N478FE

Part: BRACKET — CRACKED (LT WING) · airframe 43,064 hrs · 29,849 cycles

LT WING BRACKET BROKEN INSIDE ACCESS PANEL 8405. REMOVED AND REPLACED BROKEN BRACKET IAW SRM 51-10-1 AND SRM 51-30-2.

Part: TRANSMITTER — FAILED (OIL PRESSURE) · airframe 42,530 hrs · 29,365 cycles

DURING CLIMB THROUGH 17,000 FT, NOTICED NR 1 ENG OIL PRESS AT 27 PSI. SHUT ENG DOWN IAW RED TABS LANDED IN MEM. ENT BY: 206208 RPT BY: 111069, SWAPED NR 1 AND NR 2 OIL PRES IND, RAN NR 1 ENG OIL PRES IND STUCK AT 27PSI, LOP LIGHT WAS OUT ALL OTHER IND WERE NORMAL, POSSIBLE OIL PRESS TRANSMITTER. REMOVED AND REPLACED PRESSURE TX REF PER MM 79-33-001-4. OPS CK AND LEAK CK NORMAL REF PER 79-32-000-5. RAN ENG PER JRH CH 5, ALL IND NORMAL.

Part: ACCESSORY UNIT — FALSE INDICATION (E&E BAY) · airframe 41,443 hrs · 28,501 cycles

LANDING GEAR LEVER LATCH FAILED TO RELEASE DURING GEAR RETRACTION. THE QRH PROCEDURE ON PAGES 2-6-2-12 /13 COMPLIED WITH. LANDING GEAR FAILED TEST NR 1 OF THE PROCEDURE. WHEN THE FLAPS WERE RETRACTED FROM 5 TO 2 DEGREES. AN INTERMITTENT HORN SOUNDED. AN EMERGENCY WAS DECLARED AND UNEVENTFUL LANDING WAS MADE ON RWY 27 AT MEM. R & R MLG ACCESORY UNIT IAW 727-200 AMM 32-09-121-5. JACKED A/C, RETRACTED AND EXTENDED GEAR SEVERAL TIMES, NO DEFECTS NOTED. R & R MLG CONTROL LEVER LOCK SOLENOID PER M/M 32-31-016-4.STILL REQUIRES OPS CK. COMPLETED OPS TEST OF LEVER LOCK SOLENOID AND ALSO RAN GROUND OPS TEST OF LDG GEAR ELECTRONIC MODULE.

Part: WARNING LIGHT — FALSE ACTIVATION (COCKPIT) · airframe 41,414 hrs · 28,476 cycles

BOTH FIRE WARNING MASTER LIGHTS ON FORWARD GLARESHIELD ILLUMINATED TWICE FOR ABOUT 1 SECOND EACH TIME DURING CRUISE AT F270. MOMENTARY BELL WITH EACH ILLUMINATION. NO OTHER WARNINGS AND ALL ENGINE INSTRUMENTS NORMAL. FIRE TEST IN BOTH LOOPS OK BOTH INFIGHT AND ON GROUND. PERFORMED FIRE WARNING DETECTOR SYSTEM TEST PER MM 26-11-000-05. OPS CK NORMAL. ALSO INSPECTED E&E COMPARTMENT FOR SECURITY OF ENG FIRE PROTECTION CONTROLLER. FOUND OK. NO HISTORY FOR LAST 90 DAYS. OK FOR SERVICE.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 40,624 hrs · 27,842 cycles

CORROSION ON FLOORBEAM AT BS 620, RBL 10, WL 208. R&R FLOORBEAM PER SRM 53-10-8.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 40,624 hrs · 27,842 cycles

CORROSION ON STR 28L, BS 640-660. R&R STRINGER PER SRM 53-10-1, 53-10-3, 53-30-3.

Part: SKIN — GOUGED (FUSELAGE) · airframe 40,619 hrs · 27,832 cycles

LT FUSELAGE EXTERIOR SKIN HAS A GOUGE AT BS 365.5 BETWEEN STR 16L - 17L. R&R SKIN PER SRM 53-30-3 FIG 3 & EA 7-5330-54319.

Part: SKIN — CORRODED (FUSELAGE) · airframe 40,619 hrs · 27,832 cycles

FOUND CORROSION ON SKIN AT BS 483-495, 528R. R&R SKIN PER SRM 53-30-3.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 40,619 hrs · 27,832 cycles

CORROSION C53-111-01 ON STRINGER 328R, BS 480+5 FWD CARGO BAY. R&R STRINGER PER SRM 53-10-3.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 40,619 hrs · 27,832 cycles

CORROSION IN FASTENER HOLES ON FLOORBEAM LOWER FLANGE AT BS 1070, LBL 45 TO RBL 45. R&R FLOORBEAM PER DWG SR27-53-034, SRM 53-10-8.

Part: SKIN — DENTED (FUSELAGE) · airframe 40,619 hrs · 27,832 cycles

DENTS ON FUSELAGE EXTERNAL SKIN AT BS 268 BETWEEN STR 19R & 20R. R&R SKIN PER SRM 53-30-2 FIG 24.

Part: SKIN — GOUGED (FUSELAGE) · airframe 40,619 hrs · 27,832 cycles

LT FUSELAGE EXTERIOR SKIN HAS A GOUGE AT BS 294.5 JUST ABOVE STR 17L. R&R SKIN PER EA 7-5330-67012.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 40,619 hrs · 27,832 cycles

CORROSION ON FLOORBEAM UPPER CHORD AT BS 344, LBL 60 - RBL 4, WL 208. R&R FLOORBEAM PER SRM 53-10-8 FIG 9.

Part: SKIN — DENTED (FUSELAGE) · airframe 40,619 hrs · 27,832 cycles

DENT ON FUSELAGE EXTERIOR SKIN AT BS 194 BELOW STR 20L. R&R SKIN PER SRM 53-30-3 FIG 24.

Part: MODULE — DEFECTIVE (COCKPIT) · airframe 40,570 hrs · 27,794 cycles

NOSE GEAR LIGHT (GREEN) DID NOT ILLUMINATE WITH GEAR HANDLE DOWN. PUSHED PRESS TO TEST GREEN LIGHT ILLUMINATED. MANUALLY EXTENDED THE GEAR. CHECKED ALIGNMENT STRIPE ON NOSE, INDICATED DOWN AND LOCKED BUT STILL NO GREEN LIGHT. REPUSHED PRESS TO TEST AND GREEN LIGHT REMAINED ILLUMINATED AFTER RELEASE BUT NO SPRING TENSION ON NOSE GEAR LIGHT. FOUND THE NOSE GEAR GREEN LIGHT ASSY BAD; PRESS TO TEST FEELS SOLID (NO SPRING TENSION) AS COMPARED TO OTHERS AND FX 727-200 M/M 33-10-051-2. REMOVED AND REPLACED THE LANDING GEAR CONTROL PANEL MODULE IAW FX 727-200 M/M 25-10-052-4. LIGHT PRESS TO TEST OPERATES NORMAL.

Part: SOLENOID — FAULTY (COCKPIT) · airframe 40,541 hrs · 27,775 cycles

AFTER LIFTOFF LANDING GEAR HANDLE WOULD NOT RAISE ABOVE THE OFF POSITION. CREW WENT THROUGH APPROPRIATE RED TABS. COULD NOT FIX PROBLEM. RETURNED TO DEPARTURE AIRPORT. REPLACED L/G CONTL LEVER LOCK SOLENOID PER 727 MM 32-31-016-4. CYCLED GEAR SEVERAL TIMES, OP'S CHECKS OK.

Part: CONTROLLER — MALFUNCTIONED (CABIN PRESSURE)

ON CLIMBOUT, A/C WOULD NOT PRESSURIZE. INSPECTION PERF PRESSURIZATION CHECK, FWD ENTRY DOOR NORM, OPS NORM. OK FOR SERVICE.

Part: GASKET — LEAKING (LT WING)

NR 3 ENGINE STRUT O/H LIGHT ILLUM. REMOVED AND REPLACED LEAKING GASKET PER MP. LEAK AND OPS CHECK NORMAL.

Part: CONTROL VALVE — FAILED (CABIN PRESSURE)

AFT T/O CABIN PRESS DID NOT WORK, PSID NEVER WENT ABOVE 1 PSID. PERF RED TABS WITH BOTH AC PACKS ON ENG BLD 1 & 3 OPEN. CARGO HEAT OUTFLOW VALVE CLOSED. CABIN PRESS WAS 1000 FT LWR THAN AC ALTITUDE. *S/D* VERIFIED OUTFLOW VALVE, CARGO HEAT OUTFLOW VALVE OPERATION. SAFETY VALVES CLOSED. CK FOR LEAKS AND BLOWN DUCTS IN DISTRIBUTION BAY (NONE FOUND), NEG PRESS VALVE CK GOOD. REMOVED AND REPLACED RT FLOW CONTROL AND MODULATION VALVE AS PER MM 36-12-061. REMOVED GILLINER AND ADJUST HORZ PUSHROD PER IAW 52-11-001-5.

Part: LINE — LEAKING (OIL PRESSURE)

00-120 LOW OIL PRESS LIGHT ON NR 3 ENGINETHRUST LEVER TO IDLE. LOWER LINE TO DIFFERENTIAL PRESSURE SWITCH LEAKING. TIGHTENED LINE. INSTALL NEW OIL FILTER & SERVICED OIL QUANTITY PER 727 MM 79-00. NO LEAKS NOTED. AC OK TO CONTINUE.

Part: DOOR — MISSING (BS 846 - 870)

ON WALK-AROUND, AFT ARRIVAL FOUND AIR CONDITIONING ACCESS PNL 3454 MISSING. *S/D* REPLACED ACCESS PNL PER MM 53-50-00.

Part: MECHANISM — NOT LATCHED (L 1 DOOR)

A/C LOST PRESSURIZATION ON CLIMB-OUT FROM COS, NO LIGHTS ILLUM ON DOOR PANEL. A/C BLOCKED IN FOUND L1 DOOR AFT SECTION WAS IN 2 INCHES. FWD SECTION WAS FLUSH.

Part: SEAL — LEAKING (CABIN PRESSURE)

99-0017 - A/C WOULD NOT PRESSURIZE, NO LIGHTS ON PRESSURIZATION PANEL, LOUD NOISE IN BACK (SEAL). PRESSURIZED A/C PER JET RUN HANDBK 7-41 THROUGH 7-49 WITH APU ON GROUND PASSED TEST.

Part: LINE — SPLIT (A HYD SYST)

SYS-A HYD FAILURE 5 MIN AFTER T/O QUAN AND PRESS ZERO. FLUID SHUTOFF SWITCH CLOSED. FOUND HYD LINE SPLIT ON A-SYS PRESS TRANSMITTER. REMOVED AND REPLACED SAME. NOTED 1 GAL FLUID IN A-SYS SERVICE TO FULL, RAN BOTH NR 1 AND NR 2 ENG. ALL SYS OPER CK NORM. RESAFTIED FLUID SHUTOFF SWITCH'S. OK FOR SERVICE.

Part: SKIN — DAMAGED (BS 1183-1150)

HOLE CUT INTO FUSELAGE FOR REMOVAL AND INSTALLATION OF STR 29R, STR 29R FROM BS 1183 TO 1150 AND SPLICE. INSTALLED PER SRM 53-10-3, DOUBLER AND FILLER INSTALLED PER SRM 53-30-3.

Part: ANGLE — CRACKED (BS 1263)

AIR STAIR RT LWR TORQUE BOX INSIDE AT BS 1263 UPPER CHORD ANGLE CRACKED BELOW ACTUATOR AMOUNT. INSTALLED DOUBLER REPAIR PER EA 7-5310-29204.

Part: SKIN — CRACKED (BS 351)

FUSELAGE SKIN CRACKED AT AFT RIGHT CORNER OF NOSE W/W DRAG BRACE SHELF PANEL BS 351, STR 27R. INSTALLED DOUBLER PER SRM 53-30-3.

Part: SWITCH — INOPERATIVE (NR 5 LE FLAP)

AFTER A NORMAL T/O AND FLAP RETRACTION, WE LEVELED AT 5,000 FT AND LEADING EDGE DEVICE LIGHT CAME ON 2 DEGREE SHOWED NR 5 LED UNSAFE. WING ANTI-ICE ON CHECKLIST COMPLETION EXTINGUISHED LIGHT BUT IT CAME ON AGAIN SEVERAL TIMES NO STRUCTURAL LIMITS EXCEEDED. ANTI-ICE CYCLED ON AND OFF WITH NO RESULTS. REPLACED NR 5 L/E KRUEGER FLAP SWITCH. L/E FLAP INDICATION OPS CHECK SATISFACTORY ON GROUND TEST.