N310FE

Part: HANDLE — DIRTY (MLG) · airframe 51,850 hrs · 16,120 cycles

PUT GEAR DOWN AND HAD 4 RED LIGHTS, PUSHED ANTI-SKID TEST AND ANTI-SKID LIGHTS REMAINED BLANK.RAISED GEA R AND LOWERED GOT 4 GREEN AND ANTI-SKID TESTED.SUSPR CT THE SWITCH WHEN THE GEAR HANDLE IS PUSHED IN, DURING PREFLT CHECKS IT WAS STICKY. JACKED ACFT AND COMPLETED GEAR SWING. FOUND THAT HANDLE SWITCH WAS STICKING OUT CAUSING RED LIGHTS TO STAY ON WITH HANDLE IN THE DOWN POSITION. ALSO CAUSES THE ANTI SKID NOT TO TEST (UNTIL HANDLE PUSHED ALL THE WAY IN. CLEANED HANDLE RELEASE MECHANISM REF. AMM DC10-32-31-02-7. NOW OPS CK'S GOOD ON GEAR SWING.

Part: DUCT — RUPTURED (NR 2 ENGINE) · airframe 51,246 hrs · 15,856 cycles

T/O AT SJC NR 2 THROTTLE MUCH FURTHER FWD THAN 1 AND 3 EGT NR 2 CREEPING UP, MAX TEMP = 880' C PULLED NR 2 THROTTLE BACK EVEN W/ 1 AND 3 GOT FIRE WARN, THROTTLE IDLE. SHUT DOWN ENGINE, FIRED BOTTLE NR 1 AS A PRECAUTION. DIVERT TO KOAK. DURING T/O N2 FOR ALL THREE MOTORS WERE APPROX. THE SAME FUEL FLOW ON NR 2 SLIGHTLY HIGHER THAN 1 AND 3. DUMPED FUEL. FOUND T-DUCT AT NR 2 ENGINE HI PRESS BLEED VALVE RUPTURED. REPLACED DUCT, HPBV AND HARNESS, FAV AND HARNESS, HPBV AND FAV SENSE AND RIGID LINES, SUPPORT RODS FOR DUCTING, LT THRUST REVERSER COOLING MANIFOLD, REPAIRED LT CORE COWL BLOW OUT DOOR. AIRCRAFT RETURNED TO SERVICE.

Part: HOSE — TORN (CARGO BAY) · airframe 50,283 hrs · 15,420 cycles

THE MANIFOLD FAILURE NR 1 & 2 LIGHTS ILLUMINATED. T/S PER DC-10 TAFI 36-23-00 FAULT CODE BD AND BE. THE 1 & 2 MANIFOLD FAIL LIGHTS WOULD ILLUMINATE WITH NO MANIFOLD PRESS. FOUND LOOPS 1A D1-44D AND 1B D1-38D SHORTED. REMOVED AND REPLACED LOOPS IAW DC-10-30 AMM 36-23-02-4. CHECK GOOD. FOUND HOSE TO FWD CARGO HEAT VALVE TORN AND LEAKING. REPLACED HOSE IAW SMP. PRESSURIZED 1 AND 2 MANIFOLDS, NO LEAKS NOTED. GROUND RAN NR 1 AND NR 2 ENG IAW DC- 10 JRH CHAPT 5 AND HAD EACH ENG PRESSURIZING ITS RESPECTIVE MANIFOLDS NO FAILURE MESSAGES APPEARED. AIRCRAFT HAS SUBSEQUENTLY FLOWN WITH NO FAULTS.

Part: DUCT — CHAFED (7TH STAGE) · airframe 49,085 hrs · 14,962 cycles

NR 1 ENG HIGH PRESSURE CONTROL VALVE CHAFING INTO 7TH STAGE AIR PRESSURE TURBINE CONTROL LINE. REMOVED 7TH STAGE COOLING TUBE, PER DC10-30 MM 75-22-00-02. REPAIRED DUCT PER EM 72-09-03. REINSTALLED DUCT AND HIGH PRESSURE VALVE. PERFORMED OPS AND LEAK CHECKS GOOD PER DC10-30 JET RUN HANDBOOK.

Part: PULLEY BRACKET — CHAFED (BS 395) · airframe 49,085 hrs · 14,962 cycles

PILOTS AILERON CONTROL CABLE RUN NR 1 CHAFED INTO PULLEY BRACKET AT FS 395 LBL 30, 8 INCHES FROM BOTTOM FLOOR. PULLEY BRACKET REMOVED AND REPLACED IAW DC10-30 SRM 51-31-01 VOL 11. AILERON RIG PINS P-67 AND P-70 VERIFIED GOOD AND AILERON MECHANICAL TEST GOOD IAW DC10-30 MM 27-10-02-5.

Part: FRAME — CRACKED (BULKHEAD) · airframe 49,085 hrs · 14,962 cycles

NR 1 ENG NOSE INLET COWL INTERIOR AFT BULKHEAD CHORD ANGLE IS CRACK AT 7 O`CLOCK POSITION CAN BE VIEWED FROM OUTBOARED SIDE. REMOVED AND REPAIRED CRACKED CHORD ANGLE IAW DC10 SRM 54-11-00, FIG 1C VOL 1. N/R # N00405, W/O NR 00030375.

Part: FRAME — CRACKED (NR 1 INLET COWL) · airframe 49,085 hrs · 14,962 cycles

NR 1 ENG NOSE INLET COWL INTERIOR AFT BULKHEAD CHORD ANGLE IS CRACK AT 7 O`CLOCK POSITION CAN BE VIEWED FROM OUTBOARD SIDE. REMOVED AND REPAIRED CRACKED CHORD ANGLE IAW DC10 SRM 54-11-00 FIG 1C VOL 1. N/R N00405, W/O N/R 00030375.

Part: SUPPORT — CRACKED (ZONE 200) · airframe 49,085 hrs · 14,962 cycles

FLOOR PANEL SUPPORTS AT STA 999 AND 1019 RBL 45 ARE CRACKED (2 EA). REMOVED, FABRICATED NEW FLOOR SUPPORT IAW DAC DRAWING NR ACA3763 REV H AND FEDEX GMM 7-0-1000, SEE FEDEX NONROUTINE N00734 OF WORK ORDER NR 0003075.

Part: FLOOR PANEL — CORRODED (ZONE 100) · airframe 49,085 hrs · 14,962 cycles

CENTER LOWER CARGO COMPT FLOOR PNL 183ZF HAS BROKE AND CORRODED INSERTS STA 1781 TO 1821 RBL 30 TO37. REMOVED AND REPLACED INSERTS IAW FEDEX DWG SRA 25-005 REV E.

Part: SUPPORT ANGLE — CRACKED (NACELLE) · airframe 49,085 hrs · 14,962 cycles

NR 1 ENG NOSE COWL AFT SIDE LOWER SUPPORT WEB ANGLE FOR STARTER VALVE WAS CRACKED. REMOVED CRACK SUPPORT ANGLE FROM NR 1 ENGINE AFT SIDE OF AFT BULKHEAD NOSE COWL IAW DC10 SRM 51-31-01 VOL 11. LOCATED AND DRILLED NEW SUPPORT ANGLE IAW DC10 SRM 51-31-01 VOL 11. INSTALLED NEW ANGLE IAW DC10 SRM 51-35-01 VOL11.

Part: ANGLE — CRACKED (BS 1781) · airframe 49,085 hrs · 14,962 cycles

CTR CARGO COMPT ANGLE CRACKED AND BENT AT TOP AFT CORNER OF DOOR CUT-OUT FS 1781 LONG 29R. REMOVED ANGLE IAW DC10 SRM 51-35-01 VOL 11. MATERIAL ID FOUND TO BE 2024-T3 IAW ASTME 1476 .050 IAW CALIPER NR E110484B. FAB`D AND PART MARKED IAW FED EX GMM 7-0-1001. INSTALL IAW DC10 SRM 51-35-01 VOL 11.

Part: SPAR — CRACKED (ZONE 600) · airframe 49,085 hrs · 14,962 cycles

RT WING, TRAILING EDGE HAS A TWO INCH LONG CRACK IN FITTING AT XORS, 14 INCHES AFT OF INNER REAR SPAR. REMOVED AND REPLACED SUPPORT FITTING ARCO472-42, ( PO# 509448.1) IAW DC10-30 SRM 51-33-01 VOLII. TIMCO MECHANIC 7921, QC INSPECTOR #QC35.

Part: SKIN — DENTED (RT WING LE FLAP) · airframe 49,085 hrs · 14,962 cycles

RT WING O/B FLAP LOWER O/B SURFACES HAS DENTS. FOUND DENTS AT X0F 775-781 TO BE WITHIN ALLOWABLE LIMITS IAW DC10 SRM 57-10-00 FIG 48 VOL 1. FOUND DENT AT X0F 783-787 TO BE OUT OF LIMITS IAW DC10 SRM 57-10-00 FIG 48 VOL1. REMOVED DAMAGE AND INSTALLED REPAIR DOUBLER AND FILLER, MAT'L ID 2024-T3 .050 PO#505741.2 AND SHIMMED IAW DC10 SRM 57-10-00 FIG 85 VOL1. ALODINED AND PRIMED IAW DC10 SRM 51-21-01 VOL 11 AND DC10 SRM 51-41-01 VOL.2.

Part: SKIN — DENTED (ZONE 500) · airframe 49,085 hrs · 14,962 cycles

LEFT WING OUTBOARD FLAP HAS DENTS 4 PLACES. DENTS AT XOF657, 639, AND 611 FOUND TO BE WITHIN LIMITS IAW DC10 SRM 57-10-00 FIG 48 VOL I. REPAIRED DENT AT XOF 516 IAW DC10 SRM 57-10-00 FIG 85 VOL I. SEE FEDEX NONROUTINE NR N00229 OF WORK ORDER 0030375.

Part: SEAT TRACK — WORN (ZONE 100) · airframe 49,085 hrs · 14,962 cycles

MAIN CABIN STA 938 RBL 47.5 SEAT TRACK WORN, BLENDED AREA IAW DC10 SRM 53-70-00 VOL1 AREA HAS 50 PERCENT MAT'L LOSS AREA IS OUT OF LIMITS. MAT'L ID FOR NEW SEAT TRACK SECTION 54929150-1200 PO NR 502938.1 IAW DC10 SRM 53-42-01 VOL II. FABRICATED SEAT TRACK SECTION IAW DC10 SRM 53-70-00 FIG 1 VOL1 ALODINED AND PRIMED IAW DC10 SRM 51-21-01 VOL I. INSTALLED NEW SEAT TRACK SECTION IAW DC10 SRM 51-31-01 VOL II. REMOVED AND REINSTALLED FLOORBOARDS IAW DC10-30 AMM 53-21-01-2 N/R N00446 WORK ORDER 00030375.

Part: ANGLE — CRACKED (ZONE 800) · airframe 49,085 hrs · 14,962 cycles

FOUND FWD LOWER CARGO DOOR FRAME AT FWD HINGE POINT ANGLE CRACKED. REMOVED AND REPLACED ANGLE IAW DC-10 SRM 51-33-01 VOL II MATERIAL ID 2024-T3 .040 BOEING DWG ADA 7118, PO 504475.2 FABED IAW DWG ADA 7118 PART MARKED IAW FEDEX GMM 7-0-1000.

Part: SKIN — DENTED (ZONE 500) · airframe 49,085 hrs · 14,962 cycles

LEFT WING INBD FLAP LOWER SKIN HAS SMALL DENTS. CHECKED DENT LIMITS IAW DC10 SRM 57-10-00 FIG 48 VOL I. FOUND TWO DENTS OUT OF LIMITS. REPAIRED DENTS AT XIFH 230-231 AND XIFH 278-280 IAW DC10 SRM 57-10-00 FIG 85 VOLI.

Part: SKIN — DENTED (ZONE 600) · airframe 49,085 hrs · 14,962 cycles

RIGHT WING INBOARD FLAP HAS SPEED TAPE (LINE REPAIR) AFT OF NR 7 TIRE. REMOVED TEMP REPAIR AND REPAIRED SKIN IAW DC10 SRM 57-10-00 VOL I AND FEDEX EA 8-5750-91110 PART 3. P3 MOD TYPE T MOD REV NO A PS P3. EA IS ATTACHED TO WORK CARD 57501429, WORK ORDER 00030375, WRI 57501429. SEE NONROUTINE N00149 OF WORK ORDER 00030375.

Part: SKIN — CORRODED (CENTER WING) · airframe 45,330 hrs · 13,694 cycles

EXFOLIATING CORROSION ON TOP OF CENTER WING AT STA 1331, LBL 97.0 ON AN AREA OF APPROXIMATELY 6 X 8 INCH. REMOVED ALL EVIDENCE OF CORROSION. INSTALLED FILLERS AND DOUBLERS AS PER EA 8-5730-74212-WING UPPER AFT SKIN PANEL, CENTER BOX-CORROSION.

Part: SUPPORT — DAMAGED (FUSELAGE) · airframe 45,096 hrs · 13,607 cycles

STRUCTURE DAMAGE TO FORWARD SHUTTLE LOAD BAR TRANSMISSION SUPPORT AND ATTACHING FLOORBEAM STRUCTURE AT FUS. STA 879. REPAIRED LOWER FLOOR BEAM STA.879 AS PER SRM53-60-01 FIGUARE 3 AND AND EA 8-5310- 71818.REF WORD CARD SEQ0005.

Part: ENGINE — FAILED (NR 1) · airframe 44,523 hrs · 13,425 cycles

AT LEVEL OFF FL 330 EXPERIENCED HARD THUMP FOLLOWED BY GRINDING VIBRATION. IMMEDIATELY SHUT NR 1 DOWN. FOLLOWED QRH PROCEDURES, LANDED KPHX. PHX U C/W MD10-30 WORK CARD 71T0101-1, AND 71T0701-1.

Part: DOOR — CRACKED (RT MLG)

ON GEAR RETRACT RT MLG IND UNSAFE ON BOTH PANELS. REMOVED AND REPLACED MAIN GEAR DOOR PER AMM 32-14-01-2.

Part: PRESSURE PANEL — CORRODED (FUSELAGE) · airframe 39,018 hrs · 11,684 cycles

CTR WHEEL WELL, LT SIDEWALL, LWR FWD CORNER, CORROSION UNDER SEALANT, AROUND ACCESS PNL.

Part: PUMP — FAILED (FUEL SYSTEM)

LOST NR 2 LT AND NR 2 RT AND NR 3 AFT TANK PUMPS. REMOVED AND REPLACED LT AFT FUEL BOOST PUMP. OPS CK NORM PER MM. CK WIRING TO ALL 3 PUMPS NO FAULT FOUND. ALL PUMPS OPS NORMAL.

Part: HANDLE — MISSING (MID CARGO BAY)

ON WALK-AROUND FOUND CTR LWR CARGO VENT PANEL HANDLE ACCESS MISSING. INSTALLED VENT PANEL HANDLE ACCESS DOOR PER STANDARD PRACTICE, OPS CK GOOD.

Part: WARNING LIGHT — ILLUMINATED (COCKPIT)

NR 3 PNEUMATIC FAIL LIGHT ILLUM. COMPLETED RED TABS.

Part: SEAT TRACK — CRACKED (BS 635&755)

MAIN DECK UPPER CARGO, SEAT TRACK CRACKED AT BS 635 X=27.5-242. UPPER CARGO SEAT CRACK AT BS Y=755 INTERSECTING X=8.5. *S/D* REPAIRED MDUC PER SRM 53-70-00 VOL 1-242 & UCST PER SRM 53-70-00 VOL 1-243.

Part: SKIN — CRACKED (WS 402)

RT WING LOWER SURFACE OF LEADING EDGE ALONG XORS 402 FOUND WITH 2 INCH CRACK. *S/D* REPAIR CARRIED OUT PER SRM 57-10-00 FIG 68 VOL 1.

Part: TR COWL — DEPARTED (NR 2 ENGINE)

NR 2 ENGINE THRUST REVERSER TRANSLATING COWL DEPARTED THE A/C ON LANDING. *S/D* REMOVED AND REPLACED NR 2 RT T/R FAN IAW MM 78-32-11-2.

Part: LIGHT — INOPERATIVE (AC DOOR)

IN CRUISE FLT LEVEL 370, AIR COND DOOR LIGHT ILLUM. CONSULT RED TABS, RETURNED TO ANC. DOOR LIGHT WENT OUT AT 6.5 PSI. BEG TO BLINK WHEN INCREASE PSI AT 7.0 PSI. A/C RELEASED PER MEL 52-4D. A/C COND DOOR CAUTION LIGHT INOP. C/W MSP 52-4C, DOORS ARE VERIFIED CLOSED AND LOCKED.

Part: FIRE BOTTLE — MALFUNCTION (NR 2 ENGINE)

AFTER TAKEOFF, AGENT LOW LIGHT ILLUMINATED ON NR 2 ENGINE. FLIGHT RETURNED TO SFS AND LANDED WITHOUT INCIDENT. REMOVED AND REPLACED NR 2 ENGINE, NR 1 FIRE BOTTLE AND SQUIBS.

Part: PROX SENSOR — DEFECTIVE (LT MLG)

LT MAIN IND UNSAFE, BOTH PANELS WITH GEAR HANDLE UP. INITIALLY GEAR WENT UP SAFE, BUT AFTER ABOUT 5 SECONDS THE RED LIGHT CAME BACK ON, THIS OCCURRED ON TWO OCCASIONS. FOUND LT/MLG DOWN LOCK SENSOR WIRES DEFECTIVE. REMOVED AND REPLACED POSITION PROXIMITY SENSOR AND CONDUIT PER 32-61-03, CK'D SYS PER TAFI 32-30-00, CK'S OK.

Part: SKIN — LIGHTNING STRIKE (RUDDER TAB)

LIGHTNING STRIKE, TOP OF UPPER RUDDER TAB RT SIDE, APPROX .25 INCH HOLE BURNED THROUGH ALUMINUM SKIN. FABRICATED DOUBLER PER SRM 55-00-01, WEIGHT CHANGE PLUS 1.502. RESTAMPED PLACARD TO ACTUAL WT OF RUDDER AS REQ SRM 55-40-02, PRIMED AND PAINTED PER SRM 51-21-02.

Part: FITTING — WORN (LT ELEVATOR)

LT DETACHABLE ELEVATOR, AFT BAYONET LATCH ASSY LOOSE IN FITTING, WORN C/W SB 55-9 AND EA NR 8-5520-25165. OPEN SKIN, REPLACED FITTINGS AND LATCHES. SKIN AND PANELS OPS CHECK OK.

Part: FITTING — LOOSE (RT TE FLAP)

RT WING O/B FLAP I/B SUPPORT FITTING TO REAR SPAR IS SUSPECTED LOOSE, MEASURED GAP 0.003. REMOVED O/B FLAP AND INSPECTED SUPT FITTING HOLES FOR CRACKS, NO DEFECTS NOTED. INSTALLED NEW STUDS AND PLI WASHERS AS PER MM 20-20-01 PG 202. REINSTALLED FLAP, FITTINGS AND SEALED.

Part: FITTING — WORN (RT ELEVATOR)

RT DETACHABLE ELEVATOR'S BAYONET LATCHES ARE LOOSE, WORN FITTINGS C/W S/B 55-9 AND EA NR 8-5520-25164. REPLACED FITTINGS AND LATCHES, OPENED AND CLOSED SKIN AND SEAL EDGES. ELEV OPS CHECK OK.

Part: FRAME — CRACKED (CTR GEAR DOOR)

LT CENTER GEAR DOOR, 2 INCH CRACK AT FWD I/B FRAME. REMOVED AND REPLACED DAMAGED FRAME AS PER SRM 51-00-00 PG 2 ITEM C.

Part: FRAME — CRACKED (CTR GEAR DOOR)

RT CENTER GEAR DOOR, 2 INCH CRACK AT FWD I/B FRAME. REMOVED AND REPLACED DAMAGED FRAME AS PER SRM 51-00-00 PG 2 ITEM C.