N223FE

Part: TUBE — BROKEN (HYD SYSTEM) · airframe 60,883 hrs · 37,753 cycles

LOST HYD SYS A INFLIGHT, ACCOMPLISHED PHASE ONES AND QRH PROCEDURES. NO FLUID OR PRESSURE REMAINED. FLUID SHUTOFF SWITCHES CLOSED. FOUND HYD TUBE BROKEN. REPLACED TUBE IAW AMM 29-11-000-1.

Part: PACKING — LEAKING (OIL SYSTEM) · airframe 60,764 hrs · 37,703 cycles

LOST OIL QUANTITY ON THE NR 1 ENGINE DURING INITIAL CLIMB. QRH PROCEDURE WAS FOLLOWED. THE OIL QUANTITY DECREASED TO ZERO.THE OIL PRESSURE DECREASED BELOW 40PSI AND THE NR 1 LOW OIL PRESSURE LIGHT ILLUMINATED. THE NR 1 ENGINE WAS SECURED FOLLOWING QRH PROCEDURES. THE ENGINE WINDMILLED FOR APPROX.3 MINUTES DURING APPROACH AND LANDING. THE OIL PRESSURE WAS NOT MONITORED DURING THE APPROACH AND LANDING. REPLACED FUEL/OIL COOLER INLET ELBOW PER AMM 79-20-001-4 AND 20-80-001-2. INSTALLED NEW SEAL ASSY AND RECONNECTED FUEL/OIL INLET TUBE PER MM 79-20-011-4. RAN NR 1 ENGINE PER JRH CH4 AND MM 72-00-00 TO 80% N2 FOR 5 MINUTES, THREE TIMES. OIL PRESSURE STEADY AT 50 PSI AND OIL QUANTITY STEADY. OIL TEMP STEADY AT 80C. OPENED COWLING AND PHYSICALLY CHECKED ENTIRE ENGINE AND OIL COOLER LINE FOR LEAKS. LEAK CHECK GOOD.

Part: LIGHT — FAILED (EXTERIOR) · airframe 60,480 hrs · 37,548 cycles

THE EXTERIOR EMERGENCY ESCAPE SLIDE LIGHT IS INOPERATIVE. FOUND STANDING WATER IN LIGHT ASSY AND LIGHT SOCKET CORRODED. REMOVED LIGHT ASSY. RETERMINATED WIRING FOR LIGHT ASSY, REF CHP 20 SMP AND WDM 31-51-01. REPLACED AND TESTED LIGHT ASSY, OP CHECKED GOOD, ALL MAINTENANCE IAW MM 33-50-041, ACFT RELEASED FOR SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 60,475 hrs · 37,544 cycles

EMERGENCY EXIT LIGHTS OVER COCKPIT DOOR INOPERATIVE. REPLACED 4 BATTERIES OVER THE ENTRY AND CONTROL CABIN DOORS IAW MM 33-50-101-2-0.

Part: LIGHT — CORRODED (EXTERIOR) · airframe 60,475 hrs · 37,544 cycles

THE EXTERIOR EMERGENCY ESCAPE SLIDE LIGHT IS INOPERATIVE. REMOVED AND REPLACED LIGHT ASSY PER AMM 33-50-041 OPS CHECKS GOOD.

Part: LATCH — WEAK (PAX DOOR) · airframe 60,194 hrs · 37,390 cycles

FWD ENTY DOOR LIGHT ILLUMINATED ON LANDING. WENT TO OPEN DOOR AT GATE, DOOR WAS CRACKED OPEN. TROUBLESHOOTING FWD ENTRY DOOR OPERATION IAW AMM 52-11-001-1-0. PERFORMED INSP AND TEST OF FWD ENTRY DOOR IAW 52-11-001-1-0. NO DISCREPANCIES NOTED. NO PRIOR HISTORY OF SOFT UNLATCHING. OK FOR SERVICE.

Part: WIRE — DAMAGED (NR 3 ENGINE) · airframe 59,762 hrs · 37,190 cycles

TEST FLIGHT: SHUTDOWN ENG NR 3 IAW QRM DUE TO HIGH OIL TEMP. ENG SHUTDOWN AT 2325 Z. ENG MATAINED 5 PSI TO TOUCHDOWN. OIL PRESS & QUANITY PRIOR TO SHUTDOWN WAS NORMAL. REPAIRED WIRE W198-060-18 IAW FX SWPM 20-10-13 AND WDM 79-33-01 PERFORMED. OPS CHECK OF NR 3 ENGINE OIL TEMP IAW FX MM 79-34-011-5-0. SYS CHECK GOOD IAW FX MM 79-34 011-5-0. FINAL CLOSED.

Part: SKIN — DAMAGED (BS 1243) · airframe 59,760 hrs · 37,180 cycles

MISSING MATERIAL STA 1243, CUT-OUT TO AIRSTAIR HINGE POINT RT SIDE. REMOVED REPAIR DOUBLER IAW SRM 51-30-2, REV 103. CUT OUT DAMAGED AREA (DIM. 7" X 1.8750") IAW SRM 51-10-1. FABRICATED SKIN FILLER FROM 2024-T3 .040" (DIM. 12.5" X 2.3") AND DOUBLER FROM 2024-T3 .050" (DIM. 6.8" X 5.5") IAW SRM 53-30-3, FIG 26. INSTALLED FILLER AND DOUBLER IAW SRM 51-30-5.

Part: FITTING — DAMAGED (BS 480) · airframe 59,760 hrs · 37,180 cycles

CUT OUT BS 480 AFT FITTING HAS CORNER HOLE WITH NO ED. REMOVED DAMAGED AFT FITTING, FABRICATED NEW FITTING 7 INSTALLED NEW FITTING AT BS 480 IAW DWG NR 53FX1286 & SRM 51-10-2 & SRM 51-30-2.

Part: FITTING — DAMAGED (BS 620) · airframe 59,760 hrs · 37,180 cycles

CUT OUT UPPER BS 620 FITTING HAS 2 ELONGATED HOLES. REMOVED DAMAGED, FITTING, FABRICATED NEW FITTING & INSTALLED NEW FITTING AT BS 620 IAW DWG. NR 53FX1286 & SRM 51-10-2 & SRM 51-30-2.

Part: FITTING — DAMAGED (BS 620) · airframe 59,760 hrs · 37,180 cycles

CUT OUT UPPER FITTING BS 620 HAS DOUBLE DRILLED .2500" HOLE. REMOVED DAMAGED UPPER FITTING, FABRICATED & DRILLED NEW FITTING, INSTALLED NEW FITTING AT BS 620 MCD AREA IAW DWG NR 53FX1286 & SRM 51-30-2, SRM 51-10-2.

Part: FITTING — DAMAGED (BS 480) · airframe 59,760 hrs · 37,180 cycles

CUT OUT UPPER BS 480 FWD FITTING HAS 1 ELONGATED HOLE. REMOVED DAMAGED FITTINGS, FABRICATED NEW FITTING & INSTALLED FITTING AT BS 480 IAW DWG. NR 53FX1286 & SRM 51-10-2 & SRM 51-30-2.

Part: SKIN — DENTED (BS 1352 S12-13L) · airframe 59,760 hrs · 37,180 cycles

DENT EXTERIOR SKIN, SECTION 48, LT SIDE, STA 1352, STR 12L-13L CUTOUT DAMAGED AREA ON EXTERIOR SKIN SECTION 48 LT STA 1352, STR 12L-13L IAW SRM 54-30-3, DIMENSION 1" X 1". FABRICATED DOUBLER & FILLER IAW SRM 54-30-3, FIG 7, INSTALLED DOUBLER , FILLER, & RAIN DEFLECTOR IAW SRM 51-30-2.

Part: FRAME — DAMAGED (BS 783) · airframe 59,760 hrs · 37,180 cycles

OVERWING RT FRAME AT BS 783, 3RD HOLE BELOW FLOOR IS AT MAX SIZE IAW EO AND STILL HAS CRACK INDICATION. CRACK INDICATION WAS FOUND TO BE DRILL START, COMPLIED WITH HFEC INSPECTION IAW NDTM, PT.6 , 51-00-00 FIG. 23, NO CRACK NOTED. FABRICATED SPLICE ANGLE, 2 REPAIR ANGLES, CHANNEL, SPLICE ANGLE, REPAIR STRAP, SPLICE REPAIR, AND 4 RADIUS FILLERS IAW DWG 65C36280 AND SRM 51-20-1 FIG 7 AND EO 7-5310-7-3367 PT9 & INSTALLED IAW DWG 65C36280 AND EO 7-5310-7-3367 PT9.

Part: SKIN — CORRODED (BS 820) · corrosion level 2 · airframe 59,760 hrs · 37,180 cycles

WING CENTER SECTION UPPER EXTERIOR SURFACE BS 820, LBL 12 HAS CORROSION. ACCOMPLISHED REMOVAL OF CORROSION FROM WING CENTER SECTION SKIN AT BS 820 LBL 12 IAW EA 7-5730-123577.

Part: SILL — MISINSTALLED (BS 570-660) · airframe 59,760 hrs · 37,180 cycles

MCD UPPER IB AFT SILL HAS NO RIVET SPACING. ACCOMPLISHED REPAIRS AT MCD UPPER INBD AFT SILLS IAW EA 7-5310-143936, EA 7-5310-123575, & EA 7-5310-143935.

Part: SILL — MISINSTALLED (BS 530-440) · airframe 59,760 hrs · 37,180 cycles

MCD UPPER IB FWD SILL HAS NO RIVET SPACING. ACCOMPLISHED REPAIRS AT MCD UPPER INBD FWD SILL IAW EA 7-5310-143936.

Part: SILL — MISINSTALLED (BS 530-570) · airframe 59,760 hrs · 37,180 cycles

MCD UPPER INBD CENTER SILL HAS NO RIVET SPACING. REMOVED, LOCATED, DRILLED, 7 INSTALLED MCD UPPER INBD CTR SILL & SPLICES ( 2 EA ) IAW EA 7-5310-143936, EA 7-5310-143935, & EA 7-5310-123575.

Part: SEAT TRACK — CORRODED (BS 720A-740) · corrosion level 2 · airframe 59,760 hrs · 37,180 cycles

MAIN CABIN SEAT TRACK FROM BS 720A, PLUS 10" TO BS 740, RBL 45.5 IS CORRODED. REMOVED SEAT TRACK FROM BS 720A PLUS 10" TO BS 740 RBL 45 AND FABRICATED NEW SEAT TRACK BAC1520-792-7178 T6511 AND INSTALLED SEAT TRACK IAW SRM 51-30-2 & SRM 53- 10-5 FIG 1.

Part: FRAME — DENTED (BS 970 S25-27L) · airframe 59,760 hrs · 37,180 cycles

AFT PIT, FRAME AT BS 970 IS DENTED BETWEEN STR 25L-STR 27L. CUT OUT DAMAGED AREA IAW SRM REV 103, 51-10-1. FABRICATED DOUBLER IAW SRM 51-40-3 FIG 1 AND 53-10-2 FIG 5. INSTALLED REPAIR DOUBLER IAW SRM 51-30-2 AND 51-40-3 FIG 1.

Part: TORQUE BOX — CRACKED (BS 1327) · airframe 59,760 hrs · 37,180 cycles

AFT AIRSTAIR AREA RT TORQUE BOX WEB CRACKED AT BS 1327. TRIMMED OUT DAMAGED AREA TO 1 RADIUS IAW SRM 51-40-2 ON AFT AIRSTAIR AREA RT TORQUE BOX WEB. FABRICATED DOUBLER FROM 7075T6 .032 DIM: 3.7500" X 2.7500" IAW SRM 51-40-2 AND INSTALLED DOUBLER IAW SRM 51-30-2 & SRM 51-40-2, FIG 1.

Part: SKIN — DAMAGED (BS 540 S2L) · airframe 59,760 hrs · 37,180 cycles

UPON REMOVING MCD SILL, FOUND SKIN DAMAGE FROM RIVET HOLE, STA 540, STR 2L. CUTOUT DAMAGED SKIN AREA, FABRICATED DOUBLER, TRIPLER, & FILLERS, AND INSTALLED REPAIR AT BS 540 S2L IAW EA 7-5310-143936.

Part: DOOR FRAME — CORRODED (ZONE 100) · airframe 59,760 hrs · 37,180 cycles

C-3 DOOR CUTOUT, FRAME IS CORRODED AT FASTENERS ON FWD SIDE BS 1183 BTWN S27-26R. REMOVED FASTENERS & FOUND TO BE OUT OF LIMITS & CORROSION, IAW SRM 51-30-2 & 53-10-1. REMOVED DAMAGE AT SHEAR TIE IAW SRM 53-10-1 REV 103, FABRICATED NEW DOUBLER, NEW FILLER & NEW SHEAR TIE IAW SRM 53-10-4 FIG 14 TABLE 1. INSTALLED SHEAR TIE, DOUBLER AND FILLER IAW SRM 53-10-4 REV 103.

Part: SEAT TRACK — CORRODED (BS 850-870) · corrosion level 2 · airframe 59,760 hrs · 37,180 cycles

CORROSION FLANGE SEAT TRACK STA 870 - STA 850, RBL 45. REMOVED SEAT TRACK IAW SRM 51-30-2 AND FABRICATED NEW SEAT TRACK IAW SRM 51-30-5 & DWG 53FX1497 INSTALLED SEAT TRACK IAW SRM 51-30-2.

Part: SEAT TRACK — CORRODED (BS 850-870) · corrosion level 2 · airframe 59,760 hrs · 37,180 cycles

CORROSION FLOATING SEAT TRACK MAIN CABIN STA 870 TO STA 850, LBL 45. REMOVED SEAT TRACK IAW SRM 51-30-2 AND FABRICATED NEW SEAT TRACK IAW SRM 51-30-5. INSTALLED NEW SEAT TRACK IAW SRM 51-30-2 & SRM 53-10-2 FIG 7A.

Part: SEAT TRACK — CORRODED (BS 850-870) · corrosion level 2 · airframe 59,760 hrs · 37,180 cycles

CORROSION FLANGE SEAT TRACK STA 870 -STA 850, BL 0. REMOVED FLOATING SEAT TRACK AT STA 870-850, BL 0 IAW SRM 51-30-2 AND FABRICATED NEW FLOATING SEAT TRACK FROM BAC 1520-14317178, T6511 IAW SRM 51-30-5. INSTALLED NEW SEAT TRACK IAW SRM 51-30-2 & SRM 53-10-2, FIG 7A.

Part: SEAT TRACK — CORRODED (BS 1130-1176) · corrosion level 2 · airframe 59,760 hrs · 37,180 cycles

CORROSION SEAT TRACK STA 1176 - STA 1130, BL 0. REMOVED SEAT TRACK STA 1176 TO STA 1130, BL 0 IAW SRM 51-30-2 & SRM 51-10-6. FABRICATED NEW SEAT TRACK DWG 53FX976, REV B 7675T651 0.5X4 DIM: 45" X 3.5". INSTALLED SEAT TRACK IAW SRM 51-30-2.

Part: DOOR FRAME — CRACKED (PAX DOORWAY) · airframe 59,760 hrs · 37,180 cycles

FWD ENTRY DOOR, AFT FRAME IS CRACKED AT LOWER CORNER, CRACK GOES UNDER STOP FITTING. CUTOUT DAMAGED AREA, FABRICATED AND INSTALLED REPAIR PARTS IAW EA7-5210-123580.

Part: SKIN — CORRODED (BS 510 S27R) · corrosion level 2 · airframe 59,760 hrs · 37,180 cycles

CORROSION STA 510, STR 27R FWD PIT. CUT OUT DAMAGED AREA OF SKIN AT BS 510 STR 27R, 4 1/8" X 2 1/8" IAW SRM 53-30-3 FIG 1. FABRICATED REPAIR DOUBLER FROM 2024-T3 .100" X 16 3/8" X 10 1/8" AND FILLER FROM 2024-T3, .090" X 4" X 1 1/8" IAW SRM 53-30-3 FIG 1. INSTALLED DOUBLER AND FILLER IAW SRM 53-30-3 FIG 1 REV. 103.

Part: SILL — DAMAGED (BS 541) · airframe 59,760 hrs · 37,180 cycles

UPPER SILL BS 541 ON UPPER FLANGE HAS FASTENERS WITH INSUFFICIENT ED. ACCOMPLISHED MCD UPPER SILL REPAIRS IAW EA NR 7-5310-143936 AND EA NR 7-5310-143935.

Part: SILL — CRACKED (BS 502) · airframe 59,760 hrs · 37,180 cycles

UPPER SILL BS 502 NEAR UPPER FLANGE HAS CRACK INDICATION AT FASTENER HOLE. ACCOMPLISHED MCD UPPER SILL REPAIR IAW EA 7-5310-143936, EA 7-5310-143935, EA 7-5310-123575.

Part: SILL — MISINSTALLED (BS 619) · airframe 59,760 hrs · 37,180 cycles

UPPER SILL BS 619 ON UPPER FLANGE HAS FASTENER WITH NO ED. ACCOMPLISHED MCD UPPER SILL REPAIR IAW EA 7-5310-143936, EA 7-5310-143935, & EA 7-5310-123575.

Part: SKIN — DENTED (BS 500 S27R) · airframe 59,760 hrs · 37,180 cycles

SHARP DENT EXTERIOR FUSELAGE STA 500, STR 27R. CUT OUT DENT ON EXTERIOR SKIN IAW SRM 53-30- 3 FIG 1. FABRICATED DOUBLER AND FILLER IAW SRM 53-30-3 FIG 1. INSTALLED DOUBLER AND FILLER IAW SRM 51-30-2 AND 53-30-3 FIG 1 REV. 103.

Part: VERTICAL BEAM — DAMAGED (BS 1183) · airframe 59,760 hrs · 37,180 cycles

AFT PIT, BS 1183, PRESSURE BULKHEAD VERTICAL BEAM HAS INSUFFICIENT SPACING AT LBL 17.8. ACCOMPLISHED REPAIR AT BS 1183 PRESSURE BULKHEAD VERTICAL BEAM IAW EA 7-5310-143934.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 59,759 hrs · 37,179 cycles

DOOR EMERGENCY EXIT LIGHT INOP. MEM R & R L-1 DOOR EMERGENCY EXIT LIGHT IAW MM 33-50-101-2-0 AND OPS CHECKED GOOD.

Part: CONTROL HANDLE — MALFUNCTIONED (AFT AIRSTAIR) · airframe 59,638 hrs · 37,129 cycles

THE AFT AIR STAIR LIGHT ON S/O PANEL CAME ON AT 1000FT ON TAKEOFF AND STAYED ON DURING DESCENT THE AFT AIR STAIR LIGHT WENT OUT AT LF 090 AND CAME BACK ON AT 4000 FT. RELEASED FOR SERVICE IAW MEL: 52-06-B. WORKED IN CONJUNCTION WITH TSI 52-30/4231. R & R S395 AFT STAIRS CONTROL HANDLE ACTUATOR SWITCH AND S268 AFT STAIRS UPLOCK ACTUATOR SWITCH. PERFORMED AFT STAIRS OPS TEST IAW AND ALL TESTS GOOD.

Part: SWITCH — MALFUNCTIONED (DOOR WARNING) · airframe 59,583 hrs · 37,105 cycles

PANEL AFT STAIR AMBER LIGHT ILLUMINATED AFTER T.O AMBER AFT AIRSTAIR DOOR WARNING LIGHT - INOP. COMPLIED WITH MTSI 52-62/4199, INSPECTED BOTH THE UPPER AND LOWER CONTROL HANDLE MECHANISMS, CONTROL HANDLE DETENT SW S395, PULLEYS, HINGE POINT, MOUNTS AND NO DISCREPANCIES FOUND. OPERATED STAIR AND CHECKED THAT IT IS FAIRED WITH THE FUSELAGE IN THE UP POSITION. T/S DOOR WARNING SYSTEM IAW WDM 52-71-01 AND SUSPECTED THAT S268 AND S395 WAS NOT OPERATING PROPERLY.R/R'D S268 AND S395, ADJUSTED IT IAW AMM 52-70-001-51. CHECKED THE AIRSTAIR OPS PER AMM 52-62-001-5 PGE 6, STEP D AND SYS WORKED OK. PER MOCC SUGGESTION THE MEL WAS NOT CLOSED UNTILL 2 FLIGHTS WITH NO PROBLEMS.

Part: MANIFOLD — SHEARED (FIRE DETECTION) · airframe 59,100 hrs · 36,882 cycles

AFTER TAKEOFF WITH STANDARD POWER SET, NR 3 ENGINE FIRE WARNING ALARM. ENGINE WAS SHUTDOWN IAW QRH FIRE LIGHT WENT OUT WITH START LEVER TO CUT OFF. GOOD FIRE WARNING TEST. FOUND SEVERED TUBING COMING TO FUEL HEATER S/O VALVE INLET PORT. ALSO FOUND GROUNDING WIRES SEVERED JUST BENEATH THE SEVERED TUBING. REPLACED FUEL HEATER S/O VALVE INLET TUBE, RAN ENGINE IAW JRH. ACCOMPLISHED FUEL HEATER CHECK IAW AMM 73-14-000-5. ALL OK. NO LEAKS NOTED. REPLACED SEVERED GROUNDING WIRING IAW STD PRACTICES MANUAL 20-10-13.

Part: SHUTOFF VALVE — FAILED (A/C PACK) · airframe 58,890 hrs · 36,795 cycles

AFTER TAKEOFF IN OUR NORMAL CONFIGURATION CABIN STARTED UP A HIGHER THAN NORMAL RATE. AFTER CLOSING THE CABIN OUT FLOW VALVE AND TURNING ON THE RT PACK, CABIN RETURNED TO NORMAL UNTIL WE REACHED 26,000' AT WHICH TIME THE CABIN WAS CLIMBING AT 800'/MIN, SAME AS THE ACFT. RAN OUR LOSS OF PRESSURIZATION V LIST, STARTED TO DESCEND AND RETURNED TO DEPARTURE. SWITCHING TO STANDBY HAD NO EFFECT AND AT THAT POINT NOTICED THE OUTFLOW VALVE WAS ALREADY FULLY CLOSED. SWITCHED TO BOTH AC & DC MANUAL TO MAKE SURE THAT THE OUTFLOW VALVE WAS CLOSED. IT WAS FULLY CLOSED BUT THE CABIN CONTINUED TO CLIMB. AFTER STARTING OUR DESCENT, FINALLY CAUGHT THE CABIN AND EVENTUALLY THE CABIN BEGAN TO DESCEND NORMALLY WITH BOTH PACKS ON & OUTFLOW VALVE CLOSED. THE CABIN AT ITS HIGHER POINT REACHED 12,000'. THE WARNING HORN WORKED AS ADVERTISED. VERIFIED PRESSURIZED AREA FOR LEAKS, NONE NOTED. NO EXTERNAL DAMAGE TO ACFT FUSELAGE. LT PACK FOUND INTERMITTENT. FOUND FWD PACK S/O VALVE NOT RESPONDING TO SW COMMANDS. REPLACED SAME IAW AMM 21-55-071-4 ALL OK. IAW MEM REQUEST ALSO ACCOMPLISHED JRH TESTS "PNEUMATIC SYS TEST" REF 8-17 AND "PRESSURIZATION CONTROL SYS OPS TEST" REF 8-21 ALL NORMAL.

Part: SKIN — GOUGED (CARGO DOOR) · airframe 57,860 hrs · 36,209 cycles

C-3 DOOR EXTERIOR SKIN HAS NUMEROUS DENTS AND GOUGES. FABRICATED NEW EXTERIOR SKIN IAW EA NR 7-5230-123319 AND BOEING DWG NR 65-56927 EA 7-5230-123319.

Part: SKIN — GOUGED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

SCIBE MARKS IN FUSELAGE SKIN FROM STA 690 TO 720D STR 19L TO 19R. CUTOUT DAMAGED SKIN DIMS 50 1/4" BY 33 1/4". FABRICATED NEW SKIN SECTION FROM 2024-T3 .063 PO NR 8204312. FABRICATED REPAIR STRAP AND FABRICATED 2 SHIMS. INSTALLED REPAIR PARTS AT BS 690-720D BETWEEN STR 25L TO 25R IAW SRM 53-30-3 FIG 12.

Part: SKIN — TORN (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

TORN SKIN NR 1 ENGINE INLET COWL 4 O`CLOCK POS INBD SIDE AT COWL ATTACH LIP. CUT OUT DAMAGED AREA DIMS 1 1/2" BY 1" IAW SRM 51-10-1. FABRICATED DOUBLER REPAIR AND FILLER IAW SRM 54-30-3 FIG 3A. INSTALLED REPAIR PARTS IAW SRM 51-30-2 AND 54-30-3 FIG 3A.

Part: FITTING — DAMAGED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

DAMAGED TENSION TIE AT STA 362 STR 17L. REMOVED AND REPLACED DAMAGED TENSION TIE AT BS 362 STR 17L WITH NEW TIE PART NUMBER 65-20984-2 PO NR.

Part: RIB — CRACKED (ZONE 600) · airframe 57,860 hrs · 36,209 cycles

RIGHT WING TIP INTERIOR CRACKED WBL 624. REMOVED WING TIP IAW B727 MM 57-20-001-4. REMOVED WING TIP RIB IAW B727 SRM 51-30-2. LOCATED AND DRILLED NEW RIB IAW B727 SRM 51-30-5. INSTALLED NEW RIB IAW B727 SRM 51-30-2 AND REINSTALLED WING TIP IAW B727 MM 57-20-001-4.

Part: SKIN — DAMAGED (BS 680 S23L) · airframe 57,860 hrs · 36,209 cycles

OPEN HOLE IN SKIN AT BS 680 STR 23L. FABRICATED AND INSTALLED FREEZE PLUG IAW B727 SRM 51-10-7, FABRICATED RETAINING PLATES USING 7075-T6 .040 PO NR 9007294 DIMS 3" BY 1" AND INSTALLED REPAIR PARTS IAW FEDEX EA 7-5330-117034, OPEN HOLE IN SKIN AT BS 680 STR 23L, REPAIR.

Part: SKIN — DENTED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

SKIN PANEL DENTED STA 615 ON MAIN CARGO DOOR DOUBLER AND TRIPLER AT STR 24L TO 28L. REWORKED SKIN TO ORIGINAL CONTOUR AT BS 620 STR 24L TO 28L IAW FEDEX EA 7-5330-117028, FUSELAGE SKIN PANEL DENT AT STA 615 STR 24L TO 28L REPAIR. INSTALLED DENT DOT IAW FEDEX GMM 6-3-101.

Part: SKIN — DAMAGED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

SCRIBE MARKS IN FUSELAGE SKIN BS 720 6 INCH BETWEEN STR 23LT AND 24 LT. FOUND AREA OUT OF LIMITS IAW SRM 53-30-01 FIG 1. CUT OUT DAMAGED AREA DIMS 2 1/2 INCH BY 1 5/8 INCH IAW SRM 51-10-01 AND 53-30-03 FIG 1. FABRICATED DOUBLER REPAIR IAW SRM 53-30-03 FIG 2 AND FILLER. INSTALLED REPAIR PARTS IAW SRM 51-30-02 AND 53-30-03 FIG 2.

Part: SKIN — DAMAGED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

SCRIBE MARKS IN FUSELAGE SKIN BS 720 6 INCHES BETWEEN STR 23 RT AND 24 RT. FOUND AREA OUT OF LIMITS IAW SRM 53-30-01 FIG 1. CUT OUT DAMAGED AREA DIMS 3 INCH BY 2 INCH IAW SRM 51-6-01 AND 53-30-03 FIG 1. FABRICATED DOUBLER IAW SRM 53-30-03 FIG 2. FABRICATED FILLER IAW SRM 53-30-03 FIG 2. INSTALLED REPAIR PARTS IAW SRM 51-30-02 AND 53-30-03 FIG 2.

Part: SUPPORT — CRACKED (BS 1253) · airframe 57,860 hrs · 36,209 cycles

LEFT LOWER TORQUE BOX, UPPER WEB SUPPORT HAS CRACK AT RIVET, STA 1253. CUT OUT AREA FOR ACCESS TO REMOVE SUPPORT ANGLE IAW SRM 51-40-2 & 51-10-1. REMOVED SUPPORT ANGLE IAW SRM 51-30-2. FABRICATED NEW SUPPORT ANGLE IAW DRAWING 65-17518. ALODINED AND PRIMED ANGLE IAW SRM 51-10-2. INSTALLED ANGLE IAW SRM 51-30-2. FABRICATED 2(EA) DOUBLERS IAW SRM 51-40-2 FIG 1. ALODINED AND PRIMED PARTS IAW SRM 51-10-2. INSTALLED PARTS IAW SRM 51-40-2 FIG 1.

Part: SKIN — DENTED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

DENT LT AFT FUSELAGE STA 1070 S18-20L. EVALUATED DENT AT STA 1070 STR 18L TO 20L AND FOUND WITHIN LIMITS IAW SRM 53-30-01 FIG1 BUT DENT CROSSES OVER STR 19L EA 7-5330-117024 "SKIN PANEL DENT AT STA 1074 S18-20L" ISSUED TO ADDRESS DENT CROSSING S19L. PER EA 7-5330-117024 SUBJECT AREA REMAINS CAPABLE OF CARRYING DESIGN LOADS AND WILL HAVE NO ADVERSE AFFECT ON SKIN FATIGUE LIFE. HFEC INSPECTED AREA AND FOUND NO CRACKS IN THE DENT LOCATIONS.

Part: SKIN — DAMAGED (ZONE 200) · airframe 57,860 hrs · 36,209 cycles

EXTERIOR SKIN OIL CANNED, BL0 STA 640-660. FABRICATED DOUBLER REPAIR FROM 2024T3 .050 PO NR 9007500 DIMS 10" BY 11 1/4 INCH IAW B727 SRM 53-30-3 FIG 1 AND INSTALLED REPAIR IAW B727 SRM 53-30-3 FIG 1 AND 51-30-2.

Part: SPAR — CORRODED (RT WING) · corrosion level 2 · airframe 57,860 hrs · 36,209 cycles

CORROSION ON RIGHT WING FRONT LOWER SPAR CHORD AT FSS 514. REMOVED CORROSION, VERIFIED REMAINING MATERIAL TO BE 0.123", HFEC INSPECTED ALL OPEN HOLES WITH NO DEFECTS NOTED, PERFORMED ULTRASONIC INSPECTION OF BLENDED AREAS, NO DEFECTS NOTED, SPOT FACED FASTENER HOLES, FLAP PEENED AREA AND REFINISHED AREA IAW EZ 7-5710-117014, WINGS, AD 2005-05-19 - EO 7-5740-7-5000, RT WING LOWER FORWARD SPAR CORROSION AT FSS 514, REPAIR.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 57,860 hrs · 36,209 cycles

EXTERIOR SKIN PILLOWING AND BULGED WITH BROKEN AND PULLED RIVETS STA 309 TO 312 STR 24L. FABRICATED REPAIR DOUBLER FROM 2024-T3 .071 PO NR 9007561 DIMS 12 INCH BY 7 INCH. FABRICATED STRUCTURAL FILLER FROM 2024-T3 .063 PO NR 9007007 DIMS 12 INCH BY 5 INCH AND INSTALLED REPAIR PARTS AT BS 309-312 STR 24L IAW B727 SRM 53-30-3 FIG 14, SRM 53-30-2 FIG 2 AND SRM 51-30-2.

Part: WEB — CRACKED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

RIGHT LOWER TORQUE BOX INBD WEB IS CRACKED WITH A STOP DRILL AT LIGHTNING HOLE BS 1223. HFEC CRACK TO VERIFY TERMINATION IAW NDTM PT6 51-00-00 FIG 23. FABRICATED REPAIR DOUBLER IAW SRM 51-40-2 FIG 1 AND 53-10-2 FIG 6. INSTALLED REPAIR DOUBLER IAW SRM 51-40-2 FIG 1.

Part: SKIN — DENTED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

SKIN DENTED RIGHT AFT FUSELAGE FROM C-3 DOOR CUTOUT STA 1148 TO STA 1183 STR 20R. CUT OUT DAMAGED SKIN, FABRICATED REPAIR FILLER USING 2024-T3 .100 PO NR 8221343 DIMS 42 7/8 INCH BY 12 INCH, DOUBLER, TRIPLER. INSTALLED REPAIR PARTS IAW EA 7-5330-117015 - FUSELAGE SKIN CREASE BELOW STR 20R LAP SPLICE BS 1140-1183, REPAIR.

Part: WEB — CRACKED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

RT LOWER TORQUE BOX INBD WEB HAS A CRACK AT BOLT STA 1223. STOPPED DRILLED CRACK 2 EACH DIMS .250 IAW SRM 51-10-1, HFEC CRACK TO VERFY TERMINATION AT STOP DRILL IAW NDTM PT6 51-00-00 FIG 23. FABRICATED REPAIR DOUBLER IAW SRM 51-40-2 FIG 1 AND 53-10-2 FIG 6. INSTALLED REPAIR DOUBLER IAW SRM 51-40-2 FIG 1.

Part: WEB — DAMAGED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

AFT AIRSTAIR, LEFT LOWER TORQUE BOX WEB HAS DAMAGED AREA ON PREVIOUS REPAIR. REMOVED PREVIOUS REPAIR IAW SRM 51-30-2, TRIMMED OUT AREA DIMS 1 1/4 INCH BY 3/4 INCH IAW SRM 51-10-1. FABRICATED REPAIR DOUBLER IAW SRM 53-10-2 FIG 6 AND 51-40-2 FIG 1. INSTALLED REPAIR DOUBLER IAW SRM 51-40-2 FIG 1.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 57,860 hrs · 36,209 cycles

HOLE WITH ZERO EDGE DISTANCE DRILLED IN SEAT TRACK FLANGE STA 990 RBL45. FABRICATED NEW SEAT TRACK SECTIONS. FABRICATED REPAIR ANGLE SPLICES 4 EACH AND INSTALLED NEW SEAT TRACK SECTIONS AT BS 950-1020 RBL 45 IAW SRM 53-10-5 FIG 1 AND SRM 53-10-2 FIG 7.

Part: FLOORBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 57,860 hrs · 36,209 cycles

MAIN CABIN BS 1070 LBL8 LOWER FLANGE ON FLOORBEAM HAS CORROSION. REMOVED 2 EACH PREVIOUS REPAIRS ON FLOORBEAM IAW SRM 51-30-2. REMOVED CORROSION ON LBL 8, FOUND AREA OUT OF LIMITS IAW SRM 51-10-6 AND 53-10-1. CUT OUT DAMAGED AREA IAW SRM 53-10-8 FIG 8. FABRICATED 2 ANGLES AND 2 FILLERS IAW SRM 53-10-8 FIG 8. INSTALLED NEW PARTS IAW SRM 53-10-8 FIG 8.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 57,860 hrs · 36,209 cycles

MAIN CABIN SEAT TRACK BS 520 BL0 HAS CORROSION. FABRICATED NEW SEAT TRACK SECTION. INSTALLED NEW SEAT TRACK SECTION USING PREVIOUS GOOD SPLICES IAW SRM 53-10-5 FIG 1 AND SRM 53-10-2 FIG 7.

Part: WEB — CRACKED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

LEFT LOWER TORQUE BOX INBD WEB LIGHTNING HOLE ROUTE OUT IS GREATER THAN SRM LIMIT. CRACK DISCOVERED ADJACENT TO ROUTE OUT. STOP DRILLED CRACK IAW SRM 51-10-1. HFEC CRACK INDICATES CRACK ENDS AT STOP DRILL IAW NDTM 51-00-00 FIG 23. FABRICATED 1 REPAIR TO COVER ROUTE OUT AND CRACK IAW SRM 53-10-2 FIG 6. INSTALLED DOUBLER REPAIR IAW 51-40-2 FIG 1.

Part: STRINGER CLIP — DAMAGED (ZONE 200) · airframe 57,860 hrs · 36,209 cycles

STA 355 STR 7R STRINGER CLIP DAMAGED. FABRICATED NEW STRINGER, 2 NEW ANGLES AND NEW EXTRUSION IAW SRM 53-10-3 FIG 2. INSTALLED REPAIR PARTS IAW SRM 53-10-3 FIG 2 AND SRM 53-10-2 FIG 9.

Part: SEAT TRACK — WORN (ZONE 200) · airframe 57,860 hrs · 36,209 cycles

SEAT TRACK WORN STA 640 BL 0. FABRICATED NEW SEAT TRACK SECTION AND INSTALLED SEAT TRACK SECTION USING PREVIOUS GOOD CONDITION SPLICES IAW SRM 53-10-5 FIG 1 AND SRM 53-10-2 FIG 7.

Part: SKIN — DAMAGED (ZONE 200) · airframe 57,860 hrs · 36,209 cycles

INTERNAL FUSELAGE SKIN AT BS 355 BELOW STRINGER 7RT HAS A DRILL START. DRILLED A .161 DIA HOLE AND INSTALLED A NAS1097AD5 RIVET IAW EA NR 7-5330-117006 AND SRM 51-30-2.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 57,860 hrs · 36,209 cycles

MAIN CABIN BS 1110 LBL 65 AND LBL 45 FLOORBEAM UPPER FLANGE HAS CORROSION. REPAIRED MAIN CABIN FLOORBEAM UPPER FLANGE BS 1110 LBL 57 CUTOUT AREA DIMS 3 1/2 INCH BY 1 INCH, FABRICATED REPAIR ANGLES (2EA). FABRICATED FILLER. INSTALLED REPAIR PARTS AT BS 1110 FLOORBEAM IAW SRM 53-10-8 FIG 3 AND SRM 53-10-2 FIG 7.

Part: SKIN — CRACKED (RT ELEVATOR) · airframe 57,860 hrs · 36,209 cycles

LARGE HOLE IN RT ELEVATOR, INSIDE NR 3 BALANCE PANEL ACCESS, PUNCTURE HOLE. REMOVED WEB AND ANGLE IAW SRM 51-30-2. FABRICATED WEB AND (1) EA ANGLE IAW DRAWING 65-26163 REV C. BONDED WEB PER BMS 5-69 IAW DRAWING 65-26163 REV C. HEAT TREATED ANGLE IAW ER 2-37153-801 REV A. ALODINE AND PRIME PARTS IAW SRM 51-10-2. INSTALLED PARTS IAW SRM 51-30-2.

Part: HANDLE — GOUGED (MLG DOOR) · airframe 57,860 hrs · 36,209 cycles

LEFT AND RIGHT MLG DOOR RELEASE HANDLES ARE GOUGED. BLENDED GOUGES AT LEFT AND RIGHT MLG DOOR RELEASE HANDLES IAW EA 7-3210-117011.

Part: LAP JOINT — GOUGED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

SKIN GOUGED RIGHT FUSELAGE LAP SEAM FWD OF STA 720E AT STR 19R. CUTOUT DAMAGED AREA DIMS 3 INCH BY 4 1/2 INCH IAW SRM 53-30-3. FABRICATED DOUBLER, FABRICATED REPAIR FILLER IAW SRM 53-30-3 FIG 14. TREATED AND PRIMED REPAIR PARTS IAW SRM 51-10-2. INSTALLED REPAIR PARTS IAW SRM 51-30-2.

Part: FITTING — CRACKED (ZONE 500) · airframe 57,860 hrs · 36,209 cycles

LT WING, EVALUATE PREVIOUS REPAIR AT INBD LOWER CORNER OF NR 7 SPOILER FITTING AT FALSE SPAR. REMOVED IMPROPER REPAIR IAW SRM 51-30-2 AND FEDEX DRAWING SR-27-57-038 REV C. REMOVED NR 7 SPOILER FITTING AND DOUBLER, TRIMMED OUT WEB, FABRICATED NEW DOUBLER USING 7075T6 .032 PO NR 9006612 DIMS 12 INCH BY 8 1/2 INCH, FABRICATED NEW INBD LOWER CHORD FROM BAC1514-1437 PO NR 8195260 DIMS 20 3/4 INCH BY 4 7/8 INCH, 2 EACH ANGLES FROM 7075- O .071 PO NR 9007470, 1 EACH STRAP FROM 7075T6 .090 PO NR 9006152 AND INSTALLED REPAIR PARTS IAW FEDEX DRAWING SR-27-57-038 REV C.

Part: SEAT TRACK — CORRODED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

CORROSION ON SEAT TRACK FLANGES AND ATTACHING HARDWARE, STA 1010 10 INCH TO STA 1050, LBL 45 FOUND CORROSION OUT OF LIMITS IAW B727 SRM 53-10-1. REMOVED (3) EA SECTIONS OF SEAT TRACK FROM BS 1010 TO 1130 IAW B727 SRM 51-30-2. FABRICATED NEW SECTION OF SEAT TRACK FROM BS 1010 TO 1130 LBL 45 USING BAC1520-792 7178T6511, DIM 114 INCH IAW B727 SRM 51-30-5 AND 53-10-5 FIG 1. ALODINE AND PRIME SEAT TRACK IAW B727 SRM 51-10-2. INSTALLED SEAT TRACK IAW B727SRM 51-30-2 AND 53-10-5 FIGURE 1.

Part: FLOORBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 57,860 hrs · 36,209 cycles

SURFACE CORROSION STA 720D RBL 12 TOP OF FLOORBEAM. REMOVED CORROSION IAW SRM 51-10-6, FOUND CORROSION OUT OF LIMITS IAW SRM 53-10-1 FIG 4, CUTOUT DAMAGED AREA IAW SRM 53-10-8 FIG 3, FABRICATED UPPER CHORD, 2 SUPPORT ANGLES AND 2 REINFORCEMENT STRAPS IAW SRM 53-10-8. ALODINED AND PRIMED PARTS IAW SRM 51-10-2 AND INSTALLED PARTS IAW SRM 53-10-8 FIG 3.

Part: KEELBEAM — CRACKED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

LEFT KEEL BEAM CHORD IS CRACKED AT STA 880. REMOVED AND DISCARDED EXISTING GUSSET PLATE AND FASTENERS COMMON TO THE KEEL BEAM CHORD IAW FEDEX EA 7-5310-117026. VERIFIED END OF CRACK USING HFEC IAW B727 NDTM 51-00-00 FIG 1. TRIMMED UPPER FLANGE OF KEEL BEAM CHORD, FABRICATED REPAIR DOUBLER, AND INSTALLED REPAIR DOUBLER IAW FEDEX EA 7-5310-117026, MLG WHEEL WELL KEEL BEAM CRACK AT BS 872 - REPAIR.

Part: FRAME — CHAFED (ZONE 200) · corrosion level 2 · airframe 57,860 hrs · 36,209 cycles

FRAME DAMAGED STA 360 STR 2R. CUTOUT DAMAGED AREA DIMS 1 1/8 INCH BY 1 INCH, FABRICATED REPAIR ANGLE FROM 7075-0 .063 PO NR 9007470 DIMS 9 INCH BY 3 INCH BY 1 INCH. INSTALLED REPAIR ANGLE AT BS 360 STR 2R IAW B727 SRM 53-10-4 FIG 2 AND SRM 53-10-2 FIG 3.

Part: KEELBEAM — CRACKED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

RIGHT KEEL BEAM CHORD IS CRACKED AT STA 872. ACCOMPLISHED REPAIR ON RIGHT KEEL BEAM CHORD AT STA 872 IAW FEDEX EZ 7-5310-117026, MLG WHEEL WELL KEEL BEAM CRACK AT BS 872 REPAIR.

Part: SPLICE — GOUGED (ZONE 100) · airframe 57,860 hrs · 36,209 cycles

SKIN GOUGED LEFT FUSELAGE LAP SEAM FWD OF 720E AT STR 19L. FABRICATED REPAIR DOUBLER FROM 2024-T3 .071 PO NR 9006288 DIMS 14 INCH BY 7 1/2 INCH. FABRICATED STRUCTURAL FILLER FROM 2024-T3 .063 PO NR 9006773 DIMS 14 INCH BY 5 INCH. INSTALLED REPAIR PARTS AT FUSELAGE LAP SEAM FWD OF 720E STR 19L IAW SRM 53-30-3 FIG 14 AND SRM 53-30-2 FIG 2.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 57,860 hrs · 36,209 cycles

CORROSION AT SEAT TRACK OUTBOARD FLANGE TOP STA 425 RBL 45. FABRICATED NEW SEAT TRACK SECTION FROM BS 390 TO BS 480. FABRICATED REPAIR SPLICES. INSTALLED NEW SEAT TRACK SECTION AND SPLICE AT BS 390 TO BS 480 RBL 45 IAW SRM 53-10-5 FIG 1 AND SRM 53-10-2 FIG 7.

Part: CONNECTOR — BURNED · airframe 57,542 hrs · 35,963 cycles

AT ROTATION OFF FLAG IN CAPT'S ALTIMETER AND ALT SELECT WINDOW APPEARED. FOUND RACK CONNECTOR D609 CENTER SECTION, BEHIND NR 1 CADC BLACK FROM ELECTRICAL DAMAGE. INSTALLED WIRE NUMBERS W0007-162-22 AND W0007-9069-2 2 IN D609A PIN 12 PER BOEING HOOK UP LIST. INSTALLED WIRE NUMBERS W0007-9069-22 AND W0007-9070-22 IN PIN 42 IN D609A OF DADC NR 1. INSTALLED CONNECTOR ASSY PN NR DPD2MB-152-33S-2 PER BOEING STANDARD WIRING PRACTICES 20-71-11. REPLACED DADC NR 1 PER B727-200 AMM 34-11-051. NEEDS OPS CHECKED. INSTALLED CABIN PRESSURE CONTROLLER PER B727 AMM 21-31-010-4. PERFORMED SYS OPS CHECK AND LEAK CHECK TO DADC, ALSO OPS CHECK AND LEAK CHECK TO CABIN PRESSURE CONTROLLER, SYS OPS CHECK NORMAL.

Part: MOTOR — FAILED (HYD PUMP) · airframe 57,284 hrs · 35,768 cycles

LOST SYS "A" HYD QUANTITY. "A" PUMPS WERE OFF FOR LESS THAN 15 MINUTES. QUANTITY REMAINED JUST ABOVE ZERO AFTER COMPLETE QRH PROCEDURES THEREFORE DID NOT TURN OFF FLUID SHUTOFF. REMOVED AND REPLACED LT AND RT FLAP PWR UNIT HYD MOTORS PER MM 27-51-062-4. OPS AND LEAK CKS GOOD.

Part: ACCESSORY UNIT — FAILED (MLG) · airframe 57,218 hrs · 35,715 cycles

DURING NORMAL CLIMB-OUT, THE LANDING GEAR LEVER WAS RAISED TO THE UP POSITION AFTER GEAR UP THE RIGHT MAIN GEAR INDICATED GREEN AND RED LIGHTS FIRST OFFICER WAS FLYING AND CONFIRMED THAT THERE WAS SIGNIFICANT DRAG ON THE RIGHT SIDE OF THE AIRCRAFT. REPLACED LANDING GEAR ACCESSORY UNIT, AND THE TEST WAS REPEATED, WITH POSITIVE RESULTS. JACKED A/C REF 727-200 MM 07-11-000-2, RETRACTED AND EXTENDED LANDING GEAR MULTI. TIMES WITH NO FAULT, SYSTEM OK FOR SERVICE.

Part: RIB — CRACKED (LT WING) · airframe 57,072 hrs · 35,589 cycles

COMPLY WITH EA 7-5710-102033 WINGS (AD 90-06-09 AND AD 94-07-08) MAIN FRAME - RIB REPAIR EO 7-5710-7-2308 PART 2. COMPLIED WITH EA 7-5710-102033 (AD90-06-09 AND AD 94-07-08) RIB REPAIR EO 7-5710-7-2308 PART 2.

Part: WEB — CRACKED (BS 760-780) · airframe 57,072 hrs · 35,589 cycles

WEB AT STA 760-780 RBL65-70.5 IS CRACKED STR 17R 3 " CRACK FABRICATED WEB ON TRAVELER T7/671242 AND SRM 51-10-1. INSTALLED ON NR S00009.

Part: WIRE — DAMAGED (NLG) · airframe 57,072 hrs · 35,589 cycles

FERRY FLIGHT AFTER RAISING GEAR HANDLE UP HAD UNSAFE NOSE GEAR RED LIGHT. CYCLED GEAR IAW QRH UNSAFE NOSE GEAR LIGHT REILLUMINATED. ALL DOORS INDICATED SAFE. CONTINUED FLIGHT WITH GEAR HANDLE UP. TROUBLESHOT SYSTEM IAW WDM 32-64-01 FOUND BAD SPLICE IN WIRE W1386-018- 20. REMOVED AND REPLACED SPLICE IAW SWPM 20-10-12, PERFORMED EXT AND RETRACTION IAW 32-33-000-5. OP'S CHECKS GOOD.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 55,924 hrs · 34,740 cycles

FLOORBEAM 380 HAS CORROSION AT RBL 53 TO RBL 56. REMOVED, FABRICATED, HEAT TREATED, CAD PLATED, ALODINED, PRIMED, PAINTED AND INSTALLED FLOORBEAM REPAIR AT STA 380 FROM RBL 53 TO RBL 56 ALL IAW FX SRZ SR27-53-034E REPAIR 5, BAC5619, AMS-QQ-P-416, B727 SRM'S 51-10-2, 51-20-031-7, 51-30-1, 51-30-2 AND 53-10-1 FIG 4A.

Part: FLOORBEAM — CORRODED (BS 344) · airframe 55,924 hrs · 34,740 cycles

MAIN CARGO COMP FLOORBEAM CORRODED, STA 344 FROM LBL36 TO RBL18. REMOVED, FABRICATED, ALODINED, PRIMED, PAINTED AND INSTALLED FLOORBEAM REPAIR AT STA 344 FROM LBL36 TO RBL18 ALL IAW SRM 51-30-2, 51-10-2, 51-20-031-7 AND SRZ SR27-53-007.**S/D COMING**

Part: ENGINE — VIBRATION (NR 3) · airframe 53,730 hrs · 33,433 cycles

EXCESSIVE VIBRATION AND GRINDING SOUND ON NR 3 ENG POWER LEVER, INCREASES WITH SPEED AND ALTITUDE. ENGINE NR 3 USED 1 GALLON OF OIL DURING THE 1 HOUR PLUS 15 MIN FLIGHT. C/W ENGINE BORESCOPE PER W/C 7200-5005. NO DEFECTS NOTED.

Part: ACTUATOR — MALFUNCTIONED (LE FLAP) · airframe 53,601 hrs · 33,361 cycles

DURING FLAP RETRACTION FLAPS FROM 5 TO 2 DEGREE AMBER LIGHT. REMAINED ON AND NR 1 LED SHOWED INTRANSIT. COMPLIED WITH QRH AND RETURNED TO MEM. IN WORK, AFTER BLOCKING BACK INTO GATE, NR 1 LEADING EDGE FLAP WOULD RETRACT BUT WOULD CREEP BACK OPEN, WITH HYD SYSTEM PRESSURIZED, SUSPECT BAD ACTUATOR TRYING TO ORDER PARTS. REPLACED NR 1 L/E FLAP ACTUATOR IAW AMM 27-81-022-4. CHECKS NORMAL PREMATURE REMOVAL/INSTALLATION OFF MFG 65-17818-20.

Part: WIRE — BROKEN (NLG INDICATOR) · airframe 53,595 hrs · 33,358 cycles

RED NOSE GEAR UNSAFE LIGHT ON FOLLOWING GEAR RETRACTION; FOLLOWED RED TABS & RETURNED TO VLN FOR LANDING. REMOVED AND REPLACED NOSE GEAR LOCK SWITCH & POSITION SWITCH. PERFORMED ADJUSMENT/TEST, NO HELP. REMOVED AND REPLACED LANDING GEAR ACCESSORY UNIT AND PERFORMED NOSE GEAR LOCK AND POSITION SWITCH ADJUSMENT/TEST AS PER MM 32-61-071-4 AND DIDN'T HELP. ALSO PERFORMED WIRING CHECK BETWEEN LOCK SWITCH AND NOSE GEAR WHEEL WEEL CANNON PLUG AND FOUND WIRE C-BROKEN. FIXED WIRE-C AS PER 727-200 SWPM. REINSTALLED ORIGINAL LANDING GEAR ACCESSORY UNIT. PERFORMED NOSE GEAR LOCK AND POSITION SWITCH ADJUSMENT/TEST, AND NOSE GEAR RED LIGHT WORKED PROPERLY WITH LANDING GEAR IN UP POSITION.

Part: SWITCH — MALFUNCTIONED (CARGO DOOR) · airframe 53,520 hrs · 33,305 cycles

MAIN CARGO DOOR LIGHT ILLUMINATED WHILE LEVELING AT FL 290. CABIN PRESSURE WAS VERIFIED AT 8.0 PSID & NO OTHER INDICATION OF AN OPENED DOORS NOTED. FOLLOWED ORH PROCEDURES AND RETURNED TO MIA. REMOVED AND REPLACED S9033, ADJUSTED AND TESTED IAW MM 52-70-009-5. MCD OK FOR SERVICE.

Part: DETECTION SYS — FAULTY (NR 1 ENGINE) · airframe 53,410 hrs · 33,229 cycles

ENGINE FIRE WARNING NR 1 ENGINE DURING CLIMBOUT. LIGHT & HORN INTERMITTENT AT FIRST, THEN BOTH CAME ON STEADY. AFTER EXECUTING QRH PROCEDURES AND DISCHARGING BOTH BOTTLES, FIRE WARNING AND HORN STAYED ON UNTIL SHORT FINAL, THEN WENT OUT FOR GOOD. INSPECTED INTAKE AND EXHAUST, NO DAMAGE FOUND. OPENED COWLING INSPECTED UPPER AND LOWER SECTIONS OF ENGINE, NO EVIDENCE OF FIRE NOTED. REMOVED & REPLACED 2 EA ENGINE FIRE BOTTLES. REMOVED & REPLACED ENGINE NR 1 FIRE DETECTION ELEMENT. ALSO REMOVED & REPLACED THE FIRE DETECTION BOX. REMOVED & REPLACED ENGINE FIRE BOTTLE DETECTION DISC. RAN ENGINES, PERFORMED HIGH POWER RUN NR 1 ENGINE ALL PARAMETERS GOOD.

Part: FRAME — CORRODED (FUSELAGE) · airframe 53,394 hrs · 33,213 cycles

CORROSION ON FRAME 910 LEFT BL 71 AT STR 17. REPAIRED IAW BOEING SRM 53-10-4 FIG 13 AND EA 7-5310-55092.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 53,392 hrs · 33,209 cycles

STA 1163 FLOORBEAM REPAIR NOT IAW STANDARD REWORK DRAWING. REWORKED FLOORBEAM REPAIR STA 1163 IAW EA 7-5310-55026

Part: ATTACH ANGLE — CORRODED (FUSELAGE) · airframe 53,392 hrs · 33,209 cycles

ATTACH ANGLE ABOVE AFT LAV SERVICE PAN CORRODED. REMOVED AND REPLACED IAW EA 7-5320-55012.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 53,392 hrs · 33,209 cycles

STA 1183 STR 20L UPPER AND LOWER TERMINATING FITTINGS HAVE CORROSION AND GOUGES AT FASTENER HOLES. REMOVED AND REPLACED STRINGER 20 TERMINATING FITTINGS IAW B727 SRM 51-30-2 AND 727-200 AMM 20-80-001-2

Part: SKIN — CORRODED (FUSELAGE) · airframe 53,392 hrs · 33,209 cycles

EXTERIOR SKIN 12 INCH FORWARD OF BS 1183 BETWEEN STRINGERS 22L AND 23L CORRODED AND FASTENERS CORRODED AND AREA BULGED. REPAIRED DOUBLER FOR AFT LAV SERVICE PAN AREA IAW EA 7-5330-55022.

Part: BOLT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 53,392 hrs · 33,209 cycles

STA 1183, FORWARD BULKHEAD LOWER TENSION FITTINGS STR 26L, 27L, 26R, 27R, AND 29R HAVE CORRODED .3750 INCH BOLTS. REMOVED AND REPLACED BOLTS IAW WORK CARD 71C716-00

Part: FRAME — CORRODED (ZONE 100) · airframe 53,392 hrs · 33,209 cycles

AFT LAV SERVICE PAN AREA CORRODED, INCLUDING LOWER ATTACH ANGLE, STRINGER 22L AND 23L AT TERMINAL FITTING AND FS 1166 FRAME FWD AND AFT FACE BETWEEN STR. 20L AND 24L. REMOVED AND REPLACED FRAME AND ATTACH ANGLE IAW B727 SRM 51-30-2 AND 51-40-2. REFERENCE SNRM N01408 W/O 00023584.

Part: CSD — OVERHEATED (NR 3 ENGINE) · airframe 52,044 hrs · 32,404 cycles

NR 3 CSD OVERHEATED DURING CLIMBOUT, 121C WITH NR 1 CSD AT 115C AND NR 2 CSD DISCONNECTED. ELECTED TO RTB AND NOT REDUCE TO ONE GEN OPERATIONS.

Part: CSD — FAILED (NR 3 ENGINE) · airframe 52,044 hrs · 32,404 cycles

REPEAT WRITE-UP, DURING CLIMBOUT NR 2 CSD OVERHEATED TO 125C WITH NR 1 & 3 CSD'S IN LIMITS AT 110C & 118C IAW QRH. DISCONNECTED NR 2 GEN FOR 3 MIN COOLING. AFTER 2 MIN NR 3 CSD OVERHEATED TO 121C WITH NR 1 CSD 115C IAW QRH. DISCONNECTED NR 3 GEN AND RETURNED TO LAND. REMOVED AND REPLACED NR 3 CSD PER M/M 24-10-011-4 AND NR 3 CSD OIL COOLER PER M-M 24-10-062-4, RAN ENGINES PER JRH CK'D OK.

Part: INDICATOR — MALFUNCTIONED (COCKPIT)

REPEAT - OUTBOARD FLAPS STUCK AT 5 DEG UPON FLAP EXT. REMOVED AND REPLACED BOTH T/E FLAP IND AS PRECAUTION PER 27-52-021-2.

Part: NOZZLE — MISSING (NR 1& 3 ENGINE)

01-296 NR 3 ENG FIRE AGENT DISPERSE NOZZLE MISSING AND CAPPED OFF. REMOVED AND REPLACED FIRE NOZZLE ON ENG 1 & 3 PER MM 26-21-00.

Part: FLAP — VIBRATION (WINGS)

EXCESSIVE FLT CONTROL VIB. INSP FLAPS AND FAIRING FOR ADJ AND MISSING ROLLERS. FOUND OK PER MM 27-51-001-5 & MM 27-51-011-5.

Part: FLAP — OUT OF ADJ (RT WING)

DURING CLIMB EXPERIENCED MILD A/C VIBRATION. FOUND RT OUTBOARD TRAILING EDGE FLAP WITH TOO MUCH PLAY. ADJUSTED GAP BETWEEN ROLLERS AS PER MM 27-51-011-5. CHECK OK.

Part: ADC — FAILED (E/E BAY)

ON ROTATION CAPT AIRSPEED IND MACH AND A/S BARREL OFF FLAG CAME INTO VIEW. REMOVED AND REPLACED AIR DATA COMPUTER. PERFORMED BITE TEST. ALL SYS OK FOR SERVICE.

Part: SKIN — CORRODED (WING) · airframe 50,849 hrs · 31,707 cycles

LOWER WING SKIN CORRODED AT BS 840, LBL 30 ABOVE PRIMARY HEAT EXCHANGE. REMOVED AND REPLACED PER IAW FEDEX 7-5710-57961.

Part: SWITCH — FAULTY (CARGO DOOR)

WHILE LEVEL FLT 330 MAIN CARGO DOOR LIGHT ILLUM ON 2ND OFF PNL. FOLLOW RED TAB HOWEVER, LIGHT REMAIN ON. *S/D* REMOVED AND REPLACED LATCH WARN SWITCH 9034 PER BOEING STANDARD WIRING PRACTICES MANUAL CHPT 20. OPS CK OK PER MM 52-70-001-5.

Part: COUPLER — LEAKING (HYD VALVE)

LOST ALL HYD B SYS FLUID A SYS DROPPED TO 2.5 GAL AND STAYED. DID RED TABS PROC FOUND CK VALVE COUPLER INSIDE HYD BAY LEAKING. *S/D* REMOVED BOTH B HYD PUMPS PER 727-200 MM 29-12-011-2. REMOVED AND REPLACED HYD DRAIN FILTER ASSY PER MM 29-12-021-2. INSTALL NEW COUPLING HALF''S AND CK VALVE PER MM 29-14-00.

Part: WARNING LIGHT — ACTIVATED (NR 3 ENGINE)

ENG 3 STRUT OVERHEAT LIGHT CAME ON. REMOVED ACCESS PNLS 5501 & 5502 INSP NR 3 PYLON OH DETECTOR ELEMENT LOOP AND ASSOCIATED DUCTING. NO DISCREPANCIES NOTED OR EVIDENCE OF AIR LEAKS. SYS CK NORM IAW MM 26-14-000-5. REINSTALLED ACCESS PNL. AC OK TO CONTINUE.

Part: WARNING LIGHT — ILLUMINATED (STRUT)

NR 3 ENGINE STRUT OVERHEAT LIGHT ILLUM. POWER REDUCED PER RED TABS AND LIGHT EXTINGUISHED. REPLACED ALL THE CLAMPS AND RETORQUED SWIVEL GLAND, RAN APU AND ENGINE. LEAK CHECK OK PER BAC MM 36-00-001. OK TO CONTINUE.

Part: CHECK VALVE — LEAKED (NR 3 ENGINE)

99-138 - NR 3 ENGINE OVERHEAT LIGHT CAME ON DURING CLIMB-OUT. RED TAB PROC ACCOMPLISHED. REMOVED AND REPLACED BLEED CHECK VALVE PER MM 36-10-21, PAGE 401, OPER CHECK OK.

Part: ACTUATOR — LEAKING (NR 14 SPOILER)

SYS-A HYD QUANTITY WENT TO 0. EXEC RED TABS LANDING UNEVENTFUL. FOUND NR 14 SPLR ACTUATOR LEAK. REMOVED AND REPLACED NR 14 SPLR ACTUATOR PER M/M 27-61-81 PG 501. SERVICED A-SYS RESERVOIR TO FULL PROGRESS REPORT COMPLETED.

Part: CHORD — CORRODED (BS 760-848)

NR 0149 010, CORROSION ON LONGITUDINAL BS 760-848, LBL 25, WL 208 UNDER NUTPLATES AND EMANATING UNDER TRACK. REMOVED AND REPLACED LONGITUDINAL BEAM BS 760-848, LBL 25, WL 208 PER FED-EX SRM 51-10-1 AND 51-30-2.

Part: STRINGER — DENTED (BS 565)

NR 0569 008 WHILE WORKING NR 0296, FOUND STRINGER TO BE DAMAGED OUT OF LIMITS BS 565, STR 28 LT. REMOVED AND REPLACED DAMAGED STRINGER 28 LT, BS 565 IAW FED-EX SRM 53-10-2, 53-10-3.

Part: SKIN — CREASE (BS 565)

NR 0296 009 CREASE IN EXTERIOR SKIN BS 565, STR 28-29 LT. REPAIRED CREASE IN EXTERIOR SKIN BS 565, STR 28-29 LT IAW FED-EX SRM 53-30-3 FIG 3.

Part: KEEL BEAM — CORRODED (BS 746)

NR 0165 005, CORROSION (C53-100-01,4) ON DELTA KEEL BEAM BS 746, RBL 5, WL 144. *S/D* REMOVED DELTA TO KEEL BEAM SPLICE PLATE BS 730 TO 750, WL 148, RBL 7. CLEANED OUT CORROSION AND REINSTALLED SPLICE PLATE AND ALL ITEMS REMOVED FOR ACCESS IAW FED-EX SRM 51-10-2, 51-40-2, 51-30-2, FED-EX M/M 51-20-151 AND BAC DRW 6523555.

Part: FLAP — DELAMINATED (RT TE FOREFLAP)

NR 0414 003, RT I/B FOREFLAP ON UPPER SURFACE I/B END IS GOUGED AND DELAMINATED. *S/D* REMOVED RT I/B FOREFLAP AND REPAIRED RUBSTRIPS ON UPPER SURFACE I/B END AND REINSTALLED FOREFLAP AND FUNCTIONAL TESTED WORK DONE IAW FED-EX SRM 51-40-6, FED-EX M/M 27-51-1, FED-EX M/M 27-51-11.

Part: INTERCOSTAL — CORRODED (BS 740)

NR 0166 004, CORROSION (C53-100-01,4) ON T-ANGLE INSIDE DELTA BOX BS 741, RBL 2, WL 144. *S/D* REMOVED OLD T-ANGLE AND INSTALLED NEW T-ANGLE, AT BS 740, WL 148, LBL 15 TO RBL 5 IAW FED-EX SRM 51-30-2.

Part: SHEAR TIE — CORRODED (BS 540)

NR 0280 001, CORROSION ON SHEAR TIE STA 540, RBL 15, WL 148 FWD CARGO BAY. *S/D* REMOVED SHEAR TIE ON BS 540, RBL 15, WL 148 FWD CARGO BAY DUE TO IT BEING OUT OF LIMITS PER FED-EX SRM 53-10-1. INSTALLED NEW SHEAR TIE PER FED-EX SRM 51-30-2, ALODINED, PRIMED AND PAINTED PER FED-EX SRM 51-10-2 AND FED-EX M/M 51-20-151.

Part: PRESSURE WEB — DENTED (BS 269)

NR 0354 002, DOUBLER STRAP IS CRACKED AND PRESSURE WEB DENTED AT BS 269, LBL 13.5, WL 193. *S/D* FABRICATED AND INSTALLED NEW DOUBLER STRAP AND REPAIRED PRESSURE WEB AT BS 269, LBL 13.5, WL 193 PER FED-EX SRM 51-40-2, 51-20-1.

Part: BEAM — CORRODED (BS 743-852)

NR 0150 007, CORROSION ON LONGITUDINAL BEAM BS 760 TO 848, LBL 45 UNDER NUT PLATES AND EMANATING FROM UNDER TRACK (MARKED). *S/D* REMOVED AND REPLACED LONGITUDINAL BEAM BS 760 TO 848, LBL 45, WL 208 PER FED-EX SRM 51-10-1 AND 51-30-2.

Part: BEAM — CORRODED (BS 743-852)

NR 0143 006, CORROSION UNDER NUT PLATES ON LONGITUDINAL BEAM BS 763 TO 848, RBL 25, WL 208 AND ONE MISSING NUT PLATE BS 846 (MARKED). *S/D* MECHANICALLY REMOVED CORROSION FROM UNDER NUT PLATES ON LONGITUDINAL BS 763 TO 848, RBL 25, WL 208. FOUND TO BE OUT OF LIMITS PER FED-EX SRM 53-10-1. INSTALLED NEW LONGITUDINAL AT BS 763 TO 852, RBL 25, WL 208 PER FED-EX SRM 51-30-2.

Part: HEAT EXCHG DUCT — DAMAGED (NR 3 ENGINE)

DURING CLIMBOUT, PASSING APPROXIMATELY 16,000 FT, GOT ENGINE 3 STRUT OVERHEAT LIGHT, ACCOMPLISHED CHECKLIST ITEMS PER ABNORMAL PROCEDURES CHECK LIST. LIGHT STAYED OUT WITH ALL THROTTLE SETTINGS. CHECKED ENGINE NR 3 STRUT DUCTS FOR LEAKS AND FOUND HEAT EXCHANGER DUCT CRACKED AT FLANGE THAT MEETS BLEED VALVE. ALSO, LOCATED SEVERAL CLAMPS LOOSE. REMOVED AND REPLACED NR 3 HEAT EXCHANGER DUCT. RAN ENGINE NR 3 TO TAKEOFF POWER AND CLIMB POWER. NO LEAKS NOTED AND OVERHEAT LIGHT DID NOT COME ON. INSTALLED DUCT DOES NOT HAVE AIR PROVISION FOR THRUST REVERSER OPERATION WITH APU AIR. ALSO, OPERATED ENGINE THRUST REVERSER, OPERATIONAL CHECK GOOD. TIGHTENED ALL LOOSE CLAMPS, NO LEAKS NOTED.

Part: OIL BYPASS SW — MALFUNCTIONED (NR 2 ENGINE)

NR 2 ENG SHUTDOWN DUE TO NR 2 OIL FILTER BYPASS LIGHT ON IN FLT AND WOULD NOT EXTINGUISH. REMOVED AND REPLACED MAIN OIL SCREEN. FOUND SMALL PIECES OF CARBON. RAN NR 2 ENG TO T/O POWER FOR 5 MINUTES. REMOVED AND REPLACED LOW OIL SCREEN, FOUND IT CLEANED. REMOVED AND REPLACED LOW OIL BYPASS SWITCH, SYS WORKED NORMAL WITH 32 ENG RUNNING.

Part: SWITCH — FAILED (NR 2 ENGINE)

NR 2 OIL FILTER BYPASS LIGHT ON AFTER TAKEOFF. SHUT DOWN AND RETURNED OIL PRESSURE 45, TEMPERATURE 90, QUANTITY 3.8. AIRCRAFT RELEASED FOR SERVICE PER MINIMUM EQUIPMENT LIST 79-4 CATEGORY B EXPIRATION 12 JUL 96. REF NR 2 OIL FILTER BY PASS INOPERATIVE, CHECKED WIRE INTEGRITY FOUND OK. CHECKED OIL FILTER BY PASS FOUND CLEAN DRAINED OIL TANK AND OIL PRESS SWITCH. REMOVED AND REPLACED SWITCH, RAN ENGINE TO TAKEOFF AND CHECKED NORMAL.

Part: CONNECTOR — DIRTY (NR 2 ENG)

SCL: ENG NR 2 OIL FILTER BYPASS LIGHT CAME ON AT FLT LEVEL 310, 1 HOUR INTO SECOND LEG. ENGINE SHUTDOWN PER PROCEDURES. NORMAL OIL QUANTITY AND PRESSURE. REMOVED CANNON PLUG FROM LOW OIL PRESSURE SWITCH AND OIL FILTER BYPASS SWITCH AND CLEANED WITH CONTACT CLEANER. REPLACED BOTH CANNON PLUGS. RAN ENG NR 2 AND ACCOMP B727 MEL. MX PROCEDURE 79-2. MX CONTROL NOTIFIED A/C OK FOR SERVICE.

Part: STRINGER — CRACKED (BS 720)

CABIN, STR END CRACKED 15R BETWEEN 720B AND 720C FWD OF LIGHT ASSY NR 1401. STOP DRILLED CRACK PER SRM 53-10-2, INSTALLED REPAIR PART PER SRM 53-10-3.

Part: FLOORBEAM — CORRODED (BS 1070)

CORROSION ON TOP AND BOTTOM OF FLOORBEAM AROUND MOUNT HOLES AT STA 1070 BETWEEN RBL 22.5 AND RBL 46. REPAIRED PER SRM 53-10-8.

Part: FLOORBEAM — CORRODED (BS 600)

TOP FLANGE OF FLOORBEAM AT STA 600 CORRODED BEYOND SRM LIMIT RBL 46.5 APPROX. CUT OUT DAMAGE, REPAIRED PER SRM 53-10-8 PG 44 TO 48. DAMAGE CUT OUT WAS 1 BY 1.5.

Part: FLOORBEAM — CORRODED (BS 1110)

CORROSION ON BOTTOM OF CABIN FLOORBEAM AROUND FLOOR BOARD ATTACH HOLES AT STA 1110 BETWEEN RBL 22.5 AND RBL 46. REPAIRED PER SRM 53-10-8.

Part: FLOORBEAM — CORRODED (BS 1110)

STA 1110 FLOORBEAM IS CORRODED ON TOP AND BOTTOM OF UPPER CAP AREA, WHERE FLOOR BOARDS MOUNT BETWEEN NR 5 AND NR 6 SEAT TRACKS. REPAIRED PER SRM 53-10-8.

Part: FLOORBEAM — CORRODED (BS 1070)

FLOORBEAM UPPER CAP WHERE FLOORBEAM MOUNTS IS CORRODED AROUND SCREW HOLES BETWEEN 5 AND 6 SEAT TRACKS STA 1070. REPAIRED PER SRM 53-10-8.

Part: FLOORBEAM — CRACKED (BS 380)

BS 380 RBL 26 TO 32, MAIN CARGO FLOORBEAM UPPER FLANGE IS CRACKED AND CORRODED. REMOVED CRACKED AND CORRODED SECTION OF UPPER FLANGE OF BS 380 RBL 16.75 AND 35.25 RBL, FLOORBEAM. FABRICATED DOUBLER PER SRM 53-10-8 PG 2A. INSTALLED FLOORBEAM REPAIR PER SRM 53-10-8 PG 2A.

Part: FLOORBEAM — CORRODED (BS 620)

CORROSION STA 620 LBL 12 CABIN FLOORBEAM. INSTALLED DOUBLER ASSY PER SRM 53-10-6 FIG 8.

Part: ANGLE — CORRODED (BS 620)

SIDEWALL SLANT PANEL ATTACHMENT IS CORRODED AT RT CREASE ANGLE ATTACHMENT JUST AFT OF STA 620, LWR AFT CORNER AREA OF DOOR CUTOUT. INSTALLED NEW SLANT PANEL ATTACH SUPPORT ANGLE AFT OF STA 620 RT, PER SRM 51-40 PAGE 1.