N218FE

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 56,903 hrs · 31,739 cycles

SEVERAL LOCATIONS OF CORROSION ON UPPER CHORD FROM FS 760 TO 840, LBL 45.5 REMOVED CORROSION BY REMOVING DAMAGED UPPER CHORD AT STA 760-850, LBL 45.5 REF SRM 51-30-2. REMOVED FLOOR SUPPORT T-CHORD AND ATTACHED FLOOR SUPPORT ASSY'S AT LBL 45.5-62.0 -25.0-45.5 STA 760-850 REF SRM 51-30-2 AND BOEING DWG 65-16279. INSTALLED SEAT TRACK TO NEW UPPER T-CHORD AT STA 760 - 850, LBL 45.5 REF SOPM20-50- 01. INSTALLED NEW BUSHING AT STA 738 REF AMM 20-10-007. INSTALLED FWD SEAT TRACK AND FITTING AT STA 850-870 PLUS FITTING AT STA 774, LBL 44, REF SRM 51-30-2 AND 51-30-4. INSTALLED T-CHORD STRAPS REF SRM 51-30-2. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: WINDOW — CORRODED (ZONE 200) · corrosion level 2 · airframe 56,903 hrs · 31,739 cycles

RT WINDOW PLUG AT BS 950 PLUS 10" AND 1020 HAVE CORROSION ON EXT SURFACE. REMOVED AND REPLACED WINDOW PLUGS AT BS 950 PLUS 10" AND 1020 RT SIDE INSTALLED BONDING STRAP (GROUND), PAINTED NEW PLUGS REF MM 56-20-004, SOPM 20-41-02, SWPM 20-20-00 PG4-8. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SKIN — GOUGED (ZONE 800) · airframe 56,903 hrs · 31,739 cycles

RT OVERWING DOOR EXT SKIN IS CORRODED/GOUGED ALONG LWR EDGE. REMOVED CORROSION AND GOUGE REF SRM 51-10-02 AND SRM 52-00-2, CHECKED LIMITS, ORIGINAL "T" IS .045, MATERIAL "T" REMOVED .015" REMAINING "T" IS .030". OUT OF LIMITS VERIFIED BY SRM 52-00-2 PAGE 3 FIG 2. MANUFACTURED REPAIR PARTS REF SRM 53-00-3 FIG 4 PG 8. REPAIR DOUBLER REF SRM 52-00-3 FIG NR 4. INSTALLED FILLER AND DOUBLER REF SRM 51-30-2 PG 2. RE-FINISHED REF SRM 51-10-2. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: FRAME — CRACKED (ZONE 100) · airframe 56,903 hrs · 31,739 cycles

LOWER STUB FRAME EXTENTION AT BS 560, WEB IS CRACKED ABOVE AND INBD OF STR 21 L, AT RIVET HOLE MARKED END OF DOT WITH BLACK DOT REPLACED LOWER STUB FRAME EXTENSION REF SRM 51-30-2, AND DWG 53FX1350. TREATED AND PRIMED REF SRM 51-10-2.

Part: FLOORBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 56,903 hrs · 31,739 cycles

SEVERAL LOCATIONS OF CORROSION ON FLOORBEAM FROM FS 760 TO 840, RBL 45.5. REMOVED FLOORBEAM STA 760 - 840, RBL 45.5. FABRICATED AND INSTALLED REPLACEMENT FLOORBEAM IAW DWG 65-16279 AND SRM 51-30-02 P1. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: FLOOR SUPPORT — CRACKED (ZONE 100) · airframe 56,903 hrs · 31,739 cycles

LOWER FOWARD PIT, STATION 680, FRAME AFT SIDE, RBL 13, BETWEEN STRINGERS 27R AND 28R, FRAME TO FLOOR SUPPORT STRUCTURE ANGLE GOUGE/CRACKED IN RADIUS. REMOVED CRACKED FLOOR SUPPORT CLIP. FABBED NEW CLIP AND DRILLED REF BOEING DWG 65-75172.

Part: SKIN — DENTED (ZONE 100) · airframe 56,903 hrs · 31,739 cycles

LOWER FORWARD PIT DOOR CUTOUT FORWARD SIDE FUSELAGE SKIN DENTED MEASURE DENT A=2" Y= .073" A/Y= 13.69 DENT WAS OUT OF LIMITS. TRIMMED OUT DENT. REMOVED .310" MATERIAL. REPAIR IS WITHIN LIMITS REF EA 7-5330-113955. USED TOOL IN17-0023 CAL DUE 12-13-08 TO MEASURE DENT. REF SRM 51-30-1 PG 2A. THIS IS A TIME LIMITED REPAIR LIMITED TO 24 MONTHS OR 3000 FLIGHT CYCLES WHICH EVER OCCURS FIRST. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: RETAINER — CORRODED (ZONE 200) · corrosion level 2 · airframe 56,903 hrs · 31,739 cycles

RT FWD OVERWING DOOR FRAME, PRESSURE SEAL ATTACH ANGLE IS CRACKED/CORRODED ON ALL FOUR SIDES AS MARKED REMOVED UPPER AND LOWER SEAL ATTACH ANGLES. INSTALLED 2 NEW ANGLE TO DOOR FRAME REF 51-30-02. REPAIR IS CLASSIFIED AS A MINOR.

Part: SKIN — CRACKED (ZONE 800) · airframe 56,903 hrs · 31,739 cycles

RT MLG GEAR DOOR INSIDE SKIN IS CRACKED REMOVE DAMAGED AREA, INSTALL REPAIR SKIN, DBLR, ACCESS PLATE, REF EO7-5280-7-4301 AND SRM 51-30-2, THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: CHANNEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,903 hrs · 31,739 cycles

AFT PIT FLOOR SUPPORT "C" CHANNEL IS CORRODED BS 1165, RBL 7, WL 160. REMOVED DAMAGE IAW SRM 51-10-1 PG 1. FABRICATED REPAIR CHANNEL, AND 2 ANGLES IAW SRM 53-10-5 PG 9/10. INSTALLED REPAIR PARTS IAW 53-10-5, AND 51-30-02 THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: ATTACH FITTING — CRACKED (ZONE 600) · airframe 56,903 hrs · 31,739 cycles

RT AILERON (OTBD) CAVITY HAS CRACKED ATTACH CLIP LOCATED BET WING TRAILING EDGE RIB AT STA 658.63 AND CAVITY AFT SPAR FABRICATED CLIP BETWEEN WING TRAILING EDGE, STA 658.63 CAVITY AFT SPAR. REF SRM 51-30-02, DWG 65-19289 PG 1. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 56,903 hrs · 31,739 cycles

LT OUTBOARD AFT FLAP, T/E INBOARD CORNER IS DELAMINATED REPAIRED LT OUTBOARD AFT FLAP T/E CORNER REF SRM 51-40-20 PARA 6, 7, 19, -21. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — CORRODED (ZONE 200) · corrosion level 2 · airframe 56,903 hrs · 31,739 cycles

LT 10TH WINDOW PLUG AFT OF AFT OVERWING EXIT HAS CORROSION INSTALLED NEW WINDOW PLUG, PAINTED TO MATCH, REF MM 51-20-013-PG 1-3 AND MM 51-20- 151-7 PAGES 1-3.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 56,903 hrs · 31,739 cycles

MAIN CABIN, FS 312 TO 328, LBL 30 FLOOR SUPPORT CORRODED. REPLACED FLOOR SUPPORT REF DWG 65-17593 AND SRM SRM 51-30-02 PG 1.

Part: DOOR FRAME — CORRODED (BS 760-783) · corrosion level 2 · airframe 56,903 hrs · 31,739 cycles

RT FWD OVERWING DOOR FRAME EXTERIOR SURFACE IS CORRODED AT 7:00 POS AS VIEWED FROM OUTSIDE REMOVED CORROSION ON DOOR FRAME REF SRM 51-10-6, MEASURED THICKNESS REF 727 NDT MAN PT 4, 51-00-00, FIG 2 ORIGINAL "T" .063". REMAINING "T" IS .060" IN DEEPEST LOCATION .003 MATERIAL LOSS WITHIN LIMITS REF SRM 52-00-2 PG 3 NOTE A TOOL II IN22-0029. CAL DUE 9-28-08 TREATED AND PRIMED REF SRM 51-10-2. LEVEL 1 CORROSION. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: DOOR FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,903 hrs · 31,739 cycles

RT AFT OVERWING DOOR FRAME EXTERIOR SURFACE IS CORRODED ALONG PRESSURE SEAL ATTACH ANGLE AT 5:00 TO 8:00, POS AS VIEWED FROM OUTSIDE. REMOVED CORROSION FROM FRAME SURFACE REF SRM 51-10-1 PG 14-16. MEASURED THICKNESS REF. 727 NDT MAN. PT. 4, 51-00-00. FIG 2, ORIGINAL "T" .040", REMANING "T" .036" IN DEEPEST LOCATION. REMOVED .004" MATERIAL LOSS WITHIN LIMITS REF SRM 52-00-2 PG 3, NOTE A TOOL NR 22-029 CAL DUE 9-28-08. TREATED AND PRIMED, REF SRM 51-10-2. LEVEL 1 CORROSION. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: RETAINER — CRACKED (ZONE 600) · airframe 56,903 hrs · 31,739 cycles

RIGHT WING LOWER TRAILING EDGE PANEL JUST BELOW NR 11 FLIGHT SPOILER ACTUATOR BULB SEAL RETAINER CRACKED. REPLACED SEAL RETAINER REF 51-30-2. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,903 hrs · 31,739 cycles

CORROSION ON FWD FRAME AROUND MESC ACCESS DOOR FWD LOCK PIN PLATE, FS 423, BL 0 WL 151. REMOVED CORROSION ON FWD FRAME FOR MESC DOOR, ORIGINAL .040, REMOVED .012", REMAINING .028". LOT OF LIMITS REF SRM 51-10-1 PG 2, NOTE J, AND 53-10-1 PG 2A FIG 1. SHEET 3 DETAIL 4, TOOL NR IN17-0623, CAL DUE 9-18-08. REMOVED AND INSTALLED NEW FRAME.REF 51-20-1 PG 14 FIG 3. HEAT TREATED NEW FABBED FRAME REF NR N00461. REMOVED AND REINSTALLED PANELS FOR ACCESS AT RBL 14, STA 420-450, LBL 14 STA 420-450. REF SRM 51-30-2. TREATED AND PRIMED REF 51-10-2 APPLIED RESIN, POTTING COMPOUND REF SRM 51-40-1 AMM 52-00-00 ADJUSTED DOOR REF MM 52-40-011-1, THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: ATTACH FITTING — CRACKED (ZONE 100) · airframe 56,903 hrs · 31,739 cycles

5" CRACK ON RT ATTACH FITTING FOR BULKHEAD 1183 BEAM AT BS 1182, BL 0, WL 166 TO 161. REPLACED CHANNEL, REF DWG 69-13353, REF SRM 51-30-2 PG 1. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — CORRODED (ZONE 200) · corrosion level 2 · airframe 56,903 hrs · 31,739 cycles

19TH RT WINDOW PLUG EXTERIOR SURFACE HAS CORROSION (APPROX 720C 6"). REMOVED AND REPLACED WINDOW PLUG REF MM 56-20-000-4, PRIMED AND PAINTED REF SRM 51-10-2 APPLIED LPS REF 51-10-2. THIS REPAIR IS CLASSIFIED AS A MINOR REPAIR.

Part: SKIN — CORRODED (ZONE 200) · corrosion level 2 · airframe 56,903 hrs · 31,739 cycles

13TH LT WINDOW PLUG AFT OF AFT OVERWING EXIT HAS CORROSION ON EXT SURFACE INSTALLED NEW WINDOW PLUG REF MM 56-20-000-4 APPLIED CIC TO INTERIOR REF SRM 51-10-2, PAINTED TO MATCH SRM 51-10-2. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: STRINGER — CORRODED (BS 1178) · corrosion level 2 · airframe 56,903 hrs · 31,739 cycles

AFT PIT BILGE STRINGER END FITTING IS CORRODED BS 1178, STR 29L, WL155 (MKD). REMOVED AND REPLACED STR 29L END FITTING PN NR 65-60208-1 IAW 51-30-2. REMOVED CORRODED SECTION OF STR 29L AND REPAIRED STR 29L IAW SRM 53-10-3 FIG I DETAIL I STA 1178-1164. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — DELAMINATED (RT WING TE FLAP) · airframe 56,903 hrs · 31,739 cycles

RIGHT WING INBOARD FOREFLAP UPPER SURFACE DELAMINATED 72" FROM INBOARD EDGE. REPAIRED SURFACE DELAMINATION REF SRM 51-40-20 PARA'S 7, 14, 15, 19, 20, 22 TAP TEST GOOD. THIS IS CLASSIFIED AS A MAJOR REPAIR. PRIMED AND PAINTED REPAIR AREA REF M/M 51-20-151-7.

Part: STRINGER CLIP — CRACKED (BS 1070 S28L) · airframe 56,903 hrs · 31,739 cycles

STRINGER CLIP CRACKED ON STR 28L, FS 1070. REMOVED STRINGER CLIP REF SRM 51-30-2. FABRICATE NEW STRINGER CLIP 7075-T6 .040 REF BOEING DRW 66-11809-6 PG 1/2. TREATED STRINGER CLIP REF SRM 51-10-2. PRIMED STRINGER CLIP REF SRM 51-10-2. INSTALLED STRINGER CLIP REF SRM 51-30-2. THIS IS CLASSIFIED AS A MAJOR REPAIR.

Part: SKIN — DELAMINATED (ZONE 600) · airframe 56,903 hrs · 31,739 cycles

RIGHT WING INBOARD FOREFLAP UPPER SURFACE DELAMINATED 96" FROM INBD EDGE. REPAIR SURFACE DELAMINATION REF SRM 51-40-20 PARA'S 7, 14, 15, 19, 20, 22. TAP TEST GOOD PRIMED AND PAINTED REPAIR AREA, REF MM 51-20-151-7. THIS IS CLASSIFIED AS A MINOR REPAIR.

Part: SKIN — GOUGED (FORE FLAP) · airframe 56,903 hrs · 31,739 cycles

RIGHT WING INBOARD FORE FLAP UPPER SURFACE GOUGE, 93" FROM INBOARD EDGE. REPAIR SURFACE DELAMINATION REF SRM 51-40-20 PARA, S 7, 14, 15, 19, 20, 22 TAP TEST GOOD. PRIMED AND PAINTED AREA REF MM 51-20-151-7. THIS IS CLASSIFIED A MINOR REPAIR.

Part: HYDRAULIC SYSTEM — DISCHARGED (A SYSTEM) · airframe 56,464 hrs · 31,403 cycles

HYD "A" SYSTEM DEPLETED W/FLAPS SELECTED TO 2 ON APPROACH ON 27 MEM. NR 2 "A" PUMP LIGHTS ON FOR 2-3 MINS, FLUID SHUTOFF SWITCHES OF 2-3 MINS.

Part: FRAME — CRACKED (BS 560) · airframe 56,304 hrs · 31,277 cycles

MAIN CARGO DOOR LOWER SILL AFT STUB FRAME AT STATION 560 IS CRACKED ALONG INBD RADIUS. FABRICATED AND INSTALLED NEW STUB FRAME PER FEDEX DWG 53FX1349 REV F AND SRM 51-30-02 PG 13.

Part: FRAME — CRACKED (BS 540) · airframe 56,304 hrs · 31,277 cycles

MAIN CARGO DOOR LOWER SILL AFT STUB FRAME AT STATION 540 IS CRACKED ALONG INBD RADIUS. FABRICATED AND INSTALLED NEW STUB FRAME PER FEDEX DWG 53FX1349 REV F AND SRM 51-30-02 PG 13.

Part: PROXIMITY SENSOR — MALFUNCTIONED (MLG) · airframe 56,174 hrs · 31,176 cycles

AFTER TAKE-OFF, COULD NOT RAISE LANDING GEAR LEVER PAST (OFF) POSITION RAN QRM PROCEDURES, AND FAILED TEST NR 1 OF STRUT EXTENSION AND NOSE ALIGNMENT TEST. REMOVED AND REPLACED AIR SENSING PROX SENSOR(M831). PERFORMED OPS CKS PER M/M 32-09-221-4 AND 32-31-011-5. FACT 27SEP06 20:51 ATL U C/W MLG SENSOR REPLACEMENT TEST PER EA 7-3200-105125. OPS CK GOOD. SERVICED MLG STRUTS PER AMM 12-15-021. RII: 306877 ENT BY: 226917 RPT BY: 226917

Part: STRUCTURE — GROUND DAMAGE (FUSELAGE) · airframe 55,897 hrs · 30,933 cycles

LEFT SIDE OF FUSELAGE JUST FWD OF WING L/E WAS STRUCK BY VENDORS CREW, ENTRY STAIRS CAUSING MAJOR DAMAGE. REPAIRED FUSELAGE SKIN DAMAGE AS PER E.A. 7-5330-100531 AND SRM 53-30-3 FIG.12.REF N/R 9

Part: ATTACH FITTING — GOUGED (CARGO DOOR) · airframe 55,071 hrs · 30,408 cycles

GOUGE IN MAIN CARGO DOOR UPPER SKIN ATTACH FITTING, FITTING AT BODY STATION 640 JUST ABOVE STRINGER 2 LEFT. REMOVED AND REPLACED BS 640 ATTACH FITTING ABOVE STR 3 LT CARGO DOOR UPPER SILL PER EA 7-5330-92260A.

Part: CHANNEL — DAMAGED (BS 620) · airframe 55,071 hrs · 30,408 cycles

WHILE WORKING FED EX EA 7-5330-72293B PT2 FOUND 2 FASTENER HOLES ON EDGE OF "C" CHANNEL BS 620 LBL-36 W/L 292. REPAIRED C-CHANNEL, BS 620, LBL 36 PER FED-EX EA 7-5330-92321.

Part: SKIN — DAMAGED (BS 620) · airframe 55,071 hrs · 30,408 cycles

FOUR HOLES BS 620 STR 2L BUCKTAILS BEHIND EXISTING STRUCTURE. REPAIRED HOLES, BS 620, STR 2L PER FED-EX EA 7-5330-92260A.

Part: SKIN — DAMAGED (BS 640) · airframe 55,071 hrs · 30,408 cycles

THREE HOLES, BS 640 STR 2L, BUCKTAILS BEHIND EXISTING STRUCTURE. *S/D* REPAIRED HOLES, BS 640, STR 2L, PER FED-EX EA 7-5330-92260A.

Part: SILL — DAMAGED (BS 604) · airframe 55,071 hrs · 30,408 cycles

OPEN HOLE NEXT TO FASTENER AT BS 604 MCD UPPER SILL O\B CHORD. REPAIRED OPEN HOLE, BS 604 IN MCD UPPER SILL PER FED-EX EA. 7-5310-92265.

Part: FITTING — DAMAGED (BS 640) · airframe 55,071 hrs · 30,408 cycles

ONE HOLE BS 640 BUCKTAIL BEHIND INTERNAL FITTING BETWEEN STR 3L-4L. REPAIRED HOLE, BS 640 BETWEEN STR 3L & 4L PER FED-EX EA. 7-5330-9226A.

Part: FRAME — DAMAGED (BS 620) · airframe 55,071 hrs · 30,408 cycles

N01449, WHILE WORKING EA 7-5330-72293B PT 2, FOUND DOUBLE HOLE IN FRAME AT 620 LBL 21 WL 302. REPAIRED DOUBLE HOLE IN FRAME, BS 620, LBL 21 PER FED-EX EA 7-5330-92327.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

WHILE WORKING FED EX EA 7-5330-72293B PT2, FOUND FASTENER HOLES ON EDGE OF FRAME WITH NO EDGE DISTANCE, BS 620 LBL-9 W/L 302 AND 303 2 EA. REPAIRED FRAME BS 620, LBL 9 PER FED-EX EA 7-5330-92323.

Part: FRAME — DAMAGED (BS 610) · airframe 55,071 hrs · 30,408 cycles

PILOT HOLES NEXT TO FASTENER HOLES IN STUB FRAME BS 610 STR3L. REPAIRED FRAME PER FED-EX EA 7-5330-92328. [CLOSED]

Part: FRAME — DAMAGED (BS 620) · airframe 55,071 hrs · 30,408 cycles

WHILE WORKING FED EX EA 7-5330-72293B PT2, FOUND DOUBLE HOLE IN FRAME "C' CHANNEL AND SUPPORT AT BS 620 LBL 22 WL 300. REPAIRED C-CHANNEL, BS 620, LBL 22 PER FED-EX EA 7-5330-62327.

Part: SILL — DAMAGED (CARGO DOOR) · airframe 55,071 hrs · 30,408 cycles

N01472 BS 364 - BS 640, STR 3L WHILE WORKING NR N01466, FOUND NUMEROUS HOLES IN MAIN CARGO DOOR UPPER SILL TO BE FIGURE EIGHTED. B.S 634 TO 640 JUST ABOVE STR.3L. (OPEN)

Part: FRAME — DAMAGED (BS 620) · airframe 55,071 hrs · 30,408 cycles

WHILE WORKING FED EX EA 7-5330-72293B PT2, FOUND DOUBLE HOLES IN FRAME AND C-CHANNEL AT 620 RBL 8 W/L 304. (OPEN)

Part: FRAME — DAMAGED (BS 620) · airframe 55,071 hrs · 30,408 cycles

WHILE WORKING FED EX EA 7-5330-72293B PT2, FOUND FASTENER HOLES ON EDGE OF C-CHANNEL FRAME BS 620 STR 2 RT. REPAIRED PER SRM 53-10-1.

Part: FRAME — DAMAGED (STA 620) · airframe 55,071 hrs · 30,408 cycles

WHILE WORKING FED EX EA 7-5330-72293B PT 2 FOUND DOUBLE HOLE IN FRAME 620 LBL 7 AND LBL 8 W/L 298. FRAME REPLACED PER FED-EX EA 7-5330-92326.

Part: DOUBLER — GOUGED (CARGO DOOR) · airframe 55,071 hrs · 30,408 cycles

MAIN CARGO DOOR FORWARD SIDE FRAME GOUGED ON REPAIR DOUBLER MIDWAY UP DOOR. INSTALLED NEW RAPAIR DOUBLER PER FED EX EZA 7-5230-92257

Part: ATTACH FITTING — CORRODED (NR 8 FLAP TRACK) · airframe 55,071 hrs · 30,408 cycles

CORROSION (27X5710-02) NR 8 FLAP TRACK FWD ATTACH FTG ON WING IS CORRODED ON I/B FACE. REPAIRED FITTING PER EA 7-5750-92237

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

WHILE WORKING NR00631 FOUND STRINGER CLIP AT BS 540 STR 22R CRACKED. REPLACED STRINGER CLIP PER SRM 51-30-2.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, STRINGER CLIP IS CRACKED, BS 950D, STR 9R. REPLACED STRINGER CLIP PER SRM 51-30-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOCE, LONGITUDINAL FLOOR SUPPORT, HAS CORROSION ON I/B AND O/B UPPER FLANGES, UNDER NUT PLATES FROM BS 760 TO 850, LBL 25. REPLACED BEAM PER SRM 51-30-2.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

N00923 AFT CARGO FRAME SHEAR TIE IS CORRODED BS 1130 LBL 9. FABRICATED DRILLED ALODINED AND INSTALLED SHEAR TIE REPAIR PER SRM 53-10-4

Part: FRAME — CHAFED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

N01117 FUSELAGE UPPER LOBE, IS CHAFED ON INNER FLANGE , BS 1030, STR 9L. CUT OUT DAMAGE ON FRAME INNER FLANGE AT BS 1030 STR 9L AND INSTALLED REPAIR PARTS PER SRM 51-40-3.

Part: DOOR — DAMAGED (EMERGENCY EXIT) · airframe 55,071 hrs · 30,408 cycles

REWORK REQUIRED, LT AFT OVERWING EMERGENCY ESCAPE DOOR EXTERNAL SKIN REPAIR DOUBLER UPPER EDGE BENT AT 2 LOCATIONS. REJECTED DUE TO NO BLEND LIMITS ON REPAIR DOUBLER. REPAIRED LT AFT EMERGENCY ESCAPE DOOR EXTERNAL SKIN PER SRM 52-00-3.

Part: FRAME — CHAFED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, FRAME REPAIR IS CHAFED, BS 970, STR 9R. REPAIRED FRAME PER SRM 51-40-3.

Part: FRAME — CHAFED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, FRAME IS CHAFED, BS 990, STR 9R. REPAIRED FRAME PER SRM 51-40-3.

Part: BULKHEAD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 55,071 hrs · 30,408 cycles

BS 870 BULKHEAD HAS CORROSION ON FWD AND AFT SIDE AT WIRE CONNECTOR ATTACH PLATE, LBL 42. REMOVED CORROSION, FABRICATRED, ALODINED, PRIMED AND INSTALLED REPAIR PARTS PER SRM 53-10-1, 51-30-2 AND 53-10-9.

Part: WEB — DAMAGED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FIG 8 HOLE AT BS 640 STR 5R FRAME WEB. REPLACED FRAME PER SRM 51-30-2.

Part: STRINGER CLIP — CRACKED (FUSLAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, STRINGER CLIP IS CRACKED, BS 950A, STR 7L . REMOVED AND REPLACED STR CLIP PER SRM 51-30-2.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, STRINGER CLIP IS CRACKED, BS 950E, STR 4L. REMOVED & REPLACED STR. CLIP PER SRM 51-30-02

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, STRINGER CLIP IS CRACKED, BS 950E, STR 3L. REMOVED AND REPLACED STRINGER CLIP PER SRM 51-30-02

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, STRINGER CLIP IS CRACKED, BS 950B, STR 6L. REMOVED AND REPLACED STR CLIP PER SRM 51-30-2.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

3 FIGURE 8 HOLES AT BS 460 FRAME VERTICAL FLANGE STR 5R. REPLACED FRAME PER SRM 51-30-2.

Part: STRINGER CLIP — CRACKED (FUSLAGE) · airframe 55,071 hrs · 30,408 cycles

N01123 E & E BAY STA 460, RBL 6, WL 145 STR CLIP IS CRACKED. REMOVED FABRICATED AND INSTALLED STRINGER CLIP BS 460 RBL 6 WL 145 PER SRM 51-20-1 AND SRM 51-30-2

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, CRACKED STRINGER CLIP, BS 560, STR 7R. REPLACED CRACKED STRINGER CLIP PER SRM 51-30-.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, STRINGER CLIP IS CRACKED, BS 700, STR 6. REMOVED FABRICATED AND REPLACED STRINGER CLIP AT BS 700 STR 6R PER SRM 51-30-02, 51-20-1, 51-10-02

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, CRACKED STRINGER CLIP, BS 580, STR 7R. REPLACED CRACKED STRINGER CLIP PER SRM 51-30-2.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, STRINGER CLIP IS CRACKED, BS 680, STR 7R. REMOVED, FABRICATED AND INSTALLED STRINGER CLIP AT BS 680 STR 7R IAW SRM 51-30-02 AND DRAWING 65-45313.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE STRINGER CLIP CRACKED BS 680 STR-5L. REMOVED FABRICATED AND INSTALLED STRINGER CLIP AT BS 680 STR 5L IAW SRM 51-20-1, 51- 30-02, 51-10-02.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

CRACKED STRINGER CLIP BS 990 AT STRINGER 28L FWD SIDE OF FRAME. REPLACED CRACKED STRINGER CLIP PER SRM 51-10-1.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, STRINGER CLIP IS CRACKED, BS 660, STR 8R. REMOVED FABRICATED AND INSTALLED STR. CLIP AT BS 660 STR 8R IAW SRM 51-20-1 & 51-30- 02.

Part: STRINGER CLIP — MISSING (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE STRINGER CLIP MISSING FRAME ATTACH FASTENERS BS 680, STR 6L. REMOVED, FABRICATED AND INSTALLED STRINGER CLIP AT BS 680 STR 6L IAW SRM 51-20-1, 51- 30-02 AND 51-10-02.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, STRINGER CLIP IS CRACKED, BS 950B, STR 8R. REPLACED CRACKED STRINGER CLIP PER SRM 51-30-2.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, STRINGER CLIP CRACKED, BS 640, STR. 9 RT.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 55,071 hrs · 30,408 cycles

FUSELAGE UPPER LOBE, STRINGER CLIP IS CRACKED, BS 950C, STR 8R. REPLACED CRACKED STRINGER CLIP PER SRM 51-30-2.

Part: PUMP — MALFUNCTIONED (FUEL BOOST) · airframe 54,623 hrs · 30,127 cycles

ON TAKEOFF ROLL, NR 2 FUEL TANK LEFT FORWARD BOOST PUMP CIRCUIT BREAKER POPPED; 3 SECONDS LATER, RIGHT AFT BOOST PUMP CIRCUIT BREAKER POPPED. NOTE: USING GEN 1 FOR ESSENTIAL POWER. CHECKED PER 24-09-100-2 FOUND OK. CHECKED PER 28-22-000-1 FOUND OK. REMOVED & REPLACED NR 2 LEFT FORWARD B/P CIRCUIT BREAKER. RAN NR 2 ENGINE PER JRH. NO CIRCUIT BREAKERS POPPED. OK FOR SERVICE.

Part: CLAMP — LOOSE (ZONE 400) · airframe 52,631 hrs · 28,902 cycles

DURING CLIMBOUT PASSING APPROX FL270 22 ENG 1 STRUT OVERHEAT 22 LIGHT ILLUMINATED. PERFORMED THE APPROPIATE RED TAB PROCEDURE AND LIGHT EXTINGUISHED. AFTER CLOSING N1 BLEED. SUSPECT AIR BLEED LEAK ITS ON THE FUSELAGE SIDE OF THE BLEED AIR VALVE PER RED TABS. PERFORMED HI-POWER NUMBER 1 ENGINE RUN-UP WITH CREW. FOUND AT NUMBER 1 BLEED AIR VALVE EXIT 2C CLAMP LOOSE. ADJUSTED CLAMP PROPERLY CHECK NO AIR LEAKS 22 ENG 1 STRUT OVERHEAT 22 LIGHT NOT ILLUMINATED DURING THE HI-POWER ENGINE RUN-UP.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 52,267 hrs · 28,697 cycles

DRAIN BAY AT STA. 295 TO 280 WL 147.5 BS 27L HAS SKIN FRAYING AND CHIPPING IN DRAIN BAY. REPAIRED DRAIN BAY STRUCTURE IN ACCORDANCE WITH FEDEX E.A. 7-5310-69487

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 52,267 hrs · 28,697 cycles

CORROSION ON FRAME 294, WL 148.5, LBL 18 ON NLG WHEEL WELL LBL BULKHEAD. REPAIRED NOSE LANDING GEAR WHEEL WELL BULKHEAD IN ACCORDANCE WITH FEDEX E.A. 7- 5310-69487.

Part: BULKHEAD — CRACKED (ZONE 100) · airframe 52,267 hrs · 28,697 cycles

RIGHT MLG WHEEL WELL STATION 870 BULKHEAD IS CRACKED AT RBL 56 W/L 185.5. REPAIRED IN ACCORDANCE WITH FEDEX EA 7-5310-69465.

Part: BULKHEAD — CRACKED (ZONE 100) · airframe 52,267 hrs · 28,697 cycles

LEFT MLG WHEEL WELL STATION 870 BULKHEAD IS CRACKED AT LBL 42 APPROXIMATELY W/L 185.5 AND BELOW HORIZONTAL CHORD REPAIRED IN ACCORDANCE WITH FEDEX EA 7-5310- 69465.

Part: BRACKET — CRACKED (LT WING) · airframe 52,267 hrs · 28,697 cycles

LEFT WING TIP UPPER SUPPORT BRACKET FOR NAVIGATION LIGHT LENS HAS 1.5 INCH CRACK IN RADIUS OF BRACKET. FABRICATED AND INSTALLED BRACKET IAW BOEING 727 SRM 51-20-1 AND 51-30-2.

Part: PANEL — TORN (CARGO BAY) · airframe 52,267 hrs · 28,697 cycles

MAIN CABIN 2 EA GILLINER PANELS TORN AT LEFT SIDE STA 1160. *S/D* FABRICATED GILLINER IAW FED EX SRZ 25-005C.

Part: STRUCTURE — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 52,267 hrs · 28,697 cycles

RIGHT WING INBOARD MID FLAP HAS 2 EACH AREAS OF CORROSION. REPAIRED AREAS IAW FED EX SR 27-51-002.

Part: FAIRING — GOUGED (LT WING) · airframe 52,267 hrs · 28,697 cycles

LEFT WING NR 2 FLAP TRACK MOVABLE FAIRING GOUGED ON INNER SURFACE OUTBOARD SIDE AFT OF FORWARD STIFFENER. *S/D* REPAIRED IAW BOEING 727-200 SRM 57-20-04.

Part: LINER — DETERIORATED (SERVICE DOOR) · airframe 52,267 hrs · 28,697 cycles

RIGHT AFT SERVICE DOOR LINER DETERIORATED.

Part: STIFFENER — GOUGED (LT WING) · airframe 52,267 hrs · 28,697 cycles

LEFT WING NR 3 FLAP TRACK MOVABLE FAIRING INBOARD FORWARD INTERNAL STIFFENER GOUGED. REMOVED AND REPLACED RIB STIFFENER IAW BOEING 727-200 SRM 57-20-03.

Part: BUSHING — GOUGED (AC PACK DOOR) · airframe 52,267 hrs · 28,697 cycles

RIGHT PACK COOLING DOOR ACTUATOR ROD OPENING ELONGATED AND GOUGED. REMOVED AND REPLACED BUSHINGS IAW BOEING 727 SOPM 20-50-03 AND REMOVED AND REPLACED SKIN IAW BOEING 727-200 SRM 51-30-02.

Part: SUPPORT — CORRODED (BS) · corrosion level 2 · airframe 52,267 hrs · 28,697 cycles

AFT CARGO WALL SUPPORT LEFT AT STA 950E HAS NUMEROUS AREAS OF CORROSION. FABRICATED WALL SUPPORT IAW BOEING 727-200 SRM 51-20-1.

Part: FAIRING — GOUGED (RT WING) · airframe 52,267 hrs · 28,697 cycles

RT WING NR 8 FLAP TRACK MOVABLE FAIRING PREVIOUS REPAIR GOUGED ON INNER SURFACE AT FORWARD OUTBOARD AREA. *S/D* REPAIRED FAIRING IAW BOEING 727-200 SRM 57-20-04.

Part: FAIRING — CRACKED (RT WING) · airframe 52,267 hrs · 28,697 cycles

RIGHT WING NR 8 FLAP TRACK MOVABLE FAIRING EXTERNAL SKIN CRACKED AT FORWARD INBOARD EDGE. REPAIRED FAIRING IAW BOEING 727-200 SRM 57-20-04.

Part: SHROUD — DENTED (FUEL SYSTEMS) · airframe 52,267 hrs · 28,697 cycles

FORWARD AUXILARY FUEL TANK SUMP SHROUD HAS DAMAGE. SUMP SHROUD OK FOR SERVICE IAW FED EX EA7-2810-68041.

Part: STIFFENER — GOUGED (LT WING) · airframe 52,267 hrs · 28,697 cycles

LT WING NR 2 FLAP TRACK MOVABLE FAIRING GOUGED ON 2ND FROM FORWARD INTERNAL STIFFENER OUTBOARD EDGE. REMOVED AND REPLACED FORWARD INTERNAL STIFFENER IAW BOEING 727-200 SRM 51-30-02.

Part: FLOOR PANEL — TORN (FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

MAIN CARGO DECK FLOOR PANEL AT BS 950 RBL 45 INBOARD EDGE TORN. *S/D* REPAIRED IAW FED EX BOEING 727 SR 27-51-002.

Part: FAIRING — BROKEN (LT WING) · airframe 52,267 hrs · 28,697 cycles

LEFT WING NR 4 FLAP TRACK FAIRING FORWARD EXTERNAL DOUBLER BROKEN. *S/D* REPAIRED FAIRING IAW BOEING 727-200 SRM 57-20-04.

Part: SKIN — DENTED (FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

RIGHT HAND FUSELAGE STA 277 FORWARD TOILET SERVICE PANEL LOWER SKIN HAS A DENT. REPAIRED IAW FED EX EA 7-5330-69463.

Part: PANEL — DAMAGED (FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

FORWARD CARGO FORWARD BULKHEAD UPPER LEFT PANEL STA 480 HAS A HOLE. INSTALLED DOUBLER AND 1 EA FILLER IAW BOEING 727-200 SRM 53-10-9.

Part: BRACKET — ELONGATED (FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

MAIN CARGO DOOR BRACKET AT STA 480 FOR CORNER REVEAL HAS TWO EACH RIVET HOLES ELONGATED. FABRICATED NEW BRACKET IAW BOEING 727-200 SRM 51-20-01.

Part: RADOME — DAMAGED (FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

RADOME FAILED MOISTURE CHECK. REMOVED AND REPLACED RADOME IAW FED EX M/M 53-15-000-04.

Part: INTERCOSTAL — BENT (LT WING) · airframe 52,267 hrs · 28,697 cycles

INTERCOSTAL BENT ON LEFT WING LOWER SURFACE AT ATTACH POINT FOR WING ACCESS PANEL 12 INCHES INBOARD OF MAIN LANDING GEAR FORWARD TRUNNION.

Part: PANEL — DAMAGED (DOOR LINER) · airframe 52,267 hrs · 28,697 cycles

MAIN CARGO DOOR LOWER PANEL DETERIORATED. *S/D* FABRICATED NEW PANEL IAW FED EX SRZ 25-005C.

Part: PANEL — DAMAGED (FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

MAIN CARGO SIDEWALL PANEL STA 560 TO 748 DETERIORATED.

Part: PANEL — DAMAGED (CARGO DOOR) · airframe 52,267 hrs · 28,697 cycles

MAIN CARGO DOOR UPPER PANEL DETERIORATED. *S/D* FABRICATED NEW PANEL IAW FED EX SRZ 25-005C.

Part: SKIN — GOUGED (NR 3 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 3 ENGINE UPPER NACELLE EXTERIOR SKIN HAS GOUGE NEXT TO NR 1 LATCH. REPAIRED NR 3 ENGINE NACELLE IAW BOEING 727-200 SRM 54-30-03.

Part: RETAINER — CRACKED (DOOR SEAL) · airframe 52,267 hrs · 28,697 cycles

RIGHT FORWARD SERVICE DOOR FUSELAGE FRAME SEAL RETAINER HAS 3 CRACKS AND SEVERAL BENT AREAS FORWARD AND AFT SIDES. REPAIRED SEAL RETAINER IAW BOEING 727-200 SRM 51-40-03.

Part: PANEL — CRACKED (RT WING) · airframe 52,267 hrs · 28,697 cycles

RIGHT WING LEADING EDGE ACCESS PANEL AT INBOARD STOP NR 7 SLAT HAS APPROXIMATELY .375 INCH CRACK AT UPPER CORNER OF CUTOUT FOR STOP. INSTALLED DOUBLER REPAIR IAW BOEING 727-200 SRM 57-50-3.

Part: FAIRING — DAMAGED (RT WING) · airframe 52,267 hrs · 28,697 cycles

RIGHT WING NR 5 FLAP TRACK MOVABLE FAIRING LEADING EDGE DAMAGED. *S/D* REMOVED AND REPLACED SKIN IAW BOEING 727-200 SRM 51-20-01.

Part: LONGERON — CRACKED (NR 3 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 3 ENGINE NACELLE INBOARD SKIN CHAFED AND CRACKED. REMOVED AND REPLACED LONGERON IAW BOEING 727-200 SRM 51-30-02.

Part: PANEL — BROKEN (FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

FUSELAGE PANEL 3354 FORWARD INBOARD CORNER BROKEN. *S/D* REPAIRED IAW BOEING 727-200 SRM 51-40-09.

Part: COVER — DELAMINATED (NLG VAVLE) · airframe 52,267 hrs · 28,697 cycles

NOSE LANDING GEAR METERING VALVE COVER HAS DELAMINATION ON UPPER SURFACE. REPAIRED NOSE LANDING METERING VALUE COVER IAW BOEING CMM 25-00-67.

Part: SKIN — DAMAGED (NR 1 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 1 ENGINE UPPER NACELLE EXTERIOR SKIN HAS A NICK AT BOTTOM OF AFT PIN LATCH CUTOUT.

Part: WEB — CRACKED (FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

AFT AIRSTAIR AREA AT STA 1223 RIGHT SIDE UPPER LIGHTENING HOLE IS CRACKED IN TAIL COMPARTMENT VERTICAL WEB. REPAIRED CRACK IN LIGHTENING HOLE WEB BY INSTALLING A DOUBLER PLATE IAW BOEING 727-200 SRM 53-10-02.

Part: DOUBLER — LOOSE (LOWER FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

LOWER FUSELAGE JUST FORWARD OF AFT AIRSTAIR LEFT SIDE HAS A LOOSE DOUBLER. *S/D* REMOVED AND REPLACED REPAIR DOUBLER IAW BOEING 727 SRM 53-30-3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 52,267 hrs · 28,697 cycles

RIGHT FLOOR SUPPORT BETWEEN STA 720 AND STA 720D HAS NUMEROUS ARES OF CORROSION. *S/D* REMOVED AND REPLACED FLOOR SUPPORT IAW BOEING 727-200 SRM 51-30-02.

Part: SKIN — CHAFED (NR 2 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 2 ENGINE FORWARD COWLING LOWER AFT CORNER INTERIOR SKIN CHAFED. *S/D* REPAIRED SKIN IAW BOEING 727-200 SRM 54-30-01.

Part: PANEL — CRACKED (PEDAL COVER) · airframe 52,267 hrs · 28,697 cycles

THE COVER PANEL OVER THE CAPTAINS RT RUDDER PEDAL IS CRACKED. REPAIRED COVER PANEL IAW BOEING CMM 25-00-67.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 52,267 hrs · 28,697 cycles

AFT CARGO PIT FLOOR PANEL STA 960E TO 990 HAS GILLINER PATCH WITH HOLE PUNCTURED THROUGH. *S/D* REPAIRED FLOOR PANEL IAW BOEING SRM 727-200 53-10-07.

Part: PANEL — CRACKED (FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

CABIN BS 1176.9 LEFT SIDE GILLINER CLOSE OUT CRACKED. REPAIRED CLOSEOUT IAW FED EX SRZ 25-016A.

Part: PANEL — TORN (CARGO BAY) · airframe 52,267 hrs · 28,697 cycles

MAIN CABIN STA 400 LEFT SIDEWALL PANEL IS TORN IN UPPER AREA.

Part: SKIN — DAMAGED (NR 3 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 3 ENGINE UPPER COWLING LOWER EDGE SKIN SEPARATED, BENT AND CHAFED AT NR 3 FRAME.

Part: DUCT — CRACKED (AIR CONDITIONING) · airframe 52,267 hrs · 28,697 cycles

OVERHEAD CABIN AIR CONDITIONING DUCT STA 450 TO 670 HAS NUMEROUS AREAS OF DELAMINATION AND CRACKING. *S/D* REPAIRED OVERHEAD A/C DUCT IAW BOEING CMM 25-00-67.

Part: RETAINER — CRACKED (FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

MAIN CARGO DOOR FUSELAGE FRAME SEAL RETAINER HAS A CRACK AT UPPER AFT SIDE. *S/D* INSTALLED DOUBLER IAW BOEING 727-200 SRM 51-40-3.

Part: FAIRING — LOOSE (TE FLAP) · airframe 52,267 hrs · 28,697 cycles

RIGHT OUTBOARD MIDFLAP INBOARD JACKSCREW FAIRING HAS A LOOSE SKIN AND DOUBLER ON SIDE. *S/D* RE-ATTACHED LOOSE DOUBLER WITH 2 EA RIVETS THAT WHERE LOOSE IAW BOEING SRM 51-30-02.

Part: SKIN — DAMAGED (NR 1 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 1 ENGINE UPPER NACELLE FORWARD UPPER CORNER SKIN SEPARATED. REMOVED AND REPLACED REPAIR DOUBLER IAW BOEING 727 SRM 51-30-2.

Part: FLOOR PANEL — MISSING (CABIN) · airframe 52,267 hrs · 28,697 cycles

FORWARD AUXILARY FUEL TANK FLOOR ACCESS PANEL AT STA 720E RIGHT SIDE HAS AREAS OF FILLING COMPOUND MISSING ON 3 OF 4 EDGES. *S/D* REPAIRED FLOORBOARD ACCESS PANEL IAW FED EX SRZ 25-005C.

Part: FRAME — GOUGED (NR 3 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 3 ENGINE NACELLE HAS A GOUGE AT FRAME NR 7. REPAIRED COWLING FRAME IAW BOEING 727 SRM 54-10-2 FIGURE 5.

Part: SKIN — DENTED (RT WING) · airframe 52,267 hrs · 28,697 cycles

RIGHT WING LEADING EDGE HAS A DENT ABOUT 6 FEET OUTBOARD OF THE FUSELAGE.

Part: FRAME — CHAFED (NR 3 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 3 ENGINE UPPER COWLING NR 5 UPPER LATCH FRAME STIFFENER HAS CHAFING CONDITION.

Part: STRUCTURE — TORN (AILERON TAB) · airframe 52,267 hrs · 28,697 cycles

LEFT WING AILERON TRIM TAB INBOARD UPPER SURFACE DISBONDED AND TORN ON HONEYCOMB MATERIAL.

Part: SKIN — DAMAGED (NR 2 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 2 ENGINE RIGHT AFT NACELLE SKIN LOWER AFT CORNER BENT AND CHAFED. *S/D* REPAIRED BENT CORNER AND CHAFED EDGE IAW BOEING 727-200 SRM 54-10-03.

Part: FLOOR PANEL — DAMAGED (LOWER CARGO) · airframe 52,267 hrs · 28,697 cycles

A .75 X 3.5 INCH HOLE IN FLOOR OF AFT LOWER CARGO COMPARTMENT STATION 1020.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

AFT CARGO PIT STA 1030 TO 1070 FORWARD CENTER FLOOR PANEL HAS SEVERAL GOUGES AND A PREVIOUS REPAIR.

Part: SKIN — DENTED (NR 3 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 3 ENGINE UPPER NACELLE EXTERIOR SKIN HAS 1 DENT APPROXIMATELY 24 INCHES FROM AFT EDGE. INSTALLED FLUSH REPAIR IAW BOEING 727 SRM 54-30-2.

Part: PANEL — CRACKED (COVER PANEL) · airframe 52,267 hrs · 28,697 cycles

BENEATH CIRCUIT BREAKER PANEL FLIGHT CONTROL, APU, HYDRAULIC SYSTEM COVER PANEL IS CRACKED. *S/D* REPAIRED CIRCUIT BREAKER PANEL IAW BOEING CMM 25-00-61.

Part: FRAME — CRACKED (NR 1 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 1 ENGINE UPPER NACELLE SKIN HAS CRACK FORWARD OF PIN LATCH CUTOUT AREA. REMOVED, FABRICATED AND INSTALLED ANGLE IAW BOEING 727 SRM 51-30-2.

Part: STRINGER — CRACKED · airframe 52,267 hrs · 28,697 cycles

FORWARD CARGO PIT HAS 1 INCH CRACK AT BS 520 STRINGER 27R . *S/D* REPAIRED IAW BOEING 727-200 SRM 51-40-3.

Part: DOUBLER — LOOSE (FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

LOWER FUSELAGE JUST FORWARD OF AIRSTAIR RIGHT SIDE HAS LOOSE DOUBLER. *S/D* FABRICATED REPLACEMENT DOUBLER IAW BOEING 727 SRM 51-51-2 AND 51-30-2 AND 51-20-1.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

AFT CARGO PIT AT STA 960E TO 990 FORWARD FLOOR PANEL HAS A HOLE.

Part: BULKHEAD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 52,267 hrs · 28,697 cycles

FORWARD CARGO PIT RIGHT AFT BULKHEAD ANGLE HAS NUMEROUS AREAS OF CORROSION. *S/D* REPAIRED RT FWD CARGO PIT BULKHEAD ANGLE IAW B727-200 SRM 51-40-03.

Part: STRUCTURE — DEBONDED (AILERON TAB) · airframe 52,267 hrs · 28,697 cycles

LEFT OUTBOARD AILERON TAB I/B AFT CORNER DISBONDED.

Part: SKIN — DENTED (NR 3 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 3 ENGINE LOWER COWLING EXTERIOR SKIN FORWARD MID AND AFT HAS 7 DENTS.

Part: SKIN — CRACKED (NR 2 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 2 ENGINE LEFT AFT NACELLE LOWER FORWARD CORNER SKIN HAS A CRACK AND CHAFING. REPAIRED NR 2 ENGINE COWLING FWD LOWER CORNER IAW BOEING 727-200 SRM 54-10-03.

Part: STRUCTURE — BENT (NR 2 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 2 ENGINE RIGHT FORWARD COWLING RAIN GUTTER BENT. REPAIRED NR 2 ENGINE RIGHT HAND COWLING RAIN GUTTER IAW BOEING 727-200 SRM 51-40-01.

Part: FRAME — CHAFED (NR 3 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 3 ENGINE COWLING FRAME NR 5 HAS A HOLE AND CHAFING CONDITION.

Part: SKIN — CHAFED (NR 3 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 3 ENGINE LOWER COWLING UPPER FRAME NEXT TO OIL TANK ACCESS DOOR HINGE HAS CHAFING CONDITION.

Part: BULKHEAD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 52,267 hrs · 28,697 cycles

FORWARD CARGO PIT AFT BULKHEAD LEFT LOWER ANGLE HAS NUMEROUS AREAS OF CORROSION. *S/D* REPAIRED LT BOTTOM FWD CARGO PIT AFT BULKHEAD ANGLE IAW BOEING 727-200 SRM 51-40-03.

Part: COVER — GOUGED (LT WING) · airframe 52,267 hrs · 28,697 cycles

LEFT WING INBOARD FORE FLAP UPPER SURFACE GOUGED UNDER NR 2 GROUND SPOILER. REMOVED AND REPLACED COVER PLATE IAW BOEING 727-200 SRM 51-30-02.

Part: FRAME — CRACKED (ZONE 100) · airframe 52,267 hrs · 28,697 cycles

CRACK AT LIGHTENING HOLE IN HORIZONTAL FRAME AT BS 1183 RBL 44 WL 194.0. FABRICATED AND INSTALLED FRAME SECTION IAW BOEING 727-200 SRM 51-30-2 PG 2 AND 3 ITEM B AND 51-30-2 PG 8 ITEM D.

Part: SKIN — CRACKED (NR 3 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 3 ENGINE NACELLE INBOARD SKIN CHAFED AND CRACKED 1 INCH LONG. *S/D* REMOVED AND REPLACED DAMAGED LONGERON IAW BOEING 727-200 51-30-02.

Part: SKIN — CHAFED (NR 3 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 3 ENGINE NACELLE SKIN CHAFED AROUND NR 4 INBOARD LATCH. *S/D* REPAIRED SKIN AT NR 4 LATCH IAW BOEING 727-200 SRM 54-10-03.

Part: STIFFENER — GOUGED (LT WING) · airframe 52,267 hrs · 28,697 cycles

LEFT WING NR 3 FLAP TRACK MOVEABLE FAIRING I/B FORWARD INTERNAL STIFFENER GOUGED. *S/D* REMOVED AND REPLACED RIB STIFFENER IAW BOEING 727-200 SRM 57-20-03.

Part: SKIN — DENTED (FUSELAGE) · airframe 52,267 hrs · 28,697 cycles

RIGHT FUSELAGE STA 277 FORWARD TOILET SERVICE PANEL SKIN HAS DEEP DENT. REPAIRED IAW FEDEX EA 5330-69463

Part: SKIN — GOUGED (NR 3 NACELLE) · airframe 52,267 hrs · 28,697 cycles

NR 3 ENGINE UPPER NACELLE EXTERIOR SKIN GOUGED NEXT TO NR 1 LATCH. *S/D* REPAIRED NR 3 ENGINE NACELLE IAW BOEING 727-200 SRM 54-30-03.

Part: BULKHEAD — CRACKED (ZONE 100) · airframe 52,267 hrs · 28,697 cycles

CRACKS IN RIGHT WHEEL WELL, 870 BULKHEAD SKIN WEB. REPAIRED CRACK IAW FEDEX EA 7-5310-69465

Part: BULKHEAD — CRACKED (ZONE 100) · airframe 52,267 hrs · 28,697 cycles

CRACK IN LEFT WHEEL WELL STATION 870 BULKHEAD SKIN WEB. ** S/D ** REPAIRED CRACK IAW FEDEX EA 7-5310-69465

Part: SMOKE DETECTOR — FAILED (MAIN CARGO #6)

02-57 MAIN CARGO SMOKE ALARM WENT ON. WENT OUT UPON EXECUTION PROC. OCCURRED WHEN ENG ANTI-ICE SECURED. RAN ALL THREE ENGINES PER JRH. NO DEFECTS NOTED. R&R #6 SMOKE DETECTOR PRECAUTIONARY.

Part: SMOKE DETECTOR — INOPERATIVE

1-398 IN CLBOUT #6 MAIN CARGO SMOKE DETECTOR LIGHT CAME ON. R&R #6 SMOKE DETECTOR PER MM 26-16-011-4.

Part: SMOKE DETECTOR — MALFUNCTIONED (CARGO BAY)

ON CLIMB WITH WING ANTI-ICE ON MAIN CARGO SMOKE DETECTION SYS DETECT SMOKE IN THE NR 6 POS. Removed and replaced NR 6 CARGO SMOKE DETECTOR PER MM 26-16-001-4. OPS CHECK GOOD.

Part: STIFFENER — CORRODED (FUSELAGE)

CORROSION ON FWD RT CORNER OF NOSE WHEEL WELL STIFFENER BS 227, WL 165, RBL 20. *S/D* REPAIRED PER FEDEX SRM 51-40-4.

Part: FLOORBEAM — CORRODED (FUSELAGE)

CORROSION ON LWR CHORD OF FLOORBEAM AT BS 1070, RBL 25 AT NUT PLATES. *S/D* REMOVED AND REPLACED PER IAW FEDEX SRM 51-10-6, 53-10-8 FIG 2.

Part: FLOORBEAM — CORRODED (FUSELAGE)

CORROSION ON LWR CHORD OF FLOORBEAM BS 1010, LBL 12-15 AROUND NUT PLATE HOLES. *S/D* REMOVED AND REPLACED PER FEDEX SRM 53-10-8 FIG 8.

Part: BEAM — CORRODED (FUSELAGE)

FOUND CORROSION ON I-BEAM AT BS 1182, RBL 25, WL 204. *S/D* OUT OF LIMITS PER FEDEX SRM 53-10-1. REMOVED AND REPLACED PER FEDEX SRM 51-30-2.

Part: FLOORBEAM — CORRODED (FUSELAGE)

CORROSION ON FLOORBEAM AT BS 328, LBL 30-45, WL 208. *S/D* REMOVED AND REPLACED PER IAW FEDEX SRM 53-10-8.

Part: SPAR — CHAFED (VERTICAL STAB)

VERTICAL STAB MIDSPAR CHORD (STR 7) IS CHAFED, LT SIDE 3 INCHES FROM FRONT OF SLIDE SEAL FRONT TRACK. *S/D* REPAIRED AREA PER FEDEX SR 27-55-008.

Part: WEB — CORRODED (FUSELAGE)

CORROSION (C53-132-01, -1) BS 850, WL 162, LBL 10. *S/D* REMOVED AND REPLACED PER FEDEX SRM 51-10-2, 51-30-2 AND 51-30-5. ALODINED, PRIMED AND PAINTED PER FEDEX PER MM 51-21-152.

Part: FRAME — DENTED (FUSELAGE)

FRAME DENTED AND GOUGED AT BS 520, STR 22 LT - 25 LT. *S/D* REMOVED AND REPLACED PER FED-EX 51-40-3, 51-30-2. ALODINED AND PRIMED ANGLE PER FEDEX MM 51-20-151.

Part: SKIN — CORRODED (FUSELAGE)

CORROSION (C53-111-01, 2) ON SKIN UNDER LEVELING COMPOUND BS 684 O/B OF STR 27R. *S/D* REMOVED AND REPLACED PER IAW FEDEX SRM 53-30-3 FIG 3.

Part: FRAME — DAMAGED (BS 720E)

NR N 934 DRILL START IN FRAME BS 720E, STR 7LH. ** S/D ** R&R & FAB & ALODINED & PRIMED PER FEDEX SRM 53-10-4 FIG 2.

Part: FRAME — DENTED (FUSELAGE)

FRAME DENTED AT BS 680 BETWEEN STR 23 LT AND 24 LT. *S/D* REMOVED AND REPLACED PER FED-EX SRM 51-40-3 FIG 1.

Part: FRAME — DENTED (FUSELAGE)

DENT ON THE FRAME BS 1090, STR 26L. *S/D* REMOVED AND REPLACED PER IAW FEDEX SRM 51-40-3.

Part: FRAME — DENTED (FUSELAGE)

FRAME 520 DENTED AT RBL 67, WL 212. REMOVED AND REPLACED PER FEDEX SRM 51-40-3.

Part: SKIN — DAMAGED (FUSELAGE)

A TEMPORARY REPAIR IS INSTALLED ON FUSELAGE AT BS 216, STR 17R. *S/D* REMOVED AND REPLACED PER FEDEX SRM 53-30-3 FIG 5.

Part: FRAME — DENTED (FUSELAGE)

FRAME DENTED AT 500, STR 22 LT, STR 25 LT. *S/D* REMOVED, REPLACED AND FAB PER FEDEX SRM 51-40-3.

Part: FRAME — DENTED (FUSELAGE)

BS 600 FRAME DENTED STR 22 LT - 23 LT. *S/D* REMOVED AND REPLACED PER FEDEX SRM 51-40-3.

Part: FLOORBEAM — CORRODED (FUSELAGE)

CORROSION (C53-224-04) AT FASTENER HOLES IN FLOORBEAM BS 1130, RBL 36-42 AND BL 0 - LBL 25, WL 201. *S/D* REPAIRED PER FEDEX EA 7-5310-56290.

Part: FRAME — CRACKED (FUSELAGE)

FRAME IS CRACKED AT CEILING SUPPORT CHANNEL ATTACH POINT BS 1070, RBL 33.5, WL 294. *S/D* REMOVED AND REPLACED PER FEDEX SRM 53-10-4 FIG 2 & EA 7-5310-56293.

Part: FLOORBEAM — CORRODED (FUSELAGE)

CORROSION ON 720A FLOORBEAM UPPER SURFACE OF UPPER FLANGE AT RBL 5 & 11. *S/D* REMOVED AND REPLACED PER SRM 51-10-1 FIG 4, 53-10-8 FIG 3 AND EA 7-5310-56300.

Part: FRAME — CRACKED (FUSELAGE)

FRAME IS CRACKED AT CEILING SUPPORT MOUNTING POINT BS 1030, RBL 33.5, WL 294. * S/D * FAB & R&R PER IAW FEDEX SRM 53-10-4 FIG 2 AND FEDEX EA 7-5310-56296.

Part: FRAME — CRACKED (FUSELAGE)

FRAME IS CRACKED AT CEILING SUPPORT BS 1030, LBL 33.5, WL 294. * S/D * CUT OUT CRACK AND REPAIRED PER IAW FEDEX EA 7-5310-56295.

Part: FRAME — DENTED (FUSELAGE)

FRAME 500 DENTED RBL 67, WL 212. *S/D* REMOVED AND REPLACED PER FEDEX SRM 51-40-3.

Part: SHEAR TIE — CORRODED (FUSELAGE)

CORROSION (SPEC C53-111-01,3) ON FRAME SHEAR TIE BS AT BS 950D BETWEEN STR 29L AND STR 28L. *S/D* REMOVED AND REPLACED PER FEDEX SRM 53-10-1 FIG 1, 53-10-4 FIG 15.

Part: FRAME — CRACKED (FUSELAGE)

FRAME IS CRACKED AT CEILING SUPPORT MOUNTING POINT BS 990, WL 294, RBL 33.5. *S/D* REMOVED AND REPLACED PER FEDEX EA 7-5310-56291 AND SRM 53-10-4, FIG 2.

Part: SUPPORT — CRACKED (FUSELAGE)

CEILING SUPPORT IS CRACKED FRAME HAS A DOUBLE HOLE AT BS 1130, WL 294. *S/D* REPAIRED PER FEDEX SRM 51-20-1, 51-40-3 FIG 1 AND EA 7-5310-56294.

Part: FLOORBEAM — CORRODED (FUSELAGE)

FWD LOWER FLANGE OF FLOORBEAM BS 1010 CORRODED BEYOND LIMITS. *S/D* REMOVED, REPLACED AND FAB PER IAW FEDEX SRM 53-10-8.

Part: WIRE — BROKEN (VERTICAL GYRO)

RADAR STILL INOP. FOUND BROKEN WIRE BETWEEN F11 AT RT TO R68 U ON VERTICAL GYRO CONNECTOR D669. REMOVED AND REPLACED WIRE ACCORDANCE WITH BOEING WIRE STANDARD CHAPTER 20. OPS CK OK.

Part: ACCESS DOOR — MISSING (HYD SERVICE BAY)

HYDRAULIC ACCESS DOOR MISSING. *S/D* INSTALLED HYD DOOR PER STANDARD MAINTENANCE PRACTICES.

Part: FIRE CONTROL — INOP (LWR AFT BODY)

99-236 - DURING CLIMB, LWR AFT BODY OVHT LIGHT ILLUMINATED NR 2 AND 3 BLEED AIR OPEN, NR 1 CLOSED. REMOVED AND REPLACED OVERHEAT AND FIRE DETECTOR CONTROL BOX. OPER CK SYSTEM PER MM 26-14-011. AC OK FOR SERVICE.

Part: VALVE — FAILED (LT PACK)

LWR AFT BODY OVERHEAT LIGHT CAME ON DURING CLIMBOUT. PERFORMED RED TABS AND ISOLATED TO BE LEAK BETWEEN NR 1 BLD VALVE AND LT PACK VALVE.

Part: ENGINE — FAILED (NR 2)

99-214 - OIL TEMP NR 2 ENG, 110 DEG C, PRESS 52. NR 1 AND NR 3 OIL TEMP 95 DEG C, PRESS 45. SHUT DOWN NR 2 ENG FOR PRECAUTION. REMOVED AND REPLACED NR 2 ENG FUEL HEAT SHUT OFF VALVE ASSY PER MM 73-14-11, AND FUEL OIL COOLER PER MM 79-20-01. OPER CK GOOD.

Part: COMPRESSOR — STALLING (NR 2 ENGINE)

AFT NORM T/O NR 2 ENG STARTED COMPRESSOR STALLING. THE ENGINES WERE AT CLIMB PWR WITH 150 EG'S FLAPS. *S/D* REMOVED AND REPLACED NR 2 ENG PER W/C 70T0002. RAN ENG PER JRH. ALL PARAMETERS NORMAL.

Part: SMOKE DETECTOR — MALFUNCTIONED (E & E COMPT)

99-0045, MAIN CARGO SMOKE IND LIGHT CAME ON FOR ZONE NR 6 FOR 30 SEC. REMOVED AND REPLACED DETECTOR NR 6 PER 727-200 MM 26-16-011-4. OPER CK GOOD.

Part: OVERHEAT LIGHT — MALFUNCTIONED (LWR AFT BODY)

CLIMBING THRU 16,000 LWR AFT BODY OVERHEAT LIGHT CAME ON. CLOSED NR 1 BLD AND LT PACK, WENT TO IDLE PWR ON NR 1 ENG. RAN BOTH PACK WITH APU AND WITH NR 1 AND 3 ENG, COULDN'T DUP. CK TEMP GUN FOR HOT SPOT, NONE FOUND. LEAK CHK GOOD AT HIGH POWER CW (144405).

Part: SWITCH — FAILED (LANDING GEAR)

98-19 - GEAR WARNING HORN (STEADY) AFTER GEAR RETRACTION WITH FLAP AT 15 AND WENT OUT WITH GEAR DOWN. REMOVED AND REPLACED AND ADJUST FLAP LAND WARN SWITCH PER M/M 31--26-12, WIR DIAG MANUAL 32-64-03. REMOVED AND REPLACED LAND GEAR ACC PER M/M 32-09-121. TEST NORM.

Part: SWITCH — OUT OF ADJUST (TAIL SKID)

TAIL SKID LIGHT ILLUMINATES WHEN GEAR IS PLACED TO DOWN AND LOCKED POSITION IN THE AIR. GEAR WAS RECYCLED AND LIGHT REMAINS ON. ADJUSTED AND CLEANED THE TAIL SKID WARNING LIGHT SWITCH, (DOWN LOCK), PER MAINTENANCE MANUAL 32-71-01. GROUND CHECK OK.

Part: RETRACT MECH — MALFUNCTIONED (NR 4 LE FLAP)

AFTER T/O, NR 4 L/E FLAP WOULD SHOW INTRANSIT, AMBER LIGHT ON SECOND OFFICER'S PANEL. COMPLIED WITH L/E DEVICE MALFUNCTION DURING FLAP RETRACTION A. NR 4 L/E FLAP W/N RETRACT, RETURNED TO MIA. REMOVED JUMPER FROM NR 4 L/E FLAP SWITCH AND RECONNECTED SWITCH. FUNCTION CHECKED TEST LEADING FLAPS PER MM 27-81-0 PAGE 512. BOTH FWD AND SECOND OFFICER'S PANEL AND L/E FLAPS NORMAL. WORK RELEASE ITEM NR 27-80/1079, CLEARED MOCC NOTIFIED.

Part: POS IND SWITCH — MALFUNCTION (NR 4 FLAP)

L/E DEVICE MALFUNCTION ON FLAP RETRACTION. WHEN FLAPS MOVED TO 2 DEGREE YELLOW L/E FLAP LIGHT IS ON AND 2, 3, 6, 7 AND 4 POSITION TEST LIGHTS ARE GREEN. REPLACED NR 4 FLAP POSITION INDICATING SWITCH IAW MM 27-82-11, OPS CK GOOD.