DEFERRED IAW MEL 73-7. PERFORMED ACCELERATION CHECK, FOUND TO BE WITHIN LIMITATIONS.

Part: LINKAGE — LOOSE (THRUST REVERSER) · airframe 59,632 hrs · 39,829 cycles

NR 2 ENGINE WENT TO FULL POWER UPON TAXI-OUT. SECURED ENGINE AND RETURNED TO RAMP. FOUND THRUST REVERSER LINKAGE LOOSE, (NUT MISSING AT AFT END), AT CROSSOVER TUBE ON RIGHT SIDE OF ENGINE. SECURED LEVER ROD END WITH NEW HARDWARE (NO RIGGING CHANGE). CHECKED THROTTLE FOR PROPER TRAVEL AND MOVEMENT, ALL INDICATIONS NORMAL.

Part: PUMP — LEAKING (NR 2 HYD SYS) · airframe 59,608 hrs · 39,809 cycles

A-SYSTEM QUANTITY DECREASING AT TOP OF CLIMB. REPLACED NR 2 A-SYSTEM PUMP FOR LEAKING AT MATING SURFACE. BLED A-SYSTEM AND SERVICED HYDRAULICS. REPLACED NR 1 & NR 2 CASE DRAIN FILTERS. NO FINDINGS IN REMOVED FILTERS. LEAK & OP CHECKED GOOD.

Part: PUMP — LEAKING (HYD SYSTEM) · airframe 59,571 hrs · 39,766 cycles

LOSS OF "A" SYS HYDRAULIC QUANTITY UPON GEAR RETRACTION AT TAKEOFF. REPLACED NR 2 A-SYSTEM HYDRAULIC PUMP. LEAK AND OP CHECK GOOD.

Part: CONTROLLER — UNCONTROLLABLE (CABIN PRESSURE) · airframe 59,555 hrs · 39,756 cycles

NR 2 AIRCRAFT PRESSURIZATION SYSTEM IS UNCONTROLABLE BOTH AUTO AND MANUAL MODE. (STATUS:ORIG/OPEN)

Part: DAMPER — DEFECTIVE (AUTOPILOT SYS) · airframe 58,884 hrs · 39,397 cycles

LOWER YAW DAMPER POPS C/B. TRANSFERRED TO DMI 1462 IAW EWA B727 MEL 22-6 CAT-C. A/P CONSIDERED INOP.

Part: LIGHT — ILLUMINATED (COCKPIT) · airframe 58,673 hrs · 39,263 cycles

NR 3 START VALVE OPEN LIGHT CAME ON START OF T/O RUN, MADE LOW SPEED ABORT (80 KTS). ON TAXI BACK - INDICATION WAS DETERMINED TO BE FALSE. MADE NORMAL DEPARTURE. LIGHT WENT OUT IN CRUISE (310) CAME BACK ON IN DESCENT (2000 FT). TRANSFERRED TO DMI LOG 1125 IAW MEL 80-1-1 CAT C.