N397FE

Part: FIRE LOOP — FALSE INDICATION (NR 2 ENGINE) · airframe 81,592 hrs · 34,446 cycles

NR 2 ENGINE LOOP, A LEVEL 2 ON 10 MILE FINAL. POSSIBLE ENG FIRE. INSPECTED FAN, REVERSER AND TURBINE COWLS AND PERFORMED GVI OF NR 2 ENGINE. NO EVIDENCE OF FIRE OR PNUEMATIC DUCT LEAK. NO EVIDENCE OF DAMAGE TO FIRE LOOPS NOTED. NO EVIDENCE OF FIRE IN TAIL PIPE AS WELL. R & R NR 2 ENGINE "A" LOOP IAW AMM 26-11-02-4. OPS CHECKED GOOD IAW AMM 26-11-02-5.

Part: BULKHEAD — CRACKED (BS 1521) · airframe 80,801 hrs · 34,041 cycles

RT BULKHEAD HAS ONE CRACK 51 INCHES FWD OF BS 1521 AND 31 INCHES UP FROM BELLY SKIN. REPAIRED IAW SRM 53-00-01.

Part: BULKHEAD — CRACKED (BS 1381) · airframe 80,801 hrs · 34,041 cycles

INBD BULKHEAD ONE CRACK 14 INCHES AFT OF BS 1381 AND 14 INCHES DOWN FROM UPPER BULKHEAD. CRACK VERIFIED USING HFEC. REPAIRED THE DAMAGED TO THE RT SIDE WHEEL WELL BULKHEAD IAW EA 8-5310-157380.

Part: BULKHEAD — CRACKED (BS 1521) · airframe 80,801 hrs · 34,041 cycles

INBD BULKHEAD CRACKED 32 INCHES FWD OF BS 1521 AND 3 INCHES DOWN FROM UPPER BULKHEAD. REPAIRED IAW SRM 53-00-01, FIG 10.

Part: BULKHEAD — CRACKED (BS 1395) · airframe 80,801 hrs · 34,041 cycles

INBD BULKHEAD HAS TWO CRACKS 21 INCHES AFT OF BS 1381 AND 7 AND 9 INCHES DOWN FROM UPPER BULKHEAD. TWO CRACKS VERIFIED USING HFEC. COMPLETED REPAIR OF AREA USING EA 8-5310-157381 AND REPAIR SKETCH 201302130091-001 AS REF.

Part: BULKHEAD — CRACKED (BS 1381) · airframe 80,801 hrs · 34,041 cycles

LT BULKHEAD HAS THREE CRACKS 12 INCHES AFT OF BS 1381 AND 3 INCHES DOWN FROM UPPER BULKHEAD, AND ONE IS 13 INCHES AFT BS 1381 AND 3 INCHES DOWN, AND LAST CRACK IS 17 INCHES. AFT BS 1381 AND 3 INCHES DOWN. ALL THREE CRACKS HAVE BEEN VERIFIED USING HFEC. REPAIR TO BE ACCOMPLISHED ON EA 8-5310-157381.

Part: ANGLE — CORRODED (BS 595) · corrosion level 2 · airframe 80,666 hrs · 33,971 cycles

NR 3 ACM BAY FOUND THE ACA3796-2 TEE ANGLE CORRODED BEYOND LIMIT AT BS 585, LONGERON 47R. R & R TEE ANGLE IAW REF 51-33-00 AND 51-35-01, VOL II.

Part: TEE FITTING — CRACKED (BS 595 L43R) · airframe 80,666 hrs · 33,971 cycles

RT FWD PRESSURE BULKHEAD AT BS 595, RT LONGERON 43, FOUND CRACKED AT THE WEB AND TEE FITTING. SERVICABLE TEE FITTING INSTALLED IAW EA 8-5310-163797.

Part: COVER — BROKEN (EMERGENCY LIGHT) · airframe 79,756 hrs · 33,463 cycles

R1 DOOR LOWER FWD EXIT LIGHT COVER BROKEN. REPLACED LIGHT COVER. OK FOR SERVICE.

Part: POWER SUPPLY — DISCHARGED (EMERGENCY LIGHTS) · airframe 78,721 hrs · 32,933 cycles

DURING PREFLIGHT, OBSERVED EMGERENCY LIGHT BATTERY 1 LOW. REPLACED EMERGENCY LIGHTS POWER SUPPLY

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHT) · airframe 78,492 hrs · 32,814 cycles

DURING PRE FLIGHT GOT EMERGENCY LIGHT BATTERY LOW ALERT. R & R EMERGENCY LIGHT BATTERY IAW MM 33-51-01-4. OPS CHECKS NORMAL IAW MM 33-51-01-5.

Part: SWITCH — FAILED (ENGINE OIL) · airframe 77,939 hrs · 32,517 cycles

NR 2 ENG OIL FILTER LEVEL II ALERT. INFLT SHUT DOWN AS PER FLT CREW WITH LEVEL II ALERT, ENG HAD NORMAL OIL PRESSURE. INSPECTED FILTER ELEMENT FOR CLOGGING, ELEMENT FOUND CLEAN AND NOT CLOGGED. INSTALLED NEW FILTER ELEMENT AS PER MM 79, RAN ENG AS PER JRH, PERFORMED LEAK CHECK. INDICATION NORMAL AT IDLE & ACCELL. NO OIL FILTER LIGHT ON ENG. INSPECTION CK FOR WIND MILL AS PER M/M 72-00-00-6. CLOSED AND SECURED NR 2 PLATFROM AS PER M/M 53-00-00-2, NR2 COWLING CLOSED & INSPECTED AS PER MM 71-00-00-2. RII PLACING OIL FILTER BYPASS DETECTION SYSTEM INOP PRECAUTIONARY. C/W ENG.2 OIL FILTER INSPECTION PER MEL 79-30-1 A/C OK FOR SERVICE. RELEASED FOR SERVICE PER MEL: 79-30-01 R & R NR 2 OIL STRAINER CLOGGING SWITCH REF MD10 M.M. 79-35-01-2. LEAK CHECK NORMAL ENGINE RUN ALL INDICATIONS NORMAL.

Part: MANIFOLD — DIRTY (HYD SYSTEM) · airframe 76,406 hrs · 31,749 cycles

DURING DESCENT, LVL 1 HYD 3 ELEV OFF-NR3 HYD LEVEL AT 4.5 GALLONS. RAN CHECKLIST SHORTLY FOLLOWED BY HYD 3, QTY LO AND THEN HYD 3 FAIL SGN - REPLACED NR3 ENG HYD SYS MANIFOLD FILTERS IAW AMM 29-12-02-2, NO METAL OR DEBRIS FOUND IN OLD FILTERS. STILL REDQUIRES LK CK.

Part: WIRE — BROKEN (NR 3 MEC) · airframe 75,123 hrs · 31,149 cycles

NR 3 ENGINE HUNG START AT FL 25.0 AND DESCENDED TO 10000 FT STILL WOULD NOT ACCELERATE; SHUT DOWN ENGINE. IDLE READINGS: ENGINE 1 N1 38 PERCENT; EGT 362; N2 71.1 PERCENT, ENGINE 2 N1 39 PERCENT; EGT 362; N2 72.6 - ENGINE 3 N1 29 PERCENT; EGT 372; N2 50.5 PERCENT. REMOVED AND REPLACED THE NR 3 ENGINE MEC REF AMM 73-20-01-2. REPAIRED A BROKEN WIRE ON PLUG PL-8079 REF AMM 20-30-02-2. PERFORMED FLT IDLE ADJUSTMENT REF AMM 71-00-00-5. PERFORMED ENGINE RUN; LEAK AND BOPS CHECK GOOD.

Part: SKIN — DENTED (FUSELAGE) · airframe 75,122 hrs · 31,146 cycles

RT FUSELAGE AT STA 1776 BETWEEN LONGERONS 39R AND 40R THE SKIN IS DENTED. REPAIR SKIN IAW E.A. 8-5330-123532 TITLE (FUSELAGE DENT IN GROSS WEIGHT MOD DOUBLER AT STA 1816, L39R - L40R ). REMOVED AND REINSTALLED ACCESS PANELS IN THE PIT IAW SRM 57-31-01; VOL II.

Part: SLEEVE — DENTED (THRUST REVERSER) · airframe 75,122 hrs · 31,146 cycles

NR 2 ENGINE LEFT TRANSLATING COWL OUTER SKIN IS DENTED. REPAIRED NR 2 LEFT TRANSLATING SLEEVE/COWL OUTER SKIN BY DRILLING INJECTED HOLES AND INJECTING EA 934 ADHESIVE AND FILLING THE DENT WITH POTTING COMPOUND AND CURING IAW CF6-6 ENGINE MANUAL 78-00-32; REPAIR NR 06. PRIMED IAW CF6-6 ENGINE MANUAL 78-00-32; REPAIR NR 06. PAINTED IAW FEDEX DC/MD-10 SRM 51-21-02; VOL II.

Part: SOLENOID — DEFECTIVE (L1 DOOR) · airframe 75,122 hrs · 31,146 cycles

L-1 DOOR TORQUE TUBE SOLENOID NOT OPERATING PROPERLY. REMOVED AND REPLACED L-1 DOOR TORQUE TUBE SOLENOID AND ADJUSTED. OPS CHECKED GOOD IAW FEDEX MD 10 AMM 52-11-13-2 AND 52-11-00-5.

Part: SKIN — GOUGED (LT WING SLAT) · airframe 75,122 hrs · 31,146 cycles

LT WING INBD SLAT GOUGED OTBD TOP CORNER. REMOVED AND RE-INSTALLED THE LEFT NR 2 SLAT. BLENDED AREA IAW SRM 57-00-01; FIG 1-A; SHEET 3; PG 5; VOL I AND 57-55-01. FABRICATED SKIN AND SPLICE PLATES THEN INSTALLED RTEF SRM 57-10-00; VOL I; FIG 3-1. GAP CHECKS GOOD REF MD10-10 AMM 27-80-01-4.

Part: SPAR CAP — CRACKED (RT WING) · airframe 75,122 hrs · 31,146 cycles

APPROX 2.75 INCH CRACK EXISTS IN RT WING LOWER SPAR CAP (PSE 57.10.008 ) AT XORS = 411. CRACK RUNS FROM AFT EDGE OF SPAR CAP AFT TANG, FWD APPROX 1.625 INCH TO RADIUS, THEN UPWARDS AND INBOARD APPROX 1.125 INCH AND TERMINATES AT VERTICAL LEG FASTENER AT APPROX = 410.

Part: SPAR CAP — CRACKED (ZONE 600) · airframe 75,122 hrs · 31,146 cycles

APPROX 2.75 INCH CRACK EXISTS IN RT WING LOWER SPAR CAP (PSE 57.10.008) AT XORS = 411. CRACK RUNS FROM AFT EDGE OF SPAR CAP AFT TANG, FWD APPROX 1.625 INCH TO RADIUS, THEN UPWARDS AND INBOARD APPROX 1.125 INCH AND TERMINATES AT VERTICAL LEG FASTENER AT APPROX = 410. REPAIRED SPAR CAP AT XORS 411 IAW EA 8-5710-123520.

Part: STRINGER — CORRODED (BS 1401 S25) · airframe 41,219 hrs · 12,840 cycles

CENTER LANDING GEAR WHEEL WELL AT FS 1401 AND STRINGER 52 HAS CORROSION. REMOVED AND REPLACED FRAME IAW SRM 51-31-01. FABRICATED A NEW FRAME IAW DWG AEA 0273. ALODINED AND PRIMED IAW SRM 51-21-01. PART MARKED IAW GMM 7-0-1001.

Part: SKIN — WORN (NACELLE) · airframe 75,122 hrs · 31,146 cycles

AFT NACELLE, FIREWALL SEAL PLANE AT FS Y2166 AND LEFT SIDE OF THE TRAILING EDGE OF THE DIVERTER, HAS WORN SKIN.

Part: SKIN — WORN (ZONE 400) · airframe 75,122 hrs · 31,146 cycles

AFT NACELLE, FIREWALL SEAL PLANE AT FS Y2166 AND RIGHT SIDE OF THE TRAILING EDGE OF THE DIVERTER; HAS WORN SKIN AND IS CRACKED. REMOVED AND FABRICATED NEW SKIN SECTION IAW SRM 51-35-01 VOL II AND DWG AJC7415 REV BK, ALODINED AND PRIMED IAW SRM 51-21-01 VOL I PG1. INSTALLED NEW SKIN SECTION IAW SRM 51-35-01 VOL II PG 1 AND DWG AJC 7415 REV BK.

Part: SKIN — WORN (ZONE 400) · airframe 75,122 hrs · 31,146 cycles

AFT NACELLE, FIREWALL SEAL PLANE AT FS Y2166 AND LEFT SIDE OF THE TRAILING EDGE OF THE DIVERTER, HAS WORN SKIN. REPAIR WORN SKIN AREA IAW SRM 51-31-01; VOL II; PG 1; SRM 55-35-04; VOL III AND DWG AJC7415, REV "BK". ALODINED AND PRIMED IAW SRM 51-21-01; VOL II; PG 1. PART MARKED IAW GMM 7-0-1000. REMOVED AND RE-INSTALLED THE NR 2 STARTER DUCT; FLANGE AND LOWER ADAPTER RING REF AMM 80-11-01-2 AND 71-10-01-2. NO LEAKS NOTED.

Part: SKIN — CORRODED (BS 1501-1521) · airframe 75,122 hrs · 31,146 cycles

CENTER LANDING GEAR WHEEL WELL, FS 1501 TO FS 1521 AT STR R50 TO L48 HAS CORROSION AND BARE METAL. REMOVED CORROSION IAW SRM 51-21-01 PG. 28 VOL. II. ORIGINAL THICKNESS ON SKIN IS .125 IAW DWG AYB7030 REV E. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-01 PG. 6 VOL. I. CUTOUT DAMAGED SECTION OF SKIN. FABRICATED REPAIR DOUBLER, TRIPLER, FILLER, & INSTALLED FINAL E.A. TO BE ACCOMPLISHED ON FEDEX N/R N00465 EA 8-5330-123517 FUSE- UNDERWING CENTER BELLY SKIN CORROSION.

Part: SKIN — CORRODED (FUSELAGE) · airframe 75,122 hrs · 31,146 cycles

CENTER LANDING GEAR WHEEL WELL, FS 1481 TO FS 1501 BETWEEN STR R50 TO L49 HAS CORROSION ON SKIN. REMOVED CORROSION IAW SRM 51-21-01 PG 28 A VOL II. SKIN ORIG THICKNESS 0.125 IAW DWG AYB 7030; REV "E". REMAINING MATERIAL THICKNESS 0.090. MATERIAL REMOVED 0.035. FOUND TO BE OUT OF LIMITS; MORE THAN 20% MATERIAL LOSS IAW SRM 53-00-01 PG 6 VOL I. CUT OUT DAMAGED SKIN. FABRICATED REPAIR DOUBLER TRIPPLER, FILLER AND INSTALLED FROM IAW EA 8-5330-123517.

Part: FITTING — CORRODED (NR 4) · airframe 75,122 hrs · 31,146 cycles

MAIN CARGO DOOR LOWER JAMB NR 4 FITTING HAS CORROSION IN HOLES "A"; "B" AND "D". REMOVED & REPLACED AFA 7132-1 FITTING & REPAIRED THE LOWER JAMB IN REF TO DC/MD-10 SRM 53-50-00 FIG 17 VOL I & DC/MD-10 SRM 51-33-01 VOL II.

Part: FITTING — CORRODED (DOOR FRAME) · corrosion level 2 · airframe 75,122 hrs · 31,146 cycles

MAIN CARGO DOOR LOWER JAMB NR 3 FITTING HAS CORROSION IN HOLES "A" AND "D". REMOVED & REPLACED AFA 7132-1 FITTING & REPAIRED THE LOWER JAMB IN REF TO DC/MD-10 SRM 53-50-00 FIG 17 VOL I & DC/MD-10 SRM 51-33-01 VOL II.

Part: FITTING — CORRODED (NR 7) · corrosion level 2 · airframe 75,122 hrs · 31,146 cycles

MAIN CARGO DOOR LOWER JAMB NR 7 FITTING HAS CORROSION IN HOLES "A"; "C" AND "D". REMOVED & REPLACED AFA 7132-1 FITTING & REPAIRED THE LOWER JAMB IN REF TO DC/MD-10 SRM 53-50-00 FIG 17 VOL I & DC/MD-10 SRM 51-33-01 VOL II.

Part: FITTING — CORRODED (NR 6) · airframe 75,122 hrs · 31,146 cycles

MAIN CARGO DOOR LOWER JAMB NR 6 FITTING HAS CORROSION IN HOLES "A"; "B"; "C" AND "D". REMOVED & REPLACED AFA 7132-1 FITTING & REPAIRED THE LOWER JAMB IN REF TO DC/MD-10 SRM 53-50-00; FIG 17 VOL I & DC/MD-10 SRM 51-33-01 VOL II.

Part: FITTING — CORRODED (NR 5) · airframe 75,122 hrs · 31,146 cycles

MAIN CARGO DOOR LOWER JAMB NR 5 FITTING HAS CORROSION IN HOLES "C" AND "D". REMOVED & REPLACED AFA 7132-1 FITTING & REPAIRED THE LOWER JAMB IN REF TO DC/MD-10 SRM 53-50-00 FIG 17 VOL I & DC/MD-10 SRM 51-33-01 VOL II.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 75,122 hrs · 31,146 cycles

MAIN CARGO DOOR LOWER JAMB NR 2 FITTING HAS CORROSION IN HOLES "B" AND "C". REMOVED & REPLACED AFA 7131-1 FITTING & REPAIRED THE LOWER JAMB IN REF TO DC/MD-10 SRM 53-50-00 FIG 17 VOL I & DC/MD-10 SRM 51-33-01 VOL II.

Part: STRUCTURE — CORRODED (ZONE 100) · corrosion level 2 · airframe 75,122 hrs · 31,146 cycles

RT MLG W/W BS 1381 RBL 116 OTBD LOWER CORNER OF SLANT PANEL VERTICAL TEE CAP HAS CORROSION. DISPLACED SLANT PANEL IAW SRM 51-31-01; VOL I. REMOVED 7, REPLACED ANGLE IAW SRM 51-33-01; VOL II AND DWG NR AEA0471; REV "A". FABBED AND INSTALLED NEW ANGLE IAW DAC DWG NR AEA0471, REV "A". RE-INSTALLED SLANT PANEL IAW SRM 51-31-01; VOL I.

Part: WIRE HARNESS — OUT OF POSITION (LANDING GEAR) · airframe 73,761 hrs · 30,532 cycles

MAIN GEAR WOULD NOT RETRACT ON AFTER TAKEOFF CHECKLIST CYCLED GEAR AS PER QRH GEAR WENT DOWN 3 GREEN BUT MAIN GEAR STILL WOULD NOT RETRACT CONFIG PAGE CONFIRMED ALL THE ABOVE. FOUND LEFT AND RIGHT UPLATCH SENSOR WIRE HARNESS INTERFERING WITH TRAVEL OF LINK ASSY'S. REPOSITIONED HARNESSES. LG POSITION SYSTEM CHECKS GOOD REF MD10-10 MM 32-61-15-4. JACKED AC SWUNG GEAR SEVERAL TIMES, OPS CHECK AND INDICATION CHECKS GOOD PER MD 10-10 MM 32-60-00-5.

Part: WIRE HARNESS — OUT OF POSITION (LANDING GEAR) · airframe 73,761 hrs · 30,532 cycles

MAIN GEAR WOULD NOT RETRACT ON AFTER TAKEOFF CHECKLIST CYCLED GEAR AS PER QRH GEAR WENT DOWN 3 GREEN BUT MAIN GEAR STILL WOULD NOT RETRACT CONFIG PAGE CONFIRMED ALL THE ABOVE. FOUND LEFT AND RIGHT UPLATCH SENSOR WIRE HARNESS INTERFERING WITH TRAVEL OF LINK ASSY'S. REPOSITIONED HARNESSES, LG POSITION SYSTEM CHECKS GOOD REF MD10-10 MM 32-61-15-4. REPOSITIONED UPLATCH SENSOR HARNESS ROUTING AND GEAR SWING IAW MD-10-10 AMM 32-61-15-4. ALL OPERATION AND INDICATIONS CHECK S ARE GOOD.

Part: SKIN — CRACKED (ZONE 100) · airframe 72,818 hrs · 30,080 cycles

MODIFICATION AND REPAIR ASSESSMENT ON 13 APRIL 2007, DURING PNEUMATIC TESTS WITH AIR, AT 9:30 A.M. THE PRESSURIZED AIR FLEXIBLE HOSE COLLAPSED CAUSING THE END CONNECTING TO THE HANGAR UNDERFLOOR MANIFOLD TO HIT THE LOWER FUSELAGE JUST FWD OF C.A.C. THE IMPACT BETWEEN THE SDR DELETE BECAUSE FOR REPAIR ASSESSMENT NOT REQUIRED. REMOVED FASTENERS, PERFORMED STRIP PAINT, PENETRANT INSPECTION AND VISUAL INSPECTION. REMOVED RADIO ALTIMETER, PERFORMED CUT LONG 52. REPAIRED LONG 52 AND SKIN IAW SRM 53-10-00 FIG 1-2 AND SRM 53-20-00 FIG 6. INSTALLED RADIO ALTIMETER ANTENNA , AND FUNCTIONAL TEST IAW MM 34-42-03-4 AND DWG SP 10240167 AND MM 34-42-00-5.

Part: LONGERON — CRACKED (ZONE 700) · airframe 72,818 hrs · 30,080 cycles

ACF MODIFICATION AND REPAIR ASSESSMENT LT MLG WHEEL WELL: AT STA 1510, AT X = 30 FOUND LONG WITH CRACK THE 1 INCH ACCOMPLISHED CRACK STOP DRILL 1/4 '' DIA AND REPAIRED LONGERON IAW SRM 53-00-01 FIG 9 VOL I.

Part: SHEAR TIE — CORRODED (ZONE 100) · airframe 72,818 hrs · 30,080 cycles

MD 10-10 ACF MODIFICATION AND REPAIR ASSESSMENT AFT CARGO COMPARTMENT: MISSING MATERIAL AND CORROSION ON SHEAR CLIP STA 1956 B/T L 48 TO L 50 LT SIDE REMOVED CLIPS ATTACHING FOR ACCESS: REMOVED INTERCOSTAL AND RIVETS, CUT OUT SHEAR CLIP DAMAGED, CLEANED EXCESS OF SEALANT, TREATED AREA. REPAIRED SHEAR CLIP AND REINSTALLED ALL PARTS REMOVED FOR ACCESS AND PAINTED WITH HIGH IMPACT PAINT.

Part: LONGERON — DAMAGED (ZONE 100) · airframe 72,818 hrs · 30,080 cycles

ACF MODIFICATION AND REPAIR ASSESSMENT\AFT CARGO COMPT TUNNEL SIDE RT: STA 1801-1821 NICK ON THE LONGERON 27 PERFORMED BLEND-OUT AND CHECK LIMITS IAW SRM 53-00-01 FIG 1 B. INSTALLED ANGLE AND EXISTING STRAP IAW SRM 53-00-01 FIG 7 AND SRM 51-33-01 VOL. II. PROTECTED IAW SRM 51-21-01 VOL II.

Part: SKIN — DENTED (ZONE 300) · airframe 72,818 hrs · 30,080 cycles

ACF MODIFICATION AND REPAIR ASSESSMENT HORIZONTAL STABILIZER LT SIDE DENTS, NICKS, DEFORMATION RIB AND SKIN AND 10 EA RIVETS LOOSE ON LOWER SKIN B/T STA 48.500 TO STA XE 67.225 AND STA XE 88.625 TO STA XE 100.455. REMOVED DETACHABLE ELEVATOR , REMOVED LWR INB SKIN PANEL. PERFORMED INSPECTION ON RIBS AND LATCHING POINT. REPLACED INBD LWR SKIN PANEL, PERFORMED EA2 REPAIRS ON OUTBOARD LOWER PANEL. INSTALLED DETACHABLE ELEVATOR , APPLIED SEALANT ON L EDGE PANEL.

Part: SKIN — CRACKED (ZONE 600) · airframe 72,818 hrs · 30,080 cycles

MD 10-10 ACF MODIFICATION AND REPAIR ASSESTMENT RT WING LEADING EDGE STA XORS 506 LOWER SIDE CLOSE TO PANEL FUEL PANEL, SKIN WITH CRACK OF ABOUT 2 INCH REMOVED ACCESS DOOR, REPAIRED FIXED L.E IAW SRM 57-10-00 FIG 68 SHEETS 2 AND 3. INSTALLED ACCESS DOOR. PERFORMED CHECK AMM 27-30-06-06.

Part: FRAME — CORRODED (ZONE 100) · airframe 72,818 hrs · 30,080 cycles

ACF MODIFICATION AND REPAIR ASSESSMENT AFT FUSE WASTE TANK COMPT STA 1996 LT SIDE TO L. 50 FROM L. 52 REPAIR EXISTING WITH LIGHT CORROSION. REMOVED EXISTING REPAIR, PERFORMED INSPECTION, CUP ANGLE B/T L46 AND L48 RT SIDE AND B/T L 48 TO L 50 LT SIDE IAW SRM 53-30-00 FIG 5 VOL I. FABRICATED AND INSTALLED NEW CAP ANGLE AND SPLICES IAW SRM 53-30-00 FIG 5 VOL I.

Part: FRAME — CORRODED (ZONE 100) · airframe 72,818 hrs · 30,080 cycles

MD 10-10 ACF MODIFICATION AND REPAIR ASSESSMENT AFT FUSE WASTE TANK COMPT STA 1996 RT SIDE TO L 47 FROM L 50 REPAIR EXISTING WITH LIGHT CORROSION. PERFORMED REPAIR WITH NRC NR 1202.

Part: DOOR FRAME — CRACKED (BS 1305) · airframe 72,818 hrs · 30,080 cycles

MODIFICATION AND REPAIR ASSESSMENT R3 DOOR ON JAMB STA 1305 SIDE LOWER FOUND WEB WITH EXISTING REPAIR REMOVED EXISTING REPAIR NOT IN COMPLIANCE WITH SRM 53-50-00 FIG 19.

Part: SKIN — CRACKED (ZONE 600) · airframe 72,818 hrs · 30,080 cycles

MODIFICATION AND REPAIR ASSESTMENT RT WING INBOARD AILERON FRONT SPAR WITH EXISTING REPAIR STA XIA 372 TO 374 REMOVED DOUBLER (EXISTING REPAIR), FOUND CRACKS. REMOVED AILERON RT INBOARD. REPAIRED SKIN DOUBLER. INSTALLED FILLER AND COVER IAW MM 20-50-02. INSTALLED AILERON AND CHECKED IAW MM 27-10-01-4.

Part: SKIN — DAMAGED (ZONE 600) · airframe 72,818 hrs · 30,080 cycles

MODIFICATION AND REPAIR ASSESSMENT RT WING DROP LEADING EDGE WITH WORN AND MISSING MATERIAL ON EXISTING REPAIR. REMOVED INNER SKIN AND EXISTING REPAIR IAW SRM 51-31-01 VOL II. REPAIR DOUBLER, INSTALLED IAW SRM 57-10-00 FIG 55 VOL I. REINSTALLED HINGE, FWD ANGLE INNER SKIN.

Part: SKIN — DAMAGED (ZONE 600) · airframe 72,818 hrs · 30,080 cycles

DURING MD10-10 ACF MODIFICATION AND REPAIR ASSESSMENT RT WING INBOARD FLAP UPPER SIDE WITH EXISTING REPAIR STA XIFH 219.550 REPAIR CARRIED OUT IAW SRM 57-10-00 FIG 85.

Part: SKIN — DENTED (ZONE 100) · airframe 72,818 hrs · 30,080 cycles

DURING MD10-10 ACF MODIFICATION FOUND 3 DENTS ON EXTERNAL SKIN BETWEEN STA 1797 TO 1804 RT SIDE LONGERON 29 TO LONGERON 30, DENT 0.32" BY 2" BY 1" STA 1802 TO 1804, DENT 0.32" BY 1" BY .050" STA 1801, DENT 0.32" 1.80" BY 1" STA 1797 TO 1799. PERFORMED REPAIR FOR SRM 53-20-00 FIG 6 VOL. I.

Part: SKIN — CORRODED (ZONE 100) · airframe 72,818 hrs · 30,080 cycles

DURING MD10-10 ACF MODIFICATION AND REPAIR ASSESSMENT PROG EXISTING REPAIR ON SKIN STA 1039 RT SIDE BETWEEN L 50 TO L 51. REMOVED EXISTING REPAIR IAW SRM 51-35-01 VOL II . CUT DAMAGED SKIN AND REMOVED CORROSION. PERFORMED CHECK LIMITS AND TREATED IAW SRM 51-21-01 VOL II. REPAIRED SKIN IAW SRM 53-20-00 FIG 6 SH 3-4.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 72,818 hrs · 30,080 cycles

DURING MD10-10 ACF MODIFICATION AND REPAIR ASSESMENT PROG EXITING REPAIR ON EXTERNAL SKIN STA 603 TO STA 617 RT SIDE BETWEEN L 43 TO L 45. REMOVED OLD REPAIR (BECAUSE IS NOT COMPLIANCE WITH SRM 53-20-00 FIG 6) AND INSTALLED NEW REPAIR IAW SRM 53-20-00 FIG 6 VOL I.

Part: DOUBLER — NONE (ZONE 600) · airframe 72,818 hrs · 30,080 cycles

MODIFICATION AND REPAIR ASSESSMENT PROGRAM. FOUND 3 DOUBLER ON CENTER WS 1257 TO STA 1319 RT SIDE B/T XCW47 TO XCW81 DOUBLER INSTALLED PER P TO F MOD, REF DWG SM10570002 AND VSP0022 (SEE FAA FORM 307,DATED 26 JUNE 1998) SEE ENGINEERING RECOMENDED ACTION. THIS SDR NEEDS TO BE VOIDED DUE TO A NCR AGAINST THIS WO- ADMISTRATOR 06/15/07.

Part: DOUBLER — DAMAGED (CENTER WING) · airframe 72,818 hrs · 30,080 cycles

FOUND DOUBLER ON CENTER WING STA 1216 TO STA 1257 RT SIDE B/T XCW 47 TO XCW 81. DOUBLER INSTALLED PER P TO F MOD, EF DWG S110570002 AND VSP0022 SEE FAA FORM 337, DATED 26 JUNE 1998, SEE ENGINEERING RECOMMENDED ACTION.

Part: SKIN — MISREPAIRED (BS 1561) · airframe 72,818 hrs · 30,080 cycles

MD10-10 ACF MODIFICATION AND REPAIR ASSESTMENT DURING INSPECTION FOUND EXISTING REPAIR WITH MISSING SEALANT STA 1561 B/T L51 LT TO L 51 RT. REPAIR HAS BEEN ACCOMPLISHED IN COMPLIANCE WITH SRM 53-30-00 FIG 8. NO ACTION REQUIRED. REPAIRED SEALANT IAW SRM 51-41-01 VOL II.

Part: LONGERON — CRACKED (BS 1381-1441) · corrosion level 2 · airframe 72,818 hrs · 30,080 cycles

DURING INSPECT, FOUND CORROSION ON L30 B/T STA 1381 TO STA 1441 RT SIDE. REPAIRED LONGERON FITTING PER SRM 53-10-00 FIG 1 AND 2 VOL I.

Part: BULKHEAD — CRACKED (ZONE 100) · airframe 72,818 hrs · 30,080 cycles

DURING ACF MODIFICATION, FOUND TO AFT PRESSURE BULKHEAD AT STA 595 LONG 9 LT WITH CRACK 1". REPLACED LONGERON CLIP FOR SRM 51-31-01 VOL II.

Part: FLOORBEAM — CRACKED (ZONE 100) · airframe 72,818 hrs · 30,080 cycles

DURING ACF MODIFICATION, FOUND TO FWD CARGO COMPARTMENT BILGE STA 1090 FLOORBEAM WITH CRACK 2" LONG. REPLACE FLOORBEAM FOR SRM 51-31-01 VOIL II P/N AFA0039-5N E TEE ADA3645-15.

Part: SUPPORT — DAMAGED (ZONE 300) · airframe 72,818 hrs · 30,080 cycles

DURING ACF MODIFICATION , FOUND ON HORIZ STAB ON SUPPORT NOTED 1 HOLE OVALIZATION DIA, 0.2720" HOLE NOMINAL: 0.1870". REPAIRED FOR EA FEDEX 8-5340-97792 REV A DATE 02-02-07.

Part: STRUCTURE — CORRODED (WING) · airframe 72,818 hrs · 30,080 cycles

MD10-10 ACF MODIFICATION DURING BOLT REMOVAL E. FOR EO.8-5710-7-3314 PART 8 STEP 7 FOUND SEVERE CORROSION ON BOLT AND LIGHT CORROSION IN HOLE. REMOVED CORROSION FOR SRM 51 VOL.II CHECKED DIA HOLE IS IN LIMIT, PROTECT AREA. INSTALL SERVICEABLE BOLT FOR EO 8-5710-7-3314.

Part: STRUCTURE — CORRODED (WING) · airframe 72,818 hrs · 30,080 cycles

MD10-10 ACF MODIFICATION DURING BOLT REMOVAL, FOR EO.8-5710-7-3314 PART 8 STEP 7 FOUND SEVERE CORROSION ON BOLT AND LIGHT CORROSION IN HOLE. REMOVED CORROSION FOR SRM 51 VOL II CHECKED DIA HOLE IS IN LIMIT, PROTECT AREA INSTALL SERVICEABLE BOLT FOR EO 8-5710-7-3314.

Part: ENGINE — FIRE (NR 1) · airframe 70,976 hrs · 29,123 cycles

NR 1 ENG FIRE ON GROUND-LOUD BANG, FOLLOWED BY SMOKE, FOLLOWED BY NR 1 ENGINE FIRE WARNING ENGINE FIRE AND SEVERE QRH COMPLIED WITH AS WELL AS ALL APPLICABLE CHECKLISTS. NR 1 FIRE BOTTLE FIRED, NR 1 PACK ON-TEMP 38C GOOD FIRE TEST. REMOVED AND REPLACED NR 1 ENG PER MX WORKCARD 71T0701-1 RAN ENG PER JRH, OPS CHECKS AND LEAK CHECKS NORMAL.

Part: ROLLER — BROKEN (THRUST LEVER) · airframe 68,731 hrs · 27,918 cycles

GEAR UNSAFE HORN SOUNDED WHEN LEVER WAS RAISED ON T/O. HORN WAS SILENCED NORMALLY WITH THE GEAR HORN OFF BUTTON. THREE RED LIGHTS ON BOTH PANELS STAYED ON WITH HANDLE IN UP POSITION. GEAR WAS LOWERED AND 3 GREEN ANNUNCIATED. HYD PRESSURE & QUANTITY NORMAL. GEAR WAS RECYCLED WITH SAME RESULTS BUT NO HORN. JACKED A/C PER 07-11-00-2 DC-10-10 M/M SWUNG GEAR PER DC-10-10 M/M 32-30-00-5, WAS ABLE TO DUPLICATE. FOUND BROKEN ROLLER ON ACTUATOR FOR NR 3 THRUST LEVER LANDING GEAR WARNING HORN SWITCH. REPLACED ACTUATOR ON SWITCH S1-342, PER DC-10MM 76-11-04-2. CYCLED LANDING GEAR SEVERAL CYCLES, PER DC-10MM 32-30-00-5, ALL INDICATIONS NORMAL.

Part: HINGE FITTING — CORRODED (T/E FLAP) · airframe 68,310 hrs · 27,676 cycles

NR S 16 COMPLY WITH EA 8-5740-73852. WINGS INBD FLAP OUTBD HINGE SUPPORT FITTING TO WING ATTACH HOLES REWORK P/N ARC0154. COMPLIED WITH EA8-5740-73852.

Part: HINGE BRACKET — CORRODED (T/E FLAP) · airframe 68,205 hrs · 27,609 cycles

NR S 9 COMPLY WITH EA8-5750-73194. WINGS-RT IB FLAP-OB HINGE BRACKET, CORROSION REPAIR P/N ARC0154-2. CLOSING ACTION ON 10/22/03. COMPLIED WITH EA 8-5750-73194.

Part: RIB — GOUGED (RT WING) · airframe 68,205 hrs · 27,609 cycles

NR S 22 COMPLY WITH EA 8-5710-73203. REWORK OF GOUGES IN WING LEADING EDGE RIB. CLOSING ACTION ON 10/22/03. COMPLIED WITH EA 8-5710-73203.

Part: LINK — WORN (ZONE 600) · airframe 68,205 hrs · 27,609 cycles

SLATS NR 14 SLAT TRACK INBOARD LINK (RT WING) WEAR REWORK P/N ARB1468-2. COMPLIED WITH EA 8-5750-73213 WINGS - SLATS NR 14 SLAT TRACK INBOARD LINK (RT WING) WEAR REWORK P/N ARB 1468-2.

Part: SUPPORT BRACKET — CORRODED (LT TE FLAP) · airframe 68,205 hrs · 27,609 cycles

LT INBOARD FLAP INBOARD TRACK SUPPORT BRACKETS CORROSION. COMPLIED WITH EA 8-5750-7, WINGS - LT INBOARD FLAP INBOARD TRACK SUPPORT BRACKETS CORROSION REPAIRED.

Part: PANEL — CRACKED (ZONE 600) · airframe 68,205 hrs · 27,609 cycles

COMPLY WITH E.A.8-7830-73199. EXHUST SYSTEM-THURST REVERSER-FWD CRACK REPAIR. CLOSING ACTION ON 10/04/03.ON N/R S00017. COMPLIED WITH E.A.8-7830-73199.EXHAUST SYSTEM-THRUST REVERSER-FWD CLOSEOUT REPAIR.

Part: BRACKET — CORRODED (ZONE 600) · airframe 68,205 hrs · 27,609 cycles

RT IB FLAP TRACK MOUNT BRACKETS CORRODED ON FACES (3 OF 4 ). CLOSING ACTION ON 10/02/03.PN. N/R N01283. REMOVED CORRODED BRACKETS, FOUND WITHIN LIMITS IAW SRM 51-21-01, FAB NEW BUSHUINGS ON TRAVLER T2/370669 IAW EA8-5750-73196, INSTALLED NEW BUSHINGS IAW E.A.8-5750-73196. REWORKED AREAS ON N/R S00010. IAW E.A. 8-5750-73196.

Part: STUD — CORRODED (ZONE 500) · airframe 68,205 hrs · 27,609 cycles

LT WING OB FLAP IB 4 EACH FITTINGS ATTACH STUDS HAVE PITTING CORROSION AND FLAT THREATS. CLOSING ACTION ON 10/03/03.ON N/R N01201. REMOVED AND REPLACED LT FLAP MOUNT STUDS HINGES IAW M/M 57-41-01-2. ENCAPSULATED (2) BOTTOM MOUNT STUDS IAW M/M 57-41- 01-2, AND E.A 8-5750-72304.

Part: BRACKET — CORRODED (ZONE 600) · airframe 68,205 hrs · 27,609 cycles

COMPLY WITH E.A.8-5750-73196. WINGS-RT IB REWORK OF 3EA FLAP TRACK ATTACH BRACKETS. CLOSING ACTION ON 10/02/03. ON N/R S00010.COMPLIED WITH E.A.8-5750-73196.WINGS-RT, IB FLAP REWORK OF 3EA FLAP TRACK ATTACH BRACKETS.

Part: HINGE — CORRODED (RT TE FLAP) · airframe 68,205 hrs · 27,609 cycles

RT OB FLAP, IB HINGE FITTING MOUNT STUD BORES AND FACES (ON FITTING) CORRODED FACT 26SEP03 21:39 BFM U REWORKED BORES AND FACES, FOUND TO BE WITHIN LIMITS IAW CMM 57-44-08 AT BFM/MAE.

Part: WIRE — CORRODED (PACK DOOR) · airframe 67,942 hrs · 27,484 cycles

ON CLIMBOUT PASSING FL280 (AIR COND DOORS) LIGHT ILLUMINATED INTERMITTENTLY, WENT OUT AT 16000 FEET ON DESCENT. PRESSURIZATION REMAINED ON SCHEDULE ENT BY: 308389 RPT BY: 061284 FACT 18JUL03 12:26 STL R FOUND LT AFT PACK DOOR SWITCH WIRES CORRODED AND BROKEN AT CONNECTOR P1-1618. REPLACED CONNECTOR SWP 20-31. OPS CHECK NORMAL IAW M/M 52-70-07-2 RII:131618 ENT BY: 308389 RPT BY: 308389

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 65,875 hrs · 26,498 cycles

N 540, 542, 544, 547, 551 CORROSION ON MAIN CABIN FLOOR PANELS. REMOVED AND REPLACED PANELS.

Part: ATTACH FITTING — CRACKED (CARGO DOOR) · airframe 65,875 hrs · 26,498 cycles

CENTER CARGO DOOR SNUBBER ATTACH ARM CRACKED. REMOVED SNUBBER PER MM 52-32-07-2.

Part: ACTUATOR — LEAKING (RUDDER) · airframe 65,428 hrs · 26,277 cycles

AT CRUISE NR 2 HYD QTY LEAKING. REMOVED AND REPLACED LOWER RUDDER ACTUATOR PER MM 27-23-01-4.

Part: STRUCTURE — VIBRATION (FUSELAGE) · airframe 59,540 hrs · 23,501 cycles

AFTER T/O PASSING 235 KTS & CLIMBING THROUGH APPROX 4000 FT ACFT BEGAN TO VIB WITH LOUD NOISE COMING FROM BELOW & AFT OF PILOT SEATS. PACKS TURNED OFF, NO HELP. THROTTLES BACK TO IDLE, NO HELP. FLAPS DOWN TO 22 GEAR DOWN 210 KTS, NO HELP. GEAR UP 180 KTS, VIB WENT AWAY.

Part: SWITCH — INOPERATIVE (NR 1 ENGINE)

NR 1 REVERSER UNLOCK LIGHT ILLUM. TAB PROC WERE COMPLIED WITH RESULTING IN ENG SHUTDOWN. REMOVED AND REPLACED NR 1 ENG RIGHT REV STOW SWITCH PER MM 78-34-02-2, OPS CK NORMAL.

Part: GUIDE VANE — MISSING (RT TE FLAP)

98-220, RT INBD FLAP OUTBD FLAP GUIDE VANE STOP MISSING. INSTALL GUIDE VANE STOP AND ADJUST PER M/M 27-50-03-2 PG 205. CK FLAP (INBD) FOR DAMAGE NONE NOTED. RETURN TO SERVICE.