N467FE

Part: SLIDE — DISLODGED (DOOR) · airframe 52,786 hrs · 37,507 cycles

ESCAPE SLIDE FELL OUT OF DOOR CONTAINER DURING FLIGHT/LANDING. R & R ESCAPE SLIDE AND HARDCASE IAW MM 25-60-015-2.

Part: SLIDE — DISLODGED (L1 DOOR) · airframe 52,776 hrs · 37,498 cycles

MAIN DOOR SLIDE FELL OUT OF HOUSING UNIT. REINSTALLED L1 ESCAPE SLIDE IN AMM 25-60-015-2. ACFT OK FOR SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 52,761 hrs · 37,485 cycles

WHEN DOOR SLIDE FELL OUT, EMERGENCY DOOR LIGHT ILLUMINATION WAS VERY DIM, R & R EMERGENCY ECAPE SLIDE LIGHT BATTERY PACK IAW AMM 33-50-121-2. OPS CHECKED GOOD. OK FOR SERVICE.

Part: SLIDE — DISLODGED · airframe 52,761 hrs · 37,485 cycles

WHEN ENTRY DOOR OPENED, GIRT BAR CAUGHT DOOR FRAME AND PULLED OUT EMERGENCY EXIT SLIDE PACK OUT OF UNIT. REMOVE DOOR SLIDE AND INSPECTED AND REINSTALLED PACK AMM 25-60-015-2. NO DEFECTS NOTED.

Part: GAUGE — OUT OF POSITION (ESCAPE SLIDE) · airframe 52,686 hrs · 37,420 cycles

ON PREFLIGHT, COULD NOT SEE THE PRESSURE GAUGE ON THE ESCAPE SLIDE. REPOSITIOND SLIDE PACK IN DOOR CONTAINER SO THAT AIR BOTTLE PRESSURE GAUGE IS VISIBLE THROUGH INSPECTION WINDOW IAW MM 25-60-015-2. ACFT OK FOR SERVICE.

Part: GAUGE — OUT OF POSITION (ESCAPE SLIDE) · airframe 52,686 hrs · 37,420 cycles

ON PREFLIGHT, COULD NOT SEE THE PRESSURE GAUGE ON THE ESCAPE SLIDE. REPOSITIONED SLIDE PACK IN DOOR CONTAINER SO THAT PRESSURE GAUGE IS VISIBLE THROUGH INSPECTION WINDOW PER MM 25-60-015-2. OK FOR SERVICE.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHT) · airframe 52,439 hrs · 37,211 cycles

FOUND EMERGENCY ESCAPE SLIDE LIGHT INOP. R & R EMERGENCY ESCAPE SLIDE LIGHT BATTERY. OPS NORMAL REF 33-50-121-2-0 OK FOR SERVICE. REMOVED AND REPLACED EMERGENCY ESCAPE SLIDE LIGHT BATTERY. OPS NORMAL REF 33-50-121-2-0. OK FOR SERVICE, CLOSED.

Part: GROUND WIRE — BROKEN (OIL TEMP) · airframe 52,417 hrs · 37,190 cycles

NR3 OIL TEMP INDICATOR BOUNCING AROUND, SUSPECT ERRONEOUS INDICATION. CHECKED GROUND AT SENSOR END FOUND NO GROUND, PUSHED BACK PIN B OF CONNECTOR, THE GROUND WIRE FELL OFF WHEN PIN EXTRACTED. TROUBLESHOT IAW WDM 79-33-01. R & R CONNECTOR D530. RAN NR 3 ENGINE PER JRH. OPS CHECKED GOOD. ACFT OK FOR SERVICE.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 52,363 hrs · 37,138 cycles

EMERGENCY EXIT LIGHT ABOVE L1 DOOR INOPERATIVE WHEN EMERGENCY LIGHTING SYS TURNED ON. R & R EMERGENCY EXIT LIGHT OVER CREW DOOR IAW AMM 33-50-101-2-0. FUNCTION CHECKS GOOD. OK FOR SERVICE. R/I FROM FACT PREMATURE REMOVAL/INSTALLATION.

Part: SOCKET — LOOSE (EMERGENCY LIGHT) · airframe 52,214 hrs · 37,011 cycles

EMERGENCY EXIT LIGHTS INOP. FOUND COCKPIT EMERGENCY LIGHT LOOSE IN FIXTURE. RESEATED EMERGENCY LIGHT. OPS CHECK GOOD. FINAL CLOSED

Part: STRUCTURE — CRACKED (LT WING TE FLAP) · airframe 51,945 hrs · 36,785 cycles

LEFT WING, I/B FLAP, MID FLAP T/E LWR CHORD HAS A CRACK , O/B OF NO. 4 FLAP TRACK. REMOVED CRACKED T/E LOWER CHORD SECTION DIM 69 1/2" IN LENGTH IAW SRM 51-30-2 LOCATED AND DRILLED NEW CHORD SECTION FROM BAC1503-100046 7075 T6 DIM 69 1/2" IN LENGTH IAW SRM 57-50-2 AND 51-30-5 INSTALLED NEW CHORD SECTION IAW SRM 51-30-2 REV 103

Part: STRINGER — CORRODED (BS 1083 S27R) · corrosion level 2 · airframe 51,945 hrs · 36,785 cycles

CORROSION ON STRINGER 27R BSTA 1083. CUT-OUT DAMAGED STRINGER 27R SECTION DIM. 53 7/8" LONG BETWEEN BS 1079 TO 1133. FABRICATED NEW STRINGER SECTION FROM BAC 1498-145 7075T62 DIM. 53 7/8" AND FABRICATED 3EA SPLICE REPAIRS FROM BAC 1498-131 7075T6 DIM. 14" AND INSTALLED STRINGER SECTION AND SPLICE REPAIRS IAW SRM 53-10-2 FIG 9, 53-10-3 FIG 1, 51-30-5, 51-10-1, 51-10-2, AND 51-30-2 REV 103.

Part: SKIN — GOUGED (ZONE 200) · airframe 51,945 hrs · 36,785 cycles

MCD INNER SURROUND SKIN GOUGED STA 480 STR 16L. CUT-OUT DAMAGED AREAS APPROX DIM. 1.1" X 0.900", FABRICATED FILLERS APPROX DIM. 1.1" X 0.900" AND REPAIR DOUBLER APPROX DIM. 14" X 3.2", INSTALLED FILLERS AND REPAIR DOUBLER IAW EA 7-5330-143910 AT MCD INNER SURROUND SKIN STA 480 STR 16L.

Part: SKIN — GOUGED (ZONE 200) · airframe 51,945 hrs · 36,785 cycles

MCD INNER SURROUND SKIN HAS NUMEROUS GOUGES STA 620 STR 12L TO 17L. CUT-OUT DAMAGED AREAS 1.25" X 1.1", FABRICATED FILLERS APPROX DIM. 1.25" X 1.1" AND DOUBLER REPAIR APPROX DIM. 18.5" X 3.1", INSTALLED FILLERS AND DOUBLER REPAIR IAW EA 7-5330-143910 AT MCD INNER SURROUND SKIN STA 620 STR 12L TO 17L.

Part: SKIN — GOUGED (BS 480 S8L) · airframe 51,945 hrs · 36,785 cycles

MCD INNER SURROUND SKIN GOUGED STA 480, STR 8L. REMOVED GOUGED INNER SKIN DIM. 22" X 11" AT BS 480 STR 8L IAW SRM 51-30-2. FABRICATED NEW INNER SKIN FROM 2024 T-3 0.125" DIM. 22" X 11" IAW SRM 53-10-2 FIG 3A. INSTALLED NEW INNER SKIN IAW SRM 51-30-2 REV 103.

Part: SKIN — GOUGED (CARGO DOOR) · airframe 51,945 hrs · 36,785 cycles

MCD INNER SURROUND SKIN HAS NUMEROUS GOUGES STA 620 STR 4L TO 8L. REMOVED MAIN CARGO DOOR INNER SKIN UPPER AFT SECTION IAW SRM 51-30-2, FABRICATED INNER SKIN MATERIAL USED 2024T3 .125" PO 20110320 DIM 79" X 48" IAW SRM 53-10-2 FIG 3A. TREATED AND PRIMED IAW SRM 51-10-2 INSTALLED NEW INNER SKIN IAW SRM 51-30-2 REV 103

Part: FRAME — DAMAGED (ZONE 100) · airframe 51,945 hrs · 36,785 cycles

FUSELAGE INTERIOR BS 1176 -9 CHORD HAS 4 OPEN FASTENER HOLES BETWEEN LBL 17.5 AND RBL 17.5 WITH LOW EDGE DISTANCE AND NO EDGE DISTANCE. COMPLIED WITH EA 7-5310-143902 , INSTALLED NEW CHORD SECTION P/N 5310212 DIM. 65.5" LONG, AND FABRICATED AND INSTALLED 2EA SPLICES FROM 7075T73511 0.500" DIM 12" X 2" IAW EA 7-5310-143902.

Part: SEAT TRACK — CORRODED (BS 1050) · corrosion level 2 · airframe 51,945 hrs · 36,785 cycles

SEAT TRACK AT BS 1050 RBL 45.5 HAS CORROSION. REMOVED, FABRICATED, AND REPLACED NEW SEAT TRACK SECTION BS 1000 TO 1070 RBL 45.5 APPROX DIM 69.50" FROM BAC1520-792 7178T6 AND SPLICE REPAIR IAW SRM 53-10-5 FIG 1 AND 51-30-2. INSTALLED REPAIR PARTS IAW SRM 51-30-2 REV 103.

Part: STRINGER — CORRODED (BS 1173 S22L) · corrosion level 2 · airframe 51,945 hrs · 36,785 cycles

AFT PIT BS 1173 STRINGER AT 22L IS CORRODED. REMOVED DAMAGED STRINGER SECTION DIM. 25 3/8" IAW B727 SRM 53-10-3 AND 51-30-2. FABRICATED NEW STRINGER SECTION FROM BAC1498-144 7075T6 DIM. 25 3/8" AND SPLICE FROM BAC1498-132 7075T6 DIM. 14 3/4" IAW SRM 53-10-2 AND 53-10-3 FIG 1 DETAIL I. INSTALLED NEW STRINGER SECTION AND SPLICE IAW SRM 51-30-2 AND 53-10-3 AT AFT PIT BS 1157 TO 1183.

Part: SKIN — CORRODED (BS 660 S28L/R) · corrosion level 2 · airframe 51,945 hrs · 36,785 cycles

CORROSION ON SKIN AT BS 660 BETWEEN STRINGERS 28L AND 28R CUT OUT DAMAGED AREA DIM. (8" X 73/4") IAW SRM 53-30-3 FIG 1. FABRICATED DOUBLER IAW SRM 53-30-3 FIG 1 AND 53-30-2 FIG 2, TREATED AND PRIMED IAW SRM 51-10-2, INSTALLED REPAIR PARTS, DOUBLER AND FILLER IAW SRM 51-30-2 REV. 103.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 51,945 hrs · 36,785 cycles

BULGE EXTERIOR FUSELAGE BS 1183-1176 STR 22L AT AFT LAV SERVICE PANEL. REMOVED INNER DOUBLER IAW SRM 51-30-2. FABRICATED NEW INNER DOUBLER FROM 7075T6 0.071" DIM. 20" X 20" IAW SRM 51-30-5 AND DWG 65-25607. INSTALLED NEW INNER DOUBLER IAW SRM 51-30-2 AT EXTERIOR FUSELAGE BS 1183 TO 1176.

Part: FRAME — CORRODED (BS 950C S27-28R) · corrosion level 2 · airframe 51,945 hrs · 36,785 cycles

CORROSION AT FASTENER HOLE ON UPPER FLANGE OF FRAME AT BS 950C BETWEEN STRINGERS 28R AND 27R. CUT OUT DAMAGED AREA DIM 1 1/4" X 1" IAW SRM 51-40-3 FIG 1, FORMED REPAIR DOUBLER IAW B727 SRM 53-10-2 FIG 5 AND 51-40-3 FIG 1 INSTALLED REPAIR DOUBLER IAW SRM 51-30-2 AND 51-40-3 FIG 1 REV 103.

Part: WEB — GOUGED (DOOR FRAME) · airframe 51,945 hrs · 36,785 cycles

C-1 DOOR CUTOUT AFT FRAME BS 620 WEB IS GOUGED ON FWD SIDE AT STR 22R BETWEEN DOOR STOPS NR 3 AND NR 4. REMOVED C-1 DOOR AFT FRAME WEB IAW SRM 51-30-2 FABRICATED NEW FRAME WEB FROM 7075 T6 .071" DIM 106" X 6" IAW 53-10-2 FIG 3 AND 51-30-5 INSTALLED NEW FRAME WEB IAW SRM 51-30-2 REV 103

Part: FRAME — PUNCTURED (BS 1090 S27R) · airframe 51,945 hrs · 36,785 cycles

AFT CARGO COMPARTMENT, FRAME AT BS 1090 ABOVE STR 27R HAS PUNCTURE IN THE UPPER FLANGE WITH MATERIAL LOSS ON THE LOWER SURFACE .5" IN DIAMETER. CUT OUT DAMAGED AREA OF FRAME DIM 1" X 1" IAW SRM 51-40-3 FIG 1 FORMED FRAME REPAIR DOUBLER IAW SRM 51-40-3 FIG 1 AND 53-10-2 FIG 5 INSTALLED REPAIR DOUBLER IAW SRM 51-30-2 REV 103 AND 51-40-3 FIG 1

Part: SHEAR TIE — CORRODED (BS 1166 S27-28R) · corrosion level 2 · airframe 51,945 hrs · 36,785 cycles

CORROSION ON SHEAR TIE AT BS 1166 BETWEEN STRINGERS 28R AND 27R. REMOVED AND REPLACED CORRODED SHEAR TIE AT BS 1166, STRINGER 28R TO 27R IAW SRM 51-30-2 REV 103

Part: CONTROLLER — MALFUNCTIONED (CABIN PRESSURE) · airframe 50,812 hrs · 35,859 cycles

CABIN PRESSURIZATION CONTROLLER WOULD NOT MAINTAIN CABIN ALTITUDE. CONSTANT CLIMB OF 1500 FT/MIN SETTING OFF CABIN ALT WARNING HORN AT 10000 AND CLIMBING TO 14000 WHILE LEVEL AT FL 250. PERFORMED DECAY CHECK OF ACFT IN REF TO JRH AND DECAY PASSED, SO AS A PRECAUTION REMOVED AND REPLACED CABIN PRESSURE CONTROLLER IN REF TO AMM 21-31-010-4, OPS CHECKED GOOD. ACFT OK FOR SERVICE.

Part: STRINGER — CRACKED (ZONE 500) · airframe 50,447 hrs · 35,587 cycles

LT WING STATION 686.5 STRINGER S-10 S CRACKED REPAIRED STRINGER S-10, AT STA 686.5 WITH REPAIR KIT 65C26139-12 REF EO NR 7-5710-7-4322 PT 1, THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: RETAINER — CRACKED (LT WING TE FLAP) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

LT WING TE FLAP WELL LWR PNL BULB SEAL RETAINER IS CRACKED 15 INCHES OUTBOARD OF NR 2 FLAP TRANSMISSION (MKD). REMOVED SEAL RETAINER REF SRM 51-30-2. FABRICATED RETAINER REF DWG 65-21658 AND GMM 7-0-1001. INSTALLED SEAL RETAINER REF SRM 51-30-2 AND IDENTIFIED RETAINER. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SPAR — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

CORROSION ON LT HORIZ STAB REAR SPAR LOWER CHORD, STAB STA 108.5 BLENDED CHORD, ORIGINAL THICKNESS .110 INCH, MATERIAL REMOVED .027 INCH MATERIAL REMAINING .083 INCH. REPAIRED CHORD REF EA 7-5510-114006 DATED 7-11-08. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: BRACKET — MISALIGNED (RT WING) · airframe 50,447 hrs · 35,587 cycles

RIGHT WING TANK UNIT (PROBE) CONTACTING STRINGER 11 REPAIR AT WS 686.5. FABRICATED NEW QUANTITY INDICATOR BRACKET AND INSTALLED. REF EA NR 7-5710-114010. THIS IS CLASSIFIED AS A MAJOR.

Part: STRINGER — CRACKED (ZONE 600) · airframe 50,447 hrs · 35,587 cycles

RT WING, STR 10, CRACKED AT W.S. 686.5, ITEM IS AD DRIVEN, IF CRACKS EXCEED LIMITS IN SECTION II, FIG 12, CONTACT STRUCTURES ENGINEERING FOR REPAIR INSTRUCTIONS PER WORK CARD E7-5710-7-4322. STOP DRILLED CRACK. NDT TO VERIFY TERMINATION OF CRACK AT STOP DRILL. LOCATED HOLES IN REPAIR ANGLES AND INSTALLED. REF E.O. 7-5710-7-4322 / FIGURE 18. CLASSIFIED AS A MAJOR REPAIR.

Part: CHANNEL — CRACKED (RT WING) · airframe 50,447 hrs · 35,587 cycles

GENERATED BY EO NR 7-5710-7-4322 RT WING, STA 686.5 WEB FWD ATTACH "Z" CHANNEL CRACKED, OUTBD. REMOVED DAMAGED "Z" CHANNEL, LOCATED AND DRILLED NEW "Z" CHANNEL AND INSTALLED. REFERENCE SRM 51-30-2. CLASSIFIED AS A MINOR REPAIR.

Part: STRINGER — CRACKED (RT WING) · airframe 50,447 hrs · 35,587 cycles

GENERATED BY EO 7-5710-7-4322 RT WING STA 686.5, VENT STRINGER STOP DRILLED CRACK, FABRICATED REPAIR PARTS AND INSTALLED REPAIR PARTS REF EO NR 7-5710-7-4322. CLASSIFIED AS A MAJOR REPAIR.

Part: SPAR — CORRODED (ZONE 300) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

CORROSION ON LT HORIZ STAB FRONT SPAR UPPER CHORD, STAB STA 4.5 BLENDED CORROSION, ORIGINAL THICKNESS IS .120 INCHES. MATERIAL REMOVED .052 INCHES. MATERIAL REMAINING .088 INCH REPAIRED UPPER CHORD REF EA NR 7-5510-114204 DATED 7-11-08. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: STRINGER — CRACKED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

STRINGER 5R CRACKED BOTH IND/UPPER AND INB/LOWER FLANGES AT STA 340 FWD LAV AFT WALL MOUNTS REMOVED DAMAGED SECTION OF STRINGER, FABRICATED, TREATED, PRIMED, AND INSTALLED REPAIR PARTS REF PART 1 OF EA 7-5310-113998. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: STRINGER — CRACKED (BS 945 S18A LT) · airframe 50,447 hrs · 35,587 cycles

LT FUSELAGE OVERWING BS 945, STR18A (L) REMOVED DAMAGED SECTION OF LT S-18A, INSPECTED SKIN AREA UNDER REMOVED STRINGER SECTION AND FUSELAGE SKIN (NO DEFECTS NOTED). DRILLED HOLES IN REPAIR ANGLES, FABRICATED SHIMS AND INSTALLED ALL REPAIR PARTS. REFERENCE EA NR 7-5310-113997. CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — CHAFED (ZONE 100) · airframe 50,447 hrs · 35,587 cycles

HEAVY CHAFE MARK FROM WING-TO-BODY FAIRING ON RT SIDE OF FUSELAGE AT BS 950D 10 TO 950D 13 WL 197 BLENDED DAMAGE REF SRM 53-30-1. ORIGINAL THICKNESS .140 REMOVED .038 AT DEEPEST BLEND OUT REMAINING MATERIAL .102 MATERIAL LOSS OUT OF LIMITS REF SRM 51-30-1. THIS IS CLASSIFIED AS A MAJOR REPAIR. AREA TO BE REPAIRED ON N/R N00256.

Part: SKIN — CHAFED (ZONE 100) · airframe 50,447 hrs · 35,587 cycles

CHAFE MARKS ON FUSELAGE SKIN FROM WING-TO BODY FAIRING ATTACH SCREWS, RT SIDE OF FUSELAGE BS 950D 9 TO 950D 12 BLENDED OUT DAMAGE. REF SRM 53-30-1 DETAIL 1. ORIGINAL THICKNESS .140 INCH, REMOVED .037 INCH REMAINING THICKNESS .103 INCH OUT OF LIMITS. REF SRM 53-30-1 PG 2A DETAIL 1. REPAIRED SKIN BY INSTALLING A DOUBLER. REF FED EX EA NR 7-5330-114002. ALODINED AND PRIMED. REF SRM 51-10-2. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — GOUGED (ZONE 100) · airframe 50,447 hrs · 35,587 cycles

EXTERIOR FUSELAGE SKIN RT SIDE AT BS 950E 1 INCH STR S-18R 4 INCH SKIN IS GOUGED. REMOVED DAMAGE REF SRM 53-30-1. NDT'D ORIGINAL MATERIAL THICKNESS .140. REMOVED .044 .096 MATERIAL REMAINING. REPAIRED ON N00256. THIS IS CLASSIFIED AS A MAJOR REPAIR. MATERIAL LOSS OUT OF LIMITS REF SRM 53-30-1 AREA TO BE REPAIRED ON N00256.

Part: CREASE BEAM — CRACKED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

FUSELAGE OUTER CREASE BEAM CHORD (STR 17L) CRACKED REMOVED CREASE BEAM CHORD, STR 17L, FROM STE 620 TO STA 663. VERIFIED MATERIAL TO BE BAC1506-1133 7075-T-6, ATAG NR A00531. LOCATED AND DRILLED FASTENER HOLES IN NEW CHORD. TREATED AND PRIMED NEW CHORD. INSTALLED NEW CHORD AND APPLIED CORROSION INHIBITOR COMPOUND REF SRM 51-30-02 PG 2, SRM 53-10-2 FIG 9, SRM 51-30-30 5 PG 3-5, SRM 51-40-4 FIG 1, SRM 51-20-014 -7, PG 1-7. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — WORN (BS 727D S19L) · airframe 50,447 hrs · 35,587 cycles

LT LOWER FUSELAGE JUST FWD OF LT LANDING LIGHT, BS 727D 14 STR19L, SKIN LAP HAS WEAR REMOVED DAMAGED AREA. REMOVED INTERNAL REPAIR, FABRICATE SKIN DOUBLER AND FILLER. TREATED, PRIMED AND INSTALLED REPAIR. REF SRM 53-30-3 FIG 5, SRM 51-30-02 PG 1-10. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: BULKHEAD — CRACKED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

FUSELAGE STA 1183 BULKHEAD RT LOWER MIDDLE FLOOR WEB CRACKED. REF EO 7-5320-7- 310 PT 1. REPLACED WEB AND ANGLE REF SRM 51-30-02 PG 4.

Part: FRAME — CRACKED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

CRACK IN MAIN FRAME STA 380, BETWEEN STRINGER 7R AND RIGHT FWD DOOR, CUTOUT FRAME. REPAIRED FRAME REF SRM 53-10-4 FIG 2, REMOVED AND REINSTALLED DOOR TRIM AND DOOR TRIM SUPPORT REF SRM 51-30-02 PG'S 1-10. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: RETAINER — CRACKED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

MAIN DECK GILL LINER RETAINER RAIL, HOLE CRACKED, BS 1170 STR 8R REMOVED GILL LINER RETAINER RAIL, DRILLED UP NEW RETAINER RAIL, AND INSTALLED NEW RETAINER RAIL, IN REF TO SRM 51-30-2 PG 1-15 AND SRM 51-30-5 PG 5. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: STRINGER — CORRODED (ZONE 200) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

CABIN S3L HAS CORROSION FROM BODY STA 720A-740 REMOVED CORROSION FROM STA 720A - 740 STR 3L. MATERIAL THICKNESS .045 AND .056, MATERIAL LOSS .008 TO .015 ALL AREAS OUT OF LIMITS. REMOVED DAMAGED STR 3L STA 720A 12 TO 740. REMOVED AND REINSTALLED STR 3L CLIPS AT STA 720B, 720C, 720D, 720E AND 720F. FABRICATED NEW STRINGER 3L STA 720A 12 AND 720 AND SPLICE PLATES. TREATED, PRIMED AND TOP COATED SKIN AT 3L STR 720-740. REF SRM 51-30-2 P1-6. 51-10-2 PG7, 53-10-1 PG 1-2A FIG 1, 53-10-3 PG 5-8B, AND MM 51-20-151-7. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: WEB — CRACKED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

FUSELAGE 1183 BULKHEAD LT SIDE LOWER OTBD FLOOR WEB CRACKED REMOVED DAMAGED PART (DITCHING PAN AND ANGLE ). FABRICATED, HEAT TREATED, ALODINED, PRIMED AND INSTALLED IAW REF SRM 51-30-02 51-10-02, 51-20-5. BOEING DWG 65-29567 THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: RETAINER — CORRODED (ZONE 500) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

LT WING LOWER T/E PANEL SEAL RETAINER IS CORRODED WS 167 TO 222 JUST AFT OF AFT SPAR LWR CHORD FABRICATED NEW, 2 EA SEAL RETAINERS ON LT WING LOWER T/E PANEL FROM WS 162 TO 222. REF DWG 65-21656-88, TREATED, PRIMED, AND INSTALLED REF SRM 51-10-2 PG 1-7, 51-30-10 PG 1, 2, 13. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: STRINGER — CORRODED (ZONE 200) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

CABIN S-6L LOWER SURFACE HAS CORROSION BETWEEN BS 720A AND 720D REMOVED CORROSION, FOUND TO BE OUT OF LIMITS. REF SRM 53-10-1 FIG 1. REMOVED DAMAGE SECTION OF STRINGER REF SRM 53-10-3, PG 6. VERIFIED ALL REPAIR MATERIALS. REF A TAG A93213, AND A48139. ALL REPAIR MATERIALS ARE 2024-T3, .071 INCH AND .125'. STRINGER IS BAC-1498-141 7075 -T62. REMOVED STRINGER CLIPS, STA 720B AND C, STR 6L. FABRICATED AND FIT STRINGER SECTIONS AND SPLICE PLATES REF SRM 53-10-3 ITEMS 5. INSTALLED WET STRINGER SECTION AND SPLICE PLATES REF SRM 53-10-3 PG-5. REFINISHED REPAIR AREA REF AMM 51-20 AND SRM 53-10-3 PG 5 ITEM 8. REINSTALLED STRINGER CLIPS REF SRM 51-30-02 PG 1-10. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — DAMAGED (ZONE 100) · airframe 50,447 hrs · 35,587 cycles

RT EXT FUSE SKIN IS GOUGED FROM CONTACT WITH FASTENER TAIL BS 950D 11 INCHES, STR 26R.

Part: SKIN — WORN (ZONE 100) · airframe 50,447 hrs · 35,587 cycles

BLENDED AREA LT LOWER FUSELAGE AFT WING TO BODY FAIRING OUT OF LIMITS. DAMAGE AT FR 950F AND 3.5 INCH FWD AND BELOW STR 25L AND INCH OF FR 950F ON STR 25L. REPAIRED BY INSTALLING A DOUBLER REF SRM 53-30-3 FIG 5. REMOVED AND REINSTALLED WING TO BODY PANEL REF SRM 51-30-02 PGS 1-4, THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: FRAME — DAMAGED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

TOOLING DAMAGE AT STA 783 FRAME JUST I/B OF STR 4R REMOVED DAMAGE PER SRM 53-10-4. FABRICATED REPAIR PARTS PER SRM 53-10-4. TREATED AND PRIMED PER SRM 51-30-02. INSTALLED REPAIR PER SRM 51-30-02 PG 1-13 AND 53-10-04. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: DOOR FRAME — CRACKED (ZONE 800) · airframe 50,447 hrs · 35,587 cycles

FWD GALLEY DOOR LWR AFT CORNER CRACKED REMOVED FWD GALLEY DOOR AND OPENED UP LOWER AFT INNER SKIN FOR ACCESS. REMOVED LOWER AFT STOP FITTING REMOVED PRESSURE SEAL, LOWER GATE, AFT LOWER SEAL RETAINER, REMOVED DAMAGE SECTION OF FRAME, AND DRILLED AND INSTALLED FRAME REPAIR. REF BOEING DRAWING NR 69-69908. INSTALLED ITEMS THAT WERE REMOVED. INSTALLED AND RIGGED DOOR REF AMM 52-12-000-5. INSTALLED LEVELING COMPOUND IN THE LOWER PART OF DOOR. INSTALLED HANDLE BOX AND LOWER HINGE COVER PLATES, PAINTED REPAIR. OPS CHECK GOOD. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: STRINGER — CORRODED (ZONE 200) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

CABIN S-2L HAS CORROSION FROM BS 720A - 740 REMOVED CORROSION, FOUND TO BE OUT OF LIMITS, CUT OUT DAMAGE SECTION, INSTALLED REPAIR AND RESTORED STRINGER TO ORIGINAL FINISH IAW REF SRM 53-10-01 AND 53-10-3 AND 53-10-2. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: WEB — CRACKED (ZONE 500) · airframe 50,447 hrs · 35,587 cycles

LEFT WING INBD T/E NR 4 JACKSCREW/ELEPHANT EAR FAIRING. CRACKED AT UPPER AFT INBD CLOSER WEB INSTALLED DOUBLER AND FILLER REF SRM 51-40-2 PG 6, THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: CREASE BEAM — CRACKED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

MID CABIN CREASE BEAM WEB CRACKED AT STA 945, LBL 47, WL 208. REPLACED WEB REF SRM 51-30-02 PG 6, DRAWING NR 65-21905. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: KEELBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

LOWER FUSELAGE INTERIOR OF KEEL BEAM, BS 760 TO 761, LBL 5 TO RBL5, WL 146, TO WL 146, KEAL BEAM FRAME T LOWER ATTACH ANGLE CORRODED. REMOVED DAMAGED STIFFENER AND REPLACED WITH A NEW STIFFENER 65-23555-67, PER REF SRM 51-30-02 PG 1-15. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: FRAME — DAMAGED (BS 740) · airframe 50,447 hrs · 35,587 cycles

TWO DRILL STARTS AT AFT LIP OF STA 740 FRAME BETWEEN STR 7R AND 8R. REMOVED DAMAGE .197 REMOVED FROM EDGE .200 INCH ALLOWED WITHIN LIMITS REF SRM 53-10-1 FIG 1 DETAIL 7, AND EA NR 7-5310-11400, THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 50,447 hrs · 35,587 cycles

LEFT WING INBD TE MID FLAP S/N BN 492 HAS LWR SURFACE DELAM AT 3 INCH FWD OF AFT EDGE AND 20 INCH THROUGH 336 INCH OB OF INBD END. REPLACED MID FLAP, NEW SERVICEABLE MID FLAP. INSTALLED ON W/C 75C075-00, THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: FITTING — CORRODED (ZONE 100) · airframe 50,447 hrs · 35,587 cycles

LOWER FUSELAGE, CORROSION ON TIE FITTING, STA 337 EXTIOR RBL 17", BELOW LANDING GEAR DRAG BRACE FITTING SUPPORT BEAM. REMOVED AND REPLACED TIE FITTING STA 337, RBL 17 BELOW AND 13-14.

Part: SKIN — WORN (ZONE 100) · airframe 50,447 hrs · 35,587 cycles

LT LOWER FUSELAGE WING TO BODY FAIRING BLENDED AREA OUT OF LIMITS. DAMAGE AT LAP JOINT STR 26L - 2.6' FWD OF FR 950E AND DAMAGE AT 2.7L BELOW STR 26L REMOVED AND REINSTALLED FAIRING SUPPORT, REMOVED DAMAGE AREA, OUT OF LIMITS. FABRICATED DOUBLER AND STRUCTURAL FILLER, REF SRM 51-30-02, 53-30-3 FIG 5 AND FIG 24. TREATED AND PRIMED, AND TEFLON COATED REF 51-30-3 FIG 24. INSTALLED REPAIR PARTS REF SRM 53-30-3 FIG 5 AND 24. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: ANGLE — CORRODED (ZONE 100) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

PANEL NR 3338 HAS FRETTING CORROSION AROUND EDGE AT MOUNT HOLE. REMOVED CORROSION, ORIGINAL THICKNESS .036". REMOVED .010", .026" REMAINING. MATERIAL IS OUT OF LIMITS REF SRM 53-10-1 PG 1 DETAIL 1. FABRICATED NEW STIFFENER ANGLE 7075-O- .040, HEAT TREATED TO T-6. REF DWG 65-25581, DOCUMENT 65-25581 REV C. TREATED AND PRIMED AND PAINTED. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: STRINGER — CORRODED (BS 720A-720B) · airframe 50,447 hrs · 35,587 cycles

LOWER SIDE SURFACE ON STR 8L AT 720A 10 INCH TO FS HAS AREAS OF SURFACE CORROSION REMOVED CORROSION BY BLENDING, NDT FOUND BLENDED AREA TO BE WITHIN LIMITS WITH ORIGINAL BEING .045". BLENDED AREA TO BE AT .041' ON LOWER SURFACE ON STR 8L AT FS 720A 10 INCHES REF SRM 53-10-1 FIG 1, WORK ACCOMPLISHED ON EA NR 7-5310114005, LEVEL 1 CORROSION THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: FRAME — DAMAGED (BS 804) · airframe 50,447 hrs · 35,587 cycles

MULTIPLE UNFILLED HOLES ON FRAME 804 BETWEEN 4L AND STR 5L INSTALLED DOUBLER ON FRAME REF SRM 51-40-3, THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: CHANNEL — CRACKED (BS 1070) · airframe 50,447 hrs · 35,587 cycles

DOT 7 AFT PIT, FLOOR SUPPORT ATTACH ANGLE MISDRILLED AND CRACKED ON LOWER SURFACE AS MARKED, LOCATED AT STA 1070 5 INCH, LBL 18 INCH. REPLACED ATTACH ANGLE REF SRM 51-30-02 PG 2. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SHEAR TIE — CORRODED · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

LOWER FUSELAGE, CORROSION ON TIE FITTING STA 337 EXTERIOR, LBL17 INCH. BELOW LANDING GEAR SUPPORT BEAM TO DRAG BRACE FITTING. REMOVED AND REPLACED TIE FITTING STA 337 LBL17 BELOW NOSE LANDING GEAR DRAG BRACE FITTING SUPPORT BEAM REF SRM 51-30-2 PG'S 8-9 AND 13-14. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: CREASE BEAM — CRACKED (BS 640-660) · airframe 50,447 hrs · 35,587 cycles

FUSELAGE CREASE BEAM WEB CRACKED, STR17L, BS-640-660 FABRICATED NEW CREASE BEAM WEB PER SAMPLE AND BOEING DWG NR 65-58536. TRANSFERED NEW FASTENER HOLES REF, SRM 51-30-2, PG 1-10. TREATED AND PRIMED WEB, REF: SRM 51-10-2, PG 1-2. WEB BE INSTALLED ON NR N00796, JPF LINE ITEM 2. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: HINGE — CORRODED (NLG DOOR) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

NLG STRUT WELL CUT OUT LT AFT DR SEAL RETAINER IS CORRODED BS 282-334, LBL 17, WL 150 (MRK). REMOVED OLD SEAL RETAINER, REF:SRM 51-30-02. INSTALLED NEW SEAL RETAINER, REF: SRM 51-30-02, P-1. THIS IS CLASSIFIED AS A MINOR REPAIR. THREE HINGE BRACKETS REMOVED FOR ACCESS TO SEAL RETAINER RIVET PATTERN. TO BE INSTALLED AND CHECKED FOR FIT, RIG, AND FUNCTION ON CARD NR 71C130-00. INSTALLED LT AFT NLG DOOR HINGES IAW SRM 51-30-02 P1. REMOVED LT AFT NLG DOOR TO FOM AND INSTALLED DOOR AFTER OTHER MAINTENANCE COMPLETED IAW MM 32-22-001-4. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: PANEL — CRACKED (PAX DOOR) · airframe 50,447 hrs · 35,587 cycles

PANEL RACK: FWD ENTRY DOOR LINER, SLIDE PACK PANEL CRACKED AT CUT OUTS. REMOVED AND REPLACED DOOR LINER SLIDE PAN REF SRM 51-30-02 PG 13-14. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: CHANNEL — CRACKED (FUSELAGE) · airframe 50,447 hrs · 35,587 cycles

NLG W/W AFT BULKHEAD STA 351.2, CRACK ON DOWN LOCK ACTUATOR MOUNT U-CHANNEL. COMING OUT OF UPPER LEFT FASTENER HOLE. REMOVED DOWN LOCK ACTUATOR MOUNT U-CHANNEL, DRILLED UP NEW CHANNEL P/N 69-19122-2, AND INSTALLED. REF DWG 69-18194 AND SRM 51-30-02 PG 1-10 THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SEAT TRACK — CORRODED (BS 910-914) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

CABIN SEAT TRACK AT STA 910 - STA 914, LBL 31, WL 208 IS CORRODED REMOVED SEAT TRACK, VERIFIY MATERIAL ID AS BAC1520-792 7178T651 ATAG NR A20604, P/O 1039090. FABRICATED SEAT TRACK, ALODINED, PRIMED AND INSTALLED IAW:BAC1520-792 REV B AND IPB 53-42-00 AND SRM 51-30-05. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SUPPORT ANGLE — CRACKED (FLAP TRACK) · airframe 50,447 hrs · 35,587 cycles

RT WING LWR FIXED T/E PANEL BELOW NR 14 SPOILER ACTUATOR. FLAP TRACK SUPPORT ANGLE CRACKED. REMOVED AND MANUFACTURED NEW O/B ANGLE FOR NR 8 FLAP TRACK SUPPORT BRACKET REF BOEING DRAWING 69-22894-9 AND SRM 51-20-1. INSTALLED NEW MANUFACTURED ANGLE ON BRACKET REF SRM 51-30-2 1-4 AND BOEING DRAWING 69-22894. INSTALLED SUPPORT BRACKET ON NR 8 FLAP TRACK REF SRM 51-30-2 PG 13. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: BRACKET — CORRODED (RT WING) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

SEAL RETAINER ON SNRM NR N00362 IS CORRODED. FOUND BRACKET UNDER RETAINER CORRODED AT WS 167 TO 222 AFT OF SPAR LOWER CHORD. REPLACED BRACKET (STIFFENER) ON NON ROUTINE W/U NR N00362. SEE ITEM NR 16 ON JPF. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SHIM — CRACKED (LT WING TE FLAP) · airframe 50,447 hrs · 35,587 cycles

PANEL RACK, LT WING I/B FLAP ASSY O/B FWD NR 3 FAIRING HAS CRACK ON INTERIOR TAPERED/CHAFF SHIM. REMOVED SHIM AND REINSTALLED NEW SHIM. REF MM 51-51-011-8 PGS 1-5. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SUPPORT — CORRODED (BS 1030) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

DOT 9 AFT PIT, RT Z-ANGLE, LOWER SURFACE CORRODED AROUND TIE DOWN FITTING, LOCATED STA 1030 14", RBL 20" TO RBL 22" WATER LINE 149 Z-ANGLE IS REPLACED WITH NEW, P/N 65-57570-2 AND WILL BE INSTALLED ON W/C 5310-7-2354 E2 P1R.

Part: ANGLE — CRACKED (RT MLG) · airframe 50,447 hrs · 35,587 cycles

RT MLG STA 940 UPPER BEAM ANGLE CRACKED IN RADIUS. FABRICATED NEW ANGLE. REF BOEING DWG 69-65045. MATCH DRILLED REF DWG 69-65045. INSTALLED ANGLE. REF SRM 51-30-2. THIS IS CLASSFIED A MINOR REPAIR.

Part: FRAME — CHAFED (ZONE 100) · airframe 50,447 hrs · 35,587 cycles

DOT 5, AFT PIT, STA 1148, FRAME WORN FROM HYDRAULIC LINES CHAFING, LOCATED BETWEEN STR 21L TO STR 22L. REPAIRED FRAME AT STA 1148 BETWEEN STR 21L TO STR22L. REF SRM 51-40-3 FIG 1. THIS IS CLASSIFIED AS A MAJOR REPAIR. INSTALLED DOUBLER ON FRAME AT STA 1148 BETWEEN STR 21L TO STR 22L.

Part: BULKHEAD — CORRODED (ZONE 100) · airframe 50,447 hrs · 35,587 cycles

NOSE WHEEL WELL AFT WALL (STA 351) SURFACE UNDER DOWN LOCK ACTUATOR MOUNT IS CORRODED. REMOVED CORROSION, NDT, MATERIAL THICKNESS, ORIG. "T" = .072" MAT REMAINING =.065". .007' MAT LOSS. WITHIN LIMITS REF FED EX EA NR 7-5310-113999, TREATED AND PRIMED, AND APPLIED CIC TO AFFECTED AREA REF SRM 51-10-6, 51-30-1, 51-30-2 PG 1-10. THIS IS CLASSIFIED AS A MINOR REPAIR, LEVEL 1 CORROSION.

Part: HINGE — CRACKED (ZONE 100) · airframe 50,447 hrs · 35,587 cycles

GROUND POWER ACCESS PANEL. TOP HINGE BRACKET CRACKED REMOVED DAMAGED PART PER REF SRM 51-30-02 PG 1-3, FABRICATED NEW PART PER REF DWG NR 66-16849-7. TREATED AND PRIMED NEW PART PER REF SRM 51-10-02. INSTALLED NEW PART PER REF SRM 51-30-02 PG 1-3. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: STRAP — CORRODED (ZONE 100) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

FWD CARGO COMPARTMENT RT STRIP AT STA 620 - 660, CORRODED ON BACK SIDE AND CRACKED FABRICATED NEW STRIP USING .063" 2024 T-3, A93206 REF BAC DWG 65-67255 1498-288 SRM 51-20-1 FIG 7. TREATED AND PRIMED REF 51-10-2 PART MARKED REF FED EX GMM 7-0-1001. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: PANEL — CRACKED (ZONE 600) · airframe 50,447 hrs · 35,587 cycles

RT LOWER SIDE T/E PANEL FOWARD OF I/B AILERON HAS CRACK IN O/B EDGE SUPPORT ANGLE 1 3/4 INCH FORWARD FROM AFT EDGE. REMOVED DAMAGED PART PER REF SRM 51-30-2 PG 1-3. FABRICATED NEW PART PER DWG 65-19281-107. TREATED AND PRIMED NEW PART PER REF SRM 51-10-02. INSTALLED NEW PART, PER REF 51-30-02 PG 1-3. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: RIB — CRACKED (NLG DOOR) · airframe 50,447 hrs · 35,587 cycles

NLG RIGHT FWD DOOR, CRACK IN AFT SIDE FRAME AT O/B STOP FITTING LOWER 2 FASTENERS FOR INNER STRUCTURE. REMOVED AND REPLACED DOOR FOR ACCESS, REPAIRED DOOR REF MM 32-22-001-4 AND SRM 51-40-3 FIG 1. ADJUSTED AND OPS CHECK OF DOOR ACCOMPLISHED ON W/C 71C130-00. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: PANEL — DELAMINATED (ZONE 300) · airframe 50,447 hrs · 35,587 cycles

TAIL DOCK VERTICAL STAB LT TOP PNL 9706 HAS DELAM ON PNL RADIUS IN CTR OF PNL. REPAIRED PANEL NR 9706 REF SRM 51-40-9 PAR 3, 4. "THIS IS CLASSIFIED AS A MINOR REPAIR."

Part: HINGE — CRACKED (ZONE 100) · airframe 50,447 hrs · 35,587 cycles

GROUND POWER ACCESS PANEL. TOP HINGE BRACKET CRACKED REMOVED DAMAGED PART PER REF SRM 51-30-02 PG 1-3, FABRICATED NEW PART PER REF DWG NR 66-16849-7, TREATED AND PRIMED NEW PART PER REF SRM 51-10-02. INSTALLED NEW PART PER REF SRM 51-30-02 PG 1-3. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: STRINGER CLIP — CRACKED (BS 804 S7R) · airframe 50,447 hrs · 35,587 cycles

MID CABIN AT STA 804 STRINGER 7R STRINGER CLIP CRACKED. REMOVED STRINGER CLIP STA 804 STR 7R. REF 727 SRM 51-30-2 P1. MATCH DRILLED NEW STRINGER CLIP P/N 65-4531342 A 18793 P/O 1038874. REF 727 SRM 51-30-2 P1. INSTALLED NEW STRINGER CLIP STA 804 STR 7R REF 727 SRM 51-30-2 P1. THIS REPAIR IS CLASSIFIED AS MINOR REPAIR.

Part: SKIN — DELAMINATED (TAIL CONE) · airframe 50,447 hrs · 35,587 cycles

TAIL CONE: VERTICAL STAB PNL 9703 HAS NUMEROUS PUNCTURES AND DELAM. REPAIRED PANEL NR 9703. REF SRM 51-40-9 PAR 3, 4 PAGES 2A-6. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: RIB — CRACKED (NLG DOOR) · airframe 50,447 hrs · 35,587 cycles

NLG LEFT FWD LEFT DOOR, CRACK IN AFT SIDE FRAME AT O/B STOP FITTING LOWER 2 FASTENERS FOR INNER SUPPORT. REPAIRED NLG DOOR REF SRM 51-40-3 PG 1-6. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: STRINGER CLIP — CRACKED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

STRINGER CLIP CRACKED BS 950C, STRINGER 5L REPLACED STRINGER CLIP REF SRM 51-30-2 PG 1-10. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: STRINGER CLIP — CORRODED (ZONE 200) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

STRINGER CLIP ON STR 9L AT FS 720B HAS CORROSION ON SIDES REMOVED STRINGER CLIP REF SRM 51-30-02. DRILLED UP NEW CLIP. INSTALLED NEW CLIP REF SRM 51-30-02, THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: PANEL — CRACKED (ZONE 100) · airframe 50,447 hrs · 35,587 cycles

PANEL RACK, UPPER APU PANEL CUTOUT FASTENER HOLE CRACKED/GOUGE FABRICATED NEW PANEL FROM 2024 T-3 .040", APPLIED ALODINE, PRIMER AND PAINT REF DWG 65-58541, SRM 51-10-02 PG 7 AND MM 51-20-151-7 PG 1/2. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: FRAME — DAMAGED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

FIGURE "8" HOLE ON STA 760 FRAME I/B OF STR 5L. FABRICATED REPAIR PART (CHANNEL) FOR FRAME STA 760, STRINGER 5L, REF SRM 51-40-03. HEAT TREATED, TRACKING NR 208-06-060, TREATED AND PRIMED AND INSTALLED REF SRM 51-10-2 PG 1-7, 51-30-2 PG 2, 51-40-03 FIG 1, THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: STRINGER CLIP — CRACKED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

STRINGER CLIP CRACKED, BS 950D, STRINGER 6L. REPLACED STRINGER CLIP AT BS 950D STRINGER 6L REF SRM 51-30-2 PG 1-11. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: TAB — DELAMINATED (ZONE 300) · airframe 50,447 hrs · 35,587 cycles

RT HORIZONTAL STAB ELEVATOR TRIM TAB IS DISBONDED ON LE UPPER SURFACE 29 INCHES OUT FROM INBD EDGE AT NR 3 HINGE. REMOVED AND INSTALLED NEW SERVICABLE TAB REF MM 27-30-011-2, OPERATIONAL AND FUNCTIONAL CHECK ACP ON W/C 73C022-00 THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: STRINGER CLIP — CRACKED (BS 760 S5R) · airframe 50,447 hrs · 35,587 cycles

STRINGER CLIP CRACKED AT LOWER O/B RADIUS STR 5R STA 760 REPLACED STRINGER CLIP TO STR 5, STA 760 REF SRM 51-30-2 PG 10. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: FRAME — DAMAGED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

FUSELAGE FORMER FRAME DOUBLE DRILLED ON VERT FLANGE WITH LESS THEN 1/4 D DISTANCE BETWEEN HOLES AT FS 760 BETWEEN STR 3R AND 4R REPAIR DOUBLE DRILLED HOLE ON FRAME STA 760 BETWEEN STR 3R AND 4R REF SRM 53-10-4 FIG 1. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: FLOORBEAM — DAMAGED (ZONE 100) · airframe 50,447 hrs · 35,587 cycles

PASS CABIN AT STA 760 CARGO FLOOR SUPPORT NUT PLATE IS MIS-DRILLED AT RBL 4, WL 208. REMOVED FLOOR SUPPORT CHANNEL, LOCATED, DRILLED, AND INSTALLED NEW FLOOR SUPPORT P/N 65-25589-6, A18848, PO NR 1038952 REF SRM 51-30-5 PG 6, 51-30-2 PG 4.

Part: FRAME — CRACKED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

FWD LAV BS 312 FRAME CRACKED FROM O/B WEB FASTENER TO O/B RADIUS JUST BELOW S-13 R. FABRICATED 3 REPAIR PARTS FOR FWD LAV BS 312 FRAME, REF SRM 53-10-4 FIG 1, HEAT TREATED, TRACKING NR 2008-06-068, 2008-06-064, AND 2008-06-065, TREATED AND PRIMED AND INSTALLED REF SRM 51-10-2 PG 1-7, 51-30-2 PG-2, THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: STRINGER CLIP — CORRODED (ZONE 200) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

STRINGER CLIP ON STR 8L, AT FS HAS AREAS OF SURFACE CORROSION REMOVED AND REPLACED STR CLIP, STA 720B, STR 8L REF SRM 51-30-2 PGS 8-9 AND 32.

Part: SPAR — CORRODED (ZONE 600) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

PANEL JUST AFT OF RT WING AFT SPAR LOWER CHORD IS CORRODED FABRICATED NEW PANEL FROM JUST AFT OF RT WING SPAR LOWER CHORD REF. BOEING DWG 65-26797-3, TREATED AND PRIMED AND PAINTED REF SRM 51-10-2 PG 1-7, MM 51-20-151-7. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: STRINGER CLIP — CORRODED (ZONE 100) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

FWD LWR PIT BILGE, CORROSION ON INBD SIDE OF STR CLIP AT FWD SIDE OF FRAME AT STA 480 STR 26R. REMOVED AND REPLACED STR CLIP AT FWD LWR, PIT BILGE STA 480, STR 26R, FWD SIDE REF SRM 51-30-02 PG 1-5. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: FAIRING — CRACKED (ZONE 500) · airframe 50,447 hrs · 35,587 cycles

NR 4 FLAP TRACK MID FAIRING, CRACK ON INNER SIDE OF MLG FLYING DOOR FWD HINGE CUT OUT ON FAIRING. FABRICATED NEW DOUBLER, REF 727 51-20-1 PG 4, MATERIAL VERIFIED AS 7075-76 .050" REF BAC DWG 65-21795. REPLACEMENT MATERIAL VERIFIED AS 7075-76 .050" BY A-TAG NR A03906. TREATED AND PRIMED NEW DOUBLER. REF 727-51-2, PG 1. INSTALLED DOUBLER REF 727 SRM 51-30-2 PG1, TOP COATED REPAIR AREA OF NEW DOUBLER REF MM 51-20-013 PG -7. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: STRINGER — DAMAGED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

STRINGER 6L, MIS-DRILLED HOLE, BS 950D, UPPER WEB. REMOVED DAMAGE SECTION OF STRG 6L, BS 950D 10. FABRICATED REPAIR PARTS REF SRM 53-10-3 PG 5-9. TREATED AND PRIMED REPAIR PARTS REF SOPM 20-43-03 PG 3. INSTALLED REPAIR PARTS REF SRM 53-10-02 PG 1-8 AND SRM 51-30-02 PG 1-11. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — DAMAGED (ZONE 300) · airframe 50,447 hrs · 35,587 cycles

DRILL START NEXT TO RIVET, UNDER PANEL 9702, VERTICAL STABILIZER UPPER SKIN, DEPTH OUT OF LIMITS. FOUND WHILE ACCOMPLISHING N/R N00752, FOUND DAMAGE TO BE OUT OF LIMITS. VERIFIED REPAIR MATERIAL TO 2024-T-3 .080". FABRICATED REPAIR DOUBLER AND INSTALLED DOUBLER IN REF TO SRM 55-30-3 PG 1-2. TREATED AND PRIMED DOUBLER, IN REF TO SRM 51-10-2 PG 1-7, THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — GOUGED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

DURING INSPECTION OF NR 2 ENG INLET, RAN JLG INTO FUSELAGE AT STATION 1030 STRINGER 1R TO 3R, LIGHT SCRATCH AND GOUGE REMOVED DAMAGE PER REF SRM 53-30-3 FIG 3. NDT DAMAGE REMOVAL AND MATERIAL LOSS. PER REF 727 NDT MAN PART 6, 51-00-00 FIG 23. TOOL IDM-0065. NO DEFECTS NOTED MAT. LOSS .003 INCH, ORIGINAL MAT. .040 INCH THICK. .037 INCH REMAIN. PER 727 NDT MAN. PART 4 51-00-00 FIG 2 TOOL ID IN-22-0029. FABRICATED AND INSTALLED REPAIR DOUBLER PER REF SRM 53-30-3 FIG 3, SRM 51-10-2 AND 51-30-2. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: STRINGER CLIP — CRACKED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

STRINGER CLIP CRACKED, BS 950 E, STRINGER 6L. REPLACED STRINGER CLIP REF SRM 51-30-2 PG 1-7. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: STRINGER CLIP — CORRODED (ZONE 200) · corrosion level 2 · airframe 50,447 hrs · 35,587 cycles

CABIN, BS 720B AT 7L STRINGER CLIP HAS CORROSION REMOVED CLIP REF SRM 51-30-02 DRILLED UP NEW CLIP. INSTALLED NEW CLIP REF 51-30-02 PG 1-17, THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 50,447 hrs · 35,587 cycles

AFT CARGO DOOR LOWER FWD SKIN CRACKED CRACK ON EDGE OF SKIN (OUT OF LIMITS). REMOVED DAMAGED SKIN INSTALLED FILLER AND DOUBLER REPAIR REF SRM 52-00-3 PG 7-13, REPAIR CLASSIFIED AS A MAJOR.

Part: STRINGER CLIP — CRACKED (ZONE 200) · airframe 50,447 hrs · 35,587 cycles

CABIN, BS 520 S 3R CLIP CRACKED (STR CLIP) REMOVED CLIP REF SRM 51-30-02, DRILLED UP NEW CLIP. INSTALLED CLIP REF SRM 51-30-2 PG 1-17. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: STRINGER CLIP — CRACKED (ZONE 100) · airframe 50,447 hrs · 35,587 cycles

STRINGER CLIP CRACKED, BS 950D, STRINGER 5L REMOVED CRACKED STRINGER CLIP FROM BS 950D, STRINGER 5L, AND INSTALLED A NEW STRINGER CLIP AT SAME LOCATION, REF SRM 51-30-02 P 1-32. THIS REPAIR IS CLASSIFIED AS A MAJOR REPAIR.

Part: DOOR FRAME — CORRODED (ZONE 200) · corrosion level 2 · airframe 49,995 hrs · 35,221 cycles

CORROSION FOUND BELOW LOWER DOOR STOP FITTING ON LT FWD DOOR, FRAME 14 LT, T1. REPAIR WAS PERFORMED BY SMOOTH BLEND OUT OF CORROSION IAW EA 6-5312-95915 AND RAS/043491/005/2006 ISSUE A.

Part: FUEL CONTROL — UNKNOWN (ENGINE) · airframe 48,763 hrs · 34,219 cycles

ON TAKEOFF ROLL, AFTER TAKEOFF POWER WAS SET, N1 AND EPR INCREASED WITHOUT ANY PILOT INPUT. THE NUMBER 3 THROTTLE WAS ADVANCED AHEAD OF OTHER THROTTLES BY 1 KNOB WIDTH. COMPLETED INSTALL OF FUEL CONTROL AND PUMP IAW 727-2 00AMM AND PWMM 73-11-01.

Part: SKIN — CORRODED (ZONE 100) · airframe 48,721 hrs · 34,188 cycles

AFT PIT STA 1050 RBL 10 SKIN IS CORRODED. REMOVED DAMAGE, FABRICATED, ALODINED, PRIMED AND INSTALLED FUSELAGE SKIN REPAIR AT STA 1050 FROM RBL10 TO RBL 12 ALL IAW FX B727 SRM 53-30-3 FIG 3, 51-10-6, 51-30-2 AND 51-10-2.

Part: STRINGER — CRACKED (ZONE 100) · airframe 48,721 hrs · 34,188 cycles

STRINGER AT FS 360 - 420 S18R IS CRACKED. REMOVED DAMAGE, FABRICATED, ALODINED, PRIMED AND INSTALLED STRINGER REPAIR AT STA 360 - 420 ON S18R ALL IAW FX B727 SRM 53-10-3 FIG 2 AND 51-10-2.

Part: REPAIR — NONE (ZONE 100) · airframe 48,721 hrs · 34,188 cycles

REPAIR DOUBLER AT STA 370, STRINGER STR 18-L , REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR DOUBLER AT STA 370 STR 18-L WAS INSTALLED USING FAA APPROVED DATA. DOUBLER WAS REMOVED AND INCORPORATED TO ADJACENT DOUBLER. THIS IS A MAJOR REPAIR.

Part: FLOORBEAM — CRACKED (ZONE 100) · airframe 48,721 hrs · 34,188 cycles

E/E COMPARTMENT RIGHT SIDE AT STA BS 420, FLOORBEAM CRACKED AROUND FASTENER AT RBL 25. REMOVED DAMAGED AREA AND FABRICATED 2 EACH ANGLES AND 1 EACH FILLER IAW B-727 SRM 53-10-8 FIGURE 1. ALODINED AND PRIMED BARE METAL IAW B-727 SRM 51-10-2. INSTALLED REPAIR IAW B-727 SRM 53-10-8 FIGURE 1.

Part: REPAIR — MISINSTALLED (ZONE 100) · airframe 48,721 hrs · 34,188 cycles

REPAIR DOUBLER AT STA BS 1140,STR 25-L. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR DOUBLER AT STA BS 1140 STR 25-L FOUND NOT IN COMPLIANCE WITH B-727 SRM 53-30-3 FIGURE 1. REMOVED DOUBLER IAW B-727 SRM 51-30-2. FABRICATED REPLACEMENT DOUBLER IAW B-727 SRM 53-30-3 FIGURE 1. ALODINED AND PRIMED BARE METAL IAW B-727 SRM 51-10-2. INSTALLLED REPAIR IAW B-727 SRM 53-30-3 FIGURE 1.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 48,721 hrs · 34,188 cycles

FOUND CENTER WING TANK LOWER SKIN PANEL HAS INTERGRANULAR CORROSION IN THE LEFT UPPER A/C PLENUM BETWEEN STA BS 795 AND 810 BETWEEN LBL 25 AND LBL 35. REMOVED ALL THE CORROSION,FABRICATED AND INSTALLED EXTERNA L REPAIR DOUBLER,2 EA INTERNAL REPAIR DOUBLER,3EA STRAPS AND 3 EA FILLERS IN SKIN PANEL BETWEEN S-3C AND S-5C.ALSO,FLAP PEENED,SPOTTED FACE THE REWORK AREAS, HIGH INTERFERENCE COLD WORKED ALL FASTENERS HOLES,APPLIED BMS 3-23,ALL IAW FEDEX EA 7-5710-95160.

Part: CONTROL CABLE — BROKEN (AILERONS) · airframe 48,308 hrs · 33,826 cycles

DURING POSTFLIGHT INSPECTION FOUND LEFT INBOARD AILERON CABLE BROKEN. INSPECTED CABLE PULLEYS NO FURTHER DAMAGE FOUND AT THIS TIME. FOUND CABLE BROKE IN HALF HANGING FROM THE LEFT WHEEL WELL JUST ABOVE APU FIRE BOTTLE AREA. A/C ARRIVED WITH INBOARD AILERON IN THE UP POSITION AND ALL OTHER CONTROL SURFACES IN THE DOWN POSITION. REMOVED AND REPLACED LT AILERON BUSS CABLE RUN ABSA(T) PER 727-200 MM 20-10-020-4. PERFORMED ADJUSTMENT AND TEST OF AILERON BUSS SYSTEM PER 727-200 MM 27-10-000- 5. OPS CHECKS GOOD, OK FOR SERVICE.

Part: SKIN — CRACKED (FUSELAGE) · airframe 48,063 hrs · 33,625 cycles

RIGHT FUSELAGE SKIN HAS BULGED AREA AT FS 380-400 STR 23R-24R. REWORKED AREA AND NDT FOUND CRACKED. REPAIRED IAW SRM 53-30-3 FIG 13.

Part: SKIN — LIGHTNING STRIKE (FUSELAGE) · airframe 46,507 hrs · 32,413 cycles

N00177 LIGHTNING STRIKE BS 350 BETWEEN STR 2L AND STR 3L. FOUND LIGHTNING STRIKE DAMAGE TO BE OUT OF LIMITS. REPAIRED DAMAGE IAW SRM 53-30-3 AT BS 350 BETWEEN STR 2L AND 3L.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,507 hrs · 32,413 cycles

CORROSION ON FLOOR SUPPORT BS 344, LBL 45, WL 208. CORROSION ON FLOORBEAM BS 344, LBL 45, WL 208. REPAIRED FLOORBEAM IAW SRM 53-10- 1, 51-10-1, 51-30-2 & 53-10-8.

Part: SKIN — DENTED (FUSELAGE) · airframe 46,507 hrs · 32,413 cycles

EXTERIOR SKIN HAS DENT AT BS 203 RBL 14 STR 26R. SKIN DENT BS 203, RBL 14, STR 26R OUT OF LIMITS PER SRM 53-30-1. REPAIRED SKIN PER SRM 53-30-3.

Part: SKIN — LIGHTNING STRIKE (FUSELAGE) · airframe 46,507 hrs · 32,413 cycles

EXTERIOR SKIN HAS SEVERAL LIGHTNING STRIKES FROM BS 334 TO BS 351 STR 25R TO STR 27R. REMOVED DAMAGE ON 7EA LIGHTNING STRIKES BS 334-351, STR 25-27 RT 5EA AREA. REMOVED DAMAGE BY DRILLING OUT DAMAGE AND INSTALLING FASTENERS PER SRM 53-30-3, 1EA AREA FOUND TO BE WITHIN LIMITS BY BLENDING OUT DAMAGE, 1EA AREA REPAIRED BY CUTTING OUT DAMAGE IN 1 X 1 INCH AREA AND REPAIRING PER SRM 53-30-3, FIG 1.

Part: FRAME — DENTED (FUSELAGE) · airframe 46,507 hrs · 32,413 cycles

AFT CARGO BAY BS 990 FRAME IS DENTED AT STR 26L. REPAIRED FRAME AT BS 990, STR 26L PER SRM 51-40-3, FIG 1.

Part: FRAME — DENTED (FUSELAGE) · airframe 46,507 hrs · 32,413 cycles

FRAME DENTED BS 520 STR 24L. INSPECTED DENTS AT BS 520, STR 24L. FOUND TO BE OUT OF LIMITS PER SRM 53-10-1, FIG 1, DETAIL II, NOTE [S]. CUT OUT AND REPAIRED DAMAGE PER SRM 51-40-3, FIG 1.

Part: FRAME — DENTED (FUSELAGE) · airframe 46,507 hrs · 32,413 cycles

AFT CARGO BAY BS 970 FRAME IS DENTED AT STR 26L AND 25L AND 23L. REPAIRED FRAME AT BS 970, STR 25L - 26L AND STR 23L PER SRM 51-40-3 FIG 1.

Part: FRAME — DENTED (FUSELAGE) · airframe 46,507 hrs · 32,413 cycles

FRAME DENTED BS 520 STR 22R TO 24R. REPAIRED FRAME BS 520, STR 22R TO 24R PER SRM 51-40-03.

Part: FRAME — DENTED (FUSELAGE) · airframe 46,507 hrs · 32,413 cycles

FRAME DENTED BS 580 BETWEEN STR 23L TO STR 5L. CUT OUT DAMAGED AREA ON BS 580 FRAME, 2 AREAS BETWEEN STR 23L AND 25L, 1.4 X 1 AND 3.8 X 1 INCH. FABRICATED REPAIR DOUBLER. ALODINED, PRIMED AND INSTALLED PER FED EX SRM 51-40-3.

Part: FRAME — DENTED (FUSELAGE) · airframe 46,507 hrs · 32,413 cycles

AFT CARGO BAY BS 950F FRAME IS DENTED IN 3 PLACES BETWEEN STR 26L AND 25L. REPAIRED FRAME AT BS 950F BETWEEN STRS 25L & 26L PER SRM 51-40-3 FIG 1.

Part: FRAME — DENTED (FUSELAGE) · airframe 46,507 hrs · 32,413 cycles

FRAME DENTED BS 540 STR 24L. CUT OUT DENTED SECTION OF FRAME STR 24L BS 540 2.2 X 1 X .050 INCH. FABRICATED REPAIR AND INSTALLED IAW SRM 51-40-3.

Part: FRAME — DENTED (FUSELAGE) · airframe 46,507 hrs · 32,413 cycles

FRAME DENTED BS 560 STR 22L TO 24L. REMOVED DAMAGED AREA OF DENTED FRAME BS 560, STR 22L TO 24L. FABRICATED, ALODINED, PRIMED AND INSTALLED REPAIR PART. ALL IAW SRM 53-10-1 FIG 1, 51-40-3 FIG 1, 51-20-04 PGS 3 AND 4, FED EX MM 51-20-000-7.

Part: FRAME — DENTED (FUSELAGE) · airframe 46,507 hrs · 32,413 cycles

FRAME DENTED BS 500 STR 22R. FRAME AT BS 500, STR 22R DENT OUT OF LIMITS PER SRM 53-10-1. REPAIRED FRAME PER SRM 51-40-3.

Part: FRAME — DENTED (FUSELAGE) · airframe 46,507 hrs · 32,413 cycles

FRAME DENTED BS 500 STR 24L. REPAIRED DENTED FRAME AT BS 500, STR 24L PER SRM 51-40-3.

Part: SENSOR — INOPERATIVE (MLG UP&DOWN LOCK) · airframe 46,418 hrs · 32,347 cycles

ON TAKE OFF, LANDING GEAR LEVER WOULD NOT RETRACT PAST THE OFF DETENT. PERFORMED QRH PROCEDURE FOR LANDING GEAR LEVER LATCH FAILED TO RELEASE. T/S PER 727-200 WDM 32-31-01. OHM CHECKED ENTIRE AIR & GROUND SENSOR CIRCUITS FROM L/G ACCESSORY RACK PLUG AND CONFIRMED AN OPEN CIRCUIT INSIDE THE AIR SENSING PROX SWITCH WHEN COMPARED TO A KNOWN NEW SWITCH. R&R'D THE AIR SENSING PROX SWITCH SENSOR LOCATED ON LT GEAR PER 727-200 MM 32-09- 221-4 & OPS CHECKED AIR GROUND SENSE & LEVER LOCK CIRCUITS PER MM 32-09-221-5 AND 32-31-016-4. AIR SENSE MODE NOW FULLY FUNCTIONAL. LEVER LOCK RELEASES ON TEST & L/G LEVER MOVES UP.

Part: INDICATOR — ILLUMINATED (MLG) · airframe 46,301 hrs · 32,260 cycles

RETRACTED GEAR, L AN R MAIN GEAR UNSAFE-RED, NOSE GEAR GREEN. EXTENDED GEAR - ALL 3 LANDING GEAR SAFE -GREEN PER CREW CONVERSATION : NOSE GEAR RETRACTED NORMAL AND NO GREEN LIGHT ON (VARIES FROM ACTUAL WRITE UP). ADDITIONAL INFO, GEAR WAS DROPPED TO SLOW A/C FOR RAPID DESCENT GEAR EXTENDED NORMALLY.AT ABOUT 20 MILES OUT IT WAS DECIDED TO RETRACT GEAR UNTIL CLOSER TO RUNWAY. WHEN RETRACTED NOSE GEAR CAME UP AND LIGHT OUT NORMAL. MAIN GEAR WENT TO INTRANSIT /UNSAFE AND AFTER A REASONABLE TIME GEAR AND DOOR LIGHTS STAYED ON PER BOOK GEAR WAS SEL DOWN AND THREE GREEN ON... INSPECTED ALL LANDING GEAR AND INDICATION COMPONENTS JACKED A/C CYCLED LANDING GEAR MULTIPLE TIMES-NO DEFECTS NOTED.

Part: INDICATOR — FAULTY (COCKPIT) · airframe 45,896 hrs · 31,949 cycles

NR 2 OIL PRESSURE AT 28 PSI IN FLIGHT, SHUT DOWN NR 2 ENGINE, WINDMILLED IN FLIGHT FOR 25 MINUTES WITH 28 PSI OIL PRESS INDICATOR. REMOVED AND REPLACED OIL PRESSURE INDICATOR IAW MM. LEAK AND OPS CHECK, OK FOR SERVICE.

Part: FIRE WARNING — MALFUNCTIONED (COCKPIT) · airframe 45,469 hrs · 31,590 cycles

ON DESCENT, RECEIVED ENGINE FIRE WARNING BELL AND ENGINE FIRE WARNING LIGHT WITH NO ASSOCIATED FIRE PULL HANDLE LIGHTS. ALL ENGINE PERFORMANCE PARAMETERS WERE NORMAL. FOLLOWED CHECKLIST. FIRE WARNING SYSTEM TEST SATISFACTORY. CONTINUED DESCENT TO LANDING AT DESTINATION. COMPLIED WITH ENGINE FIRE DETECTION IAW B727-200 AMM 26-11-000-5. ALSO COMPLIED WITH CARGO SMOKE DETECTION TEST IAW B727-200 AMM 26-16-001-5, NO DEFECTS NOTED. SYSTEM OPERATES NORMAL.

Part: FIRE WARNING — MALFUNCTIONED (COCKPIT) · airframe 45,469 hrs · 31,590 cycles

ON DESCENT, RECEIVED ENGINE FIRE WARNING BELL AND ENGINE FIRE WARNING LIGHT WITH NO ASSOCIATED FIRE PULL HANDLE LIGHTS. ALL ENGINE PERFORMANCE PARAMETERS WERE NORMAL. FOLLOWED CHECKLIST. FIRE WARNING SYSTEM TEST SATISFACTORY. CONTINUED DESCENT TO LANDING AT DESTINATION. T/S AND COMPLIED WITH ENGINE FIRE DETECTION IAW B727-200 AMM 26-11-000-5. ALSO COMPLIED WITH CARGO SMOKE DETECTION TEST IAW B727-200 AMM 26-16-001-5, NO DEFECTS NOTED. SYSTEM OPERATES NORMAL.

Part: CLAMP — LOOSE (NR 2 ENGINE) · airframe 44,595 hrs · 30,848 cycles

DURING CLIMB AT 8000 FT MSL WITH PWR SET NR 3 ENG FIRE LIGHT ILLUMINATED ALONG WITH FIRE BELL. NR 3 THROTTLE WAS RETARDED TO IDLE FIRE LIGHT AND BELL WENT OUT. FOUND LOOSE CLAMP ON 13TH STAGE PNEUMATIC BALL JOINT IN PYLON. TORQUED CLAMP, LEAK CK GOOD.

Part: ENGINE — FAILED (NR 2)

AT 200 - 300 FT ABOVE GROUND LEVEL NR 2 ENGINE FAILED WITH VIBRATION, NO FIRE IND. FIRED NR 1 FIRE BOTTLE. *S/D* REMOVED AND REPLACED NR 2 ENGINE AND NR 1 FIRE BOTTLE MM 26-21-001-4 & 71-00-000-4-1. ALSO FEDEX WORK CARDS 70T0002 & 70T0301-02.

Part: BUSHING — MISSING (NR 3 ENGINE)

NR 3 ENGINE STRUT LIGHT DIMLY ILLUM. REPLACED BUSHING AND SECURED FIRE LOOP CLAMP. RAN ENG PER JET RUN HDBK. NO FAULTS FOUND. OK FOR SERVICE.

Part: DETECTOR — MALFUNCTIONED (NR 3 ENGINE)

NR 3 ENGINE STRUT OVERHEAT FAINTLY ILLUM DURING DESCENT. RAN NR 3 ENG PER JET RUN HANDBOOK CHAP 5, NO DISCREPANCY NOTED. INSP NR 3 ENG STRUT, NO DISCREPANCY NOTED.

Part: WARNING LIGHT — ILLUMINATED (NR 1 & 3 ENGINE)

NR 1 & 3 ENGINE STRUT OVERHEAT LIGHT BOTH FLICKERED 5 MIN AFT T/O. CHECKED NR 1 & 2 ENG OVERHEAT SENSORS FOR PROPER INSTALL PER MM 26-14-000-1. ALL IND SAT DURING RUN AS PER JET RUN HANDBOOK. AC OK TO CONTINUE.

Part: SWITCH — DIRTY (LANDING GEAR)

ON T/O LANDING GEAR RED DOOR LIGHT AND AMBER NOSE GEAR LIGHT REMAIN ON WITH GEAR UP. COMPLIED WITH RED TABS AND LIGHT REMAIN ON. CLEANED DOOR AND GEAR SWITCHES, CHECKED FOR ADJUSTMENT AND ALL INDICATIONS NORMAL.

Part: VALVE — INOP (MAIN GEAR)

GEAR HANDLE PLACED IN OFF POSITION, NOSE GEAR DOOR LIGHT AND MAIN GEAR DOOR LIGHT ILLUM. *S/D* REMOVED AND REPLACED LANDING GEAR ASSY UNIT PER MM 32-09-221. REMOVED AND REPLACED MLG SEL VALVE PER 32-31-03-4. AC OK TO CONTINUE.

Part: OVERHEAT LOOP — OUT OF POSITION (NR 3 STRUT)

ENGINE NR 3 STRUT OVERHEAT MOMENTARILY FLICKERED FOR 1 SEC ON APPROACH. INSP NR 3 ENGINE STRUT FOR LOOSE CLAMPS AND ADEQUATE CLEARANCE OF DETECTOR LOOP. TIGHTENED SEV CLAMPS PER MM 26-14-1. RAN ENG PER JET RUN HDBK, NO STRUT OVERHEAT LIGHT ILLUM. ALL INDICATIONS NORMAL.

Part: BEAM — CORRODED (NR1 CARGO DOOR)

NR0402 AND 020, NR 1 CARGO DOOR LWR TRANSVERSE BEAM I/B EXTRUSION IS CORRODED BEYOND LIMITS ABOVE LWR LIGHT ASSY. *S/D* REMOVED NR 1 CARGO DOOR LOWER TRANSVERSE BEAM INBOARD, FABRICATED NEW BEAM AND INSTALLED PER FEDEX SRM 51-10-1, 51-30-2.

Part: HINGE LUGS — CORRODED (NR 2 LE FLAP)

NR0088 AND 021, NR 2 K-FLAP CENTER HINGE LUGS UPPER AND LOWER FASTENERS HAVE CORROSION. *S/D* REMOVED K-FLAP AND REPLACED IAW FEDEX MM 27-81-1.

Part: FLAP — CORRODED (NR 4 LE FLAP)

NR0078 AND 018, NR 4 K-FLAP O/B HINGE LUGS CORRODED UNDER FASTENERS. *S/D* REMOVED CORRODED NR 4 K-FLAP AND INSTALLED NEW NR 4 K-FLAP IAW FEDEX MM 27-81-1, FUNCTIONAL CHECK GOOD IAW FEDEX MM 27-81-11.

Part: TEAR STRAP — CORRODED (BS 1148)

NR0156 AND 019, CORROSION (C53-113-10, -2) BETWEEN SKIN AND FRAME SHEAR TIE AT BS 1148 RBL 23 WL 154. *S/D* REPAIRED TEAR STRAP PER FEDEX SRM 53-30-04, REPAIRS FWD AND AFT SHEAR TIES PER FEDEX SRM 53-10-04.

Part: STRINGER — CORRODED (BS 720)

NR0224 AND 017, CORROSION (C53-113-01) AROUND FASTENERS INSIDE CHANNEL OF STR 27L AT BS 720F PLUS 17.

Part: T-CLIP — CORRODED (BS 1177)

NR0151 AND 016, CORROSION (C53-113-10, -2) ON T-CLIP AT BS 1177 RBL 32 WL 170. *S/D* REMOVED AND REPLACED T-CLIP AT BS 1177 RBL 32 WL 170 IAW FEDEX SRM 53-10-4.

Part: SKIN — CORRODED (BS 720)

NR0228 AND 011, CORROSION (C53-113-01, -1) ON INNER SURFACE OF SKIN BS 720B TO 720B PLUS 3 LBL 3 TO RBL 3 WL 148.5. *S/D* REMOVED CORROSION FROM INNER SURFACE OF SKIN PANEL NR 3363. FOUND TO BE OUT OF LIMITS PER FEDEX SRM 53-10-1. FABRICATED TREATED AND INSTALLED PANEL NR 3363 IAW FEDEX SRM 53-30-1.

Part: STRINGER — CORRODED (BS 720)

NR 0225 AND 013. CORROSION C53-113-01(1) AROUND FASTENERS INSIDE CHANNEL OF STR 27R AT BS 720F + 17. ****S/D***** FOUND TO BE OUT LIMITS. REMOVED CORRODED SECTION OF STR 27B. FABRICATED AND INSTALLED REPAIR PARTS IAW FEDEX SRM 53-10-3.

Part: SHEAR TIE — CORRODED (BS 1130)

NR0158 AND 014, CORROSION (C53-113-10, -2) ON FRAME WEB AND SHEAR TIE AT BS 1130 RBL 8 TO 11 WL 147. *S/D* REMOVED CORROSION FROM FRAME WEB AND FOUND TO BE IN LIMITS PER FEDEX SRM 51-10-1. REMOVED, FABRICATED AND INSTALLED SHEAR TIE IAW FEDEX SRM 51-10-6 AND 53-10-1.

Part: SKIN — DENTED (BS 189)

NR0447 AND 010, DENT AT BS 189 STR 28L WAS FOUND TO BE OUT OF LIMITS. *S/D* REPAIRED SKIN AT BS 189 STR 28L PER FEDEX SRM 53-30-3.

Part: SPLICE PLATE — CORROSION (BS 481)

NR0227 AND 012, CORROSION (C53-113-01, -1) ON BUTT SPLICE DOUBLER BS 481 BETWEEN STR 28L AND R. *S/D* BLENDED CORROSION DOUBLER, FOUND TO BE OUT OF LIMITS. FABRICATED DOUBLER AND FILLER AND INSTALLED PER FEDEX EA 7-5310-29235.

Part: ANGLE — CORRODED (CARGO DOOR)

NR0307 AND 015, NR 2 CARGO DOOR SECOND TRANSVERSE BEAM FROM BOTTOM OF DOOR I/B L-ANGLE IS CORRODED. *S/D* REMOVED TRANSVERSE BEAM, FABRICATED NEW AND INSTALLED IAW FEDEX DRAWING 65-57204.

Part: SHEAR TIE — CORROSION (BS 1130)

NR0159 AND 009, CORROSION (C53-113-10, -2) ON FRAME WEB AND SHEAR TIE AT BS 1130 LBL 1 TO 4 WL 147. *S/D* REMOVED CORROSION ON FRAME WEB, FOUND TO BE WITHIN LIMITS PER FEDEX SRM 53-10-1. REMOVED AND REPLACED SHEAR TIE IAW FEDEX SRM 51-10-1 AND 51-20-1.

Part: SHEAR TIE — CORRODED (BS 1148)

CORROSION (C53-113-10, -2) ON FRAME WEB AND SHEAR TIE AT BS 1148, RBL 1 TO 5 AT WL 150. *S/D* REPAIRED FRAME WEB AND SHEAR TIE AFT AND FWD SIDE AT BS 1148 LBL 1 TO 5 WL 150 IAW FEDEX SRM 53-10-4.

Part: SHEAR TIE — CORRODED (BS 1148)

NR0162 007, CORROSION (C53-113-10, -2) ON FRAME WEB AND SHEAR TIE AT BS 1148 RBL 7 TO 13 AT WL 150.

Part: SHEAR TIE — CORRODED (BS 1130)

NR0157 008, CORROSION (C53-113-10, -2) ON FRAME WEB AND SHEAR TIE AT BS 1130, RBL 4 TO 1 AT WL 147.

Part: SHEAR TIE — CORRODED (BS 1148)

CORROSION (C53-113-10, -2) ON FRAME WEB AND SHEAR TIE AT BS 1148, RBL 9 AT WL 150. *S/D* REPAIRED FRAME WEB AND SHEAR TIE AT BS 1148 RBL 9 WL 150 IAW FEDEX SRM 53-10-4.

Part: FRAME — CRACKED (BS 1148)

NR0132 AND 004, CRACKED FRAME AROUND NUTPLATE HOLE AT BS 1148 LBL 28 WL 160. *S/D* REMOVED DAMAGED AREA IN FRAME AT BS 114B LBL 28, WL 160, FABRICATED REPAIR PARTS AND INSTALLED IAW FED EX SRM 51-40-2.

Part: FORE FLAP — DELAMINATION (RT TE FLAP)

DELAMINATION ON R/W I/B FORE FLAP UPPER SURFACE ABOVE CENTER TRACK. *S/D* REPAIRED R/W I/B FORE FLAP UPPER SURFACE ABOVE CENTER TRACK IAW FEDEX SRM 51-40-6 FIG 36.

Part: SKIN — DELAMINATION (RT TE FLAP)

NR 0324, 003 DELAMINATION ON R/W O/B AFT FLAP ABOUT 5 INCHES FROM I/B END. *S/D* REPAIRED DELAMINATION ON R/W O/B AFT FLAP 5 INCHES FROM I/B END IAW FEDEX SRM 51-40-06 FIG 40.

Part: SKIN — DELAMINATION (RT TE FLAP)

NR 0322, 001 DELAMINATION ON R/W I/B FLAP UPPER SURFACE 48 INCHES FROM I/B END. *S/D* REPAIRED DELAMINATION ON R/W I/B AFT FLAP UPPER SURFACE 48 INCHES FROM I/B END IAW FEDEX SRM 51-40-06, FIG 40 PG 75.

Part: MODULE — FAILED (LE FLAPS)

NR 1 LED SLAT, LT WING DID NOT RETRACT WHILE GOING FROM FLAP 5 TO FLAP 2. AMBER LIGHT ON FRONT PANEL WAS ON AND S/O PANEL IND AMBER, INTRANSIT RED TABS COMPLETED WITH SAME IND. ALSO, WING ANTI-ICE ATTEMPTED. NR 1 SLAT FUNCTIONS NORMAL, POSITION SWITCH INOPERATIVE. APPLIED HEAT TO NR 1 RETRACT SWITCH, NO HELP. INSTALLED SWITCH CONTACT JUMPER, NO HELP. REPLACED L/E POS CONTROL MODULE, RAN FLAPS THROUGH NUMEROUS CYCLES AND ALL IND NORMAL.

Part: ACTUATOR — MALFUNCTIONED (NR 1 LE SLAT)

NR 1 LT WING SLAT DID NOT RETRACT ON SCHEDULE. NR 1 SLAT OPS CHECK NORMAL ON EXTEND AND RETRACT. INSTALLED SLAT SWITCH JUMPER CABLE. LIGHT INDICATIONS NORMAL. RETURN JUMPER CABLE TO SECOND OFFICER'S DESK WHEN SWITCH REPLACED. REPLACED L/E SLAT ACTUATOR PER 27-80-01 COMPLIED WITH REQ ITEMS INSPECTION. OPS CHECKED, LEAK CHECKED OK. CLOSED ALL PANELS.

Part: HYD SYST — REQD SERVICE (A-HYD SYST)

UPON GEAR RETRACTION, HYD A-SYS QTY, FELL FROM 3.5 TO 1.625 GALLONS. UPON BLOCK, FOUND 3 GALLONS IN SYS, BELIEVE AIR IN SYS FROM PREVIOUS MX REF WRI 29-10/378. SERVICED HYD AS REQ, CYCLED FLT CONTROLS SEVERAL TIMES AND NO LEAKS OR QTY DROP NOTED. OK FOR SERVICE.